BOLETINES TURBOCOMMANDER
Transcript of BOLETINES TURBOCOMMANDER
ATPINDEX
COPYRIGHT 2004
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PUBLISHER.
b~cL Aircraft Technical Publishers Customer Service
P~i"lOl South Hill Drive 6AM-5PM PST M-F
Brisbane, CA 94005 (800)227-4610
ATP Grid Index to Manufacturer’s Publications:
Twi n Commander A/C
695, 695A, 695B
SERVICE INFORMATION
Issue Type Eye-Readable Code
SERVICE BULLETIN SE
SERVICE LETTER SL
SERVICE INFORMATION SF
SERVICE ALERT SRA
CUSTOM KIT CK
AD’S ADs
End of Index
04/04/2002 Copyright Aircraft Technical Publishers Page 1 of 1
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SB
Aircraft Technical Publishers Customer Service
101 South Hill Drive 6AM-5PM PST M-F
Brisbane, CA 94005 (800)227-4610
ATP Grid Index to Manufacturer’s Publications:
Twi n Commander A/C
695, 695A, 695B
SERVICE BULLETIN
1) Applicable AD
2) Part Kit (1)
Issue Number 3) Part Kit (2)
Issue Date Issue Description 4) Compliance Time
171 UNFEATHERING PUMP SUPPLY 1)
04/08/1980 HOSE REPLACEMENT 2) SEE ISSUE
3)
4) SEE ISSUE
172 FUEL VENT SYSTEM INSPECTION 1)
05/19/1980 2)
3)
4)
175 R1 OIL FILTER ADAPTER REPLACEMENT 1)
08/06/1980 AND ENGINE MOUNT RETAINER 2)SEE ISSUE
MODIFICATION 3)
4) SEE ISSUE
176 MAIN CABIN DOOR BAYONET 1) 89-18-08
08/22/1980 RIGGING CHECK 2) SEE ISSUE
3)
4) W/IN 25 HRS
177 MAIN LANDING GEAR STRUT HOOK 1)
09/26/1980 INSTALLATION 2)SEE ISSUE
3)
4)SEE ISSUE
178A R1 AILERON ACCESS DOOR INSPECTION 1)
03/16/1981 AND REPLACEMENT 2)SEE ISSUE
3)
4)SEE ISSUE
01/20/2004 Copyright Aircraft Technical Publishers Page 1 of 7
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1) Applicable AD
2) Part Kit (1)
Issue Number 3) Part Kit (2)
Issue Date Issue Description 4) Compliance Time
180 INSPECTION OF SIDE WINDOW 1)
01/08/1981 HEATER INSTALLATION 2)SEE ISSUE
3)
4)SEE ISSUE
1818 INSTALLATION OF FAIRLEADS ON 1)
07/15/1981 AFT FUSELAGE FRAMES 2)SEE ISSUE
3)
4) SEE ISSUE
183 EXHAUST PIPE SEAL REPLACEMENT 1)
07/07/1981 2)SEE ISSUE
3)
4)SEE ISSUE
184 MAIN CABIN DOOR FASTENER 1)
06/10/1981 INSPECTION 2)SEE ISSUE
3)
4)SEE ISSUE
185 CABIN CHIMES INSPECTION AND 1)
08/28/1981 MOC I FICATION 2)SEE ISSUE
3)
4) SEE ISSUE
186 TRIM TAB FREE PLAY MEASUREMENT 1)
12/23/1981 2)SEE ISSUE
3)
4)SEE ISSUE
187 ANTENNA INSPECTION AND 1)
02/05/1982 MODIFICATION 2)
3)
4)SEE ISSUE
188 R1 SECURING ENGINE CONTROL CABLES 1)
02/22/1982 2)SEE ISSUE
3)
4)SEE ISSUE
01/20/2004 Copyright Aircraft Technical Publishers Page 2 of 7
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1) Applicable AD
2) Part Kit (1)
Issue Number 3) Part Kit (2)
Issue Date Issue Description 4) Compliance Time
189 APPLICATION OF ABRASION 1)
03/12/1982 RESISTANT TAPE ON DOWTY-ROTOL 2)SEE ISSUE
PROPELLER 3)
4)SEE ISSUE
190A EXHAUST PIPE INSPECTION AND 1)
09/22/1982 MODIFICATION 2)SEE ISSUE
3)
4)SEE ISSUE
191A R1 NOSE LANDING GEAR CENTERING 1)
12/14/1984 CAM AND/OR CENTERING PIN 2)SEE ISSUE
REPLACEMENT 3)
4)SEE ISSUE
193 PASSENGER OXYGEN DISPENSER 1)
10/29/1982 MODIFICATION 2)SEE ISSUE
3)
4)SEE ISSUE
194A EXTENDED PROPELLER DEICER 1)
03/23/1983 BOOTS 2) SEE ISSUE
3)
4)SEE ISSUE
1958 RUDDER CONTROL CABLE 1)
08/26/1985 INSPECTION AND/OR REPLACEMENT 2)
3)
4) 25 HRS
196 FUEL LEAK INSPECTION AND WING 1)
06/15/1983 COMPARTMENT SEALING BETWEEN 2)
WING STATION 103.0 AND 113.0 3)
4) SEE ISSUE
197 MODIFICATION OF PITOT TUBE 1)
09/09/1983 ASSEMBLY INSTALLATION 2)
3)
4)SEE ISSUE
01/20/2004 Copyright Aircraft Technical Publishers Page 3 of 7
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1) Applicable AD
2) Part Kit (1)
Issue Number 3) Part Kit (2)
Issue Date Issue Description 4) Compliance Time
198A R1 ELEVATOR TRIM TAB INSPECTION 1)
06/05/1987 AND MODIFICATION 2) SEE ISSUE
3)
4)SEE ISSUE
200 MODIFICATION OF NOSE GEAR 1)
03/28/1984 STEERING COMMAND POTENTIOMETER 2)SEE ISSUE
INSTALLATION 3)
4) 25 HRS
201 ENGINE ISOLATOR ASSEMBLY 1)84-19-05
05/11/1984 INSPECTION AND/OR REPLACEMENT 2)
3)
4)SEE ISSUE
202 NOSE GEAR STEERING COMMAND 1)
08/15/1984 POTENTIOMETER ALIGNMENT 2)
3)
$)SEE ISSUE
203 INSPECTION AND REPLACEMENT OF 1)
02/08/1985 COLLINS AP-106 AND AP-107 2)SEE ISSUE
AUTOPILOT CAPSTAN ASSEMBLIES 3)
4) SEE ISSUE
204 INSPECTION AND REPLACEMENT OF 1)
02/08/1985 COLLINS APS-65 AUTOPILOT 2) SEE ISSUE
CAPSTAN ASSEMBLIES 3)
4) SEE ISSUE
205 VA PLACARD INSTALLATION 1)
12 /20 /1985 2) 860783 689
3)
4)SEE ISSUE
206 INSPECTION OF EMPENNAGE 1)
08/17/1987 A~TACH AREA AT FUSELAGE 2)
STATION 409.56 3)
4)SEE ISSUE
01/20/2004 Copyright Aircraft Technical Publishers Page 4 of 7
GC 0853 SI SE
1) Applicable AD
2) Part Kit (1)
Issue Number 3) Part Kit (2)
Issue Date Issue Description 4) Compliance Time
207A INSPECTION AND/OR REPLACEMENT 1)
08/16/1988 OF DEVORE TEL-TAIL LOGO/ 2)SEE ISSUE
RECOGNITION LIGHT BULBS 3)
4)SEE ISSUE
209 INSPECTION AND/OR REPLACEMENT 1)
11/15/1990 OF NOSE LANDING GEAR AXLE 2) P/N 9545
3)
4)SEE ISSUE
210 REPLACEMENT OF FLAP MASTER 1)
02/01/1991 PULLEY AND CABLE WITH 2)
INSPECTION OF REMAINING FLAP 3)
SYSTEM 4) MANDATORY
213 WING FATIGUE INSPECTION AND 1)95-12-23
07/29/1994 MODIFICATION 2) SB213-1
3) SB213-2
4) MANDATORY
214 Thorough examination of the 1) 2003-07-03
03/01/2000 pressurized cabin structure 2)
(the cockpit, passenger cabin 3)
and the inboard portion,contd. 4) None Found
214 R1 Wing and fuselage fatigue 1) 2003-07-03
04/19/2000 inspection and modification 2) See Issue
3)
4) None Found
214 R2 Wing and fuselage fatigue 1) 2003- 07-03
05/21/2001 inspection and modification 2)
3)
4)See Issue
216 FUELING PLACARD AND FLIGHT 1)
06/09/1992 MANUAL ADDENDUM 2) SB216-1
3) SB216-2
4)SEE ISSUE
01/20/2004 Copyright Aircraft Technical Publishers Page 5 of 7
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1) Applicable AD
2) Part Kit (1)
Issue Number 3) Part Kit (2)
Issue Date Issue Description 4) Compliance Time
218 R2 EMPENNAGE-VERTICAL STABILIZER 1)95-13-02
09/23/1994 INSPECTION AND MODIFICATION 2)SEE ISSUE
3)
4) MANDATORY
218 R2 EMPENNAGE-VERTICAL STABILIZER 1) 95-13-02
09/23/1994 INSPECTION AND MODIFICATION 2)SEE ISSUE
3)
4) MANDATORY
220 MANDATORY REDUCTION IN SPEED 1) 95-19-18
02/01/1995 DURING TURBULENCE 2)SEE ISSUE
3)
4) MANDATORY
223 R2 WING LEADING EDGE A~TACHMENT 1)98-08-19
08/18/1997 INSPECTION AND MODIFICATION 2)SEE ISSUE
3)
4)SEE ISSUE
224 RC REPLACEMENT OF NOSE LANDING 1)98-08-25 R1
07/25/1996 GEAR BOLT 2) ED10055
3)
4) MANDATORY
226 R1 FLAP SYSTEM INSPECTION 1)98-07-17
07/15/1997 2)
3)
4) MANDATORY
227 INSPECTION AND MODIFICTION OF 1)
08/01/1997 LOWER MAIN GEAR SCISSORS 2)
3)
4)SEE ISSUE
228 Nose gear steering pin 1)
01/04/1999 2)See Issue
3)
4) Mandatory
01/20/2004 Copyright Aircraft Technical Publishers Page 6 of 7
GC 0853 SI SE
1) Applicable AD
2) Part Kit (1)
Issue Number 3) Part Kit (2)
Issue Date Issue Description 4) Compliance Time
233 Engine nacelle firewall 1)
10/15/2003 rei nforcement 2) S8233 -1
3)
4) Recommended
235 Upper rudder structural 1)
04/16/2003 inspection 2)
3)
4)See Issue
End of Index
01/20/2004 Copyright Aircraft Technical Publishers Page 7 of 7
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i
IjB RoCkwelllntematlansl
Service Bulletin O´•nNJ Av*tlon Divition
5001 North Roc~well Avenue
Bethlny. OLlahoma 74005
SERVICE BULLETIN NO. 171 j8 April 1980
f UNFEATHERING PUMP SUPPLY HOSE REPLACEMENT
MODELS AFFECTED: MODEL 690C, SERIAL NO’S 11600 THRU 11619, 11621 AND MODEL 695, fSERIAL NO’S 95001 AND 95002.
REASON FOR PUBLICATION: POSSIBILITY OF OIL LINE CHECK VALVE BEING FORCED OUT OF
HORIZONTAL POSITION DUE TO HOSE ASSEMBLY BEING TOO SHORT.
POTENTIAL ALSO EXISTS FOR POSSIBLE HOSE ASSEMBLY FAILURE
BY CONTINUED TIGHT HOSE INSTALLATION AND ENGINE MOTION.
i COMPLIANCE: WITHIN NEXT TWENTY-FIVE (25) HOURS TIME ]N SERVICE.
54075
JF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYING WITH
I THIS SERVICE BULLETIN, CONTACT YOUR NEAREST ROCKWELL
COMMANDER AUTHORIZED SERVICE FACILITY. ff
A P MECHANIC OR EQUIVALENT.BY WHOM WORK WILL BE ACCOMPLISHED:
APPROVAL: ’FAA WA SW-2 Approved.
ESTIMATED MAN HOURS: TWO (2) HOURS. fPARTS DATA: Parts required to comply with this Service Bulletin may be procured through your nearest
Rockwell Commander Authorized Service Facility at no charge. Reference this Service Bulletin, aircraft
model and factory serial number when ordering Service Bulletin No. 171 kit consisting of the following: fDESCRIPTION fQTY PART NO.
2 ea. S- 0421(308-155 Hose Assy fI lea. Compliance Card
lea. Service Bulletin No. 171 Instructions fSPECIAL TOOLS: NONE.
ACCOMPLISHMENT INSTRUCTIONS:
1. Remove lower left cowl door from left and right engines. ff
Remove and discard elristing hose assembly (P/N 5-0421G08-136) that is routed from check valve to Iunfeathering pump inlet port (see Figure i.).
d 3’ Ensure that the check valve is in a horizontal plane with the engine. If check valve is not in a horizontal fplane with the engine, loosen "B" nut, on steel tube assembly, at lower aft end of oil tank, rotate tube f
f assembly until check valve is in a horizontal plane with the engine and then retighten "B" nut.
1 4. Uiarnll 5-0(21MB-lil Mle .sspmb$ rm otleo* ua~ue aM un~P´•ihtnlq ~ump iolrt pml´• Ensur. L~t
check valve is not in a ’pre-loaded" condition when hose assembly is installed and then secure hose fassembly to engine using eldsting clamps and hardware (see Figure 1.).
WOTIE
Push check valve up as high as clamps will allow it to go and still fmaintain a horizontal plane with the engine. Assure 0.05-inch
f clearance between check valve and/or steel tube and the engine fuel
tube(s). ff Page 1 of 2
f
i////////////////////////I////
SERVICE BULLETIN NO. 171
FWDIB~ hlore. PU"" CHECK VALVE UP AS HIGH
AS CLAMPS WILL ALLOW IT TO
GO AND STILL MAINTAIN A
HORIZONTAL PLANE WITH THE
ENGINE. ASSURE 0.03-INCHCLEARANCE BETWEEN CHECK
VALVE AND/OR STEEL TUBE
AND THE ENGINE FUEL TUBE(S).
~;Jl"lg;s
-BCHECK VALVE
i~ (REF)BT~ L-;.a:
g,i 8a
h;ilr ;i~
EXISTING CLAMPS UNFEATHERING PUMPREMOVE EXISTING HOSE
(REF) ASSY AND INSTALLINLET PORT (REF)
S-0421G08-155 HOSE ASSY
figure I.
5. Select Airstart and operate unfeathering pump and check installation for leaks.
6. Reinstall cowl doors on engines.
7. Fill out and mail Compliance Card. ORIGINALELECTRICAL IX)AD: NO CHANCE. As Received By
ATPWEIGHT AND BALANCE: NO CHANGE.
SPARESAFFECTED: NO.
PUBLICATIONS AFFECTED: The Illustrated Parts Catalog change required by this document will be
incorporated at the next scheduled change/revision.
RECORD COMPLIANCE: Make an appropriate entry In the airplane maintenance records as follows:Service Bulletin No. 171, dated 8 April 1980, entitled "Unfeatherrig Pump Supply Hose Replacement",accomplished (date)
Page %ofa
Service Bulletin Roc:kwell
smt N~h l)rm1l *mu
SERVICE BULLETIN NO. 172
18 Mag 1880
FUEL VENT SYSTEM INSPECTION
MODELSAFFECTED: MODEL 880C, SERIAL NO’S 11800 THRU 11618, 11821 THRU 11621 AND
lloae AND MODEL 885, SERIAL NO’S 85000 THRU 89004 AND 86008 THRU
85010.
REASON FOR PUBLICATION: TO ENSURE THAT NO BLOCKAGE M1828 IN FUEL VENT BY6TEM WHICH
COULD CAUSE POSSIBLE STRUCTURAL DAMAGE TO WING.
COMPLIANCE: WITHIN TWENTY-FIVE (25) HOURS TIME IN SERVICE
AFTER RECEIPT OF TH18 SERVICE BULLETIN.
*011
FLIGHT INTO KNOWN 1ChNO CONDITIONS I PROHIBITED PRIOR TO
COMPLIANCE WITH THIS 8ERVICE BVLLETIN.
IF ANY PROBLEMS ARE ENCOU~PERED WHILE COMPLYING WFIH
THIS 8ERVICE BULLETIN, CONTACT YOUR NEAREG~ ROCKWELL
COMMANDER AUTHORIZED SERVICE FACILITY.
BY WHOM WORX:WILL BE ACCOMPL1SHED: A P MECHANIC OR EQUIVALENT.
APPROVAL: FAA DOA SW-a Approved.
EmIMATED MAN HOURS:
PARTS DATA: 1 Be. Compliance Card.
8PECIAL TOOLS: NONE.
ACCOMPLISHMENT INSTRUCTIONS:
i. Remove aft secess door, located above fuel vent scoop, from left and right upper ~uing surface to gain
access to fuel vent check valve.
a. Inspect existing Left and right cheek va~ves (P/W PC?50), located on art side of front spar lust inboard
of W. S. 285. 82, for presence of shipping "cap" on end of valve (see Figure I.).
S. U cap is present, remove and discard.
4. Remove the rubber hose that connects the main vent line to the cheek wive (Pj~ PC750) and check inside
of hose and check valve to there is no obstruction. Clean or clear ang obstruction if necessary.
5. Reinatall hose on check valve and main vent line. Tonpe hose clamps 26 to 90 inch-pounds.
8. Inspect vent system plumbing for security of attachment and en~re that no tube assembly or shipping
caps are LnstaYed on any ports.
7. Reinstall access doors on upper alng surface.
8. Fill out and mall Compliance Card.
page 1 of 2
8ERVEB BULLETIN NO. 112
FWDCOUTED a.l.
sa.ll
U12
n)sOCnlCI LI.
VLLVI IREII 191.11
A A i j
Ii.1 i’ i __Z u~unrm*r
’i
i’Sml.soarl.~OTCIPIID
1U1D *eleae NO
VIEW A-A s~ocr*o.rxllrs
IN nOgEIUELVENT
LEFT INSTALLATION SHOWN
RIGHT INSTALLATION OPPOSITE
ripur´• 1.
ELECTRICAL LOAD: NO CHANCE.
WEIOIfI~ AND BALANCE: NO CHANGE.
8PARES AFFECTED: NO.
PUBLICATIONS AFFECTED: NONE.
RECORD COMPLIANCE: Mere an npproprinte entry in drplsne mointennnce secards as Service
DvUetln No. l?a, dated 19 May 1880,entltleb "FueI Vent 8getem Inspectim’j gccompliahed (dpte)
Page a or a
SERVICE PUBLICATIONS Rockwell international
revision notice a~nl ari´•aon oiri´•im
6m( Norh R~c*ail
SERVICE BULLET1N NO. 115
Revision No. i
BAugust 1980
OIL FILTER ADAPTER REPLACEMENT AND ENGINE MOUNT RETAINER MODIFICATION
APPROVAL: FAA DOA SW-2 Approved.
SUPPLY DATA Page 1 of 1
CHANGE: 5-9413-613 DWng to S-9413-519 ~rlng in all appllcatlona
PART n ACCOMPLISHMENT INSTRUCTIONS:
Page 5 of 1
ADD: l?a. Modify exis~ing left inboard and light outboard engine stde mount
brackets by machilung or filing brackets in area shown in Figure 4.
I.Cl~iUTioN 1CAUTION
DO NOT GRIND brackets as permanent damage to the
beat treat may occur.
NOlr
Bracket must be removed to aooompllsh this work.
ADD: Figure 4. as shown below.
a CLAMP PLATE
r
1.40"~1 MOUNT BRACKETo.lz~yo.sa´•´•
(REF)~I RADIUS
i
MAX o0.03"
MATERIAL MAY BE
REMOVED FROM SHADED
AREA TO PROVIDE
CLEARANCE BETWEEN
CLAMP PLATE AND
MOUNT BRACKETVIEW LOOKING FWD
~ieu,s 4.
Page 1 of i
Service BulletinRockwell intemanonal
r~ Nan Roa*all annu
s´•mm*.o*l´•hom´•l~ce
SERVICE BULLETIN No. 115
21 July 1880
OIL FILTER ADAPTER REPLACEMENT AND ENGINE MOVNT RETAINER MODIFICATION
MODELS AFFECTED: MODEL 690C, SERIAL NO’S 11800 THRU 11830 AND MODEL 895,SERIAL NO’S 85000 THRU 85011.
REASON FOR PUBLICATION: TO PREVENT POSSIBLE CONTACT BETWEEN ENGINE OIL FILTER
ADAPTER AND ENGINE SIDE MOUNT WHICH COULD CAUSE LasS OF
OR DAMAGE TO OIL FILTER RESULTING 1N LOSS OF OIL.
COMPLIANCE: PART I IMMEDIATELY UPON RECEIPT OF THIS SERVICE BULLETIN.
*011
IF UPON INSPECTION OF OIL FILTER ADAPTER, BETWEEN
ENGINE SIDE MOUNT AND OIL FILTER ADAPTER IS EVIDENT, COMPLY
WITH PART n of THIS SERVICE BULLETWNhlMEEDAATEL.
PART n AT NEXT IOO-HOUR INSPECTION OR WITHIN NEXT
50´•HOUR8 TIME IN SERVICE, WHICHEVER OCCURS FIRST.
~OTI
IF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYING WITH THIS
SERVICE BULLETIN, CONTACT YOUR NEAREST ROCKWELL COMMANDER
AUTHORIZED SERVICE FACILITY.
BYWHOMWORK WILL BE ACCOMPLISHED: A P MECHANIC OREPUIVALENT.
APPROVAL: FAA DOA SW-2 Approved.
ESTIMATED MAN HOURS: PART I and PART n EIGHTEEN (18) HOURS TOTAL.
na´•rr
RoLwell InlernaUona~, General Aviation Division, will allow a credit of 18
hours upon receipt of a properly e~eeutsd Warranty Claim and a CompUaneeCard.
PARTS DATA: Parts required to comply with this Service Bulletin may be procured through your nearest
Rockwell Commander AuLorieed Service Facility for )2,211.81. A hll credit will be issued upon receipt of
old adapter P/N 89411?-2, a properly e.eecuted Warranty Claim and a Compliance Card. Reference this
Serdce Bulletin, aircraft model and factory serla~ number when ordering service Bulletin No. 115 hit con-
slstlng of the following:
QTY PART NO. DESCRIPTION
2 ea. 820090-501 Retainer
2 ea. 3102590-1 Adapter2 ea. 3102616-2 Clamp Plate
2 ea. 885014-1 Swivel
2 ea. 8-9413-115 O-Wng2 ea. 5-9419-251 O-Wng
2 ea. 8-9413-813 O-Rlngi a.. Compliance Card
1 ea. Service Bulletin No´• 1?5 Instructions
Fags 1 of?
SERVICE BUiLETIN NO. 115
c~
INSERT A ´•Iv’ 2"
BLOCK HERE
MOUNT RETAINER i
"iIgEE STEP 11)TW ISOLATOR
ASSY IREF)ISEE STEP B
IREFIISEE STEP II
(SEE STEP 121
MOUNT BRACKET IREF)
LEFT INSTALLATION SHOWN
RIGHT IN STALLATION TYPICAL
Pigur´• i.
Pageloi?
SERVICE BULLETIN NO. 115
SPECIAL TOOLS: PROPELLER SLIN(I AND ENO1NE HOISIT
ACCOMPLISHMENT IN8TRUCTION8:
PART I INSPECT OIL FILTERADAPTER
I. Remove upper cowllng from lan and right engines.
2. Inspect oil tilter adapter, located on upper right side of engine, for evidence at possible contaot with
engine side mount. Look Lor scratch mads on adapter and EheoL raised letters on adapter for possible
worn spots.
3. If contact between oil filter adapter and engine side mount is evident, comply with Part 1l of this
Service Bulletin immediately
If no contact is evident between oil filter adapter and engine side mount, comply with Part n of this
Service Bulletin at ned 100-hour inspection or within next ill-hours time in service, whichever occurs
first.
5. Reinstall upper cowllng on engines
a. Fill out and mall Compliance Card specifying that Part I has been accomplished and note the results
of the inspection.
PART n REPLACE OIL FILTER ADAPTER
The following procedures apply to both left and right engines.
I. Remove upper and Lower cowllng from engine.
2. Attach propeller sling to propeller blades and connect sling mi ring to engine hcdst and assure that
engine is Supported by sllllg and hoist.
9. Remove engine torque limiter and torque limiter amMlg to facilitate remova~ of oil filter and oil
biter adapter.
Remove engine plumtdng in area of oil tilter, as necessary, to facilitate removal of oil biter and oil
filter adapter.
Do not damage oil lifer cap, buaN~g, tebon washer and filter Pement
when removing them because they are to be relnstalied on engine
5. Loosen oil tilter cap bushi~ and remove oil tilter cap, bushing and titter element from engine.
B. Remove bolt attaching left and right engine aide mount braoket. to mount isolators (see Figure 1.).
Remove bolt (4 places) attaching engine top mount isolator assembly to top mount (see Figure 1.).
8. Allow the e~ine to move forward and insert a 1-1/2 inch to 2 inch block between e~ine tap mount
and mount retainer. This will teep the engine from moving aft and will allow removal of oil fiber
adapter
Page 3 of if
SIT(VICE LIUiLETIN NO. llJ
’1
a.lo´•´• MIN. n~
CLOSESTPOINT
RUN´•OUT
~00
i~tetR
VIEW IOOKINO *FT A~
LEFT INBD MOUNT OR
RIBHT OUTBO MOUNT
lipur´•
Page 4 oi
SERVICE BULLETIN NO. 115
TOROUE BOLT (4 PLS)3W TO 980 IN´•LBS
WITH THREADS DRY
TOR(IUE BOLT IJ PLSI350 TO 380 IN-LEE
WITH THREADS DRY\
rOROul eOLT
480 TO 600
roROuE BOLT Il4WTOSWIN´•Lss
P~NDSPIFETYWIRE
TOROUE BOLT400 TO Sm IN´•LB9
~ilur´• 3.
8. Raise hoist to allou. lower portion of engine to move forward lust far enough to aYow for removal of
oil filter adapter.
10. Remove oil filter adapter (P/N 884111-2) from engine.
ffoTg
Adapter is to be returned to Rookwell international for credit (see PARTS DATA).
11. Remove bolt (3 places) attaching left inboard and right outboard engine side mount retainers to
engine mount (see Figure 1.).
12. Remove bolt (4 places) attaching left Lnboard and right outboard mount braLets to engine (999 Figure i.).
13. Remove mount bracltets from engine.
14. Remove and discard elds~ing Left inboard and right outboard engine side mount retainers from engine
(see Figure 1.).
15. Chamfer corner on Left inboard and right outboard engine side mounts as shown in Figure 2.
16. Prime reworkea area on engine side mounts with zinc chromate primer.
i?. Install 620090-501 mount retainer on left in~aard and right outbaard engine side mrunta using eidstllg
hardware. Torque bolts 350 to 390 inch-pounds with threads dry (see Figure 3.).
18. Reinstall e~dsting Left inboard and right outboard aids mount braelets on engine using e~eting hardware.
Tor~ue bolts 400 to 500 inch-pounds and safety wire (see Figure 3.).
page 5oL?
SERVICE BULLETW NO. 115
SBd13´•1160´•RIN(i
R:
S´•8~13´•P1
Ilo?ssol
885074´•1 SWIVEL
TOROUE NUT 14 PLS)50 IN-LBS
~1028162 CLAMP PLATE
FLAT SPOT MUST BE
INSTALLIDDOWN
EXISTIN13 TEFLON
W~SHER IREF)
EXISTIN(IOIL FILTER
ELEMENT (R5FL
55018418 O´•RIN(I
EXISTIN(I CPIP IREF)
BUSIIIN(I (R5FL
Agure 4.
PageBof?
SERMCE BULLETIN NO. 11I
is. Install 5-9413-351 O-ri~, 9103080-1 adapter and 3102818-2 clamp plate on engine uslRB
hardware (see Figure 4.) as follows:
a. Lightly coat 5-9419-251 0´•ri~ with an approved clean engine oil.
b. Install 5-8413-231 Drlng on 3102580-1 adopter.
c. Install 3102588-1 adapter and 3102818-2 clamp plate on e~ne using existing hardware. Rotate
adapter, as necessary, to assure that no interference slats between adapter and engine mount.
Torque nuts to 50 inch-pounds (see Figure 4.).
20. Lower hcdst to allow engine to settle bacL into place and remove bloc~, inserted in step 8., from
engine top mount.
21. ReinstaU, eidsting hardware that attaches engine top mount isolator assembly to engine tap mount.
Torque bolts 350 0 380 inch-pounds with threads dry (see Figure 3.).
22. Reinstall eldsting hardware that attaches left and right el\gine side mount brackets to mount Lsolabrs.
Torque bolt 400 to 500 inch-pounds (see Figure S.).
25. Insta~ 5-8413-115 O-rl~g and 8850’14-1 swivel in cdl Biter adapter (see Figure 4.).
24. Install existing teBon washer, oil tilter element and 5-9413-813 ~ring in oil filter adapter (see
Figure 4.).
25. Install els~lng cap over filter element and secure with edstlng bushing. Tighten bushing hand tight
and safety wire (see Figure 4.).
26. Reinstalltems removed in steps 3. and 4.
2?. Remove sling from propeller.
as. Assure there are no lea~a.
29. Reinstzll upper and Lower eowU~g on engines.
SO. Fill out and mail Compliance Card speeifying that Part II has been accomplished.
ELECTRICAL LOAD: NO CHANGE.
WEIGHT AND BALANCE: NO CHANGE.
BPARES AFFECTED: NO.
PUBLICATIONB AFFECTED: The Airplane Maintenance Manua~ and illustrated Parts Cats~ag changes
required by this document will be incorporated at the next sehsm~lad
change/redden.
RECORD COMPLIANCE: Ma~re an appropriate entry in airplane maintenance records as follows: Serdee
Bulletin No. 1?5, dated 21 July 1BBO, entitled "Oil Filte. Adapter Replacement and Engine Mount Retainer
Modification", Part I accomplished (date) Part IL
Page? of?
SEBVICE NO. 118
2. The recommended procedure for inspeett~ bayonet penetration is as lollou,s:
a. With door open and bzyonets in extended position, apply layout inr to bayonets.
b. Retract bayonets by placing handle in open position.
c. Close door and eqage baganets in retaining blalls Mt, handle in loe*ed position.
d. LLghtly scribe a mar*,ln the layout init only, on inboard surface of bayonet along surface of
door lamb as shosn:
WOR WOR
(REF) JAMs
(REFI
1NBD II in INeo) JO~´•RIREF)
RET~ININ(IBLDCI (RIFI
gRIIY
SCRIBE(REF)
AFT BA’IONETS UPPER BIYONRS
e Measure distance from nose of bayonet to scribe line and record for each blyonet´•
WOA IREFI
INBD
INeD
WOR (REF)
SCRIBE
L~NE
SCRIILLINI
AFI BAIONETS UPPER BAYONETS
Page 2 oI I
SERYICE BULLETIN NO. 110
3. Recheck pnetration of bayonets pr step 2.o. Urru 2.g.
*011
IL minimum penstratlon of bayonet(s) Into fuselage retaining blocl(s)is not obtainable, contact Rockasll InterMtlmPL Customer BsNlce
for further instructions.
4. 11 removed, upholstery on main cabin door.
S. Ineert Maintenance Manual Interim Change Notice In applicable Maintenance Mplual.
B. Fill out and mall Compliance Card.
ELECT~CAL. LOAD: NO CHANGE.
WEIGHT AND BAW\NCE: NO CHANGE.
SPAREB AFFECTED: NO´•
PWL1CCA1ONB AFFECTED: The Airplane Maintenance Manual Interim Change Notice is furnished
with this Service Bulletin.
RECORD COMPLIANCE: Mate an appropriate entry in the airplane maintenance records as follows: Se~oe
Bulletin No. 118, dated 21 August 1980, entitled "Main Cabin Door Bayonet Rlggl~ Cheer", aceompllahat
(date).
Page 4 014
SERVICE BULLETIN NO. 1??
(CFWDMAIN LANDING GEAR
STRUT (REF)
RAMP (REF)
0.125" RADIUS
(MINIMUM)
MAMFER O. 08" X 450
SIDES)
71v I
o.so´•yo.sz~´•
LEFT INSTALLATION SHOWN
RIGH’I INSTALLATION OPPOSITE
E)CISTING RAMP (REF)
400-1S8-RE3 HOOK
0.032 CORROSION
RESISTANT STEEL
SAFETY U~XE
O.I56"/0. 180" DIA.
HOLE 11IRU RAMP TO MATCH
400-138-RE3 HOOK. INSTALL
LINE UP HOOK MS18582-42 ROLL PIN AND
WITH RAMP SURFACE SAFETY WIRE ROLL PIN TO
HOOK AND RAMP
FILL OAF (0.020" NOMINAL)WITH EC1151 B/A (OR EQUIY.)
STRUCTURAL ADHESIVE
FiQura 1.
Page2o~3
SERVICE BULLETIN NO. 1??
8. Apply EC1151 B/A (or equivalent) strueblral adhesive to UU any gap between hook and ramp (see
Figure i.).
WOll
If adhesive other Dan EC1151 B/A is used, the adhesive should be
suitable for steel to aluminum bonding with minimum shear strengthof 2180 psi.
9. Install 400-139-RE3 hook on existing ramps using MSIBSBI-IP rall pin and safety wire roll pin (see
Figure
11011
Do not disturb loeatton of hook until structural adhesive has cured.
EC1?S1 B/A Cure Temperature Time
150F 24 to 48 Hmre
150"F 1 Hour
Far adhesives other than EC 1751 B/A, follow the manufacblrers
recommended cure times and temperatures.
10. Touchup paint an ramps.
11. Perform an aperahonal cheek of main landing gear system to assure that system is functioning properly.
12. With the landing gear in the retracted position, check for any possible interference with the eldsting330086 yoke or the e~daLLng 330087 link. If there is interference, remove material from yoke or link
or from both to clear hook by 0.03 inch and blend ail cuts with a 0. 50 inch minimum radius. Brush
alodine yoke and/or link after removal of material.
WOll
It is recommended that the roller be removed from the U~r if Lt La
necessary td remove any material for clearanee.
1S. Remove lacks from airplane´•
14. Fill out and mail Compliance Card.
ELECTRICAL LOAD: NO CHANGE.
WEIGHT AND BALANCE: NO CHANGE.
SPARESAFFECTED: NO.
PUBLICATIONS AFFECTED: The Model 69(IC/685 IHustrated Parts Catalog changes required by this
document will be incorporated at the next scheduled revision.
RECORD COMPLIANCE: Make an appropriate entry in airplane mafntenance records as follows: Service
Bulletin No. 177, dated 26 September 1980, enlltled’Uain Landing Osar Strut Book Installation", accomplished(date)
Page3ofa
SERVICE BULLETIN NO. 118A, REVISION NO. 1
LEFT INSTALLATION SHOWN
RIGHT INSTALLATION OPPOSITE
O
BACKDRILL OR USE HOLE FINDER TO
DRILL 0.180~’10.184" DIA HOLE IN DOOR
AT EXISTING STRUCTURE HOLE POINTSEXISTIY(12SW06-25 (TYP BOTH DOORSI
AFToovs~EnEXISTING NUTPLATES IREF)
~oureD/( 8 O Ls 18o.oo"l0.a?" GAp ~TYP)
BOTTOM SIDE I ~-Msaes3sz72 SCREW
MS2IDIQL3K i~ :li ITYP 27 PLS)
(NUTPLATE 4 PLSI r0.30" E.D.260006-28 LOWER
MS21D18L3 NUTPLATE IC EOSPACESDOOR
USE EXISTING HOLE IN
RlB ar THIS POSITION
FOR LOCATING NEWMS27038-1´•25
0.180..10.184’. oln
A HOLE PLSI B ITYPIPLS) DOOR
BA
IT M~Y BE NECESSARYTOUSELONOERORSHORTER SCREWS DUE
TOTHICINE6SOFWEIGHTS.
Ic0.38.. 0.25’.MIN.
m0054´•513. -615 WEIGHTS MAY It--- -r +I MIN. ITYPI´•MS27038´•(´•12
no~ll n
BE TRIMMED TO OBTAIN CORRECT-CV- VSCREW ITYP 3 PLSI
BALANCE IDO NOT TRIM BEYONDO.SO"MIN. 2SW94´•528WEIOHT
MINIMUMSSHOWN)260036-1 GANG CHANNEL
Msno38´•l-26sCREW-~ k26W1S-M)1 GANG CHANNEL
ITYP I PLSI
4´•651 OPPOSITE
WEIGH THE WEIGHTS WEIGHTS IAS REODL
WOll 250034-513. -515. ´•527. -635
WEIGHTPRIOR TO INSTALLATION.WEIOHTADOEOSHOULDEounL WEIGHT REMOVED VIEW B_B
VIEW A-A
fiour´• 2.
’GPageaofS
IER~CE BULLETIN NO. 1?BA
*011
WEIGH THE WEIGHTS WHEN THEY ARE
REMOVED. AND RECORD SANE
EXISTING 1636201-272 SCREW (3 PLS)EXISTING
1 EXISTING 260034-517
210034´•518 BALANCE WEIGHTS
260034´•526 OPPOSITE
WEIGHTS
B
260036´•1 GANG8
B CHANNEL
EXISTING
mW1S´•SO1 GnNG4 O 8 O m
CHANNEL EXISTING 260005-23O C C C CG
ACCESS DOOR
C t C C C C t C C C C C C C C C, C\ 26005-24 OPPOSITE
0~
Ccocoooocooopo~
~ourso~ILERON I\SSY IREFI
VIEW LOOKING DOWN
LEFT INSTALLATION SHOWN
R1G HT INSTALLATION OPPO SITE
~ipur´• i._4
Psge 2 of B
SERVICE BULLETIN NO. 118A
LEFT INSTALLATION SHOWN
RIGHT INSTALLATION OPPOSITE
BACKDAILL OR USE HOLE FINDER TO
DRILL DIA HOLE IN DOORAT EXISTING STRUCTURE HOLE POINTSITYP BOTH DOORSI
AFT \I I EXISTING NUTPLATES IREFL
CoursD´•i O 8
o.w´•7o.o3´•´• onP cTvPI
BOTTOM SIDEMS21048L3K
ITYP 17 PLS)
MS21048L31N:TPLI\TE E.O.
EOSPACES 25000525 LOWER
DOOR
-"-__ EXISTING HOLE IN
RIB AT THIS POSITION
FOR LOCATING NEW
ACCESSDOORS
AcC, HOLE !4 PLSI MS27034-1-12 SCREW UPPERB ITYP 3 PLSI DOOR
A B
i?
*01.-j iLI11´•´• I´•Ps´•MIN
250034´•613. ´•5~6 WEIGHTS MAY (t-- i MIN. ITYP)MSZ1034´•1´•1Z
BE TRIMMED TO OBTAIN CORRECTBALANCE IDO NOT TRIM BEYDND
SCREW ITYP 3 PLSL
MINIMUMSSHOWNI 0.60’~MIN,mW34´•528WEIOHT
2500361 GANG CHANNEL
M970JB-1-21SCREWITYs 7
PLSI.~.,...,26WJS´•SD1(I~NO CHANNEL
11011250034613. ´•515. ´•527. -655
WEIGH THE WEIGHTS WEI(IHTS(*S RE(IDL
´•53( OPPOSITE PRIOR TO INSTALLATION
WEIGHT ADDED SHOULD
EOUAL WEIGHT REMOVED VIEW 8~gVIEW A-A
FiOur´•
SERVICE BULLETIN NO. 118A
19. Mark onfive (5) equal spaces between holes and drill four (4) additional holes through both doors.
20. Remove both dmts and dimple holes.
21. Install nualate. PiN MS21049L3 on doubler, PIN 240005´•25 securing with rivets, PIN MS20426AD3.
22 install four (4) nutp)ates. PiN MS21049L3K on inside of lower door securing with rivets, MS2042BAD3.
23. Install upper doors, PIN 250005´•27 -28 using screws, PIN MS24093S272.
NOTE
Prior to installing weights in step 24. place weight on scale.
Add this to weight recorded in step 4. or step 5. Total weight
should equal weight removed and recorded in steps 2. and 3
if not, use any combination alweighta, PIN’s 250034´•513,
515, -527, or 535 to obtain correct weight Weights, PIN
250034-613, or 515 may be trimmed as necessary to obtain the
correct weight, provided they are not trimmed in excess of
minimums illustrated in Figure 2.
24 Install weight, PIN 250034´•529 and gang channel, P/N 250035´•1 in leading edge of upper door and secure with
screws, PIN MS27039-1-1213 placesl.
25. Install lower doors, PIN 250005-29, -30 using screws. P/N MSZ4093S272.
26. Balance aileron in accordance with procedures outlined in Chapter 57 of the Maintenance Manual
NOTE
Any combination of weights, PIN’s 250034-513, -515. -527, or
´•535 may be added in leading edge of upper door to balance
ailemn. If weight, PIN 250034-513 or -515 is too heavy, it
may be trimmed as required to obtain correct balance weight,
provided it is not trimmed in excess of minimums illustrated
in Figure 2.
27. Install aileron on airplane in accordance with procedures outlined in Chapter 27 of the Maintenance Manual
28 Fill out and mail Compliance Card, specifying that Part II of this Service Rulletin has been complied with.
ELECTRICAL LOAD: NO CHANGE
WEIGHT AND BALANCE: NO CHANGE
SPARES AFFECTED: NO
PUBLlCATIONS AFFECTED: The airplane Maintenance Manual and Illustrated Parts Catalog changes required by
this Service Bulletin will be incorporated at the next scheduled revision
RECORD COMPLI~NCE: Make an appropriate entry in airplane maintenance record as follows: Service Bulletin No.
118A, dated 1 February 1981, entitled "Aileron Access Door inspection and Replacement, PART I accomplished
(datel PART I1 accomplished (date)
Page B of 6
SERMCEBULLETLI NO´• 1BO
a~a/g c~ RIGHT INSTALLATION SHOWN
LEFT INSTALLATION OPPOSITE
~i
rLOIELIN(I
II1DEWINDOWOUTLET
HUTER, Y -MERHALWYITCH
CUUIP (WP)
ELECTRIWLWIRINO
d
cuus mpl
BLOWERMbrrR
~lpu,´• i.
PylofS
[IISRVICE BULLETIN NO. 188
UPPER COWLINOSHELL
O EXHAVSTPIPE
EXTENSION ASSY
EXH*USTPIPEASSEMBLY
b
FonwnRDFnlmNo
LOwEn
NOSE RIN(I COWLINO
ASSEMBLY SHELL
EXHP~VSTPIPE
~SSY
ENGINE
EXHAUST
OI~PHRAOM
BOLT
COLLAR
~80WB´•17
ENGINEEXHAUSTSEAL
IYPOHER
NUT
Fags 2 d 6
:o;L!.E:TIN NO. 188
FLANOE ASSY (REFIRESTRAINT ASSY IREF)
B1OBS1´•RE13 SEAL IMODEL BBOC)OR
B1OBBI-RE(IGEI\L (MODEL 8861
EXHAUST PIPE ASSY IREFI
HSZM21M3´•3 RIVET. At REOD. WITH FIL´•PRO
MAXIMUM SPPICIN(I OF RIVETS 06/\ OR E(IUIVALENT COPPER
TO BE APPRDXIMATELY 2~’, BASE LUBE TO FACILITATE
ASSEMBLY OF EXHAUST PIPE
DETP~IL A
no~r
BUCK RIVETS SECURELY
TO FACILITATE ASSEMBLY
OF EXHAUST PIPE ONTO
FLANGE ASSY.
CUT ENDS PIT 460 AND BUTT TOGETHER
INO O~P PERMITTEDIMS20127M3´•3
RIVET IREFI~ I SEAL cREFI
o o
VIEW LOOK1N(i AT 8EAL
INSIDE EXHAUST PIPE AgSY
FlpnZ.
Page 4 of 5
LIERVICE BULLETIN NO. 184
~RUTOB.IIP.CTrD
4
STRAP IREF) INSERT SHIM STOCKHERE TO CHECK rOR
SHEARED FISTENER
WOR FRAME IREFL
olo! I ~EEIECIION IREF)
INSPECT 8111 (BI FASTENERS
*TTACHINO THIS CLIPOUTER SKIN IREFI
Rpun
Page a ola
~IIService Bulletin CulF8tFeamAmerican
CORPOR*TION
ComMndn Dirkion
6WI Norm Ra;LMIII Avenue.Bamanl, OLlahome 73W8
SERVICE BULLETIN NO 186
23 December 1981
TRIM TAB FREE PLAY MEASUREMENT
MODELS AFFECTED: MODEL 685, SERIAL NOS. 12000 THRU 12066, MODEL 690, SERIAL NOS. 11001 THRU11079, MODEL 690A, SERIAL NOS. 11100 THRU 11344, MODEL 690B, SERIAL NOS. 11350 THRU 11566. MODEI.69OC. SERIAL NOS. 11600 THRU 11614, 11676 THRU 11694, 11696, 11698, 11100 AND 11101, MODEL 6951 SERIALNOS. 96000 THRU 95084 AND MODEL 695A, SERIAL NOS. 96001, L~003, 96005 THRU 86007, 96009, 96011 AND96018.
REASON FOR PUBLICATIDN: TO ASSURE THAT NO EXCESSIVE FREE PLAY EXISTS ON AILERON,ELEVATOR AND RUDDER TRIM TABS
COMPLI*NCE: WITHIN NEXT TWENTY-FIVE (26) HOURS TIME IN SERVICE.
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILECOMPLYING WITH THIS SERVICE BULLETIN, CONTACTYOUR NEAREST GULFSTREAM COMMANDERAUTHORIZED SERVICENTER.
BY WHOM WORK WILL BE ACCOMPLISHED: A P MECHANIC OR EQUIVALENT.
APPROYAL: FAA DOA SW-2 APPROVED.
ESTIMATED LIIN HOURS: THREE (S) HOURS.
PARTS DATA: 1 EA. COMPLIANCE CARD
SPECIAL TOOLS: DIAL INDICATOR WITH A RANDE OF 0-1.00 INCH IN INCREMENTS OF 0.001 INCHRESOLUTION. BRACKET (FABRICATED LOCALLY) TO ATTACH DIAL INDICATOR HOLDER TO CONTROLSURFACES.
ACCOMPLISHMENT INSTRUCTIONS:
NOTE
The procedures for measuring trim tab free play for controlsurfaces (aileron, elevators and rudder) are very similar. The
setup procedure for measuring rudder him tab free play is
slightly different f~om the setup made when measuringsilemn and elevator trim tab fre~ play.
1. Determine free play of the control surface trim tab in accordance with the following procedures:
a. Position control surface in a streamlined position.
b. Rigidly fasten the dial indicator holder to the control surface:n line with trim tab actuator so that dial indicatoris positioned as in Figure 1.
NOTE
Position dial indicator so that plunger tip contacts the trailingedge of the trim tab an olthe actuator rod. Dial indicatormust have a range of 0-1.00 inch, in increments of 0.001 inch.
Page 1al7
8ERVICE BULLETIN NO. iBB
’t
´•t
TRIM T~B FREEPLAY i:I‘i
WORK1HEET:ii
ii’ ii
’1"
i:l i’
i’
i i
i I’i’
I :i’
i:
i:: ii Ii
I i
i i-::::I
::I:::i:
ii _IlilUPLDAD
ji-- i;
10. i i: i -B -1t2 tB itib
oowhlLono i~ssl:i:
I´• i:li
´•i: ´•;i i
´•-i-I-4r t :i
i
i
1::i ´•:::I:
i.. i..... iiii i ´•:I::I:
i;
:1, i´•I
ii:: ii::i
:i :.I, i:i
Flmn.
PPgeSofl
BERVICE BULLETIN NO. 188
ii polrT?
FREE FLAT DEFLECTION
PIILERON DEFLECTION POINT(’POINT 2 OR 0.010 0.011 0.061 INCH.
L. ELEVATOR DEFLECTION I WINT 3 POINT 1 OR O.W8 -0.ON I O.WJ INCH.
*OII:WHEN ONE POINT Is LOCATED BELOW TnE O DEFLECTION LINE
AND THE OTHER POINT IS LOCATED ABOVE IT. ADD THE moNUMERICAL VALUEITO OBTAIN TOTAL DEFLECTION. WHEN
BOTH POINTS ARE EITHER ABOVE DR BELOW THE O DEFLECTION
LINE SUBTRACT THE SMALLER VALVE FROM THE LAR(IER VALUETO OBTAIN TOTAL DEFLECTION.
ppgeloI?
BERYICE BULLETIN NO. 186
PUBUCITION8 AFFECTED: The Airplane Maintenance Manual change required by this document will beincorporated at the next scheduled revision.
RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: brviee Bulletin No.186, dated 29 Derember IsB1, entitled "Rim Tab Free Play Meaaurement", accomplished (date)
PPge?ofl
SERVICE BULLETIN NO. 181
2. Remove baggage compartment liner, as necessary, to expose antenna attaching hardware.
NOTE
The antenna connector and attaching hardware are located
directly above the aileron servo.
3 Inspect fuselage skin, both internally and externally, in area of antenna base for possible cracks.
4 If no eracks are found, assure that antenna attaching hardware is in place and secured (tight) and then proceed to
step 6.
5. If cracks are found in fuselage skin, proceed immediately to step 3. of Part II (CI 119 antenna) or step 3. of Part III
(VF10-1IS antenna).
6. Reinstall baggage eompartment liner.
7. Fill out and mail Compliance Card specifying that part I has been accomplished noting if all antenna attachinghardware was in place and secured (tight).
P*RT II MODIFY CI119 ANTENNA ATTACHMENT.
I. Gain access to antenna connector through baggage compartment door.
2 Remove baggage compartment liner, as neecessary, to facilitate removal and installation of antenna.
3. Disconnect antenna connector from antenna
4. Remove screws attaching antenna to top of airplane and remove antenna. Discard gasket from bottom of antenna if
installed.
5 Remove aileron servo, if necessary, to facilitate installation of antenna doublers. Capstan and Cable rigging are to
be left intact
6 If fuselage skin is creaeked around antenna base and cracks are outside the area to be covered by a 8-inch by 10-inch
doubler as shown in Figure 2., contact GulFstream American Corporation, Commander Division Customer Service
Department, Bethany, Oklahoma 73008 for further instructions.
7 Ifno creeks are found or cracks found are within area to be covered by a B-inch by l0-inch doubler, proceed as follows
(refer to Figure Il:
a. Remove rivets from fuselage skin in area where a Ii-inch by 10-inch doubler is to be installed (refer to Figure2).
b. Fabricate a doubler,ll-inches by l0-inches, from 0.010-inch, 2024-118 clad aluminum sheet.
e. Fabricate an angle, l.50-inches long, from AND10134´•1201, 2024-T3511 aluminum extrusion or from 0.063-inch,2024-T3 clad aluminum sheet.
NOTE
Trim angle on installation as necessary.
d. Fabricate a spacer, 0.75-inch wide by 3.85-inches long, from 0.(183-inch, 2024-’13 clad aluminum sheet.
NOTE
Trim spacer on installation as necessary.
i-
Page 2 of 10
SERYICE BUUETIN WO. Is?
O
O Q
Qoo.~´• DIA´• HOLE
I4PLS)
ACTUAL SIZE USE AS TEMPLATE
FI\BRICe~TE METAL CASKET FROM
O.DM". ZMLTJ CLAD ~LUMINUMSHEET
BEND UP 80"
E BEND~1ACTUAL S12E USE AS TEMPLATE
FABRICATE PICLIP FROM O.OQ1"
mZ4´•TO CLAD ALUMINUM SHEET
Figun 1.(9*´•12 ot II
PaQ.e 4 ot 10
SERYICE BULLETIN NO. 181
6. If fuselage skin is cracked around antenna base and cracks are outside the area to be covered by a 8.?0-inch by 12.60-
inch doubler as shown in Figure 4., contact Gulfstream American Ca~orstion. Commander Division Customer
Service Department, Bethany. Oklahoma 13008 for further instructions
7 If no cracks are found or cracks found are within area to be covered by a 6.70´•inch by 12.60-inch doubler, proceedas follows (refer to Figure 3):
a. Remove rivets from fuselage skin in area where the 6.70-inch by 12.50-inch doubler is to be installed (refer to
Figure 4).
b. Fabricate a doubler, 6.70-inches by 12.50-inches,.60-inches, from o.0l0´•inch. 2024-’13 clad aluminum sheet.
c Fabricate two (2) clips from 0.063-inch, 2024-T3 clad aluminum sheet.
d. Fabricate a plate from 0.063-inch, 2024´•T3 clad aluminum sheet and install two (2) MS21069L08 nutplates on
fabricated plate.
e Fabricate an angle, 1S-inches long, From 0.063-inch, 2024-’13 clad alurmnum sheet.
8. Dye check cracks to determine ends of cracks and stop drill using a No. 40 drill.
9. Locate and drill parts, fabricated per step 7., on airplane (refer to Figure 4).
NOTE
Dimple holes in doubler that pick up existing holes in fuselageskin and countersink holes in doubler that match new holes
drilled through fuselage akin.
10 Remove fabricated parts from airplane and deburr all holes.
L1. To assure proper grounding of doubler, remove paint from fuselage skin, in area where fabricated doubler is to be
installed, using an appropriate solvent and then apply alodine to this area.
CAUTION
To prevent damage to skin surface, abrasives and scrapers,other than the rotary stainless steel brush, should not be used
to remove paint.
12. Locate, drill and install MS21469LOB nutplate (2 places) on fabricated angle (refer to Figure 4).
13. Install all fabricated parts on airplane (refer to Figure 4).
NOTE
All rivets used are MS2042BAD4 rivets unless otherwise
noted. NAS1309B or NAS1139B blind rivets may be
substituted For MS20426AD4 rivets. Length of rivets to be
determined on installation.
14. Reinstall existing antenna using existing hardware (refer to Figure 4).
15. Fillet seel around the antenna, doubler and antenna mounting screws as outlined in Chapter 20 of the AirplaneMaintenance Manual.
16 Prime doubler with zinc chromate primer and paint as necessary.
17. Reconnect antenna connector to antenna.
18. Reinstall any equipment that has been removed for this modification.
19 Reinstall baggage compartment liner.
:s 20 Fill out and mail compliance Card specifying that Part III has been aceomplished noting if any crack, were found
and the extent of cracks
Page 7 of 10
SERVICE BUlLETIN NO. 181
ELECTRICAL LOAD: NO CHANGE.
NOCHUIDB
SPARES AFFECTED: NO.
PUIUCATIONS AFFECTED: NONE.
RECORD CO~PLIANCE: Make an appmpriate entry in airplane maintenance records as follows: Service Bulletin No.
187, dated 6 February 1982, entitled "Antenna Inspection and ModiBeation", Part I accomplished (date)Part II accomplished (date) :Part In accomplished (date)
Page 10 of 10
BWVICE BULLETIN WO. 188
YOll
THOROUBHLY CLEAN TnREADS ON CABLE ASSEMBLIES
IIITH METHYL ETHYLKEYTONE IMEKI PRIOR TO APPLYING
LOCTITE 280 ON TnREADS
SAFETY IYIRE JAM NUT TO ROD END OR LOOSEN JAM NUT. APPLY LOCTITE 281 TO THREADSAND RETOROUE NUT TO
SMPINCHPOUND6.
O LOOSEN JAM NUT. APPLY LOCTITE 220TO THREAOS AND RETOROUE NUT TO 2040 INCHWUNDS.
O LOOSEN 8ECOND~RY JAM NUT. APPLY LOCTITE 220 TO THREADSAND RETOROUE NUT m 210220 INCHOOUNDg
*011
DO NOT LOOSEN PRIMARY JPIM NUT.
LOOSEN JAM NUT. APPLY LOCTITE 290TO THREADS AND RETOROUE NUT TO 12(6 INCRWUNDG.
´•O LOOSEN JAM NUT. APPLY LOCTITE 280 TO THREADLIAND RETOROUE NUT TO W07111 INCHQOUNDS.
´•O LOOSEN JAM NUT, APPLY LOCTITE 220 TO THREADS AND RETOROUE NUT rO aos~ Irrcn~ou*wr.
LOOSEN JAM NVT. APPLY LOCTITE 190 TO TnREADS AND RETOROUE NUT TO 210280 INCHPOUNaR
cnvrlore
EMERGENCY CONTROL~8E SURE EMERGENCY CONTROL CABLE IS
BPROPERLY RIOOED PER MAINTENANCE MANUAL
AFTER APPLYING LOCTITE TO CABLER
OIL COOLER DOOR
CABLE AgSY (REFI
CONDITION CONTROL
CABLE ASSY IREFI
rowERCONTROL ii ICABLE ASSY (REF)
I
t~12PLS1
EMERGENCY FUEL
LEFT INSTALLATION SHOWN SHUTOFFMNTROL
CABLE IREF)
~unl´•~´•r´•
ppge 2 or a
SERVICE BULLETW NO. 188
4TY PART NO. DESCRIPTION
13 it. 8661 Tape1 ea. Compliance Card
1 ea. Service Bulletin No. 189 Instructions
SPECULIOOLS: HARD RUBBER ROLLER AND HEAT DUN WITH loO’F TO 160’F CAPABILITY.
ICCOMPLISHMENT INSTRUCTIONS:
NOTE
The air temperature and surface of propeller blades must be
above 60’F during installation ofabrasion resistant tepe.
1. To prepare propeller blades for installation of abrasion resistant tape PIN 8661, proceed as follows (refer to Figure
NOTE
Area to be cleaned is the leading edge of propeller blades and
an area, minimum of i-inches, an each side ofleading edge.
a. Remove existing sealer at end of propeller de-ieer boot and clean surface using Methyl Ethyl Ketone (MEK).
b. Remove paint from propeller blade in area where tape is to be applied.
c. Smooth out rough areas using "fins’~ emery cloth.
d Weahpro.sll.rbllde~wiB hn Nlte~ Donotuss POI~BFPI I(iBp
e. Drythe surfacewith alintfreeeloth.
f Clean area using a 50150 ratio of Isopropyl alcohol to water solution and wipe surface using a lint Eres cloth
CAUTION
To avoid sconng damage to blade surface, the tape must not
be cut or trimmed on the blade.
2. Apply 8561 tape to propeller blades using a hard rubber roller. Apply tape starting at de-icer boot edge and work
outboard. Speciai care should be taken so as not to touch adhesive side of tape during installation.
3. Inspect tape to insure no lifting edges, air bubbles, wrinkles or overlaps are present. If unsatisfactory, remove and
install a new length of tape
i. After tape has been rolled smooth, use heat gun to apply heat to tape such that surface temperature of tape is raised
to at least 100’F (but not over 160%). Maintain this temperature while accomplishing step 5.
CAUTION
Do not allow heat to remain in any position so long that
discoloration or deformation of tape occurs.
5 Reroll tapeduringapplication of heat.
6. When tape has cooled down, reseal end of propeller de-icer boot using sealant compound per MIL-S-7502, MIL-S-8802
or an equivalent.
7. Repaint black side of propeller blades using Sherwin Williams F-63B-12 carbide black texised polane along with
Sherwin Williams Y66V29 polane catalyst (two part mixture) or equivalents. (Available from Local propeller jrepair agencies or Dowty-Rotoll. Do not paint over the abrasion resistant tape.
Page aof(
SERVICE BULLETIN NO. 188
BUTT TAPE AGAINST DE-ICER
BOOT I\ND SEAL AFTER TAPE
HAS BEEN INSTALLED PROPELLER BLADE ITYs)
DE-ICER ~ROPF; Zg.0..
.I
W NOT PAINT OUT WHITE
APPLY 8581 x TAPE UNE WHEN REPAINTINGSO THAT TAPE EXTENDS PROPELLER BLADES.EOUALLY ON EACH SIDE OFPROPELLER BLADE CENTERLINE.INSTALLATION TO BESMOOTH ANO FREE OF AIRBUBBLES OR WRINILE~.
RUBBER ROLLER IREFL
c
PROPELLER BLADE IREFI
USE HARO ROBBER ROLLER TO APPLY 8581 TAPE
Eisur´• i.
Page S of 4
8ERVICE BULLETIN NO. 180A
EXHAUST IIPE AJ6V (AEFI
AWE SEAL IREF)EXHAUSTIlFE
PSSY rREF)
REMOVE EXHAUSTPIPE
A6SY FROM ENL31NE AT
THIS WINT BY REMOVING
BOLTS.
SILICOFIE SEAL
IREFI
C-:BENYEEN ~POT´•WELD(
a.zs rO O.Sd´•’ i I ITYP 12 PL81
´•INOIWTEI6POT´•WELO~
INDICnrEI) INTERSI*CID RIVETs I
0.25"
WB81BLE TACK
a RIYET LOCATION
MOUNTING BRACKET (AEFI
Fi(un
Psse S ol 5
SERVICE BULLETIN NO. 1slA
no 1 No.lKIT KIT
BTY BTY PART NO DESCRIPTION
1 ea. 1 ea. ED10057´•S01 Centering Pin
1 ea. ED1O1S9 Centering‘Cam1 ea. 1 ea. 5201-31 Nameplate1 ea. 1 ea. Compliance Card
1 ea. 1 ea. Service Bulletin Na. 191A Instructions
SPECIAL TOOLS: TWO (2) HYDRAULIC PRESSURE GAGES WITH 0 TO 1000 PSI CAPABILITIES AND AN
EXTERNAL HYDRAULIC PRESSURE SOURCE CAPABLE OF PRODUCING AN AIRCRAFT
SYSTEM PRESSURE OF 0 TO 1015 PSIG.
ACCOMPUSHMENTINSTRUCTIONS:
NOTE
SERIVCE BULLETIN NO. 191 WAS EFFECTIVE ON
MODEL 690D, SERIAL NOS. 15002, 15003, 15006, 15008,15(109 AND 15012 AND ON MODEL 695A, SERIAL NOS.96001 THRU 86030, 96082, 96034 AND 96035. ONLY
THESE AIRPLANES ARE REPUIRED TO ADJUST
THEIR POWER BRAKE VALVES. IF YOUR AIRPLANE
WAS NOT AFFECTED BY SERVICE BULLETIN NO. lsl
OR COMPLIED WITH SERVICE BULLETIN
NO. 191, DISREGARD STEPS 3 THRU 6 AND ALL OF
STEP 15.
1. Jack airplane as outlined in Chapter 7 of the Airplane Maintenance Manual.
n.
3. Remove upper cowling from left engine.
4. Close fuelihydraulicshutoffvalves
5. Disconnect hydraulic pump lines from firewall and cap off
NOTE
Do not rotate engine with hydraulic pump lines capped off
6. Conned an external hydraulic system pressure source, capable of producing a system pressure of 0 to 1075 psig,to hydraulic system flttings on engine Brewall. Open fuelihydraulic shutoff valves.
7 Place landing gear handle in the up position to bleed hydraulic presaure to zero. Place nose Landing gear at an
approximate 45" aft position. If bleed pressure did not pull gear from over-center, this can be done manually byapplying upward pressure on center ofdrag brace assembly.
8. Remove existing centering cam, centering pin and orifice tube as follows (refer to Figure i):
a Reduce nitrogen pressure to zero by removing cap on the nitrogen and hydraulic fillport valve and
depressing valve core.
b. After pressure has bean removed, remove valve core from nitrogen and hydraulic fillport value.
c. Cover nose wheel and tire assembly ulth a plastic bag to moted them from hydraulic fluid.
d. Remove cotter pin and nut from lower drag brace bolt.
a. Hemove center bolt from scissors.
F Remove snap ring and washer that retain fork and rod assembly in strut body.
Page2olS
4
S~RVICE BULLETIN NO. 181A
EXISTING ED10121
ORIFICE TUBE
(REF)
--1
EXISTING HOLESDRILL 0. 457" DIA. HOLE ALL (REF)
THE WAY THRU ORIFICE TUBE.
CLEAN AND DEBURR HOLE ON
BOTH SIDES OF ORIFICE TUBE.
VIEW A-A
Figure 2.
Page lafS
SERYICE BULLETIN NO. 191A
G.i:
UAIN LANDING GEAR (REF)
INSTALL HYDRAULIC Ij I1
LEFT INSTALLATION SHOWN
PRESSURE OAOE ON bFl I RIGHT INSTALLATION OPPOSITETHIS TEE F~TINO
LEFT AND RIGHT
MAIN GEAR
Figure 9.
PageGolS
B
SERVICE BULLETIN NO. 181A
POWER BRAKE VALVE(REF)
c
BALL
(REF)
8INSERT FABRICATED~BAR BETWEEN BOTH
POWER BRAKE VALVESAND DEPRESS BRAKE PEDALS
PRESSURE AATUGTINO VALVE LEVER
CHECI(NUT IREF) (REF)
PRESSURE ADJUBTING
SCREW (REF)
VIEW LOOKING INBD
FROM LEFT ACCESS DOOR
Fiyre i.
Page 8 of 9
Service Bulletin CulfstreamAmericanCORPOR*TION
Comm~Nln ~rblon
1001 North R~twall ~usnus.Bsmany, OLI´•h~nu 73WB
SERVICE BULLETIN NO. 193
29 October 1982
PASSENGER OXYGEN DISPENSER MODIFICATION
MODELS AFFECTED: PART I MODEL 690C, SERIAL NOS. 11719 THRU 11721, 11126 AND 11727
MODEL 690D, SERIAL NOS. 15002, 15003 15004, 15006, 15008, 15009, 15011
AND 16014.
MODEL B9SA, SERIAL NOS. 96001 THRU 96030, 96032 THRU 96035, 96037,
96039, 96040 AND 96042.
PART I1´• MODEL 690C, SERIAL NOS .11119 THRU 11727.
MODEL 690D, SERIAL NOS. 16001 THRU 15014.
MODEL 695A, SERIAL NOS. 96001 THRU 96042.
REASON FOR FUBLICI\TION: TO PREVENT POSSIBLE MALFUNCTION OF OXYGEN MASK DLSPENSING
LIDS.
COMPLIANCE: WITHIN NEXT TWENTY-FIVE (25) HOURS TIME IN SERVICE
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE
COMPLYING WITH THIS SERVICE BULLETIN,CONTACT YOUR NEAREST GULFSTREAM
COMMANDER AUTHORIZED SERVICENTER.
BY WHOM WORK WILL BE ~CCOMPLISHBD: A B P MECHANIC OR EQUIVALENT.
PIFPROVAL: FAA DOA SW-2 APPROVED.
ESTIMATED MAN HOURS: PART I MODIFY LIDS SEVEN (7) HOURS.
PART II INSTALL PLACARD AND TEST SYSTEM ONE (1) HOUR.
PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE BULLETIN MAY BE PROCURED
THROUGH YOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR: KIT NO. 1 $17.13
OR KIT NO. 2 52.46. A FULL CREDIT WILL BE ISSUED UPON RECEIPT OF A PROPERLY EXECUTED
WARRANTY CLAIM AND A COMPLIANCE CARD. REFERENCE THIS SERVICE BULLETIN, AIRCRAFT MODEL
AND FACTORY SERIAL NUMBER WHEN ORDERING SERVICE BULLETIN NO. 193 KIT CONSISTING OF THE
FOLLOWING:
pnr´• ´•uala I~ ~moa nocio´•.
Kit No. 1 Part I
Kit No. 2 Part II
Kit Kit
No. 1 No. 2
QTY. BTY. PART NO. DESCRIPPION
8 ea. 860183-663 Placard
8 ea. 862061-460 Washer
1 ea. 1 ea. Compliance Card
1 ea. 1 ea. Service Bulletin No. 193 Inatructians
Page 1 of 7
SERVICE BULLETIN NO. 1BU\
VIEW LOOKING AFT
AT F.S. 260.00
B~GOn(lECOMPARTMENT8TRUCTURE IREF)
aNeeoalownsHER 1 8112031-247
MSZIOMN) NUT AN(ILE
12PUI)
ACFT
rnsu~l. Ishat tot zl
Page 4 of 11
SERVICE BULLETIN NO´• 184A
CHUB FACE
1.75" 1~1. -8125)
INNER EDGE OF BOOT
DEICER BOOT
IREF)
PROPELLER BLADE
IREFI
FlgureJ
nEwA´•n
MSS3B7´•I´•STIEDOWNI~RnP
FITTEDBIIWEENOUTER
AND CENTRAL CABLE
M533872´•8 TIEOOWN 8TRAF
BRACKET
MS3387´•2´•8 TIEDOWN STRPIP
FITTED AROUNO WIRE
HARNESS AND INDENTED
AREA OF CONNECTOR BRACKET
A
C aPmo*s~*aEnPwarl*.CONNECTOR INSTALLATION
FiCn O
Page B of 171
SERVICE BULLETIN Na 18SB
nuooEncnsLE RUODER HORN
IREFI IREFI
d.,e\
9CLEVIS IREPI
inlp~s i.
Page a d S
SERYICE BULLETIN NO. 1919
SPECIAL TOOLS: NONE.
*CCOMPUSHMEM INSTRUCTIONS:
i. Gain access to rudder control cables and cable pulleys just forward of fuselage station 409.00 to inspect Fables
for paseible fraymg (refer O Figure 1).
NOTE
On some airplanes, access to pulleys and rudder cables may
be gained through access door installed just sit of fuselagestation 386.82 par Service Latter No. 345. On later model
airplanes, access to pulleys and rudder cables may be
gained thmugh lower fuselage access door att of fuselagestation386.60.
2. Inspect rudder control cables, beginning at Ridder born clsvis and extending for a length of six (6) inches forward
of rudder horn clevis, for possible fraying of cables.
3. VNdder control cables are not frayed, proceed to step
4. If any rudder control cable is frayed, it is accaptable for an slrplane to remain in service with up to Wires (S) wires
broken, provided no two (2) wires are in the same strand ofthethe rudder cable. Airplanes ~u?th this condition must
have thecables rglacsd at the nsxt 100´•hour inspection period.
NOTE:
control cable consists of seven strands and
each strand consists of 19 single wires.
5. Inspect Ridder control cable pulleys and replace ifnacsssary.
B. If any rudder control cable does not meat the requirements stated in step 4., replace cable and check rudder
control rigging as outlined in We applicable Airplana Maintenance Manual.
7. Fill out and mail Compliance Card and note condition of cables on Compliance Card.
ELECTRICAL LOAD: NO CHANGE.
WEIGHT ANO 8*L~NCE: NO CHANGE.
SPARES I\FFECTED: NO.
PVBUCATIONS bFFECTEO: The Aicplane Maintenance Manuals atrected by this document will be changed at Be nea
scheduled ranaion.
RECORD COMPLIINCE: Malts an appmpria~e entry in alrplana mountanancs records asfollows: Service Bulletin No.
195B, dated 28 AuSuat 1985, entitled ´•Rudder Control Cable InspeEtian andlor Replseement", aceompiished 9(date)
NOTE
if inspection of Ridder control cables meet the reqlursmentsas noted in step 4.. make an entry in airplane maintenance
records stating that cables are to be replaced at the next
100-hour inspection period.
i page S ol 3
SERVICE BULLETIN NO. 181
c.o
~o´•rl
APPLY SEALANT TO PITOT TUBE
Agpy PRIOR TO INSTALLING ON
MOUNTING BRACKET.
CNsElaor.nN
IREFI
MOUNTINB BRACKET
e, IREFI
O
SEAL WITH EC1239 "Br’SEALANT OR AN EOUIVALENT
MII;SISOZCSEI\LANTO
plmr TUBE ASW
(REFI
C
Fieurs 2.
Page Soil
SERVICE BULLETIN NO. 19?
ELECTRIC*L
WEIGHT AND BALANCE: NO CHANGE
SPARES AFFECTED: NO.
PUBLICATIONS AFFECTED: NONE
RECORD COMPLIANCE: Malts an appropriate entry in airplane maintenance records as follows: Service Bulletin No.
107. dated 9 September 1983, entitled "Modifieation of Pitat Tubs Assembly Installation", accomplished Ldate)
page Boil
II
i Service Bulletin GulfstreamAerospace
~RVICE BULLETIN NO. IssA
Revision No. t
5 June 1981
ELEVATOR TRIM TAB INSPECTION AND MODIFICATION
APPROVIL: ENGINEERING DESIGN ASPECTS ARE FAA APPRO~D.
PPIRTS OITA:
Page 3 of 6
Change quantity of CR3243-C1 blind rivets in Kit No. 2 to 30 ea.
e
Psgelofl
-I
Sewice Bulletin GulfstreamAerospace
SERVICE BULLETIN NO. 198A
(Supersedes Ssrvice Bulletin Na. 198 in its entirety),,,,,,, IELEVATOR TRIM TAB INSPECTION AND MODIFICATION
MODELS AFFECTED: MODELS 500, 500A, 520, 660, 560A, 560E, 680, 680E, 720: 5008, S0OU, 560F, 680F, 680F(P), IB80FL, 680FL(P), 680T, B80V AND BB0W, SERIAL NOS. 1 THRU 1854.
MODEL 6008 SERIAL NOS. 1166 THRU 1876 AND 3050 THRU 3323.
MODEL 681, SERIAL NOS. 6W1 THRU 6072.
MODEL 685, SERIAL NOS. 12000 THRU 12066.
MODELS 690, 690A AND 690B. SERIAL NOS 11001 THRU 11566.
MODEL 690C, SERIAL NOS. 11600 THRU 11132.
MODEL 690D, SERIAL NOS. 15001 THRU 15012, 15014 THRU 15024 AND 15029 THRU
15032
MODEL 695, SERIAL NOS. 85000 THRU 95084.
MODEL 695A, SERIAL NOS. 96001 THRU 96055, 96059, 96060, 96083 THRU 96069, 96072.
96015, 96078 AND 96085.
NOTE
SERVICE BULLETIN NO. 198A REPLACES SERVICE
BULLETIN NO. 198 AND IS BEIND ISSUED TO ADD
AIRPLANES WITH SERIAL NOS. 1 THRU 1397. IF PART
II OF SERVICE BULLETIN NO. 198 HAS BEEN
COMPLIED WITH, DISREGARD THIS SERVICE
BULLETIN, IF PART II OF SERVICE BULLETIN NO,
198 HAS NOT BEEN COMPLIED WITH, COMPLIANCEWITH THI~ERVICE BULLETIN IS REQUIRED.
REASON FOR PUBLICATION: POSSIBLE CRACKS IN INTERNAL RIBS.
COMPLIANCE: WITHIN NEXT TWENTY´•FIVE 1251 HOURS TIME IN SERVICE AND EVERY 100 HOURS
THEREA~TER UNTII. BOTH ELEVATOR TRIM TABS HAVE BEEN MODIFIED PER PART II OF
THIS SERVICE BULLETIN
NOTE
LF ANY PROBLEMS ARE ENCOUNTERED WHILE
COMPLYING WITH THIS SERVICE BULLETIN,CONTACT YOUR NEAREST GULFSTREAM
COMMANDER AUTHORIZED SERVICENTER.
BY WHOM WORK WILL sE ACCOMPLISHED: A P MECHANIC OR EQUIVALENT.
APPROVAL: ENC1INEERING DESIGN ASPECTS ARE FAA APPROVED.
ESTIMATED MAN HOURS: PART I INSPECT FOR CRACKS ONE I1)HOUR
PART II MODIFY TRIM TABS THREE B ONE-HALF 13.6) HOURS EACH TAB
PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE BULLETIN MAY BE PROCURED
THROUGH YOUR NEAREST DULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR: KIT NO, 1 $0.67
OR KIT NO. 2 518.68. REFERENCE THIS SERVICE BULLETIN, AIRCRAFI~ MODEL AND FACTORY SERIAL
NUMBER WHEN ORDERING SERVICE BULLETIN NO 198A KIT CONSISTING OF THE FOLLOWING: I
a*´• ´•uaM *Imoul nl~
Page 1 of 5
SERVICE BULLETIN NO. 198A
.or.
HOLIP LIRI TO II LOCITTO ON
UPPIA 91(IN O( LL~T IRIM1P1B
IND ON LOWIR IKIH OIRI(IHTTAI~TRB.
0.(0" IIIA. H(I11~lls PLUG IUTTONI1PLOL
1.10"
D o o o s o o~ o o o o.o o o o o o o
d
.I
´•r´•i
n o
A
VIEW LOOKING DOWN CON LEFT ELEVATOR TRIM TAB Inrrl
O
SUPPDRT IIRI\EKITO IRERTO BIINSPECTEO
B B ~ORPOSJIIIEERI\EIIAISYIRE~l
IIONE RI\BIUIO~ RIIIS
OrRIMTaa
1KINIAs~lO
i"iL-
ACTUATORSUs~ORTIA~(I(ET arSY IRsR /I I I ~INsrrcrron
mrFI maerrssnl
Rlewrs
IAIR
VIEW B-B
VIEW A-A
Fieun i.
PageDofSii
SERVICE BULLETIN NO. 198A
KIT No. i PIRT I
KITNO.Z PARTn
Kit Kit
No. I No. 2
9TY BTY PART NOS. DESCRIPTION
4 ea. SS48152 PlugButton2 ea. 410001-RE13 Tee
Ib ea. CR3243-4-1 Blind RivetB ea. MS21011L3 Nutplate
1 ea. 1 ea Compliance Card1 ea. 1 ea. Service Bulletin Na. 198A Instructions
SPECIALTOOLS: BORE SCOPE OR SMALI. DENTAL TYPE INSPECTION MIRROR AND BLIND RIVET GUN.
P.CCOMPLISHMENT INSTRUCTIONS:
1. Drill two (2) O.S(I´•inch diameter holes, one II) on eeeh side of actuator support bracket amembly. in the skin thatis opposite the actuator support bracket assembly (refer to Figure 1).
2. Using a bore scope or dental type inspection mirror, inspect both inboard and outboard sections of ribs in bendradius (refer to View A-A, Figure 1).
3. If no cracks are found, proceed as follows:
a Clean plug buttons and area around edge of holes, drilled in step 1., with alcohol.
b. Apply a thin bead of commercial RTV1OB (elear) or an equivalent sealant to edge of holes and install8348152 plug buttons.
Cc. Clean offexeess RTV and smooth out around edge of plug buttons.
d. Proceed to step 5.
NOTE
Inspection for cracks must be accomplished every l(l0-hourstime in service until Part II of this Service Bulletm hasbeen accomplished
4. If creeks are found in either rib, proceed to Part 11 of this Service Bulletin.
5. Fill out and mail Compliance Card specifying that Part I has been accomplished
PART II MODIFY TRIM TABS
1. Remove existing elevator trim tabs as outlined in the applicable Airplane Maintenance Manual.
2. Remove existing actuator support bracket assembly from trim tab.
CAUTION
When performing the following steps, care should be takenso as not to damage trim tabs.
Page 3 of 5
’i´•
SERVICE BULLETIN NO. 198A
nmlno´•i\lan~nr uunno~rruaronELIYI\TORTRIMTAB IRET) SUPPDRT BRI\CI(ETI\SSI
fRIrI
i Y~ o D
ER11~´•I IO oD
BLINO AIVIT
II PLSI IO --2-r.
THISSKIN
00111341 BLIND RIVITRLL RIVETS I\RIMS2WIOIOJ IPLSI
BXEIPT WHERE BLIND RIYETS 888 USEOC
f C f
IRrn
Ho~EToaarcHi-IXISTINO SUPPOAT
THISSUR~I\CI 01 TEE BAACKITASSYTO 88111 LINE am MS1101113 NUTPLATT
rlnn~ae or ExlsnNo I II L~ C: (In.INTIRSPICI I 0180
Ms2IYIIOnDI ;It,.lo´•´•
naolus
i I I I ’ExISTINO DIBS
mErlrx,snaa HOLI TOTRIMRNO/OR
111101111181 RIVET EHAMIIR EPOIOITsl TO MLIEHI3rLS) III R1OIUS O~ RII1 t
EENTIRLINI
Or RIBS
DO NOT RIMOYE
THIS RIYET
TRIM EXISTING DIBSC
nsslown
EXISTING TAAILINO sOOESTRIPNOTAPPLln\IIETDMODE LS BM)O. BOOP. 885 OA 1811\ ;1 i-i
VIEW C-C LliC;i
rigura
Page 4 of 5
SgKVICE BI~LI.ETIN NO. 198A
Carefully drill out all rivets and remove skin that is located on sanle side as the actuator ruppol´•t bracret
assembly. Skin is to be reinstalied on b’im tab Il´•eLr to Figure 2).
NOTE
If cracks extend beyond material to be removed ~ol´•
instnilntiur, of tee ol´• cracks are Found in other areas of i´•ibs.replace I´•ibs
´•I. Drill out and remove existing nutplates From ribs.
5. Rsmo´•e three (31 forward rivets that attach the two (21 ribs together. Do not i´•emovr Liic aft ,ivet irefrr to view
C-C, Figure 21.
6. Using a ,’outer bit, trim forward end olnanges from ribs. Smooth routed edges of ribs with ~400 gl´•it emery cloth
ireEer to Figure 21.
7. Locate, drill and install 440001-RE13 tee an existing ribs using MS20170AD4 rivets irefel´• to Figure 21.
8. Position existing skin, removed in step 3., on trim tab assembly, align all holes and clamp skin in p’ace.
9 Using existing hole pattern in skin, drill lour 0.192 1+0.0021 inch diameter holes in 440001-RE13 tee for
attachment of existing actuator support bracket assembly. Care should be Laren to assure that holes in actuator
support bracket assembly match holes in 440001´•RE13 tee (reEer to Figure 2)
10 Remove skin from trim tab
L1. Drill and install MSZlo71L3 nutplates (4 places) on 440001-RE13 tee using MS20426AD3 rivets trefer to Figure2).
i?. ReineUII .rintlna ´•X,n.n trim Ub vine MSZW70*D9 nrofa ~indial CR9213-.-L Llind n~T. Irabr to F~purp 2)
13 Reinstall existing actuator support braeret assembly on trim tab using existing hardware il´•efel´• tu Figure 21.
14 Repaint elevator trim tubs as necessary
L5 Reinstall existing trim tab on elevatoi´• as outlined in the applicable Ail´•plane Maintenance Manual
is Cheer rigging olelevator trim tabs as outlined in the applicable Airplane Maintenance Manual.
17 Fill out and mail Compliance Card specifying that Part II has been accomplished
ELECTRICP~L LOAD: NO CHANGE
WEIGHT AND BALPINCE: NO CHANGE.
SPARES AFFECTED: NO,
PUILICC\TIONS AFFECTED: The Lllustl´•oted Parts Catalog ebangr re~uilpd by this document will be incorpo,arcd at
the next scheduled revision.
RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service Bulletin No.
198A, dated 3 July 1985, entitled Trim Tub inspection and Modification", Ps,´•t I accomplished d~Part 11 accomplished idatel
Page 5 of5
I
B~Q seaini-llerosg~cle
SERVICE BULLETIN NO, 200
28 March 1984
MODIFICATION OF
NOSE GEAR STEERING COMMAND POTENTIOMETER INSTALLATION
MODELS AFFECTED: MODEL 6900, SERIAL NOS. 11729, 11131 AND 11732.
MODEL 690D, SERIAL NOS. 15021 THRU 15032 AND 15037.
MODEL 695A, SERIAL NOS, 96053 THRU 86061, 96063 THRU 96069, 96072, 96075, 96078,96085 AND 96088.
REASON FOR PUsLICATION: M PREVENT LIMITED RUDDER CONTROL AND FALSE TURN SIGNAL IF THE
NOSE GEAR STEERING COMMAND POTENTIOMETER ROD SHOULD BECOME
JAMMED,
COMPLIANCE: WITHIN NEXT TWENTY-FIVE (25) HOURS TIME IN SERVICE
MOTE
LF ANY PROBLEMS ARE ENCOUNTERED WHILE
COMPLYING WITH THIS SERVICE BULLETIN,
C CONT~CT YOUR NEAREGI~ 00LISTRE*M
COMMANDER AUTHORIZED SERVICENTER.
BY WHOM WORK WILL sE P.CCOMPLISHED: A P MECHANIC OR PBUIVALENT.
APPROVAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED
ESTIMATED MAN HOURS: ONE (1) IIOUR.
PARTS DATA: PARTS REBUIIIED TO COMPLY WITH THIS SERVICE BULLETIN MAY BE PROCURED
THROUGH YOUR NEAREST GULPSTREAM COMMANDER AUTIIORTZED SERVICENTER POn 83.68.IIEPEPIBNCF. THIS SERVICE BULI.ETIN, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN
ORDERING SERVICE BULI.ETIN NO, 200 KIT CONSISTING OF THE FOLLOWING:
PliiD IY4~1 ID (n´•n0´• lilhDYI
~TY PART NO. DESCIIIPTION
t ea. 790348-11 Clamp2 ea. ANOGOI)LO Washer
1 ea. Compliance Card
1 ea. Service Builetin Na. 200 InJtruetions
SPECIAL TOOLS: NONE
ACCOMPLISHMENT INSTRUCTIONS:
1. Gain access to nose gear.teering command patontiometcr, located in nose section, through lower forward nose
access door (refer to Figure 1).
2. Apply tape to bath ,´•udder cable and potenliometcr rod, just below and against existing clamp rssembly. Lo .Issul´•e
that cliln,p assembly is rcinstalicd in same position on potentiometer rod and rudder cnble ~rom which it was
removed iro(er to FiEure ii.
9. Remove ciamp assembly attaching hardware and discard existing AN964D10L washers only
Page 1 of 3
SERVICE BULLETIN NO. 200
I 1LEAVE OPEN
EXISTING IOLT
nND NUT IREFI
POTENTIOMETERSHAFT (REF)
EXISTING
RUDDER CABLEANIB0D10WASHER (REF)
780)48´•11
CLAMP IREFLA
VIEW A-AEXISTINGCLAMPASSY
(REF)
790548´•11 CLAMPEXIGTING
BRACKET ASSY
IREFLAPPLY TAPE TO RUDDER CABLE ANDPOTENTIOMETER ROO PRIOR TO REMOVINGCLAMP assv
EXISTINGRUDDER CABLE
IREF)
EXISTING NOSE GEAR
COMMAND POTENTIOMETERIREFI
VIEW LOOKING FORWARDREMOVE THIS ACCESS
AT R IG HT SIDE DOOR TO GAIN ACCESSTO COMMAND POTENTIONETER
Filun I.
Page 2 oI 3
SEHYICB BULLETIN NO. 200
C R.iyrtsa .rl.sne.lsmr and 790918´•11 ebmi~ on rod ~nd mdd.r.kll. u.ng.*ating
bolts, AN960D10 washers (under nuts) and existing nuts. Assure that bottom of existing clamp assembly and
700348-11 clamp align against tape applied to potentiameter rod and rudder cable per step 2. Torque bolts 20
to 25 inch-pounds and remove tape (refer to Figure 1)
NOTE
Rudder cable is to be muted between 790548-11 clamp and
sn side of existing clamp assembly. Leave hole open in
existing clamp assembly where rudder cable was routed.
6. Functional check nose gear steering system and rudder travel limits.
6. Reinstall lower forward nose access door using existing hardware
Fill out and mail Compliance Card.
ELECTRICI\L LOAD: NO CHANGE.
WEIGHT AND BALANCE: NO CHANGE.
SPARES PIFFECTED: NO.
PUBLICATIONS PIFFECTED: The Illustrated Parts Catalog change required by this document will be incorporated at
the next scheduled revisian.
RECORD COMPLIANCE: Make an appmpriate entry in airplane maintenance records as follows: Service Bulledn Na.
200, dated 28 March 1984, entitled "Modifieation of Nose Gear Steering Command Potsntiometer Instellation~’,
accomplished (date)
C
page 8 of 3
c Se~ce ~B1Beain GulfstreamAerospace
SERVICE BULLETIN NO, 201
11May 1984
ENGINE ISOLATOR ASSEMBLY INSPECTION AND/OR REPLACEMENT
YODELS AFFECTED: A. MODELS 690 AND 690A, SERIAL NOS. 11001 THRU 11284 WHICH HAVE HAD
ENGINE ISOLATOR ASSEMBLIES REPLACED AFTER JULY 28, 1975.
B. MODEL 690A, SERIAL NOS. 11285 THRU 11344
MODEL 6B0B, SERIAL NOS. 11350 THRU 11566.
MODEL 690C, SERIAL NOS. 11600 THRU 11732.
MODEL 690D, SERIAL NOS. 1SO(I1THRU 16033 AND 15037.
MODEL 695, SERIAL NOS, 95000 THRU 96084.
MODEL 696A, SERIAL NOS, 86001 THRU 96061, 96063 THRU 96072, 96075, 96078,98085 AND 96088.
REASON FOR PUBLICATION: SOME BARRY WRIGHT CORP. ENGINE ISOLATOR ASSEMBLIES HAVE A
MANUFACTURING DEFECT WHICH COULD PREVENT PROPER BOLT
PRELOAD AND RESULT IN PREMATURE FATIGUE FRACTURE OF ISOLATOR
ASSEMBLY THRU-BOLT.
COMPLIANCE: PART I INSPECT AND CHECK ENGINE ISOLATOR ASSEMBLIES USING SPECIAL CHECK
TOOL WITHIN NEXT TEN (10) HOURS TIME IN SERVICE.
PARTII- IF INY ISOL^TOR ISSE~WLY THRVBOLT IB PR*CTVR.O. REPLACI ALL
THREE (3) FORWARD ISOLATOR ASSEMBLIES ON THAT ENGINE PRIOR TO
NEXT FLIGHT.
IF ISOLATOR ASSEMBLY ON RIGHT SIDE OF EITHER ENGINE IS FOUND TO RE
DEFECTIVE. REPLACE THAT ISOLATOR ASSEMBLY PRIOR TO NEXT FLIGHT.
IF MORE ~HAN ONE (1) ISOLATOR ASSEMBLY IS FOUND TO BE DEFECTIVE ON
AN ENGINE, REPLACE DEFECTIVE ISOLATOR ASSEMBLIES ON THAT ENGINE
PRIOR TO NEXT FI.IGHT
IF UPPER ISOLATOR ASSEMBLY ONLY OR LEFT ISOLATOR ASSEMBLY ONLY IS
FOUND TO BE DEFECTIVE:
(1) REPLACE ISOLATOR ASSEMBLY PRIOR TO OR AT ENGINE HOT SECTION
[NSPECTION IF AIRPLANE HAS LESS THAN 1850 HOURS TIME IN SERVICE.
(2) REPLACE ISOLATOR ASSEMBLY AT NEXT 100-HOUR INSPECTION IF
ENGINE HOT SECTION INSPECTION HAS ALREADY BEEN ACCOMPLISH OR
AIRPLANE HAS MORE THAN 1860 HOURS TIME IN SERVICE.
NOTE
IF ONLY UPPER OR LEET ISOLATOR ASSEMBLY IS
FOUND TO BE DEFECTIVE, NOTE IN AIRFRAME LOD
BOOK (SPECIFY TIME) WHEN ISOLATOR ASSEMBLY
MUST BE REPLACED AS N(Y~ED PER COMPLIANCE.
IF ANY PROBLEMS ARE ENCOUNTERED WHILE
C ooMPLYINO ~nTH THIS S&IIYICI BVLLETIN.
CONTACT YOUR NEAREST GULFSTREAM
COMMANDER AUTHORIZED SERVICENTER.
Page t of 11
SERVICE BULLETIN NO. 201
s~WHo.WDRKWIILBE*CCOMPL16l(e.; B P MECH*NIC OR EQUIv*LENT i*N *PPROYED CGULFSTREAM AEROSPACE SERVICENTER IS RECOMMENDED).
APPROVAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED.
ESTIMATED MAN HOURS: PART I INSPECT ISOLATOR ASSEMBLIES ONE (1) HOUR.
PART II REPLACE ISOLATOR ASSEMBLIES TEN (10) HOURS PER ENGINE
PARTS DATA: ENGINE ISOLATOR ASSEMBLIES REQUIRED TO COMPLY WITH PART II OF THIS SERVICE
BULLETIN MAY BE PURCHASED THROUGH YOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED
SERVICENTER USING NORMAL PARTS ORDERING PROCEDURES. A FULL CREDIT, BOR ENGINE ISOLATOR
ASSEMBLIES THAT WIRE FOUND TO BE DEFECTIVE, WILL BE ISSUED UPON RECEIPT OF A PROPERLY
EXECUTED WARRANTY CLAIM, DEFECTIVE ISOLATOR ASSEMBLIES AND A COMPLIANCE CARD.
SPECIAL TOOLS: GULFSTREAM AEROSPACE SERVICENTERS HAVE ENGINE ISOLATOR ASSEMBLY CHECK
TOOL PART NUMBER 9348-1. IT WILL BE NECESSARY TO FABRICATE A SPECIAL TOOL
FOR REMOVAL AND TORQUE OF BOLTS (REFER TO FIGURE 3).
ACCOMPLISHMENT INSTRUCTIONS:
PART I INSPECT ENGINE ISOLATOR ASSEMBLIES.
i. Remove upper and lower cowling shells from left and right engines.
2. Using a flashlight and an inspection mirror, eheek isolator assembly brackets to determine if the isolator
assemblies are manufactured by Barry Wright Corp, or Lord Mfg. Co. Barry brackets are identified with raised
letters and Lord. braeketa are identified by ink stamped letters (reBr to Figure 1).
3. If all engine isolator assemblies are manufactured by Lord Mfg. Ca., preceed to step 11.
4. If all engine isolator assemblies are manufactured by Barry Wright Corp., proceed to step 6.
i. If ~in an.n. ia f~u.d is have irma~F a~ambim in.laiied tbar era not dl ~rom the lams.endm .ilher the BeFEl
or the Lord isolator assembly(s) should be removed and replaced, per Part II of this Service Bulletin, to assure
that all isolator assemblies on that engine are ham the same vendor.
6. Visually check to see if isolator assembly thru-bolt is broken.
Using engine isolator cheek tool PIN 9348-1, inspect upper and both side engine isolator assemblies by checkinghow far the isolator assembly thru-bolt protrudes through the aft end of isolator assembly (refer to Figure 2).
8. If any isolator assembly thru-bolt is found to be broken, cheek all engine mount support structure for damage
and check for possible damage to oil filter housing or engine hard lines, remove and replace as necessary. Fill
out and mail Compliance Card specifying that Part I has been accomplished, whet was found and proceed to Port
II and replace all engine isolator assemblies an that engine.
NOTE
Note on the Compliance Card the location of broken thru-
bolt (ieft or right engine on left side, right side or upper)and specify hours in service on part and airplane if
different.
9. If all engine isolator assemblies are found to be geeeptable, apply a 060-inch mart (dot), using white aorylic
point (or equivillent) on aft end of isolator assemblies near cast.llated nut as shown on Figure 2. Proceed to step11
10. If any engine isolator assembly thru-bolt checks No-Do (eontaets check tool), refer to Part II Compliance, an Page
1, and proceed to Part II as required.
11. Reinstall upper and lower eowling shells on left and right engines.
Page 2 of 11
SERVICE BULLETM ND. 201
ENGINE UPPER MOUNT RACK OF ENGINEIREFI GEAR CASE
IREFIA
IREF, eRncKET
O IREFI
BRACKET
IREF) O
SAFETYWIRE Yo) (oY
A VIEW A-A
UPPER ISOLATOR ASSY
IREF)
ANCHOR IREF)
STRUT ASSYS
IREFI *011
LORD BRACKETS SHOULDsE IDENTIFIED WITH
VENDOR NAME PRINTEDON BRACKETS.
aoE MOUNTS
ITYPL IREFI
LORD SIDE ISOLATOR ASSYS
WVESHOULDERONTHRU´•BOLTS
(REFI
InEFI
O
SIDE 1SOLATORIREFL
WIRE
O
PACK OF ENGINE -appnoxlMnrE
GEARCASE LOCATION
B ’AE" VIEW 8-B
LORD ISOLATOR ASSY IDENIIFICATION
~iours 1. ISh´•´•tl of
Page S of 11
SERVICE BULLETIN NO. aal
UPPER 16OLATOR ASS_Y ,BACK OF EN(IINE
GEAR CASE
IRE FL
(REF)
BRACKET
111661 ~P)V(O/) E~:O)~(OOR
0) yo) \(q
SAFETYWIRE LocnnoN
ENIIINE UPPER MOUNT
IREFI C VIEW C-C
IRE Fl
ASSYS
IREFI
*011
BARRY BRACKETS SHOULDBE IDENTIFIEO WITH VENDOR
NAME IN RAISED LETTERS.
ENOINEgDEBARRY 6161 ISOLATOR ASSYS
MOUNTRAVE FLAT AREA ON BOTH
(REF)61DE8 OF THRU´•BOLT.
BACK OF ENGINE
GEAR CASEIREFI
RETAINER
Illm
s~LTlnrrl
;j BRACKET
IREF)
/,,,,,,,,,IM,,,m LOCATION
SAFETY
SIDE WIRE
A6EY IREFI D ~L´• VIEW D-D
BARRY ISOLATOR ASSY IDENTIFICATION
Plpurs i. (Sh´•´•l 2 ol 2)
Page 4 of 11
SERVICE BULLETIN NO, aol
12. Fill out and mail Compliance Card specifying that Pert I has been accomplished and what type of isolators are
installed on engines (Barry or Lord)
NOTE
Note on Compliance Card if Part II needs to be Compliedvlth.
PART II REPLACE ENGINE ISOLATOR ASSEMBLIECI.
i. To replace side and upper isolator assemblies, proceed as follows (refer to Figure 4).
NOTE
To replace only the upper isolator assembly, proceed to step
a Disconnect batteries.
b Remove upper and lower cowling shell, from engine.
c. Remove propeller spinner dome, drain Lines ham lower cowl support end (manifold gang drain) and Lower
cowlingsupport.
d. Install "A" frame sling an propeller and position lack stand under aft end of engine to support engine
during engine isolator assembly removal.
e Disconnect bleed air line from engine firewail and disconnect electrical cables from starter-generator.
f Disconnect any hose assemblies or tube assemblies that may restrict side or forward movement of engine
of approximately one (1) inch. The following item. may have to be removed to facilitate the approximateone (i) inch movement of engine:
(1, Wing ice light.(2) Starter-generator inlet duct assembly to allow for wrench movement.
(9) Engine case negative line and raw pressure lines and flttings on engine.(4) Px and Py lines on engines with Bendix Fuel Control Units.
(5) P3 line to inlet sensor.
(6) Fuel 8lter lines on engines with Bendia Fuel Control Umta.
g. Remove bolts that attach upper isolator assembly retainer plats;ta upper engine mount and remove bolts
that attach upper isolator assembly to engine gear osse.
h. Remove spindle bolt that attaches side isolator assembly bracket to isolator assembly thru-bolt.
i. Remove screws that attach lett and right beam assembly to nose cowl support ring and engine mount
structure.
j. Remove Lower bolt that attaches aR engine mount to engine.
k. Fabricate a wrench, as required, for removal and installation of bolts that attach isolator assemblybrackets to engine gear case (refer to Figure 3 for a typical tool outline).
i. Cut safety wires and remove bolts that attach side isolator assembly brackets to engine gear case.
m. Remove bolts that attach aide isolator assembly retainer to side engine mounts.
Page 5 of 11
BERYICE BULLETIN NO. aol
ISOLATOR AasvIREFI
MOUNTCHECnTOOL
Q (REFI
APPLY LI(IHT PRESSURE
WITH INDEX FINGER TOWING NUT AS MAINTAIN POSITIVE
NECESSARY TO ROTATEHANDLE WHEN INSERTIN(I
TOOLCONTACTTO
CHECK TOOL THRU *FT ISOLATOR ASSY SURFACE
OPENING IN MOUNT
IF COTTER PIN iS BENT OVER
END OF BOLT. REBEND COTTER
pin OVER SIDE OF BOLT.WITH BOTH LEGS OF CHECK TOOLFIRMLY AGAINST BASE OF ISOLATORCOTTER PINASSY. CHECK TOOL MUST PASS OVEREND OF ISOLATOR ASSY THRU%OLT
WITHOUT TOUCHING. U6E INSPECTIONMIRROR TO VERIFY.IF CHECK TOOL
END OF BOLT.ISOLATOR ASSY
MUST BE REPLACED. PER PART II.
PAINT WHITE DOT IMIN. 0.504THISAREA. IT MUST BE VISIBLEWHEN ISOLATOR 1\SSY iS INSTALLED
IN ENGINE MOUNT.
*011
DO NOT CHECK TOROUE OR
DISTURB NUT ON THRU-BOLT.
Figure 2.
BageBofll
SERVICE BULLETIN NO. 201
CAUIK)N
When pulling engine forward, assure that engine is
properly supported by propeller sling and jack stand to
prevent any damage to engine or equipment.
n. Pull engine forward, approximately one (1) inch, and push to side to facilitate removal of isolator
assemblies.
o Prior to installing new isolator assembly(s). assure that isolator assembly has a white dot painted on
aft end (refer to Figure 2).
NOte
if white dot is not an isolator assembly, cheek isolator
assembly with 9948-1 check tool to assure that isolator
assembly is acceptable. If acceptable, paint a dot on isolator
assembly, as shown in Figure 2.. using white acrylic paintor equivalent prior to installing on engine.
T;n’;n~"lCI\VTION
When removing and installing an isolator assembly, care
should be taken so 88 not to scratch inside surface of enginemount. Do not use a petroleum base mold release when
inserting isolator assembly in engine mount.
p Remove and replace isolator assemblies, as required, one at a time. Apply mold release (or equivalent)to isolator assembly or inside surface of engine inserting isolator assembly into
engine mount.
1~1cnurlou
When tarqueing bolts that attach isolator assemblybrackets to engine gear case, using fabricated wrench, refer
to Figure 8. for torque value calculations.
q. Reinstall side isolator brackets on engine gear case usmg existing hardware. Torque bolts and safetywire (refer to Wgurea 0 and 4).
r. Reinstall side isolatar assembly retainers on side engine mounts using existing hardware. Torque bolts
as shown in Figure 4.
s Reinstall bolts that attach upper isolator assembly plate to upper engine mount. Torque bolts as shown
in Figure 4.
t. Push engine back into position and install existing hardware that attaches aR eng~ne mount. Finger
tighten bolt only.
u. Install spindle bolt that attaches side isolator braelrets to isolator assembly thru-bolt, align and then
install bolts that attach upper isolator assembly to engine gear osse. Torque bolts and safety wire (refer
to Figures 3 and 4).
NOTE
Torque lower bolt on aft engine mount 160 to 190 inch-
pounds.
v. R8install screws that attach left end right beam assemblies to nose oowl support ring and engine mount
structure
Page 7 of 11
SERVICE BULLETIN NO. 201
CUT BOX fND WRENCH OFF
I\ND WELD A PIECE OF 0.250"
THICISTEEL PLATE TO0.250" STEEL PLATE WRENCH.
BOXEND
WRENCH
IcO.BZS..
MnKECurOUrro
TOROUE WRENCH DRIVE0.576" ALLEN SOCKET
WRENCH1)011!
IT IS ADVISABLE TO
HEATTREATWRENCHFOR LONG TERM USE
i. INSERT ALLEN WRENCH IN BOLT HEAD.
2. POSITION BOX ENDWRENCH OVER ALLEN WRENCH.
3. INSERTTOROUEWRENCH DRIVE SOCKET INTOCUTOUT
IN BOTTOM OF FABRICPITEDWRENCH.
BOLT
WRENCH
FORMULA FOR FIGURING TOROUE
r-x_ VALUES UEINO EXTENSION ON WRENCH
LwT1~400
GLw
5.01’ T1-450
4 i/ r, ..,,,,,,,,,,,E WRENCH READING
FOR PROPER BOLT TOROUE.
TZ.MAXIMUM TOROUE WRENCH READING
FOR PROPER BOLT TOROUE.
X 3 ANGLE BETWEEN CENTERLINE
OFTOROUEWRENCHANDFABRICATEDWRENCH.
LwIF X.00. THEN 4 Lw tP’.
Lt DISTANCE FROM MIDPOINT OF
TOROUE WRENCH HANDLE IALON(IWRENCH THE WRENCH) TO POINT EVEN WITH
BOLT.
Lw C DISTANCE FROM MIDPOINT OF
HANDLE TO CENTERLINE OFMIDPOINTOF TOR(IUEWRENCHW)CI(ETHANDLE
CENTERLINE OF
TOROUEWRENCH
LwTO OBTAIN MINIMUM ALLOWABLE READING ON TOROUE WRENCH.MULTIPLY 408 IN´•LBS
lwTO OBTAIN MAXIMUM ALLOWABLE READING ON TOROUE WRENCH. MULTIPLY 450 IN´•L88x
ligur´• 3.
Page B of 11
SERVICE BULLETIN NO. 201
w. Reinstall any hose assemblies tube assemblies or equipment that may have been removed ordisconnected in order to move engine forward.
x. Assure that electrical cable connectors are cleaned and then reconnect electrical cables to stsrter-generator and rec~nnect batteries
Y´• Reinstall lower cawl auppart and drain lines.
rr Remove ding from propeller and removejack stand from aft end of engine,
as. Reinstall spinner dome an propeller using existing hardware and proceed to step 3
2 To replace only the upper isolator assembly. praceed as follows (refer to Figure 4):
a. Remove upper eowling shell from left andlor right engme.
b: Disconnect clamps from upper engine mount strut assemblies Wat support hose assemblies and electricalcables.
c. Mark location of fire deteetars (if installed), located on upper engine mount strut assemblies loosenclamps and lay f,re detectors out arthe way.
d. Remove safety wire and remove bolts that attach upper isolator assembly bracket to engine gear ease
e Remove bolts that attach engine mount strut assemblies to strut anchors (refer to Figure 4).
cnurlow
When removing upper engine mount strut assemblies,assure that rod ends and lamb nuts are not disturbed whichcould affect We adjustment of strut length.
f Remove upper engine mount, isolator assembly and engine mount strut assemblies, as a unit, fromengine.
6´• Remove baits, through plate, that attach upper isolator assembly to upper engine mount and removeisolator assembly. Assure that barrel nuts and looking devices are still in place in engine mount.
b. Prior to installing new upper isolator assembly, assure that isolator assembly has a white dot paintedan aft end (refer to Figure 2).
NOTE
If white dot i, not on isolator assembly, cheek isolatorassembly with 9548-1 oheck tool to assure that isolatorassembly is acceptable. If acceptable, paint a dot an isoiatar
assembly, as shown in Figure 2, using white acrylie paint(or equivalent) prior to installing on engine.
install new isolator assembly in upper engine mount using existing hardware. Align bracket and enginemount as required and Lighten bolts to hold in alignment.
i Reinstall upper engine mount, isolator assembly and engine mount strut assemblies on strut anchorsusing existing hardware.
k. Reinstall bolts that attach upper isolator assembly bracket to engine gear ease. Torque bolts and safetywire (refer to Figures 9 and 4).
i. Attach existing hose assemblies and electrical cables to engine mount strut assemblies using existinghardware and clamps.
Page 9 of 11
SERYICE BULLETIN NO. 201
UPPERENGINEMOUNT
PLATE
REMOVE THISBOI.T.WASHERAND NUT
TOROUE BOLT310980 IN´•LBS
ROD ANCHORISOLATOR
ASSv I nFT ENGINE MOUNT
iORoUE BOLT I ~6n 1 -C5nl ,TOROUE BOLT
(IOOaOD IN´•LBS 180´•1801N´•LBS
AND SAFEN WIRE
SUPPORT RIN(I
smurnssvsMauNTNOSE
TWO 12) SCREWS
REMOVE TWO 121 SCREW8 IZPLB)
ATTACHING BEAM ASSY
TO NOSE COWL SUPPORT EN(IINE
RING 12 PLSI
BEAM ASSY
SIDE ISOLATOR
TOROUE BOLTi
400´•500 IN´•LB~AND SAFETY WIRE
BRACKET g j V LEFT ENGINE MOUNT
Q
REmlNER
THRU-BOLTTOR(IIIE BOLT
SPINDLE BOLT 3505801N´•L88 no´•rr
TOA(1UE450´•6WIN´•LBS LEFTSHOWNAND ~FETYWIRE RIGHTOPPOSITE
(BARRY)
Pi8ura 4.
Page 10 of 11
SERVICE BULLETIN NO. 201
m. Reinstall engine fire detectors on engine mount strut assemblies using existing clamps. Assure that
detectors are installed in same place from which they ware removed.
n. Reinstall upper cowling shell on engine and proceed to step 3.
5. Apply a relect tag on all defective isolator assemblies and note isolator assembly hours in service, airplane serial
number, where engine isolator assembly was located on engine, failed gags test or broken thru-bolt. Assure that
Lag is securely attached to isolator assembly. (This is required if credit for parts is to be given).
4. Fill out and mail Compliance Card specifying that Part II has been accomplished and note on Compliance Card
what isolator assemblies were replaced (left or right engine, upper, left or right) and hours in se~ice.
ELECTRICPIL LOAD: NO CHANGE.
WEIGHT AND BALI\NCE: NO CHANGE.
SPARES AFFECTED: ALL ISOLATOR ASSEMBLIES IN SPARES STOCK MUST BE CHECKED AND IDENTIFIED
WITH A O.LO-INCH DOT USING WHITE ACRYLIC PAINT (OR EQUIVALENT) IF
ACCEPTABLE.
PUBLICPIT(ONS AFFECTED: The Airplane Maintenenee Manual change required by this document will be
incorporated at the next scheduled revision.
RECORD COMPLIPINCE: Malts an appropnate entry in ai~hne maintenance records as follows: Service Bulletin Na
201, dated 11 May 1884, entitled "Engine Isolator Assembly inspection andior Replacement’: Pert I accomplished(date) Part II (if required) accomplished (date)
Page 11 of 11
Se~ice GulfstreamAerospace
SERVICE BULLETIN NO. 202
15 August 1984
NOSE GEAR STEERING COMMAND POTENTIOMETER ALIGNMENT
MODELS AFFECTED: MODEL 600C, SERIAL NOS. 11727 AND 11729 THRU 11732.
MODEL 690D, SERIAL NOS. 15021 THRU 15033 AND 15037
MODEL 6958, SERIAL NOS. 96055 THRU 96072, 96075, 96078, 96086 AND 96088.
NOTE
IT IS RECOMMENDED THAT SERVICE BULLETIN NO.
200 (1F APPLICABLE) BE ACCOMPLISHED IN
CONJUNCTION WITH THIS SERVICE BULLETIN
REASON FOR PUQLICATION: IMPROPER ALIGNMENT CAUSES FAILURE OF POWER STEERING COMMAND
SIGNAL. WITH SYSTEM ON, AND PILOT HAS NO CONTROL OF STEERING.
COMPLIANCE: WITHIN NEXT TWENTY-FIVE (26) HOURS TIME IN SERVICE
NOTE
IF *NY PKDRLEMS *KE ENC~UNTERED WXILE
COMPLYING WITH THIS SERVICE BULLETIN
CONTACT YOUR NEAREST GULFSTREAM
COMMANDER AUTHORIZED SPRVICENTER.
BY WHOM WORK WILL BE ACCOMPLISHED: A 8 P MECHANIC OR EqUIVALENT
APPROVAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED.
ESTIMATED MAN HOURS: TWO (2) HOURS
PARTS DATA: ONE(1) EACH COMPLIANCE CARD.
SPECIALTOOLS: NONE.
ACCOMPLISHMENT INSTRUCTIONS:
i. Gain access to nose gear steering command potentiometer. located in right fuselage nose section, through lower
forward nose access door (refer to Figure 1).
2. Check parallel alignment of rudder cable and nose gear steering command potentiameter as follows:
a Place rudder pedal in full right position.
b Choose a point of reference on either the rudder cable or the nose geal´• steering command potentiomoter
~od and note measurement of distance between rudder cable and potentiometer rod
c. Place rudder pedal in full left position.
d. Measure distance between rudder cable and potentiometer rad st same point of reference that was chosen
in step b A maximum of0.020-inch misalignment is allowed hem full right to full left rudder position.
Page 1 of3
SERVICE BULLETIN NO. 202
c
P3
REMOVE THIS ACCESS
DOOR TO GAIN ACCESS
TO COMMAND POTENTIOMETER
A --.--i.f
FwopnEssunE
WELL BULKHEADBULKHEAD (REF)
(888)
TO ACHIEVE PARALLEL RE(IUIREMENTS.SHIM AS REO’D BETWEEN BRACKET
ASSv AND POTENTIOMETEH. ATTACH
SH(M TO BRACKET nSSY WITH A
MINIMUM OF ONE (1) No´• 3 FLUSH
snacKETassv ii R’VET. RIVET SHALL NOT INTER-
FERE WITH INSTALLATION DO NOTEXISTING
ATTACH SHlM TO POTENTIOMETER.RUDI)ER CABLE
(REFI
CABLE I\NO ROD RUN PARALLEL TOEXISTING NOSE
PREVENT DAMAGE TO POTENTIOMETERGEARCOMMANDPOTENTIOMETER
//I I1(nEF)RUODERCABLE
(REF) iicEan
COMMAND POTENTIOMETER
C~TO I\CHIEVE P~RI\LLEL ci~inOF BRACKET ASSY WITH CONTROL
CABLE. 8HIM AS AEO´•D nT TOp on
BOTTOM. ATTACH snlM To BRACKET EXISTING
WITH A MINIMUM OF ONE (1) NO. 3 BRACKET ASSY
FLUSH AIYET. RIVET SHALL NOT (nEF)INTERFERE WITH INSTI\LL~TION
VIEW LOOKING FORWARD VIEW LOOKING INBOARD
AT RIGHT SIDE jFigure
PaCe2ofS
SERVICE BULLETIN NO. 202
e. If rudder cable and potentiometer rod are not parallel or exceed 0.020-ineh dimension noted in step d.
C ’isting brarlrat ~asembly ´•a nrluirrd Iul io Oo(amch) Lo miseiignment rref.r b figure
NOTE
Fabricate shims from 2024T3 or 2024114 aluminum sheet
stock.
f if shimming does not achieve a parallel system within tolerance noted in step d., iemove existing bracket
assembly and replace with new 790348´•3 bracket assembly.
3. Actuate putentiomrter rad (by hand) to assure that movement of the potentiometer rad is a smooth continuous
movement during extension and retraction althe rod. Do not lubricate the potentiometer rod.
4. IEpotendameterpotendameter rod binds or has rough spots through stroke, remove and replace existing potentiometer with new
46991A patentiometer
5 Functional cheek nose gear steering, system as outlined in Chapter 32 of the Airplane Maintenance Manual.
6 Heinstall lower forward nose access door using existing hardware.
Fill out and mail Compliance Card.
ELECTRICAL LOAD: NO CHANDE.
WEIGHT AND BALANCE: NO CHANCE.
SPARES AFFECTED: NO.
CPUBLICATIONS AFFECTED: The Airplane Maintenance Manual change required by this document will be incorporated
at the next scheduled revision.
RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service Bulletin
No. 202, dated 15 August 1984, entitled "Nose Dear Steering Command Potentiometer Alignment", accomplished
rdate)
C
rage 3 of3
C~IIService Bulletin GulfstreamAerospace
SERVICE BULLETIN NO 203
8 February 1985
INSPECTION AND REPLACEMENT OF COLLINS AP-106 AND AP-107AUTOPILOT CAPSTAN ASSEMBLIES
MODELS AFFECTED: A. THE FOLLOWING MODELS WITH FACTORY INSTALI.ED hP-106 AUTOPILOT.
MODEL 690C. SERIAL NOS. 11728 AND 11730 THRU 11732.
MODEI. 690D, SERIAL NOS. 15017. 15019, 15021 THRU 15025, 15027. 15029, 15031.15093 AND 15057
MODEL 695A. SERIAL NOS. 96043, 96045 TRRU 96048, 86050 THRU 96055. 96059,96061, 96064. 96068 AND 96072.
R. THE FOLLOWING MODELS THAT HAVE EITHER REPLACED CAPSTANS,BETWEEN I OCTOBER 1982 AND 8 FEBRUARY 1985, ON THEIR AP-106 OH AP-107AUTOPILOT OR HAVE HAD AN AP-106 OR AP-107 AUTOPILOT INSTALLED.BETWEEN 1 OCTOBER 1982 AND 8 FEBRUARY 1985, BY A SOURCE OTHER THANTHE FACTORY:
MODEL 100, SERIAL NOS. 10001 THRU 10032.MODEI. 690A, SERIAL NOS. 11100 THRU 11344.
MODEL 690C, SERIAL NOS. 11600 TBRU 11721ANI) 11729.
MODEL 690D, SERLAI. NOS 16001 THRU 15016. 15018. 15020, 16088, 15028, 15030AND 15032.
MODEL 695. SERIAL NOS. 95000 THRU 95084.MODEI. 69SA. SERIAL NOS 96001 THHU 96042. 96044, 96049. 96057, 96058, 96060AND 96066.
REASON FOR PUBLICAT1ON: CERTAIN CAPSTAN ASSEMBLIES IN COLLINS AP-106 AND AP-10? AUTOPII.OTINSTALLATIONS ARg SUBJECT TO CORROSION WHICH COULD CAUSE THEFRICTION SI.IP CLUTCH TO SLIP AT A HIGHER THAN NORMAL TORqUE ORELSE NOT SI.IP AT ALL REFER TO COLLINS 334C-9Aill SERVICE BULLETINNO 2 (KF.VISION NO. II AND 3341)´•6( i SERVICE BULLETIN NO. 11(REVISIONNO, ii.
COMPLIANCE: INSPECTION WLTLIIN NEXT TWINTY-FIVF:(211 HOURS 1´•LME IN SERVICEREPLACEMENT REFER TO STEP 5. PAGE 4.
NOTE
IF ANY PROBI.BMS ARE ENCOUNTERED WHILE(:OMPLYING WITII THIS SERVICE BULLETIN.CONTACT YOUR NEAREST DUI.FSTREAMCOMMANDER AUTHORIZED SIRVICENTER.
8Y WHOM WORI( WILL sE *CCOMPLISHED: INSPECT CAPSTAN ASSEMBLIES A L P MECHANIC OREQUIVAI.ENT
REMOVAI. AND REPLACEMENT OF CAPSTAN ASSEMII1.LRSAN AUTHORIZED COLLINS AUTOPILOT INSTALLATION ANL)
j;
RerAms*crr.pru
--*PPROVPIL: ENGINEERING IIESIGN ASPECTS ARE FAA APPROVED.
Page 1 oT4
SERVICE BULLETIN NO. 203
INIPECTC*PST*N I199EMBLIES-TWO I1)HoUHS
REMOVE ANI) REPLACE CAPSTAN ASSEMBLIES REFER TO PARTS DATA FOR
TIME ESTIMATE.
PARTS DATA: AF.I’LACEMENT CAPSTAN ASSEMBLIES IF REQUIRED, MAY DE OBTAINED ON A NO
CRARGI WARRANTY EXCHANGE BASIS BY CALLING COLLINS ATLANTA FACTORY SERVICE CENTER AT
1401) 996-5406, ~PELEX: 64´•2259 COLLINSRAD ATL TO THE ATTENTION of MR DEE ATWOOD. UPON
COMI1I.ETLON OF THIS SERVICE BULLETIN, THE ORIGINAL UNITS IAFFECTED CAPSTAN ASSEMULIESI
MUSP BE IIE1’IIRN~D (WITHIN TnFE UNITED STATES, SHIP FEDERAL EXPRESS STANDARD AIR COLLECT OR
INTBKNI\’I‘IONI\L1.Y. SHII’ AIll FREIGHT COLLECTI TO COLLINS ATLANTA FACTORY SERVICE CENTER. II
SUSI’ECT UNITS ARE NOT RETURNED WITHIN 15 DAYS 130 DAYS INTERNATIONALLYI OF THE SHIPMENT
OF’rHE WARRANTY EXCHANGE UNITS. THE AIRCRAFT OWNEKIOPERATOR WILL BE BILLED FOR THE
EXCHANGE UNITS THIS OFFER OF NO CHARGE WARRANTY EXCHANGE WILL EXPIRE 1 JULY 1985.
CO1.LINS AVIONICS WILL PROVIDE UP TO TWO (21 HOURS PER UNIT ICAPSTANI FOR REMOVAL AND
REPI.ACEMENT BY AN AUTHORIZED COLLINS DEALERISERVICE AGENCY REFERENCE AIRORAW MODEL
AND FACTORY SERIAL NUMBER WHEN ORDEKIND CAPSTAN ASSEMBLIES. FOLLOWING IS A GULFSTREAM
AEROSPACE CORP. CERTIFICATION APPROVED LISTING, BY MODEL AND SYSTEM POSITION, OF THE
CAPSTAN ASSEMBLY PART NUMBERS:
GUI.FSTREAM AEROSPACE CORP. CAPSaN ASSEMBLY PARTS LISTING
MOL)$I. AII.ERON ELEVATOR RUDDER ELEVATOKTRIM
700 618-5973-002 618-5973´•002 618-5973-003 618-5957-001
6904\ 618´•5973-002 618´•5873´•002 618-5913´•003 618-5957-001
fi(MR 618-59731-002 618-5973-002 618-6913-(103 618-5917-001
69(1(: 6L8-5973-003 6L8-5973´•002 618-5913-003 618´•5957-001
GOOC 618-5Ln3´•0113 618-5973-002 618-6913-003 618-6957-001
B~il (ilS-5975-003 618-5973-002 618-5973-008 618-5957-001
68Bn filX-59?S´•OO3 618-5913-002 618-5978-003 618-5967-001
SPECIAL TOOLS: REFER TO COI.I.INS B54C-9Alll SERVICE BULLETIN NO 2 IREVLSION NO I)AND 331113-6( 1
SERVICE DULI.B1‘IN NO. IltHEVISION NO. II.
ACCOMPLISHMENT INSTRUCTIONS:
NOT6
Only the eapstan nssemhlics are to be replaced. Originalservo ilssemblics are to be retained for reinslnllntion.
I Cain ;I.usJE to oilen,n, elevator. ruddel´• and elevator trim autopilot capston sssomblies. Refer to applicnblrC~,llinl Sol´•vice Info,.miltion Letter for ;Ippmximute loa,tion of eapatnn assemblies in airplane (rrfel´• to Figul´•eII.
MOI)I1L COLLINS PUBLICATION
700 SERVICE INFORMATION I.ETTER 5-78 (REV !)For AP-107
6~OA SERVICE LNI?ORMATION LETTER 11-14 tKEV 4) Far AP-106
69011 SERVICE INFORMATION I.E~EK 11-14 (REV 4) For AP-106
6Y0C SERVICE INFORMATION I.E~IR 3-80 (REV 1)For AP-106
6901) SERVICE INFORMATION LETTEH 1-81 (REV 4)For AP´•1O(I
695 SgllVICF. INFORMATION LET~ER 8-80 IRIV 1) Far AP-1OB
6984\ SERVICE INFORMATION LE1TER 1´•81 (REV 4) Far AP-106
Figure I.
2. Inupoct uilrran, elevator, rudder and elevator trim eapstan assemblies br revision letter, loented next to the
purl number, on the edge of capatan mounting plate irefer to Figure 21.
Page 2 oft
SERVICE BULLETIN NO. 203
CnPaaLTRIM TYPICALTRIMCAPSTAN ASSY SERVO ASSY(REF)
INSPECT CAPSTAN ASSYAPPLY WHITE PAINT TO THIS MOUNTING PLATE FOR
AREA ANO INK STAMP SLIP REVISION NUMIIERCLUTCH TORGUE SETnNO
TYPICAL PRIMARY NplcnLpnlMnnvcaPSrAa assY seRvonssv(REF) IREF)
INSPECTCAPSTANAS8YAPPLY WHITE PAINT TO THIS MOUNTING PLATE FOR
AREA AND INK STAMP SLIP REVISION NUMBERCLUTCH TORDUE SETTING
NOTE
i IT MI\Y BE NECESSARY TO USE AN
INSPECTION MIRROR TO LOCATEPART NUMBER AND REVISION LETTER.
Figure 2.
Pageaof 4
SERVICE BULLETIN NO. 203
9 iT th. ..uilan I.Lta. i´• RIV L’(plimoo ro.atnn.l or REV K iLnm eiquUn.) and yaarin.nth and isr~rr RWK(are NOT stamped on the capstan assembly, the capstan assembly must be replaced. Proceed to step 5.
NOTI
Only primary capstan aaaembliss stamped with REV P andtrim capstan assemblies stamped with REV K are the
affected capatan assemblies.
4. If eapstan assemblies are stamped with any revision letter other than those listed in step 3 or are stamped with
the revision letters listed in step 3 but are also stamped with yeadmonth and letters RWK and have the number2 on sel´•vo mad plate marted out, they do not have to be replaced Proceed to step 8.
5. If eapstan assemhlylsl need to be replaced, contact the Collins Atlanta Factory Service Center to schedule the
ilpplapl´•inte quantity of exchange capstan assemblies. If the exchange assemblies will not be received in a timelymannel´•.lnd it is necessary for the airplane to continue operating until capstan assemblies are available, the
airplane owneriopel´•stor must have the break-away torque setting of the capstan assembly safety Friction slipclutch verined by a Collins approved maintenance facility. The airplane can then be returned to normal
ope,´•nting service if the break-away torque is within specified range listed in the applicable Collins ServiceInformation Letter listed in Figure i. This return to service will be time limited and capstan assemblyis) must
still be replaced by 1 July 1985: however, ilthe inspection indicates that a capstan assembly has been partiallycnl´•mded or completely frolen. it is recommended that the airplane be suspended from all night operations untiltbs capstan assembly is replaced.
6. Remove and replace capstan assembly(s) as follows:
a Disconnect and remove control cables fiom copstan drumb Remove servo assembly and capstan assembly from airpfane.
c. Sat slip clutch torque on new capstan assembly(si per applicable Collins Service Information Letterlisted in Figure i.
d Apply white paint on side of capstan assembly and ink stamp slip clutch torque setting on painted area
(reLr to Figure 2).
e l’ag identify capstan assembly(sl with airplane model. airplane serial number and system position(silemn, elevator, rudder or elevator trim) to assure that capstan assemblies are not intermixed priorto installation.
F Remove identifying tag (see step e)and install capstan asesmblyls) on airplane using e*istinghsldware.
g. Inspect and replace any night control cables as necessary.b. Reconnect cables to capston oasembly(s).
Set primary control cable tensions as outlined in the applicable GulFstream Aerospace Corp AirplaneMaintenance Manual.
j. Set bridle control cables as outlined in the applicable Collins Service Information Letter listed in Figure
k. Reinstall existing servo assemblies on capstan assemblies using eristing hardware.
7. Functional check autopilot system.
8. Fill out and mail Compliance Cord Specify the Following on Compliance Card:
a Inspected and Found that capstan assemblies do not need to be replacedb. Inspected and Found that ispecify aileron, elevator. rudder or trim) capstan assemblies need to be
replaced. Compliance will be in accordance with Collins, Atlanta per step 5, page 4
c. Inspected and replaced capston esfiembliel. List quantity of capstan assemblies replaced and systemposition (aileron, elevator, rudder or trim).
ELECTRICAL LOAD: NO CHANGE.
WEIGHT AND BAL*NCE: NO CWANG&.
SPARES*FFECTED: AI.L AFFECTED AP-106 ANI) AP-107 AIITOPILOT CAPSTAN ASSEMBLIES MUST nE
PULLED FROM SHELF STOCK, INSPECTIO ANO REPLACED AS NECESSARY
PUBLICATIONS I\FFECTED: NONE.
RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as Follows: Specify paragraphBu., 8h. or He. of Service Bulletin No 203, dated 8 February 1985, entitled "lnspeetion and Replacement of Collins AP-IOB and AP-IU1 Autopilot Capstan Assemblies", accomplished tdoto)
page I of 4
Senrice Bulletin GulFstreamAerospace
SERVICE BULLETIN NO. 204
8 Frbrusry 1985
INSPECTION AND AEPLACEMENT OF COLLINS APS-65AUTOPILOT CAPSTAN ASSEMBLIES
MODELS AFFECTED: MODEL 695A, SERIAL NO. 96051MODEL 695R, SERIAL NOS. 96063, 96069, 96016, 86018, 96085 AND 96201 THRU 96202.
THIS SERVICE BULLETIN APPLIES TO THE FOLLOWING COLLINS SMT SERVOMOUNTS (CAPSTAN ASSEMBLIES):
COLLINS
PART APPLICABLE TOUNIT NUMBER SERIAL NUMBER
SMT´•GS 622-5755-001 24 thru 51, 261 thru 285,288 thru 304, SO? thru 831,347, 363 and 316.
SMT-6S 622-6135-002 63, 68 thru 77. 80 thru 96,485 thlu 620. 634, 154,136,739, 140,143, 146,149 and 750.
SMT-GSD 622-6411-002 43, (6 thru 48, 60 thru 69,?1 thru 73, 78, 19 and 81.
REASON FOR PUBLICATION: CERTAIN CAPSTAN ASSEMBLIES IN COLLINS APS-BS AUTOPILOTINSTALLATIONS ARE SUBJECT TO CORROSION WHICH COULD CAUSE THEFRICTION SLIP CLUTCH TO SLIP AT A HIGHER THAN NORMAL TORFLUE ORELSE NOT SLIP AT ALL. REFER TO COLLINS SMT-66( SERVICE BULLETINNO. 1(REVISION NO. 1).
COMPLII\NCE: INSPECTION WITHIN NEXT TWENTY-FIVE (26) HOURS TIME IN SERVICE.REPLACEMENT REFER TO STEP 5, PAGE 2.
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILECOMPLYING WITH THIS SERVICE BULLETIN,CONTACT YOUR NEAREST GULFSTREAMCOMMANDER AUTHORIZED SERVICENTIR.
BY WHOM WORK WILL BE ACCOMPLISHED: INSPECT CAPSTAN ASSEMBLIES A d P MECHANIC OR
EQUIVALENT.
REMOVAL AND REPLACEMENT OF CAPSTAN ASSEMBLIESAN AUTHORIZED COLLINS AUTOPILOT INSTALLATION ANDREPAIR FACILITY.
APPROVAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED.
ESTIMATED MAN HOURS: INSPECT CAPSTAN ASSEMBLIES TWO (2) HOURS.
REMOVE AND REPLACE CAPSTAN ASSEMBLIES REFER TO PARTS DATA FORTIME ESTIMATE.
Page I of 3
SERVICE BULLETIN No 204
CHARGE WARRANTY ExcHarraa a*as su C*LLMC COLLINS *TUINT~ ~CToRY BERVICE CENT~R *TPARTS DI\TA: KgPLACEMENT CAPSTAN ASSEMBLIES, 1F RE~UIKED, MAY BE OBTAINED ON A NO
(404) 896´•540G. TELEX: 51-2239 COLLINSRAD ATL TO THE ATI‘ENTION OF MR. DEE ATWOOD UPON
COMPLETION OF THIS SERVICE BULLETIN. THE ORIGINAL UNITS (AFFECTED CAPSTAN ASSEMBLIES)
MUST BE RETURNED IWITAIN THE UNITED STATES. SHIP FEDERAI. EXPRESS STANDARD AIR COLLECT OH
INTERNATIONALLY, SHIP AIR FREIGHT COLLECT) TO COLLINS ATLANTA FACTORY SERVICE CENTER. IF
SUSPECT UNITS ARE NOT RETURNED WITHIN 15 DAYS (30 DAYS INTERNATIONALLY) OF THE SHIPMENT
OF TIIE WARRANTY EXCHANGE UNITS, THE OWNEWOPERATOR WILL BE BILLED FOR THE
EXCHANGE UNITS. THIS OFFER OF NO CHARGE WARRANTY EXCHANGE WILL EXPIRE 1 JULY 1985.
COLLINS AVIONICS WILL PROVIDE UP TO TWO (2) HOURS PER UNIT (CAPSTAN) FOR REMOVAL AND
REPLACEMENT RY AN AUTHORIZED COLLINS DEALERISERVICE AGENCY. REFERENCE AIRCRAFT MODEL
ANI) FACTORY SERIAL NUMBER WHEN ORDERING CAPSTAN ASBEMBLIES. FOLLOWING IS A DULFSTREAM
AEROSPACE COKP. CERTIFICATION APPROVED LISTING, BY MODEL AND SYSTEM POSITION, OF THE
CAPSTAN ASSEMBLY PART NUMBERS:
GULFSTREAM AEROSPACE CORP. CAPSTAN ASSEMBLY PARTS LISTING
MODEI. AILERON ELEVATOR RUDDER ELEVATORTRIM
696A 622-5135-002 622-5735´•001 622-6735-002 622´•6411-002
BSSB 622-5135-002 622-6736-001 622-5736´•002 622´•6411-002
SPECIP~LTOOLS: REFER TO COLLINS SMT-65( )SERVICF. BULLETIN NO. 1 IREVISION NO. 1)
ACCOMPLISHMENT INSTRUCTIONS:
NOTe
Only the capatan assemblies are to be replaced. Originalservo assemblies are to be retained far reinstellation.
1 Gain access to aileron, .I~uatar, ´•udder and Bl.v.tor Vim ~spstan s~xmblra Re(sr ia Collins Sprui..~I
information Letter 3-83 for SCS-65 for approximate location of capston assemblies in airplane.
2. Inspect aileron, elevator, rudder and elevator trim capstan assemblies for serial numbers. The serinl number
is located on the capxlan assembly identification plate (refer to Figure I),
3 if the capstan assemblies have one of the serial numbers affected as listed under "MODELS AFFECTED~’, the
capstun assembly(si must be replaced. Proceed to step 5.
4. If the capatan assemblies are not any of the serial numbers affeotad as listed under "MODELS AFFECTED",
they do not have tu be replaced. Proceed to Step 8.
5. Il eupsten assembly(s) need to be replaced, contact the Collins Atlanta Factory Service Center to schedule the
appropriate quantity of exchange eapstan assemblies. If the elehnnge assemblies will not he received in a timely
manner and it is neceasary for the airplane a continue operating until capstan assemblies are available, the
airplane ownedoperntur must have the break-away torque setting of the capstan assembly safety friction slip
clutch verilied by a Collins approved maintenance facility. The airplane ran then be returned to normal
operating service if the break-away torque is within spsei8ed range listed in the applicable Collins Service
(nfbrmution Letter 5-88 for SCS-65. This return to service will be time limited and Eoptan assembly(sl nlust
still he replaced by 1 July 1985: however, if the inspection indicates that a capstan assembly has been partially
corroded or completely it is recommended that the airplane be suspended from all night operations until
the cnpstnn assembly is replaced.
6. Remove and replace cnpstan assembly(s) as follows:
a. I)isconnect and remove control cables E~am capstan drum.
b. Remove servo assembly and capstan assembly from airplane.
c. Set slip clutch torque on new capstan assembly(s) pr Collins Service Information i.etter 3-83 for SCS-
65. i
Page 2 of 3
SERYICE BULLETIN NO. 204
enpsrahl nSsu
IDENTIFICATIONPLATE IREFI
NPIC~L SERYO
ASSY (REFI
TYPICAL C/\PSTAN
ASSY (REFI
norr
IT M~Y BE NECESE~RY TO USE I\ FLASHLIORT
nND INSPECTION MIRROR TO CHECK SERIAL NUMBERS.
Figure i.
d. Tag identify eapstan assembly(s) with airplane model, airplane serial number and system position(aileron, elevator, rudder or elevator trim) to assure that eapstan assemblies are not intermixed priorto installation.
a. Remove identifying tag (see step d.) and install capstan assembly(s) on airplane using existing
hardware.
f inspect and replace any flight control cables as necessary
g. Rewnneet cables to capstan assembly(s).
h SeC primsn. mntmi cabl. ta~ioos .a ouflind in th. applunbl. O.h~sm h~roalirr. Gory ~rplanE
Maintenance Manual.
i. Set bridle control cables as outlined in Collins Service Information Letter 3-85 for SCS-GS
j. Reinstall existing servo assemblies on capstan assemblies using existing hardware.
Functional cheek autopilot system.
8. Fill out and mail Compliance Card. Specify the following on Compliance Card:
a. Inspected and found that capstan assemblies do not need to be replaced.
b. Inspected and found that (apeeib aileron, elevator, rudder or trim) capstan assemblies need to be
replaced. Compliance will be in accordance with Collins, Atlanta per step 5, page 2.
e. Inspected and replaced capstan aas.mblies. List quantity of capstan assemblies replaced and syetem
position (aileron, elevator, rudder or trim).
ELECTRICAL LOAD: NO CHANGE.
WEIGHT ANI) BALANCE: NO CHANCE.
SPARES AFFECTED: ALI. AFFECTED APS-BS AUTOPILOT CAPSTAN ASSEMBLIES MUST BE PULLED FROM
SHELF STOCK,INSPECTEO AND REPLACED AS NECESSARY.
PUBLICATIONS AFFECTED: NONE.
RECORD COMPLI~NCE: Malts an appropriate entry in airplane maintenance records as Follows: Specify paragraph
Be., 8b., or 8c. of Service Bulletin No 2011. d.ted II February 1985. entitled "lnspeetion and Replacement olCollins APS-
,,..,,ilat Capstan Assemblies accomplished (date)
Page 3 of 3
Culfstream Aerospace Corporation
Wiley Poll Qi,portP. O. Box 22500
Oklahoma City, Oklahoma 73123
Telephone: (4051 7895000 Tslsx:796 200
December 20, 1985
TO: OPERATORS OP COMMANDER TURBO PROP AIRCRAFTSUBJ: DESIGN MANEUVERING SPEED
A review of the Pilot Operating Handbook (P.O.H.) or Plight Manual (P~M) for
Commander Turbo Prop Aircraft has revealed a possible lack of emphasis of
the importance of the Design Maneuvering Spaed in aircraft operations.
As explained below, the enclosed P.O.H. or F/M changes end the placard state
that abrupt control movements above Maneuver Speed (111-149 Kts, dependingon aircraft model and weight) can result in dangerous structural damage and
possible loss of the aircraft. The P.O.H. or F/M changes are in the Airspeed
Limitation, Flight in Severe Turbulence and Definition sections. When you install
the placard and make the P.O.H. or P/M page changes, please read and understand
what is stated and that the possible consequences of making abrupt control
movements above maneuvering speed for any reason could result in structural
damage and possible loss of the aircraft.
Design Maneuvering Speed, Va is the speed defined by Vs (~j) where Vs is the
stalling speed with flaps retracted and N is the design maneuvering load factor.
This means that the aircraft, when operating at speeds equal to or less than Va,will stall prior to, or at the design load factor and thus not be overloaded byfull travel abrupt control surface movements or from gust encounters. Va varies
with the aircraft operating weight. The change pages attached hereto present
operating weight versus Va information for your specific aircraft.
We have made changes in the various Pilot Oparsting Handbooks or Flight Manuals
to emphasiee the importance of understanding Va, and have included a placardto be placed on the centerpost in the cockpit. The authorization and instructions
for installing the placard are contained in the enclosed copy of Service Bulletin
Ii you have any questions regarding the importance of this warning, please call
our Service Department at the following number; (405) 789-5000.
_
Se~iee BLeB getin g~llGulfstreamAerospace
SERVICE BULLETIN NO. Zo5
20Deccmber1985
Vn PLACARD INSTALLATION
MODELS AFFECTED: MODELBS0, SERIAL NOS. 11001 TIIRU 11079.MODEL 690A, SERIAI. NOS. 11100 THKU 11344.MODEL 690R, SERIAL NOS 11350’PHRU 11566.
MODE1.690C, SERIAI. NOS. 11600 THRU 11703, 11709 AND 11119 THRU 1 1?85.MODEL 690D, SERIAL NOS. 15001THRU 15042.MODEL 695, SERIAL NOS. 85000 THRU 95084.MODEL 695i\. SERIAL NOS 96001 THRU 96061, 96064 THRU 96068, 96070 THRU 96074.96076, 96077, 96019 THRU 96084AND 96086 THT(U 96100.MODEL 69IB, SERIAL NOS 96063, 96069. 96075, 96078, 96085 AN1)96201 THRU 96207.
REASON FOR PUBLlCATION: TO EMPAASIZE THE IMPORTANCE OF ORSERVINGVn SPEEDS.
COMPLlANCE: UPON RECEIPT OPTHIS SERVICE BULLETIN.
BY WHOM WORK WILL BE ACCOMPLlSHEI): OWNEWOPEKATOR, A P MECHANIC OR EQUIVALENT.
APPROVAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED.
ESTIM~TEDMI\N-HOURS: THIRTY(SO)MINUTES.
PARTS DATA: PLACARD P/N 860783-689 COMPLIANCE CARD AND AIRPLANE FLIGHT MANUAL OR PILOT’SOPERATING HANDBOOK REVISION IS BEING FURNISHED WITII THIS SERVICE BULLETIN
SPECIALTOOLS: NONE.
/ICCOMPLISHMENT INSTRUCTIONS:
i. Apply860783-689 placard inch above any existing placards on windshield centerpost cover (referto Figure i).
2. Insert applicable revision in Airpfane Flight Manual or Pilot.. Operating Handbaaltas noted:
MODEL MANUAL REVISIONNO.
680 FlightManual 21690A FlightManual 28690B Pilot’s Operating Handbook 21690C Pilot’s Operating Handbook 19690D Pilot’s Operating Handbook 10696 Pilot’s OperatingHandbook 10695A Pilot’s OperatingHandbook 1869511 Pilot’s Operating Handbook 7
3. Fillautand mail Compliance Card.
ELECTRICALLOAD: NoChange.
WEIOHTPINDBALANCE: NoChange.
SPARESAFFECTED: No.
PUBLICATIONS AFFECTED: The Airplane Flight Manual or Pilot´•s Operating Handbook revision is furnished with thisSelvieeBulletin.
RECORDCOMPLII\NCE: Make an appropriate entry in airplane maintenance records as Bllaws: Service Bulletin No. 205,dated 2(1 December 1985, entitled "V* PLACARD INSTALLATION". aeeomplished (date)
Page 1 oE2
SERYICEnULLETINNOlao6
,o\ m o ~h
WINDSHIELDCENTERPOST COYGR
(REF)
0. 5" ABOVE UPPERMOST
880185´•888 PLACARD
PLACARD L
MAGNETIC COMPASS I I EXIS~ID PLACARDS
(REF) AND COMPASS CARDS
(REF)
CENTERLINE OF
AIRPLANE
VIEW LOOKING FORWARD AT
WIN DSH IELD CENTERPOST COVER
Figure 1.
Page 2 of 2
Sewice Bblllefin CulfstreamAerospace
SERVICE BULLETIN NO, 206
1? August 1881
INSPECTION OF EMPENNAGE ATTACH AREA AT
FUSELAGE STATION 409.56
MODELS AFFECTED: MODELS 690, 690A, AND 690B, SERIAL NOS. 11001 THRU 11566.MODEL 690C, SERIAL NOS. 11800 THRU 11135.MODEL 89OD, SERIAL NOS. 15001 THRU 15042.MODEL 695, SERIAL NOS. 95000 THRU 95084.MODEL G9SA, SERIAL NOS. 96001 THRU 96100.MODEL 695B, SERIAL NOS. 96082, 98063, 96069, 96015, 96078, 96085 AND 86201 THRU98208.
REASON FOR PUBLICATION: TO CHECK EMPENNAGE ATTACHMENT FOR CORRECT HARDWARE ANDTOR~UE. INSPECT FOR POSSIBLE CRACKSIDAMAGE IN AREA.
COMPLIANCE: AT 2000 HOURS TOTAL AIRFRAME TIME OR WITHIN NEXT 25 HOURS IF BEYOND 2000
(.3HOURS *ND BEPE~T E~CX L1 MONTHS OR im Bouns, wmcwEvER COMES RRST
BY WHOM WORK WILL BE ACCOMPLISHED: A p,P MECHANIC OR EQUIVALENT.
APPROVAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED.
ESTIMATED M*N HOURS: MODELS 690, 690A AND 69011 UP TO SIX (B) HOURS.MODEL 690C, SERIAL NOS. 11601) THRU 11718 UP TO FOURTEEN (14) HOURS.MODEL 690C, SERIAL NOS. 11719 THRU 11135 UP TO SIX (6) HOURS.MODEL 690D UP TO SIX (6) HOURS.MODEL 696 UP TO FOURTEEN (141 HOURS.MODEL 895A, SERIAL NOS. 88001 THRU 98013 AND 96018 UP TO FOURTEEN (14)HOURS.MODEL 695A, SERIAL NOS. 96014 THRU96011 AND 96019 THRU 96100 UP TOSIX (6) HOURS.MODEL 695B UP TO SIX (6) HOURS.
PARTS DATA: AN AND MS HARDWARE (IF REQUIRED), PROCURE LOCALLY.
SPECIAL TOOLS: Torque wrench with 330 inch-pound oapability.
Page 1 of 6
SERVICE BULLETIN NO. 208
INSPECT~REAAROUNO
80LT HOLES AND FLANOES
OF 8PPIR CAP FOR CRACKS
CONTROL LINI(AOE
ACCESS DOOR IREFI
VERTICAL STABILIZER
AFT SPAR IREF)
HORIZONTAL
SIABlLIZER
FRONT SPAR
O IREFI
O o o e9 O
dlo
0 o,oo e
00
00 O
6\1 I O "N"OD5’8 WASHER
~NS´•B BOLT
IUNDER NUT ONLY)
0´•O Mnlazs´•a NUT
MS2(888´•132 COTTER PIN
TOROLIE 180 TO 208 1N´•LBS
(4 PLSID
O O
0000
DO 00 O
INSPECT AREA BELOW
8PI\R FOR CRACI(S
0c00 eo
NOTE
VIEW LOOKING FORWARD 00 NOT INSTALL ANY WASHERS
AT FUSELAGE STA. 409.56 UNDER HEAD OF BOLT
FilYla 1´•
Page aoi8
SERVICE BULLETIN NO 206
*CCOMPLISHIENT INSTRUCTIONS:
1. Remove left and right rudder control linkage access doors that are lacated just aft of iuselage station 409.56.
2. Remove screws attaching tail cone
3 Disconnect electrical wiring from tail position lights and remove tail cone,
Install tail stand on tail skid.
5. Inspeet the following areas, at station 409.58, where vertical stabilizer attaches to horizontal stabilizer, forpossible craeksidamage:
a. Area around bolt holes (refer to Figure 1).
b. Upper and lower spar cap nsnge (refer to Figure II,
Spar web.
d. Station 409.56 bulkhead below horizontal spar (refer to Figure 1)
a. Around rivete that attach lower vertical stabilizer skin to ribs (refer to Figure 2).
F Lower ribs in vertical fin.
g. If no cracksldamage is found, proceed to step 8.
h. If cracks/damage is found, contact Gulfstream Aerospace product Support.
6. Inspect arear noted in step 5 for sheared. working or loose fasteners. Replace fasteners as necessary,
C ..r.
Working rivete are usually indicated by blaekidark coloring aroundrivet heads andlor black streaks on outer surface of the skin,around fasteners.
Inspect four (4) bolts attaching vertical stabilizer to front spar of horizontal stabilizer Lr installation ofcastellated nuts on bolts and washers under bolt heads (refer to Figure 11
NOTE
Service Letter No. 345 installs castellated nuts and an access doorfor saay access to empennage attach balte.
8. If there are castellated nuts installed and no washers under bolt heeds, proceed as follows:
a. Remove existing cotter pins and check bolt torque. Torque to be iso to 200 inch-pounds.
b Assure that nut. can be secured properly with new MS24665-132 cotter pins (refer to Figure 31.
c. If nuts cannot be secured prope’ly´• remove nut. Install an additional AN960D516 washer (under nutaniy), reinstall existing nut and torque 160 to 200 inch-pounds by tightening nut to low side of torrluerange and. if necessary, continue to tighten until a nut slot aligns with hale in bolt. Install new11´•1524665´•132 cotter pins.
d. Praceed to step II,
9. Ifcaateliaied nuts are not installed, replace existing vertical stabilizer attach bolt (4 places), one at a time, osfollows irefer to Figure 1):
a. Remove bolt and inspect bolt hole for possible damage.b. if hole is not damaged. install ANS´•B bolt, AN860D516 washer lunder nut only) and MS11815-6 nut.
Torque bolt LBO to 200 inch-pounds by tightening nut to law side of torque range and, if neeessery.eontinur to tighten until a nut slot aligns with hole in bolt. Install MS21665-132 cotter pin (refer toFigure 31
Page aolB
SER~CE OULLETIN NO. 20(i
n?
-i:g
X4
VERTICAL 1?
C
INSPECT LOWER RIBS
FOR CRACKS
INSPECT FOR CRACKSI\ROUND RIVETS ATTACHINGRIBS TO SKIN
Figure 2.
Page lofs
SERYICE BUI.LETIN NO ?I)h
I\DDITION*L WPISHER M*Y BEUSEO IF REOUIRED TO ~LIONHOLE IN BOLT WITH SLOT IN NUT
VIEW SHOWING INCOARECT VIEW SHOWING CORRECT~LIONMENT OF HOLE (N BOLT I\LIGNMENT OF HOLE IN BOLT
Figure 3.
NOTE
An additional AN960D6iB washer may be installed lunder nut
oniyl. if necessary. to assure proper alignment of hole in holt withslots in nut.
fxe i) hol. is damng.d, it is acceptable to use ANG-7 bolt 0.3;9" diameter hale) only if an edgedistance of(l.56inch or more can be maintained.
d ilit is determined, prior to reaming existing hole, that an edge distance of 0S6-inch or more cannotbe maintained, contaet OulUream Aerospace Product Support for further inrtructions.
e II it is determined, prior to reaming existing hole, that an edge dirtmee uP O.SB-inch or more can bemaintained ream damaged hole to 0.315"10.379" diameter and install ANG´•i bolt, AN960D616 w~her(under nut onlyl and M517825-6 nut Torque bolt 300 to 330 ineh´•paonds by tightening nut to low sideof torque range and. if necessary, continue to tighten until a our slot aligns with hole in bolt. InstallMS2J665-1311 cotter pin (refer to Figure 3)
NOTE
An additional ANSBODB1G washer may be installed lunder out
only), if necessary to assure proper alignmem of hole in bolt withslots in nut.
10. if there are castellated nuts installed and washers under bolt heed, proceed as follows:
a P\emo~r bolts affected, one at a time, and inspect bolt heir. for poalibls damage
NOTE
Do not have more than one (1) bolt out at the same tin,e
b If IloleJ are not dnmnged, reinstall existing ANS-B bolt. ANYI(OD,IB ~unshel. .,r w;lsberx (under nutonl,´•l and existing MS11825-5 nut. Torque bolt to L60 to 200 incb-pilunlis by tightening nut to low sideof tol´•qus range and. if necessary, continue to tightm until r nut Jlot nliiinx with bile in holt. Installnew MS21665-131 cotter pin (refer to Figure 31.
Pab’eSofG
SERVICE BULLETIN NO. 206
c If hales are damaged, it is acceptable to use AN6-? bolt (0.376"10.379" diameter hole) only if an edgedistance of OS6-inch or more can be maintained.
d. If it is determined. prior to reeming existing holes, that an edge distance of O.58-inch or more cannotbe maintained, contact Gulfstream Aerospace Product Support for further instructions.
e if it is determined, prior to reaming existing holes, that an edge distance of 0.56-inch or more can bemaintained, ream damaged hole or holes to 0.376"10.379" diameter and install ANB-? bolt, ANSB~TiGIBwasher (under nut only) and MS11825-6 nut. Torque bolt S00 to 330 inch-pounds by tightening Rut tolow side of to~que rang. and, if necessary, continue to tighten until a slot aligns with hole in bolt.Install MS24685-134 cotter pin irefer to Figure 3).
NOTE
An additional AN960D616 washer may be installed (under nutonly), if necessary, to assure proper alignment of hale in bolt withslOtP in nut. The above listed hardware is to be procured Lacelly.
11 Reconnect electrical wiring to tail position lights and reinstall tail cone on airplane using elisting hardware
12. Reinstall lelt and right rudder control linkage access doors using existing hardware.
13 Touchup paint as necessary.
14. Fill out end mail Compliance Card specifying if cracks were found and if oversi.e bolts were installed.
ELECTRICAL LOAD: NO CHANCE
WEIGHS AND BALANCE: NO CAANOE.
SPPIRES AFFECTED: NO.
PUsUC*TUINS*FFECICO: NONE C_RECORD COMPLI*NCE: Make an appropriate entry in airplane maintenance records as follows: Sely-ice Bulletin No.206, dated I? Au~ust 1981, entitled "lnspection of Empennage Attach Area at Fuselage Station 409.56,,’ accomplished:(date)
page BufB
cko~l,Service Bwlletin GulfstreamAerospace
SERVICE BULLETIN NO. 20?A
BUI~Y´•NI IINSPECTION AND/OR REPLACEMENT OF DEVORE TEL-TAIL
L00O1RECOGNITION LIGI´•IT BULBS
MODELS AFFECTED: THE FOLLOWING MODELS WITH DEVORE TEI,TAIL LOGOIRECOGNITION LIGHTING8YSTEM INSTALLED PER 8TC gA1O1?EA OR FACTORY INSTALLED PER COMMANDERDRAWINGS 890449 OR 880453 AND IPPILIZING DEVORE TEL-TAUL BULBS P~ DA-21AND DA-1S:
MODELS 500, 50OA, SOOB, 50011, 520, 660, 560A, 560E, 5608, 680, 680E, 680F, 680F(P),680n, 680FL(P), 680T, 680V, 680W AND 720, SERIAL NOS. 1 THRU 1876.MODEL 5005, SERIAL NOS. 1166 THRU 1816 AND 3080 THRU 3313.MODEL BB1, SERIAL NOS. 6001 THR~ 60?a.MODEL 685, SERIAL NOS. 12000 THRU 12066.MODELS 690, 69(IA AND BgOB, SERIAL NOS. 11001 THRU 11666.MODEL 690C, SERIAL NOS. 11600 THRU 11135.
MODEL B9oD, SERIAL NOS. 15001 THRU 15042.
MODEL 695, SERIAL NOS. 86000 THRU 95084.MODEL 695A, SERIAL NOS. 96W1 THRU 96061, 86064 THRU 86068, 96010 THRU 96014,116016, 96011, 86018 THRU 9608´•1 AND 96088 THRU 96100.MODEL 69511, SERIAL NO8. 96062 AND 86201 THRU 96207.
REASON FOR PUBLICATION: REPORTS OF GLASS BEADS VIBRATING OUT OF LOoOlRECOCNBION LIGHTBULB BASE DUE TO POTI~INCr PROBLEMS. GLASS BEADS COLLECTED INGREASE ON ELEVATOR TRIM CHAIN AND CAUSEDA JERKEY OR JAMMEDCONDITION.
COMPLIANCE: WITHIN NEXT TWEEFI~Y-FIVE (25) HOURS TIME IN SERVICE AND EVERY TWENTY-FIVE (25)HOURS THEREAFI~ER UNTIL LIGHT BULBS ARE REPLACED WITH DA61 OR DA?2 BULBS. I
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYINGWITH THIS SERVICE BULLETIN, CONTACT YOUR NEARESTGULFSTREAM COMMANDER AUTHORIZED SERVICENTER.
BY WHOM WORK WILL sE ACCOMPLISHED: OWNER/OPERATOR, A L P MECHANIC OR E$UIVALENT.
AFPROVAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED.
ESTIMATED MAN HOURS: 1.6 HOURS.
PARTS DATA: CONTACT DEV(IRE AVIATION CORPORATION PRODUCT SUPPORT DEm.. 6104B KLRCHERBLVD., N.E. ALBUQUERBUE, NEW MEXICO 81108 TO ARRANGE FOR BULB P/N DA-16 OR DA-21REPLACEMENT EXCHANGE.
SPECIAL TOOLS: NONE.
Psgs 1 of S
SER~ICE BULLFNN NO. aO?A
RH LO(IOIREW(INITIONLIGHT
LH LO(OOREECWNTTIONLIGHT
LINI(I\(IEACCES8DMIR
IN8PECT WTTIN(I COMWVNPELEVATOR FOA CR*CI(S. OHIPPINO ANO
DISLODOEMENT(REF) ~4
~Pa-E"F9"
ROLLERCHI\IN
IREFIE~EvnroRTl\sIREFI
fRPP~CKET
FCra i.
PpgePofS
~t
SERVICE BULLETIN NO. 207A
)ACCOMPUSHMENT INSTRUCTIONS:
i. Assure that battery switch is in the OFF position.
a. Remove covers hem left and right logoiremgnition lights (refor to Figure 1).
3. Remove bulbs from logolrecognition lights.
4. Check bulb potting compound for cracks, chipping or dislodgement. If any of these conditions exist, the bulbsI
must be replaced with new bulbs. The new bulbs should be P~ DA61 or DA?O.
NOTE
Tbs 0116 bulb (II MC Ivatan~) i, by Dh61 ´•nd 0~7 1bulb (28 VDC system) is replaced by DA?2.
5. Contact DeVore Aviation Product Support Dept., 61048 Kircher Blvd. N.E., Albuquelque, NM 87109 to arrange
for obtaining improved DA61 OR DA72 light bulbs,
NOTE
If new improved DA61 or DA72 bulbs are not immediately
available, it is acceptable to use new DA1S or I)AZ? bulbs if the
potting compound is acceptable. These bulbs must be replaced when
new improved DAS1 or DA?2 bulbs are available.
6. Install bulbs in logoirecognition lights.
NOTE
Handling bulbs with bare fingers will deposit finger prints and
grease on bulbs. Clean bulbs witb a grease-free solvent such as
acetone before illuminating bulbs.
If the logoirecognition light system has been deactivated, the
airplane should not be operated witb non-functioning bulbs. It is
recommended that bulbs be removed ham the fixture and wiring be
capped and stowed, Alternate deactivation of the system would be
removal of the entire light assembly and installing cover plate,DeVore Pi~ 00033078-1, and insulation and tie back of wires.
7. Install covers an logoirecognition lights usmg existing hardware. Torque screws 8 to 8 inch-pounds.
8. Remove left and right rudder control linkage access doors that are located just below horizontal stabilizer on
aft fuselage tail section (refer to Figure i).
9. Inspect elevator trim chains and sprockets for grease contamination with glass beads (refer to Figure i).
10. Check cavities in horizontal stabilizer and empennage far glass bead contamination. Remove ail glass beads.
11 if glass heads are present in greese on elevator trim chains and sprockets, clean elevator trim chains and
spmckets and remove contaminated grease and glass beads.
12. Lubricate elevator trim chains and sprockets as outlined in the applicable Airplane Maintenance Manual.
1S. Functional check elevator trim system to assure that system i. operating properly and smoothly.
14. Reinstall rudder control linkage access doors using existing hardware.
15. Fill out and mail Compliance Card.
ELECTRICAL LOAD: NO CHANGE.
WEIGHT FIND BI\LANCE: NO CHANGE.
SPARES AFFECTED: ALL DA1B AND DA21 BULBS SHOULD BE REMOVED FROM STOCK AND REPLACEDI
WITH DAS1 AND DA72 BULBS.
PUBLICI\TIONS AFFECTED: NONE
RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service Bulletin No.
20?A, dated 18 Augustl988,entitled "Inspection sndlor Replacement of DeYore TeI-Tail LogolRscognition Light Bulba.’´• Iaccomplished: (dste)
Page 3 of 3
,Service Bulletin IIRCRIIFT CORPORIT)ON
P.O. Box 3389
Adinm~n. WA 98223
Tel: (206) 4358797 Fax:1206)~1112
8ERVICE BULLETIN E10. 209 original: November 15, 1990
INBPECTION AND/OR REPLACEMENT OF NOBE WUmINO OEAIL AXLE
MODeL8 AFFECTEDI
The following medals that have replaced nose landing gear axlesbetween January i, 1986 and February 24, 1988:
All Commander twin-engine models equipped with reciprocatingengines or turboprop engines except Serial Nos. 1 through 190 andModel 700.
NOTEIf you have not replaced an axle, P/N 9545, duringthe time noted shove, inspection is not required
REABON FOR FWLICATIONt
Possible error in heat treatment. Material may be of a lesserstrength than drawing requires.
COMPLIANCE:
Within next twenty-five (25) flight-hours time in service.
8Y ISgOn IPORX wILL BE ACCOMPLISBED:
n 8 P Mechanic (or equivalent).
APPR(IVAL:
Engineering design aspects are FAA approved.
ESTIMATED MAN HOVRS:
Two (2) hours.
Page 1 of 4
SERVICE BULLETIN NO. 209
PARTS DATA:
Parts required to conply with this service bulletin may be procuredthrough your nearest Twin Commander Servicecenter. If axle is
found to be defective, a credit of two (2) hours labor and creditfor nose landing gear axle will be issued upon receipt of a
properly executedwarranty claim, accompanied by the defective axle
and proof of compliance. Reference this service bulletin, aircraft
model and factory serial number when ordering Service Bulletin No.
209 Kit consisting of the following:
QTY Part No. Description
1 ea. 9545 Axle
1 as. Service Bulletin No. 209 Instructions
SPECIAL TOOLS:
Material hardness tester.
ACCOMPLISHMENT INSTR~OCTIONSt
1. Jack airplane as outlined in the airplane Maintenance Manual.
2. Remove nose landing gear axle as follows:
a. Remove axle bolt nut, axle bolt and plugs.
b. Remove axle from fork assembly.
c. Remove nose wheel assembly and spacers.
3. Using a material hardness tester, check hardness of nose landing
axle. Axle must teet 150 ksi minimum (Rockwell hardnesss of C34
to C37) (refer to Figure i).
4. If axle test is acceptable, proceed to step 6.
5. If axle test is not acceptable, replace with new 9545 axle and
proceed to step 6.
Page 2 of 4
SERVICE BULLETIN NO. 209
)6. Tnstall new or enistin~J 954~ axle as iallare:
a. Clean wheel bearings/races in high grade kerosene.
NOTE
Do not clean bearings in gasoline.
b. Dry bearings with compressed air. Do not spin bearings.
c. Inspect bearings for pits, scoring, corrosion and wear.
Replace if necessary.
d. Pack bearings with clean bearing grease as outlined in
the airplane Maintenance Manual.
e. Install bearings in wheel asssembly.
NOTE
Additional grease may have to be added to
hearing housing after bearing has been installed.
f. Lubricate load bearing surfaces of axle, washer and
axle nut.
g. Install spacers in gear fork assembly.
h. Install nose wheel assembly in gear fork assembly.
i. Insert axle through fork and nose wheel.
i. Install axle plugs, axle bolt and nut. Tighten axle bolt
until wheel bearings begin to bind, then back off until
bearings are just free.
k. Functionally check gear operation.
7. Remove jacks and tail stand from airplane.
8. Fill out and mail Compliance Card and note on Compliance Card
if axle was replaced.
Rage 3 of 4
SERVICE BULLETIN NO. 209
PLUO
AXLE BOLTAXLE WHEELAGSYBOLT
NUT
SPACER
AXLEI/
TSPACER
ACCEPTABLE TO PERFORM
HARDNESS TEST HERE
PAEFERREOTOPERFORMHPIRDNESS TEST AT ENDS
OF AXLE
Piguee i.
ELECTRICAL LOAD: NO CHANGE
IPEIORT AND BALANCE1 NO CHANGE.
SPARES AFFECTED:
All axles in spares stook must be checked for hardness and removed
if found to be defective.
POBLTCATIONB APBECBED: NONE.
RECORD COMPLIANCEr
Make as appropriate entry in airplane maintenance records as
follows:
Service Bulletin No 209, dated November 15, 1990, entitled
"Inspection and/or Replacement of Nose Landing Gear Axle"
accomplished: (date).
Page 4 of 4
,Senn’ce Bu iletinBox 3388
IIRCRIFT CORPORITION
Arlington. WA 98223Tsl: (208) 435´•8791 Fax: (208) lCH12
SERVICE BULLETIN NO. 210 Original: February 1,1991
OF FLAP MASTER POLLEY A~D CABLE wITB INSPECTION OF
REMAINING FLAP 8Y8TEM
HODELB AFFECTED:
All models of piston and turbine twin engine Aero Commanders
except the model 700.
REASON FOR PWLICATIONt
Part I: Complete flap system cable inspection.
Part II: Mandatory replacement of the master cable pulley.
Note: A master pulley is located on the leftside of the fuselage, and is attached to
the flap actuator. On one aircraft the
groove of the master pulley was Found to
be too narrow for the cable. The cablewas forced to ride on the sides of the
groove rather than seated in the bottom of
thegroove. This condition accelerates
cable fatigue. A review of the drawingsshows that the master pulley dimension isin error throughout the fleet.
On the right side of the fuselage is a
slave pulley attached to the master pulleyby a pushrod. Review of all drawingseffecting allpulleys in the cable flapdrive system for the models effected,demonstrates that only the master pulleygroove dimensions are in error. However,one slave pulley has been found to alsohave groove dimensions that were in error.
With respect to the inhoard and outboard
flap pulleys, two outboard flap pulleyswere found to be rubbing on their mountingbrackets. The pulley clip retaining the
cable was nearly worn through due to
rubbing.
Page 1 of 7
SERVICE BULLETIN NO. 210
The Part I inspection if. for the purposeof inspecting slave pulley grooves and to
detect any other flap system pulleycausing accelerated cable fatigue.
Outboard pulleys are also to be inspectedfor bracket and clip rubbing.
COHPLUUYCE:
Timing: Part I, inspection, and Part II, master cable pulleyreplacement, shall occur within the next 100 hours
for aircraft with less than 2200 landings and within
20 hours for aircraft with greater than 2200
landings or with an unknownnumber of landings.
Part I: A. Cable inspection of all Flap system cables shall
be done with a soft cotton cloth.
8. Inspect all flap pystem pulleys for rubbing with
their support brackets.
C. Gage inspection of slave pulley.(Refer to Figure
Part II: A. Mandatory master pulley replacement.(Refer to
Figure i)
B. Mandatory replacement of master pulley cable.
BY wBOM BORX wILL BE ACCOMPLIQHED:
A P Mechanic (or equivalent)
APPB~AL:
Engineering design aspects are F.A.A. approved.
Pace 2 of 7
SERVICE BULLETIN NO. 210
ESTIIIATED MAN BOIIR8:
Part A. 18 hours (both sides)
B. 2 hours (both sides)
c. 1 hour (both sides)
Part II A. 2 hours
B. 2 hours
PARTS DATA:
Figure I leads into Table I for identifying the master andslave pulley numbers and their respective cable numbers.
SPECIAG TOOL81
Make a gage for inspecting the groove in the slave pulley.The gage may be:
a. An 0.125 +1- 0.001 diameter sphere
cl4.
B. An 0.125 o.001 diameter rodC. A flat gauge with the following profile: 0. 5 NIN
PICCOMPLISBXENT IN8PROCPI~ONB:
Part I A. With a soft cotton cloth, rub each flap systemcable over it’s length. where it snags, inspectfor bro]renwires. If there are any broken wires,the cable must be replaced.
8. Inspect each flap system pulley on both sides for
signs of rubbing against the upper and lower
support brackets. Be especially alert for wear on
the clip that secures the cable. Replacement is
mandatory if any clip is being worn.
Page 3 of 7
SERVICE BULLETIN NO. 210
C. Insert the gage (made under the Special Tools
section) into the slave pulley groove. Back lightthe gage. If the gauge does not touch the bottom
of the groove, the slave pulley and it’s cable rrm~be replaced.
Part II A. Replace the master pulley.
8. Replace the master pulley cable and any slave
pulley cable when the slave pulley is replaced.
Figure 1. and Table i. coordinate the component parts with the
appropriate aircraft.
ELECTRICAL LOAD: NO CHANGE
1(IIOHT AND BALANCE: NO CHANGE.
SPARED AFFECTED: Purge inventory of all master pulleys.Gauge inspect all slave pulleys for
dimension error, and purge inventory of
those slave pulleys found to have wrong
dimension.
PWLICATIONB EFFECTED: NONE.
RECORD COMPLIANCEt
Make an appropriate entry in aircraft log book as follows:
Service Bulletin No. 210, dated February i, 1991
entitled "REPWLCEMENT 08 FLAP EASTER POLLEY AND
CABLE wITE INSPECTION O~’RI~MAININO FLAP SYSTEM"
Part I Accompliahad:(date) State what was found on
cable/pulley inspection and slave pulleyinspection.
Part II Accomplished:(date) State what cables and
pulleys were replaced in addition to the
master pulley and cable if any.
Pace 4 of 7
SERVICE BULLFTIN NO. 210
TABLE I MASTER RULLEY ~D CABLE REPLACEMENT PART NOMBER8
nODEL EASTER PULLEY SERIAL EASTER PULLEP CABLE SERIAL
"A" in Figure I NOHBERB "1" in Figure I N~1MBER8
500 510101- 7 411 500012- 89 ALL
SUBS
500 A 510101- 7 ALL 500012- 89 ALL
500 B 510101- 7 ALL 500012- 89 ALL
500 U 510101- 7 ALL 500012- 89 ALL
500 S 510101- 7 ALL 500012- 89 ALL
520 510101- 5 1 500012- 89 ALL
150
560 510101- 5 151 500012- 89 ALL
230
560 A 510101- 5 231 500012- 89 ALL
410
560 A 510101- 7 411 500012- 89 ALL
SUBS
560 E 510101- 7 411 500012- 89 ALL
SUBS
560 F 510101- 7 411 500012- 89 ALL
SUBS
680 510101- 5 231 500012- 89 ALL
410
680 510101- 7 411 500012- 89 ALL
SUBS
680 E 510101- 7 411 500012- 89 ALL
SUBS
680 F 510101- 7 ALL 500012- 89 ALL
680 F(P) 510101- 7 ALL 500012- 89 ALL
Piiga 5 Of 7
8EBVICE BULLETIN NO. 210
MODEL KA8TW PULLEY 8ERULL HABTER PULLEY CABLE BWIAL
IIAll i, Figure I NUPIBERB "1" in Figure I NUWEERB
680 FL 510101- 7 ALL 500012- 89 ALL
680 FL(P1 510101- 7 ALL 500012- 89 AU
680 T 510101- 7 ALL 500012- 89 1413
680 V 1725
680 W 510101- 7 ALL 500012- 89 1473
1850
681 510101- 7 ALL 500012- 89 6001
6063
681 510101- 7 ALL 500012-272 6064
6072
685 510101- 9 ALL 500048-1 ALL
690 510101- 9 ALL 500048-1 ALL
690 A 510101-11 ALL 500048-1 ALL
690 B
690 C 510101-11 11600 500048- 1 11600
11999 11999
690 D 510101-11 15000 500048- 1 15000
15939 15999
695 510101-11 95000 500048- 1 95000
95999 95999
695 A 510101-11 96000 500048- 1 96000
695 B 96999 96999
720 510101- 7 411 500048- 1 ALL
SUBS
Paae 6 of 7
SERVICE BULLETIN NO. 210
k?bd3 i
B L~n.Ylarhl.´•n. Idonthva DI Mh. CO.RIUCE WRO
A Maater Pulley (le(t aide (uaelage)TYPICAL
Slave Pulley (rigM aids. *aslage)CLIP c lnboard Flap Pulley (lan or dgh0
a Oumaerd flap Pulley lien or dgM)5i;
1 cable (lsRaida)
2 cable (riQM lids)3 ~sbls(lsnordgM)
cable (lener dgM)
cable (Isn or righh
Figure I Flap Pulley and Cable Assembly
Page 7 of 7
COXPLIANCE CARD
8ERVICE BOLLIITIN NO 210
REPWLCEHEN~ OF FLAP ~LAS’PER POLLEY AND CABLE WITII INSPEC~ION OF
REWAIHIN(I FLAP 8Y8TM
Model: Airplane:
Total Time: Total Number of Flights:
owner:
Address:
Part I IN8PECalON
A. Using the cable numbers in Figure I, give the cable
number, whether left or right wing, and number of
wire breaks, if any, found.
cable number left right no. of wire breaks
8. Identify any pulleys found to be rubbing with the
brackets.
Rubbing pulley identity:
C. Did the gauge touch the bottom of the slave pulley?
yes no
From the grease tracks does it appear that the cable
has been riding in the bottom of the groove as it
should7 yes no
Part II REPWACEMENT
A and B: state all pulleys and cables replacedincluding master pulley and cable.
Inspected By:
Date:
Telephone No.
MANDATORY
Se rvice Bulletin AIRCRAFT CORPORA TIONtsom Bgth Dr. N´•e, AT110110n. WAg8nJTel: (203) 4U8787´• Fu: (208) 41111iZ
Service Bulletin No. 213 Date: July 29, 1994
WING FATIGUE INSPECTION AND MODIFICATION
MODELS AFFECTED: MODEL 690C, SERIAL NOS. 11600 THRU 11730
MODEL 685, SERIAL NOS. 95000 THRU 95084MODEL BgOC, SERIAL NOS. 11731 THRU 11735 (PART I. ITEM 10 ONLY)
REASON FOR PUBLICATION:
PART I: TO PROVIDE INSTRUCTIONS FOR WING STRUCTURAL INSPECTIONS IN AREAS SUBJECTTO FATIGUE.
PART II: TO PROVIDE MODIFICATIONS TO WTEND FATIGUE LIFE AND REDUCE FUTURE MINSPECTION RECIUIREMENTS. PART II IS TERMINATING ACTION AND NO FURTHERSPECIAL INSPECTIONS PER THIS SERVICE BULLETIN ARE REQUIRED FOR ALL ITEMS AU(CEPT PART I. ITEM 10.
NTHIS INFORMATION IS AVAILABLE FROM FULL SCALE FATIGUE TESTING OF AMODEL B95A WING AND PRESSURE CABIN. THE MODEL 880C/695 WING IS THE SAME I DCONFIGURATION AS THE TESTED 695A WING.
A
COMPLIANCE: ITPART I: (INSPECTION) loINITIAL INSPECTION: BOW HOURS TOTAL AIRFRAME TIME IN CONJUNCTION WITH MAJOR I R
INSPECTION GUIDE I. IvSECOND INSPECTION: 7500 HOURS TOTAL AIRFRAME TIME IN CONJUNCTION WITH MAJOR
~RSPECTION GUIDE II, UNLESSPAR771 PREVIOUSLY ACCOMPLISHED.
SVBSWUENT 1000 HOUR INTERVALS UNTIL ACCOMPLISHMENT OF PART II. PART I. ITEM
INSPECTIONS: 10 IS TO BE REINSPECTED AT 1000 HOUR INTERVALS (SEE FIGURE 5).
PART II: (MODIFICATIONS)
INCORPORATION OF THE MODIFICATIONS AT THE TIME OF THE FIRST INSPECTION IS
RECOMMENDED IN ORDER TO MINIMIZE THE POSSIBILITY OF STRUCTURAL DAMAGEREQUIRING REPLACEMENT OF PARTS OR ADDITIONAL REPAIRS, AND TO ELIMINATE
FURTHER PART I INSPECTIONS.
Page 1 of 16
SERVICE BULLETIN NO. 213
BY WHOM WORK WILL BE ACCOMPLISHED:
A 8 P MECHANIC (OR EQUIVALEN1) AND A CERTIFIED NDT INSPECTOR (OR EQUIVALENT) PERINSPECTION ~UALIFICATIONS.
NOTE:DUE TO THE COMPLEXITY OF THIS SERVICE BULLETIN IT IS RECOMMENDED THAT THEMODIFICATION PORTION BE COMPLETED BY AN AUTHORIZED MIIN COMMANDERSERVICE CENTER.
APPROVAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED.
~SUMATED MAN HOURS: (INCLUDING ACCESS PER SIDE)
PART I: INSPECT WIND RIBS W.S. 39 AND W.S. 89 38 HRS
INSPECT WIND STRINGER ENDS 12 HRSINSPECT WING UPPER SKIN W.S. 103 W.S. 113 11 HRSINSPECT FUSELAGE STATION 144 FRAME 5 HRS
PART I: 88 HRS
PART II: M001N WIND RIBS WiS. 39 AND W.S. 80 -1 KIT 20 HRS
MODIFI WING STRINGER ENDS 3 HRSMODIFI WING UPPER SKIN W.S. 103 TO W.S. 113 -2 KIT 10 HRS
PART II: E 33 HRS
PARTS DATA: PART I: NOT APPLICABLE
PART II: PARTS RE~VIRED TO COMPLY WITH THIS SERVICE BULLETIN MAYBE PURCHASED FROM YOUR NEAREST TWIN COMMANDERFACTORY AUTHORIZED SERVICE CENTER UNDER KlT NUMBERSLISTED BELOW.
Kit Number 61213.1:
City Part Number Desoridlon1 170425-1 Angle1 170425´•2 ´•Angle1 170428´•1 Angle1 170426-2 Angle2 K180010-505 Filler2 K160015-1 Shlm1 170428-1 Angle1 170428´•2 Angle1 170428-501 Angle1 170428-502 Angle4 HL20PB´•5-3 Pin20 HLZ1PB-5-12 Pin
24 HL88-5 Collar
Page 2 ot 18
SERVICE BULLETIN NO, 213
Kit Number 58213-2:
alv Part Number Descriotion1 K170316-1 Doubler
t K170318´•2 Doublert K170316-3 Doubler1 K1703164 Doubler
1 K170316-5 Filler
NOTE:
DESOTO 825309 POLYURETHANE PRIMER USED FOR TOUCH UP ON PARTS FURNISHED
WITH THIS KIT TO BE PROCURED LOCALLY.
KIT NUMBER ARV\ TO BE MODIFIED
58213-1 LEFT 3 RIGHT WING Rl8 WIND STATION 39 AND 69
88213-2 LEFT 3 RIGHT WING UPPER SKIN WING STATION 103 TO 113
SPECIAL TOOLS: NONE
INsPECTloNsunLlnCnTIoNS: (PART I)
1. PERSONNEL CIVALIFICATIONS
a. Level II Liquid Penetnnt with documented experience of no less than 200 hours.
b. Vision acuity requirements of MIL-STD-410E, or latest revision.
c. Documented training in accordance with MIL-STO-4108, or latest revision and recommended practiceSNT-TC-1A of the American Society for Nondestructive Testing,
2. MATERIALS ANDIOR EOUiPMENT
a. Solvent Cleaner, SKC-NF (Magnaflux) or equivalent per MILI-25135E.
b. Water Washable Fluorescent Penetrant, ZL60C, Level II (Magnanux) or equivalent per Mll-I-2513JE.
c. Non-Aqueous Developer, ZP-OE (Magnanux) per Mll-I´•25135E or equivalent.d. ZB-lOO Blacklight (Magnaflux), 100w, 115v, 60Hr or equiv.a. Inspection minor.
f. Cleaner. Penetrant and Developer to be from the same manufacturer,
3. PROCESS
a. Per MIL-STD´•B~BB.
b. Sensitivity Type I. Method A. Level II
PART I ACCOMPLISHMENT INSTRUCTIONS (INSPECTIONS)
1. Disconnect batteries.
2. Os-fuel airplane as outlined in the Airplane Maintenance Manual.
3. Perform a general structural $speotlan in acco~anca with applicable Maintenance Manual procedures and
inspection Program selected per Maintenance Manual Chapter 5. Particular attention should be given to
rivet lines, end fastener locations in splices, nn$gs or doublers and at any changes in cross se*lon. Also
areas having curved members and areas having small (less than 2 limes fastener diameter) edge distances.
Pace 3 ct 16
SERVICE BULLETIN NO. 213
PART I ACCOMPLISHMENT INSTRUCTIONS (INSPECTIONS) (cont’d)
4. Close visual inspection is required, using Fluorescent Penetrant method as an aid in disclosing cracks.
Carefully remove sealants or finishes as necessary in o~er to allow inspection of the structural elements.
Moderate hand pressures applied between pans, in order to produce any relative movement allowed, may
assist in the detection of failure of the parts or joining fasteners. AIso, observe any rub marks indicatingrelative movement of parts under load. Finishes or sealants must be restored per recommended
Maintenance Manual practices after inspections are completed. Inspections refer to both right and left
aides of the airframe unless specified otherwise,
5. Remove upper wing skin access doon inboard and autboad of Wing Station 38.00 ribs.
6. Gain access to the lower nanges of the Wing Station 39.00 rib between the Main Spar Lower Cap and
stringer No. 7.
NOTE:
THESE INSPECTIONS REQUIRE THAT THE AFT INBOARD AND OUTBOARD FUEL
CELLS SE MOVED ASIDE TO GAIN ACCESS TO THE RIBS (L DOUBLERS. REFERENCE
MAINTENANCE MANUAL CHAPTER 28 FOR PROCEDURES.
7. Inspect the Wing Station 39 rib and doubler lower flanges, an of the main spar and foma~d of stringer No,
7, for cracks in or near the flange radius or adjacent to rivets (reference Figure 1), using Fluorescent
Penetrant Method.
Inspect the Wing Station 39 and 69 ribs at the stringer No, 3 cut-out at the upper nange area for cracks in
or near the flange radius, web or flange adjacent to rivets (reference Figure 2), using Fluorescent
Penetrant Method,
8. Inspect wing upper Stringers, No, 1, 2, and 2A at their inbaalrl termination for cracks in the stringen or
attaching structures and for any failed fastenen (reference Figure 3), using Fluorescent Penetrsnt Method.
The inboartl 4.5 Inches of the stringers are to be inspected for cracks from the forward side, The
corresponding area of the frame is to be inspected from the an side. All visible fanenen in the inboard
end of the stringer; are to be inspected for loose, working or sheared conditions.
NOTE:
THIS INSPECTION WILL REQUIRE THE REMOVAL OF A PORTION OF: THE PASSENGER
CABIN INTERIOR TO GAIN ACCESS TO THE STRINGERS IN THE UPPER CABIN. IN
AODITION, THE CABIN OXYGEN LINES IN THE AREA OF THE STRINGERS ARE TO BE
DBCONNECTED FOR ACCESS,
9. Inspect the upper skin in the area outboed of Wing Station 103 and an of stringer No. 1, for cracks in the skin
(reference Figure 4), using Fluorescent Penetranl Method.
NOTE:
SERIAL NUMBERS 11620, 11864, AND 95038 ARE EXCLUDED FROM STEP 8.
10. Inspect Fuselage Station 144 frame, doublers at wing attach nnlngs above Water Line -10 for cracks and for tailed
fasteners (reference Figure 5), using Fluorescent Penetrant Method.
CAUTION:
THE 144 FRAME IS TO BE INSPECTED THRU THE EXISTING PANEL LIGHTING HOLE
FROM THE FRONT 91DE ONLY. DO NOT REMOVE THE FIBERGLASS CABIN PRESSURE
SEAL COVERING THE AFT SIDE OF THE FRAME AT THE WING ATTACH FITTING,
Page 4 of 19
SERVICE BULLETIN NO. 213
PARTII ACCOMPLISHMENT INSTRVCTIONS (MODIFICATIONSI
NOTE:FOR LOCAL TOUCH UP ON EXISTING STRUCTURE, USE ZINC CHROMATE. DO NOT MIXCHROMATE AND POLYURETHANE PRIMERS ON THE SAME PART. ALL NEW ALUMINUMPARTS FROM TWIN COMMANDER ARE POLYURETHANE PRIMED.
i. -1 KIT. MODIFICATION OF WING STATION 39 AND 68 RIBS.
DAMAGE LIMITS
THIS MODIFICATION IS APPLICABLE:A. IF THE WING STATION 39 RIB LOWER FLANOE CRACKS ARE IN THE BEND RADIUS
ONLY (DO NOT EXTEND UPWARD INTO THE RIB WEBS SEE FIGURE 1.B. IF THE WING STATION 39 AND 69 R1B AT THE UPPER WING STRINGER NO. 3 iS NOT
CRACKED SEE FIGURE 2.
IF THESE LIMITATIONS ARE EXCEEDED, DO NOT PROCEED WITH MODIFICATION.DAMAGED PARTS MUST BE REPLACED OR AN APPROVED REPAIR MUST BE INSTALLEDPRIOR TO COMPLETION OF THE MODIFICATION AND RETURN TO SERVICE.
CAUTION:EXERCISE EXTREME CARE WHEN CUTTING TO AVOID DAMAGING THE MAIN SPARLOWER CAP, SPAR DOUBLER PLATES OR OTHER WING STRUCTURE. USE STAINLESSSTEEL SHIMSTOCK OR OTHER MEANS AS APPROPRIATE TO PROTECT THE STRUCTUREFROM DAMAGE. TO REMOVE RIVETS, DRILL OFF HEADS AND DRIVE OUT. DO NOTDRILL OUT. TO REMOVE HVCKBOLTS, USE A COLLAR SPLITTER FIND DRIVE THE STEMOUT. ACCEPTABLE TO USE A 3X RIVET GUN OR SMALLER. WHEN REMOVING ANDIORINSTALLING INTERFERENCE FIT FASTENERS (HUCKBOLTS OR HI-LOKS) BACKUP THESTRUCTURE WITH AN APPROPRIATE BUCKING BAR.
a. Modify the Wing Station 39 rib and doubler lower flanges per Figure B which replaces the formed flangesbetween the main soar and stringer No. 7 with back to back extruded angles.
b. Trim away the lower existing wing station 39.00 rib nan8es (rib has both inboard and outboard nanges).including the bend radius from the Main Spar LowerCap to stringer No. 7 -(reference Figure 1 and 8).00 NOT DAMAGE THE EXISTING INTERNAL ALUMINUM STRAP UNDER THE RIB FLANGE.
c. Remove existing fasteners g rivets common to the rib and 170318-1/-2 cap angle sind 10 fastenerscommon to the rib lower nanges and lower wing skin.
d. Discard the removed db nangeo.
CAUTION:
THE HI-LOK COLLARS WILL BE VERY CLOSE TO THE VERTICAL LEG OF THE ADDED170425-1 AND 170020-1 ANGLES ON SOME AIRPLANES, MARK THE ANGLES BEFOREDRILLING TO DETERMINE IF THE COLLARS CAN BE INSTALLED. IF THE COLLARS
CANNOT BE INSTALLED, DETERMINE IF A SUBSTITUTE MSZ1OIZ OR M521043 NUT CANBE INSTALLED. IF THE NUTS CANNOT BE INSTALLED, CONTACT TWIN COMMANDERAIRCRAFT CORPORATION BEFORE CONTINUING.
o~..
SERVICE BULLETIN NO, 213
1 KIT. MODIFICATION OF WING STATION 39 AND 69 RIBS (cont’d)
a. Fit the 170425-1,170426-1 angles and K160010-505 fillers to the rib and lower wing skin.
i. Check for gaps between the 170625-1. 170428-1 angles and the lower wing skin. If a gap is present.select a K180015-501 tapered shim as required to prevent prelaading the structure. Shlms may hereworked and cut to sire to fill gaps. Shims must pick up a minimum of two fasteners. A MS2d426AD4rivet may be installed between existing Hi-Loks (minimum pitch .75 inch).
NOTE:IN LIEU OF A SOLID METALLIC SHIM, THE USE OF CAST PLASTIC SHIM MATERIAL (EPON934 OR EOUIVALENT, PER THE MANUFACTURES DIRECTION) IS PERMITTED UP TO AMAXIMUM OF.020 INCHES. ANY NECESSARY REMAINING SHIM MATERIAL REQUIREDBEYOND .020 SHALL BE METAL AS ABOVE. CHECK ALL INSTALLED FASTENERS WITH A.002 INCH THICK BRASS FEELER GAGE FOR SHANKING. GAGE MUST NOT TOUCH THESHANK OF THE FASTENER BEMIEEN PARTS.
9´• Remove all parts, break and smooth all sharp edges, deburr and prime per item i., as required.
h. Refinish all bare areas of the new parts with Desoto polyurethane paint 825-309 (added scarfs, reworkof tapered Shlms K180015, act.).
i. Line ream all Hi-Lok holes to the limits indicated on Figure 6.
j. Drill out any remaining fastener holes.
k. Permanently install all pans and fasteners;.
I. Modify the Wing Station 39 and 88 ribs per Figure 6, Detail B which adds a doubler angle to the upperflange and web ad]acent to the stringer and wire bundle cutout at stringer No. 3.
2. MODIFICATION OF END TRIMS OF STRINDER NO 1, 2 AND 2A.
NOTE:IF DAMAGE IS FOUND, DO NOT PROCEED WITH MODIFICATION. DAMAGED PARTSMUST BE REPLACED OR AN APPROVED REPAIR INSTALLED PRIOR TO COMPLETION OFMODIFICATION AND RETURN TO SERVICE.
a. Modify the end trims of st~nger No. 1, 2 and 2A per Figure 7 which´•adds a radius to the bulb section filletradius see Figure 3.
CAUTION:
THE 63 FINISH CALLED FOR ON FIGURE I IS EOUIVALENT TO A SMOOTH MACHINEDSURFACE, EXERCISE CARE TO NOT UNDERCUT THE EXTRUSION LEGS.
eano PI nf IR
SERVICE BULLETIN NO. 213
3. -2 KlT. MODIFICATION OF WING UPPER SKIN WING STATION 103 TO 113.
DAMAGE LIMITS
(SEE FIGURE 4)
THIS MODIFICATION IS APPLICABLE FOR:A MAXIMUM CRACK LENGTH OF 1.00 INCH IN THE UPPER WING SKIN WHICH EXTENDSFROM THE INTERSECTION OF THE LEADING EDGE SKIN (STRINDER #1) AND THENACELLE FAIRING (W.S. 103.5), AFT AND OUTBOARD AT APPROXIMATELY A 45
DEOREEANGLE.ii UPPER WING 5KIN BUCKLE IN THE BnY.
SKIN BUCKLES BETWEEN RIVETS ON STRINGER #2.
THIS MODIFICATION IS NOT APPLICABLE FOR:
t~ I\ CRI\CI( LONGER THIIN l.L)O INCH.CRACKS IN THE UPPER WIND SKIN IN AREAS OTHER THAN A OF THESE LIMITATIONS.
IF THESE LIMITATIONS ARE EXCEEDED, DO NOT PROCEED WITH MODIFICATION. DAMAGEDPARTS MUST BE REPLACED OR AN APPROVED REPAIR INSTALLED PRIOR TO COMPLETIONOR MODIFICATION AND RETURN TO SERVICE.
CAUTION:EXERCISE CARE IN DRILLING RIVETS AT WING STATION 113. THE THIRD RIVET FROMTHE FRONT OF THE 110316-3 IS DIRECTLY OVER AN EXISTING TUBE WITH NO CLEARANCETO REINSTALL A RIVET. DO NOT DRILL THIS RIVET OUT. MARK THE RIVET BUTT ON THE
ADDED PARTS AND TRIM THE PARTS (U SHAPE) TO CLEAR THE BUTT.
a. Stop drill the ends of all crackswith a No. 30 stop drill hale. Dye penetrant inspect to ensure crack does
not extend beyond stop drill.
b. Modify the wing upper Jkin per Figure 8 which adds a spacer and stiffening angles to the skin bay between
Wing Station 103 and 113, and stringer No. 1 and 2.
NOTE:
COMPLY WITH THOSE PORTIONS OF SERVICE BULLETIN 198 NECESSARY TO ENSURESEALING OF THE WING STATION 113 RIB.
NOTE:
SERIAL NUMBERS 11620, 11684, AND 99038 ARE EXCLUDED FROM STEP 3.
4. Restore finishes, sealants and paint and reinstall fuel cells, access doors and interiors as required.
NOTE:
THE FUEL CELL NIPPLE CLAMP TOROUE PROCEDURES IN SERVICE BULLETIN 167,"FUEL CELL INSPECTION ANDIOR REPLACEMENT," ALSO COULD BE OF ASSISTANCE INTHE REINSTALLATION OF ANY FUEL CELLS DISTURBED OR REMOVED.
Refuel aircraft as outlined in the Airplane Maintenance Manual.
NOTE:THE FUEL SYSTEM PRESSURE CHECK PROCEDURE OUTLINED BY SERVICE BULLETIN
185, "FUEL CELL INSPECTION ANDIOR REPLACEMENT", COULD POSSIBLY EXPEDITE
THE LEAK CHECK OF THE FUEL SYSTEM FOR THE REINSTALLED FUEL CELLS WHICHWERE DISTURBED OR REMOVED.
ntlfi
SERVICE BULLETIN NO. 213
6. Fill out the information on the Compliance Card and send to:
Twin Commander Aircraft CorporationService DepartmentP.O. Box 3388
Arlington, WA 88223
ELECTRICAL LOAD: No change.
WEIGHT AND BALANCE: No significant change.
SPARES AFFECTED: None.
RECORD COMPLIANCS; Make an appropriate entry In Airplane Maintenance Recods as follows: Senrice
Bulletin No. (213), dated June 2, 1884. entitled "WING FATIGUE INSPECTION
AND MODIFICATION," complied with as follows:
Part I inspection: List inspection items accomplished by item no., title, airplane total time, and date.
If the recommended modification of the inspection item listed has not been accomp-lished, list the next scheduled inspection times to repeat inspection of the item.
Part II Modification: List modincalions accomplished by drawing and dash no., title, airplane total time.and date.
Pane a nt 18
SERVICE BULLETIN NO. 213
w.s.
O O 0~0)F3 01C
U -io-i- ij
NSP ITEM 7 (LIR)
INSPECT FOR CRACKS
(REF. FIGURE B FOR MOD.)
MAIN 1703154 RIB (REF.)
Figure I
LEFT W.S. JB SHOWN
aTR 1i7" (Rshrrnsa 1.P.C. Figure 2-19)W.P. W.S.
INSPECT FOR CRACKSLREF. FIDURE B. OETAII B
FOR MOI)IFICATIONIO a~Ma or o
UOCIU!OCI1C~
13
i..
OTRIH3W(RBLCI
INSP. ITEM 7 C 1IOU(´•MI SlIFFENER (Rrr)(L 6 R)
~I I I i VIEW LOOKING INBOARD
FigmlLEFIWb. 38 8nOWN. W.8. 89 MI.
(Ra(aacsl.P.C.Rgun~Js)
PROS 9 0(16
SERVICE BULLETIN NO. 213
,.:5\
P
a "~.XINSP. ITEM 8 (L 6 R) P’
OISCONNECTOXYGEN I ;jIINE AT STR tll *NO #2
hlJm~,FORCRACKS (O
CHECKULF/ISTENIRS FlpuraJi*´•~IPcnwnwn
INSP ITEM g (L 1 R)
W.S.INSPECT FOR CRACKS IN THESE W.I.
AREAS (REF FIGURE 7 FOR MOO.) 1(*0 (01.5UPPER NACELLEFAIRING
LUAOINOSKIN
"01o
noio,
SrR´•I
INSPECTFOROAMIOE I
i
SEE FIGURE B I
I
n
LJRgun 4
(Rs~rsnso I.P.E. Rgwa u7. ZJg)
VIEW LOOKING DOWNgB UPPER WING SKIN
Pegs ~O of l6
SERVICE BULLETIN NO. 213
INSP ITEM 10
(i a R)
144.W
FOR CRACKS FS.
r"NO INSPECTIONi II
I i II FROMAFTSIOE
I 1 it i REOLIIRED
tW I--C----j
nu
i iil/ ~WING A~TACH i iii.YI FII1~NO (REF) I U’ I II
W
--W~TERLINE´•(O.OO
VIEW n-n I-~-n
FbnsRIGHT HAND SnOWN. LEFT HAND OPPOSITE
(Rslsranca I.P.C. FiQurr~230. 2~52)
Page 11 of 16
COMPLIANCE CARD
SERVICE BULLETIN NO. 213
WING FATIGUE INSPECTION AND MODIFICATION
MODEL: AIRPLANE SERIAL NO. TOTAL TIME (HRS)
AIRPLANE REGISTRATION NO.:
OWNER NAME:
ADDRESS:
City State Zip
TELEPHONE NO. AIRPLANE AGE: CIEARS)
PART I INSPECTION:
ilST INSPECTION ITEMS COMPLIED WITH BY ITEM NO.. TITLE, AND DATE OF COMPLIANCE.LIST DETAILS OF ANY CRACKS OR DAMAGED FOUND.
INSPECTED BY: TELEPHONE NO.
DATE SIGNATURE
PARTII MODIFICATION:
LIST MODIFICATIONS COMPLIED WITH BY MODIFICATION DRAWING AND DASH NO., TITLE.AND DATE OF COMPLIANCE.
MODIFIED BY: TELEPHONE NO.
ADDRESS:
Cny State Zip
DATE SIGNATURE
r~lllY
AIRCRAFT CORPORATION
SERVICE BULLETIN 214
March 2000
Operators of Model 900 (690D) and 1000 (695A/695B) Twin Commanders soon will
be able to bring their aircraft up to the service life standards of the last of these
models produced. Twin Commander Aircraft Corporation has developed a series of
airframe inspections and modifications, which will accomplish this. The inspectionsand modifications are explained in SE (Service Bulletin) 214.
This service bulletin provides a very thorough examination of the pressurized cabin
structure (the cockpit, passenger cabin and the inboard portion of the wing between
the two engines). The modifications involve the installation of new parts and
reinforcement of existing parts in various locations.
The areas requiring inspection andlor modification were identified by extensive
fatigue testing of a fuselage. The test fuselage accumulated significantly more
cycles than any airplane will ever experience in service. Due to the time required to
complete the testing, airplanes were being produced before the testing was
concluded. As the testing identified changes, they were incorporated into productionairplanes as they were being built. Thus, the later serial number aircraft had more of
the modifications incorporated at the factory than earlier serial number aircraft. SE
214 addresses these differences and outlines procedures required to upgrade each
aircraft to the very latest production configuration.
To complete this service bulletin, access to the complete inside of the fuselage is
required. The interior is removed; as well as the windshields, cockpit and cabin
windows, control yokes, instrument panel, cabin flooring and ductwork.
Pressurization sealer and anti corrosion compounds must also be removed in the
areas requiring inspection and modification.
Incorporation of SE 214 will ensure the continued safe and reliable operation of
these aircraft while enhancing their value. The issuance of this service bulletin is a
continuation of Twin Commander Aircraft Corporation’s commitment to support the
owners and operators while maintaining the airworthiness of the Twin Commander
fleet.
Contact your Twin Commander Service Center for additional information and details
on this service bulletin. They have knowledge, capabilities and have completed the
required training for the incorporation of SE 214 at a factory-authorized school. A
listing of Twin Commander Service Centers is attached.
Bill D. HurleyVice President and General Manager
nnJIN COMMANDER AIRCRAFT CORPORATION Arlington Airport 19010 591h Dr. N.E. Arlington, WA 98223 Telephone: (360) 435-9797 FAX: (360) 435-1112
SERVICE PUBLICATIONSLfLIAll~nAU17~EIQ
revisionII
notice A /RCRAFi’ CORPORA 7~ON19010 59’h Dr. N.E. Arlinglon,WA 98223-7832
Tel:(360)435-9797 FAX:(360)435-11~2
Service Bulletin No. 214
Revision No.
Release Date: April 19, 2000
WING AND FUSELAGE FATIGUE INSPECTION AND MODIFICATION
APPROVAL:
Engineering design aspects are FAA approved.
REVISED ITEMS AS INDICATED.
1) Part I INSPECTION I MODIFICATION TIMES, Table I, Pages 7, 8, 9, 8 10 of 72
a) Changed LEGEND at right hand side ofpage to read:
L FIGURE(S) 8 88
2) Part I INSPECTION, Figure #8B, Page 28 of 72
a) Changed REFERENCE at uppermost center ofpage to read:
TCAC DRAWING #300006-11 -529 ASSY FOR MODIFICATIONS
b) Changed FIGURE EFFECTIVITY at lower right hand corner ofpage to read:
EFFECTIVITYMODEL SIN
690D 15001 THRU 15034
695A 96014THRU 96017
695A 96019THRU 96076
EXCEPT SIN 96063,96069 96075
3) Part I INSPECTION, Figure #8C, Page 29 of 72
a) Changed REFERENCE at uppermost center ofpage to read:
TCAC DRAWING #300006-11 -529 ASSY FOR MODIFICATIONS
b) Changed FIGURE EFFECTIVITY at lower right hand corner ofpage to read:
EFFECTIVITYMODEL S/N
690D 15001THRU15034
695A 96014THRU 96017
695A 96019THRU 96076
EXCEPT SIN 96063.96069 3 96075
Page No. of i
MANDATORYr~lAI
Service Bulletin A /RCRAFT C~RPORA T/ON19010 59’" Dr.N.E. Arlington.WA 98223-7832
Tsl:(360)435-9797 FAX:(360)435-1112
Service Bulletin No. 214 Date: January 26, 2000
WING AND FUSELAGE FATIGUE INSPECTION AND MODIFICATION
EFFECTIVITY: MODEL NO,690D (Serial Numbers 15001 thru 15040, Except as Noted)695A (Serial Numbers 96001 thru 96100, Except as Noted)6958 (Serial Numbers 96063, 96069, 96075, 96078, 96085 8 96204 thru 96208)
NOTE:
SERIAL NUMBERS 15037, 15041, 15042, 96064, 96072, 96088, 96201, 96202 AND 96203 ARE
NOT SUBJECT TO THE PROVISIONS OF THIS SERVICE BULLETIN (REF. TCAC SE 232
WING AND CARGO DOOR FUSELAGE FATIGUE INSPECTION AND MODIFICATION
MREASON FOR AThis Service Bulletin information is based on data devslopsd during the iull scale Fatigue Te~t conducted I Non the Model 695A wing and pressurized cabin. These modifications are required at the specific time
Dintervals indicated to maintain airframe life of 7,500 Hours or more. This Service Bulletin does not
superrade any prior Se~vice Publicaiions issued with respect to inspections or structural modlflaatiens IAT
COMPLIANCE:O
This Service Bulletin contains three (3) time compliance schedules. There is a schedule for inspectionRmodification set forth ´•in Part I, Table I; a schedule for recurring inspections set forth in Par! II, Table I; and
the following Table A, "lnitial Compliance Times".
YINITIAL COMPLIANCE TIMES
CURRENT AIRFRAME COMPLIANCE REQUIRED PRIOR TO (HOURS TIS)OURS/ TIME-IN-SERVICE) I OR WITHIN THE NEXT TMONTHSJ WHICHEVER COMES FIRST
0000-1700 (2700) Hours or [36]Months1701-2500 (3400) Hours or [36] Months
2501-3000 (3800) Hours or [36]Months3001-5000 (5500) Hours or [30]Months5001-6000 (6400) Hours or [24] Months
6001-7500 (7800) Hours or [181MbnthsOver 7500 121 Months
Table A
The interrelationship of these schedules is as follows:
No inspections i modifications are required before the expiration of the time period set forth in Tabk~.-L
applicable to the airplane; however it is highly recommended that all of the Part r, Table I inspections I
modifications be accomplished at the earliest practicable time.
Page No. 1 of 72
2/
SERVICE BULLETIN NO. 214
COMPLIANCE: (cont.)
Before the expiration of the time period set forth in Table A applicable to the airplane, all inspectionsmodifications that are overdue according to Part I, Table I must be accomplished. Thereafter all remaininginspections I modifications described in Part I, Table I must be accomplished in accordance with the time
periods set forth in that table.
It is highly recommended by Twin Commander Aircraft Corporation that all inspections modifications
specified in Part I, Table I be completed at the time of first compliance with this Service Bulletin regardlessof total airframe hours. This will eliminate removing the same assemblies parts multiple times, and
reduce the possibility of damaging these assemblies I parts with subsequent airframe disassembly.
After initial inspections modifications have been accomplished, recurring inspections must be
accomplished in accordance with the schedule set forth in Part II, Table I.
EXAMPLE.. Aircraft has 5000 airframe Hours I Time-in-Service. The items with 1700, 2500, 3000, and 5000
Hour Aircraft Inspection Time Periods as required by Part I, Table I "INSPECTION
MODIFICATION TIMES" must be completed at or prior to 5500 Hours Time-in-Service or
30 Months, whichever comes first. It is recommended that the 6000 Hour and 7500 Hour items
also be accomplished at that time. If the 6000 Hour and 7500 Hour items are not accomplishedat the time of initial compliance, then these items must be accomplished as they come due
according to Part I, Table I. All aircraft will be subject to the recurring inspections set forth in
Part II, Table I commencing with the first compliance which includes the 3000 Hour inspection I
modification.
Part~ INSPECTIONS I MODIFICATIONS
i. All inspections modifications are MANDATORY and are set forth in Part I, TableI
2. If CRACKING or DAMAGE is found in the existing structure, and structure IS NOT REQUIRED TO BE
REPLACED WITH NEW PARTS, damaged parts must be replaced or an approved repair installed prior to
completion and return to service, except as noted per S8 214, Part I and indicated by FIGURES 21, 22 and
24 where limited cracking is allowed.
3. If CRACKING or DAMAGE is found in the existing structure, and structure IS’REQUIRED TO BE
REPLACED WITH NEW PARTS (Machined Frames, Intercostals, Angles, Clips; Fasteners, Etc.) the
modification is acceptable.
4. Twin Commander Aircraft Corporation requests that all damaged parts if any, be returned to TCAC
(Freight Postage Paid) to help us further our efforts to support the fleet for analysis.
Part II: RECURRING INSPECTIONS
There are four areas of the airc;aft depending on the model that require a recurring inspection at a specified time
interval. These areas will require a recurring inspection program, and are defined per Part II, Table I.
EXAMPLE: Aircraft has 3000 airframe Hours Time-in-Service. Full compliance with items 1700, 2500,
3000, 5000, 6000, and 7500 Hour Aircraft Inspection Time Periods per Part I, Table I was
accomplished at 1900 Hours. Compliance with Part II, Table I(Cabin Door, Figures 1 -1E
1000 Hour intervals) must be completed at this time, with the next inspection due at 4000 Hours
Time-in-Service and subsequently thereafter.
Page No. 2 of 72
/5
SERVICE BULLETIN NO. 214
INFORMATION FORMS:
For further assistance, the following forms have been included in this Service Bulletin:
COMPLIANCE FORM This form will be used as a guide for determining which InspectionsModifications have been accomplished during the course of the Service Bulletinand allows the Mechanics and Inspectors to check off or initial each item as
they are completed. After the completion of the items required by the Service
Bulletin, a copy of the Compliance Form will be added to the aircraft logbookand a copy submitted to Twin Commander Aircraft Corporation.
TRACKING FORM This form will be used as an internal guide for receiving modification parts at the
repair station facility, installations, inspections and man hour estimates.
MATERIAL DISCREPANCY This form will be used for reporting deviations, damage and or corrective
FORM action required.
BY WHOM WORK WILL BE ACCOMPLISHED:
A P Mechanic (or Equivalent), and An ASNT Level II Certified NDT Inspector (or Equivalent) per INSPECTION
QUALIFICATIONS.
NOTE:
´•IT IS RECOMMENDED THAT ALL MODIFICATIONS BE COMPLETED ONLY AT AN AUTHORIZED
TWIN COMMANDER SERVICE CENTER. TCAC HIGHLY RECOMMENDS THAT AT LEAST ONE
MECHANIC, AND ONE QUALITY INSPECTOR RECEIVE TRAINING FOR IMPLEMENTING THIS
BULLETIN. THIS TRAINING IS AVAILABLE AT FLIGHT SAFETY INTERNATIONAL (FSI) IN
BETHANY OKLAHOMA.
APPROVAL:
Modifications and Repairs described by this Service Bulletin are FAA DER Approved.
RELATED PUBLICATIONS:
SE SERVICE BULLETIN TITLE AD AD TITLE
196 Fuel Leak Inspection Wing Compartment SealingBetween W.S. 103.00 8 113.00
209 Inspection and I or Replacement of the Nose Landing Gear
Axle
218 Em Vertical Stabilizer Modification 95-13-02 Vertical Stabilizer
223 Wing Leading Edge Attachment Inspection Modification 98-08-19 Inspect Wing to FuselageAttach Points for Cracks
224C R ent of the Nose Landi Gear Bolt 98-08-25 NLG Link Bolt
226 Fla S em Ins 98-07-17 Fla S em Cable
227 ´•1 Modification of Lower Main Gear Scissors
229 Inspection of Front Spar Lower Cap at Left and Right WingStation 39.00
Page No. 3 of 72
SERVICE BULLETIN NO. 214
RELATED PUBLICATIONS: (cont.)
SL SERVICE LETTER TITLE
347 Replacement of Inner Structural Cabin Window Glass
349A Elevator Push-Pull Tube Assembly Inspection Replacement
350 1 Cockpit Insulation Overhead Switch Panel
352 Fuel Cell Interconnect Hose
353 Flight Control Chain Connector Link I
355 Fuselaae Station 386.82 Screw Torque
359 1 Fuselane Station 386.82 Frame Assembly Modification
ESTIMATED MAN HOURS:
Per Table II
PARTS DATA:
Kit parts required to comply with this Service Bulletin may be purchased through any of the nearest
TWIN COMMANDERFACTORY AUTHORIZED SERVICE CENTERS. Reference SE 214, aircraft model and
factory serial number when submitting order.
Supplied with the applicable modification kits:
TCAC DRAWING NO. 300004, 300005, 300006, 300007, and 300008 defining each modification
TCAC DOCUMENT NO. MP3-4, MP3-5, MP3-6, MP3-7, and MP3-8 detail each inspection modification
procedure sequence
TCAC PROCESS SPECIFICATIONS NO. 10.10, 30.6, 30.8, 260.1, and 260.8
May be required to be replaced, if damaged during compliance:
CABIN ENTRY DOOR PRESSURE SEAL (Part No. 90-935)
TO BE PROCURED LOCALLY: las required)
i. Polyurethane primer used for touch up on parts furnished with the Modification Kits. MIL-C-23377 per TCAC
Process Specification 30.8 or MIL-C-27725 TYPE II, CLASS A per TCAC Process Specification 30.6
2. Plexiglas Scrapers3. Fasteners required for specific modifications and I or re-installation of removed parts
CODE IDENTIFICATION DESCRIPTION
BE MS20426AD Countersunk Head Solid Rivet
BJ MS20470AD Head Solid Rivet
LZ NAS1097AD Countersunk Reduced Mead Solid Rivet
BF MS20427M Countersunk Head Monel Solid Rivet
LN MS20615M Head Monel Solid Rivet
SPECIAL TOOLS:
1. CherryMax fastener installation equipment2. GO-NO-GO gages for HI-LOK fastener inspection3. Expanded sheet metal tool kit for difficult access areas
Page No. 4 of 72
4
SERVICE BULLETIN NO. 214
GENERAL INSPECTION CRITERIA:
TYPES OF INSPECTION FOUND IN THIS SERVICE BULLETIN PER AC 43.13-18 CHAPTER 5
"NONDESTRUCTIVE INSPECTION" (NDI).
OPerform close VISUAL structural inspection as an aid in disclosing crack indications, and or failed or
working fasteners along rivet lines, terminal fastener locations in splices, fittings or doublers and at any
changes in cross section. Also areas having curved members and areas having short fastener edgedistances. Carefully remove sealant as necessary in order to allow inspection of structural elements.
Perform FLORESCENT DYE PENETRANT structural inspection as an aid in disclosingcrackingindications or other failures not detectable by visual means. Carefully remove sealant and or finishes
as necessary in order to allow inspection of the structural elements. Moderate hand pressure appliedbetween parts, in order to produce any relative movement allowed, may assist in detection of failure of
parts or joining fasteners. Also obsen/e any rub marks indicating relative movement of parts under load.
Perform either VISUAL or FLORESCENT DYE PENETRANT inspections as indicated per each applicablefigure, Part I, Table I has been arranged by INSPECTION I MODIFICATION TIMES, with the items grouped to
four basic areas of the airframe for convenience of compliance.
Areas to be inspected are identified by Part Number and i or Name and are located per the applicableFIGURE(S) and or INSPECTION FIGURE LOCATOR diagrams located on pages 13, 19, 52. Removal of
Access Panels, Pilot I Passenger Seating, Carpeting, Interior Panels, Windows, Equipment, Fuel Cells and in
some cases the removal of Structural Elements may be required to gain adequate access to the structure of the
aircraft being inspected modified.
NOTE:
ILLUSTRATED PARTS CATALOG MAY BE USED FOR ASSISTANCE IN LOCATING INSPECTION
AREAS (REFERENCE ONLY)
INSPECTIONS APPLY TO LEFT AND RIGHT HAND SIDES OF THE AIRCRAFT UNLESS
OTHERWISE SPECIFIED BY THE APPLICABLE FIGURE(S)
INSPECTION REQUIREMENTS:
i. PERSONNEL QUALIFICATIONS
a. Level II Liquid Penetrant.
b. Vision acuity requirements of M11-STD-410E, or latest revision.
c. Documented training in accordance with MIL-STD410E, or latest revision and recommended practiceSNT-TC-1A of the American Society for Nondestructive Testing.
2. MATERIALSAND EQUIPMENT
a. Solvent Cleaner, SKC-NF (Magnaflux) or equivalent per MIL-I-25135.
b. Water Washable Fluorescent Penetrant, ZLGOC, Level II (Magnaflux) or equivalent per MIL-I-25135.
c. Non-Aqueous Developer, SKD-NF (Magnaflux) per MIL-I-25135 or equivalent.d. ZB-?OO Blacklight (Magnaflux), ?OOw, 115v, 60Hz or equivalent.e. Inspection mirror.
f. Cleaner, Penetrant and Developer to be from the same manufacturer.
3. PROCESS
a. Per MIL-STD-6866.
b. Sensitivity- Type I, Method C, Level 3.
Page No. 5 of 72
SERVICE BULLETIN NO. 214
ACCOMPLISHMENT INSTRUCTIONS Partl INSPECTIONS I MODIFICATIONS
1. Refer to Part I, Table I, locate the applicable INSPECTION I MODIFICATION TIMES for the aircraft. Parr I,
TPble I defines the appropriate INSPECTION FIGURE(S) and or REQUIRED MODIFICATION DASH
NUMBER per TCAC DRAWING NO. 300004, 300005, 300006, 300007, 8 300008.
2. Disconnect batteries.
3. De-fuel airplane as outlined in the Airplane Maintenance Manual.
4. Support fuselage with wing jack stands and tail tie-down stand as outlined in Airplane Maintenance Manual.
5. Remove all interior i exterior components (Access Panels, Interior Panels, Cabin Windows and Equipment) as
required to gain access to the applicable areas of the aircraft.
6. Follow the inspection criteria specified by each FIGURE(S) to determine if any cracking or damage is present.Coordinate with the appropriate REQUIRED MODIFICATION DASH NUMBER to modify the inspected area(s).
7. For further assistance in regard to modification procedures, reference TCAC DOCUMENT NO. MP3-4, MP3-5,
MP3-6, MP3-7, and MP3-8. These procedures have been developed to aid in the inspections and or
installation of the modification parts and I or assemblies and have been arranged by REQUIRED
MODIFICATION DASH NUMBER.
NOTE:
IF CRACKING OR DAMAGE IS FOUND REFER TO ITEM #2 #3 IN COMPLIANCE SECTION.
8. Sealant and finishes must be restored per recommended Aircraft Maintenance Manual practices after
inspections modifications are completed.
NOTE:
FOR LOCAL TOUCH UP ON EXISTING STRUCTURE, CHROMATE PRIMER MAY BE USED.
DO NOT MIX CHROMATE AND POLYURETHANE PRIMERS ON THE SAME PART. ALL NEW
PARTS SUPPLIED FROM TCAC ARE ~OLYURETHANE PRIMED.
9. Perform operational check of cabin pressurization system for leaks per Aircraft Maintenance Manual practices.
10. Re-install items removed as noted per Item 5.
Page No. 6 of 72c~jr
PARTI SERVICE BULLETIN N0.~214INSPECTION /-MODIFICATION TIMES TABLE IMODEL 690D
1700 2500 1 3000 1 5000 1 6000 1 7500 AIC INSP. TIME PERIOD
AIC RND WING r FWD i PILOT I FWD AFT I PILOT FWD I AFT I PILOT FWD I AFT WING I PILOT FWD AFT WING AIC LOCATION BY TCACCABIN CABIN COMPT. CABIN CABIN COMPT. CABINI CABIN COMPT. CABIN CABIN COMPT. CABIN CABIN DRAWING NO.
SIN 300006 300008 300006 300005 300006 300007 300005 3000061 300007 300005 300006 300007 300008 300005 3000~6 300007 300008
j S: LnN cJ TI~INIC\I Ol~lr N C~ O N O 010 O S: jl O
m c3 o~lTlo cr, cr,Lno
,le---- REaD.MOD. DASH NO.
LO ~n in 1 Ln I In I In I ~n I u~l LO LnllOllnlro In Inllollollnllolln to Inllo to ~o IlolrollolYn to In I in rolln LnllnllnlLo in to rn Ln I LO NO CURRENTLY APPROVEDMODIFICATIONS AVAILABLE
15001 1 a d I LIA E E I C. F P P R S IW X Y Y Y Y via G Ii TIW V VI H O O V Z Y L a Z IIJK I- t~O O b c L~GENLI15002 1 O d LJA E E I C F P P R S IW X Y Y Y Y YIB G T TIW ‘J VI H O O V Z Y 2 a 2 ~IJ K n b c
15003 I d Ia L A E E I C F P P R S W X Y Y Y YIB G T TIW V VI H O O V 2 Y 2 a 2 ~IJ K n~ o b cl A=FIGURE(S) 1A. 1B. 1D81E
15004 1 I d IQ L A E E I C F P P R S W X Y Y Y IB G T TIW VI H a O V Z Y Z a 2 IIJ K ~3 b CI B=FIGURE1D
15005 1 1 d a LIA E E 1 C F P P R S W X Y Y Y IB G T TIW \I VI H O a V 2 Y 2 a 2 IIJ K ~3 b cl C=F’GURE1C
D=FIGURE1F15006 d I LIA E E 1 C F P P R S IW X Y Y Y IB G IT TIW V VI H O OiV Z Y 2 a Z ~IJ K b C
15007 1 I d I L A E E I C F P P R S W X Y Y Y IB G i TIW V VI H o o v z v z a Z ~IJ K Q ~1 ~I O b c
E FIGURE(S)Z g 2A
F FIGURE 2A
15008 1 I d I L A E E I C F P P R S IW X Y Y Y IB G T TIW ?I VI H O a V 2 Y Z a 2 IIJ K a ~3 ~3 b C
G FIGURE 3
15009 I d I L A E E I C F P P R S W X Y Y Y IB G IT TI-W :J VI H O O V 2 Y 2 a Z ~IJ K I Q~tlO O b c
H FIGURE 4
isoio I I d 1 LIA E E I C F P P R S IW X Y Y Y IB G T TIW V VI H O OIV 2 YI 2 a 7 ~IJ K a ~T3 b c
FIGURE 5
15011 1 d I L A E E I C FI- P P R S W X Y Y Y IB G T TIW V VI H O OIV 2 Y 2 a 2 IIJ K O b C
J FIGURE 6
15012 1 I d L A E E I C F P P R S W X Y Y Y IB G T TIW VI H O a V 2 YI Z a 2 ~IJ K a b c
K FIGURE 7
15013 1 I d I L A E E I C F P P R S W X Y Y Y (B G T TIW VI H O a V 2 Y Z a Z ~IJ K a O b cL FIGURE(S) 8. 8A. 8D 8 8E
15014 d L A E E I C F P P R S 1W X Y Y Y IB G T TIW \I VI H O OIV 2 Y Z a 7 ~IJ K 1~3 b cM FIGURE(S) 8. 8B, 8C 8 8E
15015 1 I d LIA E E I C F P P R S W X Y Y Y IB G T TIW VI H O a V 2 Y 2 a Z ~IJ K bN=FIGURE(S)S-9E
15016 1 I d L A E E i C FI P P R S IW X Y Y Y IB G T TIW V VI H O O V 2 Y 2 a Z ~IJ K b cO=FIGURE10
15017 d I LIA E E I C F P P R S W X Y Y Y IB G T TIW \I VI H O a V 2 Y Z a Z ~IJ K O b cP=FIGURE11
15018 1 I d I LIA E E I C F P P R S IW X Y Y Y IB G T TIW V VI H 10 O\V Z Y Z a 2 ~IJ K a b cQ=FIGURE12
15019 1 I d L A E E I C F P P R S IW X Y Y Y IB G T TIW V VI H O O V Z Y 2 a 2 ~IJ K I~7 b CI R=FIGURE13
15020 1 d I L A E E I C F P P R S W X Y Y Y IB G T TIW W VI H O O V Z Y 2 a Z ~IJ K Q b cl -s=FIGURE14
15021 1 I d L I A E E I C F P P R S IW X Y Y Y 18 G T TIW V VI H O O V Z Y Z a Z ~lj K b c I T FIGURE(S) 14 8 15A
15022 d I LIA E E 1 C F P P R S W X Y Y Y IB G IT TIW V VI H O a V Z Y 2 a 2 ~IJ K a 1f1 b c) U=FIGUREIS
15023 1 I d I L A E E I C F P P R S W X Y Y Y I IT TIW V VI H O O V 2 YI Z a 7 ~IJ K Q~O b cl V=FIGURE1G
15024 I d I L A E E 1 C F P P R S W X Y Y Y I IT TIW V VI H O O V 2 Y 2 a 2 ~IJ K QRO O b cl W=FIGURE17
15025 1 I d LI D E E C F P P R S W X Y Y Y I I IW V VI H O a V 2 Y 2 a Z ~LIJ K B Q IElO O b cl X=FIGURE18
15026 1 I d I L D E E C F P P R S IW X Y Y Y I I Iw v vl H lo OIV Z YI 2 a 2 ~IJ K B Q~ISZj If\ b CI Y=FIGUREIS
15027 1 I d I L D E E C F P P R S W X Y Y Y I I IW c VI H O a V 2 Y 2 a 2 ~IJ K 8 a O O b c I Z FIGURE 20
15028 1 I d I L D E E C F P P R S W X Y Y Y I I IW I’ VI H O O V Z Y Z a 2 ~IJ K B Q~O O b cl a=FIGURE(S)21821A
15029 1 I d D E E C F M P P Y Y I I IW V VI H O a V Y Z IJ K B a I~1 O O b c I b FIGURE 22
15030 I d 1 1 D E E C F M P P I v v I I I v vl H 10 O V Y I 2 IJ K B a O I~ O b c c FIGURE(S) 23 8 23A
15031 1 I d D E E C F M P P Y Y I I I L; VI H O O V Y Z IJ K B a O b c I d FIGURE 24
15032 1 I d D E E C F M P P Y Y I i I V VI H O O V Y Z IJ K B a O O b c I a FIGURE 25
15033 1 I d O E E C F M P P Y I I I L. VI H O O v Z IJ K B a O O b c I f FIGURE 26
15034 d I 1 o E E C F M P P v I I v vl H IO 01 YIZ IJ K BIQ ~j O O b cl I=\NSTAL~ MODIFICATIONAS REQUIRED
15035 1 I d D E E F P P Y I I I ~1 10 O YIZ IJ K B a ~O O b ciTR INSPECT PER APPLICABLE
15036 1 I d D E E F P P v I I I vl 10 a v 2 IJ KB Cfl b c FIGURE 8 MOD!P/ PER THEAPPLICABLE REQD. MOD.
15038 1 1 d D E E F P P I I I I V Y IZ IJ K B a I~ O O b I DASH NUMBER (-11-5XX)
15039 1 I d I I o E E F I I I I I vlz IJ K Bla 1 1 CI=FIRST INSPECTIONREQUIREOca, THE ABOVE TIME PERIOD.
15040 d I o E E F I I I I I ’J vl IJ K B a ~O REOCCURRING INSPECTIONSPER ~´•IRf II. I;lBIEI
Page No. 7 of 72
PARTI SERVICE BULLETIN NO. 214INSPECTION MODIFICATION IIMES TABLE co~MODEL 695A
1700 1 2500 1 3000 5000 1 6000 7500 AIC INSP. TIME PERIOD
:i AIC FYD WING I FWD I PILOT FWD I AFT I PILOT FWD AFf I PILOT R/VD I AFT WING I PILOT FWD AFT WING 1 AIC LOCATION BY TCACCABIN CABIN COMPT. CABIN CABIN COMPI. CABIN CABIN COMPT. CABIN CABIN COMPI. CABIN CABIN DRAWING NO.
SIN 300006 300008 300006 300005 300006 300007 300005 300006 300007 300005 300006 300007 300008 300005 300006 300007 300008
i o o (3) C3 10 O) LD a, In o, In o o,~cr, In t~ ~o (3 r? m In o, ,I~---- REQD.MOD. DASH NO.
In I In jun I Inlln mllnllnllnllnl~nl .I~nllo u, lolull~llnllnlm in LO G~IS: Inllo InlLn ~n S: O O O O O O O O 6 aN r*1 C\I O C~ CV I- O O O O O (U OIn in In In in to in to to In In u7 In to LO ~t NO CURRENTLY APPROVED
MODIFICATIONS AVAILABLE
960O1 1 d Q fA E E C F P P R S ´•I~IW X Y Y Y Y YIB G T TIW V Vf H O O V Z Y Z a Z ~IJ K ~I O b c
96002 1 d Q IA E E I C F P P R S OIW X Y Y Y Y YIB G T TIVJ V VI H O O V Z Y 2 a Z ~IJ K b C
96003 1 I d Q IA E E I C Fl P P R S NIIW X Y Y Y Y YIB G T TIW V VI H O O1V Z Y Z a Z ~(J K ~3 ~3 A FIGURE(S)1A. 1B, ID&1Ea b c
96004 1 I d Q IA E E I C F P P R S NIIW X Y Y Y Y YIB G IT TIVJ V VI H O O V Z Y Z a Z IIJ K b clB=F’GURE1D
96005 1 I d IQ A E E I C F P P R S NIIW X Y Y Y Y YIB G T T W V VI H O OrV Z YI 2 a 2 IIJ K ~OC=FIGURE1C
O b c
D=FIGURE1F96006 a IA E E C FI P P R S I)I~1W X Y Y Y Y vie G T i w v vl H to o v 2 v z a 2 ~IJ K I ITil~ ~3 b c
96007 1 I d Q IA E E C F P P R S ´•~IW X Y Y Y Y YIB G T TIVJ V VI H O O V Z Y Z a Z ~IJ K ~O O b cE=FIGURE(S)2g2A
F FIGURE 2A
96008 d I Q IA E E C F P P R S I) OIW X Y Y Y Y YIB G T TIVJ V VI H O O V Z Y 2 a 2 ~,IJ K ~3 ~3 [~3 b C
G FIGURE 3
96009 I I d I Q A E E I C F P P R S OIW X Y Y Y Y YIB G T T \rJ V VI H O O V Z Y 2 a 2 IIJ K ~3 Jb C
H FIGURE 4
96010 d I Q IA E E C F P P R S OIW X Y Y Y Y YIB G T T W V VI H 10 OIV 2 Y 2 a Z ~IJ K ~3 b c
FIGURE5
96911 I I d JQ A E E I C F P P R S ´•I~JW X Y Y Y Y YIS G T TIVJ V VI H O OIV 2 Y1 2 a 2 ~IJ K I~3 b c
J FIGURE 6
96012 d I Q IA E E C F P P R S OIW X Y Y Y Y Y1B G T TIW V VI H O O V 2 Y 2 a 2 ~IJ K b cK FIGURE 7
96013 1 I d Q IA E E C F P P R S OIW X Y Y Y Y Y(B G T TIW V VI H 10 O V Z Y 2 a Z ~IJ K b cL FIGURE(S) 8. 8A, 8D 8 8E
96014 j I d Q LIA E E C FI P P R S W X Y Y Y Y YIB G T T W V VI H O O V Z Y 2 a 2 IIJ K ~3 b CM FIGURE(S) 8. 8B, 8C 8 8E
96015 1 I d Q L IA E E C F P P R S W X Y Y Y Y YIB G T T W V VI H O O V 2 Y 2 a Z ~IJ K ~3 b c
N=FIGURE(S)S-SE
96016 d Q LIA E E 1 C F P P R S IW X Y Y Y Y YIS G IT TIVr! V VI H 10 O\V 2 Y\ 2 a 2 ~IJ K ~llul b cO=FIGURE10
96017 d IQ LIA E E C F P P R S IW X Y Y Y Y YIB G T TIVJ V VI H O O V 2 Y 2 a 2 ~IJ K ~3 b cP=FIGUREII
96018 1 I d Q IA E E C F P P R S O(W X Y Y Y Y YIB G T T W V VI H 10 O V Z YI Z a Z ~IJ K I~3 bO=FIGURE12
96019 d IQ LIA E E C F P P R S W X Y Y Y Y YIB G T T V VI H 10 O V Z Y Z a 2 ~IJ K L~ ~3 ~3 b clR=FIGURE13
96020 d IQ LIA E E C F P P R S W x v v v v vie G T TIVII V VI H O O V Z Y Z a Z ~IJ K b clS=FIGURE14
96021 1 8 Q L I A E E C FI P P R S W X Y Y Y Y YIB G IT TIW V VI H O O V Z YI Z a Z ~IJ K O b c I r FIGURE(S)14 8 1SA
96022 d IQ L IA E E C F P P R S W X Y Y Y Y YIB G T T V~ V VI H 10 O V 2 Y Z a Z ~IJ K O b clU=FIGUREIS
96023 1 I d Q L IA E E C F P P R S w x Y Y Y Y YIB G T T W V VI H O OIV 2 Y Z a 2 IIJ K b clV=FIGUREIG
96024 d 1 (3 L I A E E C F P P R S W X Y Y Y Y YIB G T T W V VI H O O V 2 Y Z a Z ~IJ K L~ O I~ b c IW FIGURE 17
96025 d IQ L IA E E C F P P R S W X Y Y Y Y YIB G T T W V VI H 10 O V Z Y Z a Z ~IJ K ~7 b clX=FIGURE18
96026 1 Q d I LIA E E C F P P R S W X Y Y Y Y YIB G T T W V VI H O O V 2 Y Z a Z ~IJ K O b c(y=FIGUREIS
96027 Q d I L I A E E C F P P R S W X Y Y Y Y YIB G T T V~ V VI H O O V 2 Y 2 a Z A(J K I O b c I 2 FIGURE 20
96028 Q d I L IA E E C F P P R S W X Y Y Y YIB G T T W V VI H 10 O V Z Y Z a 2 ~IJ K ~O O b c a=FIGURE(S)21821A
96029 d I Q L i A E E C F P P R S W X Y Y Y YIB G T T Vv V VI H O O V 2 Y Z a Z ~IJ K O b c I b FIGURE 22
96030 1 I d Q L I A E E C F P P R S W X Y Y Y IB G T T W V VI H O O V 2 Y Z a 2 ~IJ K b c I c FIGURE(S) 23 8 23A
96031 1 I d Q L I A E E C F P P R S W X Y Y Y IB G T T Me V VI H O O V Z Y Z a Z ~IJ K O O b c Id FIGURE 24
96032 1 I d I Q L A E E C F P P R S W X Y Y Y IS G T T W V VI H 10 O V Z Y Z a 2 ~IJ K O O b c I a FIGURE 25
96033 d I L I A E E C F P P R S W X Y Y Y IB G T T VV V VI H O O V 2 Y Z a 2 ~IJ K g O O b c I f FIGURE 26
96034 d I L I A E E C F P P R S W X Y Y Y IB G T T V~ V V I H O O V Z Y Z a Z IIJ K O b c I I INSTALL MODIFICATIONAS REQUIRED
96035 d I L IA E E C F P P R S W X Y Y Y IB G T T W V VI H 10 O V Z Y 2 a Z ~IJ K a~III1 ~3 b cINSTALL MODIFICATION.
96036 d I L IA E E I C F P P R S W X Y Y Y 18 G T T W V V I H IO O V Z Y Z a Z IIJ K Q ~il O b cNO INSPECTION REQUIRED
96037 I d I LIA E E I C F P P R S W X Y Y Y IB G T T WV VI H 10 O V Z Y 2 a Z 1~IJ K b cTR= INSPECT PERAPPLICABLE
FIGURE 8 MODIFY PER THE
96038 d I L IA E E C F P P R S W X Y Y Y IB G T T W V VI H 10 O V 2 Y Z a 2 ~1J K ~3 b cAPPLICABLE REQD. MOD.DASH NUMBER (-II -5XX)
96039 I d L I A E E C F P P R S W X Y Y Y IB G T T W V V i H I O O V Z Y Z a Z IIJ K Q O O b ~jO FIRST INSPECTIDN REQUIRED
96040 d I L IA E E C F P P R S W X Y Y Y IB G T T V\’ V VI H O O V Z Y z a Z ~IJ K I~ O b c ~ETHE ABOVE TIME PERIOD.OCCURRING INSPECTIONS
d I L I A E E C F P P R S W X Y Y Y IB G T T W V VI H O O V Z Y Z a Z IIJ K O I b c I PER P.JRTIL TABLEI
PARTI SERVICE BULLETIN NO. 214INSPECTION MODIFICATION TIMES
MODEL 695A TABLE I~1700 1 2500 1 3000 1 5000 1 6000 1
AIC FwD I WING RND I PILOT I RND AFT I PILOT I FWD AFT PILOT I FWD AFT WING PILOT FVVC AFT WING A/C LOCATION BYTCACCABIN CABIN COMPT. I CABIN CABIN COMPT. I CABIN CABIN COMPT. i CABIN CABIN COMPT. CABIN CABIN DRAWING NO.S/N 300006 300008 300006 300005 1 300006 300007 300005 1300006 300007 300005 1 300006 300007 300008 300005 300006 300007 300008
I m o (3) ~n I r3 0, cT)I1D I ~j r-lln I~ I o o c~lln a,ln ,If----- REQO.MOD.DASH NO.N
LD C: N N O N N O 10 1 O O 01010 O N l(r Oin ul ~llc: LII u, ul lo ~llo I ul lnIlnIln to Imlu, mim mllolvllu, ml~n in in ln I m NO CURRENTLY APPROVED’Ilnilni1niu3
MODIFICATIONS AVAILABLE
96043 I d LIA E E I C Ff P P R S W X Y Y Y IB G 7 T WV VI H 10 a V Z Y Z a Z A(J K t a i~ 01 c
96044 d L A E E I C FI P P R S W X Y Y Y B G T T W V VI H lO O V Z Y 2 a Z ~IJ K IIi3 b c
96045 d I LIA E E I C FI P P R S W X Y Y Y 18 G T T W V VI H 10 O V 2 Y Z a 2 IIJ K .i~01 c/ A=FIGURE(S)1A. 1B, 1D81E
96046 1 I d L I A E E I C F/ ’P P R S W X Y Y Y IB G T TIW V VI H 10 O V Z Y Z a 2 ~IJ K a j~ O [I~ b c 1 B FIGURE 10
96047 1 I d L I A E E I C Fi P P R S W X Y Y Y lB G T T w v vl H lo O v z v 2 a Z ~IJ K a 1~3 O C FIGURE 1CIII b c
96048 i I d I LIA E E I C FJ P P R S W X Y Y Y IB G T TlW \I VI H 10 O V Z Y Z a Z ~IJ K ofZ11~3D=FIGURE1F
b c
96049 1 I d LIA E E I C FI P P R S W X Y Y Y IB G T TIW V VI H lO O V Z Y Z a Z ~IJ K a ~O b cj E=FIGURE(S)28 2A
F FIGURE 2A96050 1 I d LIA E E I C FI P P R S W X Y Y Y IB G T TIW V VI H lo O V Z Y Z a Z ~IJ K O b c
G FIGURE 396051 1 I d I L(A E E I C FI P P R S W X Y Y Y IB G T T W V VI H 10 OIV Z Y 2 a 2 ~IJ K a ~t10 n b c
H FIGURE 496052 1 I d LIA E E I C FI P P R S W X Y Y Y IB G T T W V VI H 10 O V 2 Y Z a 2 ~iJ K a O b c
FIGURE 596053 d I LIA E E I C F´•l P P R S W X Y Y Y iB G T T W V VI H 10 O V Z Y Z a 2 ~IJ K b c
J FIGURE 696054 d I LI E E I C FI P P R S W X Y Y Y I AIT T W V VI H 10 O V Z Y Z a Z ~IJ K a b c
K FIGURE 796055 1 I d L I E E I C FI P P R S W X Y Y Y I AIT T W V VI H 10 O V Z Y 2 a Z ~IJ K a ~3 b c
L FIGURE(S) 8, 8A, 8D 8 8E96056 1 I d I L I D E E C FI P P R S W X Y Y Y I I Iw v vl H lo OIV Z YI 2 a Z ~IJ K B a ~7 ~3 tll b c
M FIGURE(S) 8. 8B, 8C 8 8E
96057 I d I LI D E E C FI P P R S W X Y Y Y I I IW v vl H lo O V Z Y Z a Z ~IJ K B O (b c
N=FIGURE(S)S-9E96058 1 i d L I D E E C FI P P R S W X Y Y Y I I IW v vl H to O V Z Y 2 a Z ~IJ K B Q r~IO ~7 b c
O=FIGUREIO
96059 1 I d I I o E E C FIM P P v v I I Iw v vl H lo O V YI 2 IJ K B O b cP=FIGUREI1
96060 d I I D E E C FIM P P v v I Iw v vl H 10 O V Y 2 IJ K B b cQ=FIGURE12
96061 I I d I I D E E C FIM P P v v I I Iw v vl H 10 .O V Y 2 IJ K B a O b cR=FIGURE13
96062 d I I D E E C FIM P P v v I I I v vl H lO O V Y 2 IJ K B aOO O b cS=FIGURE14
96065 I I d I D E E C FIM P P v Y I I I v vl H lo O V Yi 2 IJ K B a IZC1 D O b c I T FIGURE(S)14 8 15A
96066 1 I d o E E C FIM P P v v I v vl H lo O V Y Z IJ K B a b c I U FIGURE 15
96067 1 I d I I o E E C FIM P P v I I I v vl H to O Y Z IJ K B Q~O b cl V=FIGUREIG
96068 d I I D E E C FIM P P v I I I v vl H lO O Y Z IJ K B Q I~O O b cl W=FIGURE17
96070 1 I d I D E E C FIM P P Y I I I v vl H lo O YIZ IJ K B a C~O O b cl X=FIGURE18
96071 d I I D E E C FIM P P v I I V V H 10 O Y Z IJ K B Q O~ O b cl y=FIGURE1S
96073 1 I d I D E E C F(M P P v I I v vl H lo O YIZ IJ K B Q If~ O b c 2 FIGURE 20
96074 d I I D E E C FIM P P v I I I v vl H lo O Y Z IJ K B Q O b c I a FIGURE(S)21 8 21A
96076 1 I d D E E FIM P P v I I I v vl H lO O Y IZ IJ K B Q I~ O O b c I b FIGURE 22
96077 d I I D E E F I P P Y I I I vl io O Y IZ IJ K B a b c I c FIGURE(S) 23 8 23A
96079 1 I d D E E F I P P v I 1 I v I to o Y IZ IJ K B a n o CSI b c I d FIGURE 24
96089 I I d D E E F I P P v I I I v I lo O v 2 IJ K B a O b c I a FIGURE 25
96081 I I d I I D E E F P P v 1 v I \O O v It IJ K B a O b c I f FIGURE 26
96082 I d D E E F I P P v I I I vl lo O y IZ IJ K B a O O b c I A INSTALL MODIFICATIONAS REQUIRED
96083 d i D E E F I P P I I I vl I I v 2 IJ K B a 1~ O O b cLTR INSPECT PER APPLICABLE
96084 d I I D E E F P P I I 1 vl I I v z IJ K B a O b c FIGURE 8 MODIFY PER THEAPPLICABLE REQD. MOD.
96086 I d I I o E E F I P P I I I I vl I I v 2 IJ K B Q D D b I DASH NUMBER (-11-5XX)
96087 d I I D E E F I P P I I 1 I v I I I v z IJ K B Q O O O b O FIRST INSPECTION REQUIREDB THE ABOVE TIME PERIOD.
96089 d I I D E E FI P P I I I I vl I I v z IJ K B(Q n b REOCCURRING INSPECTIONSPER P.JRTII. TrlBLE I
96090 d I I D E E FI P P I I I I v! I I v z IJ K B O 0096091 d I I D E E F I P P I I I I vl I I Y I IJ K B a [~j O O b
96092 d I I o E E FI I I I I vl I I v J K B a O
Page No. 9 of 72
PARTISERVICE BULLEIIN NO. 214
INSPECTION MODIFICATION TIMESMODEL 695A TABLE I co~r,
1700 1 2500 1 3000 5000 6000 i3 AIC FWD I WING FWD I PILOT FWD I AFT I PILOT FWD AFT PILOT FWD AFT WING PILOT NWD AFT WING 1´• AIC LOCATION BY TCACCABIN CABIN COMPT. CABIN CABIN COMPT. CABIN CABIN COMPT. CABIN CABIN COMPT. CABIPJ CABINS/N 300006 300008 300006 300005 300006 300007 300005 300006 300007 300005 300006 300007 300008 1 300005 300006 300007 300008
DRAWING NO.
I ct I lr I r-lmm re
N o o a n ,It-- REao. MOO. DASH ND.~-ln m In
oN CI 00 NN 00 a D N
1O _ _ _ in LO in YI Y1 in Lnln mlu~ NO CURRENTLY APPROVED
o N o o NIn In in Ln to LD LO ~n to In to to to In to to to to
MODIFICATIONS AVAILABLE
96093 1 I d I D E E FI I I I r vl I I YI IJ K Bin96094 d D E E F vl i I Yl IJ K B Q
96995 r I d I I D E E F I I I I I vl I I Y J K B Q ~O I 1 A FIGURE(S)1A. 16. 1D81E
96096 d I I D E E FI I I i vl I I Y J K B Q I~O O I 1 B=FIGURE1D
96097 1 I d I I D E E F I I I I I v Yl iJ K B Q I I C FIGURE 1C
96098 1 I d I I O E E F I I I I i vl I I Yl IJ K B Q I I D FIGURE 1F
96999 I I 6 I I D E E FI I I I I vr I I Y J K BIQ I I E=FIGURE(S)28 2A
96100 1 I 6 I I D E E F I I I I I v Y I I B la 1I~ I IF FIGURE 2A
G FIGURE 3
H FIGURE 4
PARTI I I FIGURE 5
INSPECTION MODIFICATION TIMESJ FIGURE 6
MODEL 695BK FIGURE 7
1700 1 2500 1 3000 5000 1 6000 7500 L FIGURE(S) 8. 8A, 8D 8 8E
AIC FWD W’NG I FWD I PILOT FWD AFT I PILOT FWD AFT I PILOT FWD AFT WING PILOT FWD AFT WING 1 M FIGURE(S) 8. 88. 8C 8 8ECABIN CABIN COMPT. CABIN CABIN COMPT. CABIN CABIIJ COMPT. CABIN CABIN COMPT. CABIN CABIN
SIN 300006- 300008- 300006 300005- 300006- 300007- 300005- 300006- 300007-1300005- 300006- 300007- 300008- 1 300005- 30000r3- 300007- 300008- N=FIGURE(S)S-SE
O=FIGUREIOcr, I cr, IT I(nllOlPI r- 10 m
o o 8 (S,LnO N O O O hi (V O CV O (V 0 O O O ~1 o o P FIGURE 11
cu (u hi O O hito 10 in in in tn Ln to Ln in In In In to in In Ln to in ~o In In tn In in to to In to In to Lo un Ln In
in In In to in In In Ln to In-
Q=FIGURE1296063 d I I 1 I I I I I I I Lf_l I I. R=FIGURE1396069 d I I I I 1 I I I I I I I I no o I ~=FIGURE1496075 d I I I I I I I I I I 1 00 O I T=FIGURE(S)14B1SA96078 1 I d I I I I I I I 1 ~7 U FIGURE 15
96085 d I I I I I I I I I I I I n V=FIGUREIG
96204 d I I E FI I I I I vl I I v a O W=FIGURE17
96205 1 I d I I E F1 I I I I v YI I la O ~3 ~3 X=FIGURE18
96206 d I I E FI I I 1 I v YI I la Y=FIGUREIS
96207 1 1 d I I E FI I I I v Y I lo 1~3 2 FIGURE 20
96208 d I I I I I I I I 1 I I I I ~a o o a FIGURE(S) 218 21A
b FIGURE 22
FIGURE(S) 23 8 23A
d FIGURE 24
a FIGURE 25
f FIGURE 26
LTR INSPECT PER APPLICABLEFIGURE 8 MODIFY PER THEAPPLICABLE REQD. MOD.DASH NUMBER (-11-5XX)
(7 FIRST INSPECTION REQUIREDTHE ABOVE TIME PERIOD.
REOCCURRING INSPECTIONSPER P,IRTII, T~BLE I
Page No. 10 of 72
SERVICE BULLETIN NO. 214
?114BL~ IIMAN HOUR ESTIMATES
COLUMN 2 (INSPECT1ON)TIME REQUIRED FOR GAINING ACCESS, INSPECTION 8 RE-INSTALLATION OF REMOVED PARTS
COLUMN 4 (MODIFICATION)TIME REQUIRED FOR INSTALLATION OF M001FICATION PARTS
PILOT’S COM PARTM ENT
TCAC DRAWING 300005
INSPECTION ESTIMATED MAN MODIFICATION ESTIMATED MAN
FIOURE(S) HOURS (INSP.) DASH NO. HOURS (MOD.)
6 10.0 HR -i 4.0 HR
7 12.0 HR ´•501 4.0 HR
4 4.0 HR -503 42.0 HR
1A, 18, iD 8 if 48.0 HR 505 66.0 HR
if i.O HR 507 1.0 HR
1D ´•1.0 HR 509 1.0 HR
iD 25.0 HR -511 18.0 HR
2 8 2A 60.0 HR 513 24.0 HR
282A 1.0 HR -515 2.0 HR
3 8.0 HR 517 5.0 HR
5 6.0 HR -519 20.0 HR
1C 8.0 HR 521 2.0 HR
1A, is, 1D 8 if 26.0 HR .523 18.0 HR
2A ´•1.0 HR 525 3.0 HR
FORWARD CABIN
TCAC DRAWING 300006
INSPECTION ESTIMATED MAN MODIFICATION ESTIMATED MAN
FIGURE(S) HOURS (INSP.) DASH NO. HOURS (MOO.)
8, 8B, 8C 8 88 3.0 HR -i 1.0 HR
10 15.0 HR ´•501 32.0 HR
´•10 2.0 HR -503 2.0 HR
11 8.0 HR -507 2.0 HR
ii 20.0 HR -509 60.0 HR
13 6.0 HR 14.0 HR
14 1.0 HR -513 1.0 HR
14 <1.0 HR -515 6.0 HR
14 8 15A 134.0 HR -517 60.0 HR
12 2.0 HR -519 2.0 HR
12 iZ.O HR -521 16.0 HR
12 iZ.O HR -523 i 4.0 HR
12 12.0 HR -525 16.0 HR
NIA 15.0 HR -527 8.0 HR
8, 8A, ED 8 8E i 2.0 HR ´•529 20.0 HR
9 98 10.0 HR NIA NIA
15 40.0 HR NIA NIA
25 8.0 HR NIA NIA
Page No. ?1 of f2
SERVICE BULLETIN NO. 214
TABLE IlconrMAN HOUR ESTIMATES
COLUMN 2 (INSPECTION)TIME REQUIRED FOR GAINING ACCESS, INSPECTION 8 RE-INSTALLATION OF REMOVED PARTS
COLUMN 4 (MODIFICAflON)TIME REQUIRED FOR INSTALLATION OF MODIFICATION PARTS
AFT CABIN
TCACbRAWING 3(r0007
INSPECTION ESTIMATED MAN MODIFICATION ESTIMATED MAN
FIOURE(S) HOURS (INSP.) DASH NO. HOURS (MOD.)
16 <1.0 HR -1 2.0 HR
20 16.0 HR 501 24.0HR
17 <1.0 HR 503 4.0 HR
18 2.0 HR 505 5.0 HR
17 8;0 HR 607 6.0 HR
19 80.0 HR 609 2.0 HR
19 60.0 HR 511 34.0 HR
19 ~1.0 HR 513 8.0 HR
19 8.0 HR 518 2.0 HR
16 <1.0 HR 617 1.0 HR
19 8.0 HR 521 2.0 HR
19 8.0 HR 523 4.0 HR
18 8.0 HR 525 6.0 HR
26 16.0 HR NIA NIA
WING
TCAC DRAWING 300008
INSPECTION ESTIMATED MAN MODIFICATION ESTIMATED MAN
FIGUR#S) HOURS (INSP.) DASH NO. HOURS (YOD.)
20 4.0 HR -1 4.0 HR
20 8.0 HR 501 16.0 HR
21 8 21A 60.0 HR 503 32.0 HR
20 i 2.0 HR 505 3.0 HR
22 12.0 HR 507 24.0 HR
23 8 23A 16.0 HR -509 24.0 HR
NIA ~1.0 HR -511 16.0 HR
24 32.0 HR ´•513 32.0 HR
Page No. 12 of 72
SERVICE BULLETIN NQ. 214
Part I
INSPECTION
FIGURE #IB zzPOF~BL´•
FIGURE #~D
l~Z."Ooo, I\ II o
O o
oO oo
b.´•~e
´•0O
FIGURE #IA "a~Lb r FIGURE #IEi I 1 L 8 RM S1DE
i 1 JFIGURE#IC-’ I
1 111
:0’’’I, I
(I 1
IiiI,,y II
FIGURE #~F
L.B.L. 6.05
FIGUREFORWARD PRESSURE BUL~KHEAD
MODELS 690D, 695A 6958
INSPECTION FIGURE LOCATOR
VIEW LOOKING AFT F.S. 5.50
Page No. 13 of 72
SERVICE BULLETIN NO. 214
Part I
INSPECTION
REFERENCE
TCAC DRAWING #300005505 8 -523 ASSY FOR MODIFICATIONS
TCAC DOCUMENT #MP3-5 FOR MODIFICATION PROCEDURES
R.B.L.310933-33 CAP 6.05(REF.)
lea~lNSPECT FOR CRACKS U(TENDINGFPI IABOVE 8 BELOW THE INBD END
OF THE 310933-29 STIFFENER IN THE
310933-11 WEB
NOTE:REMOVE THE 310933-29 STIFFENER
310933-11 WEB TO GAIN ACCESS TO THE 310933-11 WEB II(REF.) FOR INSPECTION PURPOSES
310933-29 STIFFENER
(REF, I+II
W.L. -48.00
rtJ--
/II/f
‘INSPECT FOR CRACKS ALONG EDGEIFPI OF 310933-29 STIFFENER IN THE
310933-11 WEB FROM R.B.L. 6.05 TO THE
OUTBOARD TERMINATING END OF PART.
INSPECT FROM THE FORWARD SIDE OF
THE PRESSURE BULKHEAD (F.S. 5.50)
IIINSPECT FOR MISSING MATERIAL
(FPI., CRACKS ON THE 310933-29
STIFFENER UP
OUTEDcj-DETAIL
INBD END OF 310933-29
STIFFENER
FIGURE #1A QVIEW LOOKING AFT THE RIGHT HAND
FORWARD PRESSURE BULKHEAD (F.S. 5.50)
Page No. 14 of 72
SERVICE BULLETIN NO. 214
Pari~
INSPECTION
REFERENCE
TCAC DRAWING #300005-505 -523 ASSY FOR MODIFICATIONS
TCAC DOCUMENT #MP3-5 FOR MODIFICATION PROCEDURES
I II 1 INSPECT RIVETS ALONG UPPER EDGEI V 10F THE 310933-11 WEB FOR LOOSE OR
SHEARED CONDITIONS FROM W.L. -40.00TO THE AIRCRAFT CENTERLINE
‘INSPECT FOR CRACKS EXTENDING~FPIooWNWARDs FROM THE UPPER OUTED a THE 310933-55 STIFFENERCORNER OF THE 310933-57 DOUBLER
TO GAIN ACCESS TO THE 310933-11WEB FOR INSPECTION PURPOSES
f 1 111 1 /-310933-55 STIFFENER
O (REF.)
f’
O +I
f( Ical INSPECT FOR CRACKS ALONG THEx FPI JVERTICAL EDGEOFTHE 310933-55
O +i!JV STIFFENER ANO 31033557 OOUBLER.
INSPECT FROM THE FORWARD SIDE
OF THE PRESSURE BULKHEAD
310933-57DOUBLER II+ O (F.S. 5.50)
(REF.)
O310933-11 WEB t
(REF.)UP
O310933-21 CAP
O O..~M-I
(REF.) +I
-r
PJ i +I
W.L. -40.00
1 INSPECT FOR CRACKS EXTENDINGFPI i UPWARDS FROM THE LOWER OUTED R.B.L. 12.00
CORNER OF THE 310933-57 DOUBLER
NGURE #?BVIEW LOOKING AFT THE UPPER RIGHT HAND
FORWARD PRESSURE BULKHEAD (F.S. 5.50)
Page No. 15 of 72
SERVICE BULLETIN NO. 214
Part I
INSPECTION
REFERENCETCAC DRAWING #300005-521 ASSY FOR MODIFICATIONS
TCAC DOCUMENT #MP3-5 FOR MO01F1CAT10N PROCEDURES
I IIIINSPECT RIVETS COMMON TO THEV 1310944-33 CLIP FOR LOOSE OR
SHEARED CONDITIONS L.B.L.INSPECT FROM THE AFT SIDE OF THE 6.OSPRESSURE BULKHEAD (F.S. 5.50) 310933-21 CAP
(REF.)
3- t t t t tt: i
------I--W.L. 40.00=-r-------------
I~
,,~r--W.L. -41.20310944-33 CLIP
(REF.) I -C II
=c’(
,-7
-511_,==-’~I t
c=-------,310933-15 FRAME
I+ (REF.)
310933-9 WEB
(REF.) +I
310933-13 DOOR
(REF.)
FIGURE CVIEW LOOKING FORWARD THE LEFT MAND
FORWARD PRESSURE BULKHEAD (F.S. 5.50)
eage No. 16 of 72
SERVICE BULLETIN NO. 214
Pari I
INSPECTION
REFERENCE
TCAC DRAWING #300005-505, -509, -511 8 -523 ASSY FOR MODIFICATIONS
TCAC DOCUMENT #MP3-5 FOR MODIFICATION PROCEDURES
NOTE: INSPECT RIVETS ALONG UPPER EDGE
OF THE 310933-9 WEB FOR LOOSE ORREMOVE THE 310933-23 BEAM AND
310933-27 STIFFENER TO GAIN ACCESS SHEARED CONDITIONS FROM W.L. -40.00
TO THE 310933-9 WEB FOR INSPECTION TO AIRCRAFT CENTERLINE
PURPOSES ~7 INSPECT FOR CRACKS ALONG THECIL 310933-9 WEB FP
310933-23 BEAM ~\1+ SVERTICAL EDGE OF THE 310933-27
(REE)7 INSPECT FROM THE FORWARD SIDE
STIFFENER.
OF THE PRESSURE BULKHEAD
(F.S. 5.50)(REF.) f It 3-
+I310933-27
STIFFENER
(REF)
+IR~I
+i;\ il!+
\II´•++I’+ +I
)+I+i! I+ ~I I I!+
.;u I,
r+
´•Iti´•, 7 UP
-tlli-/tt-\+ +i f f fW.L. -40.00
U
~INSPECT RIVETS COMMON TO LOWERL.B.Li6.a5 \--310433-21CAP CB.L 12.00
U (REF.)I 1ENDOFTHE310933-23 BEAMFOR
LOOSE OR SHEARED CONDITIONS
INSPECT FOR CRACKS AROUND THE RINGleal INSPECT FOR CRACKS ALONG THE
I i OUTFLOW VALVE DOUBLER RINGS.IFPJVE,T,CAL EDGE OF THE 310933-23REMOVE DOUBLER RING TO INSPECT
BEAM ON THE 310933-9 WEB.
INSPECT FROM THE FORWARD SIDE
OF-THE PRESSURE BULKHEAD (F.S. 5.50)
FIGURE #?DVIEW LOOKING AFT THE UPPER LEFT HAND
FORWARD PRESSURE BULKHEAD (F.S. 5.50)
Page No. 17 of 72
SERVICE BULLETIN NO. 214
PartlINSPECTION
REFERENCE
TCAC DRAWING #300005-505 -523 ASSY FOR MODIFICATIONS
TCAC DOCUMENT #MP3-5 FOR MODIFICATION P~ROCEDURES
310933-3 FRAME NOTE:(REF) REMOVE THE AFT CORNER GUSSET
310933-11 WEB TO GAIN ACCESS TO THE CORNER
(REF)-;r RELIEF CUT-OUT
310933-21 CAP
(REF.)
iT’;-T--+----+-----t’;~CORNER GUSSET
LOCATED ON AFT SIDE
OF FWD PRESSURE
BULKHD(REF)WL. -40.00----
UP
I INSPECT FOR CRACKS AROUND THE INBOARDFPI J END OF THE ANGLE RELIEF CUT-OUT IN THE
310933-11 WEB.INSPECT FROM THE AFT SIDE OF THE
PRESSURE BULKHEAD (F.S. 5.50)
FIGURE #?EVIEW LOOKING FORWARD THE LEFT HAND
FORWARD PRESSURE BULKHEAD (F.S. 5.50)
REFERENCE
TCAC DRAWING #300005-507 ASSY FOR MODIFICATIONS
TCAC DOCUMENT #MP3-5 FOR MODIFICATION PROCEDURES
L.B.L.
6.05310933-13 DOOR 310933-9 WEB NOTE:
(REF.)----\ (REF.)~ DO NOT REMOVE THE 310933-35
310933-31-\ STIFFENER F~PECTIONCAP (REF.
$-II
W.L. -55.50-
C f I c
I 11 1 INSPECT RIVETS ALONG 310933-35
310933-35 STIFFENER
L.~..tlIcl B
I! jfj I
(REF.)U JSTIFFENER AND GENERAL AREA FOR INSPECT FOR CRACKS ALONG THE UPPER
LOOSE OR SHEARED CONDITIONS IF PI LOWER EDGE OF THE 310933-35 STIFFENER
IN THE 310933-9 WEB.
INSPECT FROM THE FORWARD SIDE
OF THE PRESSURE BULKHEAD (F.S. 5.50)
NGURE #1F gVIEW LOOKINGAFT THE LOWER LEFT HAND
FORWARD PRESSURE BULKHEAD (F.S. 5.50)
Page No. 18 of 72
B
SERVICE BULLETIN NO. 214
Part IINSPECTION
FIGURE #~7FIGURE #~6FIGURE #~4
;´•n FIGURE#23AFIGURE
#20FIGURE #~OFIGURE #2 FIGURE #5-
FIGURE #~5A
Page #24 7 /r
Page #20 Page #38 Page #42 Page #51 Page #41 Page #48
FIGURE #2A R/H Side Only 4 UH Side 8 4 R/H Side
(8 Total Locations) F.S- FIGURE #~9 FIGURE #26Page #21 FIGURE #15A
7 Page #57164.82
W.L. Page #46 Page #46 Page #50 Page #60
+2.001111 11 I
IW.L. ~I
0.00W.L. j Ij-10.00
FIGURE #4Page #23
W.L.
-28.00
W.L.
-40.00
W.L.
11\ 111\1111111 1 1111 1 1 11) 111~ 11,
W.L.
12.50 37.00 52.67 69. 87.00i
108.00 126.00 144.00163.50 178.715 198.00F.S. F.S. F.S. F.S.
65.00
iF.S. F.S. F.S. F.S. F.S. F.S. F.S.
217.14 230.00
F.S. F.S.
F.S. F.S. F.S. F.S. F.S. F.S. F.S. F.S. F.S. F.S. F.S. F.S. F.S. F.S.
5.50 23.50 45.34 60.50 78.00 96.50 99.00 117.00 135.00 155 54 172.50 188.00 209.24 223.98
FIGURE #6 FIGURE #3 FIGURE #12 FIGURE FIGURE #25 FIGURE #~8
Page #25 Page #22 Page #40 Page #39 Page #59 Page #49
UH Side Only I UH Side 6 10 NH Side
FIGURE #7 (17 TotalLocati~ns)FIGURE #25
Page #25Page #59
R/H Side Only
FUSELAGE STATION DIAGRAM
MODELS 690D, 695A 695B
INSPECTION FIGURE LOCATOR
Page No. l9 of 72
SERVICE BULLETIN NO. 214
Part
INSPECTION
REFERENCE
TCAC DRAWING #300005-513 8 -515 ASSY FOR MODIFICATIONS
TCAC DOCUMENT #MP3-5 FOR MODIFICATION PROCEDURES
NOTE:
PARTIAL REMOVAL OF THE 31~928-31 INNER INSPECT ALL RIVETS COMMON TO THEFRAME DOUBLER IS REQUIRED TO GAIN ACCESS 310928-31 INNER FRAME DOUBLER FORFOR INSPECTION PURPOSES LOOSE OR SHEARED CONDITIONS
INSPECT
5.00 INCH
Q310928-31 INNER FRAME
DOUBLER (REF)
COCKPIT OVERHEAD 61~x
xWINDOW (REF.)31089913 EYEBROW
NOTE:FRAME (REF.)
REMOVE THE 310883-1 INTERCOSTAL
i:W.L. -10.00) TO GAIN ACCESS FOR
INSPECTION PURPOSES
:Bx~--LEFT HANDCOCKPIT
310883-1 INTERCOSTAL
(REF)WINDSHIEtD(REF.)
+´•´•´•´•´•~f-W.L. -lo.ooz’
I\ UP
FS.
48.00WINDOW(REF.)
ZI´•~.\ X;
AFTCOCKPIT SIDE
a~s´•s(~P)INSPECT FOR CRACKS IN THE 310883- O
´•INTERCOSTAL(~W.L. -10.00) INNER/OUTER
FLANGE, RADIUS AND WEB FROMF.S. 40.00 TO 48.00. INSPECT PART AFTER
IT HAS BEEN REMOVED FROM THE AIRCRAFT
)C
(FpllNSPECT FOR CRACKS IN THE 310898-501
´•CANTEDWINDSHIELD FRAME INNERIOUTER
FLANGE, RADIUS AND WEB 5.00 INCHES ABOVEW.L. -10.00 TO 5.00 INCHES ABOVE W.L. -28.00.
INSPECT FROM THE AFT SIDE OF THE FRAMES, I L 310898-501 CANTEDTHROUGH THE WINDOW OPENINGS IN THE SKIN FRAME (REF.)
FS. 40.00
FIGURE #2VIEW LOOKING UP, FORWARD AND OUTBOARD
THE UPPER LEFT HAND CANTED WINDSHIELD
FRAME INTERSECTION AREA (F.S. 40.00)
RIGHT HAND SIDE OPPOSITE
Page No. 20 of 72
SERVICE BULLETIN NO. 214
PartINSPECTION
REFERENCE
TCAC DRAWING #300005-525 ASSY FOR MODIFICATIONS
TCAC DOCUMENT #MP3-5 FOR MODIFICATION PROCEDURES
310899-13 EYEBROW
FRAME (REF.)FP INSPECT FOR CRACKS IN THE 31089413
EYEBROW FRAME INNER i OUTER FLANGE,RADIUS AND WEB FROM THE OUTBOARD
END W.L. -10.00 EXTENDING 5.00 INCHES
‘f‘ INBOARD INTO THE FRAME. GAIN ACCESSAND INSPECT FROM THE FORWARD SIDE
X
X
NOTE:
REMOVE THE 310776-71 CLIP TOGAIN ACCESS FOR INSPECTIONPURPOSES
310776-71 CLIP
O (REF)INSPECT
5.00 INCHES _(7 PRIOR TO REMOVAL OF THE 31077871 CLIP
44V/-CLJ INSPECT ALL FASTENERS COMMON TO THE
310716-71 CLIP FOR LOOSE OR SHEAREDCONDITIONS
/C" FP INSPECT FOR CRACKS IN THE 310898-501CANTED WINDSHIELD FRAME INNER I OUTER
FLANGE, RADIUS AND WEB 5.0 INCHES ABOVEW.L. -10.00 TO 5.00 INCHES ABOVE W.L. -28.00.
INSPECT FROM FORWARD OR AFT SIDE OF
o310898-501 CANTED
~O’ FRAME(REF)
O
310883-1 INTERCOSTAL
(REF.)
FIGURE #2AVIEW LOOKING UP, AFT AND OUTBOARD
THE UPPER LEFT HAND CANTED WINDSHIELD bFRAME INTERSE%TION AREA (40.00)
RIGHT HAND SIDE OPPOSITE
Page No. 21 of 72
SERVICE BULLETIN NO. 214
Parl~lINSPECTION
REFERENCE
TCAC DRAWING #300005-517 ASSY FOR MODIFICATIONS
TCAC DOCUMENT #MP3-5 FOR MODIFICATION PROCEDURES
NOTE:REMOVAL OF THE AILERON DRUM
PULLN MAY BE REQUIRED TO GAIN IINSPECTALLRIVETS COMMONTOTHE
ADEQUATE ACCESS TO THE LOWER AIRCRAFTV 1530466-1 BRACKET ASSY BETWEEN
BRACKET STRUCTURE
7 CIL F.S. 23.50 AND F.S. 37.00 FOR LOOSE
OR SHEARED CONDITIONS
F.S. 23.50
IfFWD
´•B’~ 530169-9 AILERON
fI’’fII, DRUM (REF.)
I´•’II I-1~- 530465-1 CHANNEL
I1_I‘\(REF.)
P
litIIIt II I I
Ih
I´•-fB r‘--------c\(l
530466-1 BRACKETk’ASSY (REF.)
‘J --1
I\f-]l, ,Lt~:I I
u II I LOWER FUSELAGEI II SKIN (REF.)IfO I’ I
zI_ F.S. 37.00
F/GURE #3VIEW LOOKING UP FUSELAGE LOWER SKIN
AILERON DRUM BRACKET STRUCTURE
Page Noi 22 of 72
SERVICE BULLETIN NO. 214
Part IINSPECTION
REFERENCE
TCAC DRAWING #300005-503 ASSY FOR MODIFICATIONS
TCAC DOCUMENT #MP3-5 FOR MODIFICATION PROCEDURES
INSPECT RIVETS COMMON TO THE FRAMEI U IATTACHMENT SMEAR CLIP F.S. 23.50 8 W.L. -28.00
FOR LOOSE OR SHEARED CONDITIONS
O O
W.L. -28.00
j jI
Ije ji
UP
nnro
INSPECT FOR CRACKS IN THE INTERCOSTAL(F Pi W.L. -28.00 IN THE INBOARD RETURN FLANGE
AND WEB 1.00 INCH FORE I AFT OF F.S. 23.50F.S.
FRAME WEB23.50
FIGURE #4VIEW LOOKING OUTBOARD AFT THE LEFT HAND
W.L. -28.00 INTERCOSTAL@ F.S. 23.50 FRAME INTERSECTION
RIGHT HAND SIDE OPPOSITE
Page No. 23 of 72
q
SERVICE BULLETIN NO. 214
PartlINSPECTION
REFERENCE
TCAC DRAWING #300005-519 ASSY FOR MODIFICATIONS
TCAC DOCUMENT #MP3-5 FOR MODIFICATION PROCEDURES
III INSPECT ALL RIVETS AROUND THE PERIMETERI Y JOF THE PILOTS WINDOW SIDE SKIN FOR LOOSE OR
SHEARED CONDITIONS COMMON TO:
INTERCOSTAL W.L. -10.00, F.S. 40.00 THRU 60.50INTERCOSTAL W,L. -28.00, F.S. 37.00 THRU 60.50
F.S. 60.50 FRAME W.L. -10.00 THRU W.L. -28.00WINDOW CANTED FRAME W.L. -10.00 THRU W.L. -28.00
a
310832-11 SKIN F.S. 40.00 F.S. 60.50
(REF.)
a tO O O 9 O
~0+W.L. -10.00
310832-47 SKIN Z
(REF.)---,a 310832-13 SKIN
a(REF.)
"´•r 8/UP e~
O
Fwo
Ot
90 a
ai’
16
+81 lo
+Z te C+
a
W.L. -28.00
F.S. 37.00
310832-7 SKIN INSPECT FOR CRACKS IN THE OUTER SKIN AROUND 8
(REF) BETWEEN FASTENER HEADS 8 COUNTERSUNK SCREW
HEAD HOLES AROUND THE PERIMETER OF THE PILOTS
WINDOW COMMON TO:
INTERCOSTAL W.L. -la.oo, ES. 40.00 THRU 60.50
INTERCOSTAL W.L. -28.00, ES. 37.00 THRU 60.50
F.S. 60.50 FRAME W.L. -10.00 THRU W.L. -28.00
WINDOW CANTED FRAME W.L. -10.00 THRU W.L. -28.00
F/GURE #5VIEW LOOKING INBOARD THE LEFT HAND
PILOTS WINDOW AND SURROUNDING SKIN
RIGHT HAND GO-PILOTS SIDE OPPOSITE
Page No. 24 of 72
SERVICE BULLETIN NO. 214
Pa~rlINSPECTION
REFERENCE
TCAC DRAWING #300005-1 ASSY FOR MODIFICATIONS
TCAC DOCUMENT #MP3-5 FOR MODIFICATION PROCEDURES
FS.10.09 /-310772-71 SUPPORT310772-11 ANGLE
(REF.)7 IJ (REF.)310785-501 DOUBLER
(REF.)NOTE:
+++++\1+c!W.L. -55.50
REMOVAL OF THE NOSE
GEAR WHEEL WELL DOORS
WILL PROVIDE BETTER
\h ’------I ACCESS INTO fHE AREA
It~
310817-503 WEB
(REF.) INSPECT FOR CRACKS UNDER THEIFPI,,,,,,_,, SUPPORT ANGLE IN THE
f310817-503 WEB. INSPECT FROM
INSIDE WHEEL WELL AREA310772-5TEE P(REF.)
UP
FWD-4FIGURE #6
VIEW LOOKING INBOARD THE LOWER
LEFT HAND FORWARD KEEL BEAM AREA
RIGHT HAND SIDE OPPOSITE
REFERENCE
TCAC DRAWING #300005-501 ASSY FOR MODIFICATIONS
TCAC DOCUMENT #MP3-5 FOR MODIFICATION PROCEDURES
rFplREMOVE THE 320025-15 FLOOR WEB AND
´•INSPECT THE HORIZONTAL ROW OF FASTENERHOLES FOR CRACKS. IN ADDITION, INSPECT
310924-3 WEB THE 310924-3 WEB FOR CRACKS AROUND THE
(REF.) WISTING NUT-PLATES (6 PLACES)
t´•
f
W.L.-55.50UP
f C/L
320025-15 FLOOR WEB
(REF.)
FIGURE #7 BVIEW LOOKING FORWARD THE LOWER CENTERLINE FLOOR
WEB AREA, AFT SIDE OF NOSE GEAR WHEEL WELL BOX (F.S. 13.00)
Page Mo. 25 of 72
SERVICE BULLETIN NO. 214
PartlINSPECTION
FIGURE #8B F.S. B1.10 F.S. !4.45 FIGURE #8B
i \e i c i i i i i i i
c i I C I o Ii i i i i ii o k I i
I VU/
FIGURE#BDi FIGURE#BC 1
+b~iOJ30Q0010
!-E´•l I~_i I! 9:1+O/ \e
I/:I D--W.L. -15.05´•cXO
+I~ O \o I+f I u,l++I:´•
+I(+I I PI o io
Clcl I rl ol I, I+t I Ic’l++I I I fl I UP I~ Ifi’ I r 1+
3 e.FwDclO ;4 B+f
o a+I% .I i iJ+J FIGURE #8D
cl~´• "FI
ii ‘1 ~rl O o
II"1 D--W.L. -26.60d JJoaaJJo~
i
O Oa
+I:i O a I~a a
ses
81+O
CI~ i II I Ic5/ I 11 18
Cli~l mi I+ I II I 1,i O a CI FIGURE #8Da a
ii I
tl% i t.l iii
Oi a II+:I D-W.L. -37.57
t
c+Ce
i a6
+Ile +:I+i
O 3CE+
fl: I I I I a I I I ;I+i
sl U r ~LL IC
+t i I r a It I+I I 1 L I 1+3~
ii; I I ci
i +:IC
FIGURE #8A i
’I FIGURE #8DeE+
it
CIF% IL i iiiIll :L~r
W.L. -48.90+I’ I e
el I 12I \I i
II
tBs:BI ,9~1L
;~s´•, ;e)l 1+
3r i t
FIGURE #8VIEW LOOKING OUTBOARD EFFECTIVITY (Ref. FIG.
MOOEL SIN
THE MAIN CABIN ENTRY DOOR ssoo 15001 THRU 15034
695A 96014 THRV 96017
695A 96019THRU 96076330407 FAIL SAFE DOOR EXCEPT SIN 96063.
CONFIGURATION SHOWN 1 1960698 96075
Page No. 28 of 72
SERVICE BULLETIN NO. 214
Pa~i IINSPECTION
REFERENCE
TCAC DRAWING #300006-529 ASSY FOR MODIFICATIONS
TCAC DOCUMENT #MP3-6 FOR MODIFICATION PROCEDURES
CA UTION: 330410-1 ANGLE
USEOCTREMECAREWHEN REMOVINGTHEOUTERI_
DOOR FRAME WEB (REF)
DOOR SEAL, IF ANY RUBBER NIPPLES ARE DAMAGED (REF.OR TORN OFF DURING DISASSEMBLY,THE SEAL MUST BEREPLACEOi II o
lcj
orr I iIiO~ ii"I i I ~----;II (D II
OOOO BiO,!i
O i
rFp’INsPECT FOR CRACKS IN THE DOOR FRAME WEB I 330432-509STRAP
I ~AND OUTER FIANGERADIUSAROUND THE j j (REF.)BAYONET GUIDE BLOCK 4.00 INCHES ABOVE AND O 330421-505 PLATE3.00 INCHES BELOW W.L. -48.90 FROM THE AFT
SIDEONLYI (REF.)
INSPECT 4.00
O OINCHES ABOVE
01(O IIOj
WL. -48.90-- II)(O
O
INSPECT 3.00 co II~INCHES BELOW O
i ´•ilr ´•~B,I. Ilh(0’
BAYONET GUIDEBLOCK ~REF.)
OUTER DOORSKIN (REF.)
NGURE #8AVIEW LOOKING OUTBOARD FORWARD
THE W.L. -48.90 AFT DOOR BAYONET
(BAYONE~PIN OMlTTED FROM I/I~WFOR CLARITY)MODEC SIN I b690D 15001THRU15028
330407 FAIL SAFE:DOOR ONLY 695A 96014THRU 96017
AFT BAYONET PIN @W.L.-48.90 ONLY 1695A 96019THRU 96058
Page No. 27 of 72
SERVICE BULLETIN NO. 214
Part I
INSPECTION
REFERENCE
TCAC DRAWING #300006-1 ASSY FOR MODIFICATIONS
TCAC DOCUMENT #MP3-6 FOR MODIFICATION PROCEDURES
CAUTION: ’F P1’NSPECT FOR CRACKS ORIGINATING FROM THE
OR TORN OFF DURING DISASS~MBLY, DIAMETER FROM THE CENTER OF THE HOLE
USE WTREME CARE WHEN REMOVING THE OUTER ~J8AYONET PIN HOLE AND GUIDE BLOCK
DOOR SEAL, IF ANY RUBBER NIPPLES ARE DAMAGED ATTACHMENT FASTENERS 1.50 INCHES IN
THE SEAL MUST BE REPLACED IN THE OUTER DOOR FRAME WEB
’9 OO DOOR FRAME
,INSPECTRIVETS COMMONIOTHEVERTICAL \s WEB (REF)V d
I JWINDOW CHANNEL UPPER END, SMEAR CLIPS OAND BAYONET GUIDE BLOCK FOR LOOSE OR OSHEARED CONDITIONS----------~ o ~--A´•, o
o’0- .0‘1 O
8 O
//B0/
o:O
ieo
0\O
I’ oc~ ~P
VERTICAL WINDOW
OUTER DOOR CHANNEL (REF.)
SKIN (REF.)
FIGURE #88VIEW LOOKING OUTBOARD DOWN THE
UPPER AFT CORNER OF THE CABIN DOOR(BAYONET PIN OMI’ITED FROM VIEW FOR CLARIT~ I EFFECTIVITY
MOOEL SIN
6900 15029THRU 15034
330407 FAIL SAFE DOOR ONLY 695A 96059 THRU 9607_6AFT UPPER PIN F.S. 91.10 SHOWN 1 D(CEPT SIN 96063,
FORWARD UPPER PIN F.S. 74.45 TYPICAL I I 98069 8 96075
Page No. 28 of 72
q
SERVICE BULLETIN NO. 214
Parr IINSPECTION
REFERENCE
TCAC DRAWING #300006-1 ASSY FOR MODIFICATIONS
TCAC DOCUMENT #MP3-6 FOR MODIFICATION PROCEDURES
r P1INSPECT FOR CRACKS IN THE BEAM UPPER FLANGEIT ~F’1RADIUS 3.00 INCHES FORWARD FROM THE AFT
IITERMINATING END OF THE PART AND THE AFT
NOTE: VERTICAL RETURN FLANGE RADIUS OF THE BEAM
IT WILL BE NECESSARY TO REMOVE
THE BAYONET GUIDE BLOCK TO INSPECTTHE UPPER DOOR BEAM RAOIUS O
DOOR FRAME
61wee (REF)
O \Oa I´•~-\\
a
UPPER AFT BAYONETGUIDE BLOCK (REF.)
I i,,,,,,,,BEAM (REF)
OUTER DOOR
FS. 91.781
\NCHES
SKIN (REF.)
(NSPECT?OL)
VERTICAL WINDOW
CHANNEL (REF)
NGURL3 #8CVIEW LOOKING OUTBOARD UP THE
UPPER AFT CORNER OF THE CABIN 0OOR(BAYONET PIN a LINKAGE OMITTED FROM VIEW FOR CLARIP~
330407 FAIL SAFE DOOR ONLY r EFFECTIVIT(
AFT UPPER PIN F.S. 91.10 SHOWN s/N
FORWARD UPPER PIN F.S. 74.45 TYPICAL 6900 15029THRU 15034 ;B695A 96059THRU 96076
EXCEPT S/N 96063,
ICOOROINATE WITH INSPECTION FIGURE #8B) I I 96069 a 96075
Page No, 29 of 72
SERVICE BULLETIN NO. 214
Part I
INSPECTION
REFERENCE
TCAC DRAWING #300006-529 ASSY FOR MODIFICATIONS
TCAC DOCUMENT #MP3-6 FOR MODIFICATION PROCEDURES
IF PJ’NSPECT FOR CRACKS IN THE OUTER DOOR
DOOR FRAME /II’ 1 FRAME PLATE DOUBLER AROUND THE BAYONET
GUIDE BLOCK 1.00 INCH ABOVE I BELOW THEUPPER I LOWER ENDS OF THE PLATE DOUBLER
WEB (REF) CAUTION:
O use EXTREME CARE WHEN REMOVING THE OUTER
IDOOR SEAL, IF ANY RUBBER NIPPLES ARE DAMAGED
OR TORN OFF DURING DISASSEMBLY.i 2, THE SEAL MUST BE REPLACED
O \I rNsPECT 1.00j INCH
O ilis
INNER DOOR STRAP
O
O
i O W.L. -26.60
DOUBLER (REF.) ‘OO
~-IFPI ’NSPECT FOR CRACKS IN DOOR
;/8 ~U FRAME RADIUS ALONG THE
OUTBOARD EDGE OF PLATE
DOUBLER
O ’O
O OINSPECT 1.00
fj INCH BE~OW
’1YiOUTED O I--I 7--\1 I
O
‘s~OUTER DOOR FRAME --J
DO NOT REMOVE THE OUTER DOOR FRAME PLATEPLATE DOUBLER (REF.) DOUBLER OR BAYONET GUIDE BLOCK (UNLESS
SPECIFIED 8Y THE MODIFICATION DRAWINGS) FORINSPECTION PURPOSES, ONLY INSPECT ON 8 TO
THE EXISTING EDGE OF PART
FIGURE #80VIEW LOOKING OUTBOARD AFT THE
W.L. -26.60 FORWARD DOOR BAYONET DOUBLER
(BAYONET PIN OMITTED FROM VIEW FOR CLARIP~
330407 FAIL SAFE DOOR ONLY I EFFECTIV!~FORWARD BAYONET P1N W.L. -15.05 TYPICAL I MOOECI S/N
FORWARD BAYONET PIN W.L. -26.60 SHOWN 690D 15001 THRU 15028
FORWARD BAYONET PIN W.L. -37.57 TYPICAL 695A 96014 THRU 96017
FORWARDBAYONETPIN ~W.L. -48.90NPICAL i 695A ~196019 THRU 96058
Page No. 30 of 72
SERVICE BULLETIN NO. 214
Prrrt I
INSPECTION
REFERENCE
TCAC DRAWING #300006-1 a -529 ASSY FOR MODIFICATIONS
TCAC DOCUMENT #MP3-6 FOR MODIFICATION PROCEDURES
\INSPECT RIVETS COMMON TO THE OUTER INSPECT RIVETS COMMON TO THE OUTERI V 1 SKIN AND VERTICAL WINDOW CHANNELS U i SKIN AND DOOR FRAME AROUND THE
ON THE FORWARD I AFT SIDE OF THE DOOR I PERIMETER OF THE DOOR FOR LOOSE.OR
FOR LOOSE OR SHEARED CONDITIONS I SHEARED CONDITIONS
F.S. I F.S:
74(451
91110
ii%i ii:5i
´•I:~+:W.L. -15.05-
’I:Zcl
i/E:
:;xl16i
i:f: i´•c´•l
i3:. iiW.L. -26.60- g:
~’,.’..+..=.+.t.t.t.?.t.t.t=..+..+.t,t.t,t.:;:
IiW.L. -37.57- I;iI,:I~
f:i~c
i +i
f~:i :C
iiW.L.i18.90-- ij f~f.
tl: lil i E,:I ii,
FIGURE #8E TIVINMODEL SIN
VIEW LOOK1NGINBOARDI@ 6900 15001THRU 15034
THE CABIN DOOR OUTER SKIN 695A 96014 THRU 96017 d695A 96019THRU 96~EXCEPTSIN 96063.
330407 FAIL SAFE DOOR ONLY I I 96069 a 96075
Page No. 31 :of 72
\d
SERVICE BULLETIN NO. 214
Partl
INSPECTION
FIGURE #9B ES´• 91.10 F.S. !4.45 FIGURE #9B
s t i c c i
f i i o f t i C f +Ionl+
1
IYLY\
FIGURE #9D cEcl I r FIGURE #9C ---J 1 I, FIGURE #9D
ossoo;:ooC~e
ia o
´•LI ´•f I I II+ W.L. -15.OSii II fl L+I
c/ ii o 3 I
ii I 1 o io
ii I I ol I^ r I Ic:lf
+li I I I UP I~ II I :ICfl:
o
c18 a a++i
FIGURE#SD o 1
FIGURE#SD+IQ
a i
o 9I I I~e
cC I~ I I %VI II+
cll sl O oa (I iLD-- W.L. -26.60
ooooiDioo+1C
o oO
9% i
g O $L~+ +c~++l 00~1o:I+
i 8~ I II I8 a
i I r I 1~ 01++
’1’13 I i I I 1+1+i
i c:l+
FIGURE #9DFIGURE #9D i O O
i I I I I I~C
+CQ to aAL:l´•+E I~ h, LI r II ~I+
O W.L.-37.57b c
f i I ~Y, 1+
o~ co
FIGURE #9A Ic ia~ e aCC+I -ri I :I r I I+il+
+I Y I I+:I++I I lil I ´•li
i i
on II no’+I\ I II+ I I Ilt
+I\ I I\ ´•I II I
FIGURE #9D ~J\ f B II’ ol I ilfl FIGURE #9Df O
+:lfC L I ;I I i
fF-l\+:i PILI F’ i +;I+´•--c--, I
r iiii I I+II D-W.L. -48.90
II ii i
+;I iii \I+
ii Ii
’LII I I Ic~+i i
i
W/s.l+
c~. i t i s s c -s s L ~rL
FIGURE~ #9VIEW LOOKING OUTBOARD
THE MAIN CABIN ENTRY DOOR
EFFECTIVITYMOOEL SIN
330247 1 330430 DOOR 1695A 196001 THRU 96013
CONFIGURATION SHOWN 1695A 96018
Page No. 32 of 72
SERVICE BULLETIN NO. 214
Part I
INSPECTION
I IINSPECT FOR CRACKS ORIGINATING FROM THE
ZEE CHANNEL7 TFP1’’11.00 INCH DIAMETER PUSH ROD HOLE IN
THE ZEE CHANNEL WEB W.L. -48.13
INSPECT FROM THE UPPER SIDE ONLY
(REF.) INTERCOSTAL a
(REF.) 6.
""""’"’7/-"\/
e
a
YC~
i8
r’ AFT
~II O
oo g o o
O9\\0 0 ---W.L. -48.13
INNER DOOR STRAPo
INNER PLATEDOOR FRAME
\r INNER STRAP
DOUBLER (REF.)
(REF.)(REF.) NOTE:(REF.)
DO NOT REMOVE ANY RIVET MOUNTED
DOOR PARTS FOR INSPECTION PURPOSES
FIGURE #9AVIEW LOOKING OUTBOARD DOWN THE
LOWER AFT CORNER OF THE CABIN DOOR(PLISH ROD LINKA GE OMITTED FROM VIEW FOR CLARIP~ I EFFECTIVITY
MODEL SIN
695A 96001 THRU 96013
330247 1 330430 DOOR ONLY 1695A )96018
Page No. 33 of 72
SERVICE BULLETIN NO, 214
Part~INSPECTION
CAUTION: I IINSPECT FOR CRACKS ORIGINATING FROM THE
OR TORN OFF DURING DISASSEMBLY, $gfP DIAMETER FROM THE CENTER OF THE HOLE
USE EXTREME CARE WHEN REMOVING THE OUTER BAYONET PIN HOLE AND GUIDE BLOCK
DOOR SEAL, IF ANY RUBBER NIPPLES ARE DAMAGED ATTACHMENT FASTENERS 1.50 INCHES IN
THESEL\L MUST BE REPLACED IN THE OUTER DOOR FRAME WEB
O DOORFRAME
(7 INSPECT RIVETS COMMON TO THE VERTICAL \O WEB (REF.)V a
I IWINDOW CHANNEL UPPER END, SMEAR CLIPS OAND BAYONET GUIDE BLOCK FOR LOOSE OR OSHEARED CONDITIONS
o
,;s~8 o.O\I O
0// OO0,/
O
O i,oo\lo
1 042i U,P
VERTICAL WINDOW
OUTER DOOR \j CHANNEL (REF.)
SKIN (REF.)
FIGURE #9BVIEW LOOKING OUTBOARD DOWN THE
UPPER AFT CORNER OF THE CABIN DOOR(BAYONET PIN OMITTED FROM VIEW FOR CLARIPI)
FECTIVITY330247 1 330430 DOOR ONLY MOOEilSIN
AFT UPPER PIN F.S. 91.10 SHOWN 695A 96001 THRU 96013
FORWARD UPPER PIN F.S. 74.45 TYPICAL 1695A (96018
Page Na, 34 of 72
SERVICE BULLETIN NO. 214
Part IINSPECTION
CAUTION:
NOTE: EXERCISE EXTREME CARE WHEN REMOVING THESE
IT WILL BE NECESSARY TO REMOVE FASTENERS NOT TO ENLARGE OR ELONGATE EXISTING
THE BAYONET GUIDE BLOCK TO INSPECT HOLES IN THE DOOR FRAME OR BAYONET GUIDE BLOCK
THE UPPER DOOR BEAM RADIUS
FOR REINSTALLING THE GUIDE BLOCK TO THE
DOOR FRAME WEB, IT IS ACCEPTABLE TO I IINSPECT fOR CRACKS IN THE BEAM UPPER FLANGE
SAME SIZE AS REMOVED aFp VERTICAL RETURN FLANGE RADIUS OF THE BEAM
SUBSTITUTE HI-LOK FASTENERS FOR THE RADIUS 3.00 INCHES FORWARD FROM THE AFT
FACTORY INSTALLED STEEL LOCKBOLTS (4 PLACES) TERMINATING END OF THE PART AND THE AFT
HUOPB6 PIN d HL86-5 COLLARO DOOR FRAMEHOLE LIMITS (.1625~1.1600)
O ol \O WEB (REF.)
0\~c--- e~
Q
IUPPER AFT BAYONETGUIDE BLOCK(REF.)
3 BEAM (REF.)
OUTER DOOR
F.S. 91.78f
\NCHES
SKIN (REF.)
I
VERTICAL WINDOW
CHANNEL (REF.)
FIGU~E #9CVIEW LOOKING OUTBOARD UP THE
UPPER AFT CORNER OF THE CABIN DOOR(BAYONET PIN LINKAGE OMITTED FROM VIEW FOR CL9R17Y)
220247/ 330430 DOOR ONLYAFT UPPER PIN F.S. 91.10 SHOWN
FORWARD UPPER PIN F.S. 74.45 TYPICALMODEL SIN I
695A 96001THRU96013
(COORDINATE WITH INSPECTION FIGURE #98) 695A 96018
Page No. 35 of 72
SERVICE BULLETIN NO. 214
Part I
INSPECTION
(~p) INSPECT FOR CRACKS IN THE OUTER ~DOOR
DOORFRAME
I’ 1 FRAME PLATE DOUBLER AROUND THE BAYONETGUIDE BLOCK 1.00 INCH ABOVE I BELOW THE
UPPER I LOWER ENDS OF THE PLATE DOUBLER
WEB (REF.) ~-CAUTION:USE EXTREME CARE WHEN REMOVING THE
O OUTER DOOR SEAL, IF ANY RUBBER NIPPLESI6 ARE DAMAGED OR TORN OFF DURING
I~ DISASSEMBLY,.Jr THE SEAL MUST BE REPLACEDAl
O ~I
INSpECT1~00I INCH A,BOVE
OO
i o
OilO -w.L.-26.aa
INNER DOOR STRAP
DOUBLER (REF)II O
OFP
INSPECT FOR CRACKS IN DOOR
FRAME RADIUS ALONG THEOUTBOARD EDGE OF PLATE
~dl DOUBLER
O lo
I’-O
o
\NCH BEL´•OW;i" (NSPECT 1.00
.~so Oat
OUTER DOOR FRAME DO NOT REMOVE THE OUTER DOOR FRAME PLATEPLATE DOUBLER (REF.) DOUBLER OR BAYONET GUIDE BLOCK FOR
INSPECTION PURPOSES, ONLY INSPECT ON 8 TOTHE EXISTING EDGE OF PART
FIGURE #9DVIEW LOOKING OUTBOARD AFT THE
W.L. -26.60 FORWARD DOOR BAYONET DOUBLER
(BAYONET PIN OMITTED FROM VIEW FOR CLARIP~
3330247 1 330430 DOOR ONLYFORWARD 8 AFT BAYONET PIN ~2 W:L. -15.05 TYPICAL I EFFECTIVITYFORWARD 8 AFT BAYONETPIN W.L. -26.60 SHOWN MODEL I SIN
FORWARD 8 AFT BAYONET PIN W.L. -37.57 TYPICAL 1695A 96001 THRU 96013
FORWARD 8 AFT BAYONET PIN W.L. -48.90 TYPICAL 1695A 96018
Page No. 36 of 72
,7
SERVICE BULLETIN NO. 214
PartlINSPECTION
r 1 INSPECT RIVETS COMMON TO THE OVTER I 1 INSPECT RIVETS COMMON TO THE OUTERV ~U1 SKIN AND DOOR FRAME AROUND THEI V JSKIN AND VERTICAL WINDOW CHANNELSON THE FORWARD I AFT SIDE OF THE DOOR I\ PERIMETER OF THE DOOR FOR LOOSE ORFOR LOOSE OR SHEARED CONDITIONS I SHEARED CONDITIONS
F.S. I F.S.
74145_
1 \91110i’
i:i~ r:S
r+
:i+i++c+.!t
Bi :a
:5:f I Tc:
,II:
W.L. -26.60i´•l
t
i
r:"’""’-Tci~i i*ii:i j=ji=i i:
:ia
ii i’
II
W.L. -48.90--
3-(iiil------------------------------------------------------------’i+i’
ir’iii
F/GURE #9EVIEW LOOKING INBOARD
THE CABIN DOOR OUTER SKIN I EFFECTIVINMOOELISIN
695A 96001THRU96013
330247 1 330430 DOOR ONLY 695A 96018
Page No. 37 of 72
SERVICE BULLETIN NO. 214
Part~INSPECTION
REFERENCE
TCAC DRAWING #300006-501 8 -503 ASSY FOR MODIFICATIONS
TCAC DOCUMENT #MP3-6 FOR MODIFICATION PROCEDURES
F.S. 96.50FS. 99.00 310841-501 FRAME
ASSY (REF.)
310774-503 FRAME II+I IflllfASSY (REF.) --7 Ilr~tf;t;rh ---W.L.-14.00
’F P’ PARZ B fl Ifili+´•INSPECT FOR CRACKS ON THE OUTER I+iliFLANGE 8 WEB OF THE 330382-17 GUSSET +ili+FOR CRACKS EXTENDING ACROSS THE ft +Il:-tFS. 96.50 8 99.00 FRAMES X+j +’rNOTE: .II r?-P7PARTATHIS INSPECTION IS ONLY REQUIRED IF I +ili iii ~eINsPECT FOR CRACKS ON THE OUTER
CRACKS ARE FOUND IN THE 96.50 OR jj+j FLANGE 8 WEB OF THE FS. 96.50 8 99.00
99.00 FRAMES PER PARTA lilt: iii FRAMES 8 FRAME ANGLE DOUBLER FROMI+ -t W.L. -14.00 TO W.L. -45.00
111 330382-21 INNER GUSSETfr
330382-17 OUTER GUSSET +i I+ill (REF.)LOWER AFT (REF.) 310780-2 INTERCOSTAL
+I ,~I+1 (REF.)330382-71 LOWERCHANNEL (REF.) W.L. -28.00
f__f~e
~++´•--+-li+j j+:I:+I-tl
I I iti~iiil i1t: I~li+ili NOTE:
REMOVE W.L. -10.00 8 -28.00 INTERCOSTALS
OUTER AIRCRAFT Ifll AFT OF F.S. 99.00 FRAME, 99.00 FRAME SECTION
SKIN(REF.) ~I I AND ANGLE DOUBLER. DETACH AT THE
EXISTING FRAME SPLICE LOCATIONS TO
GAIN ACCESS FOR INSPECTION PURPOSES
fll!i I
t:ll
W.L. -45.00UP
FWD-1- I
FIGURE #~OVIEW LOOKING OUTBOARD THE R/H
F.S. 95.50 99.00 FUSELAGE FRAMES
RIGHT HAND SIDE ONLY
Page No. 38 of 72
Iq
SERVICE BULLETIN NO, 214
Part I
INSPECTION
REFERENCE
TCAC DRAWING #300006-507 8 -509 ASSY FOR MODIFICATIONSTCAC DOCUMENT #MP3-6 FOR MODIFICATION PROCEDURES
W.L. -48.9
NOTE:IT WILL BE NECESSARY TO DRILL BACK
THE 310928-45 INNER FRAME STRAP ItTO GAIN ACCESS TO THE INNER FLANGE -tOF THE FRAME
I’ I
I 1INSPECT FOR CRACKS IN THE LOWER FRAME j:FPII1’’12.00 INCHES ABOVE I OUTED AND 2.00 INCHES
BELOW I INBD ON THE INNER FRAME FLANGE, I i!RADIUS AND WEB ;--ii
-3´•~1
iW.L. -54.45
MAY VARY IN DESIGN PER \,I
’9" W.L. -55.50
I ~I )INSPECT FOR CRACKS ORIGINATING AT
FOR LOOSE OR SHEARED CONDITIONS ill\ I~ W.L. -57.75
I V IFASTENER HOLES IN THE FRAME WEB
COMMON TO SUPPORTS, BRACKETS
AND LINE BLOCKS
I310773-503 FRAME
’REF.’
i+
f Up
INBDi7 R.B.L. 22.57
R.B.L. 19.38
1 INSPECT FOR CRACKS IN FRAME WEBFP1 11.00 INCH DIAMETERAROUND UPPER
END OF STRINGER CUTOUT
FIGUREVIEW LOOKING ATT THE LOWER LEFT HAND
F.S. 96.50 FUSELAGE FRAME SECTION
TYPICAL ON THE UH F.S. 96.50 99.00 FRAMES ONLY
Page No. 39 of 72
2/0
SERVICE BULLETIN NO. 214
Part IINSPECTION
REFERENCE
TCAC DRAWING 4300006-519, -521, -523 8 -525 ASSY FOR MODIFICATIONS
TCAC DOCUMENT #MP3-6 FOR MODIFICATION PROCEDURES
W.L. -45.001PARTB’FPI IINSPECT FOR CRACKS IN THE FRAME W.L. -49.00
t´•;WHERE THE INNER FRAME DOUBLERS-~ND 1.00 INCHABOVE AND ~.00 INCH BELOW IN THE INNER FRAME
FLANGE, RADIUS AND WEB
PA~PrB r ’ooNOTE: (PART B, ONLY)IT WILL BE NECESSARY TO DRILL BACK THE 31092853
-WL4900f
THE INNER FLANGE OF THE FRAME
(FPI INSPECT FOR CRACKS IN THE LOWER FRAME fI-jleal PART A
BELOW THE FLOORLINE 2.00 INCHES ABOVEI.,,,,\I
AROUND THE OUTBOARD LIGHTENING HOLE
AND z.ao INCHES BELOW I INBO ALONG THE INNER~ r FLOOR BRACKETFRAME FLANGE, RADIUS AND WEB
t(REF.)
----W.L. -55.50
lul INSPECT FOR CRACKS ORIGINATING AT-tr~7 INSPECT PER PARTA 8 B EFFECTIVITY
FOR LOOSE OR SHEARED CONDITIONS,d~FASTENER HOLES IN THE FRAME WEB
COMMON TO SUPPORTS, BRACKETS, oOLINE BLOCKS kND DOUBLERS i_
I I
OUTED LIGHTENINGii
HOLE (REF.)I
I\j/
i\II I\L
II I
c ii’l i -t UPf s
~____’I~Lf i
NOTE:DEPENDING ON THE MODEL BEING INSPECTED,THE INNER FRAME DOUBLERS MAY VARY ASSHOWN. IT MAY BE NECESSARY TO DRILL OFF
Ir al INSPECT PER PART A 8 B EFFECTIVIN
L.B.L. 22.57AND REMOVE THE DOUBLERS ON THE FORWARDSIDE OF THE FRAME TO GAIN ACCESS FOR
INSPECTION PURPOSES
FPIINSPECTFORCRACKS IN FRAMEWEB1.00 INCH DIAMETER AROUND UPPEREND OF STRINGER CUTOUT
A-INSPECTIONUODEL SIN
690D 15001THRU 15032
6954 96001THRU 96067
EXCEPT S/N 96063
PART B INSPECTION
FIGURE #12 MOOEL ISIN
690D 15033THRU 15040VIEW LOOKING AFT THE LOWER LEFT HAND 8954 96068THRU 96100
FUSELAGE STATION 69.00 FRAME SECTION 16958 196204 THRU 96208
EXCEPT SIN 96069,
96075, 96078, 96085
RIGHT HAND SIDE OPPOSITE 1 18 96208
Page No, 40 of 72
-21
SERVICE BULLETIN NO. 214
Part I
INSPECTION
REFERENCE
TCAC DRAWING #300006-511 ASSY FOR MODIFICATIONS
TCAC DOCUMENT #MP3-6 FOR MODIFICATION PROCEDURES
rFpl’NSPECT FOR CRACKS ALONG THEIWELD PANASSEMBLY INNER RADIUSAROUND THE PERIMETER OF THE
DOOR FRAME
330109-109 FRAME 330109-109 FRAME
(REF.) Ih, (REF.)
-I IINSPECT FOR CRACKS ALONGFPI ITHEWELDPANASSEMBLY
INNER RADIUS AROUND THE
PERIMETER OF THE DOORFRAME CHANNEL
(REF.)NOTE: /IREMOVE THE FORE I AFT INNER
33010913 PANS TO GAIN ACCESS (j~lNSPECT FOR CRACKS ALONGFOR INSPECTION PURPOSES L’ 1THE VERTICAL WINDOW STIFFENING
CHANNELS ALONG THE OUTBOARD
RADIUS OF THE PART
33010913 PAN
SECTION A-A (REF.) SECTIONB~B
i7 INSPECT FOR CRACKS ON THE WELD ASSEMBLY PAN,FPI JRADIUS BETWEEN INNER FVANGEAND WEB.
WINDOW VERTICAL STIFFENING CHANNELS,RADIUS BETWEEN OUTBOARD FLANGE AND WEB
INSPECT BOTH FORE IAFT SIDES OF THE EMERGENCY FS. 96.50F.S. 69.00U(IT HATCH AS INDICATED
W.L. -10.00 I--
I I I I a
I I
O IIiC;iOjl
Al II\A
i j
UP OI
OR~VD1 Q j/l /I i 0,jj jj i
W.L. -28.00
FIGURE#~3 jVIEW LOOKING OUTBOARD THE
EMERGENCY EXIT ESCAPE HATCH
Page No. 41 of 72
Y
SERVICE BULLETIN NO, 214
PartlINSPECTION
RE~ERENCETCAC DRAWING #300006-513, -515 -517 ASSY FOR MODIFICATIONS
TCAC DOCUMENT #MP3-6 FOR MODIFICATION PROCEDURES
117.00fll:f
INSPECTINSPECT
FS.
310928~5 GUSSET
(REF.) i+
310928-3 GUSSET ~iil+ LOOKING DOWN~REF.) +si\+
iI+i+:II Irsl PART BOUTER AIRCRAFT
j+I’ ’JFP INSPECT FOR CRACKS ON THE OUTERSIDE SKIN (REF.)
FLANGE 8 WEB OF THE FRAME AND FRAME
ICE SHIELD (REF.)k
OUTER AIRCRAFT I i ]li ANGLE DOUBLER 7.00 INCHES ABOVE AND
5.00 INCHES BELOW W.L. -28.00
r U ’PAR’ BI 1 I NOTE
COMMON TO THE OUTER ICE%/iJ7.a0REMOVE THE CABIN WINDOWSI V 1 INSPECT THE FIRST RIVET ABOVE
W.L. -28.00 F.S. 117.00 8 126.00 j Ii TO PREVENT ACCIDENTAL DAMAGE
.----~---´•111’- IDURING INSPECTION I MODIFICATION
SHIELD ON THE RIGHT HAND SIDE PROCEDURES
ONLY FOR LOOSE OR SHEAREDCONDITIONS
W.L. -28.00++f+ft- fi
NOrr~ (PnRTB. ONLY) II I
PVRPOSES I+fi]i II)
REMOVE THE LOWER WINDOW I +’IIINTERCOSTAL W.L. -28.00 ANO ATTACHING
5.00
SMEAR CLIPS FORE I AFT OF THE FRAME i"’ I_jTO GAIN ACCESS FOR INSPECTION
ifj ii
NOTE: (PARTB, ONLY3 ’iIiREMOVE THE VIBRATION DAMPER ASSY +ililAND ATTACHING STRUCTURE AS REQUIRED
REMOVE THE 310928-3 8 3109285GUSSETSff+ I;jltf I
TO GAIN ACCESS FOR INSPECTION PURPOSES
NOTE: (PARTS, ONLY)
TO GAIN ACCESS FOR INSPECTION PURPOSES. i jlij:DO NOT REMOVE FASTENERS UNTIL THEY HAVE j +ilj/S.BEEN VISUALLY INSPECTED FOR LOOSE OR
SHEARED CONDITIONS IIf
COMMON TO IHE FUSELAGE--/\~I I~il/ ´•eFWDIll1PARTAI V )INSPECT RIVETS
INNER FRAME FLANGE AND THE 310928-3 -5
INNER FRAME GUSSETS FOR LOOSE OR
SHEARED CONDITIONS
FIGURE #~4VIEW LOOKING OUTBOARD THE UH
PART INSPECTIONF.S. 117.00 FRAME, FRAME ANGLE INNER MODEL I S/N
FRAME GUSSET DOUBLER’S 690D 15001 THRU 15028
NPICAL F.S. 126.00, 144.00 155.54 1695A 196001 THRU 96058
FUSELAGE FRAMES I PAR~gS-MODEL SIN
6900 15001THRU 15024
RIGHT HAND SIDE OPPOSITE 1695A (96001 THRU 96055
Page No. 42 of 72
23
SERVICE BULLETIN NO. 214
PerilINSPECTION
FIGURE ~5 GENERAL SKIN INSPECTION CRITERIA
P/PICAL SIGNS OF WORKING FASTENERS INCLUDE:
CHIPPED OR CRACKED PAINT AROUND FASTENER HEADS
BLACK OXIDE OR (SMOKING) USUALLY TRAILING THE FASTENER HEAD 1F EXPOSED TO THE
AIRSTREAM
WHITE CRYSTALLINE DEPOSITS MAY FORM AROUND WORKING FASTENERS FROM WATER BEING
TRAPPED
iO I~jn-7
i ~L´•I
LL~CRACKED RIVETHEAD AROUND SHEARED OR MISSING BLACK OXIDE OR SMOKING TIPPED RIVET HEAD
CIRCUMFERENCE OF SHANK RIVETHEAD OR BU77 AROUND RIVET HEAD
NOTE:
ANY SIGNS OF WORKING FASTENERS SHOULD BE IDENTIFIED AND NOTED PRIOR TO
STRIPPING AIRCRAFT PAINT FINISH TO DETERMINE AREAS OF POSSIBLE INTERNAL DAMAGE
TYPICAL SKIN LAP CROSS SECTION
INSPECT FOR CRACKS IN THE OUTER~SKIN LAP AREA AROUND OR BETWEEN n INSPECT SKIN RIVET LINES COMMON TO
FASTENER HOLES FOR CRACKS
7 ?rI V i INTERNAL STRUCTURE FOR CRACKED,TIPPED, SMOKING, WORKING OR SHEARED
CONDITIONS
FRAME, ANGLE OR
STRINGER (REF.)
SHEARED OR MISSING --r II CRACKED SKIN BETWEEN
RIVET HEAD OR BUTT II RIVET HEADS
Page No. 43 of 72
SERVICE BULLETIN NO. 214
PartlINSPECTION
FIGURE 15 GENERAL SKIN INSPECTION CRITERIA (cont.)
NOTE:
BEFORE PROCEEDING WITH THE LNSPECTION ITEMS IDENTIFIED PER FIGURE 15, THE
EXTERIOR SKIN IN THE PRESSURE VESSEL AREA SHOULD BE CHEMICALLY STRIPPED OF
PAINT, NO MECHANICAL MEANS MAY BE USED.
INSPECT THE FOLLOWING AREAS PER FIGURE 15: (see next pagel
1. FUSELAGE SKIN LAP W.L. -10.00 -14.00, F.S. 40.00 THRU 178.715
2. FUSELAGE SKIN LAP W.L. -28.00, F.S. 5.50 THRU 209.24
3. FUSELAGE SKIN LAP W.L. -40.00, F.S. 5.50 THRU 37.00
4. FUSELAGE SKIN LAP W.L. -55.50, F.S. 5.50 THRU 178.715
5. FUSELAGE SKIN F.S. 172.50 178.715 FRAMES FROM, W.L. -15.00 TO -28.00
6. FUSELAGE LOWER BELLY SKINS F.S. 78.00 THROUGH 163.00, ALONG FR4ME RIVET LINES
FROM THE LEFT TO RIGHT HAND KEEL BEAM CAP ANGLE INTERSECTION
7. FUSELAGE UPPER SKIN F.S. 155.54 ALONG FRAME RIVET LINE FROM AIRCRAFT CENTERLINE
U(TENDING OUTBOARD TO THE LEFT AND RIGHT HAND WING FAIRINGS
NOTE:IF ANY DAMAGED FASTENERS ARE FOUND DURING COMPLIANCE WITH FIGURE 15 ITEMS
O.NE THRU SEVEN, REPLACE WITH THE SAME TYPE AND SIZE FASTENER AS REMOVED. IT IS
ACCEPTABLE TO INCREASE THE FASTENER BY ONE SIZE IF ALLOWABLE PITCH AND EDGE
DISTANCE CRITERIA CAN BE MAINTAINED.
Page No. 44 of 72
SERVICE BULLETIN NO. 214
Part IINSPECTION
FIGURE~5,1TEM2Left Hand Side
Cb
FIGURE 15 ITEM 4 ,oLeft Right Hand Sides 4´•28’
FIGURE 15 ITEM 6
GB’
FIGURE 15 ITEM 7
FIGURE 15 ITEM 1Left g Right Hand Sides
FIGURE 15 ITEM 5r
FIGURE 15 ITEM2iLeft Right Hand Sides
Right Hand Side
URE 15 ITEM 3Left g Right Hand Sides
FIGURE #153 DIMENSIONAL EXTERIOR
SKIN LOCATION DIAGRAM
Page No. 45 of 72
SERVICE BULLETIN NO. 214
Part I
INSPECTION
REFERENCE
TCAC DRAWING #300006-515 8 -517 ASSY FOR MODIFICATIONS
TCAC DOCUMENT #MP3-6 FOR MODIFICATION PROCEDURES
NOTE:
IFP1 INSPECT FOR CRACKS ALONG THE W.L. -28.00 FULL OR PARTIAL REMOVAL OF THEJ INTERCOSTAL ON THE INBOARD I OUTBOARD W.L. -28.00 INTERCOSTAL WILL BE
RETURN FLANGES AND WEB REQUIRED TO GAIN ACCESS FOR
INSPECTION PROCEDURES
F.S.FS.
i ii+’WL. -28.00
f L~ i´•U~ ii
-t i 9 ?~aOUP
(i I I+ili AFF
i ,I 1 INSPECT RIVETS COMMON TO THE INTERCOSTALI V J FORWARD I AFT SMEAR CLIP ATTACHMENT AREAS
FRAME INTERSECTIONS FOR LOOSE OR SHEARED
CONDITIONS
FIGURE #15AVIEW LOOKING INBOARD FORWARD THE LEFT HAND
W.L. -28.00 INTERCOSTAL FUSELAGE FRAME INTERSECTIONS
SKIN OMITTED FROM VIEW FOR CtARIN
INSPECT THE FOLLOWING AREAS
LEFT RIGHT HAND SIDES TYPICAL
W.L. -28.00, F.S. 37.00 THRU 60.50
W.L. -28.00, F.S. 99.00 THRU 209.24
Page No. 46 of 72
2-3(
SERWCE BULLEfN NO. 214
Parl I
INSPECTION
REFERENCE
TCAC DRAWING #300007-1, -517 8 -525 ASSY FOR MODIFICATIONS
TCAC DOCUMENT #MP3-7 FOR MODIFICATION PROCEDURES
rylPARTAINSPECT RIVETS COMMON TO THE310926 CLIP OW.L. -13.00 FOR LOOSE
OR SHEARED CONDITIONS4 -t
4W.L. -13.00
~CiL 370828
INTERCOSTAL
(REF.)
178.715 lj2.50
310926 CLIP
F.S. (REF.)
OUTER AIRCRAFTSIDE SKIN (REF.)
’I\r 310850-501 f (REF.)310811-1 FRAME
leplPARTB FRAMEil+i(FPJ INSP~CT FOR CRACKS ON THE INNER I OUTER (REF.)
FLANGE 8 WEB F.S. 172.50 FRAME 7.00 INCHES I
NOTE: (PARTB, ONLY)(REF.)
ABOVE 8 5.00 INCHES BELOW W.L. -28.00 i 310871-1f(/lNTERCOSTAL f /UP
STRAPS TO GAIN ACCESS FOR INSPECTIONf
I ;LPFWDREMOVE THE 310928-39 1 -41 INNER FRAME 7.00
PROCEDURESF.S. +I
188.00
WL. -28.00+"t 1+ 1
II!CLI Ii
5.00L310928-39 DBLR~I n +I I+310928-41 DBLR
(REF.) X.lli~ +Ii IPARTB
INSPECT FOR CRACKS IN THE INNER FRAME IJj f f
INTERCOSTAL d W.L. -28.00. IN ADDITION,j f
INSPECT THE INNER FRAME STRAP
DOUBLERSPARTC +il I 1310928-39 8 310928-41 BETWEEN FS. 172.50 L
THRU 188.00
I V I INSPECT RIVETS COMMON TO THE LOWERWINDOW INTERCOSTAL W.L. -28.00, CLIP
ATACHMENT AREAS AND INNER FRAME
STRAP DOUBLERS FOR LOOSE OR SHEAREDCONDITIONS I PARTA- INSPECTION
MODEL S/N
690D 15001THRU15032695A 96001THRU96066
EXCEPT SIN 96063
PART B 4 C INSPECTIONSMODEL ISIN
690D 15001THRU15040695A 96001THRU981006958 96201THRU96208
EXCEPT S/N 96063,
NGURE #f 6 1 8 96208
VIEW LOOKING OUTBOARD THE UH,,,,~,NsPEcnolY
F.S. 172.50, 178.715 8~ ~88.00 MODEL IS/N
FUSEtAGE FRAMES 690D 15001 THRU 15034695A 96001 THRU 960ZF B
EXCEPT S/N 96063,
RIGMT MAND SIDE OPPOSITE 96069 8 96075
Page No. 47 of 72
7J"h
SERVICE BULLETIN NO. 214
PartlINSPECTION
REFERENCETCAC DRAWING #300007-503 8 -507 ASSY FOR MODIFICATIONS
TCAC DOCUMENT #MP3-7 FOR MODIFICATION PROCEDURES
310968-9 ANGLE
(REF.)
310868-51 WEB
(REF.)F.S. 209.24
I IPARTBIFPI INSPECT FOR CRACKSIN THE 310868-51 WEB
SECTION A-A
RADIUS
310868-39 ANGLE(REF.).I´•~"
310868-37 ANGLE
(REF.)
~ze"OL´•
i;:i
i Ic’ Lt
1 PARTA I´•rlU I (+II I INSPECT RIVETS COMMON TO THE INTERCOSTAL-----~
SMEAR CLIP AND AFT PRESSURE BULKHEAD
OUTER FRAME W.L. -28.00, FS. 209.24 FOR LOOSE 310868-35 ANGLEOR SHEARED CONDITIONS
lic*’ (REF.)310968-9ANGLE ~I
(REF.) I 310868-11 ANGLE
310868-51 WEB(REF.)
I lil(REF.) ´•I
,,I
aso t=UP
ct~8’;O
I:: o´•
‘PARTB(FPI INSPECT FOR CRACKS IN THE 310868-51 lit
BULKHEAD WEB ALONG THE VERTICAL ~cl Fk/ORADIUS WHERE SUPPORTED BY AFT SIDE
iANGLE B.L. 19.15, W.L. -13.00 TO -53.50rL:
’rg
FIGURE #77~S .,,E,PARs~NA-INSPECTION
VIEW LOOKING AFT OUTBOARD 690D 15001THRU15028
THE LEFT HAND AFT PRESSURE 695A 96001THRU96058
BULKHEAD (F.S. 209.24) PART B INSPECTIO~MODEL SIN
690D 15001THRU 15029
RIGHT HAND SIDE OPPOSITE 695A 96001THRU96061
Page No. 48 of 72
2-CI
SERVICE BULLETIN NO. 214
Part~INSPECTION
REFERENCE
TCAC DRAWING #300007-505 ASSY FOR MODIFICATIONS
TCAC DOCUMENT #MP3-7 FOR MODIFICATION PROCEDURES
310868-25 WEB
(REF.)
320027-1 ANGLE
(REF.)
W.L -53.50
320037-1 PANELAFT (REF.)
SECTION A-A
I II IINSPECT RIVETS COMMON TO THEI V ]LOWER 320027-1 ANGLE (BOTH FLANGES)
FOR LOOSE OR SHEARED CONDITIONS
10.00 INCHES INBDI OUTED OF CENTERLINE
UP
310868-25 WEB
(REF.)
320027-1 ANGLE
(REF.)
~-t,,4
W.L.-S3.50
iZINSPECT
10.00 INCHES
AFT (REF.)320037-1 PANELAIRCRAFT
C/LI INSPECT
10.00 INCHES
FIGURE #~8VIEW LOOKING DOWN FORWARD LOWER
AFT PRESSURE BULKHEAD (F.S. 218.40)
Page Na. 49 of 72
SERVICE BULLETIN NO. 214
ParilINSPECTION
REFERENCE
TCAC DRAWING #300007-501, 300008-1, -501 8 -505 ASSY FOR MODIFICATIONS
TCAC DOCUMENT #MP3-7 8 MP3-8 FOR MODIFICATION PROCEDURES
I II 1 INSPECT ALL VISIBLE FASTENERS COMMON TOI V ITHE STRINGER ENDS FOR LOOSE. WORKING OR
SHEARED CONDITIONS. TYPICAL FOR STRINGER
310859-1 FRAME NO. 1, 282A
(REF.) F.S.
155.54 4.170317-5 STRINGER
NO. 2 (REF.)
FS. 164.82 S
FS. 1~170317-3 STRINGER
171.00 O NO. 1 (REF.)
O /I
INSpECT 1.Pg INCNC
INfjpECT3.001NCHFR4ME 8 GUSSETPIP~CAL "-310809-3 FRAME
(REF.)
170317-7 STRINGER
NO. 2A (REF.)
310398-13 GUSSET j(REF.)
310392-7 GUSSET
(REF.)
170314-13 RIB
V_QSTRINGERS NO. 1, 2 8 2A FROM THEIR INBOARD
(REF.) INSPECT FOR CRACKS IN THE UPPER WING
TERMINATING END 4.50 INCHES OUTBOARD,UP FROM THE FORWARD A~TACHING SIDE310828-503 INTERCOSTAL
~--tNn(REF.)NOTE:
INSPECT FOR CRACKS IN ALL A~TACHING
STRUCTURES(FRAMES,GUSSETS,ETC.)INBD i OUTED FLANGES 8 WEBS FROM
1.00 INCH ABOVE 8 3.00 INCHES BELOW
THE ATTACHING STRINGERS
FIGURE #20VIEW LOOKING OUTBOARD AFT THE LEFT HAND
STRINGER I FRAME INTERSECTION (STRINGER #1, 2 2A)
RIGHT HAND SIDE OPPOSITE
Page No. 51 of 72
W.S.
91.46AIRCRAFT cn
W.S. 0.0W.S. W.S.
103.46 ~L, 79.46 W.S.24.07
FIGURE #22 FIGURE #24
113.00 I) /W.S. W.S.
Page #55
W.S. W.S. W.S. W.S. W.S.197.32 178.66 160.00 142.00 69.00 39.00
~-FIGURE #23O Page #56
Zu, v,
m-oz ~NGURE #21
n (nG)Ocn O O, o,
z mZ
Z v, 00n
o co O MAIN SPAR CAP rC z (REF.) O r
a o, ~L1 m=!m cor 01P Z ZO bO z
poP IS h)
\-FIGURE #26
O 0) RfAk SPAR CAP P;D ~O (REF.)
01
LEFT 4 R/H SIOE
jFIGURE#21A
Page #60
Page #54
SERVICE BULLETIN NO. 214
Part~INSPECTION
REFERENCE
TCAC DRAWING #300008-503 ASSY FOR MODIFICATIONSTCAC DOCUMENT #MP3-8 FOR MODIFICATION PROCEDURES
ALLOWABLE DAMAGE LIMITS
CRACKS ARE ALLOWED THAT EXTEND ALONG THE LOWER 2D MINIMUM FASTENER
RETURN FLANGE OF THE W.S. 39.00 RIB BEND RADIUS. EDGE DISTANCE
CRACKS ARE ALLOWED THAT EXTEND UPWARDS INTO THE MEASURED FROM CENTER
VERTICAL WEB OF THE W.S. 39.00 R1B WEB, IF 2D OR 170318-1 CAPI OF FASTENER HOLE TO
(2 x FASTENER DIAMETER) EDGE DISTANCE CRITERIA CAN ANGLE (REF.) CRACK TERMINATING END
IF CRACK INDICATIONS ARE WITHIN THE APPLICABLE CRACKS(REF.) f-
1BE MAINTAINED ALONG THE EXISTING LOWER FORE AFT
FASTENER ROW. T(PICALACCEPTABLE
DAMAGE LIMITS, REFER TO TCAC DWG. 300008-503 ASSY
FOR MODIFICATION PROCEDURE. 170315-3 RIB
NOTE: -4_ 1
IF CRACK INDICATIONS EXTEND BEYOND SPECIFIED LIMITS
DAMAGED PARTS MUST BE REPLACED OR AN APPROVED
REPAIR INSTALLED.
DAMA GE UMITS
VIEW LOOKING INBOARD
1 INSPECT FOR CRACKS ALONG THE LOWER HORIZONTALFPI i FLANGE AND RADIUS OF THE 170315-3 RIB ON.S. 39.00)
FROM THE LOWER MAIN SPAR CAP AFT TOi 703 1 5-7 ANGLE I STRINGER #7
(REF.)
MAIN SPAR WEB 4Y
u-\ /‘CI(REF.) 4
MAINSPARLOWERk X h ‘h
CAP (REF.)
Y--~-t- x
~170315-3 RIBx
4~ ~x (REF. jx ‘i-xx -h /-170318-1 CAP
x~ xANGLE (REF.)
xx xx
xX~ X
x x
x X
xx
x Lt
rx
x
x
x
X
(REF.)
S
"oox ~-170317-33 STRINGER #7
o~sOx
´•Q~z x
s´•p‘*"~PFIGURE #2~
VIEW LOOKING INBOARD FORWARDTHE LEFT HAND W.S. 39.00 RIB LOWER FLANGE
RIGHT HAND SIDE OPPOSITE
Page No. 53 of 72
SERVICE BULLETIN NO. 214
Parl I
INSPECTION
TCAC DRAWING #30000&503 ASSY FOR MODIFICATIONS
TCAC DOCUMENT #MP3-8 FOR MODIFICATION PROCEDURES
170317-11 STRINGER #3
(REF.)7 i 1 INSPECT FOR CRACKS IN THE 1703183 RIB-
r- ’NsPECT
FPi’’J Onl.s. 39.40 3 69.00) ~g STRINGER #3 CUTOUT
RIB WEB, UPPER RETURN FLANGE AND FLANGE
RADIUS2.00 INCHES INSpECT2.00 !NCHES7
INSpECT
-f‘ :i -C- -j-f-
I-L
1703341 CAP ANGLEFWD_e c170315-3 RIB(REF.)170321-501 STIFFENER (REF.)
(REF.)
FIGURE #2?AVIEW LOOKING INBOARD THE LEFT HAND
W.S. 39.00 UPPER RIB STRINGER #3 CUTOUT
W.S. 39.00 SHOWN, W.S. 69.00 T/PICAL
RIGHT HAND SIDE OPPOSITE
Page No. 54 of 72
7/
SERVICE BULLETIN NO, 214
Part~INSPECTION
REFEREEJCETCAC DRAWING #30000&501 ASSY FOR MODIFICATIONS
TCAC DOCUMENT #MP3-8 FOR MODIFICATION PROCEDURES
ALLOWABLE DAMAGE LIMITS
MAXIMUM CRACKS LENGTH OF 1.00 INCH IN THE UPPER WING SKIN
UPPER WING SKIN BUCKLE IN´•THE BAYSKIN BUCKLES BETWEEN RIVETS ALONG STRINGER #2
IF DAMAGE INDICATIONSARE WITHIN THE APPLICABLE
DAMAGE LIMITS, REFER TO TCAC DWG. 300008-507 ASSYFOR MODIFICATION PROCEDURE.
NOTE:IF DAMAGE INDICATIONS EXTEND BEYOND SPECIFIED LIMITS,DAMAGED PARTS MUST BE REPLACED OR AN APPROVEDREPAIR INSTALLED.
I 1 INSPECT FOR CRACKS IN THE UPPER WING SKINFP
170400-1 LEADING~’’IWHICH EXTENDS FROM THE INTERSECTION OF THE
LEADING EDGE SKIN (STRINGER #1) AND THE NACELLEEDGE SKIN (REF.) FAIRING (W.S. i 03.46) AFT AND OUTBOARD APPROX.
A 45 DEGREE ANGLE
NOTE:
DO NOT REMOVE THE UPPER
II NACELLE FAIRING FOR INSPECTION
\-t +;I -t -t~STRINGER 41 CI,It
+9 i (V
.i t ;I i’~J/
I’;I I
-t++ 1- 7´• J170197-501STRAP
f.’ :-t. (REF.)~:i+iit
i- -------_
~tL_ I’ i) :-STRINGER #2
W.S. 113.00
170346-503 SKIN I ’‘’------‘---IW.S. 103.46(REF.)
U IINSPECT UPPER WING SKIN FOR BUCKLES
FWD ~BETWEEN STRINGERS #1 8 #2 W.S. 103.46 8 113.00
.~.II rFp’INSPECT UPPER WING SKIN ALONG STRINGER #2\’’IFOR CRACK INDICATIONS BETWEEN FASTENER
HEADS FROM W.S. 103.46 TO 113.00
FIGURE #22VIEW LOOKING DOWN
THE LEFT HAND UPPER WING SKIN
RIGHT HAND SIDE OPPOSITE
Page No. 55 of 72
5
SERVICE BULLETIN NO. 214
Part I
INSPECTION
REFERENCE
TCAC DRAWING #300008-509 ASSY FOR MODIFICATIONS
TCAC DOCUMENT #MP3-8 FOR MODIFICATION PROCEDURES
UP IFPI INSPECT FOR CRACKS IN THE 1-70314-13 RIB
FUSELAGE STATION 165.00, STRINGER #2 CUTOUT
170317-5 STRINGER(W.S. 24.07) ALONG THE VERTICAL FASTENER ROW
#2 (REF.)
AND AROUND VERTICAL RIB BEADS BETWEEN
STRINGERS #1 AND #2 F.S. 165.00
170317-3 STRINGER #1
(REF.) F.S.155.54
ff170339-1 CAP ANGLE
(REF.)4
4
f
,’t \t~iII+I+
;li
(III I
fI II
170314-13 RIB II i
(REF.)(REF.)II
I/I) j17[)302-503 BRACKET ii
’li/f11 2
170317-19 ANGLEI I I I I I I I II(REF.)7
I
t_l_+ -7~ ~Inf I
f
+I c
[FPJ INSPECT FOR CRACKS IN THE 170314-13 RIB LOWER FUSELAGE :\I170317-23 STRINGER
170317-21 ANGLEINSPECT
IcalPARTA (REF.)
OnV.S. 24.07) ALONG THE LOWER FLANGE RADIUS SKIN (REF.) 45 (REF.)AND 110197-13 FAIRING ALONG THE FLANGE
RADIUS ONE INCH FORE AFT OF THE EXISTING 110197-13 FAIRING 170338-1 CAP ANGLEVERTICAL RIVET LINE FS. 155.54 (REF.) (REF)NOTE:
CRACKS DETECTED IN THE WING TO FUSELAGEFAIRING MAY INDICATE POSSIBLY INTERNAL
STRUCTURE FAILURE
FIGURE #23VIEW LOOKING INBOARD THE
LEFT HAND W.S. 24.07 RIB
RIGHT HAND SIDE OPPOSITE
NOTE: REFERENCE TCAC SE 223. FIGURES 4 d 5
PART A SPECIAL CONDITIONS PART B SPECIAL CONDITIONS
IF SE 223. PARTI HAS BEEN ACCOMPLISHED, IF SE 223, PART II HAS BEEN ACCOMPLISHED,
INSPECTION REQUIREMENTS PER FIGURE #23, PART A INSPECTION REQUIREMENTS PER FIGURE 423, PART B
ARE NOT REQUIREDI ARE NOT REQUIRED!
Page No, 56 of 72
t\
SERVICE BULLETIN N0.214
Part I
INSPECTION
REMOVE THE 170405-1 VERTICAL TEEBRACKET AND INSPECT FOR CRACKSON ALL FLANGES AND ALONG PART
RADIUS
BRACKET~MAY BE RE-INSTALLED PERENGINE CONTROL
THE PROCEDURES SPECIFIED BYCABLES (REF.) TCAC SE 223, PART II, ITEM 4, a
OO ~o
Q
8 8 8 8 i´•i I,"i 1 INSPECT FOR CRACKS IN THEFP1 1310777-501 FRAME(F.S. 144.00)
WEB 5 INNER RETURN FLANGE1.00 INCH ABOVE I BELOW THE
O g g O THE 170405-1 BRACKET BASEINSPECT FROM THE FORWARDAND INBOARD SIDE OF FRAME
e oo iij
170302-503 BRACKET i/I U
(REF.) l.OO\FICH170405-1BRACKET II(REF.)
NOTE: ouTBD
310777-501 FRAMEF.S. 161.00 (REF.)
REMOVE SEALANT TO GAIN
ACCESS FOR INSPECTIONPROCEDURES
FIGURE #23AVIEW LOOKING OUTBOARD FORWARD
THE LEFT HAND F.S.´• 144.00 W.S. 24.07 R1B
BRACKET ATTACHhiENT AREA
RIGHT HAND SIDE OPPOSITE
NOTE: REFERENCE TCAC SE 223, FIGURE 7
INSPECTION SPECIAL CONDITIONS
IF AREA WAS PREVIOUSLY INSPECTED PER SE 223. PARTII
INSPECTION REQUIREMENTS PER FIGURE #234
ARE NOT REQUrREDI
Page No. 57 of 72
MAXIMUM ALLOWABLE CRACK LENGTH ---t~.90 1.15 -----~t---MAXIMUM ALLOWABLE CRACK LENGTH
STEEL AND I OR ALUMINUM BULKHEADS TYPICAL I‘ I TYPICAL STEEL AND I OR ALUMINUM BULKHEADS
.90 INCH TYPICAL INBOARD AND I OR I I I 1 1.75 INCH TYPICAL INBOARD AND I OR
OUTBOARD FROM THE UPPER TWO (112) 1 I I I OUTBOARD FROM THE UPPER TWO (#1)ENGINE MOUNT ATTACHMENT HOLES ENGINE MOUNT ATTACHMENT HOLES
W.S. 91.46AND ALONG THE UPPER BEND RADIUS
STOP DRILL ENDS OF CRACKS I I I I I OF THE BULKHEAD
PER TCAC DOCUMENT MP3-8
AS REQUIRED O T~ INSPECT FOR CRACKS IN THE FORWARD-rIFPI STEEL AND AFT ALUMINUM FIREWALL
BULKHEAD ASSEMBLY ORIGINATING FROM
O EXISTING FASTENER HOLES AND ALONG THE
UPPER BEND RADIUS OF THE BULKHEAD
r- II -I
I II1--i-- c--I I o
11 6
’I1
I’ og
I I I O
coII 11~1
cn71 71-4< m
;dLI II ~Z 9a
I I ,I I I lo I~C) m C)I
~D --I I II I ~Ormr II ACCEPTABLE Ps O
TYPICAL CRACKS ’r’o Zm
P1 I r -n O ~n IIcn II II(P m -10 I, II o~o
o,z t I o o c
Z t I 7F Y’ _II II -nP~ V, 01Z t3 rgo 11W
O~ rO I IIIm r
z,1~ III I
ImUP OJ, *r --I
73 IIII
II
OUTED
m
9 o0710 11 I V911- P
-I II ---r--- _~m z
cn II II I ao zn v, ____l_____j II r(a Oh) O L0[3 ;D I I 48
II OIcn mmo II II z0 Y-I ~O II II I´• o Pm71
C NOI~It PPI_ -II II THE AFT ENGINE MOUNT
OoII II
_
BRACKETS MUST BE o~II II -I m-IREMOVED TO GAIN ACCESSI I _I, o--_
IIaO
zli~J II SIDE OF THE FIREWALL "o,
m’I 1!1 I I BULKHEAD ASSEMBLY v,
FOR INSPECTIONPROCEDURES
IF CRACK INDICATIONS ARE WITHIN THEFIREWALL
MAXIMUM ALLOWABLE CRACK LENGTH
ALLOWABLE DAMAGE LIMITS
3.00 INCHESOUTBOARD3’-
3.00 INCHESINBOARDIMAXIMUM ALLOWABLE CRACK LENGTHS STEEL AND I OR ALUMINUM BULKHEADS
AS SPECIFIED. REFER TO TCAC .50 INCH TYPICAL INBOARD AND I ORINSPECT BULKHEAD INSPECT BULKHEAD
DWG. 300008-513 ASSY FOR OUTBOARD FROM TI-(E LOWER TWO (115)MODIFICATION PROCEDURE. ENGINE MOUNT ATTACI-1MENT IIOLES
NOTE:
IF CRACK INDICATIONS EXTEND BEYONDSPECIFIED LIMITS, DAMAGED PARTS MUST
BE REPLACED OR AN APPROVED REPAIR
INSTALLED.
SERVICE BULLETIN NO. 214
Part I
INSPECTION
W.L. -45.00FLOOR BRACKET CONFIGURATIONAND FASTENER PATTERN MAY VARY I fIN DESIGN PER FRAME (REF.)
L.B.L. 22.57
f-tf
‘INSPECT FOR CRACKS IN THE LOWER FRAMELFPIAROUND THE OUTBOARD LIGHTENING HOLE
BELOW THE FLOORLINE 2.00 INCHES ABOVE i OUTED +iAND 2.00 INCHES BELOW I INBD IN THEINNERFRAME FLANGE, RADIUS AND WEB
NOTE:
TO GAIN ADEQUATE ACCESS TO THE LOWER OUTBOARDFRAME LIGHTENING HOLES IT WILL BE NECESSARY TO
REMOVE THE FOLLOWING ITEMS:
OVTBOARD SEAT TRACK RAILSe
FORE I AFT OUTBOARD FRESH AIR DUCTS
OUTBOARD FLOOR PANELS
ELECTRICAL WIRE BUNDLES
ETC., AS REQUIRED FOR ACCESS R----W.L. -55.50
I t-, I
00
I
NOTE:REFER TO TCAC DRAWING NO. 300004,jj+
OUTBOARD CABIN FLOOR FRESH AIR DVCTSSHEET 2 OF 2 TO MAKE THE D(ISTING
REMOVABLE FOR FUTURE REOCCURRING ~IINSPECTIONS
j/2’ OUTED LIGHTENINGHOLE ALL FRAMES
I
I
D<CEPT WH 96.50 8 99.00
(REF.)
f,I
UP
INBD
INSPECT FOR CRACKS IN FRAME WEBFP
l.oo INCH DIAMETER AROUND UPPER
INSPECT FOR CRACKS ORIGINATING AT
END OF STRINGER CUTOUT
I 9 JFASTENER HOLES rN THE FRAME WEB
FOR LOOSE OR SHEARED CONDITIONS
COMMON TO SUPPORTS, BRACKETSAND LINE BLOCKS
F/GURE #25VIEW LOOKING FORWARD THE LOWER
RIGHT HAND FUSELAGE STATION 87.00 FRAME SECTION
TYPICAL ON THE RIH F.S. 78.00, 87.00, 96.50 99.00 ONLY
TYPICAL ON BOTH THE L R/H F.S. 60.50 108.00 THRU 155.54
(17 LOCATIONS TOTAL)
Page No, 59 of 72
SERVICE BULLETIN MO, 214
Part I
INSPECTION
INSPECT FOR CRACKS IN THE 310844-29/-39 HOODIF PJ FORMER ALONG THE UPPER RETURN FLANGE, RADIUS,
AND FORMER WEB FROM L.B.L. 10.80 TO THE OUTBOARD
TERMINATING END
INSPECT FOR CRACKS IN UPPER SKIN HOOD
NOk: ~1 FORMER WEB AROUND THE LOWERINBOARD
TO GAIN ADEQUATE ACCESS TO THE UPPER OUTBOARD CORNER OF THE LIGHTENING HOLE,FIANGE RADIUS, IT WILL BE NECESSARY TO REMOVE OR I U(TENDING FROM LOWER RELIEF
DISCONNECT THE FOLLOWING ITEMS:
NOTE:CABLES GAIN ACCESS THROUGH THE FORWARDNITROGEN LINES UPPER FUSELAGE I BAGGAGE COMPARTMENT PANELHYDRAULIC LINES SKIN (REF)STATIC LINES
ETC., AS REQUIRED FOR ACCESS
eg a
a ees
a iia!
e~T V~ I I\ Q QO
;i 8
310844-29/-39 HOOD
FORMER (REF)
W.L. -5.10
QQg Q g Q g g g/~ g Q g~Q 9.UP
.I --_I
310844-29/-39 HOODWING REAR
SPARiF.S. 209.24 BULKHEAD
FORMER (REF.) L.B.L. 10.80UPPER CAP (REF.) (REF.)
FIGURE #26VIEW LOOKING UP FORWARD THE UPPER
LEFT HAND F.S. 209.24 BULKHEAD UPPER SKIN HOOD FORMER
RIGHT HAND SIDE OPPOSITE
Page No, 60 of 72
-J
SERVICE BULLETIN Nd, 214
Part ~IIRECURRING INSPECTIONS
ACCOMPLISHMENT INSTRUCTIONS %rlll RECURRING INSPECTIONS
1. Refer to Pan Il, Table I, and proceed with the applicable RECURRING INSPECTIO’N ITEMS which
defines the appropriate INSPECTION FIGURE(S).
2. Disconnect batteries.
3. Support fuselage with wing jack stands and tail tie-down stand as outlined in Airplane Maintenance Manual.
4. Remove all interior I exterior components as required to gain access to the applicable areas of the aircraft.
5. Follow the inspection criteria specified by each FIGURE(S) to determine if any cracking or damage is present.
NOTE:
IF CRACKING OR DAMAGE IS FOUND REFER TO ITEM #2 #3 IN COMPLIANCE SECTION.
6. Sealant and finishes must be restored per recommended Aircraft Maintenance Manual practices after
inspections are completed.
NOTE:
FOR LOCAL TOUCH UP ON EXISTING STRUCTURE, CHROMATE PRIMER MAY BE USED.
DO NOT MIX CHROMATE AND POLYURETHANE PRIMERS ON THE SAME PART.
7. Perform operational check of cabin pressurization system for leaks per Aircraft Maintenance Manual practices.
8. Re-install items removed as noted per Item 4.
Page No. 61 of 72
5
SERVICE BULLETIN NO.´•214
TABLE IPart II b
RECURRING INSPECTION INTERVALS
Part I Part II EFFECTIVITY.INSPECTION RECURRING INSP. MODEL/ SERIAL NO.FIRST INSPECTION
ITEM HOURS/ FIGURE(S) HOURS I FIGURE(S)
1. CABIN DOOR 3000 HRS i FIG. 9 98 1000 HRS I FIG. 1 lE 695A
96001 MRU 96013
8 96018 ONLY
2. 1 LOWER CABIN SKIN 7500 HRS I FIG. 15 750 HRS i FIG. 2 690D ALL
CRACKS 695A -ALL
6958 -ALL
3. LOWER CABIN FLOOR 7500 HRS i FIG. 25 1500 HRS I FIG. 3 690D ALL
FRAMES 695A ALL
6958 ALL
4. AFT PRESSURE 7500 HRS FIG. 26 1500 HRS I FIG. 4 690D ALL
BULKHEAD HOOD 695A ALL
FORMER 209.24 6958 ALL
INITIAL INSPECTIONS OF THE ABOVE AREAS ARE REQUIRED FOR ALL MODELS AND SERIAL
NO.’S AS SPECIFIED BY SE 214, Tart I, Table 1;
Item 1
EXAMPLE: Aircraft has reached 3000 airframe Hours Time-in-Service. Full compliance with items 1700,
2500, 3000, 5000, 6000, and 7500 Hour Aircraft Inspection Time Periods per Pmt I, Table I was
accomplished at 1900 Hours. Compliance with PartlI, Table I (Item #1 Cabin Door, Figures #1
#18 1000 Hour Intervals) must be completed at 3000 Hours, with the next recurring inspectiondue at 4000 Hours Time-in-Service and subsequently thereafter.
Item 2
EXAMPLE: Aircraft has reached 7500 airframe Hours I Time-in-Service. Full compliance with items 1700,
2500, 3000, 5000, 6000, and 7500 Hour Aircraft Inspection Time Periods per Parr I, Table I was
accomplished at 1900 Hours. Compliance with Part Il, Table I(ltem #2 Lower Cabin Skin Cracks,
Figure #2 750 Hour Intervals) must be completed at 7500 Hours. with the next recurring
inspection due at 8250 Hours I Time-in-Service and subsequently thereafter.
Item 3 &4
EXAMPLE: Aircraft has reached 7500 airframe Hours I Time-in-Service. Full compliance with items 1700,
2500, 3000, 5000, 6000, and 7500 Hour Aircraft Inspection Time Periods per Parr I, Table I was
accomplished at 1900 Hours. Compliance with Part U, Table I (Item #3 Lower Cabin Floor Frames,
Figure #3 and Item #4 Aft Pressure Bulkhead Former at 209.24, Figure #4 1500 Hour Intervals)must be completed at 7500 Hours, with the next recurring inspection due at 9000 Hours I
Time-in-Service and subsequently thereafter.
Page No, 62 of 72
SERVICE BULLETIN NO. 214
Part. IIRECURRING INSPECTIONS
FIGURE #~B 1F.S. 81.l0 F.S. 74.45 ,FIC;URE 1118
\i
t o c c o c c
1 .Il\e
+r I~LYI \f
FIGURE #lD FIGURE #lDFIGURE #lCc
OOQQOJOOOf +Je
D I r I II II+~-L-W II II+ W.L. -15.05r
+I ~I++I ii o
O II Y+:le
´•cl o1
o +:lfJ
UP c
+eco hFWD
1
J
o
+10 a8 $1++
FIGURE IIlU o3
~LI (3 1 jl+l FIGURE #~D
0\ /3´•r
-r
cll\cDI o5
a (I+j~ D-W´•L1~26.60D D O O O J S 3 O
O O8c
+L+I I I I I+
c a8 ~i+
’I I+a
+I:ra c
FIGURE #1D a 9 a FIGURE HD+Le +’I+
a ~I.. ..I-´• I´• 71 ..~19 a d+a
c a I I+ :I D- W.L. -37.57c
a
a8 a
FIGURE #1A3 8
CI I I
:I+c
I ´•I+
OQ
f
C I I ~lt
Tl\l I\ I I 11 I Il:li
FIGURE#1D---\ IIli I~lo Cor I ;I+ FIGURE IIlU
’I"I I+
+I I- L C´•(
t
’:L D--W.L.-48.90c I+ Ic
FIGURE #1VIEW LOOKING OUTBOARDTHE MAIN CABIN ENTRY DOOR
(REF. SE 214, PART I, FIGURE #9)EFFECTIVITY
MODEL SIN
330247 i 330430 DOOR 695A (96001 THRU 96013
CONFIGURATION SHOWN 695/4 96018
Page No. 63 of 72
SERVICE BULLETIN NO. 214
Part IIRECURRING ’INSPECTIONS
(Fpl’NSPECT FOR CRACKS ORIGINATING FROM THE
ZEE CHANNEL
7 r1’’1´•1.00 INCH DIAMETER PUSH ROD HOLE IN
THE ZEE CHANNEL WEB W.L. -48.13
INSPECT FROM THE UPPER SIDE ONLY
(REF.) INTERCOSTAL a
T~ (REF´•)
CLIP(REF.)--\~\I j /i"
’Ie
i´•8 8
om
(7>
C3~ XAFTs-----IC~s
O
Ooo Ci; o b
----W.L. ~8.13
INNER DOOR STRAPo
o
INNER PLATEDOOR FRAME
INNER STRAP
DOUBLER (REF.)
(REF.)(REF.) NOTE:(REF.)
DO NOT REMOVE ANY RIVET MOUNTED
DOOR PARTS FOR INSPECTION PURPOSES
FIGURE #?AVIEW LOOKING OUTBOARD DOWN THE
LOWER AFT CORNER OF T~-1E CABIN DOOR(PUSH ROD LINKAGE OMITTED FROM VIEW FOR CLARIP~
(REF. SE 214, PART I, FIGURE #9A)
330247 1 330430 DOOR ONLY
NOTE:
RECURRING INSPECTIONS REQUIREDMODEL yN
~1000 HOUR INTERVALS PER SE 214.695A 96001 THRU 96013
PART II, FIGURE #1A695A 96018
Page No. 64 of 72
18
SERVICE ~ULLETIN Nb. 214
Pari IIRECURRING INSPECTIONS
CA UTION: I 1 INSPECT FOR CRACKS ORIGINATING FROM THE
OR TORN OFF:DURING-DISASSEMBLY,FP DIAMETER FROM THE CENTER OF THE HOLE
USE U(TREME CARE WHEN REMOVING THE OUTER BAYONET PIN HOLE AND GUIDE BLOCK
DOOR SEAL, IF ANY RUBBERNIPPLES ARE DAMAGED ATTACHMENT FASTENERS 1.50 INCHES IN
THE SEAL MUST BE REPLACED IN THE OUTER DOOR FRAME WEB
’g OO DOORFRAME
~7 INSPECT RIVETS COMMON TO THE VERTICAL \o dWEB (REF.)
V Oi IWINDOW CHANNEL UPPER END, SMEAR CLIPS
AND BAYONET GUIDE BLOCK FOR LOOSE OR 9~5SHEARED CONDITIONS
O~8‘´•, o
;"´•~s8 8.O\I O
O OB
0/
0/ ~G/
oi
o
o
o
i UP
VERTICAL WINDOW ~jt/""OUTER DOOR CHANNEL (REF.)
SKIN (REF.)
NGURE #~BVIEW LOOKING OUTBOARD DOWN THE
UPPER AFT CORNER OF THE CABIN DOOR(BAYONET PIN OMITTED FROM VIEW FOR CLARIP~
(REF. SE 214, PART i, FIGURE #9B)
3302471 330430 DOOR ONLYAFT UPPER PIN F.S. 91.10 SHOWN
FORWARD UPPER PIN F.S. 74.45 TYPICAL
NOTE:EFFECTIVITY
RECURRING INSPECTIONS REQUIREDMODEL S:N
1000 HOUR INTERVALS PER SE 214, 695A 96001 iHRU96013PART II, FIGURE #1 B
695A 96018
Page No, 65 of 72
SERVICE BULLETIN NO. 214
Part IIRECURRING INSPECTIONS
NOrr: CAUTION:IT WkL BE NECESSARY TO REMOVE THE BAYONET DUE TO REPEATED REMOVALS OF THE BAYONETGUIDE BLOCK TO INSPECT THE UPPER DOOR BEAM GUIDE BLOCK FOR INSPECTIONS EXERCISERADIUS EXTREME CARE WHEN REMOVING THESE FASTENERS
NOT TO ENLARGE OR ELONGATE EXISTING HOLES IN
FOR REINSTALLING THE GUIDE BLOCK TO THE THE DOOR FRAME OR BAYONET GUIDE BLOCKDOOR FRAME WEB, IT IS ACCEPTABLE TO INSTALLHL20P6-5 PIN 8 HL86-5 COLLAR ~7INSPECT FOR CRACKS IN THE BEAM UPPER FLANGE
IF REQUIRED, THE HL20PB-5 PIN 8 HL86-5COLLARPP
VERTICAL RETURN FLANGE RADIUS OF THE BEAM
HOLE LIMITS (.1625 1.1600) RADIUS 3.00 INCHES FORWARD FROM THE AFFTERMINATING END OF THE PART AND THE AFT
MAY BE TAKEN TO THE NEXT SIZE FASTENER
HL20PB-6 PIN 8 HL86-6 COLLAR
HOLE LIMITS (.1885 1.1855) O I)OOR FRAME
O ,1WEB (REF.)
0\a
UPPER AFT 8AYONET
l~e
GUIDE BLOCK(REF.)
I ji,,,,,,,.
BEAM ~REF.)
OUTER DOOR
1SKIN (REF.)
~NSPECTSaOFS. 91.78 INCHES
VERTICAL WINDOWCHANNEL (RE~)
O~’e,
FIGURE #~CVIEW LOOKING OUTBOARD UP THE
UPPER AFT CORNER OF THE CABIN DOORIBA YONET PIN 4 LINKAGE OMI~ED FROM VIEW FOR CLARITY)
(REF. SE 214, PART I, FIGURE #9C)
220247 1 330430 DOOR ONLYAFT UPPER PIN F.S. 91.10 SHOWN
FORWARD UPPER PIN F.S. 7;4.45 TYPICAL
(COORDINATE WITH INSPECTION FIGURE #´•1B)
NOTE:
RECURRING INSPECTIONS REQUIREDh~ODEL SIN
1000 HOUR INTERVALS PER SE 214,695A 96001 THRU96013
PART II, FIGURE #1C695A 96018
Page No. 66 of 72
SERVICE BULLETIN NO. 214
Part IIRECURRING INSPECTIONS
(Fj~ INSPECT FOR CRACKS IN THE OUTER DOOR
DOOR FRAME
I")FRAME PLATE DOUBLER AROUND THE BAYONETGUIDE BLOCK 1.00 INCH ABOVE I BELOW THEUPPER I LOWER ENDS OF THE PLATE DOUBLER
WEB (REF.) /--CAUTION:USE UCTREME CARE WHEN REMOVING THE
O
J-/6OUTER DOOR SEAL, IF ANY RUBBER NIPPLESARE DAMAGED OR TORN OFF DURING
DISASSEMBLY,THE SEALMUST BE REPLACED
~T1?O IsINSPECT 1.00INCH ABO~E
O
o W.L. -26.60
INNER DOOR STRAPDOUBLER (REF.)
O j/oIFP’ INSPECT FOR CRACKS IN DOOR
I~I" I FRAME RADIUS ALONG THEOUTBOARD EDGE OF PLATEDOUBLER
BAYONET GUIDE-/-I! a
P_O
O
O INSPECT 1.00
j I\NCH BECOW
iYi,.. O I"
V-NOTE:DO NOT REMOVE THE OUTER DOOR FRAME PLATE
PLATE DOUBLER (REF.) DOUBLER OR BAYONET GUIDE BLOCK FOR
INSPECTION PURPOSES, ONLY INSPECT ON 8 TOTHE U(ISTING EDGE OF PART
FIGURE #?DVIEW LOOKING OUTBOARD AFT THE
W.L. -26.60 FORWARD DOOR BAYONET DOUBLER(BAYONET PIN OMITTED FROM VIEW FOR CLARITY)
(REF. SE 214, PART I, FIGURE #9D)
3330247 1 330430 DOOR ONLYFORWARD 8 AFT BAYONET PIN W.L. -15.05 TYPICALFORWARD 8 AFT BAYONET PrN W.L.. -26.60 SHOWN
FORWARD 8 AFT BAYONET PIN W.L. -37.57 TYPICAL
FORWARD 8 AFT BAYONET PIN W.L. -48.90 TYPICAL
NOTE:
RECURRING INSPECTIONS REQUIRED EFFECTIVITYMODEL S,N
1000 HOUR INTERVALS PER SE 214,695A 96001 THRU96013
PART II, FIGURE 410695A 96018
Page No. 67 of 72
SERVICE BULLETIN-MO. 214
Part IIRECURRING INSPECTIONS
INSPECT RIVETS COMMON TO THE OUTER 1-7INSPECT RIVETS COMMON TO THE OUTERU jSK,NAND VERTICAL WINDOW CHANNELS UI I SKIN AND DOOR FRAME AROUND THEON THE FORWARD I AFT SIDE OF THE DOOR I PERIMETER OF THE DOOR FOR LOOSE ORFOR LOOSE OR SMEARED CONDITIONS I SHEARED CONDITIONS
F.S. I F.S:
74(45 91110
f:::: fff
li:fit5
WL. -15.05-- I´•:S
,J I;;
i
EIWL. -26.60--Tq:ji \iT5 I’ 3=3
I:i
fsl
W.L. .37.57- i´•I i:iii i,i
xiI~
:+;;+i sL~´•-j
r:l
E i:i,,
1
.;b I´•!
FIGURE #~EVIEVV LOOKING INBOARD
THE CABIN DOOR OUTER SKIN
(REF SE 214, PART I, FIGURE #9E)
330247 1 330430 DOOR ONLY
NOTE CLEAN AREA FOR VISUAL INSPECTION PROCEDURES ONLY!DO NOT REMOVE PAINT FROM THE SIDE SKIN SURFACE!
NOTErRECURRING INSPECTIONS REQUIRED TrVIPI
MODEL S/N1000 HOUR INTERVALS PER SE 214.
695A 96001 THRU 96013PART II, FIGURE #1E
695A 96018
Page No. 68 of 72
SERVICE BULLETIN NO. 214
Part IIRECURRING INSPECTIONS
INSPECT ALONG RIVETS LINES COMMON TO FUSELAGEI U I FRAMES FOR CRACKED, TIPPED, SMOKING, WORKING
OR SHEARED FASTENER CONDITIONS
INSPECT FUSELAGE SKIN ALONG RIVET LIMES COMMON
TO FUSELAGE FRAMES FOR CRACKING BFMIEEN RIVETHEADS
NOTE:
IF DAMAGED RIVETS OR CRACKING INDICATIONS ARE
NOTED DURING VISUAL INSPECTION PROCEDURE,REMOVE PAINT AND CONTINUE WITH FLORESCENT
DYE PENETRANT INSPECTION PROCEDURE
ii Irl Itl\ B_EP_MKEELCAPL.B.L. 9.07
j AIRCRAFT
NTERLINEFWD--’ -L;-,,,,-L"-,-,’~,,--LL;L-----U;LC-L 8. L. 0~0
KEELBEAMCAP
R.B.L. 9.07
87.00 108.00 1 126.00 144.00F.S. F.S. ES. F.S.
F.S. F.S. F.S. F.S. F.S.
78.00 96.50 99.00 117.00 135.00
FIGURE #2VIEW LOOKING UP THE LOWER FUSELAGE
(REF. SE 214, PART I, FIGURE #15)
INSPECT THE FOLLOWING AREAS ALONG
FRAIME RIVET LINES (SKIN 8 RIVETS ONLY)F.S. 78.00, L.B.L, 9,07- R.B.L. 9.07
F.S. 87.00, L.B.L. 9.07- R,B.L. 9.07
F.S. 135.00, L.B.L. 9.07- R.B.L. 9.07
F.S. 144.00, L.B,L. 9.07- R.B.L. 9.07
NOTE: CLEAN AREA FOR VISUAL INSPECTION PROCEDURES ONLY!
DO NOT REMOVE PAINT FROM LOWER SKIN SURFACE!
NOTE:
RECURRING INSPECTIONS REQUIRED750 HOUR INTERVALS PER SE 214,
PART II, FIGURE #2
Page No. 69 of 72
SERVICE BULLETIN NO. 214
Part IIRECURRING INSPECTIONS
FLOOR BRAGKET CONFIGURATIONAND FASTENER PATTERN MAY VARY W.L. ~5.00
ill INSPECT FOR CRACKS IN THE LOWER FRAME IN DESIGN PER FRAME (REF.)I v ]AROUND THE OUTBOARD LIGHTENING HOLE
fU
P´• -eBELOW THE FLOORLINE 2.00 INCHES ABOVE I OUTEDAND 2.00 INCHES BELOW I INBD ALONG THE INNERFRAME FLANGE, RADIUS AND WEB
NOrr:
IF DAMAGED RIVETS OR CRACKING INDICATIONS ARE\ I fNOTED DURING VISUAL INSPECTION PROCEDURE, L.B.L. 22.57
REMOVE PRIMER AND CONTINUE WITH FLORESCENT
DYE PENETRANT INSPECTION PROCEDURE
NOrr:TO GAIN ADEQUATE ACCESS TO THE LOWER OUTBOARDFRAME LIGHTENING HOLES 1T WILL BE NECESSARY TOREMOVE THE FOLLOWING ITEMS:
FORE I AFT OUTBOARD FRESH AIR DUCTS
ETC., AS REQUIRED FOR ACCESSWL. -55.50
i +I
i a´•i~J FASTENER HOLES IN TnE FRAME WEB
FOR LOOSE OR SHEARED CONDITIONS t\ I~COMMON TO SUPPORTS, BRACKETSAND LINE BLOCKS
OUTED LIGHTENINGHOLE ALL FRAMESE(CEPT R/H 96.50 99.00
(REF.)f jl~L
UP
.~LeU
INSPECT FOR CRACKS IN FRAME WEB1.00 INCH DIAMETER AROUND UPPEREND OF STRINGER CUTOUT
FIGURE #3VIEW LOOKING FORWARD THE LOWER
RIGHT HAND FUSELAGE STATION 87.00 FRAME SECTION
(REF SE 214, PART I, FIGURE #25)
TYPICAL ON THE R/H F.S. 78.00, 87,00, 96.50 8 99.00 ONLYTYPICAL ON BOTH L 8 R/H F.S. 60.50 8 108.00 THRU 155,54
(17 LOCATIONS TOTAL)
NOTE: THE R/H FS. 96.50 8 99.00 FRAMES WILL NOT REQUIREINSPECTION THE OUTBOARD LIGHTENING HOLE
NOTE:RECURRING INSPECTIONS REQUIRED
1500 HOUR INTERVALS PER SE 214,PART II, FIGURE #3
Page No, 70 of 72
SERVICE BULLETIN NO, 214
Pa~r IIRECURRING INSPECTIONS
‘INSPECT FOR CRACKS IN THE 310844-29/-39 HOODCF~ FORMER ALONG THE UPPER RETURN FLANGE, RADLUS.
AND FORMER WEB FROM L.B.L. 10.80 TO THE OVTBOARDTERMINATING END
NOTE:
1F CRACKING INDICATIONS ARE NOTED DURINGVISUAL INSPECTION PROCEDUREi REMOVE PRIMER
AND CONTINUE WITH FLORESCENT DYE PENETRANT
INSPECTION PROCEDURE
rii~ 1NSPECT FOR CRACKS IN UPPER SKIN HOOD
NOtE: JFORMERWEBAROUNDTHE LOWERINBOARD
TO GAIN ADEQUATE ACCESS TO THE UPPER OUTBOARD CORNER OF THE LIGHTENING HOLE,
FLANGE RADIUS, IT WILL BE NECESSARY TO REMOVE OR U(TENDING FROM LOWER RELIEF
DISCONNECT THE FOLLOWING ITEMS:NOTE:
CABLES GAIN ACCESS THROUGH THE FORWARDUPPER FUSELAGE BAGGAGE COMPARTMENT PANELNITROGEN LINES
HYDRAULIC LINESSKIN (REF.)
STATIC LINES
ETC., AS REQUIRED FOR ACCESS
e~ g Q
iia!
!I\ o QO
O310844-29/-39 HOOD
FORMER (REF)
W.L. -5.10
a o g g Q O Q g O/Q O g Qj~Q gUP
Q
310844-29/-39 H000WING REAR
SPARiF.S. 209.24 BULKHEADFORMER (REF.) L.B.L. 10.80UPPER CAP (REF.) (REF.)
FIGURE #4VIEW LOOKING UP FORWARD THE UPPER
LEFT HAND F.S. 209.24 BULKHEAD UPPER SKIN FORMER
(REF. SE 214, PART I, FIGURE #26)
RIGHT HAND SIDE OPPOSITE
NOTE:
RECURRING INSPECTIONS REQUIRED1500 HOUR INTERVALS PER SE 214,
PART II, FIGURE #4
Page No, 71 of 72
\3
SERVICE BULLETIN NO. 214
ELECTRICAL LOAD:
No change
WEIGHT AND BALANCE: (Partl, ONLY)
Perform LEVELING AND WEIGHING as outlined in the Airplane Maintenance Manual per Chapter 8
SPARES AFFECTED: (PariL ONLY)
None
RECORD COMPLIANCE:
PARTJT Make an appropriate entry in the Aircraft Maintenance Records as follows: Service Bulletin No. 214,Dated JANUARY 26, 2000, entitled "WING AND FUSELAGE FATIGUE INSPECTION AND
MODIFICATION", complied with (either) FULL COMPLIANCE or PARTIAL COMPLIANCE (list specificitems) as specified by Part I, "COMPLIANCE FORM". Attach copy of Part I, COMPLIANCE FORM to
aircraft logbook. If FULL COMPLIANCE is selected, only Part LT RECURRING INSPECTIONS will be
required. Identify next recurring inspection time hours, per item, in the aircraft logbook. If PARTIAL
COMPLIANCE is selected, identify the next required INSPECTION I MODIFICATION TIME per
Partl; Tablel.
PARTU Make an appropriate entry in the Aircraft Maintenance Records as follows: Service Bulletin No. 214,Dated JANUARY 26, 2000, entitled "WING AND FUSELAGE FATIGUEINSPECTION AND
MODIFICATION", complied with items 1. 2. 3. or 4. as specified by Part II,’COMPLIANCE FORM".
Attach copy of Part II, COMPLIANCE FORM to aircraft logbook. Identify next recurring inspection time
hours, per item, in the aircraft logbook.
SUBMIT A COMPLETED COPY OF THE COMPLIANCE FORMS TO:
TWIN COMMANDER AIRCRAFT CORPORATION
Attn.: SERVICE DEPARTMENT
19010 59’" DRIVE N. E.
ARLINGTON, WA. 98223
Page No. 72 of 72
SERVICE BULLETIN NO. 214
rWIIY COMPLIANCE FORMPartlIVLIEIQ I a/e MODEL: 695A FULL COMPLIANCE g PCEASECHECK
A/RCRA~T. CORPORA 7~ON PARTIAL COMPLIANCE [7 ONLY ONEAIC S/N: 96006
If partial compliance is selected. identify next I ICURRENT DATE: Jan. 26, 2000 AIC TOTAL HOURS: 1,900.0 required INsPECTIONI MODIFICATIONTIME
REQD.MOD.DASH 300005 1 300006 1 300007
NO. I MOD. MOD. FIG. I MOD. MOD. FIG. I MOD. MOD. FIG. I~noo. I/MDD. FIG.INSTL. INSP. INSP. I INSTL. INSP. INSP. I INSTL. INSP. INSP. I INSP.
isi /fNS~.-1 .*´•sc: NIA NIA N/A ;~s.e i NIA
\5’
-501Isi ~1 I5~j ~CficjSB2~1
-503 :ASC
ni~p´•-505 1 ls~l S.J.
-507 1 N/A NIA NIA r~Tj-509 ~X j~T-5111 N/A N/A N/A
sB~i~i. NIA NIA NIA
-515isi
-517s C.i I~sc.
ILI11
(/N/Aisl
S.J.-521 iSB~lli
-523 1 N/A N/A I/N/A I MIA\ I NI sezc~ ~SC i
i"ls NIA A /Y N/A ~51-525 1S"nt"l
-527 Hood Former/ Figure 26
-529 N/A ly N/A N/A
Cabin Door IS.J. Figures 9 9E
,ifi~´• I Cabin Skin Cracks
Figure 15
Lower (1Frames I Figure 25
sueTOTAL 11/I 11 1 10 10 1 12 1 13 13 14 1 6 6 5
TOTAL1 MOD. I~STL.POMPLETE 40 1 MOD. INSP COMPLETE 40 1 FIG. INSP COMPLETE 42
MOD. Required Modification Dash No. Installed INSPECTION:INSTL. (Techniclan Sign-off far Worle Accomplished 1 58-214 STAMP)
MOD. Required Mod. Dash No. Inspected after Installation NAME: "~e DATE:INSP. (Inspector Sign-oft for Wor(e Accomplished I COMPANY STAMP)
FIG. 1"5pection Completed per Applicable Figures
INSP. (1"5pecror Sign-off for Work Accomplished COMPANY STAMP)NAME: ~eal Cr~C DATE.
NIANOt Applicable for This Aircraft Serial No.
AIR.511 is Only Required if Short Edge Distance is Found
per TCAC Dwg. No. 3D0008-505NAME: Steoe ~oltes DATE.
No recurnng inspections are required if the -5CO Modifications are installed.
Four (4) items do not have approved modiftcatians and require recurringInspections per SE 214. Part II. Table i. Initial Inspections per (Figures 9-9E. 15.
This FORM to be Added to the Aircraft Logbook and a COPY Sent to
25. 8 26)8 recurring inspections per ?an II (Figures l-1E. 2. 3. 8 4)TCAC for Compliance.
Page No. 1 of 2
COMPLIANCE RECORD
SE~ICE BULLETIN: N~ 214
WING AND FUSELAGE FATIGUE INSPECTION ANDIOR MODIFICATION
AIRPLANE REG. TOTAL
MODEL S/N NO. TIME (HOURS)
OWNER NAME
ADDRESS
TELEPHONE NO FAXNO
COMPLIANCE WITH SE 214:
DATE
WORK PERFORMED BY
COMPANY
ADDRESS
TELEPHONE FAX
I~
SERVICE BULLETIN NO. 214
Part I
~WIIY COMPLIANCE FORM
%tlllllWAULJEIQI AICMO~L: FULL COMPLIANCE C? PLEASE CHECK
A /RCRAF;T CORPORA 7-/ON A/C S/N:PARTIAL COMPLIANCE O DNLY ONE j
CURRENT DATE: IAIC TOTAL HOURS: required INSPECTION I M001FICATICH TIME I IIf partial compliance is selected, idemify next
REQD.MOD.
DASH 300005 1: 300006 1 300007 1 300008
NO. I MOD. MOD. IFIG. I MOD. MOD. FIG. I MOD; IMOD. FIG. I MOD. MOD. FIG.INSTL. INSP. INSP. I INSTL. INSP. I INSP. I INSTL. INSP. INSP. I INSTL. INSP. INSP.
-501
-503
-505
-507
-509
-5111 1 I I I I I I 1 IA/R ~VR
-513
-515
-517
-519
-521
-523
-525
A ressure u ead-527 Hood Fonner/ Figure 26
-529
Cabin Door/
Figures 9 9E
abin Skin Cracks
Figure 15
Lower Cabin Floor(l7)Frames Figure 25
sueTOTAL
TOTAL I MOD. INSTL. COMPLETE I MOD. INSP. COMPLETE I FIG. INSP COMPLt:r
MOD. Required Modification Dash No. Installed INSPECTION:INSTL. (Technician Sign-off for work Accomplished 1 68-214 STAMP)
MOD. Required Mod. Dash No. Inspected after Installation NAME: DATE.INSP. (I"spector Sign-off far Worle Accomplished I COMPANY STAMP)
FIG. I"spaction Completed per Applicable FiguresINSP. (I"specror Sign-off for Wor)e Accomplished I COMPANY STAMP) NAME: DATE.NIA
NOt Applicable for This Aircraft Serial No.
A/R-511 is Only Required if Short Edge Distance is Found
per TCAC Dwg. No. 300008-505NAME: DATE.
No recurring inspections are required a the -500 Modifications are Installed.
Four (4) items do not have approved modifications and require recumng
Inspections per SE 214. Part II. Table I. Initial Inspections per (Figures 9-9E. 15.This FORM to be Added to the Aircraft Logbook ane a COPY Sent to
25, 6 26) 6 recurnng inspections per Part II (Figures l-1E. 2. 3. 6 4).TCAC for Compliance.
PageN~.lafZ
SERVICE BULLETIN NO. 214
Partl
rrWIAI COMPLIANCE FORM
UICIEIQ I Ale MoDEL: FULL COMPLIANCE PLEASECHECK
PARTIAL COMPLIANCE C1 oNLY ONEA/RCRAF7- CORPORA T70N AIC S/N:
CURRENT DATE: A/C TOTAL HOURS: required INSPECTION I MODIFICATION TIMEI IIf partial compliance is selected. identify next
~JI I
This FORM to be Added to the Aircraft Logbook and a COPY Sent to TCAC for Compliance.
Page No. 2 of 2
117
SERVICE BULLETIN NO. 214
~JCWIY COMPLIANCE FORMPartII%L~WAIAULIEIQIAle MODEL: B95A
A /RCRAFr CORPORA ;r/ON AIC SIN: 96006
CURRENT DATE: March 15, 2002 AIC TOTAL HOURS: 3,000.0
Part I Part IIINSPECTION INITIAL INSPECTION RECURRING INSP. TIVIP(:
ITEM HOURS FIGURE(S) HOURS I FIGUREIS)DE 7 IAL NO.
1. CABIN DOOR 3000 HRS FIG. 9 98 1000 HRS I FIG. 1 1 SIN
TH
9601
NEXTINSPECTION DUE@ 4000.0 TOTALAIRFRAMEHOUR ANDSUBSEQ TH R
OF C CKING G
1 Na crack indications noted of l-1E
INSPECTED BY: 03/15 00
2. LOWER CABIN SKIN 7500 HRS i FIG. 1 S1 .2 690D ALL
CRACKS 695A ALL
6958 ALL
NEXT INSPECTION DUE ZSI1Qa~TbTAL Aid AND SUBSEQUENTLY THEREAFTERLIS ET SOF NYC CKIN G F
Not until 7500 hours
INSPECTED BY: DATE: 03/15/2002
3. LOWER CABI LOO 7500 FIG. 1500 HRS i FIG. 3 690D ALL
FRAMES 695A ALL
6958 ALL
N TION TOTAL AIRFRAME HOURS AND SUBSEQUENTLY THEREAFTERD S ANY ING OR DAMAG
INSP BY: DATE: 03/15/2002
4. SSU 7500 HRS i FIG. 26 1500 HRS i FIG. 4 690D ALL
BU EAD OD 695A ALL
FOR R 209.24 6958 ALL
NEXT INSPECTION DUE ZSDOS TOTAL AIRFRAME HOURS AND SUBSEQUENTLY THEREAFTER
LIST DETAILS OF ANY CRACKING OR DAMAGE FOUND:
Not required until 7500 hours
INSPECTED BY: Biee SHfitk DATE: 03/15/2002
This FORM to be Added to the Aircraft Logbook and a COPY Sent to TCAC for Compliance.
/Y
COMPLIANCE RECORD
SERVICE BULLETIM: NO. 214.
WING AND FUSELAGE FATIGUE INSPECTION AND/OR MODIFICATION
AIRPLANE REG. TOTAL
MODEL S/N NO. TIME (HOURS)
OWNER NAME
ADDRESS
TELEPHONE NO FAXNO
COMPLIANCE WITH SE 214:
DATE
WORK PERFORMED BY (PRINTED)
(SIGNATURE)
COMPANY
ADDRESS
TELEPHONE FAX
r2~)
SERVICE BULLETIN NO. 214
Pari I~
~WIY COMPLIANCE FORM
~IAJIMAULIEIQ I An: MODEL:
A~CRAF7- CORPORA ;T/ON AJC SIN:
CURRENT DATE: AIC TOTAL HOURS:
a
Part I Part UINSPECTION FIRST INSPECTION RECURRING INSP. O EFFECTIVITY:
ITEM HOURS FIGURE(S) HOURS FIGrlRE(S) MODEL I SERIAL NO.
i. CABIN DOOR 3000 HRS FIG. 9 98 1000 HRS FIG. 1 -18 695A S/N
96001 THRU 96013
96018 ONLY
NEXT INSPECTION DUE TOTAL AIRFRAME HOURS AND SUBSEQUENTLY THEREAFTERLIST DETAILS OF ANY CRACKING OR DAMAGE FOUND:
INSPECTED BY: DATE:
2. LOWER CABIN SKIN 7500 HRS FIG. 15 750 HRS FIG. 2 6908 ALL
CRACKS 695A ALL
6958 ALL
NEXT INSPECTION DUE TOTAL AIRFRAME HOURS AND SUBSEQUENTLY THEREAFTERLIST DETAILS OF ANY CRACKING OR DAMAGE FOUND.
INSPECTED BY: DATE:_
3. LOWER CABIN FLOOR 7500 HRS I FIG. 25 1500 HRS FIG. 3 6908 ALL
FRAMES 695A ALL
6958 ALL
NEXT INSPECTION DUE TOTAL AIRFRAME HOURS AND SUBSEQUENTLY THEREAFTERLIST DETAILS OF ANY CRACKING OR DAMAGE FOUND:
INSPECTED BY: DATE:’
4. AFT PRESSURE 7500 HRS I FIG. 26 1500 HRS FIG. 4 6908 ALL
BULKHEAD HOOD 695A ALL
FORMER 209.24 6958 ALL
NEXT INSPECTION DUE TOTAL AIRFRAME HOURS AND SUBSEQUENTLY THEREAFTERLIST DETAILS OF ANY CRACKING OR DAMAGE FOUND:
INSPECTED BY: DATE:
This FORM to be Added to the Aircraft Logbook and a COPY Sent to TCAC for Compliance.
Service Bulletin AIRCRAFT COF)PORATION
p~O. BoX 3389
Arlington. WA 98223
Tel: POB) 43~i-9787 FEU: (208) 435´•1~12
SERVICE BULLETIN NO. 216 Original: June 9, 1992
FUELING PLACARD AND FLIGHT MANUAL ADDENDUM
MODELS AFFECTED:
All Twin Commander Airplanes
REAI1ON FOR PUBLICA1CION:
Twin Commander airplanes (like many others) are equipped with
multiple interconnected fuel tanks. Extended fueling time is
required for fuel to flow and equalize the fuel level among the
interconnected tanks. This is necessary to assure that the desired
proper fuel level is achieved. Although this fueling characteristic
is believed to be well-known among operators and service personnel,Twin Commander Aircraft Corporation has received a report of a
ditching of a Model 5005 in Hawaiian waters which was attributed to
fuel exhaustion, caused by insufficient fuel. This Service Bulletin
;heing issued in an effort to prevent the possibility of the above
iccurring. It provides additional warning and guidance to Twin
Commander operators and fueling personnel to assure proper fuel level
is achieved during fueling.
COMPLIANCE:
Accomplish at next convenient opportunity, not later than the next
required periodic inspection.
APPROVAL:
Engineering design aspects are FAA approved.
ESTIMATED MAN HOOR8:
Less than one hour.
PARTS DATA:
Enclosed herewith:Part No.
a ea Warning Placard 58216-1
1 ea Aircraft Flight Manual Special Supplement Fueling... 55216-2
Page 1 of 2
SERVICE BULLETIN NO. 216
ACCOnPLI8H IN8TRUCTI~091B
i. Select a smooth area near each fuel filler port. Clean the
aircraft surface and install Warning Placard, P/N SB216-1 in
each area so as to be highly visible during fueling.
2. Place Aircraft Flight Manual Special Addendum Fueling P/N58216-2 at the front of the Aircraft Flight Manual or Pilots
operating Handbook, whichever is available for your airplane.
RECORD COMPLIANCE:
i. Make an entry in the Aircraft Logbook as follows:
Service Bulletin 216, dated June 9, 1992, "Fueling Placard
and Flight Manual Addendum" accomplished (DATEI.
2. Mail attached compliance card to Twin Commander Aircraft
Corporation.
Page 2 of 2
TWIN COHHANOER ATRCIIAFT
AIRCRRlrT CORPDI~TION FLl:aHT MANUAL Date: May 29. 1992
BPECIAL ADDENDUM F6ELINO
WARN~ND
This aircraft is equipped with multiple interconnected fuel tanks. To
assure proper fuel level it is necessary for fueling personnel to allow
extended fueling time for fuel to flow and equalize level among the
interconnected tanks.
I~ ACTION REOUIRED
Insure that fueling personnel understand the requirement to allow
extended fueling time to assure proper fuel level.
Verify proper fuellevel prior to flight dep8r~ure.
PLACARD
The following placard is to be permanently maintained adjacent to
each fuel filler port:
WARNING
TO ASSURE PROPER FUEL LEVEL,ALLOW EXTENDED FUELING TIME
TO EOUALIZE FUEL LEVEL AMONG
TnE INTERCONNECTED TANKS.
P/N 58216-1
NOTE: Permanently retain this Special Addendum at the front
of the aircraft Flight Manual or Pilots OperatingHandbook.
PIN 58216-2
COMP LIANCE CARD
Se~ica Buiierin/L´•rrer,; Iniormarion No.
airc:art Mooel Si N
1 Owner:
COMPLIANCE:
WOrK Periormed By:
Dare:
Signature
TC 14 OW191
~IIIAl
AIRC RA FT CO RPO RA TION
27 June 94
Dear Twin Commander OwnedOperator:
This cover letter is included with Service Bulletin No. 218 to explain the use of the wordMANDATORY on the first page of the service bulletin.
Twin Commander Aircraft Corp. (TCAC) considers our service bulletins to be mandatory.Therefore,;ill TCAC service bulletins will have MANDATORY written on the first page. Thiswill eliminate confusion regarding compliance with TCAC service bulletins. Compliance withall service bulletins issued by TCAC, both new and existing, is required and mandatory.
In some cases TCAC will recommend rather than require compliance with a service
publication. In these cases a Service Letter or Service Information will be issued, rather than a
service bulletin. Compliance with service letters and service information is stronglyrecommended.
All questions regarding this letter or any TCAC service publication should be addressed to theTCAC Engineering Dept.
Sincerely,
,_PMathesonGeneral Manager
JKM/gw
rwlu Cnhl*asoea alaea~FT E0apananoN o, NE L\llln.f.n Wa II111 nl´•ononl~mr F´•r ul loM, al.n~l?
SE RVICE PUB LICATIONS ~HMRNDERAIRCRAFTCORPORATION
revision notice p.g. sox 3388
Adington. WA 98283
Tel: (208) 433-8187 Fax: (208) 435-1112
Service Bulletin No. 218
Revision No. 1
Release Date: July 11, 1994
EMPENNAGE VERTICAL SLABILIZER INSPECTION AND MOD.CICATION
APPROVAL:
Engineering design aspects are FAA approved.
1. Delete (80) MS27039DD1-09 screws from 58218-501 paris list.
2. Add (80) MS35206-264 screws to 58218-501 parts list.
REVISE ACCOMPLISMMENT INSTRUCTIONSAS NOTED:
1. Replace "MS27039DD1-08" with "MS3520B-264" at all locations.
2. Add the following NOTE after step 15c.
NOTE:
Twin Commander Aircraft Corp. recommends the use of an anti-seize compoundwhen installing the M535206-264 screws in the MSZ7130-A19 -AaO rivnuts.
REVISE FIGURES AS N~ED:
Replace "MS27039D01-09" with "MS35206-264" at all locations.
SERVICE PUBLICATIONSAIRCRAFT CORPORATION
revision notice Fo. sox 3388
Mington. WA 9a223TaI: (208)~359181 Far: (206) 435´•1112
Service Bulletin 218
Revision No. 2
Release Date: September 23, 1994
EMPENNAGE VERTICAL STABILIZER INSPECTION AND MODIFICATION
APPROVAL:
REVISE FIGURES AS NOTED:
1. Please note on page 15 of 20 FIGURE 2 bottem of page under "MS20426AD4through nut ring, sltin and doubler flush N.S. 10 FL" NOTE: THE DOUBLERREFERRED TO IS THE EXISTING DOUBLER WHICH IS UNDER THE SKIN. THIS ISNOT REFERING TO THE NEW DOUBLER K410008-1.
2. R]ote:an page 22 of 22 FIGURE 8 bottem of page NOTE: BE SURE TO CUT OUTDOUBLER K410008-1 SO THAT ACCESS DOOR K410008-3 IS FLUSH WITHK410008-1 DOUBLER WHEN COMPLETE.
--MANDA TORY
~ervice Bulletin AIRCRAFT CORPORATION
p.o. B~x
*,lington. WA 08221
Tsl: (20(1) 435´•8187 Pax: (20a) 45?1´•11(2
Service Bulletin No. 218
Dated: May 19, 1994
EMPENNAOE VERTICAL STABILIZERIISPECTION AND MODIFICATION
NOTE:
This Service Bulletin supercedes and replaces Service Bulletin No. 206 in its
entirety for the effective models.
I;SEE~ULIIY;
A685 12000 thru 12066
690 11000 thru 11079 1 NB90A 11100 thru 11344 D6908 11350thru11566
690C 11800 thru 11735 IA690D 15001thru15042 T695 85000 thru 95084
695A 98001 thru 98100 10
RNOTE:
Model 6958 airplanes (Serial Numbers 96062, 96063, 96069, 96075, 96078, IY96085, and 96201 thru 96208) are excluded from this Service Bulletin. Service
Bulletin 206 is still effective for 6958 airplanes.
REASON FOR PVBLICATION:
TCAC has received several reports of aircraft with damage to the vertical stabilirer.
These reports include: cracks in lower ribs, wrinkles and/or cracks in skin near lower
ribs, cracked shear clips between lower ribs and rear soar, and cracks in upper relief
cutouts of FS 409.58 bulkhead. If left unrepaired, this damage could propagate? to
the point of failure of the Vertical tail. This Service Bulletin defines the requirementsfor inspection of these areas. In addition, modifications are defined which eliminate
the need for further action.
If any of the above damage is found, then the Part II modifications must be
completed immediately as damage could propagate to the point of failure.
PAGE 1 OF 22
SERVICE BULLETIN NO. 218
COMPLIANC~
At 2000 hours total airframe time or within next 50 hours if
beyond 2000 hours and repeat each 12 months or 500 hours, whichever comes first.
EXCEPTION:
Airplanes recently inspected per Service Bulletin 206 and found to be free of
damage shall be inspected per Service Bulletin 218 within 12 months or 500
hours, whichever comes first, from the date of the last Service Bulletin 206
inspection.
Part II: Modification Before further flight if damage is found during Part I inspection.Part II is terminating action and no further special inspections per this service bulletin
are required.NOTE:
If no crac)cs are found during the Part I inspection the ownerloperator can
choose between repetitive inspections teach 12 months or 500 hours) or
completing Part II.
BYWHOM WORK WILL BE ACCOMPLLSHED:
1. A P Mechanic or equivalent.2. Eddy Current inspectors shall be Level II or Level III certified per MIL-STM1OE
and SNT-TC-1A.
APPROYBL:
Modifications described by this Service Bulletin are FAA DER approved.
i. Service Bulletin 206,"lnspection of Empennage Attach Area at Fuselage Station
409.56".
2. Service Letter 345, "Vertical Stabilizer Attach Bolts Inspection".
Part I Inspection: 10 hours tall models).Note: The time noted assumes that an access hole per Service Letter No. (SL) 345
has already been installed on the applicable models.
Part II Modification: 90 hours (models 685, 690, 690A, 690B, 690C, and 695).85 hours (models 690D and 695A).
ZL OF 4.
SERVICE BULLETIN NO. 218
PARTS DATA:
Parts required to comply with this Service Bulletin may be ordered from your nearest
Twin Commander Service Center under kit number listed below for the applicableairplane model. The kits consist of parts listed below.
Part I. access door only
Kit number SB218-501:
Otv Part Number DeScriDtion1 K410008-3 Access door
1 K410008-5 Nut ring20 NASBB03-2 Screw
60 MS271 30-A19 Rivnut
30 MS271 30-A20 Rivnut
80 MS270390D1-09 Screw
80 ANBBOPD1OL Washer
Part II. Modification
Models 685. 690. 690A. 690B. 690C, and 895 kit number S8218-503:
Qt~ Part Number Descriotion
1 K310025-1 Strap1 K310025-2 Strap2 K310025-3 Filler
1 K310025-5 Doubler
1 1<310025-6 Doubler
2 K310025-7 Filler
2 K310025-9 Strap1 K410009-1 Doubler
1 K410009-3 Filler
1 K410009-5 Angle1 K410009-7 Angle2 K410008-1 Lower Skin Doubler
2 K410008-7 Strap2 M535489-46 Orommet
18 HL18PB5-2 Hilok
4 HL18PB5-3 Hilok
8 HL18PB5-4 Hilok
12 HL18PBS-6 Hiiok
4 HL18PBB-3 Hilok
6 HL18PB6-4 Hilok
2 HL1LIPBB-~ Hilok
20 HL19PBB-2 Hilok
4 HLB5PB6-7 Hilok
PAGE 3 nF 22
SERVICE BULLETIN NO. 218
PARTS DATA: Kit number SB218-503 (cont’d)
4 HL18PB6-2 Hilok
40 HL70-5 Collar
36 HL70-6 Collar
4 HL87-6 Collar
Models 690D and 695A kit number SBZ18-505:
2 K310025-3 Filler
1 K310025-5 Doubler
1 K310025-6 Doubler
1 K410009-1 Doubler
1 K410009-3 Filler
1 K410009-5 Angle1 K410009-7 Angle2 K410008-1 Lower Skin Doubler
2 K410008-7 Strap2 N15335488-46 Grommet
16 HL18PB5-2 Hilok
4 HL18PB5-3 Hilok
8 HL18PB5-4 Hilok
12 HL18PB5-8 Hilole
4 HL18PBB-3 Hilok
6 HL18PB6-4 Hilok
2 HL18PB6-5 Hilok
4 HL18PB6-6 Hilok
20 HL19PB6-2 Hilok
4 HLB5PB6-7 Hilok
40 HL70-5 Collar
36 HL70-6 Collar
4 HL87-8 Collar
OPTIONAL Right hand access panel. kit number 58218507:
Otv Part Number
1 31101711 Door
1 311017-6 Doubler
1 311017-7 Angle1 311017-9 Angle1 311017-11 Doubler
1 311017-13 Doubler
10 MS21049L3K Nutplate10 MS246Q4S49 Screw
1 Service Letter 345 instructions
4 OF i.ri
SERVICE BULLETIN NO. 218
PARTS DATA: (cont’d)
Airplanes that do not have the left hand access panel per SL 345 can order and
install the following kits:
SL 345-1 Models 685, 690, 690A, 690B,690C 11600 thru 11529, and
695 95000 thru 95010
SL 345-2 Models 690C 11630 thru 11681 11709 and
695 95011 thru 95079
TO BE PROCURED LOCALLY AS REQUIRED:
1. MS20470AD4, AD5, AD6, MS20428AD4, AD5, AD6, ~173243-4,-5,-6,and CR3242-4 RIVETS,
2, 825-309 (DESOTO) POLYURETHANE PRIMER FOR TOUCH-UP ON
PARTS SUPPLIED WITH KIT.
3, R411N SEAL (RUBATEX) AND EC-1403 OR EC-1300L ADHESIVE
(3M) OR EQUIVALENT.
4. LOCTITE 609 OR EQUIVALENT.
SeEWBCZQPLS: Torque wrench with 330 inch-pound capability
ACCOMPLISHMENT INSTRUCTIONS: PART I-INSPECTION
i. Install tail stand on tail skid and shore horirontal tail per procedure in applicableAirplane Maintenance Manual.
2. Remove left and right rudder control linkage access doors that are located justaft of fuselage station 409.56.
3. Remove:
a) The left and right vertical-to-horirontal stabilizer fairings.
b) The rudder hinge cover.
4. Install the left hand access panel per SL 345, if not already installed. Remove
the access panel, if installed,
NOTE:
The SL 345 access panel is not required for 690C sin 11719 thru 11735, 690D
all, and 695A s/n 96014 thru 96017 96019 thru 96100. For these airplanes,gain access through the door in the belly of the fuselage forward of FS 386,
Pnc.F 5 nF 33
SERVICE BULLETIN NO. 218
ACCOMPLISHMENT INSTRUCTIONS: Part I (cont’d)
5. Visually inspect vertical stabilizer skin, left and right sides, for cracks (refer to
Figures 2 and 3.)
CAUTION:
If cracks are found in the vertical stabilizer side skin at the holes identified as A
and B in figure 2, or if the holes indicate working fasteners, then the holes
must be Eddy Current inspected for cracks in the spar caps. If no cracks are
found, continue with the Part I inspection,the airalsne is notto csntinue in senn~: contact Twin Commander Aircraft
Corp. prior to further flight.
NOTE:
Working rivets are usually indicated by blackldark coloring around rivet heads
andlor black steaks on outer surface of the skins around fasteners.
6. Inspect the following areas, both fore and aft, at station 409.56, where vertical
stabilizer attaches to horizontal stabilizer, for possible cracks/damage (refer to
Figure 1):
a. Area around bolt holes.
b. Upper and lower spar cap flange.
c. Station 409.56 bulkhead below horizontal spar, pay special attention to the
corner reliefs.
d. Horizontal spar web.
e Vertical stabilizer rear spar web, pay special attention to the joggle in the
spar web,
f. Aft clip (refer to Figures 1 and 2)
7. Cut a hole in the vertical stabilizer left hand side to accommodate the access
door, but do not install the door at this time (refer to Figure 2). Inspect for cracks
in the following areas through hole:
a. Around rivets that attach lower vertical stabilizer skin to ribs (refer to Figure
3).
b. Lower two ribs in the vertical stabilizer, pay special attention to the corner
reliefs.
c. Vertical stabilizer rear spar web, between the two lower ribs.
PAGE 6 OF 22
SERVICE BULLETIN NO. 218
ACCOMPLISHMENT INSTRUCTIONS: Part I, step 7 (cont’d)
d. The forward clip.
8. Inspect fairing fastener holes around access hole. Plug any fairing fastener
holes with less than .35 edge distance using MS20426AD4 rivets, flush both
sides. Install K410008-5 nutring per Figure 2. Acceptable to cut K410008-5
nutring approximately in half to simplify installation if desired.
9. If cracks/damage are found in steps 5, B, 7, then modify per Part II of this Service
Bulletin prior to further flight.CAUTION:
If cracks are beyond the limits shown in Figures 1 and 2, or if cracks intersect
resulting in loose or missing material, then the damage is not covered by this
service bulletin, lLamaged Darts_not covered bv_tbls seoricebulletin must be
realacebnran aooroved repair mustbemade Driorto comoletion of the
and return of thaa~licplanatP_saod?Ik
10. Inspect areas noted in steps 5, B, and 7 for sheared, working, or loose fasteners.
Replace fasteners as necessary.
NOTE:
Working rivets are usually indicated by blackldark coloring around rivet heads
andlor black streaks on outer surface of the skins around fasteners.
11. Inspect four bolts attaching vertical stabilizer to front spar of horizontal stabilizer
for installation of castellated nuts on bolts and washers under bolt heads (referto Figurel).
12. If there are castellated nuts installed and no washers under bolt heads, proceedas follows:
a. Remove existing cotter pins and check bolt torque. Torque to be 160 to 200
inch-pounds.
b. Assure that nuts can be secured properly with new MS24665-132 cotter pins(refer to Figure 4).
c. If nuts cannot be secured properly, remove nut, Install an additional
AN8600516 washer Imrt~nutPnly, reinstall existing nut and torque 160 to
200 inch-pounds by tightening nut to low side of torque range and, if
necessary, continue to tighten until a nut slot aligns with hole in bolt. Install
new MS24665-132 cotter pins.
13. If castellated nuts a~Pt installed, replace existing vertical stabilizer attach bolt
(4 places), one at a time. as follows (refer to Figure 1):
Dar~s 7 nE
SERVICE BVLLETIN NO. 218
ACCOMPLISHMENT INSTRUCTIONS: Part I, step 13(cont’d)
NOTE:
Do not have more than one bolt out at the same time,
a. Remove bolt and inspect bolt hole for possible damage.
b. If hole is not damaged, install AN5-6 bolt, ANBBODB1B washer undernut
only, and MS17825-5 nut. Torque bolt 180 to 200 inch-pounds by tighteningnut to low side of torque range and, if necessary, continue to tighten until a
nut slot aligns with hole in bolt. Install M524665-132 cotter pin (refer to
Figure 4).
NOTE:
An additional AN960DS16 washer may be installed under nut only, if necessary,
to assure proper alignment of hole in bolt with slots in nut.
c. If hole is damaged, it is acceptable to use ANBJ bolt (0.375"/0.370"diameter hole) only if an edge distance of 0.58 inches or more can be
maintained.
d. If it is determined, prior to reaming existing hole, that an edge distance of
0.58 inches or more cannot be maintained, contact Twin Commander Aircraft
Corporation for further instructions.
e. If it is determined, prior to reaming existing hole, that an edge distance of
0.56 inches or more can be maintained, ream damaged hole to
0.375"/0.379" diameter and install ANB-7 bolt, ANBBOD616 washer under nut
only and MS17825-6 nut. Torque bolt 300 to 330 inch-pounds by tighteningnut to low side of torque range and, if necessary, continue to tighten until a
nut slot aligns with hole in bolt. Install M524885-134 cotter pin (refer to
Figure 4).
NOTE:
An additional AN960D616 washer may be installed ImdBLIUbtPnly, if necessary,
to assure proper alignment of hole in bolt with slots in nut.
14. If there are castellated nuts installed and washers under bolt head, proceed as
follows:
a. Remove bolts affected, one at a time. and inspect bolt holes for possible
damage.NOTE:
Do not have more than one bolt out at the same time.
pnc,F R nF 37
SERVICE BVLLETIN NO. 218
ACCOMPLISHMENT INSTRUCTIONS: Part I, step 14 (cont’d)
b. If holes a~nnt damaged, reinstall existing AN5-6 bolt, AN860D518 washer
under nut only, and existing MS17825´•5 nut. Torque bolt to 180 to 200 inch-
pounds by tightening nut to low side of torque range and, if necessary,continue to tighten until a nut slot aligns with hole in bolt. Install new
MS24665-132 cotter pin (refer to figure 4).
NOTE:
An additional AN960D516 washer may be installed under nutsnlv if necessary,to assure proper alignment of hole on bolt with slots in nut.
c. If holes are damaged, it is acceptable to use AN6-7 bolt(0.375"/0.379"diameter hole)only if an edge distance of 0.58 inches or more can be maintained.
d. If it is determined, prior to reaming existing holes, that an edge distance of
0.56 inches or more cannot be maintained, contact Twin Commander Aircraft
Corporation for further instructions.
e. If it is determined, prior to reaming existing holes, that an edge distance of
0.58 inches or more can be maintained, ream damaged hole or holes to
0.375"10.379" diameter and install ANB-7 bolt, AN960DB16 washer imdar~t
MJY~ and MS17825-6 nut. Torque bolt 300 to 330 inch-pounds by tighteningnut to low side of torque range and, if necessary, continue to tighten until a
slot aligns with hole in bolt. install MS24665-134 cotter pin (refer to Fig. 4).
NOTE:
An additional AN980DB16 washer may be installed under nut only if necessary,to assure proper alignment of hole on bolt with slots in nut. The above listed
hardware is to be procured locally,
15. Make vertical-to-horizontal fairing removeable (refer to Figure 5).
a. Install MS27130-A19 and a20 rivnuts in every other fastener hole in
designated areas unless two adjacent holes were plugged in step 8. Use
-A1B rivnuts through thinner sections and a20 rivnuts through thicker
sections. If two adiacent holes are plugged, install rivnuts in fastener holes
on either side. In areas outside of designated areas, install rivnuts in all
fastener locations. Install rivnuts using Loctite 808 or equivalent. Excess
rivnuts may be discarded. Install fasteners in horizontal spar cap as noted in
Figure 5. Flush plug all other holes with "AD" rivets (salid or blind as reqd.)
CAUTION:
Use drill stops, steel shims, etc. as required to avoid damaging adjacentstructure while drilling rivnut holes. Penet install rivnuts thru vertical or
horizontal stabilizer spar caps.
panF~ CIF ~7
SERVICE BULLETIN NO. 218
ACCOMPLISHMENT INSTRUCTIONS: Part I, step 15(cont’d)
b. Flush plug holes in fairing that will not be used with MS20426AD4 rivets.
Open holes that will be used to diameter .218-.229. Bond R411N seal to
fairing using EC-1403 or EC-1300L adhesive.
c. Install fairing using two existing screws on forward edge and
MS27039DD1-09 screws and ANgBOPD1OL washers at all rivnut locations.
CAUTION:
Remove all aluminum shavings from the rudder and elevator roller chains.
Relubricate the chains par the applicable maintenance manual.
16. Reinstall left and right rudder control linkage access doon using existinghardware.
17. Reinstall SL 345 access panel or door in belly of fuselage using existinghardware.
18. Install K410008-3 access panel per figure 2 using NAS8603-2 screws.
19. Reinstall vertical-to-horirontal fairing (refer to Figure 5).
20. Touch up paint as necessary.
21. If no damage is found and if Part II is not completed at this time ahotocoov the
Compliance Card. Fill out and mail the Compliance Card copy to:
Twin Commander Aircraft Corp.19010 59th Drive NE
Arlington,WA 98223
NOTE:
Partial completion of Part II is not allowed, All the Part II modlncatlons (exceptstep 1 which is optional) must be completed at one time.
1. Optional to install kit number 58218-507, righthand access panel. The pads in
SB218-507 are opposite hand parts to the parts in SL 345. Refer to SL 345 for
installation instructions.
2. Remove rudder from vertical stabilizer per instructions in the applicable AirplaneMaintenance Manual.
3. Remove rudder torque tube per instructions in the applicable AirplaneMaintenance Manual.
on~e ~n ne
SERVICE BULLETIN NO. 218
ACCOMPLISHMENT INSTRUCTIONS: Part II (cont’d)
4. Following are instructions for modifying the aft spar web (refer to Figure 8).
a. If the aft spar web is within the crack limits allowed in figure 1, stop drill
crack ends with a 0.125" stop drill hole. Dye penetrant inspect to ensure
crack does not extend past stop drill.
CAUTION:
Do not stop drill into spar caps. Insert thin stainless steel shim stock between
web and spar cap to protect spar cap extrusion prior to stop drilling, ItslaLis not to return to service uotiLtLlgsBEIUrBiS
b. Touch up exposed surfaces with brush alodine and and zinc chromate as
required.
c. Install K410009-1 doubler, K410009-3 filler, K410009-5 angle, and
K410009-7 angle as shown in Figure 8.
5. Following are instructions for modifying the F.S. 409.56 bulkhead upper relief
cutouts and stiffening angle (refer to Figure 7).
a. Permissible to trim inboard edge of leading edge skin of horizontal stabilizer.
Maintain 20 edge margin.
b. If the bulkhead upper reliefs are within the crack limits allowed in figure 7,
stop drill crack ends with a 0.125" stop drill hole. Dye penetrant inspect to
ensure crack does not extend past stop drill.
c. Touch up exposed surfaces with brush alodine and zinc chromate as
required.
d. Install K310025-1 8 -2 straps, (2) K310025-3 fillers, K310025-5 8 -6
doublers, (2) K310025-7 fillers, and (2) K310025-9 straps as shown in
Figure 7.
Note:
~310025-1 8 -2 straps, (2) K310025-9 straps, and (2) K310025=7 fillers are not
required for models 690D and 695A
6. The following are instructions for modifying the lower vertical stabilizer side
skins. Refer to Figure 8.
a. If the side skin is cracked within the limits allowed in Figure 2, then stop drill
the ends of the cracks using a .125 diameter hole. Dye penetrant inspect to
ensure crack does not extend past stop drill.
onne ilncll
SERVICE BULLETIN NO. 218
ACCOMPLISHMENT INSTRUCTIONS: Part II, step 6 (cont’d)
b. Disconnect deicer boot pressurization lines through skins of vertical
stabilizer.
c. Remove and discard grommet.
d. Cut hole thru right side skin similar to hole shown in Figure 2. Hole is to be
same shape, same distance from existing structure but opposite, and same
size or smaller as hole on left side.
e. Pilot drill (2) K410008-1 lower skin doublers.
f. Mark the door and grommet holes on the K410008-1 doublers and carefullycut holes. Do not cut door in right side doubler.
g. Countersink the hole identified as "A" in Figure 8 .34/.38 X 100 degrees.Dimple holes "A" 8 "8" in the K410008-1 doublers.
h: Install (2) K410008-1 doublers, (2) K410008-7 straps, K410008-3 door, and
(2) MS35489-48 grommets per Figure 8. The K410008-1 doublers may be
trimmed on installation, maintain 2D edge distance.
i. Add (10) new fasteners each side to attach the vertical stabilizer side skin to
the forward leg of the vertical stabilizer rear spar cap. The fasteners to be
added are above the K410008-1 doublers.
Note:
Ten new fasteners each side are not required for models 690D and 696A. On
all other airplanes this area is difficult to inspect and the spar cap leg tapers.To locate these fasteners with proper edge distance it is recommended that a
straight line be drawn between existing rivets that attach the ribs above and
below this area to the spar caps. Locate the fasteners on the straight line at
1.00 inch pitch.
i. Reconnect deicer boot pressurization lines.
CAUTION:
Remove all aluminum shavings from the rudder and elevator roller chains.
Relubricate the chains per the applicable maintenance manual.
7. Reinstall vertical-to-horizontal fairing, access panels, torque tube, rudder, and
rudder hinge cover per applicable Airplane Maintenance Manual.
8. Cycle check deicer boot operation per the applicable Airplane Maintenance
Manual.
SERVICE BULLETIN NO. 218
ACCOMPLISHMENT INSTRUCTIONS: Part II (cont’d)
9. Touch-up paint as necessary and return aircraft to service.
10. Fill out and mail Compliance Card stating that Palt II of this Service Bulletin was
accomplished.
No change.
Part I: Not significant
Part II: Weight 5 poundsMoment/1000 2.25 in-lbs
SeABESBFFFECTED: No.
None.
BEL;PRD COMPLIA~E: Make an appropriate entry in airplane maintenancerecords as follows:
Part I of Service Bulletin 218, dated May 8, 1994, entitled "Empennage VerticalStabilizer inspection and Modification" accomplished: (date)
ORParts I and II of Service Bulletin 218, dated May 8, 1994, entitled "EmpennageVertical Stabilizer inspection and Modification" accomplished: (date~
PAGE 18 OF 22
SERVICE BULLETIN NO. 218
.75 INCH TYP MAXIMUM
CRACK LENGTH ALLOWED
VERT~CAL
IN WEB
STAB
SPAR WEB
VERTICAL
STABILIZER
AFT SPAR
INSPECT AREA
AROUND BOLT
HOLES AND RUOOER CONTROL LINKA(IEINSPECT FOR
PICCESS 0O0R IREFIFLANGES OFIN
SPAR CAPJOGGLE AREA
FOR CRACKSOF WEB
INSPECT FOR CRACKS
IN FWD AND AFT CLIPS
HORIZONTAL
STABILIZER
PRONTSFARboa ,(REFI
o oO
a. a a a o~ a
a aa a a,
a a O O a
a a,a oo
oo
O 05 O
o ~j n#es BOLT
a nNBaoDBls wns~ltl
a IUNDER NUT ONLYI.75 INCH
TYP MAX ~I D~MS~dBB&132 CDTFER PIN
Mn78P6 NUT
CRACKa a iOROUE 180 T1 2W IKLBS
LENGTH o
ALLOWED I4PLSIa
O o
IN WEB 8_ O a a O
oO 00 O
INSPECT BELOW
SP*R FOR CRPICKS
0000000
NOTE
\’IEW LOOK1NG FORWARD 00 NOT INSTALL I\NY W~SHERS
.T FUSELAGE STA. 409:56 UNDER HE~D OF BOLT
FIGURE 1
Page 14 of 22
SERVICE BULLETIN NO. 218
1-7
7" cl
I’ RUDDER HINGE
iCOVER
STnslLIZER RIB BELOWIREFI
Fan ~RncKs
INSPeCT FOR CRIICKI
~ROUND RIVETJ I\TT~CHINO
AIBSTO SKIN
FIOWE 3
Page 16 of 22
SERVICE BULLETIN NO. 218
I\DDITIONAL W/\SHER MIY BEUSED IF AEaUIRED TO ~LIGN’10LE iN BOLT WITH SLOT IN NUT ij
YIEW SHOWING INCDRRECT YIEN SHOWING CORRECTOF HOLE IN BOLT ILIONMENT OF HOLE IN BOLT
FIGURE 4
Page 17 of 22
SERVICE BULLETIN NO. 218
EX,ST,NG SK,N a
F.S. 409.56
BULKHEAD
K310025-9 STRAP 7 iiil
K310025-5
K310025-7 FILLER
K310025-1 STRAP" .01-.031~e /I
EXISTING FAIRING---~
FWD
VIEW AARLL MODELS EXCEPT 690D AND 695A
F. S. 409.56, 11
K310025-5
EXISTING FAIRING
jiFWD
vlEw AAMODELS 690D AND 695A ONLY
FIGORE 7
SHEET 2 OF 2
Page 21 of 22
COMPLIANCE CARD
Page 1 of 2
SERVICE BULLETIN NO. 218
EMPENNACIE VERTICAL STABILIZER INSPECTION AND MODIFICATION
PLEASE PILL IN THE REPUESTED INFORMATION AND CXECK THE
APPROPRIATE BOXES.
MODEL: AIRPLANE SERIAL NO. TOTAL TIME (AOURS)
AIRPLANE REGISTRATION NO. Airplane Age (YEARS)
OWNER NAME
ADDRESS
City State Zip
TELEPHONE NO.(
PART I INSPECTION
Vertical Stabilizer Skin:
i No damage found.
Crack(s) within S8218 limits.
I i Crack(s) exceeding SB218 limits.
Vertical Stabilizer Rear Spar Web:
No damage found.
i Crack(s) within 58218 limits.
Crack(s) exceeding SB218 limits.
Horizontal Stabilizer Spar Web:
i No damage found.
Crack(s) within SBZ18 limits.
i Crack(s) exceeding SB218 limits.
Forward and Aft Clips:
i No Damage found.
Crack(s) in forward clip.
Crack(s) in aft clip.
%s
COMPLIANCE CARD
Page 2 of 2
PART I INSPECTION, continued.
Vertical Stabilizer Ribs:
No damage found.
Crack(s) found.
Rivets, Hiloks, Hucks, and Lockbolts:
No missing or loose fasteners found.
Missing fastenerls). Where?
Loose fastener(s). WhereP
Bolt Holes which attach Vertical Horizontal Stabilizers:
No damage found, fasteners correctly installed.
Fastener(s) found incorrectly installed tie. missingwashers, missing cotter pins, etc.)
Crack(s) within SBals limits.
Crack(s) exceeding SB218 limits.
INSPECTED BY: TELEPHONE NO.(
DATE: SIGNATURE
EART I1: MODIFICATION:
Modifications determined not to be required at thistime.
Modified by:
TELEPHONE NO.(
ADDRESS
CITY STATE ZIP
DATE
SIGNATURE
21
-----MANDATORY
Se rvice Bulletin AIRCRAFT CORPORA TION(8010.58m Dr. NE, Adkgtm, WA Dllp37832
Ta: FsC (580) U51112
SERVICE BULLETIN NO.: 220 DATE: Februaryl, 1995
MANDATORY REDUCTION IN SPEED DURING TVRBULENCE
MODELS AFFECTED: MODEL 680T/680V, SERIAL NO. 1473 THRU 1720MODEL 680W. SERIAL NO. 1721 THRU 1850MODEL 681, SERIAL NO. 6(101 THRU 6072MODEL 690, SERIAL NO. 11001 THRU 11079MODEL 690A, SERIAL NO. 11100 THRU 11344
MODEL 6906, SERIAL NO. 11350 THRU 11566MODEL 8g0C, SERIAL NO. 11800 THRU 11735MODEL 890D, SERIAL NO. 15001 THRU 15042MODEL 695, SERIAL NO. 95000 THRU 95084
MODEL 695A, SERIAL NO. 96000 THRU 86100
MODEL 6956, SERIAL NO. 98201 THRU 96208 INIA
REASON FOR PUBLICATION:
There have been two accidents involving Model BgO senes aircraft resulting in loss of the aircraft, due to Dencountenng turbulence while descending at high airspeed. The purpose of this bulletin is to re-emphasize to
operators the importance of always reducing airspeed before starting descent or immediately upon experiencing Atu~ulence at any time.
Excessive airspeed in turbulence can cause structural damage or loss of the aircraft. Adverse gusts associated Owith turbulence cause an instantaneous increase in angle of attack. A sudden change in angle of attack producedby gusts creates increased loads which can lead to structuraldamage. Reducing airspeed reduces the effect of Rgust induced loads from turbulence. Maintaining airspeed at Turbulent Air Penetration or#aneuverlng YSpeed (hoth well below the red-line limits of Vnn01MIO)~ provides an increase in structural margin when
encountering turbulence. This is extremely impoRant if areas of forecast or reported turbulence cannot beavoided. or even in cruise Right, if turbulence is encountered. Since a finite period of time is required to reduceaircran speed from the onset of turbulence, a speed reduction should be accomplished in anticipation of suspectedturbulence areas, whenever possible. The need for additlonel airspeed matgin in descent arises because of theother unknowns introduced by descending from one air mass to another, and dmloulty of reducing speed whiledescending.
Operating the aircraft at Maneuvering Speed is the safest speed forfllght in turbulence. ManeuveringSpeeds are listed in the "Limitations" section of the AFMIPOH.
Specific guidance, including a Placarcl and AFMIPOH revisions is provided in this Service Bulletin to adviseoperators of ta~get speeds, as a function of night conditions.
PAGE I OP 5
RELATED PUBLICATIONS:
1. Service Bulletin 205, "VA Placard Installation", December 20, 1985. Issued to emphasize importance of robserving VA speeds. A waming placard was added to the instrument panel and a rev.ion was made tothe Airplane Flight Manual or Pilots Operating Handbook of the venous models of the 690 and 695 senesTwin Commander airplanes.
2. Airman’s Information Manual (AIM), ’7urbulence Reporting Criteria Table". Lists turbulence Intensity andaircraft reaction to vanous intensity levels. Copy included with this Service Bulletin.
COMPLIANCE:
Part I: (Order appropriate service kit) Upon receipt of this Service Bulletin.
Part II: (Install kit) Upon receipt of Service Bulletin Kit.
BY WHOM WORK WILL BE ACCOMPLISHED:
Owner/Operator. A&P Mechanic (or equivalent).
APPROVAL:
Engineenng design aspects are FAA approved.
ESTIMATED MAN HOURS: G
One hour,
PARTS INFORMATION:
Pads required to comply with this Service Bulle8n may be purchased from your nearest Twin Commander FactoryAuthorized Service Center under kit numbers listed below:
L(Ui~Le hdaPEL PLACARD Bn~e58220-1 660T 110205-1 Airplane Flight Manual 1558220-2 6B0V 110205-3 Airplane Flight Manual 1358220-3 B50W 110205-3 Airplane Flight Manual 1058220-4 881 110205-5 Airplane Flight Manual 1358220-5 690 110205-7 Airplane Flight Manual 25$82206 690A 110205-7 Airplane Flight Manual 32$8220-7 B908 110205-9 Pilots Operating Handbook 2458220-8 6g0C 110205-11 Pilafs Operating Handbook 2588220-9 6908 110205-13 Pilots Operating Handbook 1458220-10 685 110205-11 Pilots Operating Handbook 1558220-11 685A 110205-15 Pilots Operating Handbook 2488220-12 6958 110205-17 Pilot’s Operating Handbook 11
SPECIAL TOOLS: None. C
pAoe 2 OP S
ACCOMPLISHMENT INSTRUCTIONS:
I. Incorporate in the Airplane Flight Manual (AFM) or Pilot’s Operating Handbook (POH), the appropriaterenslon sent by Twin Commander as part of the Service Kit.
2. Attach the placard received from Twin Commander as part of Lhe Service Bulletin Kit on the windshieldcenterpost.
Mi( me anachsd C.mpllancs Cam. Se~Nre B.letb No. 220, t. Twin Commander*ircran
ELECTRICAL LOAD: No change.
SPARES AFFECTED: None.
WEIGHT AND BALANCE: No change.
PUBLICATIONS AFFECTED:
AFM or POH revision to include procedures for Flight in Moderate to Severe Turbulence and Recovery frominadvertent Overspeed and table of airspeeds for safe operation,
RECORD OF COMPLIANCE:
Make an entry in the airplane maintenance records as follows: SERVICE BULLETIN NO. 220, DATED(Oate, ENTITLED "MANDATORY REDUCTION IN SPEED DURING TURBULENCE. ACCOMPLISHED(Datel
COMPLIANCE CARD:
Upon completion of all actions required under Service Bulletin 220. complete the attached Compliance Card andmail (postage is prepaid) to Twin Commander Aircraft Carporation.
FACE 3 OF 5
TURBULENCE REPORTING CRITERIA TABLE
INSIDE REPORT(NOINTENSITY AIRCRAFT REACTION AIRCRAFT I TERM-DEFMITION
Turbulence that momentarily Occupants may feel Occasional-Less than 113causes slight, erratic changes in a slight nrrain against of the time.altitude and/or attitude (pitch, roil, seat belts or shoulderyawl. Report as Lieht Turbuience;´• straps. Unsecured Intermirtenr-113 to 2/3.
Lieht or objects may be displacedTurbulence that causes slight, rapid slightly. Food service Continuous-More that 2/3.and somewhat rhythmic bumpiness may be conducted andwithout appreciable changes in little or no difficultyaltitude or attitude. Report as is encountered in
LiPhr~hpn´• walking.
Turbulence that is similar to Light Occupants feel deiinite P~PTE.Turbulence but of greater intensity. mlinr against near belts
Changes in altitude and/or attitude or shoulder straps. I. Pilots rhould reportoccur bur the aircraft remains in Unsecured abjecrs are locarion(s), rime (UTC),positive control at all rimes. It dlsiodged. Food service intensitv, whether in or
usually causes variations in indicated and walking are difficult. near clouds, altitude,MPrlewll airspeed. Repon as Mpderate type of aircraft and,
rurbulence:’ when applicable,or duration of mrbulence.
Turbulence that is similar ra Lighf t2. Duration may be based
Chop but of greater intensity, on time between twoIt causes rapid bumps orjoltr locations or over awithout appreciable changes in single location. Allaircraft altitude or anirude. locations should beReport as MPd~ateChPp. readily identifiable.
EXAMPLES:
a. Over Omaha, 12322,Turbulence that causes large, Occupants are farced Moderate Turbuience.abrupt changes in altitude and/or violently against rear in cloud, Flight Levelamtude. It usually causes large belts or shoulder stmpp. 310, 8707.
SeYere variations in indicated airspeed. Unsecured objects are b. From 50 miles southAircrafl may be momentarily tossed about. Food of Albuquerque to 30out of control. Report an service and walking are miles north of Phoenix.Snura3CurbulenEe,´• impossible. 12102 to IZ~OZ,
occasional Moderate
Chop, Flight LevelTurbulence in which the aircraft 330, DC8.is violently tossed about and is
Extreme practically impossible to control.
It may cause srmctursl damage.Repan as Extreme Turbulence."
High level turbulence (normally above 15,000 feet ASL) not associated with cumuliformcloudinem, inciuding thunderstorms, should b~ rsponed as CAT (Clear Air Turbulence) ipreceded by the appropriate intensity, or light ormoderate chap.
PAGE 4 OF 5
COMPLIANC1~ RECORD
BULLETIN NO. 220
MANDATORY REDUCTION IN SPEED DURING TURBULENCE
MODEL: AIRPLANE SIN REG. NO._
TOTAL TIME IHOURS)
OWNER NAME:
ADDRESS:
TELEPHONE NO: AIRPLANE AGE:
COMPLIANCE WITH SERVICE BULLETIN 220.
DATE
WORK PERFORMED BY:
COMPANY
FAX
PA(IB 5 OF 5
SERVICE PUBLICATIONS ~"Y
revision notice A/RCRAFT~ T/ON(9010 19" Dr. N.e. n,llnssn, wa 8822~´•1812
ral: gee) 4Jse7sl pnx:(3(PJ dSB´•1HZ
Service Bulletin No. 223
Revision No. 2
Release Date: August 18, 1997
WING LEADING EDGE ATTACHMENT INSPECTION_AND MODIFICATION
REVISE KIT 58223-503 EFFECTIVITY
Change to read:
KIT NO. S8223´•503
Qty Part Number Description Model Eftectivitv
1 K17046717 LEFT BRACKET ALL 690C, 695, 6908, 695A,1 K170467-8 RIGHT BRACKET &6958
1 K170467-11 LEFT DOUBLER
1 K~7046712 RIGHT DOUBLER
1 FIBERGLASS CLOTH
SERVICE PUBUCATIONS ~r~"Y
C~MIIJILI, WLIEIP
revision notice A/RCRAF’I~CORPOR4 nON1P0(010’" O,. H.e. i\rlington. W*
r´•I: FaX: (560)
Sen/ice Bulletin No. 223
Revision No. 1
Release Date: May 8. 1997
WING LEADING EDGE ATTACHMENT INSPECTION AND MODIFICATION
REVISE BY WHOM. WORKWILL BE ACCOMPUSHED:
Change to read:
NOTE:
IT IS RECOMMENDED, BUT NOT REQUIRED, THAT THIS SERVICEBULLETIN BE COMPLETED BY AN AUTHORIZED TWIN COMMANDERSERVICE CENTER.
REVISE ACCOMPLISHMENT INSTRUCTIONS AS NOTED:
1. Revise Page 7 hole callout as follows:
.312 DIAMETER HOLEDRILL IN FAIRING ONLY
SEAL HOLE WITH SEALANT AFTER
DOOR INSTALLATION
2. Revise Page 11, Note 15 to read’FOR ALL MODELS EXCEPT 630D,695A, AND
6958, GO TO ITEM 17.
------MANDA 70RY
jlwrw~e rvice Bulletin COM~AIANDER
A IR CRA FT C ORPORA nON19110 5Rh Dr. NE. Allingtm. W~ OBPj~7832
Tal: 1360) U58197. Far (380) 4351(12
Service sulletin No. 223 Date: October 24, 1996
_WING LEADING EDGE ATTACHMENT INSPECTION AND MODIFICATION
EEE~LK: ~MeDLL NO.
500 SERIES AIC (500, 500A, 5008, 5008, 500U, 520, 560, 560A, 5608 and 560F)600 SERIES AIC (680, 6808, 680F, B80FL, 680FLP, 680FP, 6807, 680V, 680W,
681, 685, 690, 690~, 6908, 690C, 690D, B95, 695A and 6858)700 SERIES AIC (720)
Twin Commander Aircraft Corporation has received several tepo~s of aircraft with damaged leadingedge to fuselage attachment(s). These reports include: Cracks in the wing to fuselage attachmentbracket(s)/ strap(s), wing leading edge close-out(s), wing station 24.0 rib(a) and fuselage frame(s). Iflan unrepalred, this damage could propagate to the point of failure in the wing leading edge tofuselage attachment.
AThis Service Bulletin defines the requirements for inspection, modification and repair of these areas.Future inspections can be accomplished thru the added wing access door.. N
ID
PART I: MODIFICATION 8 INSPECTION AModels 520 8 560 are excluded from the wing leadingedge secess doon, and inspection per PART I I T
Provides Installation instructions for wing leading edge access doors. The access holes will provideO
adequate means for inspection of the wing leading edge to fuselage attachment area. The Initial Rinspection must be performed at or before total airframe time or within ifbeyond 690ehours. If no damage is found, the airplane may be returned to service and reinspected Yat intervals. If damage is found, PART II is required. After the access door has beeninstalled, inspection of the bracket(s) I strap(s) can be done thru this access door and removal of thefalrings is not required. If no damage is found and new bracket(s) I strap(s) an, installed through thewing leading edge access doors and the PART II inspection is not accomplished at that time, thePART II is required on or before the next 19PB_hP~. The reinspection of the new bracket(s) Istrap(s) will be required at 69Mdeurs and SE 223 inspections will be repeated as applicable fromthat time.
PARTII: INSPECTION& REPAIR
If damage is found during PART I, before further flight PART II (INSPECTION 8 REPAIR) must beperformed. After completion of PART II, PART I reinspection is required at 890ehour intervals for allareas, except as noted in PART III.
Medals 520 8 560 only, at or before 6.900 hours or within 1Pehnurs it beyond 5.000 hours, PART IIIINSPECTION g REPAIR) must be pe~ormed. PART II reinspection is required at 89Mbou1 interval.for all areas, except as noted in PART III.
Page 1 of 25
SERVICE BULLETIN NO. 223
COMPLIANCE: (cont.)
PART m: INSPECTION OF F.S. 144.0 (EXTENDED FUSELAGE) I F,S. 100.0 (SHORT FUSELAGE)(All models except, BgOC and B95 Reference Service Bulletin No. 213)
If PART 1l is not accomplished PART m must be complied with at 8.000 hours total airframe time for pressuri2edairplanes and 12.000 hours for unpressuriled airplanes with reinspection required at 1.000 hour intervals.
BY WHOM WORK WILL BE ACCOMPLISHED:
A 8 P MECHANIC (OR EQUIVALENT), AND A CERTIFIED NDT INSPECTOR (OR ECIUIVALENT) PERINSPECTION LIUALIFICATIONS.
NOTE:THIS MODIFICATION MUST BE COMPLETED ONLY BY AN AUTHORIZED TWIN COMMANDERSERVICE CENTER.
APPROVAL:
MODIFICATIONS AND REPAIRS DESCRIBED BY THIS SERVICE BULLETIN ARE FAA DER APPROVED.
RELATED PUBLICATIONS:
SE 112’INSPECTION OF WING RIB AT W.S. 24.07 FOR INSTALLATION OF RIVETS’: IT IS REQUIREDTHAT SE 112 BE ACCOMPLISHED AT THIS TIME.
SE 213 "WING FATIGUE INSPECTION AND MODIFICATION" IT IS RECOMMENDED THAT SE 213 BEACCOMPLISHED ON THE MODELS 8809 AND 885, IF PART n of TH1S SERVICE BULLETIN IS REOUIRED.
IF THE 12 OR 15 YEAR INSPECTION OF THE AIRPLANE 18 DUE, IT IS RECOMMENDED THAT THEINSPECTION BE ACCOMPLISHED IN CONJUNCTION WIM PART n of THIS SERVICE BULLETIN.
ESTIMATED MAN HOURS: (INCLUDING ACCESS PER SIDE
PART I:
WIND LEADIND EDGE ACCESS DOOR MODIFICATION 78 HRSINSPECT FORWARD ATTACH. BRACKET(S)/ STRAP(S) (FROM WIND ACCESS HOLE) 4 HRS
PARTI: i 82 HRS
PART n:
REPLACE FWD ATTACH. BRACKET(S) I STRAP(S) (FROM WING ACCESS HOLE) 3 HRSINSPECT WIND LEADING EDGE CLOSE-OUTS (FROM INSIDE 1171E WING) 22 HRSINSPECT W.S.24,0 UPR L LWR RETURN FLANGE RADIUS (FROM INSIDE THE WIND) 22 HRSINSPECT FUSELAGE FRAME WHERE tEE BRACKET ATTACHES (FROM INSIDE THEFUBELAOO 25 HRSINSPECT INBD SIDE OF WS. 24.0 ATTACH. BRACKET (FROM INSIDE ME FUSELAGE) 24 HRSINSPECT FRAME TEE BRACKET (SENCH INSPECTION) 4 HRS
PARTB: 3 108HRS
Page Z of 25
SERVICE BULLETIN NO. 221
ESTIMATED MAN HOURS: (cont.)
PART m:
REMOVAL OF AIRCRAFT INTERIOR FOR ACCESS TO FUSELAGE 100.0 144.0 FRAMES 6 HRSINSPECT FWD SIDE OF FUSELAGE FRAME WHERE TEE B~ACKET ATTACHES 1 HRS
PARTIII: 7 HRS
PARTS DATA:
PART I: ONING LEADING EDGE ACCESS DOOR KITS ONLY BOTH LEFT 8 RIGHT WINGS)
KIT NO. 58223501
PadP~umber OesodPlion Model Effectivity1 K170487-1 LEFT DOOR ALL 500, 600 AND 720 SERIES AIC1 K170487-2 RIGHT DOOR EXCEPT 520 580
1 Klj04b7-3 LEFT TEMPLATE1 K17D4b7-4 RIGHT TEMPLATE
1 K17048’1-5 LEFT DOUBLER
1 K170467-8 RIGHT DOUBLER28 NAS1088-A08 NL~PLATE
26 NASBB02-2 SCREWS
PARTII: (RfPAIRS BOTH LEFT AND RIGHT WINGS)
NOTE:THE FOLLOWING KITS WILL REPAIR DAMAGE 70 ONLY THE BRACKET(S)/ STRAP(S) THATATTACH THE WING LEADING EDGE CLOSE-OUT TO THE FUSELAGE FRAME AS SEEN THRU THEPART I ACCESS HOLES. FOR REPAIR OF DAMAGE FOUND IN OTHER AREAS, PARTS MUST BE
REPLACED OR AN APPROVED REPAIR MUST BE INSTALLED PRIOR TO RETURN TO SERVICE.
KIT NO. 88223-503
otv Part Number DegcriDtion Model Effec(lvilv1 K170487-7 LEFT BRACKET ALL 69OC, 695, B90D 5 6958
1 K170487´•8 RIGHT BRACKET 895A EXCEPT S~ 96083, 88, 89,1 K170487-11 LEFT DOUBLER 75, 78 5 85
1 K17MB7-12 RIGHT DOUBLER
1 MIL-Y-1140 FIBERGLASS CLOTH
KIT NO. 58223505
My P4LNvmber ~escrfdlon Model Effectlvnv1 K170487-8 LEFT BRACKET ALL 885, 6g0A 5 6808
1 K170467-10 RIGHT BRACKET 690, S/N 11041 ONLY
1 K170467-13 LEFT DOUBLER1 K170487-~4 RIGHT DOUBLER
1 MIL~-1140 FlBERGLASS CLOTH
KIT NO. 58223-50’1
ah Pad Number DesPdPtlon_
Modal Enectlvltv1 K170487-15 LEFT BRACKET ALL 880 EXCEPT S/N 11041
1 K178487-18 RIGHT BRACKET
1 K17W87-17 LEFT DOUBLER
1 K~70487-18 RIGHT DOUBLER
1 Mll´•Y-1140 FIBERGLASS CLOTH
Page 3 of 25
SERVICE BULLETIN NO. 223
PARTS DATA: (oont.)
KIT NO. 58223409
gtv Part Number DesclfPtlon ModelEffectivitv1 170052-5 LEFT UPPER STRAP ALL 880T, 680V, 680W a 6811 170052-6 RIGHT UPPER STRAP 880FL a 680FLP. SIN 1281 SUBCI.1 170052-7 LEFT LOWER STRAP
1 1’10052-8 RIGHT LOWER ST~AP-1 MILY-1140 FIBERGLASS CLOTH
KIT NO. 58223-811
1 170038-5 LEFT UPPER STRAP ALL 500,1 1700388 RIGHT UPPER STRAP ALL J60A, 5808. 580F a 7201 17003&P LEFT LOWER STRAP ALL 680, 6806, 880F a 680FP1 170038-8 RIGHT LOWER STRAP 680FL a 880FLP, S/N 1281 1280.
MIL-Y-1140 FIBERGLASS CLOTH
TO BE PROCURED LOCALLY: las required)
i. HL1BPBS/ -8 PIN, HL20P&5 Is PINS, HL86-51 -B COLLARS. HL94-5 /-B COLLARS, MSZ0470AD4. AD5
RIVETS, MS20426AD3, AD4 RIVETS, CR3242 AND CR3243 RIVETS.2. DESOTO 825-308 POLWRETHANE PRIMER USED FOR TOUCH UP ON PARTS FURNISHED WITH
TH1S KIT.
3. EC-1300L ADHESIVE (3M) OR EOUIVALENT.
4. M5212865 OROMMET.5. .60 INCH SPIRAL WRAP (ICORALLY CORP.)8. PR890A1R SEALANT
SPECIAL TOOLS:
NONE
INSPECTION RE9UIREM~NTS:
1. PERSONNEL OUALIFlCATIONS
a. Level Il Uquld Psnetrant
b. Vision acully requirements of MILSTM1OE, or latest revision.c. Documented trahlng in accordance with MIL-STM1OE, or latest revision and recommended practice
SNT-TC-1A Of the Amedean Society for Nondestructive Testing,
2. MATERIALS AND E(IVIPMENT
a. Solvent Cleaner, SKC´•NF (Magnenux) or equivalent per Mltl-25135.b. Water Washable Pluoreseent Penetrant. ZL60C. Level II (Magnanux) or equivalent per MIL-I-25135.c. Non-Aqueous Developer, SKD´•NF Flaenanux) per MIL-I-25135 or equivalent.d. 28-100 Blackllght (Magnanux). 10hv, 115v, 60Hr or equivalent.a. Inspection mlrmr.
f. Cleaner, Penetrant and Developerto he from the same manufacturer.
3. PROCESS
a. Per MIL-STaa8BB.b. Sensltlvlty- Type I. Method C, Level 3.
Pa(le~ of 26
SERVICE BULLETIN NO. 221
PART I -ACCOMPLISHMENT INSTRUCTIONS IM013IFIC~ION 8 INSPECTIONI
1. Disconnect baneries.
2. De-fuel airplane as outlined in the Airplane Maintenance Manual.
3. Protect aircraft fuselage and cabin windows directly forward and ah of the wing leading edge with an appropriatemedium. (See Figure i, far items 3 thru 8)
4. Remove upper wing skin access doom between Wing Station 24.0 and 38.0 ~bs, fomald of the Main Spar.
5. Push back the fuel cell located between Wing Station 24.0 and 38.0 ribs lomad of the Main Spar as outlined in
die Airplane Maintenance Manual.
CAUTION:
a) IF THE FUEL CELL IS NOT PUSHED BACK. REMOVAL OF THE FA1RINO FASTENERS MAY
DAMAGE THE FUEL CELL.
b) USE CARE IN REMOVING THE FAIRING ON PRESSURIZED AIRCRAFT SO THE PRESSURE SEAL,
WHICH MAY ADHERE TO THE FAIRING DUE TO EXCESS SEALANT, IS NOT DAMAGED.
NOTE:
FUEL CELL MUST BE DISCONNECTED AND REMOVED IF PART II OF THIS SERVICE BULLETIN IS
REOUIRED.
a. Cautiously drill out rivets and remove the fomarrl inboad left and right hand wing leading edge fairings.
7. If airplane is equipped with factory supplied inboard delcer or abrasion boots, remove locally.
a) Use Methyl Ethyl Ketone (MEK) or Toluol as a dissolving agent forthe adhesive used to adhere the boot to
the leading edge of the wing.
b) Loosen an inboard area olthe boot lame enough to grab hold of.
c) Pull the deioer boot while applying liberal solvent, with an even, steady pulling power until a 10 inch section
has been peeled outboa~d from the inboard edge.
d) Fold boot back and tape to wing.
CAUTION:
DO NOT RUSH, EXCESSIVE FORCE MAY CAUSE UNREPAIRABLE DAMAGE TO BOOT.
8. Clean excess sealer residue from wing leading edge with (MEK) and plastic scraper.
Page B of 25
SERVICE BULLETIN NO. 228
PART~I- ACCOMPLISHMENT INSTRUCTIONS (cont.)
PART I-ACCESS
PUSH BACK FUEL? r REYOM ACCESS EXEEsICELL (mM I) WOR (ITEM SEALER (mM LI)
REMOM FAIRING(IrrMB)
FUSELAGE(REF.)
REMOVE BOOT FOR(D.O INCHES (ITEM I)
I II II II I /C4
I
I I
PROTECT FUSELAGE/vro WINOOWS (ITEM S)
FOR BVBSTI’IUTE FASTENERSSEE PART I. (ITEM l8)
FIGURE1VINV LWKIN(I Am ~1NBOARD gJ WH WING LEADINCI EWE
LeeTWINOOPPOSm
8. Place the applicable K170487-3 -4 template on the wing leading edge with the inboalri lawar edge flush with the
wing skin (W.S. 24.0) inboa~ edge. Equal space the upper and lower edges between the existing inboard
outbaard civet lines. Mark ail fastener locations and the skin cut-out. If existing fasteners interfere, install hush
or double gush AD rivets as required. Pick-up existing rivets whets 2 x fastener diameter minimum edgedistance and 4 x fastener diameter m$imum pitch can be maintained. (See FiBure 2 or 2A for hems 8 thru 12)
CAUTION:
ON MODELS 690, A, B, C, D AND 696, A, B THE CONTROL CABLES ARE LOCATED DIRECTLY AFT OF
LEADING EDGE SKIN, W(ERCISE U(TREME CAUTION NOT TO CUT OR NICK CONTROL CABLES
10. Cut the leading edge skin to the inside doubler line. 00 NOT CUT ANY DEEPER THAN NECESGARYI It is
recommended that the tap inboad outboard cut be made first, then wt dorm one inch ham the outboa~ upper
comer. Bend the nap forward. Locate the engine aontml cables ton sppllcab* models) and move them to the
upper cut with safety wire, continue wtting the access hole.
11. Place the K170467-2 door snug an the wing leading edge skin with the inboard edge hush with the wins skin
inbaard edge. Equal space the door between pilot holes. Mad: amund the outside of the door. Maintain a
minimum of 2 x diameter edge distance (center of hole to edge of pert) an all fasteners. Remove the door end
make the final skin wt for a gush door installation.
Page 8 of 28
SERV1CE BULLETIN NO. 223
PART I-ACCOMPLISHMENT INSTRUCTIONS
12. Remove any excess sealer from famed sumce of wing leading edge attachment bracket(s) I strap(s).
13. inspect wing leading edge attachment bracket(o) or srrap(s) for cracks with special attention to the bend radius
and adjacent to rivets, using Fluorescent Penetrant Method. (See Figure 3, A, or B for applicable Models)
NOTE:
Close visual inspection is required, using Fluorescent penetrant method as an aid in disclosingcracls. Carefully remove sealants ornnishes as necessary in order to allow inspection of the
strunuralelemenle. Moderate hand pressures applied between parts, in order to produce anyrelative movement allowed, may assist in the detection of cmcks in parts or sheared or workingfasteners. Also, observe any rub marks indicating relative movement of parts under load.
Inspections refer to both left and right hand sides of the simama unless specified otherwise.
PART I´•INSPECT16N
INsPECT FOR CW\CKS (ITEM 13)IF CW\CKS ARE FOUND. PART 11 18 RE(IUIAED.
FINISH CUT IF NO CR~CKS *RE FOUND. CONTINUE WITH(REF) ITEM (5.
ENGINECONTROL REMOVE UCUSUBLECUT-OVTC*BLEs (REF.) SULER nIEH 12) MODELS seOC. (IBJ. seOD
O OO
OFUSEL90E(REF)
O I;1 10
O O O1 O
--L I
KODELS BeOh L18(la a
888 ~N HO(’I ONLY
(rrH iS)
mNe LEADING EWEHolE´• ATTACHMENTBR*CKST
IF cR*cKs *RE FOUND OH dNB aoe. MODELSBOTH LEFT a RIGHT BTUcKETS YUST
BIREPUCED. seo/l 8808. tiB(IC. IBS.(195A~L1958
FIOORE3 sea snr ONLY
VIEW LOOKING AFT a INBOARO 81 RM mNO L~V)INO EOiE
page B of 26
SERVICE BVLLETIN NO. 220
PART I-ACCOMPLISHMEN7 INSTRUCTIONS (cont.)
PART I-INSPECTION
INSPECT FOR CRACKS (ITEM 1J)IF CRACKS ARE FOUND. PART II IS REOUIRED.
FINISHCUT IF Nb CRACKS ARE FOUND. CONTINUE WlTHIREF.) ITEM le.
CONTROL REMOYE EXCESSC*sLss (REF.) SWER (ITEM 12)
O OO oV
oi FUSEV\OEO
(RIF.)I
0’o o
O O 0~o
U)h~ROLW\BLECUTOUTMODEL (iQO ONLY. EXCEPTSM 1(061
(ITEM iS)
WING LEADING EDGENOTE: hTTACHMEMsRACKET
IP CR*CKS*Re FOUND ON aNe SIDE. MODELSSOTlI LEFT L RIGHT BRACKETS MUST
BPIREPUCED. (iBO. EXCEPT S~ 1(M~
FIOORE3AVIEW LOOKING AF7 b INBOARD 69 RM WING WING EDGE
LEFTHANDOPPMITE
Pass 10 ar 21
SERVICE BULLETIN NO. 233
PART I-ACCOMPLISHMENT INSTRUCTIONS (cont.)
PART I-INSPECTION
FINISH CUT REMOVE EXCESS
(868.) SEALER (ITEM 12) ssoTNNV. SB1.S/N (181 SUB~.
INSPECT FOR CRACKS (ITEM 10)IF CRACKS ARE FOUND. PART 1118 REOUIREe. MODELS 5001AlslSN. (BO/WFIF Na CRACKS ARE FOUND. CONTINUE WITH BIIOMkP It~OFUFLP 9~ (?siITEM Iii. i i I 1 -1290 ONLY) MODELS ~20 a 1110
EXCLUDED
~O do
oUoo
FUSELAGEO(REF.I
O o o
(ITEM 13)
WING LEADING EDGENOn~ ATTACHMENTSTWIPB
IF CRACKS me Faum, ON aNE sOm
FIOURE38VINY LOCKING AFT a INBOAIO 80 wn WING LEADING EDGE
LEFTH~UIDOPWSITE
14. If no udcks are found in the wing leading edge attachment bracket(s)/ strap(s), continue with next step.
(F CRACKs ARE FOUND. COMPLIANCE WITH PART n is REQUIRED before con~lnuing with access door
installation.
15. Install wing leading edge acCessdoor modification pads as indicated. (Ses Figure 2 or 23 for applicable Medals)
FOR ALL MODELS U(CEPT 890D, 895A AND BBSB. GO TO ITEM 18.
Page 1( of 25
SERVICE BULLETIN NQ. 223
PART I-ACCOMPLISHMENT INSTRUCTIONS (cont.)
18. On mpdels 890D, 895A and 8958 series aircraft, inspectthe Wing Station 24.0 Ribs (fmrn inside the wing).
a) Inspect the rib radius for cracks one inch fomsd and one inch aft per Figure 4.
b) Inspect the rivet line at Fuselage Station 185.0 for cracks as shown per Figure 5.
NOTE:
IF CRACKS ARE FOUND IN THE RIB PARTS MUST SE REPLACED OR AN APPROVED REPAIR
MUST BE INSTALLED PRIOR TO RETURN TO SERVICE.
c) If no cracks are found, continue with ned hern.
PART I-INSPEC710N
UIOTINOMS1OI~AM
Qw.s.naonle(REF,1
’lmP02838R4CKET,,
,,I~, .II
(REF.) I j1703(7~(BANOLE
(R"’ /j!la -e
Y~ O 1111 (REF.)
OI i
-F
iOO
JII/iii
INSPECTfORCRICKSINLOWER RIB RAOIVS, ONE
INCH RVDI~FT OF U1SnNORNETLINE
FIOUREIVI~W LOWER RIB
Page 12 ct 28
SERVICE BULLETIN NO. 223
PART I-ACCOMPLISHMENT INSTRUC710NS (oant~rn´•
17. Sealant and Finishes must be reston,d per recommended Aircraft Maintenance Mamsl practices affer
modification and inspections are completed.
NOTE:
a) RESEAL CABIN WITH PR 8901\112 SEALER PER MIXING INSTRUCTIONS.
b) FOR LOCAL TOUCH UP ON EIXISTINO STRUCTURE, USE ZINC CHROMATE. DO NOT MIX
CHROMATE AND POLYURETHANE PRIMERS ON THE SAME PART. ALL NEW ALUMINUM PARTS
FROM TWIN COMMANDER ARE POLYURETHANE PRIMED.
18. Reinstall faidn8s. Existing cabin sealer may prevent reinstalling factory rivets at the lower faidng row. It is
acceptable to substitute CR3242 or CR3243 ilvets same size as removed for the existing factory rivals (SeeFigure 1)
19. Reinstall items removed Foam. Fuel Bags, Doon, Etc.
20. Pressure test the cabin for leaks per approved methods, for applicable models.
21. Resaal the deice boots perthe applicable Aircraft Maintenance Manual.
Page 13 of 26
SERVICE BULLETIN NO. 225
PART II-ACCOMPLISHMENT INSTRUCTIONS IINSPECTION& REPAIR)
The following areas are to be inspected using Fluorescent Penetrant Methods per Pan I, both left and right hand wing
1) Thru the upper wing skin aCcess door:
a) Remove sealant from all areas requiring inspection below.
b) Inspect for cracks in the bend radius of the wing leeding edge close-out, both upper and lower nanges.Inspect from the Wing Station 24.0 rib outboad for a minimum of B.O inches. (See Figure 5)
c) Some models have a vertical nange or angle that attaches the leading edge dose-out to the Wing Station
24.0 rib. Inspect for cracks in the nange or angle from top to bottom.
d) Inspect for cracks inlhe bend radius of the wing station 24.0 rib, both upper and lower nanges. Inspectfmm the wing leading edge closeout to the main spar caps.
e) inspect for cracks in between rivet lines and around beads of the Wing Station 24.0 rib. Inspect from the
wing leading edge closeout to the main soar caps.
PART II-INSPECTION
INSPECTFOR UPPERWINOSKIN(REF.)INBPECrFORcWIU(s
WINQLUV)INOEWE I cnEu 1, a
IN BEND RMIUs OF cA*CKs
CL08eOLIT(rrM D) o
INSPECT aLI.(XIINW
O
b~ob.%T~ a
Olj~ a
o~o oo___o__p o LIo o o
a
;OIJO/n I ’I wnG sanaNI.ORIB(REP.I
OI I OI OI I O
O I INSPECIFORCR4CISD D /o
o r(mM(, a)
ol I o ol I O
a a INspEcTponw\cnsIN BENo AM)IUGOF
a W.s. 2~.0 RIB (mM I, d)a
a
LE*oIMO eWE IUDSE*IUT(REF´•) I
neuow SE*UM
mr*l.´•)
LOWERWINOSKIHIREF.)
UP OacePrsemaseuRNEIMlnrro 7_ \o
FIQUREBYIRW LOOKING FORW*RD 6 INBO*RD do VH WING LUDING
EDGE CLOSE-OUT AND WING gRnM12~.0 R1BRI(IHTWDO~POSITE
Page 14 of 25
SERVICE BULLEalN NO. 223
PART II ACCOMPLISnMENT INSTRUCTIONS RNSPECTION REPAIRI (cont.)
2) From insldelhe fuselage:
a) Protect the inside surface of the cabin windows.
b) Remove the cabin interior in the area of the wing leading edge anachment.
c) On aircraft with Picture Windows, drill back the inner frame aluminum panels. (600 Figure a)
PART II-ACCESS
F.s. 144.0 (Ensnded Fuselsga) ORILlBACKINNERFR*ME
F.S. 1M.O (Sh.n Fuaalaga) ALUMINUM PANELS TO W\INACCBSSTOFmlNG8(ITEM 2 c)
LEADING EWE TO W.S. 24.0
RIBATTACNMENTF~INO(REF.)
Lr´•; DO
L
t~L.
pROrrCTINSIOESURWIAEOFCABINWINWWS
(ITEMZ.a)REINSTAIL FASTENERSPER PART II. (mM 4. b)
FIGURE 6VIEW LOOKING OVTBOARD e) Wn W.S. 24.0 RIe ATCACHMENT
FITTING ANO INNER FRAME ALUMINUM PANELSLEFT HAND OPWSISI
Page 16 of 26
SERVICE BULLeTIN NO. 225
PART II -ACCOMPLISHMENT IN~STRUCTIOFIS IINSPECTION B REPAIRI (cont.)
d) Remove the cabin sealant (mm the leading edge attachment nnlngs as indicated. (See Figure 7)
a) Remove the vertical tee bracket (822 Figure 7) from the aircraft.
O inspect for cracks in the vertical tee bracket.
g) Inspect for clacks in the forward side of the fuselage frame imm one inch above to one inch below where
the vertical tee bracket was removed end around the fastener holes from the ah side.
PART II´•INSPECTION
REMOVE BVILANT
(ITEM 2, 0)
1.00 O
I
o o
INOPECTFWIME IO
I
(ITEM 2. 1) I OO o oREINSTUL I
FABrrNERSPER PART II. I I O(ITEM 1. a) I O O
I OI
LEMINO EWE TOW.8. 2~.0 RIBATTACHMEM
1.00 O F~NG(RV.)
REMOVE AND INLIPECT
I MRTICAL TEE BRACKETI (ITELI 2. a)
FUSELADE FWUIE(REF.)
FMaURE 7VIEW UXZKING OLIT8OARD 6 FORWARO Q) R~ VUITIW TEE BRACKET
LEm HAND OPPOSITE
Palls IB ol 2fi
SERVICE BULLETIN NO. 223
PART II-ACCOMPLISHMEN7 INSTRVCTIONS IINSPECTION& REPAIR) (cont.)
hf inspect for cracks in the rib anachmeni wing leading edge to the Wing Station 24.0
db. (800 Figure 8). it is not required to inspect the ah vertical nange of this fitting.
PART II-INSPECTION
LEMINCI EODE rO w.s. 2´•.0
FUsEVIOE FRIMERls A1TACHMENT FITnNO (REF.)
(REF.)r w.s. 24.0 RIB (REF)
sPAUWT?,d) O
O
o ~o
..´•o o~Oo~l o
o I: oa o \JI
oci olo IOO h9. O o ol
oo oo o
INsPECT FOR CR*CKS
1N FISTING (ITEM 2, h)
AFSMRTICMFUNOE.NO IHSPECTION REOD.
FIGURE BVIEW LWI(INO OVTBOARD O WH W.S. 11.0 RIB ~TACHMENT FmlNG
LEFT H~NO OPPOSITE
3) If any damage is found in the above areas, parts must be replaced or an approved repair must be installed
p~or to retum to service.
4) If no damage is found, reinstall the parts removed.
a) For reinstalllnp the vertical tee bracket section to the fuselage frame and the rib attachment fitting, n is
acceptable to substitute HUOPBS -8 Pins (00010 size as removed) and HL865 -8 Collar for Factory
installed aluminum or steel lockbolts. If total hole cleanup cannot be obtained, n is acceptable to install
the 1184" oversired HLB4P&5 1 -8 Pin end nL87-5 /-g Collar. Solid rivets must be installed where
removed. Install the vertical tee bracket to the frame using a faylng surface seal (PR890A1R Sealer).
b) For nlndslllng the inner frame aluminum panels, It is acceptable to substitute ChenyMax blind fasteners
CR3243 for solid rivets per TCAC Custom Kit No. 144, item D.
Papa I~o(28
SERVICE! BULLETIN NO. 223
PART II AC_CqMPL!SHMENT INSTRVCTIONS nNSPECTION 8 REPAIR) (cod.)
5) Replacement ol the wine leading edge dose-out brscket(s)/ strap(s).
NOTE:
IF ONLY ONE BRACKET I STRAP IS DAMAGED, ALL MUST BE REPLACED, ON BOTH THE LEFT
AND RIGHT HAND WINGS. REPAIR PARTS ARE PROVIDED IN THE APPLICABLE KITS.
a) Drill off and remove the existing leading edge dcse-out bracket(s)/ ntting(r).
b) Select the applicable SB223-XXX Kit fmm the Pads Data Section.
c) Install the Kit perthe applicable Figure.
KIT NO. FIGURE PAGE MODEL EFFECTIVITY58223-503 8 18 ALL B9OC. 895, BgOD, BgSA 5 8858
58223-505 10 20 ALL 890A. 8808 5 890 S/N 11041
58223-507 11 21 ALL 890 EXCEPT SIN 11041
58223´•509 12 22 NOTED
58223-511 12 22 NOTED
Page 15 o( 25
SERVICE BUUETIN NO. 223
PART II-ACCOMPLISHMENT INSTRUCTIONS (INSPECTION 8 REPAIR) (cont.)
8) For applicable models, replace sealant as rembved fmm the lorwad edge of the W.S. 24.0 rib attachment Mtlngas per Part n. (Figure 7 8 8), see pmcedure below.
a) Cut 3 sections of fiberglass cloth far eacllside´• (total of 8 pieces) approximately 8 inches square (8 x 8).
b) Mix 1/2 cup (8 oz.) of 8B0A1/2 sealer and ha~dware per mixing instmctions and apply with a stiff bristle paintbrush.
c) Inside the cabin, coat the left 8 right W.S. 24.0 fitting, vertical tee bracket and adjacent wing mot areas. Placeone layer of fiberglass cloth on the wet sealer and form the cloth over the nttlng onto the tee, fuselage frameand wing mot fsidng in o~erto complete seal overthe wing leading edge root area. Stipple the cloth into thesealerwith the paint brush and fold the cloth where necessary in oder to make it lay down and adhere to thepads. For models with engine codml cables running thmugh the fitting. cut a slot in the cloth and form theedges of the cloth amund the cables as much as possible.
d) Allow at lea11/2 hour for the first application of sealer to harden, then mix 1 pint of 880A1R sealer and harden
per mixing instructions. Recoat the previously covered area. Lightly saturate the first layer of cloth with sealer.If there went~ly areas on the cloth fmm the first application, the entire area of the cloth can now be wetted.
a) Apply a second layer of nbemlass cloth on top of the first layer and stipple the cloth into the wet sealer until thesecond layer of cloth is saturated. Cut a slot in the cloth to form around control cables if necessary. Make surethe second layer of cloth overlaps onto the tee, frame and adjacent wing mot structue same as the first layer.
O it is not necessary to walt for the second application of sealer and cloth to harden before applying the third andfinal layers. Lay a ihild layer of cloth on top on the second layer. It may be necessary to recoat areas withadditional wet sealer in Mderta saturate the thld layer of cloth. Cut a slot for control cables if necessary.Small pieces of cloth can be added st this time to fill in gaps or to overlaploints in the cloth.
g) When nnlshed, the tree layers of fiberglass cloth saturated in sealer should form so airtight seal of the wingmot between the fitting and the closest fuselage structure. Clean up excess wet sealerwlth MEK or lacquerthinner.
7) Finish the installation of the 58223-501 Kit (See Figure 2 8 2A)
8) See Patt i, Items 17 thru 21.
PART iII: INSPECTION OF F,S. IEXT. FUSELAGEI I F.S, 100.0 ISHORT FUSELAGE)
1) Pmted the inside surface of the cabin windows with appmprlate medium.
2) Remove the cabin interior above the windows to gain access to the forward side ofthe frame.
3) inspect F.S. 144.0 (UCTENDED FUSEU\GO I F.S. 100.0 (SHORT FUSELAGE) frame, at the tee bracketattachment above W.L. 10 for cracks orfalled fasteners. inspect the forwarri side of the frame fmm one inchabove to one inch below the area where the tee bracket is installed, using the Flarescent Penetrant Method.
(See Figure 13)
Page 23 of 26
SERVICE BULLETIN NO. 223
PART III: INSPECTION OF F,S, 144.0 IEXT. PllsEU\aEII F.S, 100.0 ISHQRT FUSELAGE) (cont.)
CAUTION:
THE 144.0 FRAME IS TO BE INSPECTED THRU THE EXISTING INNER FRAME PANEL LIOHTENINO
HOLE FROM THE FORWARD SIDE ONLY.. DOINOT REMOVE THE FIBERGLASS CABIN PRESSURE
SEAL COVERING THE AFT SIDE OF THE FRAME AT THE TEE BRACKET.
NOTE:
IT 19 ACCEPTABLE TO DRILL OFF THE INNER FRAME PANEL TO REMOVE SEALER FROM THE
FORWARD SIDE OF THE 144.0 FRAME. DO NOT RESEAL THIS AREA. AFTER INSPECTION,
REINSTALL THE REMOVED INNER FRAME PANEL PER Psrt II, ITEM 4), b).
PART III´•INSPECnON
F.8. 10I.O(E*tsrdad FMsOa)F.S. Imo (s~od Fusslags)
INSPECS FOR CW\CK(I
NO INgPECSIONFROM
SIDEOFFW~ME
TEE BRACI(ETj jj i(RV~
YWTERUNE- ~o.m
VIEW A-A
FIOURE~SY1EWLOOKINO OUTBOARD O RIH BtOE
LEFTW\NDOPPOSITE
Pa~e 24 d 26
SERVICE BUUETIN NO. 223
PART III: INSPECTION OF F.S. 144.8 IEXT, FUSELAGE) IF.S. 1D~.O ISHORT FUSELAGEI (cont.)
4) Finishes must be restored per the recommended Airuan Maintenance Manual practices after inspection are
completed.
NOTE:
FOR LOCAL TOUCH UP ON EXISTING STRUCTURE, USE ZINC CHROMATE. DO NOT MIX
CHROMATE AND POLYVRETHANE PRIMERS ON THE SAME PART. ALL NEW ALUMINUM PARTS
FROM TWIN COMMANDER ARE POLYURETHANE PRIMED.
5) Reinstall all cabin interior panels.
Fill out the information an the Compliance Ca~d and send to:
Twin Commander Alrciaft CorporationService DepartmentPO Box 3369
Arlington, WA. 98223
ELECTRICAL LOAD:
No change
WEIGHT AND BALANCE:
No significant change
SPARES AFFECTED:
None
RECORD COMPLIANCE:
Make an appmp~ate entry in Airplane Maintenance Recods as follows: Service Bulletin No. 223, dated
240CTOBER1898, entitled ’WING LEADING EDGE ATTACHMENT INSPECTION AND MODIFICATION’,
compiled with as follows:
Pan I List inspection hems accomplished by item no., title, airplane total time, and date performed. If the
recommended modmcalion of the inspection hem listed has not been accomplished, list the next
scheduled inspection times to repeat inspdlon of the item.
pan n List modlflcaUons and inspection hems accomplished by drawing and dash no., tie, airplane total
time, and date perfoned.
Panm List modifications and inspections accomplished noting airplane total time end date performed.
Page 25 or 21
COMPUANCE CARD
Pzlpe~ o~Z
SERVICE BULLETIN NO. 223
WING LEADING EDGE ATTACHMENT INSPECTION 4ND MODIFICATION
MODEL: AIRCRAFT SERIAL NO. TOTAL AIC TIME (HRS)
AIRCRAFT REGISTRATION NO.
OWNER(S) NAME:
ADDRESS:CIP/ STATE ZIP CODE
TELEPHONE NO. AIRCRAFT AGE: C(EARS)
PART I(MODIFICATION (L INITIAL INSPECTION)
LIST INSPECTION ITEMS COMPLIED WITH BY ITEM NO.. TITLE. AND DATE OF COMPLIANCE. LIST
DETAILS ON ANY CRACKS OR DAMAGE FOUND.
INSPECTED BY: TELEPHONE NO.
DATE: SIGNATURE:
PART II (INSPECTION LL REPAIR)
LIST INSPECTION ITEMS COMPLIED WITH BY ITEM NO.. TITLE, AND DATE OF COMPLIANCE. LIST
DETAILS ON ANY CRACKS OR DAMAGE FOUND.
INSPECTED BY: TELEPHONE NO.
DATE: SIGNATURE:
h(p
COMPUANCE CARD
SERVICE BUUETIN NO. 223
WING LEADING EDGE ATTACnMEM INSPECTION AND MQDIFICATION
PART III(INSPECTION OF F.S. ~46.0 (EXT. FUSELAGE) I F.S. 100.0 (SHORT FUSELAGE)
LIST INSPECTION ITEMS COMPLIED WITH BY ITEMNO.. TITLE, AND DATE OF COMPLIANCE. LISTDETAILS ON ANY CRACKS OR DAMAGE FOUND.
INSPECTED BY: TELEPHONE NO. I
DATE: SIGNATURE:
TWINjCoMA~HANoERService Bulletin A IR CRAFT C ORPORA TION
PO. 3369 Arlinglon. Wa 3822]
~el: (360) 435-9797 ~ax: (3801 4i5-I:;1
Service Bulletin 224 rev C’
July 25, 1996
REPLACEMENT OF NOSE LANDING GEAR BOLT
EFFECTIVITY: This Service Bulletin applies to airplanes of the following models with the
following serial numbers: 5005:3185,3228.3230.3262,3291:500U:1765;680F:1195:
680V:1677:681:6027;690:11b35,11053,11068. 11074:690A:11111.11134. 11146.
11153,11173,11177,11205.11215,11237,11249,11271,11273,11282:6908:11360,11382,11409,11424 11451.11455, 11463,11491, 11513,11521,11535,11536.11539.
11566;690C:11638,11643.11689,11719;880D:15041;695:95010,95033.95044.95066:695A: 96010, 96041, 96056, 96061. IMREASON FOR PUBLICATION: Improperly heat-treated landing gear drag link bolts may Ahave been installed on these airplanes. I N
COMPLIANCE: It is mandatory, within the next 10 hours of operation, that the nose gear dragD
link bolt be replaced on those airplanes whose serial numbers are listed above.
BY WHOM WORK WILI BE ACCOMPLISHED: A P Mechanic or equivalent iTAPPROVAL: Technical aspects of this service bulletin are FAA approved. I o
ESTIMATED MAN HOURS: One hour I R
PARTS DATA: Nose landing gear drag link bolts part numbers 750076-1 (for models 6900 IYand 695A), and ED10055 (for models 690C and earlier) may be obtained from any factory-
authorized Twin Commander Service Center.
INSTRUCTIONS: Replace the bolt that attaches the forward end of the nose landing gear
drag link to the strut (see the pictures on the next page) with a new bolt obtained from any
factory-authorized Twin Commander Service Center. Follow the procedure in the airplane
maintenance manual for workingon the strut. Return the bolt that was removed to Twin
Commander´•
RECORD COMPLIANCE: Make an entry in the airplane maintenance records:
’Complied with SE 224C. Replaced nose gear bolt on date i with part number i".
Fill out and return the Compliance Record that is included in this Service Bulletin.
REIMBURSEMENT: See attached Compliance Record for details.
Revision A superseded theoriginal release of S.B. 224 and limited the effectivity to certain
serial numbers. Revision B added serial numbers 3228, 11074, 11249, 11491, 11521. 115aB.
95010.95066.96010.96041.96056.96061. 11643 was 11676. Rev C adds S/Ns 1677.
11153. 95044 and adds 750076-1 bolt for later models.
Page 1 of 2
Service Bulletin 224 c
BOLT 1750076-1
(for 6900 and 695A)ED10055
(for 690C and earlier)
´•69
Page 2 of 2
COMPLIANCE.RSCORD
SERVICE BULLETIN NO. 224C
REPLACEMENT OF NOSE LANDING GEAR BOLT
AIRPLANE MODEL SIN REG. NO. TOTAL TIME (HRS)
OWNER’S NAME
ADDRESS
TELEPHONE FAX
COMPLIANCE WITH SERVICE BULLETIN 224C:
TCAC WILL REIMBURSE OWNERIOPERATOR FOR THE PRICE OF THE BOLT. PIN 750076-1 OR ED10065,
(BY CREDIT MEMO THROUGH THE FACTORY-AUTHORIZED SERVICE CENTER WHERE THE BOLT WAS
PURCHASED) AND IF THE WORK IS PERFORMED BY A TCAC FACTORY-AUTHORIZED SERVICE
CENTER TCAC WILL PAY 550 FOR LABOR CONTINGENT UPON RECEIPT OF THE FOLLOWING:
1. THIS COMPLETED COMPLIANCE RECORD.
2. THE REPLACED BOLT.
9. COPY OF THE LOGBOOK ENTRY SHOWING RECORD OF INSTALLATION.
4. COPY OF RECEIPT OF PURCHASE DMTH PIN) FOR NEW BOLT FROM A
TCAC FACTORY-AUTHORIZED SERVICE CENTER.
5. THIS OFFER APPLIES ONLY TO COMPLIANCE WITH S.B. 224 REV C.
BOLT REPLACED ON I DATE)
PART NUMBER OF NEW BOLT~SERIAL NUMBER OF NEW BOLT
WORK PERFORMED BY (PRINTED)
(SIGNATURE)
COMPANY
ADDRESS
TELEPHONE FIV:
SERVICE PUBLICATIONS((f17AIWAULII~:IP
revision notice A/RCRAFT CORPORA T/ON19010 59’" DI. N.E.~rlin.ton. W~ 9822578J2
r.l: (180) 49(19197 45~-1’112
Service Bulletin No. 226
Revision No. 1
Release Date: July 15, 1997
FLAP SYSTEM INSPECTION
APPROVAL:
Engineering design aspects are FAA approved.
REVISE ESTIMATED MAN HOURS:
Change to read:
Part II: A. 1 Hour/Pulley(Rework)
B. 5 Hours/Side
REVISE SPE~AL TOOLS:
Change to read:
A gage is available at Twin Commander Aircraft Corporation Service Centers foruse in conducting the inspection: PN TOOL-S8226
IMANDATORY
Senrice Bulletin A/RCRAF~CORPORAT70N(8010 68’" O1. N.e. nrl..ton. WA 88883-1888
rtll: (3110) 411´•8181
SERVICE BULLETIN NO, 226 April 14, 1997
FLAP SYSTEM INSPECTIPN
MODELS AFFECTED:
All models of piston and turbine twin engine Twin Commanders except themodel 700.
REASON FOR PUBLICATION:
Twin Commander has received a report from the field of two flap pulleyassemblies with cable grooves that were found to be too narrow. There arethree pulley assemblies per side in all Twin Cammsndsrs except the Model Ib~700. The two pulleys were the right inboard (slave pulley) and the rightoutbaara sssemblis~. The inboard assembly was included in service Bulletin W210 which required inspection of the cable groove. This service bulletin willreplace SE 210 in its entirety and require inspection of all pulley assemblies Mon both left and right sides of the aircraft. Compliance with SE 210 does notreplace any requirements of this service bulletin. BPan I: Inspeclion of all flap system pulleys and cable aspemblisE. I w
Part II: Replacement or rework of any pulley assemblies as determinedb’OPart I inspection. Replacement of cables, support brackets, or clips
as determined by Part I inspedian. aPart ill: Identify pulleys complying with this service bulletin. Il v
COMPLIANCE:
Timing: Part I inspection shall occur within the next 100 hours of airplaneflight time.
Part I: A. Gage inspect all Rep system cable grooves. (Refer to Figure 1)
B. Inspect all flap pulleys for rubbing on the support brackets.
C. Inspect all flap pulley cables for frayed wires.
Part II: A. Mandatory pulley rework or replacement if cable grooves aretoo narrow.
Page 1 or 7
Service Bulletin No. 226
8. Mandatory replacement of cables if cable grooves are toonarrow or cables are frayed.
Part III: A. Permanent identification of all pulleys with the proper groove radius.
BY WHOM WORK WILL BE ACCOMPLISHED:
A P Mechanic (or equivalent)
APPROVAL:
Engineering design aspects are F.A.A. approved.
ESTIMATED MAN HOURS:
Part I: A. 16 hours (both sides)
8. 2 hours (both sides)
C. 4 hours (both sides)
Part II: A. 1 hour(rework per pulley), 2 hour (replace both sides)
8. 10 hours (both sides)
PARTS/REWORK INFORMATION:
Replacement Part Numbers can be obtained from the Twin Commander PartsCatalog for the model being inspected.
Pulley assemblies can, as an option to replacement, be reworked by TwinCommander Aircraft Corporation. Contact a Twin Commander Service Center orTwin Commander Aircraft Corporation for rework instructions.
SPECIAL TOOLS:
A special tool, part number 58228, to inspect the cable grooves is available fromTwin Commander.
ACCOMPLISHMENT INSTRUCTIONS:
Part I: A. Insert the gage marked ’A’ into each of the cable grooves in each ofthe 6 flap system pulleys. This checks for a cable groove that has a
bottom radius that is too narrow. If the gage does not contact thebottom of the groove (see figure 2), refer to Part II paragraphs A andD for corrective action. Recheck the cable grooves with the gage
Page 2 ol 7
Service Bulletin No. 226
marked ’B’. This checks for e~ble groove that has a bottom radiusthat is too wide. If the gage can be moved from side to side in thecable groove bottom radius (see figure 3), refer to Part II paragraphB for corrective action.
If the pulley cable grooves have the proper radius, refer to Part illformarking the pulley.
Any pulley cable grooves that are found to have an out of toleranceradius must either be destroyed, reworked or replaced.
B. Inspect each of the 6 flap system pulleys on both sides for signs of
rubbing against the upper or lower support brackets. Be especiallyalert for wear on the clips securing the cables. If worn clips or
support brackets are found, refer to Part II paragraph C for correctiveaction.
C. With a clean soft cloth, rub each flap system cable over its length. If
snags are found, inspect for broken wires. If broken wires are found,refer to Part II paragraph D for corrective action.
Part II: A. Replace any pulleys that have a cable groove bottom radius that istoo narrow. As an alternative to replacement, pulleys may bereworked by Twin Commander Aircraft Corporation. Contact a TwinCommander Service Center or Twin Commander Aircraft Corp. forrework instructions.
B. Replace any pulley that has a cable groove bottom radius that is toowide.
C. Replace any damaged support brackets and any worn clips.
D. Replace associated cable assembly when any pulley is replaced or
reworked for a cable groove bottom radius that is too narrow.
Replace any frayed cables.
Part III: A. Using a permanent marker, draw two(2) parallel lines on the pulleyvisible for future inspections indicating compliance with SE 226.
B. Reworked pulleys will be marked with ’SB 226’, the date of rework,and an inspection stamp.
ELECTRICAL LOAD: No change.
WEIGHT AND BALANCE: No change.
SPARES AFFECTED: Any spares found in inventory must be inspected perPart 1 and either scrapped or reworked.
Page 3 or 7
Service Bulletin No. 226
PUBLICA7I0NS AFFECTED: None.
RECORD COMPLIANCE:
Make an entry in the aircraft log book as follows:
Complied with Service Bulletin No. 226, dated April 14, 1997,entitled "Flap System Inspection".
Part I Accomplished: (Date) State results of the pulley and cable
inspections.Part II Accomplished: (Date) State which if any, pulleys were
replaced or reworked, and which cables were replaced.
Complete the information requested on the self addressed Compliance Card and returnto Twin Commander Aircraft Corp.
Page 4 of 7
Service Bulletin No. 226
+.007.064R~ .000
TYPICAL RADIUS ON
ALL CABLE GROOVES
FIGURE 1
Page 5 of 7
CD
Service Bulletin No. 226
Gage Can Be Rotated
SE 226 Gage
F9Cg
ReDlaee or Rework
Cable Groove Too Narrow Cable Groove
Within Tolerance
FIGURE 2
Page 6 or 7
Service Bulletin No. 226
Gage Can Be Rotated
SE 226 Gage
d
e3
Gape Can Be Moved
Side to Side Replace Pulley Cable Groove
Within TDleranee
FIGURE 3
Paae 7 a17
COMPLIANCE CARDSERVICE BULLETIN NO. 226
MODEL AIRCRAFT SERIAL NO. TOTAL AIC TIME (HRS)
AIRCRAFT REGISTRATION NO.
OWNER(S) NAME
Street P.O. BOX
CITY STATE ZIP CODE
TELEPHONE NO.:(
LIST RESULTS OF PULLEY GROOVE INSPECTION FOR EACH PULLEY.
*CCEPII\BLE
LEFTOUTBOARD 7]LEFT CENTER 17 C1 C1
LEFT INBOARD(MASTER) CI [7 7]
RIGHT OUTBOARD O O 7]
RIGHT CENTER O O 77
RIGHT INBOARD(SLAVE) O O O
INSPECTED BY TELEPHONE NO.:
DATE: SIGNATURE:
LIST ACTION TAKEN FOR OUT OF TOLERANCE PULLEY GROOVES.
REWORK REPLACE
PULLEY PULLEY
GROOVE
LEFT OUTBOARD C1 C7
LEFT CENTER I~ [7]LEFT INBOARD(MASTER) O [7
RIGHT OUTBOARD 73 C1
RIGHT CENTER O 7]
RIGHT INBOARD(SLAVE) D 7]
INSPECTED BY TELEPHONE NO.:
DATE: SIGNATURE:
MANDATORY
Sesvice Bulieiin ~´•rr~Y’Y
A/RCRAF)- CORPORA T/ON
11~10 611" D I. N.e. arllnolon, warot: IP101115´•)711 FaX: (3.0) ~31.(1(2
Service Bulletin No. 227 August 1, 1997
Insoection and Modification of Lower Main Gear Scissors
EFFECTIVIPI
All models of piston and turbine engine Twin Commanders except the model 700.
REASON FOR PUBLICATION:
Twin Commander has received reports from the field of interference between thelower main gear scissors and the upper portion of the main gear fork. The scissorswere redesigned from a machined forging to allow machining from plate material.This resulted in areas that were thicker than the forging since the new machined
part did not require draft angles. This interference occurs when the strut isextended and could result in failure of the scissor assembly causing loss ofdirectional control during landing. I FII
COMPLIANCE IA
Part I: Inspection loLeft and right main gear scissor assemblies must be inspected before the next I A
flight to determine if there is any interference between the scissor assembly and I Tthe main gear fork. I o
Part II: Modification I R.
If damage is found, the scissor must he modified before further flight.
BY WHOM WORK WILL BE ACCOMPLISHED
A 8 P Mechanic (or Equivalent),
APPROVAL:
DESIGN ASPECTS OF THIS BULLETIN ARE F.A.A. APPROVED
RELATED PUBLICATIONS:
None
Page 1 of _5_
Service Bulletin Na. 227
SSTIMATED ~N HPURS:
PART i:
Inspect left and right scissorslforks for damage 2.OHR(Both)
PART II:
Modify left end right scissor 2.0 HR(Both)Prime and paint left and right 1.0 HR (Both)
10 BE PROCURED LOCALLY:
1. DESOTO 825-309 Polyurethane primer (or Equivalent)2. Paint for touch up
SPECIAL TOOLS:
None
INSPECTION R~C\UIREMENTS:
1. Personnel Quaiifications
a) A&P Mechanic
PART I-ACCOMPLISHMENS INS7RVCTIONS (INSPECTION)
1. Refer to the Maintenance Manual and lack the airplane up to fully extend both maingear.
2. Inspect the area shown in Figure 1 for interference between the scissor and thegearfork.
3. If there is no inte~erence, no further action is required.
4. If interference is found, lower the aircraft to the ground, remove both scissorhalves (Vpper and Lower), and inspect the bushing holes in the scissors and forkfar damage. Replace damaged bushings, scissors or hardware as required.
5. Modify the lower scissor per Part II.
Page2o1_5_
Service Bulletin No. 227
PART II-ACCOMPLISHMENT INSTRUCTIONS IMOD1FICATION1
i. Verify whether the part is made from a forging or if it is machined from platematerial. The forging will have rounded edges in the nonmachined areas and theplate material will have sharp corners. If the part is a forging do not proceedbefore contacting Twin Commander Aircraft Corporation.
2. Remove material on the lower scissor in the area of interference being careful notto exceed the maximum allowable as shown in figure 2. Be sure to burnish anytool marks that may have occured in the area of material removal.
3. Prime and paint the area of removed material.
4. Reinstall the scissor halves. With the strut fully extended inspect for clearancebetween the scissor and the gear fork. If the scissors still interfere with the maingear fork, contact Twin Commander Aircraft Corporation before proceeding.
ELECTRICAL LOAD:
No Change
WEIGHT AND BALAN~
No Change
SPARES AFFECTED:
None
RECORD COMPLIANCE:
Make an entry in the aircraft log hook as follows:
Complied with Service Bulletin No. 227, dated August 1, 1997,entitled "lnspection and Modification of Lower Main Gear Scissors".
Complete the information requested on the self addressed Compliance Check Card andreturn to Twin Commander Aircraft Corp.
Pagelof_S_
Secvice Bullenn No. 227
MAIN GEAR STRUT
AREA OF INTERFERENCE
O
QII~
o
0~ MAIN GEAR STRUT
MAIN GEAR FORK
Figure 1
Paga´•ld_S_
Service Bulletin No.:227
View B
A
-r iS I-Atl 15
leSECTION A-A
Centerline of
scissor
-+t ;;Op.
.50R
Typ.V \/L-- ´•15
(Ref)
View B
PageSof_S_
COMPLIANCE RECORD
SERVICE BULLETIN NO. 227
INSPECTION AND MODIFICATION OF LOWER MAIN GEAR SCISSORS
MODEL AIRPLANE SIN REG. NO. TOTAL TIME (HOURS)
OWNER NAME
ADDRESS
TELEPHONE NO FAX NO
COMPLIANCE WITH SERVICE BULLETIN 227:
INTERFERENCE BETWEEN SCISSOR ASSEMBLY MAIN GEAR FORK FOUND?
YES O NO CII
IF YES, PLEASE GIVE DESCRIPTION OF INTERFERENCE AND A DESCRIPTION OF HOW
REPAIR WAS ACCOMPLISHED AND PARTS USED:
DATE
WORK PERFORMED BY (PRINTED)
(SIGNATVRE)
COMPANY
ADDRESS
TELEPHONE FAX
~WVDATORY
Sen/i~e BuI letin%LIW~WAUIIEIQA/RCRAFTCORPORAT70N18(110 58’D Dr. N.E. Arlington. WA 90229´•7832
rat: (Jao) 455´•8187 FAX: 1555) 451´•(112
SERVICE BULLETIN NO, 228 January 4, 1999
MODELS AFFECTED:
All models of piston and turbine twin engine Twin Commanders.
REASON FOR PUBLICATION:
Twin Commander has received a report from the field of nose gear steeringpins that did not have the required hole for a cotter pin. This service bulletin
provides the instructions to inspect, and if necessary, rework the pin.
Part I: Inspect and verify configuration of part.MA
Part II: Remove nose gear steen’ng pin and drill hole for cotter pin as shown.
NReinstall pin using castellatednut and cotter pin instead of lockingnut. ID
AcoMpLlaruce:
TTiming: Inspection and nnn~oit, if required, shall oocur wnhin the next O
100 hours of airplane flight time or at next annual inspection
(Whichever comes first). RY
BY WHOM WORK WILL BE ACCOMPLISHED:
A 8 P Mechanic (or equivalent)
APPROVAL:
Engineering design aspects are F.A.A. approved.
ESTIMATED MAN HOURS FOR REWORK:
4 hours
Page 1 of 5
Service Bulletin No. 228
PARTSIREWORK INEORMATION:
AN320-4 Nut or equivalent (Obtaln locally)MS24665-132 Cotter Pin or equivalent (Obtain locally)
Existing part may be reworked by an A 8 P Mechanic (or equivalent).
Replacement Part Numbers can be obtained from the Twin Commander Parts
Catalog for the model being inspected.
SPECIAL TOOLS:
No special tools are required for this Service Bulletin.
ACCOMPLISHMENT INSTRUCTIONS:
Part I: Locate the nose gear steering pin as shown on Figure 1. Determineif the pin is inst~illed with a castellated nut and cotter pin. If It Is, no
rework is required. If it is not, continue to Part II.
Part II: Remove the nose gear steering pin and discard the lock nut. Drill the
cotter pin hole as shown in Figure 2 using accepted shop practices.Reinstall the nose gear steering pin using a AN320-4 nut (orequivalent) and M524685-132 cotter pin (or equivalent).
ELECTRICAL LOAD: No change.
WEIQHT AND BALANCE: No change.
SPARES AFFECTED: Any spares found in inventory must be inspected perPart 1 and reworked if necessagl.
PUBLICATIONS AFFECTED: None.
RECORD COMPLIANCE:
Make an entry in the aircraft log book as follows:
Complied with Senice Bulietln No. 228, dated January 4, 1899,entitled "Nose Gear Steering Pin".
Accomplished: (Date) State whether or not the pin was modified.
Complete the information requested on the self addressed Compliance Card and retum
to Twin Commander Aircraft Corp.
Page 2 of 5
Service Bulletin No. 228
NITROGEN ~ND HYOAAULIC
FILLPORTVALVE
o\ I te~) I--BODY
PIN
oil iUPPER
CENTERING
IICoLLnR nssv
PISTON ROD
ORIFICE TVBE
CENTERING PIN
ATTACH BOLT
COLLAR
DOWN STOP ANo/ I ICo~dl I I BUSHINO
CINTERIN(I PIN
SCISSORANTISHIMMY II ‘YWI L/1 I I II II nspv
FRICTION
CYLINDER STEERIN(I CYLINDERBRACKET POINT
s~P a.alm.ouao
RING
SCISSOR BUSHIN(I
AVSY
Fl GU RE
Paae 3 of 5
Service Bulletin No. 228
750080-1
DRILL #48 .076 +.004/-.001 THRU
FIGURE 2
Page 4 of 5
COMPLIANCE CARD
SERVICE BULLETIN NO. 228
NOSE GEAR STEERING BOLT
MODEL_
AIRCRAFT SERIAL NO. TOTAL AIC TIME (HRS)
AIRCRAFT REGISTRATION NO.
OWNER(S) NAME
P.O. BOXStreet
CITY STATE ZIP CODE
TELEPHONE NO.:~)
DlD THE PIN NEED TO SE REWORKED? YES~ NO~
INSPECTED BY TELEPHONE NO.:
DATE: SIGNATURE:
COMPANY
ADDRESS
TELEPHONE FAX
ALERTZUIIAI
Service Bulletin %OIIIIMAU17;EIQA /RCRAF7- CORPORA T~ON
19010 59th Drive N.E. Arlington, WA. 98223Tel: (360)-435-9797 Fox: [360)-435-1112
Service Bulletin No, 233 Date: October 15, 2003
ENGINE NACELLE FIREWALL REINFORCEMENT
EFFECTIVITY: MODEL NO.
690C (Serial Numbers 11600 thru 11735)695 (Serial Numbers 95000 thru 95084)
REASON FOR PUBLICATION:
The above aircraft have experienced cracking indications in the aluminum and or stainless steel webs of
the engine firewall assembly at the aft engine mount location. The firewall assembly is built of
components consisting of a stainless steel fire shield (forward side) and formed aluminum bulkhead (aftside). The firewall cracks were found radiating from the fastener holes that secure the aft engine mount
to the firewall, and or along the upper radius of the bulkhead directly above the two upper mount holes.
COMPLIANCE:
INITIAL COMPLIANCE TIMES
CURRENT AIRFRAME COMPLIANCE REQUIRLED PRIOR TO (HOURS TIS)(HOURS/ TIME-IN- OR WITHIN THE NEXT [MONTHS] WHICHEVER COMES
FIRST
0000-1700 (2700) Hours or 136] Months
1701-2500 (3400) Hours or [36]Months2501-3000 (3800) Hours or [36] Months
3001-5000 (5500) Hours or (30]Months5001-6000 (6400) Hours or [24]Months6001-7500 (7800) Hours or [18]MonthsOver 7500 1 1121 Months
Tabk A
No inspections modifications are required before the expiration of the time period set forth in Table A
applicable to the airplane; however it is highly recommended that all of the inspections i modifications be
accomplished at the earliest practicable time. Firewall modifications per this Service Bulletin are
terminating action.
Page No. 1 of 9
SERVICE: BULLETIN NO. 233
BY WHOM WORK WILL BE ACCOMPLISHED:
A P Mechanic (or Equivalent), and An ASNT Level II Certified NDT Inspector (or Equivalent) per INSPECTIONQUALIFICATIONS.
NOTE:
IT IS RECOMMENDED THAT ALL MODIFICATIONS BE COMPLETED ONLY AT AN AUTHORIZEDTWIN COMMANDER SERVICE CENTER.
APPROVAL:
Modifications described by this Service Bulletin are FAA DER Approved.
ESTIMATED MAN HOURS: (INCLUDING ACCESS L 8 RH SIDES)
Inspection of firewall assembly forward (STEEL) and aft (ALUMINUM) bulkheads 32 HRS
Reinforcement modification of firewall assembly forward (STEEL), 32 HRS
aft (ALUMINUM) bulkheads and lower fire shield
Total Installation Time 64 HRS
PARTS DATA:
Kit parts required to comply with this Service Bulletin may be purchased through any of the nearest
TWIN COMMANDER FACTORY AUTHORIZED SERVICE CENTERS. Reference SE 233, aircraft model and
factory serial number when submitting order.
S~olied with modification kit:
TCAC DRAWING NO. 610681
TCAC PROCESS SPECIFICATIONS NO. 260.8
KITNO. SB233-1 (Left and Right Hand Engine Nacelle Firewall Reinforcement)
Parf Number
1 610681 DWG SE 233 ENGINE NACELLE REINFORCEMENT 610681-1
2 K660000-3 ANGLE
2 K660000-4 ANGLE
2 K660000-5 ANGLE
2 K660000-6 ANGLE
2 K660000-7 PLATE
2 K660000-9 CLIP
2 K660000-10 CLIP
1 K660000-11 ANGLE
1 K660000-12 ANGLE
1 K660000-13 ANGLE
1 K660000-14 ANGLE
Page No. 2 of 9
SERVICE BULLETIN NO. 233
PARTS DATA: (cont)
KIT NO. SB233-~ (Left and Right Hand Engine Nacelle Firewall Reinforcement)
1 I K660001-3 IDOUBLER
1 1 K660001-4 1 DOUBLER
2 1 K660001-5 1 RADIUS BLOCK
AIR MS20427M3 COUNTERSUNK HEAD MONEL SOLID RIVET
AIR I MS20427M4 COUNTERSUNK HEAD MONEL SOLID RIVET
AIR I MS20615M4 I PROTRUDING HEAD MONEL SOLID RIVET
A/R I MS20615M5 PROTRUDING HEAD MONEL SOLID RIVET
12 1 HL20PB6-6 I PIN
8 1 HL20PB6-8 I PIN
4 1 HL20PB6-10 I PIN
24 1 HL86PB6 I COLLAR
TO BE PROCURED LOCALLY: las required)
i. Polyurethane primer used for touch up on parts furnished with the Modification Kit. MIL-C-23377 per TCAC
Process Specification 30.8 or MIL-C-27725 TYPE II, CLASS A per TCAC Process Specification 30.6
SPECIAL TOOLS:
i. GO-NO-GO gages for HI-LOK fastener inspection
GENERAL INSPECTION CRITERIA:
TYPES OF INSPECTION FOUND IN THIS SERVICE BULLETIN PER AC 43.13-18 CHAPTER 5
"NONDESTRUCTIVE INSPECTION" (NDI).
Perform FLUORESCENT DYE PENETRANT structural inspection as an aid in disclosing crackingindications or other failures not detectable by visual means. Carefully remove sealant and I or finishes
as necessary in order to allow inspection of the structural elements. Moderate hand pressure appliedbetween parts, in order to produce any relative movement allowed, may assist in detection of failllie of
parts or joining fasteners. Also observe any rub marks indicating relative movement of parts under I´•iad.
SERVICE BULLETIN NO. 233
GENERAL INSPECTION CRITERIA: (cont.)
Areas to be inspected are identified by Part Number and I or Name and are located per the applicableINSPECTION FIGURE(S).
NOTE:
ILLUSTRATED PARTS CATALOG MAY BE USED FOR ASSISTANCE IN LOCATING INSPECTIONAREAS (REFERENCE ONLY)
INSPECTIONS APPLY TO LEFT AND RIGHT HAND AIRCRAFT ENGINE FIREWALLS
INSPECTION REQUIREMENTS:
i. PERSONNEL QUALIFICATIONS
a. Level II Liquid Penetrant.
b. Vision acuity requirements of MIL-STD-410E, or latest revision.
c. Documented training in accordance with MIL-STD-410E, or latest revision and recommended practiceSNT-TC-1A of the American Society for Nondestructive Testing.
2. MATERIALSAND EQUIPMENT
a. Solvent Cleaner, SKC-NF (Magnaflux) or equivalent per MIL-I-25135.
b. Water Washable Fluorescent Penetrant, ZL6OC, Level II (Magnaflux) or equivalent per MIL-I-25135.
c. Non-Aqueous Developer, SKD-NF (Magnaflux) per MIL-I-25135 or equivalent.d. ZB-100 Black light (Magnaflux), 100w, 115v, GDHz or equivalent.e. Inspection mirror.
f. Cleaner, Penetrant and Developer to be from the same manufacturer.
3. PROCESS
a. Per MIL-STD-6866.
b. Sensitivity- Type I, Method C, Level 3.
SERVICE BULLETIN NO. 233
ACCOMPLISHMENT INSTRUCTIONS:
1. Disconnect Batteries.
2. Secure and jack aircraft per Maintenance Manual.
3.; Bleed the air i nitrogen charge from the Main Landing Gear emergency extension system per the Aircraft
Maintenance Manual.
4. Remove upper and lower cowling shells from engine.
5. Remove engine oil cooler in accordance with the following procedures:Remove and cap engine oil lines from firewall fittings.Remove jam nuts from bulkhead fittings of oil cooler.
Remove oil cooler I firewall attachment fasteners immediately below hydraulic fittings (two total).Remove oil cooler fire detector probe and fasteners (three total) from forward side of the firewall.
Remove oil cooler door screws (37 total) and door.
Remove oil cooler by rotating aft end of cooler down and forward to clear landing gear.
6. Remove ejector assembly and exhaust pipe in accordance with the following procedures:Remove the (three) bolts attaching the ejector to the outboard skin of the nacelle,
(NOTE: Access to the bolts is from the inside of the nacelle, outboard of the landing gear.)Remove attaching screws from forward and aft ejector fairing.Remove fairing and ejector assembly, being careful not to damage exhaust pipe assembly.Loosen forward clamp and aft clamps from exhaust pipe and seal and remove.
Remove bolts that attach the exhaust pipe assembly to the engine (18 totalj.Remove exhaust pipe assembly from aft side of the firewall.
7. Disconnect the landing gear door linkage from the landing gear.
8. Remove the bolts from the hydraulic reservoir lower attachment to the nacelle (L/H SIDE ONLY).
9. Disconnect and cap the plumbing line from forward side of the emergency gear extension system gage
(LIH SIDE ONLY).
10. Remove the insulation from the bleed airline and elbow at the rear spar and separate the forward bleed
airline from the elbow. (NOTE: Secure aft end of bleed airline prior to nacelle removal.)
11. Remove the hydraulic plumbing clamp fasteners that are common to the upper aft nacelle bulkhead and the
lower aft nacelle bulkhead, if nacelle is equipped with clamshell doors.
12. Disconnect and cap plumbing lines and remove fittings that are common to the mating bulkheads, if so
equipped. (NOTE: Support the lower aft nacelle prior to proceeding.)
13. Remove the lower aft nacelle and firewall attachment bolts from the forward side of the firewall (16 total).
14. Remove the attachment bolts that secure the common bulkheads together (four upper and ten lower,
14 total places).
15. Drop down and support lower aft nacelle on appropriate material to prevent any damage.
16. Remove the landing gear bungee to permit the drag brace to be folded over center and to allow the gear to
rotate aft.
Page No. 5 of 9
SERVICE BULLETIN NO. 233
ACCOMPLISHMENT INSTRUCTIONS: (cont.)
17. With the gear clear of the lower aft nacelle, remove the nacelle.
18. Remove the engine controls support bracket from the aft top center location of the engine to allow access tothe aft engine mount and upper firewall.
19. Remove the aft engine mount link assembly from the firewall bracket and the engine attach point.
20. Disconnect the Prop. Sync. Actuator from the firewall to allow access to the forward side of the repair area
(R/H SIDE ONLY IF EQUIPED WITH WOODWARD TYPE 1 SYSTEM).
21. Remove aft engine mount firewall fitting and brace from forward side of firewall.
22. Remove sealer and primer and perform inspection for cracks at locations indicated per Figure #1 on both theforward stainless steel and aft aluminum engine nacelle firewall bulkheads.
23. If cracks are not present in either bulkhead, proceed with modification per item 26).
24. If cracks are present, and DO NOT extend inboard or outboard beyond the limits as indicated perNGURE stop drill the ends of cracks with .098 inch diameter bit (#40 drill). (CAUTION: Do not stop drill
through both the forward steel or aft aluminum bulkhead, insert steel shim stock material between firewallsto prevent damage during stop drilling procedures.)
25. DAMAGE LIMITS Modifications are only applicable if damage (if any) is within the following limits.
Maximum allowable crack length steel and I or aluminum bulkheads 1.75 INCH TYPICAL inboard and I
or outboard from the upper two engine mount attachment holes and along the upper bend radius of thebulkhead.
Maximum allowable crack length steel and I or aluminum bulkheads .90 INCH TYPICAL inboard and IOF outboard from the upper two (second row from top) engine mount attachment holes.
Maximum allowable crack length steel and I or aluminum bulkheads .50 INCH TYPICAL inboard and Ior outboard from the lower two engine mount attachment holes.
Page No. 6 of 9
MAXIMUM ALLOWABLE CRACK LENGTH---t~-.90 --I~ ~t-- 1.75 ---r+--MAXIMUM_ALLOW~BLE CRACK LENGT_HSTEEL AN D OR ALUMINUM BULKH EADS TYPICAL TYPICAL STEEL AND I OR ALUMINUM BULKHEADS
.90 INCH TYPICAL INBOARD AND OR I 1 ~7 1 i 1.75 INCH TYPICAL INBOARD AND OR
OUTBOARD FROM THE UPPER TWO (#2) 1 I I w.s. I OUTBOARD FROM THE UPPER TWO ~1)ENGINE MOUNT ATTACHMENT HOLES I I 91´•46 I I ENGINE MOUNT ATTACHMENT HOLES
AND ALONG THE UPPER BEND RADIUS
STOP DRILL ENDS OF CRACKS --7 1 I I I OF THE BULKHEAD
PER ACCOMPLISHMENT
INSTRUCTIONS, ITEM #24 1~7 O ~7 INSPECT FOR CRACKS IN THE FORWARDr STEEL AND AFT ALUMINUM FIREWALL
BULKHEAD ASSEMBLY ORIGINATING FROM
O /I I EXISTING FASTENER HOLES AND ALONG THE
UPPER BEND RADIUS OF THE BULKHEAD
i;, .I
II II _liII II I 1
1,1~11rl II
II V)a II I I I i I II m
mi II ii AO mm
I r~ II o
P 1r,, I~ II OJ o
ACCEPTABLE m
TYPICAL CRACKS mca I rT10~1 II II
b m O II IIII II c
Z Z C I 7;;o C]O
I I i I II FZ II III I 1 mV, III 13 11 (h II I
C7 m 71, 11up
4~ mII \LTl I
Z
u,I I I OUTED-tco O II ---r---
z
o~ oa cn II ii I
O cn c~;o II
u, mm I I uC3 II IIHOh II II cNOTE:m -T]\CL~ II IIr7 I- -II II THE AFT ENGINE MOUNT
II II BRACKETS MUST BEII I I I -I
REMOVED TO GAIN ACCESSIIII /zp TO THE FORWARD STEEL
110~ I 111 i I SIDE OF THE FIREWALLn II/ I I BULKHEAD ASSEMBLY
-I I FOR INSPECTION
PROCEDURES
MAXi..: JM A;ir3WABLE CRACK LENGTHS
F~REWALL
TYP.
ALLOWABLE DAMAGE LIMITS
j.50if CRACK I;USICATIONS ARE WITHIN THE MAXIMUM ALLOWABLE CRACK LENGTH
3.00 INCHES OUTBOARD
STEEL AND I OR ALUMINUM BULKHEADS
AS REFER TO TCAC .50 INCH TYPICAL INBOARD AND ORINSPECT BULKHEAD INSPECT BULKHEAD
b1068 i ASSY FOFZ OUTBOARD FROM THE LOWER TWO (#5)3.00 INCHES INBOARDMODIFI~ATION PROCEDURE ENGINE MOUNT ATTACHMENT HOLES
NOrr:
IF CRACK INDICATIONS EXTEND BE vOND
SPECIFIED LIMITS, DAMAGED PARTS MUST
BE REPLACED OR AN APPROVED REPAIR
INSTALLED
SERVICE BULLETIN NO. 233
ACCOMPLISHMENT INSTRUCTIONS: (cont.)
26. Remove field fasteners from the firewall assembly and stringer #2 as required to allow installation of
K660001-3 -4 doublers, K660001-5 radius block and K660000-7 plate as indicated per 610681-1 ASSY.
27. Locate, drill cleco K660001-3 1 -4 doubler on aft side of firewall assembly and K660000-7 plate on forwardside of firewall assembly and match drill parts to existing fastener locations.
28. Approximately 1.00 inch excess material has been left on the K660001-3 1 -4 doubler and K660001-5 radiusblock parts to allow optimum fit. Trim inboard and outboard ends of the parts as required to maintain a
minimum of 2 x fastener diameter edge distance.
29. Locate, drill 8 cieco K660000-3 1 -4 angles, K660000-5 1 -6 angles, K660000-9 -10 clips, K660000-11 1 -12
and K660000-13 j -14 angles as indicated.
30.Sealant and finishes must be restored per recommended Aircraft Maintenance Manual practices after
inspections I modifications are completed.
NOTE:
FOR LOCAL TOUCH UP ON EXISTING STRUCTURE, CHROMATE PRIMER MAY BE USED. DO
NOT MIX CHROMATE AND POLYURETHANE PRIMERS ON THE SAME PART. ALL NEW PARTS
SUPPLIED FROM TCAC ARE POLYURETHANE PRIMED.
31. Prime all bare surfaces and apply sealer per TCAC Process Specification 260.8, install above parts and
fasteners as indicated per 610681-1.
32. Reinstall, reconnect and service components addressed in items 3) thru 20).
Fill out information on the Compliance Card and send to:
TWIN COMMANDER AIRCRAFT CORPORATION
Attn.: SERVICE DEPARTMENT
19010 59’" DRIVE N. E.
ARLINGTON, WA. 98223
Page No. 8 of 9
SERVICE BULLETIN NO. 233
ELECTRICAL LOAD:
No change
WEIGHT AND BALANCE:
No significant change
SPARES AFFECTED:
None
RECORD COMPLIANCE:
Make an appropriate entry in the Aircraft Maintenance Records as follows: Service Bulletin Na. 233, Dated
OCTOBER ?5, 2003, entitled "ENGINE NACELLE FIREWALL REINFORCEMENT", has been accomplished on
(DA TE).
Page No. 9 of 9
COMPLIANCE CARD
SERVICE BULLETIN NO. 233
ENGINE NACELLE FIREWALL REINFORCEMENT
MODEL AIRPLANE S/N REG. NO. TOTAL TIME (Houns)
OWNER NAME
ADDRESS
TELEPHONE NO FAXNO
COMPLIANCE WITH SERVICE BULLETIN 233:
CRACKS FOUND: YES O NO O
IF YES, DESCRIPTION AND LOCATION OF CRACK(S):
DATE
WORK PERFORMED BY (PRINTED)
(S IGNATU RE)
COMPANY
ADDRESS
TELEPHONE FAX
(D
ALERT
Service Bulletinrrw~U
AIRCRAFT CORPORATION
SERVICE BULLETIN No. 235 DATE: April 16, 2003
UPPER RUDDER STRUCTURAL INSPECTION
1. MODELS AFFECTED Model 685 all serial numbers
Model 690 all serial numbers
Mode1690A all serial numbers"
Model 690B all serial numbers"
Model 690C all serial numbers
Model 690D all serial numbers
Model 695 all serial numbers
Model 695A all serial numbers
Model 695B all serial numbers
Note: all serial numbers are equipped with the fiberglass composite Rudder Tipall serial numbers are equipped with the aluminum Rudder Tip
2. REASON FOR PUBLICATION:
2.1 Paragraph 9 titled Part A of this Bulletin defines a one-time inspection of the fiberglasscomposite rudder tip (P/N 420092-501, -503) which is common to each of the 685, 690,
690A, and 690B models.
2.2 Paragraph 10 titled Part 1B of this Bulletin defines a one-time inspection of the
aluminum rudder tip (P/N 420156-all dashes) which is common to each of the 690C,
690D, 695, 695A, and 6958 models.
2.3 In two recent events involving Twin Commander 690B aircraft the fiberglass compositerudder tip appears to have departed the aircraft in flight. In one event, the aircraft landed
safely; in the second event, the aircraft was lost. Neither rudder cap has been located,
nor has a determination been made as to the cause of either event.
2.4 Reports from the field indicate that some composite rudder tips have sustained unusual
wear of the leading edge (erosion, pitting and cracking) which could result in an overall
weakening of the attendant structural assembly. Reports from the field also indicate
evidence of cracking in welds and fasteners holes of some aluminum rudder tips. In
addition, Twin Commander has received reports of some fiberglass or aluminum repairsaffecting the balancing of the rudder being accomplished without the requiredadjustment to the mass balance in accordance with the aircraft Maintenance Manual
paragraph on Control Surface Balancing.page 1 of 8
SERVICE BULLETIN 235
2.5 This Service Bulletin defines the requirements for inspection of the rudder tip and
attendant structure.
2.5.~ If any damage to the fiberglass composite Rudder Tip is found, replace the
damaged Tip with the aluminum Rudder Tip P/N 420156-511 (available from anyTwin Commander Aircraft Corporation approved Service Center) per Paragraph 11
of this Service Bulletin.
2.5.2 If damage beyond standard repair is found to the aluminum Rudder Tip, replacethe damaged Rudder Tip with the aluminum Tip P/N 420156-511 (available from
any Twin Commander Aircraft Corporation approved Service Center) per
Paragraph 11 of this Service Bulletin.
2.5.3 If damage is found to structural parts other than the Rudder Tip, request advice
from Twin Commander Aircraft Corporation as to the appropriate action.
3. COMPLIANCE: Within 25 hours or 90 days, whichever comes first.
4. BY WHOM WORK WILL BE ACCOMPLISHED: A 8 P Mechanic or equivalent
5. APPROVAL: Engineering Design Aspects are FAA approved.
6. ESTIMATED MAN-HOURS: 10 hours
7. SPECIAL TOOLS: None
8. INSPECTION METHODS: Close Visual Inspection unless preliminary findings call for further
inspection by another method.
9. PART 1A: INSPECTION INSTRUCTIONS: (Fiber~lass Composite Rudder Tip, see Fia 1)
9.1 Install Rudder Gust Lock on Rudder to line up Rudder with Vertical Stabilizer. Verifythe alignment of the leading edge of the Rudder Tip with the leading edge of the Vertical
Stabilizer. Misalignment would be indicative of structural damage.
9.2 Remove Rudder from aircraft per applicable Maintenance Manual.
9.3 Remove Rudder Tip and perform Inspection of the Rudder Tip. Check for:
9.3.1 Leading edge erosion evidenced by chips, cracks, missing paint, leadingedge delamination (Coin Tap Test)
9.3.2 Previous Leading edge repairs degrading the original strength of the
Rudder Tip (Coin Tap Test).9.3.3 Elongated holes at lower attach screws, missing countersink fairing
washers, cracks around holes and in sidewalls
9.3.4 Proper adhesion of the three vertical stiffener ribs
page 2 of 8
SERVICE BULLETIN 235
9.3.5 Existing damage due to excessive sanding or exposure to paint strippercaused by the paint preparation process
9.3.6 Inspect for loose fasteners on second vertical stiffener rib web at the lightflasher installation
9.3.7 Delamination or debonding of the trailing edge
9.4 Inspect top Rudder Rib (2 Parts, forward and aft of Rudder Spar).
9.4.1 Inspect top rudder rib forward of rudder spar for cracks. Pay particularattention to the bend radius of rib flange, flange joggle area, and the area
around fastener holes.
9.4.2 Inspect counter weight attachment fasteners to rib (tight, corrosion free,
safetied). Note findings.9.4.3 Remove and Inspect Counter Weight
9.4.3.1 Inspect attach area for corrosion
9.4.3.2 Inspect for proper hardware
9.4.3.3 Inspect for cracks at weight attach holes in rib
9.4.3.4 CAUTION: If counterweight has raised Part Number or letters on
lower surface (surface in contact with rib web), file raised numbers
flush to surface and inspect rib web for damage. Replace Fwd Rib if
required9.4.4 Inspect top rib to rudder spar interconnection area, including splice plate
between Fwd and Aft Rib. Watch for loose fasteners and cracks in
aluminum sheet metal.
9.4.5 Inspect top rudder rib aft of rudder spar for cracks. Pay particular attention
to the bend radius of rib flange, flange joggle area, and the area around
fastener holes.
9.5 Inspect Forward Rudder Spar as follows:
9.5.1 Inspect forward side of Rudder Spar for cracks around fastener holes and in
bend radius, paying particular attention to the Spar area between the topHinge and the Top Rudder Rib
9.5.2 Inspect upper part of the Rudder Spar above Top Rudder Rib, payingparticular attention to the area of the joggle in the spar flange just above the
Top Rudder Rib
9.5.3 Inspect Rudder Hinges and their fasteners
9.6 If no damage is found, reinstall Counterweight, Rudder Tip, and perform Balancing of the
Rudder per applicable Maintenance Manual.
9.7 Touch up paint as required and return aircraft to service.
page 3 of 8
SERVICE BULLETIN 235
10. PART 1B: INSPECTION INSTRUCTIONS: (Aluminum Rudder Tip, see Figure 2)
10.1 Install Rudder Gust Lock on Rudder to line up Rudder with Vertical Stabilizer. Verifythe alignment of the leading edge of the Rudder Tip with the leading edge of the Vertical
Stabilizer. Misalignment would be indicative of structural damage.
10.2 Remove Rudder from aircraft per applicable Maintenance Manual.
10.3 Remove Rudder Tip and perform Inspection of the Rudder Tip. Check for:
10.3.1 Leading edge erosion or damage10.3.2 Previous sheet metal repairs degrading the originalstrength of the Rudder
Tip (non-standard or undocumented repairs) and/or affecting the balance
of the rudder
10.3.3 Elongated holes at lower attach screws, missing countersink fairingwashers, cracks around holes and cracks in the weld joining both tip halves
10.3.4 Proper assembly of the 2 (two) vertical stiffener ribs (some are riveted,some are spot welded), no cracks in weld area or loose rivets
10.3.5 Existing damage due to excessive sanding during the paint preparation10.3.6 Inspect counter weight attachment fasteners to first stiffener rib (tight,
corrosion free, safetied). Note findings.10.3.7 Inspect for loose fasteners on second vertical stiffener rib web at the light
flasher installation
10.4 Inspect top Rudder Rib (2 Parts, fwd and aft of Rudder Spar).
10.4.1 Inspect top rudder rib forward of rudder spar for cracks. Pay particularattention to the bend radius of rib fiange, flange joggle area, and the area
around fastener holes.
10.4.2 Inspect top rib to rudder spar interconnection area, including splice platebetween Fwd and Aft Rib. Watch for loose fasteners and cracks in
aluminum sheet metal
10.4.3 Inspect top rudder rib aft of rudder spar for cracks. Pay particular attention
to the bend radius of rib flange, flange joggle area, and the area around
fastener holes
90.5 Inspect Forward Rudder Spar as follows:
10.5.1 Inspect forward side of Rudder Spar for cracks around fastener holes and in
bend radius, paying particular attention to the Spar area between the topHinge and the Top Rudder Rib
10.5.2 Inspect upper part of the Rudder Spar above Top Rudder Rib, payingparticular attention to the area of the joggle in the spar flange just above the
Top Rudder Rib
page 4 of 8
SERVICE BULLETIN 235
10.5.3 Inspect Rudder Hinges and their fasteners
10.6 If no damage is found, reinstall Counterweight, Rudder Tip, and perform Balancingof the Rudder per applicable Maintenance Manual.
10.7 Touch up paint as required and return aircraft to service.
11. PART 2: MODIFICATION:
11.1 Fiber~lass Composite Rudder Tip: If the existing composite Rudder Tip is found to
be damaged, it should be replaced with Kit Number SB235-1 which includes a
replacement Rudder Tip in Aluminum with Installation Instructions and requiredHardware.
11.2 Aluminum Rudder Tip: If the existing aluminum Rudder Tip is found to be damagedbeyond standard repair, it should be replaced with Kit Number SB235-2 which includes
an aluminum replacement Rudder Tip with Installation Instructions and requiredHardware.
12. ELECTRICAL LOAD: No Change
13. WEIGHT AND BALANCE: Negligible
14. PUBLICATIONS AFFECTED: I P C
15. RECORD OF COMPLIANCE:
Make an entry in the airplane maintenance record as follows:
SERVICE BULLETIN NO 235, DATED ,TITLED "UPPER RUDDER
STRUCTURAL INSPECTION", ACCOMPLISHED
16. COMPLIANCE CARD:
Upon completion of all actions required under Service Bulletin 235, complete the attached
Compliance Card and mail (postage is prepaid) or FAX to Twin Commander Aircraft Corp. at
(360)435-1112.page 5 of 8
SERVICE BULLETIN 235
FIGURE COMPOSITE RUDDER TIP
up
AFT TOP RUDDER RIB
SPLICE PLA
FWD
COUNTERWEIGHT
RUDDER TIP
FORWARD TOP RUDDER R1
TOP HINGEj
RUDDER SPAR I
page 6 of 8
SERVICE BULLETIN 235
FIGURE 2 ALUMINUM RUDDER TIP
FWD I AFT TOP RUDDER RIB
SPLICE PLA
COUNTERWEIGHT
RUDDER TIP
~´•3
FORWARD TOP RUDDER R
TOP HINGE
RUDDER SPARi
page 7 of 8
SERVICE BULLETIN 235
UPPER RUDDER STRUCTURAL INSPECTION
COMPLIANCE CARD (p]ease mail this card to Twin Commander at the address shown on
the other side, or fax it to 360-435-1112)
AIRCRAFT MODEL SERIAL NUMBER
AIRCRAFT REGISTRATION TOTAL TIME (HOURS)
OWNER’S NAME AND ADDRESS:
TELEPHONE: FAX:
PARTS REPLACED:
WORK PERFORMED BY (NAME AND COMPANY NAME AND ADDRESS):
TELEPHONE: FAX:
DATE: SIGNATURE:
page 8 of 8
SL
Aircraft Technical Publishers Customer Service
South Hill Drive 6AM-5PM PST M´•F
Brisbane, CA 94005 (800)227-4610
ATP Grid Index to Manufacturer’s Publications:
Twi n Commander A/C
695, 695A, 695B
SERVICE LE~TER
1) Applicable AD
2) Part Kit (1)
Issue Number 3) Part Kit (2)
Issue Date Issue Description 4) Compliance Time
332 ENGINE FIRE DETECTOR 1)
05/19/1980 RELOCATION 2)
3)
4)100 HR IN SV
333 ENVIRONMENTAL CONTROL UNIT 1)
05/19/1980 (ECU) PRESSURE SWITCH 2) P/N SKA1820
RECALIBRATION OR REPLACEMENT 3) P/N P10M-58
4) 100 HR IN SV
334A ELECTRIC START SYSTEM MODIFI- 1)
03/1611981 CATION AND STARTER-GENERATOR 2)SEE ISSUE
GROUND BUS BAR REPLACEMENT 3)
4) W/I 100 HRS
335 CIRCUIT BREAKER PANEL ASSEMBLY 1)
08/2811980 MODIFICATION 2)SEE ISSUE
3)
4) NEXT 100 HRS
337 ENGINE MOUNT BRACKET 1)
11/21/1980 MODIFICATION 2)
3)
4)SEE ISSUE
338A AFT FUSELAGE THERMOSTAT 1)
03/13/1981 INSTALLATION 2)SEE ISSUE
3)
4) W/I 100 HRS
04/04/2002 Copyright Aircraft Technical Publishers Page 1 of 6
GC 0853 SI SL
1) Applicable AD
2) Part Kit (1)
Issue Number 3) Part Kit (2)
Issue Date Issue Description 4) Compliance Time
339 BAGGAGE HEATER ANNUNCIATOR 1)
01/15/1981 LIGHT LENS REPLACEMENT 2) P/N ACR 11-3AL
3)
4)SEE ISSUE
340 INSTALLATION OF PLACARD FOR 1)
04/24/1981 USE OF ALTERNATE ENGINE OIL- 2)SEE ISSUE
ML-L-7808G 3)
4)SEE ISSUE
342 INSPECTION OF ENGINE MOUNT 1)
06/19/1981 CASTING BOLTS 2)SEE ISSUE
4)SEE ISSUE
343 HIGHER WATTAGE PITOT TUBES 1)
10/19/1981 2)SEE ISSUE
3)
4)SEE ISSUE
344 MAIN LANDING GEAR TORQUE LINK 1)
07/10/1981 SHAFT REPLACEMENT 2)SEE ISSUE
4)SEE ISSUE
345 R1 VERTICAL STABILIZER A~TACH 1)
05/21/1982 BOLT INSPECTION 2) SEE ISSUE
4)SEE ISSUE
346 R1 REPLACEMENT OF INNER 1)
06/23/1986 STRUCTURAL CABIN WINDOW GLASS 2)
3)
4)
347 REPLACEMENT OF INNER 1)
11/03/1981 STRUCTURAL CABIN WINDOW GLASS 2)SEE ISSUE
4) SEE ISSUE
04/04/2002 Copyright Aircraft Technical Publishers Page 2 of 6
GC 0853 SI SL
1) Applicable AD
2) Part Kit (1)
Issue Number 3) Part Kit (2)
Issue Date Issue Description 4) Compliance Time
349A ELEVATOR PUSH-PULL TUBE 1)
02/24/1984 ASSEMBLY INSPECTION AND 2)SEE ISSUE
REPLACEMENT 3)
4)SEE ISSUE
350 COCKPIT INSULATION OVERHEAD 1)
04/15/1982 SWITCH PANEL 2)SEE ISSUE
3)
4)SEE ISSUE
351 PARKER HANNIFIN CORPORATION 1)
06/17/1982 PRODUCT REFERENCE MEMO (PRM) 2) SEE ISSUE
NO. 27 3)
4) SEE ISSUE
352 FUEL CELL INTERCONNECT HOSE 1)
07/30/1982 REPLACEMENT 2) SEE ISSUE
3)
4)SEE ISSUE
353 FLIGHT CONTROL CHAIN CONNECTOR 1)
09/03/1982 LINK INSPECTION 2)SEE ISSUE
3)
4)SEE ISSUE
354 MAIN LANDING GEAR WHEEL 1)
10/01/1982 BEARING AND AXLE HOUSING 2)SEE ISSUE
INSPECTION 3)
4)SEE ISSUE
355 FUSELAGE STATION 386.82 SCREW 1)
11/30/1982 TORQUE INSPECTION 2) SEE ISSUE
3)
4) SEE ISSUE
356 PNEUMATIC TUBE ASSEMBLY 1)
02/25/1983 INSPECTION 2)SEE ISSUE
3)
4)SEE ISSUE
04/04/2002 Copyright Aircraft Technical Publishers Page 3 of 6
GC 0853 SI SL
1) Applicable AD
2) Part Kit (1)
Issue Number 3) Part Kit (2)
Issue Date Issue Description 4) Compliance Time
357A AILERON LEADING EDGE SKIN 1)
11/04/1983 MODIFICATION 2)SEE ISSUE
3)
4) 100 HR
358 TO ASSURE AUTOMATIC OXYGEN 1)
04/26/1983 MASK DEPLOYMENT 2) SEE ISSUE
3)
4) 100 HR
359 FUSELAGE STATION 386.82 FRAME 1)
06/17/1983 ASSEMBLY MODIFICATION 2)SEE ISSUE
3)
4) 100 HR
360 FLAP BRACKET INSPECTION 1)
08/01/1983 2)SEE ISSUE
3)
4)100 HR
361 TO ELIMINATE POSSIBLE 1)
11/04/1983 INTERFERENCE BETWEEN HYDRAULIC 2) SEE ISSUE
HODE ASSEMBLY AND ELECTRICAL 3)
WIRING 4) 100 HR
362 R1 INSPECTION AND/OR MODIFICATION 1)
05/02/ 1984 OF OBSERVER SEAT SHOULDER 2)
HARNESS STRUCTURE 3)
4)
363 FUEL DRAIN SYSTEM INSPECTION 1)
11/01/1983 2) SEE ISSUE
3)
4)SEE ISSUE
364 SERIES MODE ANNUNCIATOR LIGHT 1)
11/18/1983 TAPE REPLACEMENT 2)TC5003
3)
4)100 HR
04/04/2002 Copyright Aircraft Technical Publishers Page 4 of 6
GC 0853 SI SL
1) Applicable AD
2) Part Kit (1)
Issue Number 3) Part Kit (2)
Issue Date Issue Description 4) Compliance Time
365 FUEL BOOST PUMP REPLACEMENT 1)
02/03/1984 2)SEE ISSUE
4)100 HRS
366A NOSE LANDING GEAR DRAG LINK 1)
03/22/1985 SUPPORT STRUCTURE MODIFICATION 2)SEE ISSUE
3)
4)SEE ISSUE
367 PARKER HANNIFIN CORP. PRODUCT 1)
01/04/1985 REFERENCE MEMO (PRM) NO.36 2)199-13000
(REV.A) (30-107 AND 30-1078 3)
BRAKE ASSEMBLIES) 4) SEE ISSUE
368 HEAVY DUTY NOSE LANDING GEAR 1)
01/04/1985 SPACER ASSEMBLY 2)SEE ISSUE
3)
4)SEE ISSUE
369 LANDING GEAR CONTROL ASSEMBLY 1)
01/11/1985 LUBRICATION 2)
3)
4)SEE ISSUE
370 FREON AIR CONDITIONER 1)
10/04/1985 COMPRESSOR BELT COVER ASSEMBLY 2) SEE ISSUE
INSTALLATION 3)
4) 100 HRS.
371 EXPAND TEMPERATURE RANGE OF 1)
04/24/1989 ENVIRO SYSTEM IN AUTO MODE 2) SEE ISSUE
3)
4) OPTIONAL
372 ENVIRO SYSTEM AMBIENT VALVE 1)
10/12/1989 REPLACEMENT 2)SEE ISSUE
3)
4)SEE ISSUE
04/04/2002 Copyright Aircraft Technical Publishers Page 5 of 6
GC 0853 SI SL
1) Applicable AD
2) Part Kit (1)
Issue Number 3) Part Kit (2)
Issue Date Issue Description 4) Compliance Time
376 Inspection of main landing 1)
04/25/2000 gear clevis and drag brace 2) ED12758
installations 3) ED12526
4) Recommended
End of Index
04/04/2002 Copyright Aircraft Technical Publishers Page 6 of 6
GC 0853 SI SL
Service Letter Rockwell intemanonal
on~n,n*anomh
sml il*ma
SERVICE LETTER NO. 552
18 May 1881)
ENGINE FIRE DETECTOR RELOCATION
MODELS AFFECTED: MODEL BBOC, SERIAL NO’S 11800 THRU 11825 AND MODEL 085,SERIAL NO’S 85000 THRU 85005.
REASON FOR PUBLICATION: TO PREVENT POSSIBLE INTERFERENCE BETWEEN FIRE DETECTOR
AND LIP OF COWLINO AIR E]OT.
COMPLIANCE: WITH[N NEXT 100-HOURS TIME IN SERVICE.
*011
IF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYINGWITH
THIS SERVICE LETTER, CONTACT YOUR NEAREST ROCKWELL
COMMANDER AIPPHORIZED SERVICE FACILITY.
BY WHOM WORK WILL BE ACCOMPLISHED: A P MECHANIC OR EPUIVALENT.
APPROVAL: FAA DOA 8W-a Approved.
ESTIMATED MAN HOURS: ONE (1) HOUR.
PARTS DATA: 1 as. Compliance Card
SPECIAL NONE.
ACCOMPLISHMENT INSTRUCTIONS:
1. Remove upper ca-uling irom left and right engines.
2. Inspect air e~dl lip an ellglne oowllng and pt~ end of engine tire detector fcr any signs oi abrasion due
to interierenoe between fire detector and cowiing air e~dt lip.
3. Inspect for location ci Up d tire detector at tbe co~ullng air sdt.
*OTI
There should be a minimum clearance of 0.12-inch between air edt
Up and att end of fire detector.
4. 1l interierence or mmslocatlon I the airstream is evident, loosen clamps Ottachirg engine fire detectors
to upper strulaassmblles, relocate tire detectors and tighten clamps (see Figure 1,).
5. Relnstsll upper oaull~ on left and right engines.
8. Fill wt and mail Compllanoe Card.
ELECTRICAL LOAD: NO CHANGE.
WEIGHT AND BALANCE: NO CHANGE.
8FARES AFFECTED: NO.
PUBLICATIONS AFFECTED: NONE.
RECORD COMPLIANCE: Make an appropl?ate entry in airplane maintenance records as IoHows: Service
Letter No. 852, dated is May 1850, entitled "Engine Fire Detector Relocation", accomplished (date)
psp~lola
SERVICE LEITER NO. 592
yppeR COWLWO (REE)
CowLnro AIR
E~OTDUCT
~EF)
L _L$kJ1
*aTr
ENBURE A ~UM CLEARANCE OF
O.la-WCB BETWEEN FIRE DETECTORAND COWLWO AIR EXIT DUCT.
~FWD
F1RE DETECTOR ~EF)
f;
L -L BU-J1
UPPER STRUT A88Y ~EF)
TYPICAL INSTALLATION
Flsue 1.
Page a ol 2
COMPLIANCE CARD
From:
Service Bulletin No. 174 PARTIJ
Aimraft S/N
Complied with: Dare
Propeller (Mub) S/N: Left
Blade SIN
Propeller (Hub) S/N: Right
Blade S/N
Time on each propeller: Left Right
Complied with by:
Signaturerco ~r´•aol
osnaal ~risaon oaslon
SW1 Nonh Roctwsll Avsnu~
Belhany.OK73W81405)lsB´•M00
rwx: sla-B3o-ea7o RockwellInternational
May 15 1980 Reference 80 RDL 10 36 pdj
Dear Owner:
Service Letter Number 333 is attached for your information
and action,
Due to temporary availability difficulties, the P10M-58,
pressure switches, are extremely hard to come by.
Be request that you make every effort to comply with part
1 of this service letter, recalibration rather than
replacement, in order to help us through this difficulty.
Sincerely,
RDCKWELL INTEILNATIONAL
AVIATION DIVISION
R,Ron Laurence
ManagerCustomer Service
RDL:pdj
Attachment
Service Letter Rockwell intemsnonal
onnluwononw~nsml N~nh *nnu
8ERVICE LETTER NO. 999
18 May 1880
ENVIRONMENTAL CONTROL UNIT (ECU) PRESSURE SWITCH
RECALIBRATION OR REPLACEMENT
lEoTg
TIES SERVICE LETTER PROVIDES INSTRUCTIONS FOR RECALI-
BRATWO EXISTING P1OM-SS ECU PRESSURE S~TCH OR INBTALL-
nNG A NEW PRESSURE SWITCH (P/N P10M-68) TO A NEW PRESSURE
SETIING RECOMMENDED BY RMCKWELL INTERNATIONAL.
MODELS AFFECTED: MODEL 880C, 8ERVLL NO’S 11800 THRU 11890 AND MODEL 886,SERIAL NO’S 86001 THRU 85010.
REALXIN mR PUBLICA1?ON: TO PROVIDE A PRESSLIRE INDICATION FOR ENVIRONMENTAL
CONTROL UNIT PRESSURE REGULATOR WITH PRESSURE SETTING
DEVEU)PED TO ASSURE THAT "ECU PRESS" LIGHT ILLUMINATES
SHOULD AN OVERPRESSURE CONDITION OCCUR.
COMPLIANCE: WITHIN NEXT 100-HOURSTIME IN SERVICE.
98018
i IF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYING WITH
THIS SERVICE LETTER, CONTACT YOUR NEAREST ROCKWELL
COMMANDER AUTHORIZED SERVICE FACILITY.
BYWHOM WORKWILL BE ACCOMPLISHED: A PMECHANIC OR EC~UIVALENT.
APPROVAL: FAA DOA 8W-2 Approved.
ESTIMATED MAN HOURS: PARTI RECALIBRATESWITCH TWO(I)HOURS.
PARTII REPLACESWITCH ONE (1)HOUR.
PARTS DATA: Parts required to comply with Part I of this Service Letter may be procured through your
nearest Rocksell Commander Authorleed Service Facility at no charge. Parts required for Part 1l may be
pracured for $141.80 and a credit of $141.80 will ire issued upon receipt of old pressure switch P/N P10M-SS,a properly executed Warranty CIaim and a Compllmce Card. Rsfsrenee this 8erlce Letter, aircraft model
and laCtory seriP number when ordering 8erviee Letter No. 188 hit consisting of the following:
Kit Na. 1 Partl
lilt Na. 2 Part II
Kit No.l Kit NO. 2
eTY PTY PART NO. DESCRIPTION
1 aa. bXAIBaO Labe~
1 ea. P1OM-S8 Switch
1 se. i ea. Compliance Card
1 ea. Iea. Service Lacer No. 989 Instructions
SPECIAL TOOLS: REGULATED PRESSURE SOURCE AND OHMMETER.
Page 1 of 4
Z
SERVICE LETTER NO. SSS
ACCOMPLISHMENT INSTRUCTIONS:
PART I RECALIBRATE ECU PRESSURE SWITCH
i. Cain access to ECU by removing air outlet duet access (avlonlcs access) cover which is Located on
bottom of an fuselage.
a. Remove BdsUng ECU pressure switch.
S. Recalibrate slddLog ECU pressure switch as follows:
Connect switch to a suitable pressure test set-up which has prodd~s for regulating or meter-
Ing the air pressure applied to the unit from 0 to 1(10 psl accurately indicating this applied
pressure d a psi or better) and connect pins A and B of pressure switch to ahmmeter.
b. Using an 0.080-lneh diameter B flute splined key (Brlebl P/N 8-080), remove locking setscrew
(ANSB5AC4L2). Then, insert key in adlustlng screw (ANWSACLII) and back-out screw oounter-
clockwise to lower setting.
ROTS
Setscrews may be type "H" sockets, in which case a standard
0.050 hex hay may be used.
Hen Socket Head FLuted Socket Head
o. AlterMtely back-out screw 1/4 turn and check trip points until switch actuates at 50 pslg on
increasing pressure. Once set, increase applied pressure to 100 psig, Ban recheolt setting.
d. Look setting adlustlng screw by applying 1 to a drops of Loetlte 2´•12 in hole and replacing
locking setscrew.
*OTT
Aiter.~adlustlng, space remaining above BdlusUng screw may be too
shallow to accept locking setscrew. In which case, omit locking set-
screw entirely and fill space xnth epoxy, Traeon Type 2101, 2128 or
equivsilent.
a. Mar completing above steps, apply bWL18aO Label on pressure switch.
4. ReinsDall edsting recalibrated pressure switch on ECU.
5. Rewire ECU pressure switch electrlosl connector as shown in Figure 2., and connect O ECU.
B. Assure no leaks are evident.
R8Lnstslll air outlet duct access cover.
8. Fill out and mail Compliance Card specifying that Part 1 has been accomplished.
2. Proceed to RECORD COMPLIANCE.
PARTn REPLACE ECU PRESSURE BWITCH
i. Ciain access to ECU by removing air outlet duct access (pvlonics access) cover which is located an
bottom of sit hselage.
2. Remove edalllll ECU pressure switch (see Figure i.).
Page 2 of 4
BERYICE LETTER NO. 553
P1OM-SI) BWPPCHENVIRONMENTAL CONTROL UNIT
(REF)
C~
Pipura i.
BEFORE CHANGE AFTER CHANGE
t--W"~2’
I)CCQPt
ii~ur´• 2.
Page 5 ol 4
IERYICE LETTER NO. )53
3. Install P1OM-18 switch on ECU (see Figure i.).
4. Rewire ECU pressure switch electrical connector as shown in Figure 2 and connect to ECU.
5. Assure no leaks are evident.
8. Reinstall dr outlet duct access cover.
Fill out and mail Compliance Card specifying that Part n has been accomplished.
ELECTRICAL I~AD: NO CHANGE.
WEIGHT AND BALANCE: NO CHANGE.
SPARES AFFECTED: NO.
PUBLICATIONS AFFECTED: The Airplane Maintenance Manual and illustrated Parts Catalog changes
required by this document will be incorporated at the ned scheduled
change/rsvialon
RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service
Letter No. 533, dated 18 May 1880, entitled "Endronmsntal Control Unit (ECU) Pressure Switch
orI(eplaoament", Part Iaccompllshed (date) i PartII accompllshed_lda_t~L__´•
Page 4 014 4
COMPLIANCE CARD
Fmm:
Senrice Bulletin No. ’ln P~RT n
Alrwan SIN
Compliedrrim: Oate~: -sj------------*--cl--
Propeller (Hub) Srm: Lan
Blade S*l
Propeller IHub)S/N: Ri~ht
Blade SIN
Time on sad,pmpller: bft Riet
Complied with by:
Si~rmn,res i~´•so)
__
Sevvi~e Letter Culf~streamAmeriranCORPOR*TION
Cammads MullionSW1 Norm Aa;tnsll Avenue.Bam´•ny. OLlahoma 73008
SERVICE LETTER NO. 9S4A((llpersedes Servloe Letter No. 554, dated a0 June 1880, in its entlretg.)
16 Maroh 1881
ELECTRIC START SYSTEM MODIFICATION AND STARTER--GENERATOR
GROUND BUS BAR REPLACEMENT
MODELS AFFECTED: PART I MODEL BgOC, 8ERUAL NO’S 11601, 11605 THRU 11BM,1180$ TBRU 11815, 11615 TH(U 11818 AND 11621 ANDMOD1L 085, SERIAL NO’S 85001 THRU 85002.
PART n MODEL 680C, SERLAL NO’S 11801, 11805 THRU 11618,11821 THRU HBZB AND MODEL BsS, SERIAL NO’S85001 THRU 85004 AND 85006.
PART m- MODEL 680C, SERIAL NO’S 11600, 11802, 11820 AND11821 THRU llBSS AND MODEL 885, SERIAL NO’S
85000, 85005 AND 86001 THRU 85015.
PART IV MODEL 685, SERIAL NO’S 85000111RU 85055.
REASON FOR PUBLICATION: PART I TO PROVIDE SERIES BATTERY VOLTAGE FOR IGNITOR
UNIT, ENGINE FUEL VALVE AND START PRESSUREREGULATOR DURING 8ER1ES START AND PROVIDEIMPROVED BATTERY GROUND.
PART n- PROVIDE SERES BATTERY VOLTAGE FOR UNFEATII-ERINO PUMP, OIL VENT VALVE, ANTI-ICE LOCKOUT
VALVE, CENTERINSTRUMENT PANEL LIGAPINO, NTS
TEST AND BLEED NE VALVES DUIL1NG SERES START,PROVIDE AN ]MPRDVED STARTER-GENERATOR GROUNDBUS BAR AND INCREASE SERVICE LIFE OF GENERATORCONTROL UNITS (OCU) BY PROTECTING INTERNALTRANSISTOR FAILURES.
PART m- To INCREASE SERVICE LIFE OF GENERATOR CONTROLUNITE (OCU) BY PROTECTING INTERNAL TRANSISTORFAILURES.
PART IV TO ENSURE THE CAPABILITY OF PERFORMING 6E111E88TART8 WITHOUT TRIPPING CIRCUIT BREAKER.
COMPLIANCE: WITHIN NEXT 100-HOUR TIME RI 8ERVICE.
*011
COMPLIANCE WITR PARTS I, n, AND m, of SERVICE LETTER NO´•
554, DATED 20 JUNE 1860, A8 AMENDED BY RFVIblON 1 AM) 2,CONSTITUTES COMPLIANCE WITH PARTS I, n, AND m or THIS
(IERVICE LETTER.
PART IV 16 AN ADDITIONAL IMPROVEMENT, RE9UIRINO COMPLIANCE.
IF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYING WITH THIS8ERVICE LETTER, CONTACT YOUR NEAREST OULFSTREAM COMMAM)ER
AUTHORIZED BERVICENTER FACILITY.
Page 1 of 14
SERVICE LETTER NO. S3UL
BY WHOM WORK WILL BE ACCOMPLISHED: A P MECHANIC DR EQUIVALENT
WOll
DUE TO COMPLEXITY OF THIS SERVICE LETTER, IT L6 RECOMMENDED
THAT AN AUTHORIZED LIEHVICENTEH ACCOMPLISH THIS WOI(K´•
APPROVAL: FAA DOA SW-2 Approved.
EST1MATED MAN HOURS: PART I ~X 16) HOURS.
PART n TWENTY (20) HOURS.
PART nI ONE (1) HOUR.
PART IV- THIRTY (80) MINUTES.
norr
Gulfstream American Corporation, Commander Division, will allow a
credit of six (6) hours for Part I, twenty (20) hours for Part n, one (1)hour far Part m and thirty()0) minutes for Part IV upon receipt of a
properly executed Warranty Claim with attached Compliance Card.
PARTS DATA: Parts required to comply with this Ber~oe Letter may be procured through your nearest
Oulfstream Commander Authorized ServlCenter Facility for: Kit No.l (BS.19, Kit No. a S?8. 58, KitNo. 3 $4.05 and Kit No.4 822.19. A lull credit will be issued upon receipt of a properly executed
4arran~y Claim and a Compliance Card. Reference this Service Letter, aircraft model and factory serialnumber when ordering Service Letter Nq´• 334A Rit(a) consisting of the following:
s.~ uai~l ~´•h´•nr ihauc nolir´•
Kit No. 1- PART I W011 Refer to airplane Seria~ Number eiectlldty ca~l-KitNo. 2 PART n out to determine which hit or hits are required.Kit No. 3 PART III
Kit No. 4 PART IV
Kit Kit I Kit I KitNo.l No.2 I No.S No.4
QTY QTY PTY 4TY PART NO. DESCRIPTION
1 ea. I I I 1 800522-1 Matntlng Strip2 ea. I I I I 800612-RE1 I Bus Bar
1 ea. I- I- I- I 800612-RE3 Cable
2 ea. I I I 1 93(1060~1 Clip Assy1 ea. I- I- I- I AOC-5 Fuse
1 ea. I- I- I- I AN4-5A I Bolt
2 ea. I I I I ANOBODIOL Washer
1 ea. I- I- I- I ANIIBODdlBL Washer2 ea. I I I I AN860D6 Washer
1 ea. I- I- I- ANO?O-( I Washer
8 ea. I I I 1 D-436-53 Splice1 ea. 1 ea. I I I HDJ-A Fuse Holder
2 ea. I I I I IN3209 I Diode
2 ea. I I I I M?8a8/1-LS Terminal
4 ea. I I I 1 M1826/1-22 Terminal
6 ea. I I I M1828/1-a4 Termina~
2 ea. I I I I M1B28/1-25 Termlnn~
2 ea. 2 ea.l I M1828/1-33 Terminal
I ea. 1 2 ea. I I I MS21a42L4 I Nut
2 ea. I I I I M8a1044NOB Nut
2 ea. I I I I MSalBlsDOB I Clamp2 ea. I I I 1 MS21058-1-08 1 Screw
2 ea. I I I 1 M835206-228 1 screw
Page 2 of 14
SERVICE LETTER NO. S9~A
1ait I 161L I- 1 M81044/8-18-8 Wireas ft I I 1 1810(4/13-22-8 Wire
IS ft 1S ft M81044/6´•a0-8 Wire2ea. I I I)OOB?a-ONI~O Cable Aesy2 ea. 8006?5-41 Bus Bar1 ea. 835058-1 Relay1 ea. AOC-?. 5 Fusea ea. ANI-UL Bolt2 ea. I I I AN86O-41BL WasherZea. MS11012L04 Nut8 ea. 2 ea.l I MSa5181-1 8utt Splicea ea. MSsS206-214 Screwlft I- I- I RNF 100 Tubing (Type I, 1-1/2"Ma.)4 ea. 8-5A2 Mode
I 1 ea. 1211-6-1-1/a- 12-501-81 Circuit Breaker1 ea. Il ea. 1 ea. 1 ea. Compliance Card
1 ea. 8erdee Latter No. SS1IA Wiring Magrams1 ea. 1 ea. 1 ea. 1 ea. Service Letter No. 334A instructions
SPECIAL TOOLS: NONE.
ACCOMPLISHMENT INSTRUCTIONS:
PARTI
1. Gain access to batteries, located in aft fuselage, through baggage computmenl door.
2. Remove baggage compartment liner to gain access to batteries and Power Distribution Panel.
3. Disconnect and remove both batteries from airplane.
4. Drill and install 830080-1 clip assembly (a places) on aft angle of right battery support (see Figure i.).
5. Install one end of 800812-RES cable on left battery support using edsting hardware and insta~l otherend of cable on fuselage frame at Sta 212.00 using AN4- SA bolt, ANB?0-4 washer, AN860D41BLwasher, and MSZ1042L4 nut (see Figure 1.).
6. Install MS21818DG8 clamp (2 places) on 80067a-RES cable and attach to 830080-1 clip assemblies usingMSa?(lSg-I-08 screw and ANLIBOD1OL washer (see Figure i.).
1. Remove cover assembly from Power Mstributlon Panel.
8. Dsconnect wires No. 6, No. No. 8, No. g and No. 88 from CR-I diode, cutoff ring terminals andsplice wires No. B, No. No. 8, No. 8 and Na. 88 together using splice (see F~gure 2.).
*011
On Model 685, wire No. 239 should also be dlaconnected andspliced to the above listed wire numbers.
g. Disconnect wires No. 106, No. 101, No. 108, No. 109 and No. 198 from CR-2 mode, cutoff ringterminals and splice wires No. 106, No. 101, No. 108, No. 109 and No. las together using D4SB-53splice (see Figure 2.).
11011
On Model 685, wire No. 243 should also be disconnected andspliced to the above Usted wire numbers.
in. Install 800522-1 mounting strip, INS208 diode (2 places) and 800612-RE1 bus bar (2 places) on elatingCR-I and Cn-2 diodes. Clean mounting strips and bus bar for good continuity (see Figure 3.).
11. MssonMeot wire No. 4 from pin Aa of KS relay and connect wire O CR-I mode and diaeonneot wireNo. 104 from Fdn A2 of KB relay and connect wire to OR-a diode (see Figure 2.).
Page S of 14
SERVICE LETTER NO. 334A
la. Install wire No. 4A from CR-1 made bus bar to pin A2 of KS relay and Lnstlll wire No. 104A from Cf(-a
diode bus bar to Fdn A2 of K8 re~ay (see Figure a.).
13. Install wire No. 131A on CR-S and CR-4 diode and tnstsill wire No. 191 on CR-S diode and route to K25
relay on relay panel and connect to terminal B3 (see Figure a.).
14. Install wire No. 130C on 82 of g25 relay, r~Le wire i~ong edsdng wire bundle at to Start
Control Panel which is Located at of left battery and insta~l HDJ-A Bae holder (F41) (see Figure 2.).
15. Install Wire No. 13OA from WJ-A fuse holder (F41) to terminal 12 of K18 relay which is Located on
Start Control Panel (see Figure 2.).
YOlr
Fuse holder should be inst~lled within B-Lnches of terminal 12 of
K18 re~ay.
16. Install AOC-5 B.e in HDJ-A fuse holder (F(1) (see Figure a.).
W~SHER IUNDER NUTLaaelo´•4 wnstlsn (8EmEEN BOLTI(EI\D AND TERMINIIl)
INUT
0.2CI" DI* AND CLE*NMIZlglsD08CLIMP
SURFPICE AROUND BOTH llDE8MSnOJS´•laBMREW
OF HOLE TO ASPURE I\NgMIDIOL WPgHERAOOOD OAOUND PLSI
slooso.~ CLIP nsSY.
PLS)
RBATTERY
IRE Fl
CABLE
ExlsnNacnsrEslREFI
HaRDwnnE
Anouhlo BOTHSIOEF OF HOLEmAIURE AOOODOROUND
\Y´•
SyppOnT IREFI
Figura i.
Page 4 of 14
BERVICE LETTER NO. S94A
nurr ~t,curaa~b mwaur a
vl,c~ rr woru ur~a
T (nP RV 1! +~Y´•Sbr
dC~W)
m ~NI m BE M/´•i~>-l
3 nnufo DEUOIE
a bOllr, LIUCI DLYIVC U/P~ C
IIL~t---* Q41 wMw~
~YUIL (S rm~
9
L-~ib x~
ICI131~
xr
8r"/1
ca ~I0´•43853SPLICE
a -3
1 1´•´•~p’
I ooc r
w
re ~cr,
r"XIIIVI~
IIV mUINPL
~__m --~i;zn ihaL-----ln~n
a~ot
Oy.lmasm wnv
naureu~n
(1 IV ~69i0 ITCC)
IIIDLX.´•)
anms mpa
Q rurnur Mn.w~r
Fipur´• i.
Page 5 of 14
SERVICE LETTER NO. 934A
B008~2´•RE1 BUSB~R rZ PLS)
1’INJZOB DIODE
II1’
12 PLSL
rr-l
;L-..iI :F8 880522-1 MOUNTINGSTRIP
1IN32W DIODE (REFI
800672-661 BUSsnR IREFI
~uL
808522-1 MOUNTINGSTRIP IAEF1
POWER DISTRIBUTION P~EL IREF)
Fiour´• 3.
1? MsooMect wire No. 16 from CBBI series au~llary circuit breaker, wNch is located on Start Control
Panel, and connect wire to terminal 11 of K17 relay (see Figure 2.).
18. Install wire No. 76A from terminal 11 of K17 relay to termlna~ 11 of K18 relay (see Figure 2.).
18. Instill wire No. 130 from Lermlna~ 12 of K17 relay to terminal 12 of gig relay (see Figure 2.).
20. Install wire No. 130B from termin~ilii of K1? relay to CB61 series audl(ary circuit breaker (seeFigure 2.).
21. Retnstall batteries in airplane but do not connect battery Lermina~s. Fill out and mail Compliance Card
specifying that Part I has bean accomplished and proceed to step 5. of Part n.
PART II
11016
The following wire numbers in Part n are M81044/9´•2P8 (20 gauge) wire:No. 1A, No. 201, No. Z0?A, No. a018 and No. a0?C. Wire No. 210 and
No. 271 are M81044/9´•18-8 (18 gauge) anre. All other wires are M81044/12-21-8 (22 gauge) ~re.
1. Gain access to batteries, located in aft fuselage, through baggage compartment door.
2. Remove baggage compartment liner to gain access to batteries and Power Mstribution Panel.
3. MeeoMect battery terminate from batteries.
4. Remove cover from Power Distribution Panel.
Page 0 of 14
IERVICE LETTER NO. 934A
POWER DISTRIBUTION PANEL
9 cb-2
i j
r-\L´•i
13~
PUSE PANEL IREFI
FII FIZ F13 Flr 115
00000MSS9206-2146CREW
BPLS)
1175
0.30"
’i llr
SS:,oSP-l RELnvIMOUNT ON B*CK SIDEOEPANEL)
iiSure 4.
5. Locale, drill and install 853098-1 relay on fuse panel assembly wNch is Located on forward side of
Power Distribution Panel, using MSSS206-21( screw (2 places) and MSZ1042L04 nut (2 places) (see
Figure 4.).
B. install wire No. 1S1B from terminal B3 of K26 relay to terminal X1 of K?S relay (see Wiring Diagrams
No. 1 and No. 2).
11011
Reference to Wring Diagrams No. 1 UIN NO. 8 are U1B
vlrl~g diagrams included wiUl Ule kit.
Page 1 of 14
BERVICE LETTER NO. 394A
7. Install wire No. 1S1C from termlna~ X2 of K?5 relay to GND terminal of overvoltage sensor (see Wiring
Diagrams No. 1 and No. 2).
8. Disconnect wire No. 1 from termin~ B2 of K8 relay and connect to termina~ A9 of K15 relay (see
Wiring Diagrams No. 1 and No. a).
8. Install sire No. lA from termlnsl AZ of K?5 relay to terminal 81 of Kg relay (see Wiring Diagrams
No. 1 and No. 2).
10. Disconnect wire No. 101 from terminal B2 of KiO relay and connect to terminal BS of K?5 relay (see
Wiring Diagrams No. S and No. 4).
II. Insta~L wire No. 207B from Fdn A of P131 connector to terminal B1 of K?S relay (see Wiring Diagrams
No. 9 and No. 4).
12. Install wire No, 2O7C from terml~plB1 of K75 relay to terminal Al of K?S relay (see Wiring Diagrams
No. i, No. 2, No. S and No. 4).
13. Install wire No. 101A from terminal B2 of K?5 relay to terminal B2 of K10 relay (see Wiring Diagrams
No. 3 and No. 4).
14. Install wire No. 207, HDJ-A fuse holder (F42) and wire No. 207A. Wire No. 207 connects b terminal
A2 of K18 relay and to HDJ-A fuse holder and wire No. 20?A connects to pin A of J197 connector and
Lo HDJ-A fuse holder (see Wiring Diagrams No. 9 and No. 4).
WOll
The HDJ-A fuse holder is an inline fuse holder installed between
5137 conneclor and start control panel. Fuse holder should be
Installed within B-inches of termina~ A2 of K1B relay.
15. Install AOC-7.5 fuse in HDJ-A fuse holder (F42) (see Wiring Diagrams No. 3 and. No. 4).
18. Disconnect wire No. 12 from terminal L2 of CS-1 left generator field current sensor, splice wire
No. 270 to wire No. 12 with MS25181-1 bull splice andconnect wire No. 21(1 to terminal 24 of K1? relay
with M7828/1-53 terminal (see Figure 5.).
17. Disconnect wire No. 128 from termlna~ LZ of CS-I right generator field current sensor, splice wire
No. 271 to wire No. 128 with MS25181-1 butt splice and connect wire No. 211 to terminal 24 of K18 relay
with M1828/1-SS terminal (see Figure 5.)
18. On Model 680C, 8eria~lnumbers 11801, 11803 thru 11609, accomplish the following:
If Wire No. 203 is connected to terminal AS of K13 relay, disconnect from K1S relay and connect to
terminal A3 of Ka5 relay (see Figure 8).
*011
Wire No. 203 must be routed from Fdn V of 548 connector to terminal
AS of K25 relay´•
18. Lower overhead switch panel as follows:
a. Loosen alien screws on all tnobs on face of the electroluminescent panels and remove ~nobs.
b. Remove attaching screws secudng electroluminescent panels.
c. Carefully remove panels and, expose electroluminesoent panel wiring.
d. Grasp wires and gently pull down until quiok disconnect and airplane wiring are exposed.Disconnect electroluminescenl panel.
a. Remove atlaehl~ screws from top of metal plate of overhead switch panel and pull top of paneldown. Entire panel will hang in a vertical position suspended by the hinges.
Page 8 of 14
BERVICE LETTER NO. 334A
*12
REMOVE D~8HED WIRE REMOVE
L2
FROM L2FROM L? 1 155
55 IREF) I IIREF)
13 e ~alL__
I ~‘bsolaEn--r72 129
1 BUTT SPLICE Mn5181´•1 BUTT 8PLICE~P~DO NEW WIRE ~DD NEW WIRE
MlllLId18´•1&8
r T1 55 (REF1
3JTERMINn~
55 (REF1 1551REF)
I I _LI h!eg, ~-09
QP 25
M)92811J3 TERMIN~L
Pieu~s 5.
28. on Modej880C, rewire the overhead switch panel as follows:
a. Disconnect and dead end the following wires: (see wiring diagrams in Chapter 81 of the Airplane
Maintenance Manua~ for wire location):
(1) Wire No. 1E1Ba2 between terminal strip TB1B and pin P of P30 Connector. Dead and at
terminal strip TB16.
(2) Wire Na. 1E1C22 between pbnP of P3O Connector and terminal a of left NTB test switch.
Dead end at NTS test switch.
(3) Wire No. 2E1B22 between terminal strip TB8 and pin R of P30 Connector. Dead end at
tsrmlna~ strip TB8.
(4) Wire No. 2E1C22 between ~Ln R of P30 Connector and terminal 2 of right NTS test switch.
Dead end at NTS test switch.
b. install wire No. 1E28D22 from terminal 2 of Left NTS teet switch to termlnail 1 of Lan ITT
compensator test switch (see Wiring Diagram No. 5).
c. Instan wire No. 2328022 from terminal 2 of right NTS test switch to terminal 1 of right ITT
compensator test switch (see Wiring Diagram No. 5).
21. On Model 885, rewire the o~srhead switch panel as follows:
a. Disconnect and dead end the following wires (see wiring diagrams in Chapter 81 of the Airplane
Maintenance Manual for ire location):
(1) Wire No. 1E1Da2 between terminal 2 of left temperature compensator test switch and
terminal 2 of left talque limit control switch.
(2) Wire No. 211022 between terminal 2 of right temperature compensator test switch and
terminal 2 of right torclue limit control switch.
Page 8 of 14
SISRYICE LETTER NO. 994A
b. lnstail wire No. 1E2BF22 between terminals a and 5 of left temperature compensator test switch
(see Wiring Diagram No. B).
c, fnsta~lwire No. 2E2BF22 between terminals 2 and 5 of right temperature compensator test
switch (see Wiring Diagram Na. B).
22. Reinstail the overhead switch panel as follows:
cnurlon
When Insfs~lilg the overhead switch panel, ensure that all wires
and busses are properly secured and are not squeeled or chafingon airframe. This will prevent possible short circuits.
a. Swing overhead switch panel up and secure with attaching screws.
b. Connect electrolumlnescent panel wiring to airplane wiring and position panel for installation.
Stow excess wiring eneudnglhat it will not be pinched or crimped when panel is secured.
c. Secure electrolumlnesoent panels with attaching screws.
d. Relnstall aill knobs using existing alien screws.
2). Remove knobs from oil temperab~re control levers to facilitate rsmov~l of radar scope.
24. Remove and disconnect radar scope from center instrument panel.
25. Remove circuit breaker panel as follows:
a. Pull co~lot control wheel to full, aft position and secure.
b. Reach under and behind circuit breaker panel and disconnect electrical connector plugs and
wiring.
c. Remove attaching screws from front of panel and carefully remove circuit breaker panel
d. Remove backppate cover from circuit breaker panel to gain access to wiring.
28. Instsill S-SAI diode (2 places) on circuit breaker panel terminal board M (see Figure 8 and Wiring
Diagram No. 1).
OO tK%oo
TERMINAL BOARD "M’~ IREF)(LOCPITED ON CB PANELI
O o
ssAu DIODE
Fieura 6.
21. Disconnect wire No. 10 from pin A of 91 connector and connect to terminal 29 of terminal board M
(see Wiring Diagram No.
11015
When viewing the J1 connector, "A" appears as "a".
28. lnstail wire No. 10A from terminal 11 of terminal board M to pin Aof SI connector (eee Wlri~ Diagram
No.
Page IO of 14
BERMCE LETTER NO. 534A
28. Install wire Na. 1SZA from terminal 22 of Lennina~ board M to termmnail D2 of K20 relay (see Wiring
Diagrams No. 5, No. B and No.
SO. Reinsts~L baoltplate cover on circuit breaker panel.
51. The following wiring is located behind the center instrument panel:
a. Install wire No. PB1022 by iud splicing to existing wire No. L23E22 and install S-3A2 mode
(2 places) (see Wiring Diagram No. 8).
*011
Wire No. P61D22 and Wire No. L25Eaa are not to exceed B-lnches in length.
b. hst~l wire No. P5ICI0 on mode installed in step a. (see Wiring Diagrams No. 1, No. 2 and No. 8).
c. Disconnect wire No. PB1AIO from pin V_ of P? connector, install wire No. PB1BIO on pin Y ofP? connector and butt splice wire Nos.PB1AfO, P61B20 and PB1COO together (see WiringDiagram No. 8).
52. Reinstall radar scope on center instrument panel and reinstall knobs on oil temperature control levers.
55. Relnsla~l circuit breaker panel as follows:
a. Ensure that backplate cover is installed on circuit breaker panel.
b. Position circuit breaker panel close to its mounting position and connect electrical connector
plugs and wiring.
c. Position circuit breaker panel for installation and secure with existing attaching screws.
d. Release ooFdlot control wheel and allow it to move forward.
34. Remove upper cowling from left and right engines.
55. Disconnectwire Nos. 1PS5A4, 1P2?A2 and 1P28A2 from left and wire Nos. 2P55A4,2P21A2 and 2P28A2 from right starter-generator (see Figure and Wiring Diagrams No. 1, No. 2,No. 9 and No. 4).
56. Install RNF 100 (1.5-inch) tubing over wires, reconnect wires to starter-generator bus bar and slide
tubing over bus bar and sire terminals. Heat shrink tubing and secure with ty-raps (sse Figure 1.).
llOTI
Clean sill terminals prior to installing.
S1. Remove and discard existing starter-generator grmnd (OND) cable and existing ground cable bus bar
from left and right starter-generators.
58. Install 800615-4’1 bus bar on starter-generators using existing hardware and reconnect eldsdng wires
(see Figure
99. Install 800612-OND-0 cable assembly using slsting hardware and AN4-4A bolt, ANgBO-41BL washer
and M821042L4 nut (see Figure
40. Reinsta~l upper cowllng on left and right engines.
41. Relnstall cover assembly on Power Distribution Panel.
42. RecoMect battery terminals to batteries.
45. Assure that airplane electrical system is functioning properly.
44. Relnstilll baggage compartment liner.
45. Fill out and mall Compliance Card specifying that Part II has been accomplished.
Page 11 ol 14
BERYICE LETTER NO. SS4A
PART III
i. Gain acoess to bat~eries, located tn ait fuselage, Ulra~gh baggage conpartment door.
2. Remove baggage eomparDnent liner to gatn access to ba~terles and Powe. Mstribution Panel.
INSTALL IX´•´• ITERMINATION
LENGTH OF TUBINGTO BE I.W" PRIOR TO SHRINKING. POSITIONTUBING SO THAT BUS 8AR. TERMINAL TONGUES
MSZ10(2L4 NUT HABDWARE ARE COMPLETELY~N980dlBL WASHER
1N44~ BOLT
,TY´•RAP (REFL
80087547 BUS BAR o(EXISTINO WIRES NOT c
SHOWN FOR CLARITY)
BWB72´•ON00 CABLE ASSY IREF)
STARTER´•OENERATOR (REF)
~igurs 7.
illi--t~I I Brll
I--
LO(REF)7 X1*1
xl B2(REF)-----IBD(RTf)
il5:i
7slarF) ----1 q_
L_ v
1------~-----DISCONNECT DASHED WIRE AND CONNECTTO TERMINAL /u OF 126 RELAY qT IREF´•--( T
Jyb P4b
~i(lur´• B.
Page 12 of 14
SERYICE LETTER NO. 3S4A
3. Disconnect battery terminals from batteries.
4. Remove cover from Power Distribution Panel.
5. Disconnect wire No. 12 from termin~lL2 of CS-1 left generator field current sensor, splice wire
No. 210 to wire No. 12 with MSa5181-1 butt splice and connect wire No. 210 to terminal 24 of Fl?
relay with M?828/1-33 terminal (see Figure 5.).
8. Disconnect wire No. 128 from terminal L2 of CS-2 right generator field current sensor, splice wire
No. 211 to wire No. 129 with MS25181-1 butt splice and conned wire No. 2?L to terminal 24 of K18
relay with M?828/1-5S termina~ (Bee Figure 5.).
89. On Model 880C, Brlsil numbers llBDO and 11802, accomplish the folloHrlng:
If wire No. 205 is connected to terminal AS ofK1S relay, disconnect from K1S relay and connect to
terminal AS of Ka5 relay.
WOII
Wire No 203 must be routed from pin V of 548 connector to terminal
AS of K25 relay.
Reinstall cover on Power Distribution Panel.
8. ReooMecl battery terminals to batteries.
8. Assure that airplane electricail system 18 functioning properly
10. Reinstallbaggage compartment liner.
11. Fill wt and mail Compliance Card specifying that Part ill has been accomplished.
PART IY
i. Cain access to start control panel, located between batteries, in aft fuselage, by removing rear baggage
compartment liner.
2. Disconnect battery connectors from batteries.
3. Remove attaching nut and washer, seeuri~g circuit breaker, CB81, to Miscellaneous Start Panel (refer
to Figure 38~218, Chapter 30, of the Maintenance Manual).
noTr
Circuit breaker will drop out from panel,
4. Remove attaching screws for wiring connection and remove electrical wires.
5. Remove circuit breaker.
8. IoBta~l electrlca~ wiring to new circuit breaker, P/N 1211-5-1 1/a-12-501-61 with attaching screws.
Position circuit breaker in panel and secure with washer and nut.
B. Connect battery connectors to battery.
8. Ensure that airplr~ns electrical system is functioning properly
1(1. Instzll rear baggage oompartment liner.
ii. Fill out and mall Compliance Card specifying that Part IY of this Service Letter has been accomplished.
Page iS of 14
SERVICE LETTER NO 13U
ELECntICAL LOAD: WD CHANGE.
WEIOBT AND BALMCE: The sdght and balanee elnrge required by i~BUUatlon ol this Sernce Letter is as
folloars:
wna;ar nes) H-ARU mrBES) H-YOYEIF QN-LQs)
Fart I- ’2.M) t185.00 590.0
Fart n NO CHANGE.
Fart m No CHANGE.
PART TV NO CHANGE.
SPARES AFFECTED: NO.
PIlDLlCAnDNS AFFECTED: The Munrenanee Manual and Illustrated Plnr Cabl~G c~n%esrequired by U1B document uill he ineorporated at the next scheduled
MOTE
Insert the Wiring Diagram chanb~es provided with this service I.cltsrIn the Airplane MaintenRnee Manual until the revised ulri~ dlayramslor the Maintenance Manual are available
RGCORD COMPLIANCE: Mate an c~ry is the ´•Irpl~p mslote~oce reeorde as lollovs: Service
Letter No. 3JU, dated 16 Yarrh 1981, entitled "Elect~e Start System YomBaUM and S~rter-Gcnmtor
Bus Bar RcplPeement". Part 1 Part n aeeomplished (dlte)Pilr(m aecompa´•beq_ (date] Part IV (dlte)
Rite 1I al II
SERVICE LETTER NO. 334A
WIRING DIAGRAMS
RETAIN THESE WIRING DIAGRAMS WITH
AIRPLANE MAINTENANCE MANUAL UNTIL
REVISION TO MAINTENANCE MANUAL IS
AVAILABLE.
Service Lettev Iponnlaru~mM´•mwnl NOrU R~*lll *mU
SERVICE LETI‘ER NO. 595
28 August lsBO
CIRCUIT BREAKER PANEL ASSEMBLY MODIFICATION
MODELS AFFECTED: MODEL 6800, SERIAL N0’S 11600 THRU 1189g AND MODEL 885,SERIAL NO’S 86(100 THRU 95024.
REASON FOR PUBLICATION: TO PREYENT P0SSlBLE CROSS CIRCUITING OF DISTR-I AND
RADIO-1 CONTROL CIRCUIT BREAKERS.
COMPLIANCE: WITHIN NEXT loO-HOUR8 TIME IN SERVICE.
11011
If ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYWG WITH
THIS SERVICE LETTER, YOUR NEAREST ROCKWELL
COMMANDER AUTHORIZED SERVICE FACILITY.
BY WHOM WORK WILL BE ACCOMPLISHED: A P MECHANIC OR
APPROVAL: FAA DOA SW-2 Approved.
ESTIMATED MAN HOURS: TWO (a) HOURS.
PARTS DATA; Parts required to comply with this Service Letter may be procured through your nearest
Rochwell Commander AuUlori.ad Service FaelllLy for $4.12. Reference this 8arvtce Letter, aircraft model
and lacbrg serial number when ordering Service Letter No. 995 kit oandstlng of the following:
aauajnto~nn*inannorc
OTY PART NO. DESCI(IPTION
1 ea. 850618-5 Insulator
3 ea. MISB7-4-8 TLedown Strap
t ea. Compliance Card
1 ea. Service Letter No. 335 Instructions
SPECIAL TOOLS: NONE.
ACCOMPLISBMENT INSTRUCTIONS:
i. Assure that bansry switch is in Ule OFF position.
a. Remove circuit breaker panel as lollo´•ua:
a. 111 copilot control wheel to b~U aft position and secure.
b. Reach under and behind circuit breaker panel and disconnect eleetriaal connector plugs and
wiring.
c. Remove attaching screws from front of panel and carehully remove circuit breaker panel.
d. Remove baokplate cover from circuit breaker panel to gain access to circuit breakers.
3. Install 850818-9 insulator between DISTR-a RESET circuit breaker and RADID1 REBET circuit
breaker using MSSSB1-~P-g tledown strap (9 places) (see Figure i.).
4. Reinstail bacbplnte cover on circuit breaker panel.
Page 1 of a
SERVICE LETTER NO. 956
!O
’"~I’ r=´•´•´•´•~
ef~i´•
a
Es
io c
clRCurr BREAKER
PANEL (REF)olsw-a RESET (CB NO.S1)CIRCUIT BREAKER
850818-3 TNBULATOR
RADIO-I RESET (CB NO. 48)MSSSB1-4-9 TIEMIWN CIRCUIT BREAKER
STRAP (5 PL8)
I´•isur´• 1.
5. Reinstaillcircuit breaker panel as follows:
a. Position circuit breaker panel close to Ya mounting poldt(on and connect electrical connector
plugs and wiring.
b. Position circuit breaker panel for insta~latlan and secure wit easll~ attaching ser~ula.
c. Release copilot control wheel and aYow to move forward.
d. Check cbcuit breaker panel for operational integrity.
8. Fill out and mail Compttance Card.
ELECTRICAL LOAD: NO CHANGE.
WEIGHT AND BALANCE: NO CHANGE.
SPARES AFFECTED: NO.
PUBLICATIONS AFFECTED: NONE.
RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as ioHove: Se~ee
Letter No. 555, dated 28 August 1980, entitled "Clrcult Breaker Panel Assembly Modilcatlon", accomplished(date)
PageaolZ
Rockwell internat~onsl
ev pnnaMlnoM´•a6W1 Nonh Ro~all *nnu
i
LITPIH NV. YY’I
91 NOVEMBER 1880
ENGINE MOUNT BRACKET MODIFICATION
MODELS AFFECTED: MODEL 690C, 8ERIAL NO’S 11681 THRU 11850 AND MODEL 696, SERIAL NO’S. 99018THRU 96035.
REASON FOR PUBLICATION: TO PROVIDE PROPER CLEARANCE BETWEEN ENGINE MOUNT BRACKET ANDOIL FILTER ADAPTER CLAMP PLATE WHEN INSTALLING MODIFIED OIL FILTER SWIVEL ADAPTER.
COMPLIANCE: WITHIN NEXT 100-HOURS TIME W SERVICE.
c.
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYING WITH THIS SERVICE LETTER, CONTACT YOURNEAREST ROCKWELL COMMANDER AUTHORIZED SERVICE FACILITY.
BY WHOM WORK WILL BE ACCOMPLISHED:_4 P MECHANIC OR EQUIVALENT.
APPROVAL: FAA DOA 8W-2 Approved.
ESTIMATED MAN HOURS: SIXTEEN (18) HOUR8:
Rockwell International, General Aviation Divieion.will allow a
credit of 16 hours upon receipt of a properly executed WarrantyClaim and a Compliance Card.
PARTS DATA: 1 ea. Compliance Card
SPECIAL TOOLS: PROPELLER SLING AND ENGINE HOIST
ACCOMPLISHMENT INSTRUCTIONS:
1. Remove upper and lower cowling from lelt and right engines.
2. Attach propeller sling to propeller blades and connect sling lift ring to engine hoist and asnure that engine is support-ed by sling and hoist.
S. Remove bolt attaching lan and right engine side mount brackets to mount isolators (see Figure 1.).
4. Remove bolt (4 places) attaching left inboard and right outboard mount brsclsts to engine (see Figure 1.). Thismount bracket is the one located below the oil filter.
6_ Remove mount brackets from anginas.
6. Modify existing left inboard and right outboard engine side mount brseleta by machining or filing bracketa in area
shown in Figure 1.
cnvrlow
DO NOT GRIND brackets se permanent damage to the heattreat may occur.
7. inbmud Md n.htoutba,.d. a´•iwnghard~´•Torque bolts 400 to 500 inch-pounds and safety wire (see Figure 1.).
:8. Reinstall edstiqhardware thatattacheslettand rightengine side mountbl.acketatomauntisolators. Torquebolt400 to 500 inch-pounds (aee Figure 1.).
Page 1 o12
SERYICE LETTER NO.351-;´•
LEFT INSTALLATION SHOWN1~ic~
RIG HT INSTALLATION OPPOSI~E
i
TOROUE BOLT 14 PLS)I iTOROUE BOLT 400 TO WO IN-L8S I j I
400 TO 500 IN--LRS j ANO SAFEN
fi:?,
0.03´•.o.l?’l.sa~
MDUNTBRICKETMAX M~X RADIUS
1´•
"-i-~ oREMOVE MATERIAL
FRoM SHADED AREA
VIEW LOOKING FWD
Figure i.
8. Reinatall upper and lower eowling on engines.
10. Fill out and mail Compliance Card.
ELECTRICAL LOAD: NO CBANGE.
WEIGHT AND BALANCE: NO CHANDE.
SPARES AFFECTED: NO.
PUBLIOlT1(INS AFIRCTaD: The Model BBOC.B. Olustraied Wrt. OLli.p ehi(oge re~uind bl.Qia doiument.ill i*incorporated at the next scheduled revision.
RECORD COMPLII\NCE: Make an appropriate entry in airplane maintenance records as follows: Berviee LetterNo. 331,dated 21 November 1880, entitled "Engine Mount Rraeket ModiBcatian", aeoomplished (date)
Page 2 of 2
Service Letter~II
CulfsrreamAmericanCL)RPOH*TII)N
Comnnndw Diuilion6801 North RocZwsll Avenue.Bsmeny, Otl´•hoM IJM8
SERVICE NO. 338ALSupereedes Service Letter No 388, dated 10 December 1980, in its entirety)
13 March 1981
AFT FUSELAGE TWERMOSTAT INSTALLATION
MODELS AFFECTED: PART I MODEL 690C, SERIAL NOS. 11600 THRU 11650 AND MODEL 695, SERIAL NOS.85000 THRU 95040. PART II MODEL 690C, SERIAL NOS. 11800 THRU 11662 AND MODEL 685, SERIAL NOS.96000 THRU 85058.
NOTE
IF BASIC SERVICE LETTER NO. 538 HAS BEEN COM-PLIED WITH, DISREGARD PART I ONLY OF THIS SER-VICE LETTER.
REASON FOR PUBLICATION: TO IMPROVE INDICATION OF ABNORMAL TEMPERATURES SHOULD THEYOCCUR IN THE AFI~ FUSELAGE AND ASSURE HOSES ARE PROPERLY INSTALLED ON ENVIRONMENTALCONTROLUNIT.
COMPLIANCE: WITHIN NEXT 100-HOURS TIME IN SERVICE.
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE COM-PLYING WITH THIS SERVICE LETPER, CONTACT YOURNEAREST DULWTREAM COMMANDER AUTHORIZEDEIERVICENTER.
BY WHOM WORK WILL BE ACCOMPLISHED: A 8. P MECHANIC OR EQUIVALENT.
APPROVAL: FAA DOA SW-2 APPROVED,
ESTIMATED MI\N HOURS: PART I THREE (3) HOURS. PART 11- ONE (1) HOUR.
NOTE
GULFSTREAM AMERICAN CORPORATION, COMMAN-DER DIVISION, WILL ALLOW A CREDIT OF THREE (3)HOURS FOR PARTI AND ONE (1) HOUR FOR PART IIUPON BECEIP~T OF A PROPERLY EXECUTED WAR-RANTY CLAIM AND A COMPLIANCE CARD.
PARTS DI\TI\: PARTS REQUIRED TO COMPLY WITH PART I OF THIS SERVICE LETTER MAY RE PROCUREDTHROUGH YOUR NEAREST CULFSTREAM COMMANDER SERVICENTER FOR 866.58. A FULL CREDIT WILLBE ISSUED UPON REC%IPT OF A PROPERLY EXECUTED WARRANTY CLAIM AND A COMPLIANCE CARD.REFERENCE THIS SERVICE LETTER, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN ORDERINGSERVICE LETI~ER NO. 338A KIT CONSISTING FOR THE FOLLOWING:
QTY PARTNO. DESCRIPTION
1 ea. 880661-35 Thermostat Aesy1 ea. M792811-15 RinpTerminal4 ft. Wire2 ea. MS26181-1 Butt Splice2 ea. Compliance Card1 as. Service Letter No. 338A instructiona
Pagelof6
SERYICE LETTER NO, 398*
SPECIALTOOLS: TORBUE WRENCH WITH 60 IN-LB CAPABILITIES.
ACCOIPUSHEBENT INSTRUCTIONS:
PARTI
1. Cain access to radio shelf and Environmental Control Unit, located in aft fuselage, through lower aft fuselage access
door.
2. Install M?B2811-15 ring terminal an ground lead of 880651-56 thermostat assembly.
3. Locate drill and install 880651-35 thermostat assembly an aft channel (Pi~ 831066´•19) of the radio shelf (refer to
Figure II.
NOTE
The radio shelf is laeated immediately above the Environmen-
tal Central Unit.
4. Connect the 880657-36 thermostat assembly to airplane electrical system by butt splicing new M8104419-12-9 wire
(W10G22) to existing thermostat using M526181-1 butt splice (refer to Figure 1).
NOTE
The existing thermostat is located an the forward channel (Pi
N 83106621) of the radio shelf.
5 Fill out and mail Compliance Card specifying that Pad I has been accomplished.
6. Proceed to step 2. of Part II.
PARTII
i. Cain access to Environmental Control Unit, located in aR fuselage, through lower aft fuselage access door.
2. Inspect Environmental Control Unit hose, located between heat exchanger and pressure regulator, to assure that
hose extends 0.2S-inch or more beyond both clamps (refel to Figure 3).
3. If hose extends O.PS´•ineh or more beyond both clamps and clamps are straight, proceed as follows:
a. With clamps and hose at ambient temperature, torque clamps to 60 IN-LBS (refer to Figure 3).
b. Proceed to step 6.
4. If hose does not extend O.OS-inch or more beyond clamps, proceed as follows:
a. Loosen clamps on hose and reposition hose on tube ends so that hose covers an equal distance over end of both
tubes (refer to Figure i).
b. Install clamps over hose, immediately behind tube beads, assuring that a minimum of 0.P5-inch of hose extends
beyond clamps.
c. With clamps and hose at ambient temperature. torque clamps to 60 IN-L88.
d. Proceed to step 5.
5. Assure that existing clamps on the other ECU hose, downstream of Pressure Regulator, are correctly installed with
rasped to tube beads. Retoque clamps (refer to Figure 3).
6. Reinstall accessdooron loweraftfuselage.
Provide a minimum of ons (1) hour oluninterrupted operation of the ECU either an the ground at 1008 RPM or
in the air. After.perstion of one (1) hour, allow the unit to cool down to an absolutely cool condition.
NOTE
The joint will retain its tightness as long as the temperatureis kept up and not allowed to cool down.
PagePofS
SER\I~CE LETTER ND. JSDA
880657-16 THERMOSTAT ASSY
-------------+_ -r-
AIRPLANE
83(088-19 RADIO SHELF
AFT CHANNEL (REFIMSZ~70AD3
RIYET 12 PLSI
VIEW LOOKING FWD
I
I.
BEFORE CHANGE AFTER CHANGE
m8104,9-222s wine
1----W1M22
WloF2z
MS25(81-1 BUTT SPLICE
12 PLSI
880657´•35
EXISTING FORWARD I THERMOSTAT~-
THERMOSTAT (861) ASSY
8’ M7828/1´•(SRINGi
EXISTING FORWAROTHERMOSTAT InE~l
TERMINAL
SERYICE LETTER NO. S38A
1,
TOROUE CLAMP
35 TO 40 IN´•LBS
PRESSURE REGULATORIREFI
B
Y
HEAT EXCHANGER(REFI
WITH CLAMPS AND HOSE PIT
*MBIENTTEMrEAATURE.TOROUE CLAMPS TO (10 IN´•LBI.
AFTER OPERATION OF ONE III
HOUR MINIMUM DURATION
ALLOW CLAMPS AND HOSE ENVIRONMENTAL CONTROL
TO RETURN TO AMBIENT I UNIT IREF)
TEMPERATURE AND RE´•
TOROVE CLAMPS BO IN´•LBS. ´•I TOROVE CLAMPS
16 TO Is INLBS
9HOSE
EXISTING I EXISTING
MS35842´•12 M515842´•12
CLAMP IREFI i CLAMP (REF)
CAUTMN
ASSURE THAT CLAMPSARE
INSTALLED BEHIND TUBE BEADS.
IF CLAMPS ARE NOT PROPERLYa2s´•´• I I I I INSTALLED. LEAKS COULD OCCUR.
MIN EXISTING 184(9 FLEXIBLEITYPI HOSEIREF)
\-cnwloN-MIN. I bO NOT PUT HOSE
CLAMPS ON TOP OF
TUBE BEAD.
ClCur´• 3.
Page lafS
SERVICE LETTER NO. SSBA
8. Remove lower aft fuselage access door to gain access ha Environmental Control Unit.
9. Apply a tightening torque to re-establish a 60 IN-LBB value to clamps originally to~qued in step 3e. or 4c. (refer to
Figure S).
NOTE
Do not loosen the clamps prior to performing step 9. It will
be necessary to comply with the intent of Part II of this Ser-
vice Letter whenever clamps are loosened for any mainte-
nance reason.
10. Rsinstall access door on lower aft fuselage.
11 Fill out and mail Compliance Card specifying that Part 1l has been acmmplished.
ELECTRICC.L LOAD: NO CHANCE
WEIGHT AND BALANCE: NO CHANGE
SPARES AFFECTED: NO
PUBIICI\TIONS AFFECTED: The Airplane Maintenance Manual change required by this document will be inrmpa-
rated at the nsrt scheduled revision.
RECORD COMPLI~NCE: Make an appropriate entry in Airplane Maintenance records as follows: lervice Letter No.
338A, dated 13 March 1981, entitled’.Aft Fuselage Thermostat Installation", Part I accomplished (date)
Part Il accomplished (datel
Page SofS
Service Letter I~sml ND~h R~dlll ImU
~lll´•n*.O*l*oMlfmB
Service Latter No. 339
15 January issl
BAGGAGE HEATER ANNUNCIATOR LIGHT LENS REPLACEMENT
MODELS AFFECTED: MODEL 680C, 8ERIAL NOS. 11620, 11621, 11623, 11628 THRU 11631, 11633, 11635,11638, 11639, 11642, 11646, 11661, THRU 11663. MODEL 685, SERIAL NO8. 85000, 95002, THRU 96005, 86009
THRU 96012, 95014 THRU 96018, 96020, 96022, 85023, 96026, 95026, 85026, 85029, 85031, 85033 THRU 85036, 86038,86041 THRU 85044, 85046, AND 96048.
REASONFORPUBLICATION: TO CHANGE BA(KiAOE HEATER ANNUNCIATOR LIGHT LENS FROM BLUE
TO AMBER.
COMPLIANCE: UPON RECEIPT OF THIS SERVICE AND AMBER ANNUNCIATOR LIGiRP LENS.
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED COM-PLYING WITH THIS SERVICE LETPER YOUR
NEAREST ROCKWELL COMMANDER AUTHORIZED
SERVICE FACILITY.
BY WHOM WORK WILL BE ACCOMPLISHED: OWNER/OPERATOR OR A Be E MECHANIC OR EQUIVALENT.
APPROVAL: FAA DOA 8W-2 APPROVED
g9pI~TBOM*N HLlmYI: NEOIlOIBLB
PARTS DATA: Parts required to comply with this Service Letter are fumished at no charge, end consist of the follow-
ing:
cm PARTNO. DESCRIPTION
1 Ea. ACR ItSAL Cap1 Ea. Compliance Card
1 Ea. Service Letter No. 939 Instructions
8PEC1ALTOOL8: NONE
ACCOMPLISHMEPIP~INSTRUCTIONS:
1. Remove existing blue BAG HEAT FAILED light lens cap.
NOTE
BAC( HEAT FAILED annunciator light is located on top rightaide of center instrument panel and is removed by unscrewing.
2. Install amber light lens cap, P~ ACR It3AL. furnished with Wis 8eruiee Letter.
3. Fill out and mail CompianEn Card.
ELECT~UCAL LOAD: NO CHANCE
WEIGHTANDBALANCe: NO CHANCE
8PARES AFFECTED: NO
PUBLICATIONSAFFECTED NONE
RECORD COMPLIANCE: Make appropriate entry in airplane maintenance recerde as follows: Service Letter No. 998,dated 15 January, lsB1, entitled "Baggsge Heater Annunciator Light Lens Replacement", aceomplished (date~
Page 1 of 1
_
Ser~ee S-~tter CulFstreamAmericanCI)RPOH*TI(IN
ComMnda Divirion
6WI No~th Ralwsll bnuc.
Bamloy. OLI´•hDM 73008
SERVICE LETTER NO. 340
24 April 1981
INSTALLATION OF PLACARD FOR USE OF ALTERNATE
ENGINE OIL MlL-L-78080
MODELS P.FFECTED: MODEL 690C, SERIAL NOS. 11600 THRU 11685 AND MODEL 695, SERIAL NOS. 95000
THRU 95059.
REASON FOR PUBLICATION: TO PROVIDE TEMPERATURE LIMITATIONS WHEN USING MIL-L-7808G OIL.
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE COM-
PLYING WITH THIS SERVICE LETI‘ER. CONTACT YOUR
NEAREST GULFSTREAM COMMANDER AUTHORIZED
SERVICENTER.
COMPLI~NCE: UPON OF THIS SERVICE
BY WHOM WORK WILL BE ACCOMPLISHED: OWNER/OPERATOR
APPROVAL: FAA DOA SW-2 APPROVED.
ESTIMATED MAN-HOURS: NOT APPLICABLE
PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE LETI~ER ARE FURNISHED WITH THIS
SERVICE LE1TER AT NO CHARGE.
PART NO. DESCRI~TION
1 ea. 110185-685 Decal
1 ea. Compliance Card
1 ea. Service Letter No. S40 instructions
SPECIALTOOLS: NONE
ACCOMPLISHMENT INSTRUCTIONS:
1. Mount decal on center instrument panel 88 indicated in Figure 1.
2. Assure that Revision No. 6 (Model 690C) or Revision No. 4 (Model 685) has been incorporated in the Pilot’s
Operating Handbook.
3. Fill outand mail ComplianeeCa~d.
ELECTRICAL LOAD: NOCHANGE.
WE1OHT AND BALANCE: NO CHANGE.
SPARES AFFECTED: NO.
PUBLICATIONS PIFFECT6D: The Airplane Maintenance Manual change required by this document will be incorpo-
rated at the nelt scheduled revision.
RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service Letter No.
340, dated 24 April 1981, entitled "lnstallation of Placard for use of Altel?late Engine Oil MIL-L-18080", accomplished
Idate)
Page lofZ
1~1 u~’
i~
x
´•Service Lettev CulfstreamAmericanCORPOR*TION
eommandn DluLim
5001 Norm RoclrMII I\vsnus.Bsm´•ny. OXlahon~s 73005
SERVICE LETTER NO 342
18 June 1981
INSPECTION OF ENGINE MOUNT CASTING BOLTS
MODELS AFFECTED: MODELS 680, 69OA AND 69011, SERIAL NOS, 11001 THRU 11566, MODEL 690C, SERIAL
NOS, llM10 THRU 11630 AND MODEL 696, SERIAL NOS. 95000 THRU 95007, 86008 THI(U 95011.
REASON FOR PUBLICATION: TO ASSURE BOLT THREADS ARE NOT BOTM)MINO OUT DUE TO POSSIBLE
MISSINGWASHERS.
COLbPLIANCE: DURING NEXT 100-HOUR INSPECTION.
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE COM´•
PLYING WITH THIS SERVICE LETPER, CONTACT YOUR
NEAREST GULFSTREAM COMMANDER AUTHORIZED
BERVICENTER.
BY WHOM WORK WILL BE ACCOsPUSnED: A L P MECHANIC OR E$UIVALENT.
APPROVAL: FAA DOA SW2 APPROVED.
ESTIMATED MAN HOURS: INSPECT FOR WASHERS THIRTY (30) MINUTES: ADD WASHER FIFTEEN (15)
MINUTES EACH.
PARTS DATA: 1 EACH COMPLIANCE CARD,
NOTE
THE ANBeOC416 WASHERS, IF NEEDED, MAY BE PRQ
CURED LOCALLY.
SPECI*LTOOLS: TORBUE WRENCH.
ACCOMPLISHMENT INSTRUCTIONS:
1. Remove upper and lower cowling shells Ram len and right engines.
2. Inspect leR and right engine mount easting., on both engines, to assure that a washer is installed under each nut
(refer to Figure 1).
S. If a washer is installed under each nut on engine mount easting, reinstall upper and lower eowling shells on engines
and proeeed to step B.
4. If washer is net installed under each nut on engine mount easting, remove nut and install a AN860C416 washer
under nut and to~que 50 to 70 ineh-paunds (refer to Figure 1).
5. Reinstall upper and lower eowling shells on engines.
B. Fill outand mail Compliance Card.
ELECTRICAL LOAD: NO CHANGE.
WEIGHT AND BALANCE: NO CHANGE
Page 1 oIZ
SERVICE LETTER NO. 542
LEFT INST*LLATION SHOWN
RIGHT INSTALLPITION TYPICAL
ENGINE MOUNTCASTING IREF)
i
ASSURE THAT AWASHER
IANSBOC41B) IB INST*LLEO
UNDER EACH NUT ON LEFT
I P,ND Rl(lnT ENGINE MOUNT
CP~TINOS
~rm
80LT6 SnDULO BE TOAOUED SD TO 70
INCH´•POUNDS
ENGINE MOUNT
CASTIN(I IAEF)
iigura i.
SPIRES AFFECTED: NO.
PUBLICP~TIONS AFFECTED: NONE
RECORD COMPLIINCE: Mate an appropriate entry in airplane maintenance records as bllows: Service I,etter No
:141. daud 19 dunr issl, entitled "lnspeetion of Engine Mount Casting Bolta~’ accomplished tdatedi
Pa:e 2 of i
Sevv~e Lettev CuHstreamAmericanCORWR*710N
Camm´•ndsr Dlrllion
IIW1 Norm Rm~wa(l I\vanua,8´•m´•ny, MII´•homs 73ma
SERVICE LETI‘ER NO. 343
18 October 1981
HIGHER WATTAGE PITOT TUBES
IOOELS ~FFECTED: MODEL 680C, SERIAL NOS. 11600 THRU 11685 AND 11109 AND MODEL 695, SERIAL
NOS. 95000 THRU 95055, 95051 THRU 95063.
REASON FOR PUBLICATION: FIELD SERVICE REPORTS INDICATE POSSIBLE FREEZE UP OF EXISTING
PITOT TUBES UNDER EXTREME ADVERSE WEATHER CONDITIONS CAUSING LOSS OF AIRSPEED
INDICATION.
COMPLIANCE: WITHIN NEXT 200 HOURS TIME IN SERVICE.
NOTE
IF ANY PROBLEMS AHE ENCOUNTERED WHILE
COMPLYING WITH THIS SI:RVICE LE~ER. CONTACT
YOUR NEAREST GULFSTREAM COMMANDER
AUTHORIZED SERVICENTER
BY WHOM WORK WILL BE ACCOMPLISHED: A d P MECHANIC OR EQUIVAI.ENT
APPROVAL: FAA DOA SW-2 APPROVED.
ESTIMATED MI\N HOURS: PART I (KIT NO. 1)- NINETEEN (19) HOURS
PART I (KIT NO. 2)- FOURTEEN I14)HOUKS.
PART II (KIT NO. 3)- THREE (3) HOURS
PART III (KIT NO 4)- TWO (2) HOURS
PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SE:RVI(:E LETTER MAY 8E PROCURED THROUGH
YOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR: KIT NO 1 8406.93: KIT
NO. 2 -1588.10; KIT NO. 3 -8351.91; KIT NO. 4 8346.49. REFERENCE THIS SERVICE LETTER, AIRCRAFTMODEL AND FACTORY SERIAL NUMBER WHEN ORDERIFIO SERVICE LETTER NO. 343 KIT CONSISTING OF
THE FOLLOWING:
Kit No. 1 (Part I) Model 690C, Se~inlNos 11600 ttlru i ifif,o
Model 695. Serial Nos. 96000 thlu 9liil´•i0
Kit No. 2 (Part II Model 690C, SerialNoa 116:ii thnl I I G~:
Model 695. Serial No%. Y;)li~ll Illrii BBi;r:. !)5057 thru 95059
Kit No. 3 (Part II) Model 69t. Seriill 1Voa. BBi)ii(l thni ~Ti´•li´•:l
Mode1690C, Ba;ialNo ii_’iiY
Kit No. 4 (Ps~t III) Model 690C, Seriili Nou LICC: I;´•ld i I ~hi
Pa%e 1 of 14
SERVICE LET~ER NO. 545
KI1 ,il Kh
No.l No2 No.a No.4
aTu BTY BTY BTY PARTNO. DEGCRIPTION
1 ea 1 ea 110186-885 Decal
lea lee 110185~881 Decal
lea 833035-1 Relay1 sa 1 ea 1 ea. 1 se. PW11WRWLEFT PitotTube
1 ea 1 as 1 ea. 1 se. PH11W-RW-RIDHT PitotTube
lea lee 1 ea. 20TC4AK-a0 Circuit Breaker SWitCh
4aa 4Ba 820566 Buick Disconnect
ass 2 a. 1211-6-10-12501-61 Circuit Breaker
4ea 4 ea AN880C10L Washer
2 ea MSa1042L04 Nut
4ea 4sa M8210MN04 Nut
4ea 4ea MS21083C3 Nut
?sa 1.a MS26056-112 Terminal Lug2 ea 2 ea MS25056-164 Terminal Lug2 as 2 ea M8ZM136151 Terminal Lug3 as 2 ea MS25181-2 Butt Splice1 as 1 ea MS2121222 Terminal Board
4 se 2 ea MS96201-215 Screw
1 ea 1 ea MS9548811 Cmmmet
1 ea LRM16W-2 Connector Pin
248 248 M608612-129 Wire
lea M1828/1-16 Terminal Lug2ea 2 ea M7928/142 Terminal Lug?ea ?ea M1B2811-61 Terminal Lug26 it 26R 18104419-14-9 Wire
26 8 20R M8104U8-r6-9 Wire
1R M8104418-20-8 Wire
1R M8101U8-22-9 Wire
1 ea lee TA1SM04-2 Cover
1 as lee Iea 1 sa Compliance Card
1 se 1 ea 1 ea 1 ea Service Letter No. 543 Instrue6ans
SPECIPIL TOOLS: NONE.
*CCOMPLISHMENT INSTRUCTIONS;
PART I MODEL B80C, 8ERIAL NOS. 11600 THRU 11883 AND MODEL 696, SERIAL NOY. 85000 THRU 96055, 95051
THRU 85059.
CAUT1ON
oround Operation of the pitotiststic system for an extended
period of time (longer than 15-seeonds) may result in damageto the heating elements.
i. Turn eleetrical system and pitot/static system an and note magnetic compass heading
NOTE
A compass heading must be taken prior to mndi:: -iion Hnd
after modification of the pitot system to check ii; con,paau
deviation.
2. Cain aecesa to airplane batteries through baggage compartment door.
1 Remove baggagt cumpartmcnt liner to e~poio battsnas.
4. DisEonneettenninals fiom both batteries.
8. Remove copilot Best and bar.
P~e 2 of 14
i O 00 72176~10´•12C0781
i OQ8i _,,_
~m
O
(2 PLACE8L
10, q
I~ei o
COPILOT LOWER
CIRCUIT BREAKER PANEL
IREF)
(REF)
21
111111111111111111111111~
TERMINAL BOARD IN MIS AREA USINGM896208´•215 SCREWS AND MS21D14NM NUTS
7r1EW lXX)KING AFT
Figure i.
Pass 9 o( 14
BERVICE LETTER NO. 945
6. Remove right interior side panels to expose electrical wiring and terminal board that is located below emergencyexitwindow.
7. Remove right interior side panel forward of emergency exit window.
8. Remove panel from right eye brow window.
8. Remove cirruitbreakerpanel as follows:
a. Pull copilot control wheel to full aft position and secure,
b. Reach under and behind circuit breaker panel and disconnect electrical connector plugs and wiring
DAUTION
Mark plugs to assure they are reconnected to their respectivemating connector
c. Remove attaching screws from front of panel and carefully remove circuit breaker panel.
d Remove back plate cover from circuit breaker panel.
10. Drill two (2) 0.50 inch diameter holes in DC circuit breaker false panel st positions 30 and 61 to match existingholes in metal panel and install 7277-6-10-12-501-61 circuit breaker (2 places), 110185-895 decal and 110186-697decal (refer to Figure 11´•
CbUTION
Care should be taken so as not to damage false panel when
drilling holes.
WOTE
if positions 30 and 61 are in use, location is optional on rightside of circuit breaker panel.
11. Locate end drill a 0.621 inch diameter hole in circuit breaker back plate cover (refer to Figure i).
nOTE
This hole is for routing new wires through back plate cover.
12. Deburrhole andinstall MS36489-1l grommet.
L3. Locate, drill and install M527212-2-2 terminal board on an side of circuit breaker back plate cover using MS35206-215 screw (2 places) and MS21044N04 nut (2 places). Location should be near hole that was dnlled per step 11Hale size to be 0.113 inch to 0.116 inch diameter (refer to Figure 1)
14 Loweroverhead switch panel as follow.:
CAUTlOhl
When removing slectroluminesoent panels, be careful not to
dan,age or break electrical wiring and connectors. Do notallow panel to hang by the wiring. Panel has to be supportedor damage may occur.
a. Loosen alien screws on all knobs on face of the slactrolumines~ent panels and remove knobs.
b Remove attaching screws securing electrolumineseent panels.
c. Carefully remove panels to expose wiring.
d. Drasp wires and gently pull down until quid disconnect and airplane wiring are exposed, Disconnectelsetrolumineseenl panel
Page 4 of 14
L~RVICE LETTER NO. 549
BEFORE CHANGE
r
i i*ILI5L)*llOL
II II 1(
IUII CIUI LUI
I
,r T ´•I
,11101 1 ikl´• I.*IOI
~*ol´•
6 6
~ir
i..
a
MODEL 890C. YN (1BW THRU 11858 MODEL B9OC. BIN 11551 THRU 11sas
MODEL 885. SIN 85088 THRU 85858 MODEL 1195. SM 85041 THRU 85068
Z.
Page I of 14
BERVICE LETTER NO´• 549
e. Remove attaching acrsxa horn top of metal plate of overhead switch penal.
NOTE
Entire panel will hang in a vertical position and is suapendedby the hinges. This allows for easy access to circuit breakerswitches and electrical wiring.
15. Disconnect and coil and stow wire Nd. 1H26A~6 and wire No. 2H26A18 fmm overhead switch panel (refer to Figure2).
NOTE
Wire No. 1H26A16 is muted hem L PITOTISTATIC circuit
breaker switch (CB8S1) to shunt (811-5) and wire No.
2H25A16 is muted Rom R PITOT circuit breaker switch (CBS
52) to shunt (8116).
16. Remove existing L PITOTISTATIC (10 amp) and R P~OT (15 amp) circuit breaker switches. Discard L PITOTI
STATIC (10 amp) switch and retain R I)ITOT (16 amp) switch for reinstallation at step i?.
17. install existing 16 amp circuit breaker switch, removed in step 16, on overhead switch panel at position labeled L
PITOT1STATIC using existing hardware.
18. install 20TC4AK-20 circuit breaker switch on overhead switch panel at position labeled R ATOT using existinghardwent.
19. Disconnect wire No. 1H25B16 from shunt (SH-S) and disconnect wire No. 2H25B16 from shunt(SH-6). Coil and
stow both wires (refer to Figure 2).
20. Disconnect wire No. 8281\18 from TB 19 and wire No. H2BA18 fmm TB 10 of terminal board that is located below
emergency exitwindow (rafer a Figure 2).
21. Remove terminal lugs from wire No. H28A16 and wire No. H26A16 and install M815181-2 Butt Splices to both
wins (rsfer to Figure 8).
22. Disconnect pitot tube connector from both pitotheads and coil and stow (mfer to Figure 2)
23 Disconnect tube assemblies from left and right pitot tube fittings.
24. Remove four (4) screws attaching pitot tube to mount~ng bracket and remove pitot tubes.
25. Apply a bead of EC 1239 "82" sealant or an equivalent M1L-S-1602C sealant inside pitot tube mounting bracketsand also on new pitot tubes (refer to Figure 4). 6se sealing procedures, Chapter 20, in Airplane MaintenanceManual.
26 Install pitot tube and PW1100-RW-RIGHT pitot tube.
2?. Ensure that pitot tubes are properly sealed to prevent any pressurieation leaks.
18. Form tube an pitot tubes, as necessary, and connect to existing tube assemblies.
29 Install new M608612´•12-8 wire (12 gauge), M8104419-14-9 wire (1( gauge) and M8104418-16-9 wire (16 gauge) and
connect to airplane electrical system. Install 320566 quick disconnects on wires just outside of circuit breaker
panel back plate cover. Silver Solder wires to pitat tube connector using "Alloy C20" solder (refer to Figure 3).
NOTE
Connect wires M terminal board, installed in step 13, usingMS21083C3 nutr nnd AN960C10L washers. Route new
wires along existing wire bundles if possible.
30. Install TA1SM04-2 cover on terminal board installed at step 13.
Page 5 of 14
IERYICE LETTER NO. 545
ATTER CHANGE
IM926058164 LPITOTISTP~TIC RPITOT
TERMINAL LU(I HEATCONTROL HEAT CONTROL
M525038´•157
iCpll.,,,12 PLS1
(2PLS1
mls*ll
cul*1, au~
MIOIBII´•11-BWIREU6
t
M527212´•22 T´•BO~AD
MS152~8´•216 SCREWi~uclbr
sapn*n.
n. ran,´•~HEnrEn~4´•: I,
,,,,,,EnrERLPITOT
6WIRE 8
POWER WIRE PIPPROX
PITOT)
11 1(
;_g~___j_J oc cs PANELCIRCUITBREAI(ER
(2~LS) M81D14/8´•1B8WIRE
520580I(IUICK DISCONNECTC yll MSZ518(´•2 BUTT SPLICE
14 PLSI n
mnodale~lsswlnl
ms261n´•2 suTT 9PLICE I Hits
~xl
MB(OM/9´•22´•8WIRE
lUI
*1~(´•
4.8TATIC
PORT I
Ivrn C CIRloHn
*LLlq
-I´•_
OWO-10
,OT.I: "i ’I C(4 ´•V´•IIOLD’RW1"E’ IO ´•ImT
mNNerrOAI UIIIWO ´•´•~LLOY No.lo-.
HIIII*OTIHIIR*TYREOI-~LLOI NO. 10* (IOLDIR is ERE"P.
UIE LUO WITH (l(il\. WIRE
Uli. HJ2~OPI´•(IITLRMIN*L LV(Io* IHUNT I~Wbl
Y9E M310YI´•l(n TIRMIN*L LUO ON (HUNT l)n´•81 rO(iii iiMiC SIN I.´•.IU I(IRU 11RSOYIIE M1828116( TERMIN~L LYD WITH 110~´• WIRE
WODII i95 S/N BEOi;’; THAU 3M14(1Y~E LUD WIIH ((IGI\. WIRE
Ylil MIB?II1´•ll TER~INI\L LUB WITH 22 01\. WIRE
Page? of 14
BE~VICE LETTER NO. 543
AFTER CHANGE
~eTunaol iI~nroTipr*nE R PltOTM9280SB´•184TERMINAL LUO HEAT CONTROL HEAT CONTROL
MS2505B151TERMINAL LUO
rZPL8I
I*~L((
C *7111 51--~11 IYI
MS088/2´•12-gWIREWb
t
MS21212-2-2 T´•BOAAOM5)6206´•21JSCREW
M8104419´•(bg s~cror NUTEBI~NII
LPITOTII--~ rlll
R PITOT
HEATER ´•´•´•10 REATER
~(I) I rid
"8" ,I, ,ND WIRE&
WWER WIRE ~PPROX
12~’ ILILR PITOT)11
~zn´•6´•lol2´•smsl,CIRCUIT BREAKER
12 PLS) T
320588 (IUICI( DISCONNECT
I4PLS)
M810P~/8´•1SBWIRE
MSZ61812 8UTT
12 PLSI ,,I,, r*~u*,ol,,
\1 ~x,
-9,
ponr
IHlaHn
STATIC
ur~nni
ILEFTI
NOTL~: ´•661LVlR IIOLOIR WIRES TD ´•llOT
0686601056 USINI) IILLOY NO. Soil.
MIITINO TEMPERATURE OI´•´•*LLOY NO´• II´• (IOLDIR iS 56101.
UIE TIIMIN~L LYLI WIM 12 (I*. WIRT
UsE M125ml´•161 rrlMIN*L LUB ON SHUNT 16Hbl EFFECTIY1TYUlil MIIRP~´•1I TERMINIL LYO ON SHUNT (6HBI MODEL 8808 8/N 11851 THRU 11883USE MIB~/ldl TERMINI\L LYO WITH 110A´• WIRI MODEL BgS S/N 05041 THRU 85055USE Mle~llll2 TIRMINII LYO WITH (I (II\. WIRI
USE MIBIII1´•ll TIRMINI\L LU. WITH 11DA. WIRE AND 95051 THRU 85058
i:ipur~ i. IShn,, 2~1 2i
PPge B of 14
8ERYICE LETTER NO. 545
81. Reinstall circuitbreakerpanel asfollows:
a. Install back plate Fever and secure with attaching screws.
b. While supporting circuit breaker panel, close to its mounting position, connect electrical connector plugs and
mnng.
c. Position circuit breaker panel for installation and secure with attaching screws.
d. Release central wheel and allow it to move forward.
32 Reinstall overhead switch panel as follows:
CAUTION
When installing the overhead switch panel, ensure that all
wires and busses are properly secured and not squeezedtowards airframe. This will prevent possible short circuits,
a. Swing overhead switch panel up and secure with existing screws.
CAUTION
To prevent bending of panel, do not over-torque screws.
b. Connect electroluminescent panel wiring to airplane wiring and position panel for installation Stow any
excess wiring to ensure that it will not be pinched or crimped when panel is secured,
c. Secure electroluminescent panels with existing screws.
d. Reinstall all existing knobs and secure with existing alien screws.
33. On Model 690C, serial numbers 11661 thru 11665 and Model 695, serial numbers 96041 thru 95055, 95057 thru
95059, proceed to step 35.
34 On Model 680C, serial numbers 11600 thru 11650 and Model 695, serial numbers 95000 thru 95040, proceed as
follows:
a. Remove right baggage compartment liner to gain access to terminal board and P48 connector located just
forward of fuselage station 239.15 (refer to Figure 5).
b. Locate, drill and install 833038-1 relay on existing channel using MS35206-215 screw (2 places) and
M821040L04 nut (2 places) (refer to Figure 5).
c. Disconnect wire No. H26A16 from pin AA of P48 connector (refer to Figure 2).
d. Install new wire No. H26BB16 (M8104418-18-9) on pin AA of P48 connector using LPM16W-2 connector pin
and connect to AS of 855058-1 relay (K?a) (refer to Figure 5).
e. install new wire (MB10(4is´•18-9) an A2 of 853038-1 relay (K72) and hutt splice to existing wire No H26A16
using MS251812 butt splice (refer to Figure S).
Install new wire No. H26AA20 (M8104418-20-9) on 833038-3 relay (K721 from A2 to X1 (reLI to Figure 3).
g. Install new wire No. H??AZ2 (M81044~-22-9) ham X2 of 838038-1 relay (K72) to TA4 of terminal board (refer
to Figure 3).
h. Proceed to step 35.
35. Reconnect terminals tobatteries.
36. Functionally test pitot heat system.
Page 8 of 14
8ERVICE LETTER NO. 543
gL
FUSELAGE SKIN
(REFI
MOUNTING BRACKET
e, IREFI
O
SEAL WITH ECIPs’~82"SEALANT OR I\N EOUIVALENT
MIL-976(12C8EALANTO
ATTACHINGFURNISHEO WtTH
P1TOT TUBES
PHIIOORW-LE~T
PITOT TUBE ((1Br)
Fipura 1
Page 10 of 1(
SERYICE LETTER NO, 549
31. Pelfonn pibtststic system check as outlined in Chapter 84 of the Airplane Maintenance Manual to aesure there
are no leaks.
CAUTION
Omund operation of the pitatiatatie system for an extended
period of time (longet then 15-seconds) may result in damageto the heating elements.
SE. Turn electrical system and pitotistatie system on and note compass heeding. Note any deviation from originalheading, taken in step1., and note deviation on devialon card. Deviation shall not exceed 10 degrees. If
deviation exceeds 10 degrees, reswing magnetic compass as necessary.
58. Reinstall liner in baggage compartment.
10. Reinstall interior side panels andeyebrowpane.
41. Reinstall eopilotseat and bar.
42. Insert Figure 3. wiring diagrams in Airplane Maintenance Manual for troubleshooting purposes.
43 Fill out andmail Compliance Card.
44. Roceed to ELECTRICAL LOAD.
PIRT II Modal 880C, Serial No. H7W IND MODEL 885, SERUL NOS. 950%0 THRV 85083.
CAUTION
Dround operation of We pitotistatic system for an extended
period of time (longer than 1S´•aeconds) may result in damageto We heating elements.
1 Turn electrical system and pitotiststie system on and note magnetic compass heading
MOTE
A compass heading must be taken prior to molfication and
aRer modification of the pitot system to cheek for compassdeviation.
2. Loweroverhesdaviteh panel asfollows:
a. Ensure that electrical power is removed.
CAUTION
When removing slectmluminescent panels, be careful not to
damage or break electrical wiring or connectors. Do not
allow panel to hang by the wiring. Panel has to be supportedor damage may occur
b. laoaen alien screws on all knobs on face of the eletmluminescent panels and remove knoba
c. Remove attaching screws securing electroluminescent panels.
d. Carefully remove panels to expose winng
e. Orasp wires and gently pull down until quick disconnect and airplane wiring are exposed. Disconnect
electrolumineasent panel.
f Remove attaching screws from top of metal plate of overhead switch panel
page 110114
SERVICE LETTER NO. 345
ALL 833038´•1 RELP~YEXISTING CHANNEL
EXISTING RELAYS
MSZIMILY
EXISTING CHI\NNEL
STArlNG
CONNECTOR IREFI
FW
FICnS.
NOTE
Entire panel will hang in a vertical position and is suspendedby the hinges. This allows for easy access to circuit breaker
switches and electrical wiring.
3. Remove existing L PITOTISTATIC (10 amp) and R PITOT (15 amp) circuit breaker switches Discard L PITOTI
STATIC (10 amp) switch and retain R PITOT(1S amp) switch for reinstallation at step(
4. Install existing 15 amp circuit breaker switch, removed in step a. on overhead switcii panel at petition labeled L
PITOTISTATIC using existing hardware.
5. Install 20TC4AK-10 circuit breaker switch on overhead switch panel at pouitioll inl;l´•iri( H 1’11‘01‘ using existinghardware.
6. Reinstall overhead switch panel as follows:
CAUTION
When installing the overhead switch panel. ensure that all
wires and busses are properly secured and not queeppdtowards airasme This will prevent possibir xholt ´•ireeir´•
a Swing overhead switch panel up and secure with existing screws
b. Connect eleetroluminaseent panel wiring to airplane wiring and positio,i pilnr! tbl in;i;ll;itli,n Stow any excess
wiring to ensure that it will not be pinched or crimped when panel is iruiireii
Page 12 of 14
8ERVICE LETTER NO. 545
c. 8eoure electmlumineaeent panels with exiatingaorews.
d. Reinstall all existing knobs and secure with existing alien screws.
Removeandraplace Isttendrightpit~ttube sssembliesasfollows:
a. Disconnect tube assemblies from left and right pitot tube Bttinga.
b. Remove four (4) screws attaching pitot tube to mounting bracket and remove pitot tube.
c. Apply a bead olEC 1238 "B2" sealant or an equivalent MIL-S-1602C sealant inside pitot tube mounting bracket
and also on new pitot tubes (refer to Figure 4). see sealing p100SdUIeel Chapter 20, in Airplane Maintenance
Manual.
d. Install PH1100-RW-LEFT pitot tube and PH1100RW-RIGHT pitot tube.
e. Ensure that pitot tub., are sealed properly to prevent any pressurization leaks.
r Form tube on pitot tubes, as necessary, and connect to existing tube assemblies.
8. Functionally test pitot heat system.
g. Perform pitatistatic system check as outlined in Chapter 34 ofthe Airplane Maintenance Manual to assure there are
no leaks.
CAUTION
Ground optation of the pitotistatic system for an extended
period of time (longer than fS-semnds) may result in damageto the heating elements.
10. Turn electrical system and pito~static system on and note compass heading. Note any deviation From original
heading, taken in step i., and note deviation on deviation card. Deviation shall not exceed 10 degrees. If
deviation exceeds 10 degrees, reswing magnetic compass as necessary.
11. Fill out and mail Compliance Card
12. Proceed to ELECTRICAL LOAD.
PART III- MODEL BgOC, SERIAL NOS. 11884 AND 11BBS.
CAUTION
Ground operation of the pitotistatic system for an extended
period of time (langer than 1S-sscondsl may result in damageto the heating elements.
1. Turn electrical system and pitotstatic system on and note magnetic compass heading.
NOTE
A eampsss heading must he taken prior to modiReation and
after modification of the yitot system to check for compass
de~iation.
2. Ensure that electrical pwer is removed
3. Remove and replace left and right pitot tube sssembljas as follows:
a. Diseonnect tube aane~nbliel from left and righl pitot tube Littings
b. Remove four (41 screws attaching pltot tube to mounting brael~et;l:ld remove pitot tube.
Page liul!a
8ERVICE LETTER NO. 545
c. Apply a bead of EC 1288 "B2" sealant or an equivalent MIL-S?SOZC sealant inside pitot tube mounting bracket
and also on new pitot tubes (refer to Figure 4). 8ee sealing prooedures, Chapter 20, in Airplane Maintenance
Manual,
d. Install PH1100-RW´•LEFT pitat tube and PH1100-RW-RIoHT pitot tube
e. Ensure that pitot tubes are sealed properly to prevent any pressurization leaks.
e Form tube on pitot tubes, as necessary, and connect to e~iating tube assemblies.
4. Functionally testpitot heat system.
5. Perform pitotistatic system cheek as 84 of the Airplane Maintenance Manual to assure th.re are
no leaks.
CAUTION
Ground operation of the pitotistatic system for an entended
period of time (longer than Ii-seconds) may result in damageto the heating elemente.
6. Turn eleetrical system and pitotistatic system on and note compass heading. Note any deviation from original
heading, taken in step 1., and note deviation on deviation card Deviation shall not exceed 10 degrees. If deviation
exceeds 10 degrees, reswing magnetic compass as necessary.
7 Fill outandmail ComplianceCard.
ELECTRICAL LOAD: PART I -18.4 AMPS
PART II -18.4 AMPS
PART 1I1 -18.4 AMPS
WEIGHT PINO BALANCE: NO CHANCE.
SPARES AFFECTED: NO,
PUBLICATIONS AFFECTED: The Pilot’s Operating Handbook, Ai~lane Maintenance Manual and Illustrated Parts
Catalog changes required by this document will be inmlpaeted at the next scheduled revision
RECORD CO~PLI*NCE: Make an appropriate entry in airplane maintenance records as follows: Service Letter No.
343. dated 18 October 1051, entitled "Higher Wattage Pitot Tubes", Part I accomplished (date) Part II
accomplished (date) Pan III accomplished (date)
Page 14 of 14
Service Letter Gulfstream AmericanCORPORA~ION
Conmau(n Divbion1001 Norm Rak~wll I\uanu´•.Bathany. OLI´•hoM 13(108
SERVICE LETTER NO. 344
10 July 1981
MAIN LANDING GEAR TORCIUE LINK SHAFT REPLACEMENT
YODELS AFFECTED: MODELS 680FL(P), 680’1, 630V AND 680W, SERIAL NOS. 1261 THRU 1854, MODEL 681, 6E´•
RIAL NOS, 6001 THRU 8012, MODEL 685, SERIAL NOS. 12000 THRU 12066, MODEL BgO, SERIAL NOS. 11001
THRU 11018. MODEL 8gOA, SERIAL NOS. 11100 THRU 11344, MODEL 680B, SERIAL NOS, 11560 THIRI 11666,MODEL 680C. SERIAL NOS, 11800 THRU 11816 AND MODEL 806, 8ERIAL NOS. 95000 THRU 850?5.
REASON FOR PUBLICATION: SHAFT FAIL~EI COULD RESULT M MAIN LANDING GEAR MALFUNCTION.
COMPLIANCE: NEXT 100-HOURS TIME W 8A~RVICE.
MOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE COM-
PLYING WPTH TH1S SERVICE LETTER, CONTACT YOURNEAREST OULFSTREAM COMMANDER AUTHORIZED8ERVICENTER.
BY WHOM WORK WILL BE ACCOMPLISHED: A d P MECHANIC OR EQUIVALENT.
APPROVAL: FAA DOA 8W-2 APPROVED.
ESTIMATED MAN HOURS: FOUR (4) HOURS.
PARTS DATA: REPLACEMENT ED12406-1 TORQUE LINK SHAFT, ED1S973-1 BUSHINGS, ES12106-1 TORQUELINK ASSEMBLY OR ED12452 THRUST RING MAY BE PROCURED THROUGH YOUR NEAREST GULESTREAM
COMMANDER AUTHORIZED SERVICENTER. ONE (1) EACH COMPLIANCE CARD 18 FURNISHED WITH THIS
SERVICE LETI~ER.
MOTE
MODEL B80FL(P) USES FF612-2 BUSHINGS INSTEAD OF
ED13313-1 BUSHINGS AND ES1O405 TORQUE LINK AS-SEMBLY INSTEAD OF ES12405-1 TORQUE LINK A88EM-BLY.
SPECIAL TOOLS: NONE.
ACCOMPLISHMENT INSTRUCTIONS:
1. Jssk airplane as outlined in the applicable Airplane Maintenance Manual.
2. Reduce hydraulic pressure to zero by applying brakes or by actuating wing naps.
3. Remove bungee mads from left and right main landing gear strut lower pulleys.
4. Push up on drag brace and allow gear to go overcenter a facilitate removal of torque link shaft. Assure that gearis properly supported.
5. Remove safety wire from torque link shaft attaching bolt (refer to Figure 2).
Page 1 of 4
BERVICE LET~ER NO. S44
ED(1~2 THRUST RING
!REF1
Eol2´•oel ronoua
1LINK SH~FT IREF)
TOR(IUE LIWK
RuSHlNa (nEFI
LINK ~69Y
(REF)
t
LINK
gsusHINa IREF)
STRUTASSY IREF)
RLnt.
Page a of 4
SERVICE LETTER NO. 544
FWD
TORQUE LINK SHI\FT IREF)AN4HIA
TOR(1UE LINK SHI\FT
RET*1NINO BOLT
TORQUE 50 TO 70 IN´•LBS.
BLEEDERPLUOIREFI
VIEW LOOKING DOWN ON MAM LANDING GEAR 8TRUT ASSY CTYP)
TOBOUE LINK SHAFT RETPIININO BOLT
MUGT BE (II\FETY WIRED *S SHOWN
TO PREVENT WIRE FROM 8LIPPIN(I
OVER TOP of BOLT HEnD nhlo OVER
TOP OF BLEEDER PLUO AND I\LLOWINB
BOLT I\NDIOR BLEEDER PLUO TO LOOSEN
FIWa 2.
Page 3 of 4
SERVICE LETTER NO, 5(4
6 Remove bolt that secures torque link shan (refer to Figure 2).
Remove torque link shaft and check for the following (mfer to Figure II:
a. Length of torque link shalt should be 4.18 inches. If shaft is not 4.18 inches in length, replace with new
ED12406-1 torque link shaft.
b if existing torque link shaft is 4.18 inches in length, inspect for straightness of shaft and wear at thrust ring
contact points Replace with new ED12(06-1 totque link shaft as necessary.
e. Cheek holes in thrust ring, through which torque link shah paste., for elongation. Replace with new ED12452
thrust ring as necessary.
d. Check bushings in to~ue link assembly for wear and possible cracks. Replace with new ED1S313-1 bushings
as necessary.
NOTE
Model 680FL(P) uses FF-612-2 Bushings.
e. Cheek existing torque link assembly for cracks end excessive wear. Replace with new ES12406-1 torque link
assembly as necessary.NOTE
Model 680FL(P) uses ES11IOS torque link assembly
e Assure that existing bolt (P~ AN4H4A) that secures torque link shaft is proper length as shown below.
1 17/32´•1 NOMIN~L
nN~Hdn BOLT
8. Install elisung or new ED12406-1 torque link shah through strut assembly and torque link assembly. Assure that
flat spot in center of shalt is aligned perpendicular to bolt hole (refer to Figure 2).
9. Ileinatall existing or new ANIH~A bolt to secure torque link shaft, torque 50 to ?0 inch-pounds and safety ulre
to bleeder plug (refer to Figure 2)
10. Remove support from main Lending gear and allow gear to go down and locked
Ii. Reinstall bungeecordson lowerpulleys.
12. Functionally check landing gear system as outlined in the applicable Airplane Maintenance Manual
13. Remove simlanejaeks.
14. Fillautandmail Compliance Card.
ELECTRICAL LOAD: NO CHANCE.
WEKIHT IND BALANCE: NO CHANDE.
SPIRES AFFECTED: YES
PUBUCPITIONS *FFECTED: The Illustrated Part. Catalog and Airplane Maintsnance Manual changes required by
this document will be incorporated at the next scheduled revision.
RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service Letter No.
344, dated 10 July 1081, entitled "Main Landing Gear Torque Link Shaft Replaeement",aeEompliahed (date)
ppgedofd
SE RVICE PUB LI CATIONSGulfstreamAmerican
revision notice (-OHI´•OR*TII)N
Conlmanda Div*ion
~001 North Rakwsll /wsnus.
Bathsnyl Otlshoma 13008
SERVICE NO. 345
REVISION NO. 1
21 May 1882
VERTICAL STABILIZER ATTACH BOLT INSPECTION
APPROVAL: FAA DOA SW-2 APPROVED.
Page 3 of g Figure 1. (9heet 1 of 2)
ADD: NOTE allowing use of nush head aorews to attach door.
~CCOMPLISHMENT INSTRUCTIONS- PART I
Page 5 of 9
CHANGE to reed: 8.e. If hale is damaged, it is acceptable to usa AN61 bolt (0.315"10.319" diameter hole) Ionly if an edge distance of 0.S6-inch or more can be maintained.
8.e. If it is determined, prior to reaming enisting hole, that an edge distance of 0.66-inch
or more can be maintained, ream damaged hole to 0.376"10.319" diameter and install
AN6-7 bolt, ANOBODBIG washer (under nut only) and M517825´•6 nut. Torque bolt 300 1to 330 inch-paunde by tightening nut to low side of torque range end, if necessary,
continue to tighten until a slot aligns with hole in bolt. Install M524665-134 cotter
pin (refer to Figure 3).
W07E
An additional AN960DB16 washer may be installed (under
nut only), if necessary to assure proper alignment of hole in
bolt with slete in nut.
P.CCOMPLISHMEKI INSTRUCTIONS- PART II
Page 8 of 9
CHANGE to read: 10.e if holes are damaged, it is acceptable to use AN6-? bolt (0.91S"i0.318.’ diameter holel I
only if an edge dists~nee of 0.56-ineh or more can be maintained.
lo.e. If it is determined, prior to reaming elisting hales, that an edge distance of 0.56-inch
or more can be maintained. ream damaged hale or holes to 0.575"10.379" diameter and
install ANB-? bolt, M880D616 washer (under nut only) and M811825-6 nut Torque Ibolt 900 to 330 inch-pounds by tightening nut to low aids of torque range and, if
necessary, cantinue to tighten until a slot aligns with hole in bolt. Install MS14865-
134 cotter pin (refer to Figure 3).
Page 1 of 2
Service Letter GulfsrreamAmericanL:ORPOR*TI(IN
Commndn Mvlon
6001 Norm Roc~well Avanus.Bamany, O*(´•hsM 73(*18
SERVICE LE1TER NO. 945
18 January 1882
VERTICAL STABILIZER ATTACH BOLTS INSPECTION
MODELS AFFECTED: PART I´• MODELS 690, 690A AND B90B, SERIAL NOS, 11001 THRU 11566. MODEL
690C, SERIAL NOS. 11800 THRU 11629 AND MODEL 695, SERIAL NOS. 95000
THRU 95010.
PART II MODEL 690C, SERIAL NOS llBSO THRU 11881 AND 11709 AND MODEL 695.
SERIAL NOS. 95011 THRU 95019.
REASON FOR PUBLICATION: A. TO CHECK FOR POSSIBLE IMPROPER WASHER INSTALLATION
RESULTING IN ERRONEOUS TOR9UE READINGS. IMPROPER
INSTALLATIONS CAN CAUSE CRACKS IN HORIZONTAL SPAR
B. REMOVAL OF TWELVE (12) MONTH OR 600 HOURS REPETITIVE
INSPECTION.
COMPLIANCE: WITHIN NEXT 100-HOURS TIME IN SERVICE.
NOTE
INSTALLATION OF CASTELLATED NUTS PER THIS
SERVICE LETI~ER‘rYILL REMOVE THE RE$UIREMENTFOR TWELVE (121 MONTH OR 500 HOURS INSPECTION
OF THE VERTICA1, STABILIZER ATTACH BOLTS AT
FUSELAGE STATION 408.66 AS STATED IN THE
AIRPLANE MAINTENANCE MANUAL.
IF ANY PROBLEMS ARE ENCOUNTERED WHILE
COMPLYING WITH THIS SERVICE LETTER, CONTACT
YOUR NEAREST GULFSTREAM COMMANDER
AUTHORIZED SERVICENTER.
BY WHOM WORK WILL BE ACCOMPLISHED: A 8r P MECHANIC OR E9UIVALENT.
APPROVAL: FAA DOA SW-2 APPROVED.
ESTIMP~TEDMANHOURS: PART I- FOURTEEN(ld)HOURS.PART II- FOURTEEN (14) HOURS.
PARTS DATA: PARTS REGLUIRED TO COMPLY WITH THIS SERVICE LETTER MAY BE PROCURED THROUGH
YOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR: PART I 880.09: PART II
816.51. REFERENCE THIS SERVICE LE1TER, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN
ORDERING SERVICE LETTER NO. 361 KIT CONSISTING OF THE FOLLOWING:
Page 1 ol 8
SERVICE LETTER NO. 366
KF NO. 1- PART I
KB NO. 2 PART II
Kit No. 1 Kit No. 2
BTY qTY PART NO, DESCRIPTION
1 se, t as. 311011-9 Door
1 es. 1 ea. 511017-6 Doubler
1 ea. 1 ea. 511017-1 Angle1 ee. 1 as. 311011-9 Angle
1 ea. 1 ea. 311017-11 Doubler
1 ea. 1 as. 311011-19 Doubler
4 ea. AN5-6 Bolt
4ea. ANBBOD61B Washer
4es. MS11825-6 Nut
10ea. 10 as. MS2104?LS Nutplate4ea. M92(BBS´•1S2 Cotter Pin
10 ea. 10 ea. MS21098´•1-10 Screw
i ea. 1 ea. Compliance Card
1 ea. 1 ea, blvice Letter No. 546 Instructions
SPECULTOOLS: TORBUE WRENCH WITH 930 INCH-POUND CAPABILITY.
ACCOLbPLISHMENT INSTRUCT)ONS:
WOTI
Bolts to be inspected are located st fuselage station 408.66
and attach the vertical stabilizer to We horizontal stabilizer
front spar. Instructions are provided for installing an access
door, just aft of fuselage skin lap aft of station 396.82, to
provide easy access to empnnage attach bolts.
PARTI
1. Make a rough cutout (smaller then hole in 311011-6 doubler) in left side of aft fuselage, just ah of fuselage shin lapaft of station 386.82, for installation of an access door (refer to Figure i).
WOTE
Cutout is to be just large enough to insert 311011-5 doubler
through skin and enable mechanic to work through hole,
Cutout is to be enlarged to match cutout in 511011-6 doubler
after doubler is positioned in place for drilling per step 3. a.
Cutout is to be between longemns number 5 and number 7.
The top longeron (centerline of airplane) is longeron 0.
Longerona are numbered munterrlackwiss for the left side
while looking forward and are numbered O, 1, 2 and so forth.
Longeron number 6 does not extend past fuselage station
986.82.
2. Remove rivets through fuselage akin and Longemns, forward and aR of door cutout, as necessary to install 311011-6
doubler.
3. Locate, drill and install 311011-5 doubler, 311011-11 doubler, 811011-15 doubler, 911011-9 angle and 511011-7 angle
on sft fuselage as follows (refer to Figure 1):
a. Locate 311017-5 doubler on fuselage and drill all rivet attach holes and enlarge cutout in skin to match door
cutout in doubler. Drill the upper 8vs (5) nualate attach holes thmuQh skin and doubler. The lower five (6)
nutplates will not be attached through skin.
Page 2 of O
IERVICE LETTER NO. 545
6 LON(IERDN
31(0(7´•11 ~J _MS20170P~D4 RIVET OR MS200001\WW2 BLIND RIVET
DOUBLERNP~1097AD4 RIVET
511017´•5 DOUBLER
NO.S
LONOERON
311(1119 DOOR
7
0 DOOR311017´•11
IAEF)
CONSTANTMS2~10ADI
ORMS2OBWI\D4W2
RIVET
311017´•15 O.j7~’51(017´•7
ANGLE
NAS1D87ADI RIVET
NO. 7
VIEW AA
0.30LoNaEnON
MS20470AD4RIVET t
oRr
o~a´•´•Mszwaonplwl
BLIND
RIVETDOUBLER
IREF)DOUBLER
NI\BIOB~AW ~(1 (REF1RIVET ll(l i LON(IERON
VIEW CC
31101)´•´•8
ANGLE (REF) 3110179 DOUBLER
-I I-´•´•´•´•´•´•U´•MS28470nDI
RIVET
MIUWWPIYW2
BLIND !III illRIVET
7 DOUBLER ACCEPTABLE TO TRIM
NIU11081AW (REF) 5110176 DOUBLER TO
RIVET CLEAR RIVET ON
7 FUSELAGE ITYP~PL8)
LONGERON
VIEW BEFICn i. ism 1 ot 2)
PPge 4 d B
SERVICE LETTER NO. 545
NOTE
Trim forward and aR ends of 511017-6 doubler, as necessary,a maximum of 0.GO-inch to prevent interference with rivets.
b, laeate 511011-7 angle, 311017-9 angle, 311011-11 doubler and 311017-13 doubler on fuselage and drill allattach holes.
c. Remove all parts from fuselage and deburr all holes.
d. Lightly countersink all holes in doubler that match original existing holes in fuselage skin to allow for dimplesin skin.
e. Install 311011-11 doubler and 511011-15 doubler on existing longerons (inboard nanges only) usingMS20470AD4 rivets or M820600AD4W2 rivets.
f Position 5110115 doubler in place, slide doubler up and install lower five (5) MS21047L3 nutplates on doublerusing M820426AD3 rivets.
g. Reposition 311011-6 doubler in place and install doubler, 311017-1 angle and 311017-9 angle usingNAS1097AD4 rivets.
h. Install upper five (5) MS21047L3 nutplates using M820426ADS rivets.
4. Remove left and right rudder central linkage access doors that are locatedjust aft of fuselage station 409.66.
5. Remove screws attaching tail cone.
6. Discanneet electrical wiring from tail position lights and remove tail cone.
Install tail stand on tail skid.
8. Remove and replace existing ve~ical stabilizer attach bolt (4 places), one st a time. as follows (refer to ngure 2):
a. Remove bolt and inspect bolt hole for possible damage.
b. If hole is not damaged, install AN5-6 bolt, ANBB0D616 washer (under nut only) end M917826-5 nut. Torque bolt
160 to 200 inch-pounds by tightening nut to low side of torque range and, if necessary, continue to tighten untila slot aligns with hale in bolt. Install M824666-132 cotter pin (refer to Figure 3).
NOTE
An additional AN860DS16 washer may be installed (undernut only), if necessary, to assure proper alignment of hole in
halt with slete in nut.
c. If hale is damaged, it is acceptable to use ANG´•B bolt (0.915"m.319" diameter hole) only if an edge distance of0.5B-inch or more can be maintained.
d. If it is determined, prior to reaming existing hale, that an edge distance of 0.56inch or more cannot be
maintained, contact aulfstream American Corporation, Commander Division, Customer 8ervice Department,Bethany, Oklahoma 73008 far further instructions.
a. If it is determined, prior to reaming existing hole, that an edge distance 90.86-inch or more canbe maintained,ream damaged hole to 0.375"10.379" diameter and install ANB-B bolt, ANBBODB1B washer (under nut only) andM817826-8 nut. Torque bolt 500 to 330 inoh´•pounds by tightening nut to low side of tarque range and, if
necessary, continue to tighten until a slot aligns with hole in bolt. Install M824665-134 cotter pin (refar to
Figure S).
NOTE
An additional AN9B0D616 washer may be installed (undernut only), if a assure proper alignment of hole in
bolt with slots in nut.
Page 5 oIO
PIERVICE LETTER NO. 545
CONTROL LINKPIGE
ACCESS woR IREF)
VERTICAL ST*BILIIER
88/\0 IREFI
HORIZONT~L
8SnBILIZER
FRONT 88/(0
D goO [)Ooo~ O
o ooo
o.oD O
o. qo oD
O Ooo
o´•O 00
wnsHa8o
luNoER NVT ONLY)
Ms~lat6a*vr
o M924W8´•132 COTTER PIN
o o TOROUE 180 TO 280 IN-LBS
14 PL8)O O
0000
O 00 O
ooooo oo
NOTE
VIEW LOOKING FORWARD 00 NOT INSTP~LL ANY WASHERS
AT FUSELAGE STA. 409.56 05080 HEnO of BOLT
Flpura 2.
PngeBofB
8ERVICE LETTER NO. 546
I\DDITIONI\L WASHER MAY BE
USED IF REOVIRED TO ALIGN
HOLE IN BOLT WITH 8LOT IN NUT
VIEW SHOWIN(1 INCORRECT VIEW SHOWING CORRECT
ALI.NMENT OF HOLE IN BOLT ALIGNMENT OF HOLE IN BOLT
FIIPrs 3.
8. Raconnect electrical wiring to tail position lights and reinstall tail cone on airplane using existing hardware.
15. Reinstall left and right rudder control linkage access doons using existing hardware.
ii. Install 311017-8 door using MS21038-1-10 screw (10 places) (refer to Figure 1).
12. Touchup paint as necessary.
13. Fill out and mail Compliance Card specifying that Part I has been accomplished
PART II
i. Make a rough cutout (amaller than hole in 311017-5 doubler) in left side sR fuselage, just aft of fuselage skin lap
aR of station 586.82, far installation of an access doar (refer to Figure 1).
NOTE
Cutout is to be just large enough to insert 311011-5 doubler
through skin and enable mechanic to work through hole.
Cutout is to be enlarged to match cutout in 311017-5 doubler
after doubler is positioned in place for drilling per step 3. a.
Cutout i. to be between longemna number 5 and number 7.
The tap langeron (centarline of airplane) is longeron 0.
Longerans are numbered counterclockwise forthe left side
while looking forward and are numbered O, i, 2 and so forth.
Longemn number 6 does not extend past fuselage station
388.82.
2. Remove rivet through fuselage akin and longsmns, forward and aft of door cutout, as necessary to install 511017-6
doubler.
3. Locate, drill and install 511011-6 doubler, 311017-11 doubler, 311011-15 doubler, 511011-8 angle and 511011-7 angle
on aft ti~aalage as follows (refsr to Figure 1):
a. Locate 811017-5 doubler on fuselage and drill all rivet attach holes and enlarge cutout in skin to match door
cutout in doubler. Drill the upper Eve (6) nutplats attach holes through skin and doubler. The Lower five (5)
nutplates be attached through akin.
NOTE
Rim forward and an ends of 51101’1-6 doubler, as necessary,
a maximum of 0.P0-inch to prevent interference wit rivete.
b, lacate I11(111-1 angle, 811011´•8 angle, 51101111 doubler and )11011´•11 doubler on fi~selage and drill all
attach holes.
Page? at 8
SERVICE LETTER NO. 545
c. Remove all parts from fus.lage and deburr all holes,
d. Lightly countersink all holes in doubler that match original existing holes in fuselage skin to allow for dimples
in skin.
e. Install 311017-11 doubler and 511017-15 doubler on existing longerons (inboard Ranges only) using
MS20470AD4 rivets or MS20600AD4W2 rivets.
t position 311011-5 doubler in place, slide doubler up and install lower 8vs (5) MS21o4?L3 nutplates on doubler
using MS20(26AD3 rivets.
g. Reposition 511011-6 doubler in place and install doubler, 311017-1 angle and 311017-9 angle using
NASlOg7AD4 rivets.
h. Install upper Rye (5) MS21047LS nutplates using MS20426ADS rivets.
4 Remove left and nght rudder control linkage access doors that are locstedjust aft of fuselage station 409.56.
5. Remove screws attaching tail cone.
6. Disconnect electrical wiring from tail position lights and remove tail cone.
Install tail stand on tail skid.
8. Inspect four (4) bolts attaching vertical stabilizer to front spar of horizontal stabilizer for presence of washer
under bolt heads (refer to Figure 2).
9. If there are no washers under bolt heads, proceed as follows:
a. Assure that nut. are secured properly with cotter pins (refer to Figure 3).
b. If nuts are not secured properly, remove cotter pin and nut, Install an additional AN960D616 washer (under nut
only), reinstall existing nut and torque 180 to 200 inch-pounds by tightening nut to Low side of torque range and,
if necessary, continue to tighten until a slot aligns with hole in bolt. Install existing or new M524665-132 cotter
pin.
c. Proceed to step 11.
10. If there are any washers under the bolt head, proceed as follows:
a. Remove bolts affected, one st a time, and inspect bolt holes for possible damage.
NOTE
Do not have more than one (1) bolt out at the same time.
b. If holes are not damaged, reinstall existing AN5-6 bolt. AN880D516 washer or washers (under out only) and
existing MS11825-S nut. Taque bolt 160 to 2W inch-pounds by tightening nut to low side of taque range and,
if necessary, continue to tighten until a slat aligns with hole in bolt. Install existing or newM824665-1S2 rotter
pin (refer to Figure 3).
c. If holes are damaged, it i. acceptable to use AN6-6 bolts (0.575"10.818" diameter hole) only if an edge distance
of 0.S6inch or more can be maintained.
d. If it is determined, prior to reaming existing holes, that an edge distance of 0.66-inch or more EBJI~ be
maintained, contact aulfstream American Corporation, Commander Division, Customer Service Department,
Bethany, Oklahoma 19008 for further instructions.
a. If it is determined, prior to reaming existing holes, that an edge distance of 0.B6-inch or more E~ebe maintained,
ream damaged hole or holes to O.S?S"/O.S?B" diameter and install ANB-B bolt, ANBBODB1B washer (under nut
only) and MB118256 nut. Torque bolt 900 to S90 inchpounds by tightening nut to low side ortorque range and,
if necessary, continue a tighten until a slot aligns with hole in bolt. Install M924BBS-1S~ cotter pin (refer to
Figure 3).
Page 5 of 8
8ERVICE LETTER NO. 545
NOTE
An additional ANOBODB1B washer may be installed (undernut only), if neosssa~y, to assure proper alignment of hale in
holt with slots in nut. The above listed hs~wsre is to be
procured locally.
11. Reconneet electrical wiring to tail position lights and reinstall tail cone on airplane using existing hardware.
12. Reinstall leR and right Ridder control linkage access doors using existing hardware.
13. Install 311017´•3 door using M821039-1-10 screw (10 places) (rsfer to Figure 1).
14. Touchup paint as neeessary.
15. Fill out and mail Compliance Card specifying that Part II has been accomplished.
ELECTRICAL LOAD: NO CHANGE.
WEIGHT AND BALANCE: NO CHANCE.
SPARES AFFECTED: NO.
PUBLICATIONS AFFECTED: The airplane Maintenance Manual changes required by this document will be
incorporated at the next scheduled revision.
RECORD COMPLUNCE: Make an appropriate entry in airplane maintenance records as follows: Service Letter No,
345, dated 18 January 1982, entitled "Vertical Stabilizer Attach Bolte Inspection", Part I accomplished (date)
Part II acmmplished_l~.
Page BolB
,Service Letter a~llCulhsrresmAaospaeeCorpo~rion
$b"B~"a*lanornl ah. o* ahoml 73123
SERVICE LETPER NO. 346
REVISION NO. 1
23 JUNE 1986
REPLACEMENT OF INNER STRUCTURAL CABIN WINDOW GLASS
PIPPROVAL: ENOINEERINO DESIDN ASPECTS ARE FAA APPROVED.
This Revision N~tice is being issued to replace PIN 330113´•28 inside giase unth PBi 330115-33 inside glass and replacePIN 330367-55 inside glass with PIN 390367-19 inside glass.
Page 1 of 1
Y,, Service Letter GulfstreamAmericancoaPoa*´•rlon
i Commndn Dk~itlm
swl N~rm Rootr~ll IW~nus.I B´•m´•ny. OCllhoma 11009
SERVICE LETTER NO. 846
t Septsmber 1881
REPLACEMENT OF INNER STRUCTURAL CABIN WINDOW GLASS
NOTE
PILOT AND COPILOT SIDE WINDOWS, EYEBROW
WINDOWS AND WINDSHIELDS ARE NOT AFFECTED BY
THIS SERVICE LETTER.
1 UODILB IFFECTED: MODEL 690C, SERIAL NOS. 11664, l166B THRU 11610, 11612, 11819 AND 11108 AND
MODEL 685, SERIAL NOS, 96080 THRU 95088, 86085 THRU 98089, 88011 THRU 95018 AND 86016 (8EE NOTE
BELOW FOR ADDITIONAL MODELS THAT MAY SE APF&CTBD BY THIS SERVICE LETfER).
i NOTE
IF ANY O~ THE FOLLOWING MODELS HAVE
REPLACED ANY WINDOW SPACERS, BETWEEN 1L JANUARY 1881 AND 16 JUNE 1891, CONTACT
GULFSTREAM AMERICAN CORPORATION, CUSTOMER
R SERVICE DEPARTMENT, BETHANY, OKLAHOMA 18008
FORWBTRUCTIONS:
MODELS 68(1FL(P), BBOT, B80V AND 680W, 8ERL9L NOS.
1281 THRU 1854, MODEL 681, SERIAL NOS. 8001 THRUi 6012, MODEL 686, SERIAL NOS. 12000 THRU 12066,
MODELS 680, 680A AND 690B, SERIAL NOS. 11001 THRU
11566, MODEL 690C, SERIAL NO8. 11800 THRU 11863
AND MODEL 686. SERIAL NOS. 85000 THRU 95059.
REASON FOR PUBLICATION: THE INSIDE STRUCTURAL WINDOW PANES ARE SU&TECT TO CRAZWC
I´• AROUND BOLT HOLES DUE TO CATALYTIC REACTION OF COMPOUND MAKEUP IN SPACERS AND
OROMMETS.
NOTE
OUTER STRUCTURAL PANES, BEING OF DIFFERENT
COMPOSITION, HAVE NOT BEEN FOUND TO CRAZE.
COMPLIPINCE: WITHIN NEXT 10OHOURG TIME IN SERVICE.
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE
COMPLYING WITH THIS SERVICE LETTER, CONTACT
YOUR NEAREST GULFSTREAM COMMANDER
AUTHORIZED 8ERVICENTER.
BY WHOM WORK WILL BE PICCOMPLISHED: A P MECHANIC OR F,BUNALENT.
APPROVAL: PAA DOA 8W-2 APPROVED.
3
9ERVICE LETTER NO. 948
MAN HOUAS: TWENTY SIX (26) HOURS.
NOTE
DULFWREAM AMERICAN CORPORATION WILL ALLOW
A CREDIT OF TWENTY 81X (26) HOURS LABOR UPON
RECEIPf OF A PROPERLY EXECUTED WARRANTY
CLAIM, CUTOUT SECTION OF EACH WINDOW
ICONTAININCI THE PART NUMBERI, OLD GPACER8 ANDA COMPLIANCEC~D.
PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE LETTER MAY BE PROCURED THROUGH
YOUR NEAREST OULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR 9601.58. A PULL CREDIT
WILL BE ISSUED UPON RECEIPT OF A PROPERLY EXECUTED WARRANTY CLAIM, CUTOUT SECTION OF
EACH WINDOW ICONTAININ(I THE PART NUMBER), OLD SPACERS AND A COMPLIANCE CARD.FACTORY SERIAL NUMBER WHEN ORDERING
SERVICE LETTER NO. 946 KIT CONSISTING OF THE FOLLOWING:
Prlw lub]oct to Ehan(ls dthoul not(oe,
BTY PART NO. DESCRIPflON
2ea. 580113-29 indde Glees8ee. 550115-51 Spacer1 ea. 580561-1 inside Classt as. 850361-8 inside Glass
2 as. 550361-66 Inside Glass
2 ea. 590561-65 Spacer2 ea. 850561-85 8pacer2 ea. 89056181 8paur2 ea. 330361-89 Space~z ea. 330361-11 8pacer2 ea. 330381-13 Spacer4sa. 830561-15 Spacer4 ea. 530361-11 Spacer8 ea. 861887´•35 Felt Pad
584 ea. WX)106621 Girommet
13 so. R. R411N yls Neoprenetmll Surgical Tape (514")1 ea. Compliance Card
1 se. Service Letter No. 546 instructions
SPECIALTOOLS: NONE.
~CCOMPLISHMENT INSTRUCTIONS:
CAUTION
WHEN PERFORMING THE FOLLOWING PROCEDURES,CARE SHOULD BE TAKEN SO AS NOT TO DAMAGE OR
SOIL ANY INTERIOR PANELS OR UPHOLSTERY.
1. Remove emergency exit window panel as follows (refer to Figure 1):
a. Remove emergency exit window from airplane.
b. Remove snaw (2 places) attaching emergency slit window release handle and remove handle.
c. Remove screw (4 places) attaching emergency exit window panel to window and remove panel.
1. Remove window penal from main cabin door as follows:
a. Remove screw attaching interior handle to door mechanism and remove interior handle.
b. Remove screws attaching center door panel to daor, disconnect wires from emergency door release switch and
remove center panel from doer. Mark wires to assure that switch will be rewired correctly after reassembly.
Page a of 11
8ERVICE LETTER NO. 548
81DE WINDOWTRIM EXTRVSION
EMERGENCY EXIT EMERGENCY EXIT PANEL
WINDOW PANEL RELEASE HANDLE ARMRESTPANEL
’i-r
meLE COVER
I
EMERGENCY EXIT
RELEASE HANDLE
EMER(IENCY EXIT
WINDOW PANEL
t;llun
Page 9 of 11
BERVICE LETTER NO. 346
c. Remove channel that holds window panel in place.
d. Remove screw (2 places) that attaches window panel to door, pull down on window panel and remove panel from
door.
e. Remove lower acrew attaching forward bayonet rod assembly and remove rod assembly and bayonet from door.
NOTE
There i. a small spacer located at the lower clevis on the rod
assembly, Asaure that apacer is not dropped and lost when
rod assembly is removed.
3. Remove curtains locatedjust aft of main cabin door and emergency exit window.
4. Remove lan and right cabin aide window panels as follows (rsfer to Figure 1):
a. Pull top of table cover out and pull table up to expose screws attaching table guide O aide of table
b. Remove either forward or aft table guide from table and remove table.
c Remove two iZ) top screws attaching table cover to fuselage structure.
d Pull down on top of arm rest panels to expose screws that attach trim extrusion to fuselage structure.
e. Remove screws attaching trim extrusion to fuselage structure and remove trim extrusion.
f Loosen aft screws attaching panel over main cabin door to facilitate removal of left cabin side window panel
g Remove upper screws attaching cabin aide window panel to fuselage structure.
h. Assure that cabin side window panel, are not stuck to insulation prior to removal
i, Remove left cabin side window panel by pushing panel back to release forward portion of panel and then pull
panel dawn to clear headliner.
j Remove right cabin side panel by pulling down on panel to clear headliner.
5 Remove screws attaching all interior window glass (tintedl to emergency exit window, main cabin door and cabin
side windows and remove interior glass from airplane.
6 Remove inside and outside windows as follows (refer to Figure 21:
a Remove foam rubber insulation ~rom around window retainers.
b Remove interior clips, attached by screws, as necessary to facilitate removal of window retainers and windows.
Mark ail clips to assure they will be reinstalled in same location from which they were removed,
c Remove all screws attaching windows to fuselage skin.
d Remove window retainers and bumpers Mark top of retainers to assure they will be reinstalled in same
position from which they were removed.
NOTE
Pumpers are bonded to retainers.
e Remove windows
f Remove and discard, only if damaged, any neoprene (gasketfil bonded to interior of fuselage skin and on
retainers,
NOTE
Daskets are to be replaced only if they are damaged.
Page 4 of 11
BERVICE LETTER NO. 548
8W1Mm
R911N 1118BROMMET
NranENr OLwlL.aasu .j
.m~.´•10.
BPnCER 14 PLSI
RI11N 1118is~ i -NEOPRENE
1- I’/
Or L cnNo
i CHI\NNEL
ka‘i´•
O ´•’I
lII ii
ExlsnNo
i OUTSIDE OLP~8S
INSIDE OL1\8(
L
EMEROENCYEXIT
WINDOW )I\NEL
INTERIOR (ILASS
CLIP
SE~L
REYEP~L
*illun 2 ishast 1 ot 3)
Page 5 of 11
SERVICE LETTER NO. 346
gC0,
MAIN cnslhl ODORWINDOW PIZNELr REVEAL
CLIP
t; OIASSTINTED INTERIOR
GANG
CHANNEL
R(IIN 1118NEOPRENE
33011331SPACER 14 PLB
B~ n411N ins
NEOPRENE
CLIPY~1
RETAINER
r;;"550113´•28
OUTSIDE GLASS
800108´•527
GROMMET
Fllun, 2 ihast i of 91
Page B oI 11
SERYICE I.ETTER NO. 346
REYEI\LTINTED INTERIOR
CH~NNEL
OI\NO
OROMMET RI1IN 1116
U(UB7´•b3SPLICERII )L~CIS1
RIIIN lilB
~1.
BUMPER330361-51PACER I? PLSI
INBIDE OL*B prill jEXI(ITING
WTIIOE GL/\S5
IUSLLAOE SI(IN
eaalma,l
cnommET WINDOW PIINEL
BUMPER GI\NG
Cnl\NNEL
RI11N 1116 NIOPRENI
33035785 SPPICLR
J3a787d3SP*CEA
R411N 11(5 NEOPRENE
Ir h II: 1G
330357-61
SP~CLARCT
REVC~L
SP~CERTINTED
INTERIOR 330367
GLI\SS INS108 GL*SSFUSLLI\GE SI(IN
EXISTING
OUTSIDE GL~iS
33035)691 ´•I
PP~CER
~iCn Z IShs~t J ot O)
Page 7 of 11
SERYICE LETTER NO. 548
CAUTION
Protect all window glass, after removal, to prevent scratchingofglass.
g. Disassemble windows, cutout portion of inner glass (eontaining the part number) for return to Oulfstream
American Corporation with old spacers, and discard the gmmmets.
h. Cheek outside glass, around each bolt hole, for chips or distress. If found, contact your nearest Gulfstream
Commander serviCenter. If no cracks are found, retain outside glass for later reinatallation.
CAUTION
Care should be taken when assembling new inside glass to
existing outside glass to assure no contaminants are trappedbetween panes of glass and assure that glass is protected from
scratches.
7. Assemble new inside glass to existing outside glass se follows (refer to Figure 2):
NOTE
This procedure applies to all windows.
a. Clean both aides of inside glass and outside glass as outlined in Chapter 56 of the Airplane Maintenance
Manual.
b. Apply one (1) inch tape over all holes an outer surface of outside glass and turn glass over so that outer surface
is down.
NOTE
Outer surface of window is contaured. The tape is used to
hold grommets in place during assembly to inside glass and
outside glass.
c. Insert new 900106-621 grommete in outside glass holes.
d. Install new spacers over grommets.
NOTE
Square corners on spacers should be positioned adjacent to
edge of glass.
e. Assure that both inside glass and outside glass are clean and ready for assembly
f Place new inside glass on existing outside glass.
g. Apply one(l) inch tape over holes to prevent grommets from falling out.
h. Apply 314 inch surgical tape on all corners of glass (refer to Figure 3)
NOTE
Picture window will require one (1) piece of 314 inch surgicaltape an top and one (1) on bottom where spacers are joinedtogether.
8. If neoprene (gaskets) are to be replaced, thoroughly clean any damaged neoprene material from fuselage skin.
emergency elit window, main cabin door and all retainers as necessary.
9. Bond new R411N 1116 neoprene on fuselage skin, emergency exit window, main cabin door and on all retainers usingEC1~03 or an equivalent contact cement and trim as necessary (refer to Figure 21
Page 8 of 11
SERVICE LETTER NO. 548
NOTE
To assure that the R411N 1118 neoprane is not wasted, layoutsites for each window prior to cutting. Cut one (1) inch stripsfor small windows and for all retainers. Cut two (2) inch
strips for picture windows.
10. Using a sharp tool, punch all holes in new neoprene.
11. Install all inside end outside windows on airplane as follows (refer to Figure 2):
a. Remove tepe, holding grommets, from both sides of glass.
b. Position window and retainers for installation on airplane and install existing screws. Assure that bumpersam bonded to retainers, if not, rebond bumpers to retainers using EC1403 or an equivalent contact cement,
E. Tighten all screws to the following torque value:
Main Cabin Door Window 12 to 15 inch-poundsEmergency Exit Window 12 a 15 inch-poundsPicture Window 20 to 25 ineh´•pounds8mall Cabin Windows 10 to 25 inch´•peunds
d. Ibinstall existing interior clip., removed in step 6.b., using existing hardware,
a. Bond 861881-53 felt pad on outboard side of picture window lower clip (4 places) on left and right side usingEC1´•IOS or an equivalent contact cement (refer to Figure 4).
NOTE
Allow contact cement to thoroughly dry before installinginteriorwindaws.
f Reinstall existing foam rubber insulation around all window retainers.
g. Assure that all glass is clean and then reinstall existing interior window glass (tinted glassl using existinghardware.
h. Reinstall emergency exit window on airplane.
CAVTlOhI
Assure that seal is not pinched when installing window.
12. Pressurieed cabin to maximum differential pressure to assure there are no leaks (refer to Chapter 21 of the
Airplane Maintenance Manual).
19. Reinstall existing left and right cabin side window panels as follows:
a. Position panel for installation and install upper screws and washers.
NOTE
On left aide panel, assure that forward edge of panel is tucked
under main cabin door panel.
b. Tighten aft screws that attach penal over main cabin doe;.
c install trim extrusion using existing hardware, Do not install two (2) serewa in area of table until arm rest
panels are tucked under trim extrusion.
d. Tuck arm rest panels under trim extrusion.
e. Install two (2) screws that attach table cover to fuselage.
Page B of 11
SERVICE LETTER NO. SE
IREF)
O914" SURGICAL TAPE OUTSIDE
GLASS IREF)O
INLIIDE GLASS
IREF)
O
SPACER IREFI
FipureS
PICTURE WINDOW
IRE Fl
BoND 8818875s FELT PAD
TOOUTBOIRD3DEOFLOWER CLIP (4 PLSI WITH
ECI403CONTACTCEMENT
L.PELT PAD
(REF)YIIYI LOOKING OUTBO~RDCLIP(REF)I\T RH SIDE LH SIDE OPPOSITE
YIEW~
Flpural.
Page 10 ol 11
BERYICE LETTER NO. 348
f Position table for installation, reinstall table track on side of table and close table.
g Push in on tap of table cover.
14. Reinstall window panel on main cabin door as follows:
a. Reinatall forward bayonst rod assembly and bayonet on door using existing hardware and assure that bayonetis rigged properly
b. Position upper panel far installation on door and install existing hardware.
E. Reinstall existing channel under window panel using existing hardware.
d. Reconnect wires to emergency door release switch and install center panel on door using existing hardware.
e. Reinstall interior handle on bor using existing screw.
f Close cabin door and check to assure that red dots on bayonet inspection windows are centered over white disks,
g. Cheek electrical f~netian of door release system.
15. Reinstall emergency slit window panel as follows:
a, With emergency exit window release handle removed, position window panel for installation and installexisting hardware.
b. Reinstall emergency exit window release handle using existing hardware.
16. Reinstall curtaina,removedin step9., uaingexistinghardwsre.
17. Touch up paint, if necessary, on f\lselage.
18. Clean upholstery and side panels as necessary.
19 Fill out and mail Compliance Card, Warranty Claim, portion of glees (containing part number) and old spacers toDulfstream American Corporation, Commander Division, Bethany, Oklahoma 15008.
ELECTRICAL LOPID: NO CHANGE.
WEIGHT FIND 8*LANCE: NO CHANCE
SPARES AFFECTED: YES.
PUBIICATIONS AFFECTED: The Illustrated Parts Catalog changes required by this document will be incorporated at
the next scheduled revision.
RECORD COMPLIANCE: Make an appropriate entry in si~lsne maintenance records as follows: Service Letter No
346, dated 1 September IsB1, entitled "Replseement of inner Structural Cabin Window Glass", accomplishedtdafe)
Page 11 of 11
Service Letter GulfstreamAmericanuonpon*1´•ln*
Commanda Dirbion
6001 Norm Ra;kwsll Ausnua.Bsmany, Oklehem 13WB
SERVICE LETTER NO. 347
3 November 1981
REPLACEMENT OF INNER STRUCTURAL CABIN WINDOW GLASS
MODELS AFFECTED: MODEL 696A, SERIAL NOS. 96001, AND 96004 THRU 96001.
REASON FOR PUBLIC*TION: INSIDE STRUCTURAL WINDOWS ARE SUBJECT TO CRAZING AROUND BOLT
HOLES DUE TO INSTALLATION PRELOAD.
COMPLIP~NCE: WITHIN NEXT 100-HOURS TIME IN SERVICE.
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE
COMPLYING WITH THIS SERVICE LETTER, CONTACT
YOUR NEAREST GULFSTREAM COMMANDER
AUTHORIZED SERVICENTER.
BY WHOM WORK WILL BE PICCOMPLISHED: A L P MECHANIC OR E9UIVALENT.
APPROVAL: FAA DOA SW-2 APPROVED.
ESTIMATED MAN HOURS: FORTY-FOUR (44) HOURS.
NOTE
OULFSTREAM AMERICAN CORPORATION WILL ALLOW
A CREDIT OF FORIIYFOUR (44) HOURS LABOR UPON
RECEIPI~ OF A PROPERLY EXECUTED WARRANTY
CLAIM AND A COMPLIANCE CARD.
PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE LETTER MAY BE PROCURED THROUGH
YOUR NEAREST DULP8TI~AM COMMANDER AUTHORIZED BERVICENTER MOR 6819.11. A FULL CREDIT
WILL BE ISSUED UPON RECEIPT OF A PROPERLY EXECUTED WARRANTY CLAIM AND A COMPLIANCE
CARD. REFERENCE THIS SERVICE LETTER, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN
ORDERING SERVICE NO. 5117 KPT CONSISTING OF THE FOLLOWING.
pd, ..qsotlo~nllr
9TY PART NO. DESCRIPTION
2 ea. 380381´•115 inside Glass
2 ea. 950581-114 inside Glass
1 ea. 950381´•115 inside Glass
1 as. 330881-116 inside Glass
1 ea. 330381-111 inside Glass
I as. 330881-118 Inside Glass
282 ea. 800106-627 Gmmmet
19.6 4´• ft. ~11N 1/8 Neoprene1 roll Sugieal Tape (2.0")
1 ea. Compliance Card
1 as, Serviee Letter No. 347 instructions
PagelolB
SERVICE LETTER NO. 541
SPECIILTOOIS: NONE.
ACCOMPLISHMENT INSTRUCTIONS:
CAUTION
WHEN PERFORMIND THE FOLLOWING PROCEDURES.CARE SHOULD BE TAKEN SO AS NOT TO DAMAGE OR
SOIL ANY INTERIOR PANELIOB UPHOLSTERY.
1. Remove left and right cabin side window panels only.
NOTE
This rework does not apply to the cabin door, emergency slrit
or pilot and copilot windows.
2. Remove screws attaching cabin interior glass (tintedl to cabin side windows and remove interior glass from airplane.
3. Remove inside and outside glass as follows (refer to Figure 1):
a. Remove insulation from around window retainers.
b. Remove all screws attaching windows to fuselage skin.
c. Remove window retainers and bumpers, Mark top of retainers to assure they will be reinstalled in same positionRom which they were removed.
NOTE
Bumpers are bonded to retainers.
d. Remove windowsfrom airplane.
a. Remove and discard, only if damaged, any neoprene (gaskets) bonded to interior of fuselage akin and on
retainers.
NOTE
Gaskets are to be replaced only if they are damaged.
CAUTION
Protect all window glass, after removal, to prevent scratchingofglass.
f Disassemble windows and discard the inside glass and the grommets.
g. Cheek outside glass, around each bolt hole, for chips or distress. If found, contact your nearest Dulfstream
Commander ServiCenter. Ifno cracks are found, retain outside glass for later reinstallation.
CAUTION
Care should be taken when assemblying now inside glass to
eliating outside glass to assure no contaminants are trappedbetween panes of glass and assure that glass is protected from
scratches.
Assemble new inside glass to aliating outside glass as Follows (refer to Figure 1):
NOTE
This procedure applies to all windows.
a. Clean both sides of inside glass and outside glass as outlined in Chapter SE of the Airplane Maintenance Manual.
Page lolB
BERYICE LETTER NO. 341
c.aN´•lo. i? Xa AI I
WINDOWPP~NEL EXISTING TINTED
Inrmlono~ass
EXISTING BUMPER
EXISTING GANG
RETAINER
R411N 1/3 NEDPRENE
39a981´•113 INSIDE GLASS
IINEOPAENE
´•i
Bb
EXISTINGSPPICERS
900108´•521(iROMMET
FUSELAGESKIN
EX18T1N(I OUT81DE
GLASS
LEFT INSTALLATION SHOWN
RIGHT INSTALLATION OPPOSITE
Figqs 1. IShaat 1 of 21
Page3ofG
SERYICE LETTER NO. 541
LEFT INSTALLATION SHOWNExlSTlNG INTERIOR
PANELEXISTING TINTED
RIGHT INSTALLATION OPPOSITE
INTERIOR GLASS
EXISTING BUMPER
EXISTING GANG
CHANNEL
P41N id NEOPRENEO
J 23438(´•117GLASS
GROMMET
~II I)R411NllsNEOPRENE
I 8KIN
L r
EXIIITINO
EXISTING OUTSIDE
CAslN SIDE
WINDOWPANEL
EXIFTING TINTED
GLASS
EXlsTIN(IGAN(I
EXIBTIN(I BUMPERRII(NlnNEOPRENE
116 INSIDE GLASS
EXISTING OUTSIDE
EXISTING RETAINER~I- b
EXlsTlNa
800108´•527 (IROMWIET
ZIL~.L*B.SIINR411N 1/8
Filure 1. (Shaa 2 of 21
Page(olB
EIERVICE LETTER NOi 341
b. Apply one (1) inch tape over all holes on outer surface of outside glass and turn glass over so that outer surface
is down.
NOTE
Outer surface of window is contoured. The tape is used to hold
grommets in place during assembly of inside glass to outside
glass.
c. Insert new 900106-621 grommets in outside glass holes.
d Install existing spacers over grommets.
e. Assure that both inside glass and outside glass are clean and ready for assembly.
f Place new inside glass on existing outside glass.
NOTE
Contour of inside glass goes tothe inboard aids.
g. Apply ons (1) inch taps over holes to prevent prammsts from fallingout.
h Apply Z.O-inch surgical tape on all corners of glass (refer to Figure 2).
5. If oeoprene (gasksts) are to be replaced, remove any damaged neoprene material from fi~selage skin and all reta~nersas necessary.
6. Bond new R~11N 11 neoprene of fuselage skin and on all rsthmers using EC140S or an equivalent contact cement
and trim a. necessary. Allow cement to cure for thirty (90) minutes prior to accomplishing step 7 (refer to Figure 1).
Using a sharp tool, punch all screw holes in neoprene.
8. Install all inside and outside windows on airplane as follows (refer to Figure 1):
a. Remove tape, holding grommets, from bath sides of glass.
b. Position ~vlndow and retainers for installation on airplane and install existing screws. Assure that bumpers are
bonded to retainers, if not, rebond bumpers to retainers using EC1´•IOS or an equivalent contact cement.
c. Tighten all screws to a torque value of 20 to 26 inch-pounds.
d. Reinstall existing insulation around all window retainers.
e. Assure that all glass is clean and then install existing inner window glass (tinted glass) using existing hardware.
9. Pressurize cabin to a maximum differential pressure to assure Bare are no leaks (refer to Chapter 21 of AirplaneMaintenance Manual.)
10. Rsinstall left and right cabin side window panels using existing hardware.
11. Touch up paint, if necessary, on fuselage.
12. Clean upholstery and aide panels as necessary.
18. Fill out and mail Compliance Card.
Page SalG
BERVICE LETTER NO. 541
IAEFI
O2.0" 8UROICAL TAPE
OUTSIDE
INSIDE
iSPACER iff EFI
FlsureZ.
ELECTRICAL LOAD: NO CHANGE.
WEI~HT AND BALANCE: NO CHANGE.
SPARES AFFECTED: YES.
PUBLICATIONS AFFECTED: The Illustrated Parts Catalog changes required by this document will be incorporated atthe nsnt scheduled revision.
RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service Letter No.941, dated 3 November 1981, Entitled "Rspl.cement of Inner Structural Cabin Side Window Glass", accomplished
(date)
PageBofB
Seavice e~ter GulfstreamAerospace
SERVICE LETTER NO. 349A
(8upersedes Service Letter No. 549 in its entirety)24 February 1984
ELEVATOR PUSH-PULL TUBE ASSEMBLY INSPECTION AND REPLACEMENT
NOTE
IF BASIC SERVICE LETTER NO. 548 HAS BEEN
COMPLIED WITH, COMPLIANCE WITH THIS SERVICE
LETTER IS NOT REQUIRED.
MODELS AFFECTED: MODELS BB0FL, 680FL(P), 680T, 680V AND 680W, SERIAL NOS. 1261 THRU 1854, MODEL
681, 8ERUL NOS. 6001 THRU 6072, MODEL 885, SERIAL NOS. 12000 THRU 12066,
MODELS 690, 690A AND 69OB, SERIAL NOS. 11001 THRU 11566, MODEL 690C, SERIAL
NOS. 11600 THRU 11718, MODEL 695, SERIAL NOS. 95000 THRU 95084 AND MODEL
695A, SERIAL NOS. 86001, 96008, 86006 THRU 96016 AND 96018.
REASON FOR PUBLICATION: POSSIBLE CRACKS IN ELEVATOR PUSH-PULL TUBE ASSEMBLIES IN BOTH
SWAGED ENDS.
COMPLIANCE: PART I- DURING NEXT 100-HOUR INSPECTION AND EVERY 200HOURs TIME 1N ISERVICE THEREAFTER UNTIL PART II OF THIS SERVICE LETTER HAS BEEN
C *cooMP~Hea
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE
COMPLYINCI WITH THIS SERVICE LE~ER, CONTACT
YOUR NEAREST GULFSTREAM COMMANDER
AUTHORIZED SERVIOENTER.
BY WHOM WORK WILL BE ACCOMPLISHED: A Be P MECHANIC OR EQUIVALENT.
APPROVAL: FAA DOA SW-2 APPROVED.
ESTIMATED MAN HOURS: PART I INSPECTTUBE ASSEMBLIES:
MODEL BBSA FOUR a ONE-HALF (4.5) HOURS, ALL OTHER MODELS
-TWO (2) HOURS.
PART II REPLACE TORE ASSEMBLIES:MODEL BBBA 81X (6) HOURS. ALL OTHER MODELS FOURTEEN (14)
HOURS.
PARTS DATA: PARTS REQUIRED TO COMPLY WITH PART II OF THIS SERVICE LEWER MAY BE PROCURED
THROUGH YOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED BERVICENTER FOR 896.64.
REFERENCE THIS SERVICE LETTER, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN ORDERING
SERVICE LE?TER NO. 349A KIT CONSISTING OF THE FOLLOWIND:
Ilrl~ UIMIID nalo´•.
OTY PART NO. DESCRIPTION
2 ea. 590578-1 or 530578-81 Tube Assy
1 ea,
or630578-5CamplisnceCsrd
1 es. Service Letter No. 349A tnstructions
Page 1011
GF,RVICE LET~ER NO, 349A
S.ECIII~DOLB; N,N$´•
ACCOMPLISHMENT INSTRUCTIONS:
PART I INSPECT ELEVATOR PUSH-PULL TUBE ASSEMBLIES.
1. On Model 696A, proceed as follows:
a. Remove pilot seat, copilot Beat and bars.
b. Remove carpet, as necessary, to gain access to nwr panels in eaokpit area.
c. Remove left and right noor panels to gain access to elevator push-pull tube assemblies (refer to Figure
d. Proceed to step 3.
2. On all Models (excspt Model 696A31 prooeeda as follows:
a. Remove interior and carpet as necessary,just aR of pilot and copilot seats, to gain access to floor panels
(refer to Figure 1).
b. Remove left and right access covers from noo~panels to gain access to aft end of elevator push-pull tube
assemblies (refer to Figure 1).
c. Remove access cover (2 places) from bottom of fuselage to gain access to forward end of elevator push-
pull tube assemblies (refer to Figure i).
d. Proceed to step i.
S. Visually inspect swaged ends of both elevator push-pull tube esaemblies for possible cracks (refsr to Figure 2).
I
6. If craets are found, proceed to Part II.
6. Reinstall acceea covers or noor panels an airplane.
7. On all Models (except Model 6BOFL and 69SA), reseal access covers on floor panels as outlined in the applicable
Airplane Maintenance Manual.
8. On Model 695A, reinstall carpet, pilot and copilot seats and bars.
9. On all other Medals, reinstall interiors and carpet.
10. Fill out and mail Compliance Card specifying that Part I has been accomplished
PART II REPLACE ELEVATOR PUSH-PULL TUBE ASSEMBLIES.
1. On Model 696A, proceed as follows:
a. Remove pilot sent, copilot seat and bars.
b. Remove carpet, as necessary, to gain access to noor panels in mchpit area.
c. Remove left and right noor panels to gain access to elevator push-pull tube assemblies (refer to Figure
d. Remove bolts attaching left and right elevator push-pull tube assemblies to control columns and to
elevator torque tubs arms and remove tube assemblies (refer to Figure 2).
PBBeaol?
SERVICE LE1TER NO. 349A
REMOVE TH18 PANEL TO
C RI~HT PUSH´•PULL TUBE
AGEY
REMOVE TnlS PANEL TO
INSPECT AND AEPLACE
LEFT PUSH´•PULL TUBE
*sEY
MOOEI.B9SA
Fi(u~a i. IWm d 2)
Page S ol 1
SEKYICE LETTER NO. 349A
REMOVE THIII FLOOR PANEL
TO REPLACE RI(IHT PUW´•PULL
TUBE ASSY
OO
O
o o
oo o’´•´•.~ o
o
o
o
~JREMOVE THIS FLOOR PANELTO REPLACE LEFT PUGH´•PULLTUBE AgSY
REMOVE ACCESS COVER 12 PLS1TO INSPECT PUFH-PULL TUBE
~616
REMOVE ACCESS COVERSTO INSPECT AND REPLACE
PUW´•PULL TUBE ASSYS
O
o o o
o
VIEW LOOKING UP AT FUSELA(IE
ALL MODELSIEXCEPT MODEL 885*1
Fi~urs IShsat 2 ot 21
Page 4017
SERYICE LETTER NO. 348A
a Rsmoa aristmg md mds. Eb.knuts and Lay loeXa imm tub. Oipard alialins tubo
assemblies and retain rod ends, checknute and key looks for reinstallation.
f Install existing rod ends, checlrnuts.and key lacks on new 590578-1 or 530518´•S1 or 530518-5 tube Bassemblies and safety wire (refer to Figure 3).
g. Install new push-pull tube assemblies on control columns and on elevator torque tube arms using
existing hardware (refer to Figure 2).
h. Check a4iustment of elevator controls as outlined in the Airplane Maintenance Manual.
i Reinstall existing floor panels on airplane using existing hardware.
i. Rsinstall carpet, pilot and copilot seats end bars.
k. Proceed to step 3.
2. On all Model, (except Model 696A3, proceed as follows:
a. Remove interiors and carpet, as necsssary,just aft of pilot and copilot seats to gain access to floor panels
(refer to Figure i).
b. Remove rivets from left and right Roar panels, just aft of pilot and copilot seats, as necessary to facilitate
removal of elevator push-pull tubs assemblies (refer to Figure i).
Remove access cover (2 places) f~om bottom of fuselage to gain access to forward end of elevator puah-
pull tube assemblies (refer to Figure i).
d. Remove bolts attaching aft end of push-pull tube assemblies to elevator torque tube arm
a. Remove left and right arms ham elevator torque tubs to facilitate removal of push-pull tube assemblies
,,,,,,,~.2,
f Remove rad end, cheeltnut and key IDck from aft end of push-pull tube assemblies. Retain rod ends,
checknuts and key locks for reinstallation.
g. Remove bolts attaching push-pull tube asaemblies to control calumns and remove push-pull tube
assemblies.
h. Remove rod end, checknut and key lack from forward end of push-pull tube assemblies. Discard existing
tube assemblies and retain rod ends. checknuts and key lacks.
Install existing rod end, chsoltnut and key lock on forward end only of 630518-1 or 530578-51 or 530578-6 1tube assemblies and safety wire (refsr to Figure 3).
j. Position push-pull tubs assemblies in place and install forward end using existing hardware.
Reinstall existing arms on elevator torque tube using existing hardware.
i. Insl.l sristin. rod end, ihsrhnut and L.y lock on an end of.0678-1 or hPDS7B61 or 650618-5 rubs Iassembly. Do not safety wire until adjustment os elevator controls has been accomplished.
m. Check adjustment of elevator controls as outlined in applicable Airplane Maintenance Manual and then
safety wire aft rad end on push-pull tube assemblies.
n. Rsinstall existing access covers and floor panel. using existing screws, CR3243-4 or CR2249´•4 blind
rivets and CR9242-4 or CR2248-4 blind rivets.
NOTe
Rivet lengths to be determined on installation.
Page 5 of 7
SERVICE LETTER NO. 949A
ELEVATOR TOROUE
TUBE IREF)
/ARM IREFI
HDWE IREFI
CONTROL COLUMN
(REF~
IN6PECT SWABED EN08 FOR
PO8SI6LE CRACKS 14 PLSI
REMOVE EXISTIN(I PUSH´•PULL TUBE ASSY
*ND I~TALL 530678-1 OR 6SOhlBdl OR
5305186 TUBE ABEY (2 PLS)
EX18T(NO HDWE IREFL
FIBYrO 2.
ROD END.CHECKNUT I\ND KEY
LOCK 12 PL~I65(1578´•1 OR 530618´•SI OR630578´•6 TUBE ASSY SAFEN WIRE CHECK
31.12.. NUT USING MS2(lsBBC32
NOMINI\L IO.M2" OIA.1 CORROOION
RESISTANTSTEELWIRE
12 PLS1
FIIYn3´•
PageGol’l
SERVICE LETTER NO. 349A
C o Aa~aal and nmE isnsle ap outlun´•d in t~ lip~irsbls Alrpleoe Meint~N).i. Manull
NOTE
Model BSOFL dose not Rquire sealing.
p. Reinstall interiors and carpet.
3. Fill out and mail Compliance Card specifying that Part II has been accomplished Note ilany cracks were found
and where they were located.
ELECTRICAL LOAD: NO CHANGE.
WEIGHT ~ND BALANCE: NO CHANGE.
BPAREB AFFECTED: NO.
PUBLICATIONS AFFECTED: The Illustrated Parts Catalog Changes required by this document will be incorporated at
the nert scheduled revision.
RECORD COMPLIPINCE: Make an appropriate entry in airplane maintenance records as follows: Service Letter No.
349A. dated 24 Bsbrusry 1984, entitled *EL8vator PushPull Tubs Assembly inspection end Replacement", Part I I
accomplished (date) Port II accomplished (date)
C
Page’lof?
~illService Letter Gulfst~amAmeriran
colPoln´•rlurr
Cammada Dirlon
BW1 Norm Roc~lall ~vsnua.(XIIhany. ~l´•homa 13006
8FIRVICE LETPER NO. 360
15 April 1982
COCKPIT INSULATION OVERHEAD SWITCH PANEL
PODELS AFFECTED: MODEL 690C, SERIAL NOS. 11600 THRU 11?21.
MODEL 69011, SERIAL NOS. 15000 THRU 16004.
MODEL 696, SERIAL NOS. 96900 THRU 95064.
MODEL BgM, 8ERIAL NOS. 88001 THRU 9BOS0.
REASON FOR PUBUCATION: INSULATION IMPROVEMENT TO CONTROL MOISTURE CONDENSATION
ABOVE OVERHEAD SWITCH PANEL.
COMPL]ANCE: WITHIN NEXT 100-HOURS TIME W SERVICE.
POTI
IF ANY PROBLEMS ARE ENCOUNTERED WHILE
COMPLYIND WITH THIS SERVICE LET~R, CONTACT
YOUR NEAREST (IULFSTR~AM COMMANDER
AUTHORIZED SERVICENPER.
BY WHOP WORK WILL BE ACCOPPLISHEO: A d P MECHANIC OR EQUIVALENI.
APPROVAL: FAA DOA 8W´•2 APPROVED
ESTIPnTED MIN HOVRS: FnTE (6) HOURS.
WOTe
FOR AIRCRAFI 8TaL hi WARRANTY, aULPSPREAM
AMERICAN CORPORATION WILL ALLOW A CREDIT OF
FIVE (6) HOURS UPON RECEIPI OF A PROPERLY
EXECUTED WNUMNTY CLAIM AND A COMPLIANCE
CARD.
PARIS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE MAY BE PROCURED THROUDH
YOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED 8ERt~CEPJTER FOR: KPT NO. 1 (46.81 OR KPT
NO. 2 -946.9?. FOE MICRAPP SPILL IN WNUMP~I, A FULL CREDIT WILL BE 18SUED UPON RECEIPI OF
A PROPERLY EX~CUTED WARRANTY CLAIM AND A COMPLIANCE CARD. REFERENCE THIS SERVICE
LE1TER. AIRCRAIT MODEL AND FACTORY 8ERML NUMBER WHEN ORDERING SERVICE LETPER NO. 350
KIT CONS1STINO OF THE FOLLOWING:
Page lolB
8ERVICE LETTER NO. SSo
KIT NO. 1- MODELSBSOC AND 895.
KIT NO. 2 MODELSBSOD AND 896A.
Kit Kit
No.l No.2
~TY BTY PARTNO DEBCRIPI~ION
lee. 860715-3 insulation
lea. 860175-4 insulation
Pea. 860115-6 Vinyl
sea. 860175-7 Insulation
1 se. 860175-9 Insulation
Zee. 860175´•11 insulation
2ea. 860115´•13 Insulation
lea. 862121-153 Insulation
las. 882121-154 insulation
2sa. 862121-156 Vinyl2ea. 882121-151 insulation
las. 882121-168 insulation
2ea. 862121-181 insulation
2ea. 862121-163 insulation
Iroll iroll #474 Tape(l")lee. lea. ComplianceCardiea, las. GervicsLetterNo.SSO Instructions
SPECI*LTOOLS: NONE.
ACCOMPLISHIENT INSTRVCTIONS:
i. Lower overhead switch panel as follows:
a. Ensure thatelectrical power is removed.
CAUTION
When removing eleetmlumin8seent panels, be careful not to
damage or break electrical wiring and connectors. De not allow
panel to hang by the wiring. Panel has to be supported or
damage may oocurto electroluminescent panels.
b. Loosen alien screwson allknabson face ofthe e*etmluminescent panels andremove knobs.
c. Remove attachingsorews securing electroluminescent panels.
d. Carefully remove panels sothatwiring forelectmlumineacsntpanelswill beexposed.
e. Grasp wires and gently pull dawn until quick disconnect end airplane wiring are enpased. Disconnect
electroluminss~entpanel.
r Remove attaehingsrrews from top ofmetalplate ofoverhead switchpanel.
g. Lower overhead switchpanel andallow(tto suspndbyths hinges.
2 Remove and discard any insulation that is installed on fuselage skin and frames in area above the overhead switch
panel.
3 Thoroughlyclean .u~faee where insulation istobe bonded usingToluene orlethylEthyl Ketone (MEK).
CAUTION
To prevent possible damage, care should be taken when usingsolvents in areaafelectrical equipmentand plasticmaterials.
Page 2 of 6
SERVICE LETTER NO. 350
FUSELAGE SKIN IREF)
_B
880775-1
INSULATION
A
.iP 86077613 INSULATION
CANTEOFRAHE IAEFI
WINDSnlELd OVERnEI\D SWITCH PANEL IREF1FRAME IREFI
860775-8 INSULATION 880775-6 VINYL
VIEW LOOKING INBD FROM LEFT SIDE
880776-1( INSULATION E 880176-11 INSULATION
BOND WITH Ecluu CEMENT BOND WITH 501103 CEMENT
5597757 INSULATION
BOND WITH EC1403 CEMENTI--F-
8807)6-7 INSULATIONANDCUTOUT
BOND WITH EC1~103 CEMENT880771´•8 INSULATION
BOND WITH ECI(DJ CEMENTEXTEND TD FRAME
JUNCTIONITYP1 VIEW A-A
LOOKING FWD AT WINDSHIELD FRAME
SLIT PIS REOD FOR WIRE
on STRUCTURE ITYP) E 880776-11 INSULATION
IREFI
-i~-
~ct=-
86071515 INSULATIONBOND WITH ECII(U CEMENT
EXTEND TO FRAME
JUNCTIONITYPI VIEW B-8
LOOKING AFT AT CANTED FRAME
MODslS 690C *ND 695 FICln 2- IOhrt 1 st 21
Page 3 of 6
SERYICF.I.ETPERN0.3~O
800715-5 VINYL 8807764 INbULPlnON
880775-18 INIULATION
(REFI I 88077618 INSULATION
L
0507751 INsuLnnoN
660775-11 INsuLnnoNVSE NO. ale TAPE TO INSTALL
(REFI880775´•3 AND INSULATION
AND 860776´•5 YINYL 880775´•7 INSULATIONIAEFI
*011
TRIM AND IN~TALL INSVLATIDN WITH
SMOOTH fACE L~OI\INST SIIN.
ASSURE THAT N,suLoEs AnE )REKNT
VIEW C-C LOOKING UP AND FWD
Fiplrs 1´• Ihrf 2 ot 21
4 install new insulation on fuselage skin and frames in area above overhead Rwitch panel ~1Hine gC1403 Cement or
an equivalent Trun insulation upon instl,llatinn and assure no bulges are prelent (refer to Figure 1 or Figure 2)
Figure 1 is for Models 690C and 695 end Figure Z is for Models 6901) and 695A
5 HeinsLall overhead switch panel as follows:
CbUTION
I~en installing the overhead switch panel, ensure that all
wires and busaen are properly secured and iae not squoeledtowards airframe. This will prevent possible shortcircuita
a. Swingoverhead switch panel up and securewith exi~6ng attaching screws.
b Connect eleetrolumineacent panel wiring to airplane wiring and position penal for installation Stow excess
winng and ensure that wiring will net be pinched or crimped when panel is secured
c Secure electroluminercent panels with attaching screws. Tighten screws evenly to prevent warping of
panels
d Reinstall all eristingknobs and secure with existing ellen screws.
6 Fill out and mail Compliance Card
Page 1 of 6
8ERVICE LETTER NO. SIO
FUSELAGE SI(IN IREF)
NO. 414 TAPE
asn,lnaINSULATION
A
.CPCANTEDFR~MEIAEF)
8~2(21´•183 INSULATION
OVEHHPAD SWITCH PANEL (REF)WINDSHIELD
FRAME (REFI
882121´•159 INSULATION 88212(´•185 VINYL
VIEW LOOKING INBD FROM LEFT SIDE
882121-181 INSULATION802121181 INSULATION E BOND WITH 801483 CEMENT
BOND WITH rc~un CEMENT88211(´•181 INSULATION
BOND WITH 801403 CEMENT
TRIM TO MATCH FRPIME
882121´•157 INSULATION ANDCUTOUT
BOND WITH 501403 CEMENT8~2121´•188 INSULATION
BOND WITH 801403 CEMENTEXTEND TO FRPIIE
~UNCTIONITYP) VIEW A-A
LOOKING FWD AT WINDSHIELD FRAME
8LITASREODFORWIREOR STRUCTURE ITYP) e 882121181 INSULATION
(REFI
882(2(´•183 INSULATIONBOND WITH EC(~03 CEMENT
EXTEND TO FRAME
Juacnw(nPI VIEW B-B
LOOKING AFT AT CANTED FRAME
MODELS 6900 AND 695Pl Flgunl. (91rt 1 ot 21
ppge 6 916
__
8ERVICELETI~ERNO.SIO
BB21ZI´•ISSVINYL INSULATION
8~2121´•183 INSULATION(REF) 882121´•183 INSULATION
(REFI
88212(´•(63 INSULATION
882121´•18( INSULATIONUSE NO. 414 TAPE TO INSTALL IREFI
882121´•163 AND ´•184 INSULATIONAND8~2121´•(S6YINYL 882121´•(87 INSULATION
IREFI
NOTE
TRIM ANO INSTALL INSULATION WITH
SMOOTH FACE AGAINST FUSELAGE SI(IN.
ASSURE THAT NO BULGES ARE PRESENT.
VIEW C-C LOOKING UP AND FWD
Fplln 2. (9H*f at 2)
ELECTFIIOALLOAO: NOCHANGE.
WEIOHTANDBILP~NCE: NOCHANGE.
SPARESAFFECTED: NO.
PUBLICATIONSAFFECTED NONE.
RECORDCOMPLIANCE: Make and appropriate entry in eirplanemaintenanoereeords as follows: arvies Letter Na. SSO,
dated 15 April 1882, entitled"Cookpitlnsulation Overhead Switch Panel", aeeompliahod (date)
Page B ol 8
Service Lettev GulfstreamAmerican
Commanda DivironSW( North Roc~rmll nvsnua.Bethlny. OXlahoma 13M8
SERVICE LETTER NO 351
17 June 1882
PARKER HANNIFIN CORPORATK)N PRODVCT REFERENCE MEMO (PRM) NO. 27
MODELS AFFECTED: FACTORY APPROVED:MODEL 690A, SERIAL NOS. 11198 THRU 11944.MODEL 690B, SERIAL NOS. 11850 THRU 11566.MODEL 690C, SERIAL NOS. 11800 THRU 11667, 11689 THRU 11709.MODEL 69011, SERIAL NOS. 15001 THRU 15004 AND 15006.MODEL 696, 8ERUAL NOS. 80000 THRU 96049, 96051 THRU 98084.MODEL 695A, SERIAL NOS. 96001 THRU 96050 AND 98052.
STC APPROVED:MODELS 660F, 6808, 680FL(P), 680T, 680V AND 680W, SERIAL NOS. 871 THRU 1850.MODEL 681, SERIAL NOS. 6001 THRU 6012.MODELS 890 AND 690A, SERIAL NOS. 11001 THRU 11194.
NOTE
ALTHOUGH THE MODEL 690B 18 NOT LISTED ONPARKER HANNIFIN CORPORATION PRM NO. 21, IT ISRECOMMENDED THAT THE REWORK BEACCOMPLISHED ON THE MODEL BB0B.
THIS 8ERVICE LET~ER APPLIES TO CLEVELANDBRAKE ASSEMBLY Pi~ 50-107 AND SO-107A WITHMANUFACTURERS DATE PRIOR TO APRIL 1982.
REASON FOR PUBLICATION: TO RECOMMEND COMPLIANCE WITH PARKER HANNIFIN CORPORATIONPRODUCT REFERENCE MEMO (PRM) NO. 21.
COMPLIANCE: WITHIN NEXT 100-HOURS TIME IN SERVICE.
MOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILECOMPLYING WITH THIS SERVICE LE~ER, CONTACTYOUR NEAREW GULFSTREAM COMMANDERAUTHORIZED SERVICENTER.
BY WHOM WORK WILL BE ACCOMPLISHED: A 8. P MECHANIC 08 E9UIVALENT.
APPROVAL: FAA DOA 9W-2 APPROVED.
ESTIMATED MAN HOURS: ONE(1)HOUR.
PARTS DATA: PARTS RE9UIRED TO COMPLY WITH THIS 8ERVICE LE1TER, FOR FACTORY APPROVEDINSTALLATIONS ONLY, MAY BE PROCURED THROUGH YOUR NEAREST OULFSTREAM COMMANDERAUTHORIZED SERVICENTER FOR 86.79. A FULL CREDIT WILL BE ISSUED UPON RECEIPT OF OLD FITI~INOPIN 104-0(1200,A PROPERLY EXECUTED WARRANTY CLAIM AND A COMPLIANCE CARD. REFERENCE THISSERVICE LETIER AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN OI(DERIND SERVICE LETI~ERNO. 911 KIT CONSWINO OF THE FOLLOWING:
Page 1 of 2
8ERVICE LETTER NO. 361
WOTE
PRIOR TO ORDERING PARTS, 8EE STEP (a) OF PRM NO.27. PARTS FOR 8TC APPROVED INSTALLATIONS MUSTBE PROCURED FROM PARKER HANNIFINCORPORATION, AIRCRAFT WHEEL AND BRAKE
DIVISION, P.O. BOX 158, AVON. OHIO 44011.
CITY PART NO. DESCRIPTION
2 ea 104´•04800 Fitting2ea. 101-24600 O-Ring1 ea. Compliance Card1 ea. Servioe Letter No. 961 Instructions
SPECIALTOOLSc NONE.
ACCONIPLISHMENT INSTRUCTIONS:
1. Comply with Parker HsnniF~n Corporation Roduet Reference Memo No. 21.
NOTE
If brake assembly nameplate is missing or date an nameplateis unreadable, it is reoommended that this rework be
aecomplished.
2. Fill aut and mail Compliance Card.
ELECTRICAL LOAD: NO CHANGE.
WEIGHT AND sALANCE: NO CHANGE.
SPARES AFFECTED: All SO-101 and 30-107A brake assemblies in spares.tock, wit nameplates dated prior to April1982, must be updated to comply with PRM No. 27 and so noted.
PUBLICATIONS AFFECTED: The Illustrated Parts Catalog ohange required by tbis dooument will be inoorporsted atthe neat aehsduled revision.
RECORD COMPLIINCE: Make an appropriate entry in airplane maintenance records as follows; Service Letter No.351, dated 1? June 1982, entitled "Parker HanniBn Corporation Product Referenos Memo (PRM) No. 21", aeeomplished
(date)
PageBofP
0)(0
PRM No. 27 L982
AIRCWLFT APPL’ICABILITY: Gulf stream American or Rockwell, CommanderModels: 560F, 680F, L80fL (P), 680’1, 680V,680W, 681, 690, 690A, 690C (840), 6900 (900),695 (980) 6 695A (1000); chose equipped withCleveland Brake aasembly 30-107 or 30-107A
Within the next 100 hours perform the following:
(a) Check each brake nameplate. If the manufacturing date is3-82 or earlier, proceed to (b). If the date is 4-82 or
later, the inspection is complete and no further serviceneed be performed per this PRM. (Make logbook entrystating such)
(b) Disconnect and cap hydraulic line at the brake inlet.
(c) Remove existing brake inlet fitting, part number 10460200.
(d) Install new inlet fitting, part number 104-04900 and o-ring(part number 101-24600 for 30-107 end parr number 101-23000for 30-107A). The new fitting is a straight thread to
flare tube end connector. Asau´•re that the straight threadland o-ring) is installed into the brake cylinder with theflare tube end out.
(e) Connect hydraulic line to the brake inlet.
(f) Bleed the brakes. While doing so, check for free flow
through the bleeder. (15 solid stream flow through the
bleeder cannot be reached, then disassemble that brake and
inspect for fluid passageway restrictions. Repair as
needed),
(g) Make a logbook entry showing compliance to PRM 1127.
Parker Hannifin CorporationPlircraft Wheel and Brake DivisionP.O. Box 158 Avon, Ohio 44011 USA
(216) 9345221
~AerospacePD((84´•618 iJj
~111Service letter CulfstreamAmeri~an
CDRMII*TION
Comm´•ndn Dhllon6001 NPllm Rm~*a(l ~vanus.Bsmany´• O*lah~ma 1)006
SERVICE LETTER NO. 362
SO duly 1982
FUEL CELL INTERCONNECT HOSE REPLACEMENT
YODELS IFFECTED: THE FOLLOWING MODELS THAT HAVE FACTORY INSTALLED LONG RANGE FUEL
8YSTEM OR HAVE MODIFIED FUEL 8YSTEM PER CUSTOM KIT NO. 152:
MODEL 6W0C, SERIAL NOS. 116M) THRU 116&1, 11668 THRU 1168?, llBsB THRU 11703,11108 AND 11118 THRU 11?21.
MODELB80D, SERLAL NOS. 16002 THRU 15004, 16008, 15008, 16008, 15011 AND 15012.
MODEL 686, SERIAL NOS. B6WO THRU 85049 AND 86061 THRU 86084.
MODEL 886~, SERIAL NOS. 06001 THRU 86058, 86051, 86038 AND 86040.
REASON FOR P(IBLICATION: FUEL INTERCONNECT HOSE MAY BE SU&IECT TO EXCESSIVE SWELLING
AND EVENTUAL DETERIORATION.
COMPLIANCE: DURING NEXT lOO-HOUR INSPECTION.
IIOTe
IF ANY PROBLEMS ARE ENCOUNTERED WHILE
COMPLYING WITH THIS 8EI(VICE LFFTER, CONTACT
YOUR NEAREST OULFSTREAM COMMANDER
AUTHORIZED SERVICECENTER.
BY WHOM WORK WILL BE ACCOMPLISHED: A 81 P MECHANIC OR EQUIVALEIIPP.
ESTIMATED MAN HOURS: UPON COMPLETION OQ AIRPLANE DEFUELINO, THE REWORK WILL TAKE
APPROXIMATELY ONE AND ONE-HALF (1.5) HOURS.
PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE LF~1TER. MAY BE PROCURED
THROUDH YOUR NEAREST aULFSTREAM COMMANDER AIPDIORIZED SERVICENTER FOR (2.41.
REFERENCE THIS 8ERVICE LETTER,AIRCRAFI~ MODEL AND *ACTORY SERIAL NUMBER WHEN ORDERING
SERVICE LE~ER NO. 862 KIT CONSISTING OF THE FOLLOWING:
nlclllulusnmcHI~HlsvrmM*oma
cm PARTNO. DEBCRIPI~ION
2es. 880082-1 ~saket
2sa. 650384-81 H~ae
1 as. Compliancs Card
1 as. Service Iatte~ Ne. 552 Instruotiana
P~e 1~3
S´•u
8:
LIERVICE LETTER NO. 952 ip~i
d"
Remove mEsE
Bnccl~ooolr
CENTER WIN(I
24.00 (REP),,WS E FUEL CELL
AFT INBOARD ICFT FUEL CELLFUEL CELL (REF)
C‘j I ~i C::
INTERCONNECT489Y IREFI
INTERCONNECTPSSY IREF) ABSY IREF1 INTERCONNECT
ASSY (REr)(DOS8CIl NOSE IN~TALL 69038451 NOSE
USING EX18TIN(I CLL~MPS USING EXISTIN(I CLI\MPS
VIEW LOOKING DOWN AT FUEL CELLS
Fi~un i.
P´•galofS
BERVICE LETlEE NO. 362
SPECIAITOOL9: NONE.
ACCOMPLISHMENT INSTRUCTIONS:
1 Defuel airplane as outlined in Chapter 28 ofWe Airplane Maintenance Manual.
2. Remove leR and right inboard sR wing access doors to gain access to fuel interconnect hoses (refer to Figure
S. Remove and discard existing fuel plate gasket (Pn~ 6500821).
4. Remove damps and discard existing left and right hud intermnnect hoses (Pi~ 690584-55) (refer to Figure i).
6. Lubricate the new interconnect hose (Pi~ 65058451) with fuel or soap and water and install hose on
interconnect assemblies using existing clamps. Torque clamps to a value of 10 to 15 inch-pounds (refer to Figure
6 install new plate gasket (P~ 650082-1) and reinstall Be wing secess doom and seal with 880B-112 or equivalentMIL-9-8802 sealant per Chapter 51 of the Airplane Maintenance Manual.
7. Torque access door screws to a value of 20 to 26 inchpounds.
8. Refuel airplane as outlined in Chapter 12 of the Airplane Maintenance Manual.
g~ Fill out and mail Compliance Card.
ELECTRICAL LOAD: NO CHANCE.
WEIGHT AND BALANCE: NO CHANGE.
SPARES AFFECTED: All hose P~ 85038455 mlaoL in color) must be removed from spares stock.
PUBLICI\TIONS AFFECTED: The Illustrated Parts Catalog change required by this document will be incorporated at
We next scheduled revision.
RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service Letter No.
562, dated SO duly 1882, entitled "Fuel Cell interconnect Hose Replacement",
p~ 5 of S
Service Letter CulfstreamAmericanconroa*rl~,r
Commansr Divllion
5001 North Ausnu´•.
_
Bamnny. OLI´•Doma ~3W8
SERVICE LE?TER NO. 363
3 September 1982
FLIGHT CONTROL CHAIN CONNECTOR LINK INSPECTION
MODELS AFFECTED: MODELS 500, 600A, 600B, S00U, 520, 560, 560A 660E, 660F, 680, 680E, 680F, 680F(P),
680FL, 680FL(P), 680T, 680V, 880W AND 720, SERIAL NOS. 1 THRU 1354.
MODEL 6005, SERIAL NOS. 1166 THRU 1816 AND 5050 THRU 3323.
MODEL 681, SERIAL NOS. 6001 THRU 6072
MODEL 685, SERIAL NOS. 12001 THRU 12066.
MODELS 690, 690A AND 6908, SERIAL NOS. 11001 THRU 11566.
MODEL 680C SERIAL NOS. 11800 THRU 11127.
MODEL 690D, SERIAL NOS. 15000 THRU 15014.
MODEL 686, SERIAL NOS. 86000 THRU 86084.
MODEL BgSA, SERIAL NOS. 86001 THRU 86042.
REASON FOR PUBLICATION: TO VERIFY INSTALLATION OF FLIGHT CONTROL CHAIN CONNECTOR LINK,
PLATE AND KEEPER.
COMPLIP.NCE: DURING NEXT 100´•HOUR INSPECTION´•
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE
COMPLYING WITH THIS SERVICE LET~R, CONTACT
YOUR NEAREST QULFSTREAM COMMANDER
AUTHORIZED SERVICENTER.
BY WHDM WORK W(LL BE ACCOYPLISHED: A d P MECHANIC OR EQUIVALENT.
AFFROVAL: FAA DOA SW´•2 APPROVED.
ESTIBP;TED MAN HOURS: TWO (2) HOURS.
PARTS DATA: CHAIN CONNECTOR LINK PIN #35 (CONTROL COLUMN) AND PIN IYPS (gLEVATOR AND
RUI)I]ER TRIM) MAY BE PROCURED THROU(tH YOUR NEAREST OUL~STREAM COMMANDER AUTHORIZED
SERVICENTER AS RE~UIRED.
SPECIAL TOOLS: FLASHLIGHT AND INSPECTION MIRROR.
ACCOMFL!SHMENT INSTRUCTIONS:
1. R.´•aove tail cone and remove left and right inspenion panels, located on an fusalage just below horilontal
s~rbilieer, to gain access to rudder and elevator trim control aprockets irefer to Figure i).
2. Using a flashlight and an inspection mirror, inspect all chain to cable connections on Ridder and elevator trim
controls to assure that plates end "keeped’ me installed and properly secured on all chain master lin~s (refer
to Figure Il.
3. If"keepars" are secured properly, proceed to step 6.
Page 1 oft
BERYICE LETTER NO. 951
RUDDER TR(M TI\B
RUDDER TRIM
TAB INOICATOR
RuooEn mlM rae
NO. 26 MASTER LINK.PLATE AND KEEPER I? PLS)
TURNBUCKLES
LINK I ELEVATOR
KEEPER
ELEVATORTRIM TAR
NO. 25 MASTER LINI(.PLATE I\ND KEEPER (2 PLSJ
ELEVATORTRIMTAB
TRIM TI\B
INDICATOR TRI\NIMIT(ER
Fir" 1´•
Page 2014
SERYICE LETTER ND. 553
NO. JS
MASTER LINK. PLATE
FIND KEEPER
MODELS.W. 6W*. 5880. 600U. 5055. 520. ~14PL8)586 5561\. 5806. S)OF. 880 6555, 6586.
COVER ASSY NO. 35
(REF) MASTER LINK. PLATE
ANO KEEPER 12 PL6)
N0.96MASTER LINK, PLATE
ANO KEEPER 12 PLSI
CONTROL COLUMNLINK IREFI
KEEPER
MODELS 1IBOFL. BBOFL(P1, 056T. BB(IV.BIIOW. 881, 685, 850. 850/\, 8508. 8550,
COVER ASSY
NO.55MASTER LINK.PLATE ANDKEEPER 12 PLSL
CONTROLCOLUMNIRE r)
LEFT INSTALLATION SHOWN
5163111 INSTPILIPITION OPPOllrl
Fipm 2.
Page 3 of 4
SERVICE LET~ER NO. 863
4 IF any "keeper" is missing from chain master link, install new X21, chain link assembly with plate and "keeper"and proceed to step 8.
6. Reinstall tail cone and inspection panels using existing hardware.
6. Remove cover assemblies from pilot and copilot control columns, as necessary, to gain access to chain assemblies
(refer to Figure 2).
NOTE
On Models 600, SWh 6008, 600U, 6008, 620, 660, 660A,
660E, 660F, 680, 680E, 680F, 680F(P) and ?20, it will be
necessary to remove carpet and noor panels to gain secess to
control column chains below fuselage floor.
Using a nashlight and inspection mirror. impact all chain master links to assure that plates and "keepers" are
installed and secured properly (refer to Figure 2).
8. Lf"keepra" ansecured properly, proceed to step 10.
g~ If any ’keeper" is missing from chain master link, install new YS6 chain link assembly with plate and "keeper"and proceed to step 10.
10. Reinstall all access panels, cover assemblies and ca~peting.
11. Pill out and mail Compliance Card.
ELECTRICAL LOAD: NO CHANGE.
WEIGHT AND BALANCE: NO CHANGE.
SPARES AFFECTED: NO.
PUBLICATIONS AFFECTED: NONE.
RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service Latter No.
858, dated 8 September 1882, entitled "Plight Control Chain Connector Link Inspection", accomplished (date)
page I of 4
Sewice Letter CulfstreamAmericanroRvoa*rloh
Commands DIrlIlon1001 Norm RDi*IWII AYLnYe,Bathany, 73008
SERVICE LETTER NO 314
1 October 1982
MAIN LANDING GEAR WHEEL BEARING AND AXLE HOUSING INSPECTION
MODELS AFFECTED: MODEL 690C, SERIAL NOS. 11600 THRU 11721, 11726 AND 11727.
MODEL 690D, SERIAL NOS. 16002 THRU 15004, 16W6, 15008. 15009, 15013, 15014 AND
15016.
MODEL 695, SERIAL NOS. 85000 THRU 96084.
MODEL 695A, SERIAL NOS. 96001 THRU 86055, 96037 AND 86039 THRU 96042
REASON FOR PUBLICATION: POSSIBLE CONTAMINATION OF AXLE GREASE WITH METAL SHAVINGS.
COMPLIANCE: DURING NEXT 100-HOUR INSPECTION.
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE
COMPLYING WITH THIS SERVICE LETTER, CONTACT
YOUR NEAREST CULFSTREAM COMMANDER
AUTHORIZED SERVICENTER.
BY WHOM WORK WILL BE ACCOMPLISHED: A d P MECHANIC OR E~UIVALENT.
APPROVAL: FAA DOA SW-2 APPROVED.
ESTIMATED MAN HOURS: THREE (8) HOURS.
PARTS DATA: 1 EA. COMPLIANCE CARD.
SPECll\LTOOLS: NONE.
ACCOMPLISHMENT INSTRUCTIONS:
I. Jack si~lsne as outlined in Chapter 7 of the Airplane Maintenance Manual.
2. Remove left end right main landing gear wheels as outlined in Chapter 32 of the Airplane Maintenance Manual.
8. Thoroughly clean and inspect wheel hubs and wheel bearings as outlined in Chapter 32 of the AirplaneMaintenance Manual.
4. Assure that any contaminants are removed from inside the axle housing.
NOTE
The use of a magnetic probe and solvent Rush will facilitate
contaminant removal.
5. After assuring that wheel hubs, wheel bearings and anles are satisfactory, repack bearings and reinstall wheels
on airplane as outlined in Chapter 32 of the Airplane Maintenance Manual.
6 Fill out and mail Compliance Card.
ELECTRICAL LOAD: NO CHANGE.
WEIGHT IND BALANCE: NO CHANGE.
Page 1 of2
SERVICE LETI~ER NO. 364
SPARES AFFECTED: NO.
PUBUCATIONS AFFECTED: NO.
RECORD COMPLI~NCE: Make an appropriate entry in airplane maintenanee reeords as follows: Service Letter No.
584, dated 1 October ~882, entitled "Main Landing Csar Wheel Bearing and A~le Inspection", aeeomplished
(date)
Page 2 of 2
Service Letter GulfstreamAerospace
SERVICE LETTER NO. 868
SO November 1Bsa
FUSELAGE STATION 386.82 SCREW TORCUE INSPECTION
MODELS AFFEOTED: MODELS 880, 080A AND 8O0R, SERIAL NOS. 11001 THRU 11688.
MODEL 0800, SERIAL NOS. 11800 THRU 11?21, 11126 AND 1112?.
MODEL BBOD, SERIAL NO8. 18001 THRU 16004, 16008, 16008 THRU 16011 AND 16014.
MODEL 606, SERIAL NOS. 88000 THRU 86084.
MODEL OOOA, 8ERIAL NOS. 88001 THRU 8009? AND 88058 THRU BBOM
REASON FOR PUBLCAT1ON: TO ASSURE THAT SCREWS ATTI\CHINCI ANGLES TO FRAME ARE TORQUED.
COMPLIANCE: DURMQ NEXT 100-HOUR INSPECTION.
MOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE
COMPLYING W1TH THIS SERVICE LETI~R. CONTACT
YOUR NEAREW OULPEITREAM COMMANDER
AUTnORIZED81ERVICENT&R.
sY WHOM WORN WILL Be CICCO~PLISHED: A P MECHANIC OR
APPROVAL: ENGINEQRIND DEBION ASPECTS ARE: PILA APPROVED.
ESTIMATED BAN HOURS: MODEL11880, 080A AND 880B TWO (2) HOURS.
MODEL 880C, SERIAL NOS. 11800 THRU 11118 EIGHT (8) HOURS.
MODEL 885, SERIAL NO. 86000 THRU 96084 EIGHT (8) HOURS.
MODEL 685A, SERIAL NOS. 96001 THRU 88018 EIDIIT (8) HOURS.
MODEL BB0C; 8ERIAL NOS. 11118 THRU 11721 ONE (1) HOUR
MODEL 080D, SERIAL NOS. 16001 THRU 15014 ONE (1) HOUR.
MODEL 886A, SERIAL NOS. 88018 THRU 88048 ONE (1) HOUR,
PARTS DATA: 1 EACH COMPLIANCE CARD.
8PECIALTOOL9: TORqUE WRENCH.
ACCOMPLISHMENT INSTRUDTIONS:
I. Cain aacesa to fuselage ti~ams at station 880.82.
2. Assure that a ANBBO-1OL washer Is installed between the angle and fiane on both left and right lower inboanl
attaching screws (refer to Figure Il.
S. Tonpe existing four (4) lower screwsthat attach 8300a4´•16 and -18 angles to Rama to a torque value of 20 to
26 inch-pounds plus running torque (refer to Figure 1).
NOTC:
Running torque i the tonpa that is required to run the nut
upon the screw threads.
Page 1 of 2
BERVICE IET~R NO. 968
1. On Model BsOD and BRSA only, torque the hKo (2) upper anaws that attach 81M12C15 and -18 angles to irame
to a taque value ,f 50 to ?0 inch-pounds plus NMing torque (,r, t. Figure 1).
6. On all other models, torque the tare (2) upper screws that attach 810024-16 and -18 angles to Rama to a toqua
value of 20 a a6 inch-pounds plus running torque (rafar to Figure 1).
8. Fill out and mail Compliance Card.
ILECTRICILLOID: NOCHANOE.
WEI(IH~ANDB*UNCE: NOCHANOE.
SFARIS AFFECTED: NO.
FUILICATK)NS AFFECTED: NONE.
RECORD COMPLI*NCE: MsLs an appropriate entry in airplane maintenance records as follows: Service Letter No.
556, dated 80 November 1882, entitled "Puwlaga Station 888.82 Screw Tor~Lue InapaWon´•’, acmmpliahsd
ronour: scnm sLS)(REFER m 8ssp nNo 6.1
ExlsnNa ad?c~snNGLE
ExlsnNo aoa2clsPINGLE IREF)
d
roBoUE 8cnEw*PLS)20 TO ?B IN´•LBS PLUSRUNNING TOA(IUE
PSSURE TnAT WgBa(OL WI\(UIERIs IN(ITI\LLED BETWEEN PNGLE
FIND FRPIME, P~LSPI\CER. FOR
THELIE mo (21 ihleonno scREws
FMELIPBE 8T~TION 38B82FAPIME PSSY
Fi~un
page 2 012
Service Lettev GulfstreamAerospace
SERVICE LE~TER NO. 356
25 Februarp 1983
PNEUMATIC TUBE ASSEMBLY INSPECTION
MODELS AFFECTED: MODEL 690C, SERIAL NOS. 11600 THRU 11721, 11723, 11126 AND 11727.
MODEL 690D. SERIAL NOS. 15001 THRU 15004, 150O6. 15008 THRU 16011, 15014, iSOiB,
16021 AND 1j022.
MODEL 695, SERIAL NOS 95000 THRU 95084.
MODEL 695r\. SERIAL NOS. 96001 THRU 96053
REASON FOR PUBLICATION: TO ASSURE THAT NO INTERFERENCE EXISTS BETWEEN PNEUMATIC TUBE
ASSEMBLY AND TOR9UE LIMITING TRANSDUCERIN RIGHT NACELLE
COMPLIANCE. WITH NEXT 100 HOURS TIME IN SERVICE.
NOTE
´•I:l´•i´•a´•: i
1F ANY PROBLEMS ARE ENCOUNTERED WHILE
COMPLYING WITH THIS SERVICE LETTER. CONTACT
YOUR NE*RTSP UULrSTREIM CoMMANDER
AUTHORIZED SERVICENTER
sY WHOM WORK WILL SE ACCOMPLISHED A P MECHANIC OR E~UIVALENT.
APPROVAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED
ESTIMATED MAN HOURS: INSPECT TUBE ASSEMBLY THIRTY (301 MINUTES
ROTATE TRANSDUCER ONE AND ONE-HALF(1 51 HOURS
:i-
PARTS DATA: i EACH COMPLIANCE CARD.
SPECIAL TOOLS: NONE
ACCOMPLISHMENT INSTRUCTIONS:
1 Remove forward access door from top of right nacelle to gain access to torque limiting transducer. The words
TOR~UE LIMITING should be stamped above tol´•que limiting transducer on engine fll´•ewall trefer to Figure ii.
2 inspect far possible interference between torque limiting tmnsducer and pneumatic tube 8´•~embt:
3. If no interference exists between torque limiting transducer and pneumatic tubs assembly, reinstall access door
on nacelle and proceed to step 5.
4. If interference exists between torque limiting transducer and pneumatic tube assembly, proceed as follows:
a. Remove upper cowling rom right engine.
b. Disconnect the pressure and vent lines from their respective Rttinga on the torque limiting transducer I
c. Disconnect electrical connector from transdueer
C d Remove nuts and washers that secure torque limiting transducer to engine fire\rall.
As Reecivod ByAIP j
,a~.._
...~_.,.i.
-C
SER\’ICE LETTER NO. 356
I cavnm~lCAUTION
Be careful not to damage threads on fittings when pullingtransducer through engine Brerall.
Remove tal.que limiting tran.ducer from engine firewall
F Slot torque limiting transducer mounting holes in engine firewall, as necessary, in order to rotate
tmnsdueer to clear pneumatic tube assembly
g Reinstall torque limiting transducer on engine Fnewali using enisting washers and nuts,
h. If any gaps are left in engine flrewali after transducer is reinstalled, seal around washers and nuts with
Pro-seal 700 firewall sealant or an equivalent sealant.
Reconnect pressure and vent lines to torque liwting transducer assuring that lines are connected to the
plaper Bttings.
j. Reconnect electrical connector to transdueer.
k StR1´•t right engine as outlined in Pilot Operating HandbooB and assure that no lealis are evident at
rorque limiting transducer connections,
I. Shut down right engine.
m Reinstall upper eowling an right engine
n ,instsll ar..aa do~i un nar~lla C5 Fill out and mail Compliance Card.
ELECTAICAL LOAD: NO CHANGE,
WEIOMT AND BALANCE: NOCHANGE.
SPARES nFFECTED: NO.
PUBLICATIONS PIFFECTED: NONE.
RECORD COMPLIANCE: Malre an appropriate entry in airplane maintenance records as follows: Service Letter No
356. dated 25 February 1983, entitled Tube Assembly inspection, accomplished Idate)
REMOVE THII MCESS
9DOOR TO EXWSE TOR(IUE
LIMITING TR~NSDUCER
COWLINO IREFI 8UPPER ENGINE
(REFINI\CELLE
As Roc,ived Byi A’" i:Bigure i.
’"5:
Page 2 of 3
1.._..~
I_
Senrice Letter CulfstreamAerospace
SERVICE LETTER NO. 3S7A
NoSI? mifa ´•ntu,m I4 November 1983
AILERON LEADING EDGE SKIN MODIFICATION
MOOELS AFFECTED: MODEL 890C, SERIAL NOS. 11800 THRU 11884 AND 11866 THRU 11721, 11723, 11726
AND 11127.(SEE NOTE).MODEL 69011, SERIAL NOS 15001 THRU 15006, 15008 THRU 15011, 16014, 16016 AND
15018
MODEL 695, SERIAL NOS. 95000 THRU 95084. (SEE NOTE).
MODEL 695A, SERIAL NOS. 86001 THRU 96037, 96039, 96040, 96042, 96044 THRU 96052.
NOTE
FOR MODEL 690C, SERIAL NOS. 11600 THRU 11666
AND MODEL 695, SERIAL NOS. 85000 THUR 95063,
SERVICE BULLETIN NO. 118A MUST BE ACCOM-
PLISHED LN CONJUNCTION WITH THIS SERVICE
LETTER IF NOT ALREADY ACCOMPLISHED
IF BASIC SERVICE LETTER NO, 557 HAS BEEN
ACCOMPLISHED, DISREGARD THIS SERVICE LET-
TER.
REASON FOR PUBLIC~TION: POSSIBLE CRACKS IN AILERON LEADING EDGE SKINS 1N AREA AROUND IN-
BOARD BALANCE WEIGHT ATPACHINO SCREW HOLES.
COMPLIANCE: DURING NEXT 100-HOUR INSPECTION.
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE
COMPLYING WITH THIS SERVICE LETIER, CONTACT
YOUR NEAREST GULFSTREAM COMMANDER AU-
THORIZED SERVICENTER.
BY WHOM WORK WILL BE ACCOMPLlsHEO: A d P MECHANIC OR EqUIVALENT.
APPROVAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED.
ESTIMATED MPIN HOURS: PART I INSTALL ANOLES- NINE (8) HOURS.
PART II INSTALL ANGLES AND DOUBLERS ELEVEN (11) HOURS.
PARTS DATA: PARTS RE~UIRED TO COMPLY WITH THIS SERVICE LETTER MAY BE PROCURED THROUGH
YU~ Ns*sE9P OULVCI.I.IU MM.~NWR IMrm~adD SBRYICINIBO FO~ ILB~ hlilillllNPli THI ISERVICE LETTER, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN ORDERING SERVICE LETI~ER
NO 367A KIT CONSISTING OF THE FOLLOWING:
Page 1 of?
SERVICE LETTER NO 357A
qTY PART NO. DESCRIPI~ION
86 se. 250006´•RE3 Washer
1 ea. 2500(15-RE6 Doubler
1 ea. 2600(15-REll Doubler
2 ea. 260038-603 Angle1 as. Compliance Card
1 as. Service Letter No. 351A instructions
SPECIILTOOLS: HOLE FINDER
PICCOMPLISHMENT INSTRUCTIONS:
PART I
r EnurloN
When removing leR ailemn, oars should be taken to assure
that aileron trim tab actuator electrical cable is not broken
ordamaged.
i. Remove left and right ailerons as follows:
LIOTE
Do oot change the position of rad end an push-pull rod.
a. Disconnect aileron push-rod at aileron.
b Remove aileron hinge bolts and attaching herdwere.
c. While holding left sileron up, remove four screws that attach cannon plug secess plate to inboard end
of ailemn. Remove plate from aileron and disconnect trim tab actuator cannon plug.
d. Remove ailemn from airplane.
2 Remove inboard leading edge access doors from ailemns.
3. Inspect aileron leading edge skins in area around inboad balance weight attaohing screws. If no crac~s are found,
proceed to step 5.
4. If cracks are found in leading edge skins and are less than 0.50 inch long and a maximum of two (21 cracks per
hole, proceed to Part II. If cracks are longer than 0.50 inch and three (3) or more cracks per hole, contact
Gulfstream Commender ServiCenter, Bethany, Oklahoma before proceeding any further.
5. The following procedures apply to both left and right ailerons:
NQTF:
This modification dae~ not require rebalance oEailerons.
a. Remove screws attachinginboard balance weight to aileron leeding edge skin and remove balance
weight.
i
Page a of
8BRVICE LETTER NO. 35?A
alvrrll.rrsl
IN8laillsooosRr~wasNEnNnslnes4srlNo
UNDER SCREW HEAD U3 PLS1
Ij IOUTBD)12 E(1. SPACES
-tir 0.31´•´•
ACCESSOOOR
InEFI Ui~lLlt:t’:
I\ILERON
VIEW LOOKING DOWN R.H. AILERON-- ST"’gZ´•~
STA 115.31 EXISTING SCREWSIREFI EXISfINGGANG
CHANNEL IHEF)
WASHER IREFI
EXISTINGWEIGHT IREFI
260038803
NASIl3S84 BLIND
RIVET IREFIVIEW B-B
IF THIS ANGLE IS INSTALLED ON AlLERON,REFERTONDTEUNDEA8TEPSbOFPARTL
~II ne~dsDa)l
RIYET113 PLSI IREFIUNDER SCREW HEAD 143 PLSI
A
0.31´•´•-I- -I- f ´•i-+
AILERON VIEW LOOKING DOWN L.H. AILERON AILERON
STI\. 182.85 STA. 171´•31
EXISTING 8~LANCE SCREWS IREFI
WEIGHT IREF)
EXISTING GANG a WASHER IREFI
CHANNEL IREF)260039-6(15 ANGLE
VIEW A-A k NAS173BB4BLIND RIVET
IRE FI
IF THIS PINGLE IS INSTALLED ON A\ILERON,
REFER TO NOTE UNDER STEP S.b OF PART I´•
Figu~s i.
Page 3 of
SERYICE LE1TER NO 367A
b TsP~orarill iuefall s´•iatinp b.l´•nra ui.lht ad 210a8-~U3 angle on eilua~ ua~ng nia8n. nar~
and gang channel. Install a 250(105-RES washer under each screw head and tighten screws (refer to
Figure 1).
NOTE
If an angle has been added to aileron akin in area where
250039´•5~3 angle is to be riveted to akin, remove the angleand install 250039-509 angle with existing screws through
weight only. This angle was added to prevent oil canningon some ailerons. If edge of 260099-503 angle laps over any
one of the rivet holes in aileron skin more than half way,
trim nange of 260039-603 angle, assuring that an edgedistance of O.PSlnch can be maintained when riveting250039-605 angle to silsmn skin. Plug open holes usingNAS1738B4 blind riusta. If an edge distance cannot be
maintained, contact Culfstream Commander BsrviCenter
for further instructions.
c. Lacab and drill thirteen (13) 0.144 inch diameter holes through aileron skin and 250039-503 angles
(refer to Figure 1).
d. Remove balance weight and 250039-503 angles from aiieran and deburr all drilled holes
a. Reinstall e.isting balance weight and 250099-503 angles on aileron using existing aerews and gang
Ie Attach 250039-603 angles to aileran skin using NA81738B4 blind rivet (13 places) irefer to Figure 1).
channel. Assure that a 260005´•RE3 washer is installed under each screw head (refer to Figure 1).
~m.us and runrsll oil s~vq onsate~ a remainin..ilaron landing algo balenta aslghta and
install a 25(1005´•RE3 washer under each screw head (refer to Figure 1).
h. Install a 250005-RE3 washer under each screw head on aileron access dam balance weight.
6. Touch up paint on ailerons as required
7. Rainatall left and right ailerons an airplane as follows:
a. On left aileron, reconnect trim tab actuator cannon plug and reinstall secess plate on inboad end of
aileron using existing hardware.
b. Position aileron for attaching to airplane.
c. Install aileron hinge bolts and attaching hardware.
d. Connect sileron pushpull rod at aileron.
e. If push-pull rod length has been altered, streamline trailing edge of opposite silemn with trailing edge
of wing and outboard nap and secure aileron.
f A4iust push-pull rad length to align attaching bolt hole with hole in aileron hinge fitting when aileran
is in neutral position.
3. Reinstall access doors on ailerons.
9. Operate the ailerons thru their full travel and check UI assure that no interference exists between screw heeds
on aileron leading edge and wing close out skins.
LO. Fill out and mail Compliance Card specifying that Part 1 haa been aeeompliahsd.
Page ´•1 ol7
BIRVICE LE~ER NO 367A
i. If cracks in aileron leading edge skin are less than 0.60 inch Long (marimum of two (2) cracks per hole). stop
drill cracks using a No. 40 drill bit.
2. The following procedures apply to both lan and right ailerona:
NOTE
This modification does not require rebaianoe of ailerons.
a. Remove screws attaching inboard balance weight to ailsron Leeding edge skin and remove balance
weight.
b. Temporarily install e.isting balance weight, 260006-RES doubler (Ieft aileron), 250006-REll doubler
(right ailemn) and 250099-503 angles on ailemns using existing screws and gang channel. Install a N
250005-RE3 washer under each screw head and tighten screws (refer to Figure 2).
NOTE
If an angle has been added to aileron skin in area where
250098-605 angle is to be riveted to skin, remove the angleand install 250099-605 angle with existing screws through
weight only. This angle was added to prevent oil canningon some ailerons. If edge of 250059´•505 angle laps over any
one of the rivet holes in aileron skin more than half way,
trim nange on 260019605 angle, assuring that an edgedistance of 0.25-inch can be maintained when riveting250039-603 angle to aileron skin. Plug open hole, usingNA81138B4 blind riveb. If an edge distance cannot be
maintained, contact Culfstream Commander serviaonter
c. Locate end drill 0.144 inch diameter holes through aileron skin, doubler end angle (refer to Figure 21.
d. Remove balance weight, doubler and angle Bom aileron and deburr all drilled holes.
a. Reinstall existing balance weight, 260005-RE5 and -RE11 doublers and 250058-603 angles an ailemn
using existing screws and gang channel. Assure that a 250005-RE3 washer is installed under each
screw head (refer to Figure 2).
f Attach 260005-RES and -RE11 doublers and 260038´•503 angles to ailerons skin using NAS173BB4
blind rivets (refer to Figure 2).
g. Remove and reinstall all screws, one.ta_tims, on remaining aileron leading edge balance weights and
install a 2500(15-RE3 washer underBsrh screw head (refer to Figure 2).
h. Install a 260006-RE3 washer under each.crew heed on aileron access door balance weight.
3. Touch up paint on ailerons as required.
4. Roinstall left and right ailerons on airplane as follows:
a. On left aileron, reconnect trim tab actuator cannon plug and reinstall access plate on inboard end of
aileron using existing hardware.
b. Position ailemn for attaching to airplane.
c. Install ailsmn hinge bolts and attsohinghardware.
Page 6 of 7
SERVICE LETTER NO. 357A
AILERON ZSWOS´•REII INSTALL 250005-853 WASHER
1~11141- ´°OUBLT. UNO.RSCR.LIYe~)llUII.I
IBE(1. r--o.eo´•´•
i~i STA 18285
F
P:CA(STU~NERIITYP’i
rolanoa?rrmi %Fi3 EO. SPS:RIVET
ACCESS DOOR
IREFI
VIEW LOOKING DOWN R.H. AILERONEXISTINGSCREWS ZS0005´•RE(( DOUBLER(REF)
BLIND RIVET IREF)
WASHER IREFIZbW39WIANOLE
EXISTING BALANCEWEIGHT IREF)
0.31~’
EXISTING GANG
NAS1138B4 BLINd I I\ CHANNEL IREFI VIEW A~A
RIVET (REFI
IF THIS ANGLE IS INSTALLED ON AILERON
REFER TO NOTE UNDER STEP 2.5 OF PART li´•
INSTALL 250006-853 WASHER I\ILEAON
UNDER SCREW HEAD (~J PLS) NAS113880 BLIND STA. 176.312501105´•RES RIVETDOUBLER
O.BO’~
15 EO.ACCESS DOOR
IREFI
GOYI~TRUE
-I- i- I- r t
PICK UP EXISTING3 EO. SP. I -I iti L FASTENERS ITYP
~0´•31´•´• 12 EO. TOP AND BOTTOM)
r
AILERON~-I VIEW LOOKING DOWN L.H. AILERON57/\. 182.85 EXISTING BALANCE
WEIGHTSCREWS IREF1
NI\S1138B4 BLIND 2600DS´•RE3WASHER IREFIRIVETIREF)
10005´•RES
DOUBLER IREFI 250038-S03~NGLEEXISTINGCHANNEL IREF)
VIEW 8-B
IF THIS ANGLE IS INSTALLED ON I\ILERON.BLIND RIVET
REFER TO NOTE UNDER STEP 2.5 OF FART II
I InaFI
FigYISZ´•
Fags O ol
BERYICE LET~ER NO. SS’iA
d Connect ailsmn pul´•pull rod at aiieron.
e´• If PUsh-PULI rod length has been altered, streamline trailing edge of opposite aileron with trailing edge
of wing and outboard nap and secure aileron.
f A~ust push-pull rad length to align attaching bolt hole with hole in aileron hinge fitting when aileron
is in neutral position.
5 Reinstsll secess doors on ailerone.
6. Operate the ailerons thru their full travel and check to assure that no interference exists between screw heads
an aileron leading edge and wing close out skins.
Fill out and mail Compliance Card specifying that Part II has been accomplished
ELECTRICAL LOAD: NO CHANGE.
WEILIHT AND 8*LANCE: NO CHANGE.
SPI\RES AFFECTED: NO.
PUBLICI\TIONS AFFECTED: NONE.
RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance record, as follows: Service Letter No.
357A, dated 4 November 1985, entitled "Aileron Leading Edge Skin Modification", Part 1 accomplished I
(dste) Part II accomplished (date)
Page 1 of 7
9 Service Letter CulfstreamAerospace
SERVICE LETI~ER NO. 358
25 April 1883
OXYGEN MASK DISPENSER LID GASKET INSTALLATION
MODELS AFFECTED: MODEL 690C. SERIAL NOS. 11721 THRU 11?2?.
MODEL 690D, SERIAL NOS. 15001 THRU 16014, 15016, 15018, AND 15021.
MODEL 695A, SERIAL NOS. 96001 THRU 86052.
REASON FOR PUBUCATION: TO ASSURE AUTOMATIC OXYGEN MASK DEPLOYMENT.
COMPLIANCE: WITHIN NEXT 100-HOURS TIME IN SERVICE.
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE
COMPLYING WITH THIS SERVICE LE1TER CONTACT
YOUR NEAREST OULFSTREAM COMMANDER
AUTHORIZED SERVICENTER.
BYWHO.W~RIWIU.E*CCOMPLIBHED: I\LPMECH~NLC oRB9UIVhLENT.
APPROVAL: ENGINEERING DESIGN ASPECTS ARE ~AA APPROVED.
ESTIMATED MI\N HOURS: TWO (2) HOURS.
PARTS DATA: MATERIAL RE~UIRED TO COMPLY WITH THIS SERVICE LETTER MAY BE PROCURED
THROUGH YOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR $12.80.REFERENCE THIS SERVICE LETTER, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN ORDERING
SERVICE LETTER NO. 358 KIT CONSISTING OF THE FOLLOWING:
P~´• ´•Ygl~ mllp´•lllh~yl n*i~´•
qTY PARTNO. DELICRIPI~ION
14 ft. 1/8" i~ l/d" Poiyfoam hesaure Sensitive Tape1 se. ComplianeeCard1 ea. Service Letter No. 358 instruotions
SPECll\LTOOLS: NONE.
ACCOMPLISHMENT INSTRUCTIONS:
Tc~CAUTION
CARE SHOULD BE TAKEN TO PREVENT SOILING OF
VINYL FABRIC ON DISPENSER LIDS AND
HEADLINER WHILE ACCOMPLISHING THIS SERVICE
Page 1 of I
SERVICE LETTER NO. 558
7
OXYGEN DISPENSER
(REFI
_t
O
iiINP)
1A"X 114~ WLYFO~MTAPE I’) PLI1
LID FOR DUAL
MASK DISPENSER
IREFL
_t
a.lr´•IrvPI
LIO~FR.NOL.
IREFI
VIEW A-A
Fisurs i.
Page a ol 6
8BRVICE LGTTER NO. 558
I YIIYIYO)Stow lanyzrd card and tubing so that neither one is entangled or
under any lanyard valve. latch mechanism or device within the
container that would prevent it from falling properly when de-
ployed.
MOTE
Remove lonyard pin before starting to told the mask to make It
easier to fold.
8TEP 1; RESERVOIR B~O´•FIAST FOLD 8TEP 2: RESERVOIR BAB´•SECOND FOLD
CLIP ATTACHMENT HOLE
3,
STEP 3; RESERVOIR BP~(1´• THIRD FOLD STEP 4; FOLD RESERVOIR BA0 AWAY FROMMASK SPRING CLIP ATTACHMENTnOLEINOOUBLEFOLD.
STEP 8: TURN MASK OPEN SIM UP AND STEP 8; BRING FOLDED REBEBVOIR Bn(lFOLD HEADSTRAP INTO FACE UP OVER 8108 OF FACE PIECE ANDPIECE. PLACE INSIDE IN DOUBLE FOLD.
wort
DO NOT I(INK THE TUBE WHEN FOLDINGFIEF I; WITH RE8ERVMR 81\0 FOLDED IT INTO MI\S~. ENSURE TUBE COIL MOE8
IN .i\er nscs, rmL maan ansv IN cllmNuoy. DIREETION PWM Y\.-TUBE ON FOLOED Bn(i. YARD VALVE OUTLET.
FILI?. IOhast(of 2)
Page 8 of 5
BERVICE LETTER NO. 568
3AIRPLANES EOUIPPED WITH THE BENCH SEAT HAVE Pi DUAL MASK CONTAINER ABOVE THE BENCH. RESERVOIR BnOSSTORED IN DUAL CONTAINERS ARE FOLDED SAME ASIN G1NOLE MASK CONTAINER. NOTE ILLUSTRATION OF TUBEINSTALLATION IN SPRING RETAINERS.
g- ii
~i
STEP B; REINSERT LANYARD PIN
STEP g: PLACE MASK IN 8TORI\OE BOX WITH OPEN 811)6 OF Mn81( UP (TOWARDS IOP OF CABIN) ANO CLOSE LID.
ENSURE HINGE PINS ON BOX LID ARE EN(IA(IED 1N PIN RECEPTACLES ON BOX INNER SURFACE WHEN
INsmLLINa LID. TO CLOSE LID. PUSH FIRMLY ON LATCH SIDE AND, 81MULTI\NEOUSLY. USING A POINTEDOBIECTSUCH 1\6~ BALLPWINT PEN OR HEAVY PAPER CLIP INSERTED THROUGH THE EYELETTED
P~OY..N(YWINLI ,LL O.TE.TL
Fl~ura 2. (8haet? of 2)
i. Lower lids on all passenger oxygen mask dispensers by inserting a thin pointed metal objeet, such as a heavypaper clip, in lid hole and push up. Lid should drop.
2. Clean inside surfaoe of lid in area where tape is to be installed.
S. Cut and install VR-ineh polyfoam pressure sensitive tape on inside surface of lids (refer to Figure i).
4. Repack oxygen masks and close dispenser lids (refer to Figure 2).
6. Perform a pound cheek of the passenger oxygen distributing system as follows:
a. Passenger oxygen switch shoi~ld he in AUTO position. Passenger oxygen mask module doors should not
open.
b. Turn passenger oxygen switch to ON position.
NOTE
All passenger oxygen mask module doors should open and
masks should drop out, held suspended by the lanyerd card
andpin.
c. Turn passenger oxygen switch to OFF position.
a and pin m ane Daal t~ prruu~ In ly~am b nllm d.or I´•1Ei~B in b.
Pnee(ofl
SEIIJICF. I.gTTER NO 3~H
5. Rspnl ra~gsn Mll´• ´•d E~K dig.nl.r lids in~ to rllM 21
7. Fill eat and mail Compliance Card.
ELECSRICAL LOAD: NO CHANCE.
WEIGHT ANO BALANCE: NO CHANCE.
SPARES AFFECTED: NO.
PUBLICPITIONS *FF~CTED: NONE.
RECORD COMPLIANCE: Make an appropriahe entry in airplane maintenanee records as follows: Service Letter No. 958,dated 26 April 1988, entitled "Oxysen Mask Dispense. Lid Casket installation’: accomplished (date)
C
Page 5 ol I
C~IIService Letter GulfstreamAerospace
SERVICE LETTER NO. 359
17 June 1083
FUSELAGE STATION 386.82 FRAME ASSEMBLY MODIFICATION
MODELS AFFECTED: MODEL 690C. SERIAL NOS. 11600 THRU 11651 PtND 11633 THRU 11729.
MODEL 690D, SERIAL NOS. 15001 THRU 15024.
MODEL 695, SERIAL NOS. 96000 THRU 96084.
MODEL 69SA SERIAL NOS. 98002 THRU 96055.
NOTE
IT IS RECOMMENDED THAT SERVICE LETI~ER NO.
355 BE ACCOMPLISHED IN CONJUNCTION WITH THIS
SERVICE LETTER.
REASON FOR PUBLICATION: POSSIBLE CRACK IN VERTICAL LEG OF BRACE IPIN 310024-63) THAT
ATTACHES TO FUSELAGE FRAME.
COMPLIANCE: DURING NEXT 100-HOUR INSPECTION.
.arr
IF ANY PROBLEMS ARE ENCOUNTERED WHILE
COMPLYING WITH THIS SERVICE LETTER, CONTACT
YOUR NEARESL~ DULFSTREAM COMMANDER
AUTHORIZED SERVICENTER.
BY WHOM WORK WILL BE I\CCOMPLISHED: A Be P MECHANIC OR EQUIVALENT
APPROVAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED.
ESTIMATED MAN HOURS: MODEL 690C, SERIAL NOS. 11600 THRU 11631 AND 11633 THRU 11718 TWELVE (12)
HOURS.MODEL 695, SERIAL NOS. 95000 THRU 95084 TWELVE (12) HOURS.
MODEL 695A, SERIAL NOS. 96002 THRU 93013 AND 96018 TWELVE (12) HOURS.
MODEL 690C, SERIAL NOS. 11119 THRU 11729 THREE (31 HOURS.
MODEL 690D, SERIAL NOS. 15001 THRU 15024 THREE (31 HOURS.
MODEL 69SA, SERIAL NOS. 96014 THRU 96017 AND 96019 THRU 96055 THREE (3)
HOURS
PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE LE~I‘ER MAY BE PROCURED THROUGH
YOUR NEAREST DULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR 86.40. REFERENCE THIS
SERVICE LETTER, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN ORDERING SERVICE LE1TER
NO 369 KIT CONSISTING OF THE FOLLOWING:
PRICI TcI WITHOUT NOIICI
9TY PART NO DESCRIPTION
2 os. 310024-103 Gusset
2 ea. 310024´•105 Shim
L ea Complionce Card
I ea Service Letter No. 359 instructions
Page 1 of 6
SERVICE NO. 359
AREAS TO BE INSPECTEDAND MODIFIED
/kExlmNo 310024´•53
BRACE IREF)
d
VIEW LOOKING AFT
AT FUSELAGE STATION 386.82
Fipur´•l.
Page 2 ol 5
SERVICE LE~ITER NO. 359
MODELS 690D AND 695*
EXISTINGWEBIREF)
C-‘s~
"p,
EXISTING HOLES
Ms2o47oaoe RIVETS I I-LPC MSzM7aaol RIVETon on
1*6173888 BLIND RIVETS I IIl V ~I NAS1738B~ BLIND RIVET
310024´•103(IUISET
f+INSPECT
EXISTING HOLESCRACKS
MS20470ADB RIVETSORNAS(738BB BLIND RIVETS
IIrvPI
NI\S1738BB BLIND RIVET
EXISTINE MS2MIO~DB RIVET
310024´•53 OR
BRACE
IREF)
310029´•(05 SHIN
t EXISTING HOLEMSZMIOPIDB RIVETOR
NAS173888 BLIND RIVET
EXISTING FRAME
IREFI
VIEW LOOKING FORWARD
LEFT SIDE SHOWNRIGHT SIDE OPPOSITE
Figure Z. ISlsst i ol 21
Page 3 al 5
SERVICE LETTER NO. 389
MODELS 690C FIND 695
EXISTINOWEB
IRE Fl
510024´•105GUSSET
EXISTINOHOLESMSZM70nOSRIVETS
ORMSZ0170AD4 RIVET
N~S115885 BLIND RIVETSORNAhl738klBLIND RIVET
INSPECTCRACKS
+t~
ExlsnNo HOLESMS2MIOI\DB RIVETS
EXISTINGOR
310024´•53 310021´•105 FHIMNAS173BB8 BLIND RIVETS
BRACE
(REFI IIRIVETS
I)
1 ITYPIPPVO~; ~jlS113BBSBL(ND RIVETS
t IXIITIN6 ~R´•MI
IREFI
VIEW LOOKING FORWARD
LEFT SIDE SHOWN
RIGHT SIDE OPPOSITE
El(Iura 2. laaat 2 af 2)
Page 4 of 5
SEAVICE LE~EK NO. 359
C EPECIIILTODLS: NONE.
ACCOMPLISHMENT INSTRUCTIONS:
1. Gain access to frame assembly at fuselage station 386.82.
2. Inspect left and right side of existing b~ame assembly brace (PIN 310024-53) for possible cracks in area oljoggleirefbr to Bigure 1).
3. If either end of brace is completely severed, inspect frame assembly $r any damage and contact GulBtreem
Aerospace ServiCenter, Bethany, Oklahoma before proceeding any further.
4 11 cracks ore found in brace but are not all the.way through brace, stop drill cracks using a No. 40 drill bit and
proceed to step 6.
5. 11 no cracks are found, proceed to step B.
6. Locate, drill and install 310024-103 gusset and 310024-105 ahim on left and right side of frame assembly (refer
to Figure 21.
7. Fill out and mail Compliance Card.
ELECTRICAL LOAD: NO CHANGE.
WEIGHT AND BALANCE: NO CHANGE.
SPARES AFFECTED: NONE.
PUBLICATIONS AFFECTED: The Illustrated Parts Catalog change required by this document will be incorporated at
the next scheduled revision
j RECORD COMPLmNCE: Make an appropriate entry in airplane maintenance records as follows: Service Letter No.
359, dated 17 June 1983, entitled "Fuaelage Station 386.82 Frame Assembly accomplished tdate)
Page 5 of 5
V1
i Service Letter ~8Nd/lCulfstreamAerospace
SERVICE LET~ER NO. 360
1 August 1885
FLAP BRACKET INSPECTION
MODELS AFFECTED: MODEL 68011, SERIAL NOS. 15001 THRU 15018.
MODEL BSSA, SERIAL NOS. 88001 THRU 96050.
REASON FOR PUBLICATION: POSSIBLE OPEN DRILLED HOLES IN FLAP BRACKET CLIP.
COMPLIANCE: DURING NEXT 100´•HOUR INSPECTION.
NOTE
IF ANY.PROBLEMS ARE ENCOUNTERD WHILECOMPLYI~D WITH THIS SERVICE LETTER, CONTACT
YOUR NEAREST (IULFSTREAM COMMANDER
AUTHORIZED SERYICENTER.
BY WHOM WORK WILL BE ACCOMPLISHED: A P MECHANIC OR EQUIVALENT.
IPPROV~L:
ESTIMATED MAN HOURS: INSPECT FLAP BRACKET ONE (1) HOUR.
MODIFY FLAP BRACKET TEN (10) HOURS.
PARTS DATA: PARTS RE9UIREO TO COMPLY WITH THIS SERVICE LE1TER MAY BE PROCURED THROUGH
YOUR NEAREST OULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR: KB NO. 1-(26.00 or KIT NO.
2 525.00. REFERENCE THIS SERVICE LETTER, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN
ORDERING SERVICE LETTER NO. 380 KIT CONSISTING OF THE FOLLOWING:
olo´• au,l´•a I~EnYlp´• Wln~ul HOll~
KIT NO. 1- LEET FLAP BRACKETKIT NO. 2 RIGHT FLAP BRACKET
Kit Kit
No. 1 No. 2
~TY PTY PART NO DESCRIPTION
L ea. 51o103-S1 DoublerLea. 510109-92 Doubler
L ee. 1 ea. 510109-83 Radius Block
1 es. 1 ea. 510103-S5 ClipL es. 1 ea. 5101(13-81 Shim
L ea. 510109-59 Doubler
1 an. 510103510 Doubler
lee. 1 ea. 510109-511 Tapered shim
L ea. 1 ea. Compliance Card
L se. 1 es. Service Letter No. 560 Instructions
p,, 1 of 6
SERVICE LETTER NO. 360
FT~GHLIHT
PICCOMPLISHMENT INSTRUCTIONS:
i. Remove upper forward baggage compartment liner to gain access to left and right nap brackets that are located
above the fuselage lavatory oompartment.
2. Using a flashlight and an inspection mirror, inspect lower inboard clip and lower bracket on left and nght Oapbrackets for open drilled holes in clip and bracket (refer to Figure 1).
8. If no open drilled holes are located in lower flap brackets or clips, reinstall baggage compartment liner and
proceed to step 6.
4. If open drilled holes are located in lower napbraekets or clips, proceed as follows:
a. Disconnect and remove aileron servo and servo brackets to facilitate modilcation offlap brackets.
b. Disconnect and remove push-pull rod a88embly from nap bracket pulley assemblies.
o. Remove lavatory interior overhead panels and aft pressure bulkhead interior panels to expose aft
pressurebulkhead.
d. Trim lower end of existing clip and drill out upper two (2) existing rivets attaching clip to vertical angle(refer to Figure 2).
a. Drill and install 610103-51 doubler (leEt aide) andior 61010352 doubler (right side) and 510103-SS radiusblack on existing clip and vertical angle picking up rivet hole locations noted in step d. (refer to Figure9).
I. Locate, drill and install 51010556 clip, 510105´•57 shim, 610105-58 doubler (left side) andior 61010S-S10a~uulr iri61~ ~na ui´•~ (ron~ a Filu~ 31 C
J~IOH 1CAUTION
Drill holes in existing lower bracket first to assure proper
edge distance is maintained.
g. Reinstall push´•pull rod assembly on nap bracket pulley assemblies using existing hardware.
h. If necessary, trim SlolOS´•S1 andior -92 doublers and 51010S´•SS clip O clear push-pull rod assembly a
minimum of O.1B8´•inah and reprime with zinc chromate primer.
i. Reinstall ailemn servo brackets and aileron servo using existing hardware.
j. Check nap central rigging as outlined in Chapter 21 of the Airplane Maintenance Manual.
k. Check aileron cable tensions as outlined in Chapter 21 of the Airplane Maintenance Manual.
i. Using sealant conforming to Military Specification MIL´•6´•8802, seal rivet heads in iavatorycompartment overhead per procedures outlined in Chapter 20 of the Airplane Maintenance Manual.
Allow sealant to cure properly prior to installing lavatory upholstery panels.
m. Reinstall lavatory overhead panels and aft pressure bulkhead interior panels.
C
Page 2 of 6
SERVICE LETTER NO. 36(1
3YERTICI\LANaLE
t~ II i i~++
IREF)
ExlanNo CLIP
(REF)
jINSPECT ~FT ENO OF THIS
BRACKET P.ND CLIP FORLEFT FLAP sRnCKET
OPEN DRILLED HOLES(REF)
CVIEW LOOKING FORWARD
R.e.P*R
(REF)
AT REAR WING SPAR
VERTICI\L~NGLE
i r-i~bl,RE, EXISTIND CLIP
rL~ i(nEF,
-i-
INSPECT P~FT END OF THISRIGHT FLAP BRACKET
sAIICKET AND CLIP FOR
OPEN DRILLED HOLES (REF)
FlgUIB i.
Page 3 of 6
SEKVICE LE~ER NO. 380
(REF)
t -t- C CrlNBO
r--
i
Al I II;IJI A
DRILL OUT TOPTWO (1)
i
LEFT FLAP BRACKET
(REP)VIEW LOOKING FORWPIRD C
EXISTING CLIP TRIM LOWER END
(REF) ONLY 1.0" RADIUS
CLEAR 510103S1 DOUBLER)
f
DRILL OUT TOPTWO 12) RIVETS
THe~T A~*CH CLIP
TO VERTICI\L I\N(ILE
f
BULKHE~O
(REF) VIEW A-A ‘YERTIC*L PINGLE
(nER
LEFT INSTALLATION SHOWNRIGHT INSTALLATION OPPOSITE i
Fisure 2.
Paee 4 of 6
SERVICE LE1TgR NO. 360
REAR SPAR
Q~
(REF)
A III I IIA IA
LEFT FLAP BRACKET
cnEF, VIEW LOOKING FORWARDNAS1138R4 BLIND RIVETS 510103-61 DOUBLEROR M8Z0470AD4 RIVETS
510103979HIMPICK UP EXISTING HOLESIN WEB S~P103´•SB 510103´•88 DOUBLER
EYISTINO LOWER
BRACKET EXISTING WEB(REF) dgl (RER
NlnnasleuNonnr.rOR M92041011D4 RIVET 510103-911 TAPERED SHIM
(8 PLS)~5173(189 BLIND RIVET
88201704\04 RIVET
(4 PLS)I
VIEW B-B510103-911X TAPERED SHIM
I~ 51o103-9laHIM
\"h510109-81 CLIP
51010381DOUBLER DOUBLER NI\S17388B BLIND RIVETS
8\’ OR
MS204101\D5 RIVETS
B 510103´•83RADIUS BLOCK
o.ls´•´• MIN. +iI
PICK UP EXISTING HOLE VLRTIC*LPINOLE
VIEW A-A EX’ST’NG CLIP NAS1138B4 BLIND RIVET (888)cnEF,
LEFT INSTALLATION SHOWN
Fleurs 3. RIGHT INSTALLATION OPPOSITE
Page 6 oE6
SERVICE LE1TER NO. 360
s ~inarsa linol C6. Fill out and mail Compliance Card.
ELECTRICPIL LOAD: NO CHANGE
WEIGHT AND SALANCE: NO CHANGE
SPPIREB AFFECTED: NO.
PUBLICATIONS AFFECTED: NONE.
RECORD COMPLIP~NCE: Make an appropriate entry in airplane maintenance reeai´•dl as follows: SBNice Letter No.360, dated 1 August 1833. entitled "Flap Bracket Inspection". accomplished idatel
C
Paea 6 of 6
Service. .Letteu GulfstreamAerospace
SERVICE LETTER NO, 361
4 November 1983
HYDRAVLIC HOSE REPLACEMENT
MODELS AFFECTED: MODEL 690D, SERIAL NOS. 1SOPSTHRU 16029.
MODEL 896A, SERIAL NOS. 06066, 98058 THRU 96061, 98063 ANO 96069.
REASON FOR PUBLICATION: TO ELIMINATE POSSIBLE INTERFERENCE BETWEEN HYDRAULIC HOSE
ASSEMBLY AND ELECTRICAL WIRING.
COMPLIANCE: DURING NEXT 100-HOUR INSPECTION.
NOTE
IF ANY PROBLEMS AP;E ENCOUNTERED WHILE
COMPLYING WPH THIS SERVICE LETTER, CONTACT
YOUR NEAREST CULFSTREAM COMMANDER
AUTHORIZED SERVICENTER.
BY WHOM WORK WILL Be ACCOMPLlSHED: A 6r P MECHANIC OR E9UIVALENT.
APPROVAL: ENGINEERING DESIGN ASPECTS ARE BAA APPROVED.
ONE (1) HOUR.ESTIMATED MAN HOURS:
PARTS DATA: PARTS REqUIRED TO COMPLY WITH THIS SERVICE LETTER MAY BE PROCURED THROUGHYOUR NEAREST GULFWREAM COMMANDER AUTHORIZED SERVICENTER FOR 513.00. REFERENCE THIS
SERVICE LETTER, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN ORDERING SERVICE LETI~ER
NO. 361 KIT CONSISTING OQ THE FOLLOWING:
~TY PARTNO. DESCRIPTION
1 ea. 790544-89 Hos~Assy3 R. U" (MIL-I-?´•4bl) Vinyl Tape3 ea. MS3S61-19 Tiedawn Strap1 se. Compliance Card
1 ee. Service Letter No. 961 Instructions
SPECIAL TOOLS: NONE.
ACCOMPPLSHMEET INSTRUCTIONS:
1. Gain access to nap actuating cylinder through baggage compartment door.
2. Remove baggage compartment liner, as necessary, to expose nap actuating cylinder. The nap actuating cylinderis locatedjust forward and above the baggage compartment door.
3. Reduce airplane hydraulic system pressure to zero.
4. Remove and discard existing naps up hydraulic hose assembly (Pn~i 1905(4-81) from nap actuating cylinder (refer
C6. Install 190344-89 hose assembly (refer to Figure 1).
Page 1 of 2
SERYICE LE~ER NO. 381
a wrer uirr buhdb .ilh´•r lid. ov.r ho* ~th Yrul~h ringl inp aai ssiure ea.h end of
tape using MS9367´•18 tiedown straps (refer to Figure i).
Perform leak oheok of the nap actuating systee tb~’a maximum normal operating pressure of 1000 psi.
8. Reinstall baggage compartm.dliner:
9. Fill out end mail Compliance Card.
ELECTRICAL LOAD: NO
WEIGHT AND BALI\NCE: NO CHANDE.
SPI\RES AFFECTED: NO.
PUBLICATIONS AFFECTED: The Illustrated Pens Catalog change required by this document will be incorporated stthe nert scheduled revision.
RECORD COMPLIP~NCE: Make an appropriate entry in airplane maintenance records as follows: Service Letter No.361, dated 4 November 1985, enwtled "Hydraulic Hose Replacement", accomplished (date)
FLPIPACTUATINOCYLINDER IREFL
REMOVE EXISTING HO8EA88Y AND IN8TI\LL78(1~4´•88 nOSE ASSY
WRAP EXIITINO WIREBUNDLE W1Tn 11’~ VINYLTAPE AND 880088 WITH
MS)SB7´•1´•8 TIEDOWNSTR*PI
VIIW LOOKING UP AND OUTED
AT EAOOAGE COMPARTMENTORIGINAL
Ffpm I.As Received By
ATP
Page 2 of 2
e~illC Culfstream
Aerospace
SERVICE LETIER NO. 362
Revision Na. 1
2 May 1884
INSPECTION AND/OR MODIFICATION OF OBSERVER SEAT
SHOULDER HARNESS STRUCTURE
~PPROYAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED.
ACCOMPLISnMENT INSTRUCTIONS:
NOTE
IF OBSERVER SEAT SHOULDER HARNESS ATTACH
FPITING IS MOUNTED ON THE AFT SIDE OF FRAME
AT STATION 98.00 MODIFICATION IS NOT
NECESSARY. PROCEED TO 8TEP 17. AND NOTE ON
COMPLIANCE CARD THAT FI?TIND 18 MOUNTED ON
AFT 81DE FRAME.
THE OBSERVER SEAT 8HOULDER HARNESS ATTACH
FITTING TO BE MODIFIED IS JUST FORWARD OF
STATION BB.S0. TO DETERMINE LOCATION OF
FITTING AT STATION 98.50, MEASURE B.6INCHES
FORWARD OF AW END OF EMERGENCY EXIT
WINDOW UPHOLSTERY PANEL.
C
Page 1 ol 1
Service Lettev CulfsrreamAerospace
SRKYI(:% I.k:1’1´•RK NO.:16P
I?Nev~mhBI´• IOH:I
INSPEC71ON AND/OR MODIF1CATION OF OBSERVER SEAT
SHOULDER HARNESS STRUCTURE
MODELS AFFECTED: ’l’llI IIO[,I,OWIN(: MOI)R1.8’PHAT IIAVF: OI(SII(VF.I( YF.AT INSTAI.I.%I).
M(11)111. BOI)I), SRILIAI. NO8. 151)1)1 THKU 16(ISH.
MOl)l(ll ~(16A, 811~1AI. NOS. HS(IOI THKU 96(L61.9806:1. 111(11114, UB(168. BHI)?P ANII HfiO?:l.
MOTE
THE OI1SEHVIK YBA11 IS I.O(:ATBI) IIEHINI) TH~
UOPLT.OT YIAT
REASON FOR PUBLICATION: TO ASSUKB PKOPEH LNYTAI.IATION OF ORSIKVIK SRAT SHOUI.I)RI(
A1TA(:HMF.NT.
COMPLIANCE: WITHIN NIX’P IOII-HOUI~ TIMR IN SIIIVICB.
C rots
IP ANY PKOnI´•gM8 AHE EN(:OUNT%KRI) WHII.I
COMI’I.YIN(: WITII THIS YglLVICg IPITPIK. CONTACT
YOUIL NF.AHEW CUI.FYTRF~AM UOMMANI)%H
AU~PHOKIZRI) SEKVI(:ENTEK
BY WHOM WOR~ WILL BE ACCOMPLISHED: A L P MECHANIC 01( IYUIVALRNT.
APPROVAL: ~N(:LNlt:RKIN(: I)ESLON ASPR(:TS AKE FAA AP~’HOVII).
ESTIMATED MAN HOURS: r"OUI( (4) HOUHS.
PARTS DI\TPI: I’AKTS RR9UIKII) TO COMPI.Y WITH THIS SERVlcl I.En´•BH MAY ng I’ItOCUKEI) TRHOU(:H
YOUH NF.AHFST QUI.FSTII~AM UOMMANI)EH AUTHOKLEBI) YBHVLCENTBK FOK (20.0(1. KgFF.KRNUE TIIIY
SIIILVI(:g AIII(:KAPP MOI)BT. ANI) FAOTOHY SIKIAL NUMDOK WHEN OKI)EHLN(: I.F~1TRI1
NO.:lliP KI1‘ (:ONSIYTLN(: OF THR FOIII.OWIN(::
~m´•´•ua*nMI´•nl´• m~ul nohu.
cl’rv PAKT NO. DESCHLYPION
leu. 10U06X-81B Pbtr
leu. Hfil)?X:l-fi69 Plueurd
:leu. MS9(1~R´•I-UROh Huck Rlllt
:I cu. MS90:194-OHOS Huck Rolt
tau. Cumpliance Curd
Iril. Sttrvire Letter No. 361 inatructionn
SPECIAL TOOLS: HUCK (:UN ANI) HOI.FI FLNI)EH.
IICCO.PUS...NT INglllUenMIP;
I. Hemeve window ~sm airplanr
1. Hcmovr ilhxarvrr saut xhuuldar hilmexu.
Page 1 ol 4
I.IPPIIINO. :162
CEMERGENCY EXITWINWWOPENIN(I
IREFI
BEFORE CHANGE
EXISTING PLATE
(REF)
"1EXISTING FITT(NO 11?
II II
IREF) illREMOVE RIVETS
ANO INSPECT FOROF
INSPECT FOR BAP )I I L;/ I HOLES
ACCEPTABLE TO INSTALL THRU
+111
RIVETS
hcHOLE THAT WAS M)UNTERSUNK
IN BELOWPLATE
AFTER CHANGE
’I IACCEPTABLE TO USE N~S17SBB(lb
IIBLIND RIVETS IF NECESSARY)
II
h;
INSTALL IWOSIS1S PLATE WITH THREE 131MS9mSbOB05 MUCKS IFOR HOLES WITH MAXIMUM
NOOnP CLEANUP DIA. OF 0.202´•1 OR M990351-08~ MUCKS
ALLOWED IFOR HOLES WITH MAXIMUM CLEANUP oln. of8285"). ANY COMBINATION OF MS90J64 HUCI(SISACCEPTABLE.
NnS1ISBB~-S BLIND RIVETSII IACCEPTI~BLE TO USE NAS113888´•5
100058-515II BLIND RIVETS IF NECESSARY)
PLATE
VIEW LOOKING OVTBD
C
Pa~e 2 of 4
SII1V1(:l r.B~PTII( NO. :l(i2
I\
i,i
850783´•689
OBSERYER FE~T ITYP)IRE Fl
Fipura 2.
Pa~e 3 aI 4
SRI(VI(:R LRTTRK NO.:162
:I
n side rsscl illilt is isc;ltrd amar~enay exit windllw opening end side pilnel below wind~lw
illl.,iLllnol.alncy exit wincl.lw 1II explu;e ~,hlerver seat shoulder hurne*s iltt,lell litting
I(aml,va channel il’iN X6111:l(l-1281 th;,t is isci)lcd below the emergenmy exit window ~,psning.
6 inspecl ~ihl,ulclsr h;ll´•lloxx;llluch litting li,l’ it ~lp between lilting ilnd support plilte (rriir tcl I’igule 1).
7 i)lill ilut tll,´•ee I:11 i´•iwlr th,,t ilttiluh i,l,servsr aeilt sh~lulder hill´•ncsx;,tti,eh iilline xuppil,´•t plate ttl lunll;lgu lulmr
;11 st;ltilll, B(i611 irular t~l [iigure Il.
H. InLil’"’t thl´•se (:II holsn in ILlaii~Ee lismr li,r pllsaihle eillnpation IrrBI to PiFurr I)
L). 11´• 11(1181 in li´•ilml´• ;~l´•r nl,t elonhratrd and nl, Rap iX evidenl between littinl: and support plate. reill*tsll
exixtinl: auppslt plate usinl: NI\SI7:IRRS-5 blind rivets and prcneed to step il.lrelir tl, PiRura 1).
111 11’ h~llaa in Ib*rlilUe irilmu are elongnterl or ovenile or a ilap between litling imd support plate is evident. pn,crad
;I Oleunup elongated holes (reLr tn Fieure 1).
b. I)l´•ill out first two 12) rivet~ above and below support plate nttachinl! hnlrs irefer to Fihrurr 1)
c. Uxing a hale finder, locate. drill and install L000SR-S18 plate on fuselage frame Assure thilt no gap
axistu between ntting and plate ire~er to Figure i).
d I’*oeeed to step ii
Il ehunnel IPIN Rfi2030´•128) using cxistinb´• hardware.
it. ..ml .b Ransla uain, harduu~
I:I Keinxtilll observer seat hack.
14 KL´•inat;lll observer neat ahuuldar harness.
I(sinst;lll emer(!enov exit window
I(i Yuijr Eu*hion on observer sent and illstall 860?H3´•689 placard on top of front lip of seat base iroLI to i’igure 21
17 Fill out and mail Complinnee Card
ELECTRICAL LOAD: NO CW~NGP
WEIGHT AND BALANCE: NO CHAN~I%.
SPARES AFFECTED: NO.
PUBLICATIONS AFFECTED: NONE.
RECORD COMPLIANCE: Make an appropriate entry in airplane mnintonance re~ordJ as B,liowa: Servicr Letter No
:1~1, dated 17 November 1983, entitled "lnspsotion anPor Mndineatinn of Observer Seat Shoulder Ilnmeua Structure’~,;ec~lnlpli*hpd (date)
Page 4 of 4
dl
Service Letter GulfstreamAerospace
SERVICE LE~PTER NO. 383
1 November 1883
FUEL DRAIN-SYSTEM INSPECTION
MODELS AFFECTED: MODEL 69OC, SERIAL NOS. 116W THRU 11150.
MODEL 690D, 8ERIAL NOS. 15601 THRU 15029.
MODEL 696 SERIAL NOS. 85000 THRU 95084.
MODEL 695A. SERIAL NOS; B6W1 THRU 96061, 86065 THRU 96065, 96069, 96072, 88076
AND86018.
REASON FOR PUBLICATION: POSSIBLE BLOCKAGE OF FUEL DRAIN PATHS WITH SEALANT WHICH COULD
CAUSE UNDRAINABLEI[INU8ABLE FUEL TO INCREASE SLIGHTLY, INCREASE
CHANCE FOR BACTERIA GROWTH IN FUEL AND POTENTIAL WATER TRAPS
IN FUEL TANK AREA.
COMPLIANCE: AT NEXT SCHEDULED TWELVE (12) CALENDAR MONTH OR LOG-HOUR INSPECTION,WHICHEVER COMES FIRST.
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE
COMPLYING WITH THIS SERIVCE LETTER, CONTACT
YOUR NEAREST
BY WHOM WORK WILL BE I\CCOMPLISHED: A L P MECHANIC OR EQUIVALENT.
APPROVAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED.
ESTIMATED MAN HOURS: THIRTY-FIVE (35) HOURS.
PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE LETTER MAY BE PROCURED THROUGH
YOUR NEAREST CULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR (8.75. REFERENCE THIS
SERVICE LET~ER, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN ORDERING SERVICE LET~ER
NO. 365 KIT CONSISTING OF THE FOLLOWING:
Prl~´•um D aun* *Im~xllno~´•.
QTY PART NO. DESCRIPTION
4 se. 690394-1 Gasket
1 ea. ComplianeeCard1 as. Service Letter No. 563 Instructions
SPECIALTOOLS: NONE.
ACCOMt´•LISHMENT INSTRUCTIONS:
1. Defuel airplane as outlined in Chapter 28 of the Airplane Maintenance Manual.
NOTE
Do not use booat pumps to off load fuel.
2. Remove upper aceee. doors, between wing station (WS) 141.0 to wing stntion 255.52, from left and right ~vlng
(refer to Figure I).
Page 1 of 6
..;I__..;
8ERYICE LETTER NO. SBS
BA-c, C-h D~h D
ii
sU-
:P,. O
oO
-r
G) ~dl
A~J Dcl Dt] DI-~i
VIEW LOOKING DOWN ON LH WINGRH WING OPPOSIPE
DONOTAEMOVEGE*L~NT AT WS 160.0
VIEW A-A
WS 160.0 AND WS 142.0
D INolcnrEsnnEnsro
iiFiaurs 1.1Shsat 1 ~t 0)
Page 2 ol B
SERV~CE LETTER NO. SBS
Inz.oONLY
142.0ONLY
VIEW B
C:
D
B INDICI\TESPIREAS TOWS 178.6
BE CLEAR OF SEALANT
F5urs i. IShsat of 3)
Page 3 ol B
SERVICE LETTER NO. S83
VIEW D-D
WS 197.3. WS 216.0 AND WS 234.6
I Y\D"B
VIEW E
SHOWING WS 216.0 SAME AS WS 234.6EXCEPT AS NOTED
88
BINDICATEII\REABTOBE CLEAR OF SE~LANT
VIEW F
SHOWING WS 197.3 SAME AS WS 216.0EXCEPT AS NOTED
Fieur´•l. (Shsat 3 of 3)
Page( olB
BERVICE LETTER NO. 583
AREA TO BE CLEAREDOFSEALANTITYR
RIBASSY
REMOVE SEALANTFROM HOLES ITYPI
TYPICAL VIEWOF RIB CUTOUTSFOR MODEL 8800. SERIAL NOS. 11800THRU 11850 ANO MODEL 885. SERIALNOS. 85000 THRU 85038.
AREA TO BE CLEARED R?BSS"OF SEALANT ITYP)
CENTERLINE OF
CUTOUT
REMOVE SEALANT IN RIB CUTOUTSTO ALLOW A IlalNCH ROo TO PASSTHROU(IH CUTOUT. BE EXTREMELYCAREFUL SO AS NOT TO REMOVEEXCESSIVE SEALANT IN AREAS SHOWN
TYPICAL VIEW OF RIB CUTOUTS WHICH COULD CAUSE LEAKS. NO EXPOSEDFOR MODEL 8800. SERIAL NOS. 11851 METAL I\LLOWEO.IF NECESSARY. TOUCHUPTHRU 11730. MODEL 8800. SERIAL NOS. SEALANT:15001 THRU15028. MODEL 586. SERIALNOS. 85038 TnRU 85084 AND MODEL 885A.SERIAL NOS. 98001 THRU 88078.
Fieure 2.
Page 5 oI6
SERVICE LE1TER NO. 383
3 Hemove screws attaching outboard and mid-wing fuel transmitters to access doors and remove doors.
1 ma~act in i .b that ela~ i. n.~
5. If any area, noted in Figure 1., is blocked by sealant, remove excess sealant from that area to eliminate blockage.See Figure 2 for typical view of area to be cleared of sealant st cutouts and stringers.
NOTE
Place protective paper or cloth below all access door
openings prior to cleaning, sealant from periphery of
opening. Remove and discard before sealing doors.
8. Remove all sealant from wing access doors and access door openings. Care should be taken so as not to scratch
the metal surface.
7. To prevent contamination of fuel, assure that all fragments of sealant are removed from wet wine fuel area priorto installing wing access doors.
8. Apply alodine solution, as necessary, to bare metal on inner surface of access doors and outer surface of access
door openings in wing.
9. Reinstall existing fuel transmitters on wing access doors using existing hardware and new 630594-1 gaskets.Torque screw 20 to 25 inch-pounds.
LO. Reinstall and seal existing wing access doors as outlined in Chapter 67 of the Airplane Maintenance Manual
11. Perform fuel system pressure check as outlined in Chapter 28 of the Ai~lane Maintenance Manual.
12. Refuel airplane as outlined in Chapter 12 of the Airplane Maintenance Manual.
L3 T.u.hu~iulintssnsEPrsSI
14. Fill out and mail Compliance Card.
ELECTRICAL LOAD: NO CRANGE.
WEIGHT AND BALANCE: NO CHANGE.
SPARES AFFECTED: NO.
PUBLICATIONS AFFECTED: NONE.
RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance I´•ecords as follows: Service Letter No.
383, dated i November 1883, entitled "Fuel Drain System Inapection", accomplished (dnte)
Page 6 ofR
Service Letter GulfstreamAerospace
SERVICE LETTER NO. 364
18 November 1983
SERIES MODE ANNUNCIATOR LIGHT TAPE REPLACEMENT
MOOBLS I\FFECTED: MODEL 690C, SERIAL NOS. 11750 AND 11152.
MODEL 680D,IERIAL NOS. 15025 THRU 15029.
MODEL 68SAl SERIAL NOS. 86068 THRU 96061, 96083 THRU 96065, 96069, 86012, 98016
AND 96078.
REPISON FOR PUBLICI\TION: STANDARDIZATION OF SERIES MODE ANNUNCIATOR LIGHT COLOR
BETWEEN ALL MODELS AND SERIAL NUMBER OF AIRPLANES.
COMPLIIANCE: DURING NEXT 100-HOUR INSPECTION.
NOTE
1F ANY PROBLEMS ARE ENCOUNTERED WHILE
COMPLYING WPI~H THIS SERIVCE LETTER, CONTACT
YOUR NEAREST OULFP´•TREAM COMMANDER
AUTHORIZED8ERVICgNTER.
sYWHO.WORKWILL BEI\CCOHPLISHUI: ~WNWOPEh*TOB OR*6rP ~CRANIC OR eQUNALENT
I\PPROVP~L: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED.
ESTIMI\TED MAN HOURS: THIRTY (80) MINUTES.
PARTS DATA: MATERIAL RE~UIRED TO COMPLY WITH THIS SERVICE LETI~ER IS FURNISHED WITH THIS
SERVICE LETTER AT NO CHARGE UNTIL 18 NOVEMBER 1984 AND CONS1STS OF THE FOLLOWING:
9TY PARTNO. DESCRIPTION
4 in. TCMIOB Chartpak Tape1 ea. Compliance Card
1 ea. Service Letter No. 364 Instructions
8PECIALTOOLS: NONE.
ICCOMPLISHMENT INSTRUCTIONS:
1. Remove two (2) aorews that attacb annuncintor face plate to annuneiator panel and remove face plate (refer to
Figure Il.
2. Remove e.isting amber tape behind’SERIES MODE" nomenclature and apply TC6009 blue tape (refer to FigureIi.
S. Re~netsll face plate on annunciator panel using existing ha~dware.
4. Fill out and mail Compliance Card.
C
Page 1 of 2
´•j/
SERVICE LETTER NO. 364
I\NNUNCI~TDR PI\NEL I\TT*CHIROSCREWC
(REF) IZPLSI
i IL~ eg YIL iiT X~ L a dr
~s0 i ´•I ´•IL*. Oe~L l~:a: .s..nr ~s ’D w ~ln n
Face pLnn REMOVE EXIST1N9 TI)PE(REF) BEHIND’´•S~RIES MOOE’´•
nND ~PPLY TCSOOJ BLVETI\PE
Flgura i.
ELECTTICI\L LO*D: NO CHANGE.
N~CHANCE
SPARES AFFECTED: NO.
PUBLICATIONS AFFECTED: Pilot Operating Handbwlt change required by this document is furnished with this
Service Letter.
RECORD COMPLI~NCE: Make an appropriate entry in airplane maintenance recoids as follows: Service Letter Na. 564
dated 18 November 1983. entitled "leries Mode Annunciator Light Tape Replacement", accomplished (dstei
Pnge2ofB
-.__-.rm,lPILI-~,- _.l_l__-~IILi -..LIXIV-I i_- ii -i__L.._. i-:l.l;ii::;:.-__
~IIc Service Letter Gulfstream
Aerospace
SERVICE LeT~ER NO. 3663 February 1984
FUEL BOOST PUMP REPLACEMENT
MODELS AFFECTEO: MODEL BBOC, SERIAL NOS. ll?SO THRU 11132.
MODEL 69011, SERIAL NOS. 15025 THRU 15032.
MODEL 685A, SERIAL NOS. 96058 THRU 96061, 96063 THRU 86069, 96012, 96075, 96018
AND 98085.
RMSON FOR PUBLIC~TION: TO PROVIDE FUEL 800ST PUMPS WITH IMPROVED RELIABILITY.
COMPLIANCE: WITHIN NEXT 100-HOURS TIME IN SERVICE.
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE
COMPLYING WITH THIS 8&RVICE LE~ER, CONTACT
YOUR NEAREST OULFSTREAM COMMANDER
AUTHORIZED SERVICENTER.
BYIYHOH BPMECH*NIC ORBqUIVILENT
APPROVAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED.
ESTIMI\TED M*N HOURS: INSPECT BOOST PUMPS FOR MODEL NUMBER TEN (101 MINUTES
REPLACE BOOST PUMPS TWO (2) HOURS.
PARTS DATA: PARTS RE~UIRED TO COMPLY WITH THIS SERVICE LETTER MAY BE PROCURED THROUGH
YOUR NEAREST GULFSTREAM AUTHORIZED SERVICENTER FOR $1061.71 PER KB, h FULL
CREDIT WILL BE ISSUED UPON RECEIPT OF OLD Pn~T 630590-103 (VENDOR MODEL NO. 3B1´•1 OR 381-1A) FUEL
BOOST PUMPS, A PROPERLY EXECUTED CLAIM AND A COMPLIANCE CARD IF RECEIVED PRIOR
TO 3 FEBRUARY 1986. REFERENCE THIS SERVICE LETTER, AIRCRAIT MODEL AND FACTORY SERIAL
NUMBER WHEN ORDERING SERVICE LETTER NO. 365 KIT CONSISTING OF THE FOLLOWING:
NOTE
EACH KIT CONSISTS OF ONE (1) 630380-603 FUEL
BOOST PUMP AND TWO (2) S-OS10-912HT O-RINGS;THEREFORE, IT IS NECESSARY TO SPECIFY
qUANTITY OF KPPS RE~UIRED WHEN ORDERING.
9TY PART NO. DESCRIPTION
1 se. 630390-509 (Model No. 981-4) Boost Pump2ea. S0310-912HT (L449´•80 Compound) O-Ring1 ea. Compliance Card1 ea. Service Letter No. 365 Instructions
C
Page 1 ol 1
SERVICE LETTER NO. 365
sPw;laLrao~; NONE´•
ACCOMPIISHMENT INSTRUCTIONS:
I. Gain access to Left and right Fuel boost pumps, Located in nacelles, through main landing gear wheel well doors.
2. Check nameplate on fuel boost pumps for Model Numbers.
3. IfModel Number is 381-4, proceed to step 14.
4. If Model Number is not 311?-4, proceed to step 5.
5. Depress Battery switch to BA1TEBY position.
6. Turn FUEL-HYDR switch to EMER OFF position.
NOTI
This closes the main fuel shutoff valve.
Depress battery switch to OFF position.
8. Remove the left andior right fuel boost pumps as follows (refer to Figure i):
a. Completely drain the fuel lines to the fuel boost pumps by using the drain valves located just below the
fuel boost pumps.
b. Disconnect the electrical wiring and ground jumper cable from the fuel boost pumps and stow wires out
of the way so as not to damage wiring while removing boost pumps.
i ,sooMsl the drain dnin ´•slr~s
d. Disconnect the fuel supply line from the existing AN919-20D reducer.
e. Disconnect the fuel scavenge Line from the existing AN?83D12 tee.
f On the left boast pump, disconnect the existing M821919DG42 lower clamp, on the boost pump, from the
existing MS21919DG8 small clamp on the fuel scavenge line.
g. Disconnect the engine fuel supply line from the existing AN?83D12 tee.
h. Loosen the two (2) existing AN?S?TWLI1 clamps, attaching boost pump to boost pump bracket assembly,while supporting the boost pump.
i. Remove existing fuel boast pump, with flttings still installed on boost pump. from boost pump bracket
assembly.
j. Remove the fittings from the boost pump, as a unit (do not disassemble nttings), and note the number
of turns required to remove 8ttings from pump.
Install 8ttings, a. a unit, on the new 630380-503 (Madel No. 311?-4) boost pump using new S-0310´•glaHT
o-rings. Screw fittings into the boast pump the same number of turns noted in step j.
I. Install the new boost pump on the existing bracket assembly end finger tighten the existing AN?3?TW91
clamps.
m. Reconnect the existing fuel and drain lines 0 fuelboost pump and reposition boost pump on the bracket
assembly as required.
n. Tighten the edsting AN?B?TWg1 clamps on the boost pump.
a. On the lett boost pump, reinstall the existing M921819DG42 clamp an the boost pump and the e.is"np iMS21918D08 clamp on the fuel scavenge line using existing hardware.
Page a of 4
8ERVICE ~TTER NO. 985
8OO8TPUMPSUPPLY LINE
BR~CKETA88Y(REF1
OROVND JUMPER CAQLE n E~d EXISTING AN789D1Z TEEIREF) \/I (I I\ .IREFL
12 PLSIEXISTINO*NIIITWBI
FUEL SUPPLY LINEIREF)
FUEL SC~YENOE LINE
EXISTING U II (REFI
ANBlPEEG REDUCER
EXISTING M821818D(Y12CLAMP IREFI
030580603 (MODEL SBI~)FUEL 8008T PUMP
MS21818DOICLAMP (REF)
orul.uwrIREFI
EXISTING FITTINGSIRE Fl
FUEL DRAIN VALVE
INSTALL NEW 60310QllnT (REF)
O´•RINO 12 PLSI
LEFT INSTALLATION SHOWNFleurs i.
p. Remnnset the electrieal wiring to the fuel boost pump.
q. Reeonnect the existing ground jumper cable on top of boost pump.
9. Depress battery switch to BA1TERY position.
LO. Turn FUEL-HYDR switch counterclockwise to NORM position.
NOTE
This opens the fuel shutoff valve.
11. Depress battery switch to OFF position.
if. Cheek all connections for fuel lealage.
13. Functionally test the fuel boost pumps and t~el scavenge system as outlined in Chapter 28 of the AirplaneMaintenance Manual under paragraph labeled Low Fuel Scavenge Gystem
14. Fill out and mail Complianee Card.
Page 3 of 4
SERVICE LETTER NO. 965
CELECTRICAL LOAD: NO CHANCE.
WB1GHT A.ND BALANCE: NO CHANGE.
SPARES AFFECTED: NO.
PUBLICATIONS AFFECTED: NONE.
RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance remrda as follows: Service Letter No.
385, dated 3 February 1884, entitled "Fuel Boost Pump Replaoement", accomplished (dato)
Page 4 of 4
´•II _I
,Seavide Letter CulfsrrssmAem~pereCo1Hnalion
on´•n~M a*, o*iah~ml loin
SERVICE LETTER NO. 366A 1(Supersedes Service Letter No. 366, dated November 2, 1984, in its entirety) I
22 March 1911
NOSE LANDING GEAR DRAG LINK SUPPORT STRUCTURE MODIFICATION
MODELS AFFECTED: MODEL 5009, SERIAL NOS. 3050 THRU 3323.
MODEL 680W, SERIAL NOS. 1121 THRU 1850.
MODEL 681, SERIAL NOS. 6001 THRU 6071.
MODEL 685, SERIAL NOS, 12000 THRU 12066.
MODEL 690, SERIAL NOS. 11001 THRU 11079.
MODEL 690A, SERIAL NOS. 11100 THRU 11344.
MODEL 680B, SERIAL NOS. 11350 THRU 11566.OMODEL 690C, SERIAL NOS. 11600 THRU 11735.
MODEL 695, SERIAL NOS. 98000 THRU 95084.
NOTE
[F PART II OF SERVICE LETTER NO, 368 HAS BEEN
ACCOMPLISHED, DISREGARD THIS SERVICE
LETTER.
.E~S(I.FoRPUBLIC*TION: LOM P*l~-8 CAP~BILITY OF DRIO LINK SVPIORT
COMPLII\NCE PART I EACH loO-HOUR INSPECTION UNTIL PART 1l IS ACCOMPLISHED.
PART II AT OR BEFORE THE FIFTH 100´•HOUR INSPECTION (AFTER NOVEMBERB, 1984) OR EIWHEN PART I REVEALS ELONGATED HOLES OR CRACKS W SUPPORT STRUCTURE.
NOTE
UI’ANY PROBLEMSARE ENCOUNTERED WHILE
COMPLYING WITH THIS SERVICE LETTER, CONTACT
YOUR NEAREST´• GULFSTREAM COMMANDER
AUTHORIZED SERVICENTER.
BY WHOM WORK WILL BE ACCOMPLISHED: A a p MECHANIC OR EqUIYALENT.
APPROVAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED. I
ESTIMATED MAN HOURS: SIXTEEN (16) HOURS,
PARTS DATA: PARTS RE~UIRED TO COMPLY WITH THIS SERVICE LETTER MAY BE PROCURED FROM
YOUR NEAREST OULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR $16.76. REFERENCE THIS
SERVICE LETTER, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN ORDERING SERVICE LETTERI
NO. 366A KIT CONSISTING OF THE FOLLOWING:
.Pagelof 7
SERVICE LETI~ER NO. BBBA
~n PARING. DESCILrPTION (I1 ea. 310054-RE3 Angle1 ea. 310054iRE4 Angle1 ea. 310054-RE5 Cha~nal1 ea. 31(0544-RE1 Strap4 ea. MS21044N3 Nut
4 ea. AN960-10L Washer4 ea. AN3-4A Bolt2 ea. Compliance Card
II 1 ea. Service Letter No. BBBA Instructions
SPECIALTOOLS: NONE.
ACCOMPL)SnMENT INSTRUCTIONB:
PART I INSPE~TION OF DRAG LINK SUPPORT.
I. Cain access to the nose landing gear drag link support structure through the access panel located on the rightaids of the airplane at FS -12.00.
NOTE
Loose bolts are to be suspected if a snap or popping sound
is detected in the nose landing gear attach area when the
tug begins the towing procedure.
2. Inspect nose landing gear drag link support far loose bolts which attach support channel to 310054-25 channel.If bolts are found to be loose, inspect Ear elongated holes in both channels (refer to Figure 1). If hales are not
dShtEn *lg. B*l.t ,I. p~.´•rri II ~f LU S.rvi~e
3. Inspect upper channel and lower channel at forward end for cracks in the radius of the bend adiacent to the
surface which attaches to the web (reler to Figure i). If cracks srs found proceed to Part II.
ii4. If no cracks or elongated hales are found, perform this inspection every 100-hours. Part II of this Service Letter
shall be accomplished at or before the~fth 100-hour inspection (after November 2, 1984) regardless ofthe link
support condition. Fill out and mail Compliance Card specifying thatPart I has been aeeompiished.´•
PART II MODIFICATION OF DRAG LINK SUPPORT.
NOTE
The following instructions modify the nose landing geardrag link support assembly with the drag link supportassembly installed on the airframe. An optional method Formodification is to remove the drag link support assemblyfrom the airframe.
1. Gain access to the nose landing gear drag link support structure through the nose wheel well and access panellocated on the right side of the airplane st FS -12.00.
2 Using a C10 bit, stop drill cracks in upper and lower channels.
3. Drill out the forward nine rivets which attach the existing upper channel to the existing web.
4. Perform step 3. for existing lower channel and web.
5. Dnll out the rivals which attach the cover to the upper and lower channels.
6. lour bolts, washers, and nuts which attach the upper and lower channels to the existing 310054-25
Page2of’i
SERVICE LET1’ER NO, 366A
7. Urill out the rivets at the forward end of the cover. These rivets attach the cover and clip to 510054-25 channel
Not. that the clip remains installed. Pry cover away from upper and lower channels. Use caution only to applyenough Fores to the cover to gain access to the interior parts of this assembly. Do not damage or sevel´•ely bend
cover. Place a screw driver or similar tool at the aft closure point of the cover and upper and lowel´• channels
to wedge the cover open at the forward end.
8. Remove the two bolt., washers and nuts which attach 310051-25 channel to the support channel. Remove aild
discard 310054-25 channel.
9. Position 310054-RE3 angle an upper channel as shown in Figure i, Detail B. Trim 310054-RE3 angle as
necessary to ensure a proper fit. Match drill rivet and bolt holes.
10. Locate and drill hales in 310054-RE3 and upper channel, follow drill pattern as shown an Figure i, Detail B.
ii. Attach 310054-RE3 angle to the upper channel and web using a NAS17S8B6 blind rivet or MS20470AD5 rivet
in the farward mast position and eight NAS1138BS blind rivets.
12. Attach 310054-RE3 to the upper channel with seven NAS1738B6 blind rivets.
13. Perform steps 9. thru 12. using 310064-RE4 and lower channel.
14 Remove wedge and secure cover to the lower and upper channels using NA91738B5 blind rivets.
15. Position 310064-RES channel between cover and support channel. Trim 310064-RE5 as necessary to ensure a
proper fit. Prior to match drilling assure that 310054-RES channel is a nush fit between caver and supportchannel. If a flush fit exists, proceed to step i?.
16. If 310064-RES channel does not fit Rush, fabricate and fit shim(s) made from 2024-T3 aluminum. A maximum
thickness of 0.010-inch shims are allowed between 310054-RE5 channel and support or channel cover.
17. Match drill 310054RE6 channel to cover and clip. Install four MS20470AD6 rivets or NAS1738B6 blind rivets
to attach channel to cover. clip and shim(s) as required,
18. Match drill 310054-RE6 channel to upper and iawer channels and install Four AN3-4A bolts, AN960-10L
washers and MS21o44N3 nuts to attach 310054RE6 to upper and lower channels. Inspect installation to ensure
that washers do not ride on radius of 310054-REB channel.
19. If washers ride on radius of 310054´•RE5 channel, remove washers and nuts. Fabricate a radius black to be
installed under both washers on the side affected. Install radius blocks, washers and nuts (next bolt grip lengthsize may be used if requiredl.
20. Trim 310054-RE1 strap as necessary to fit in forxerd side oFsupport channel.
21. Position 310064-RE1 strap on forward side of support channel. (See Figure 1. View D-D). Match drill holes in
strap,
22. Drill two 0.250 to 0.294-inch diameter holes in Si0054-BE5 channel to match location in support channel
23. Locate and drill eight holes in S10064´•RE1 strap and support channel, tSee Figure i, View D-D for rivet
pattern),
24. Attach 310054-RE7 strap to support channel using sight NAS1738B6 blind rivets or MS20410ADB rivets.
25. Secure 310064-RE5 channel to support channel, 310054-RE1 strap and shim(s), as required, with two ANI-SA
bolts, ANPB0-41B washers and MS21044N4 nuts.
26. Inspect AN4-6A bolt heeds installation to ensure that bolt heads do not ride on radius of310064RE5 channel.
27. If bolt heads ride an radius of 310054-RE5, remove bolta, washers and nuts. Fabricate a radius block to be
installed under bolt heads. Install radius blocks. bolts (next bolt pip length size may be used if required),washers and shim(s) (if required).
28. Fill out and mail Compliance Card. I
ELECTRICI\L LOAO: NO CHANGE.
Page 3 of 7
SERVICE LETTER NO. aBBA
EXIST1NB
SUPPORT
"JI
EX18TIN(I UPPER r
CHANNEL SHOWN PI
WITH nhlqLe prm
ExlsnNo LOWER3(W0eRESINSTALLED
CHANNEL SHOWN
WITH AN(ILE PIN~1DOW´•RII
INSTALLED
DET~II B(8haat? Dt
%SD~g,
ExlsnNoP
CHANNEL EXISTINB 8P~CER
IIP IN(ITAILEO)
9 Il Il IO
Oln a
oa
lo~-.- a
o,
EXISTIN(I
STRAP CDVER00 NOi
REMOVEEXISTIN(I OLO P/N CHANNEL
CLIP NEW PIN 3100MeRE6 CHANNEL
DETAIL A
FIWI~1. Nala Landinp Oasr Dng Lin~ Suppsn IShset 1 o( 3L
Page 4 ol 7
SERVICE LETTER NO. SBGA
0.16510.187" DIA HOLE
NAS1738BS BLIND RIVETS
OR RIVETS
PLSL3100J4´•RE3CHANNELSWOWN
31W54´•RE4 IOPPL
C~ I;i i+ta76.´•
ii O I t´• EXISTING SPACER0.35’~ 1 IIF INSTALLED)
0.78"
mpll II I t
’t CH~NNELISHOWN) ITYPI
COVER 1’EXISTING UPPER 0.35.:
LOWER CHANNEL
IOPPI
DETAIL E
VIEW LOOKING DOWN
o.las/o.la´•´• alA. HOLEDIA. HOLE NI\S1738B5 BLIND RIVET
NASI)JI1BS BLIND RIVETS (18 PLSITRIM FLAMIE
EXISTING UPPERTO MATCH CHANNEL 310054RE3
ANGLE CHANNELMSJOS53-05BLIND RIVET
laPLsl
~e -i- -.i-: I iiil+
D1A. HOLE tNAB171sBS f
BLIND RIVET
OR MS10470AO5RIVETS II 1 1111 1 1~1 C
I2PLS) II
L i i; i´• C C
TRIM FLANOE 310054RE4
TOMATCHCH~NNEL ANGLE EXISTING LOWER I
ITYPL CHANNEL
DO NOT REMOVE THESE
VIIW C.C RIVETSUNLESSDAAGLINK SUPPORT I\SSY IS
TO BE REMOVED AND
LOOKING OUTED MODIFIED ON THE BENCH
Figula i. Naa L~ndlna Osn Drse Lin* Suppo~ (Shwt Z of 31
PageDof7
SERYICE LETTER NO. QBBA
0.183W.189’~ DU. HOLE
ACCEPTABLE TO USE0.180/0.184" DIA. HOLE NASl73888 Is PLSI
BOLT
rl II\NBBO´•1OL WASHER
MS21044´•N3 NUT14PL4
1-c r! (.SD’´•
ANGLEIREFI
EXISTINGCOVER
IREF)ii
II
M82047P~DB
O
j AN4´•6P1 BOLT0.183/0.189" DI*. HOLE 0.250/0.254" OIA. HOLE
OR NI\S173888 0 0 I\NBBO~1R WASHER (21
I4PLS) MSZ1044´•N4 NUT12 PLS)
f
ANGLE I.ls" (np)IREFI
0/10"
INPI
VIEW D-D
LOOKING FWDE
lr31WSaRE6
CHANNEL
II,i
VIEW FOR
CLARITY ONLY
31W54´•RE7ITRI\P
II i\ SHIM IF RE(IUIREO BE~WEENII 310094´•REb CHANNEL ANO
31018521 CHANNEL OR 310054´•43COVER. FABRICATE SHIMI.I FROM
111 202473 IO´•MDII MAX. SnlM THlCI(NE8hILI ALLOWED1.
VIIW E´•E
LOOKING INBD
Filura(. Nora Llndln( Osar 014 Link Support rShast 3 ot 3)
Page sof7
BERVICE LETTER NO. 386A
WEIGHT AND BALPINCE: NEDI.IGIBLE.
SPPIRES AFFECTED: NO.I
PUBLICATIONS AFFECTED: The applicable Maintenance Manual and Illustrated Farts Catalog ehnnaes rcqoirrd by
this document will be incorporated at the nent scheduled i´•evision.
RECORD COMPLI*NCE: Make an appropriate entry in the airplane maintenance records as follows; Service i.t~tt*r INo. 366A, dated 22 March 1885, entitled "Nose Landing Gear Drag Link Support Structure ModiAeation". Pal´•t 1
accomplished (date) Part II accomplished (date)
Page’lof?
´•2*
$e~j@e ke~ter GulfstreamAerospace
SERVICE LET~ER NO. 361
4 January 1985
PARKER HANNIFIN CORP. PRODUCT REFERENCE MEMO (PRM) NO. 36 (REV. A)(30-107 and 30-1078 Brake Assemblies)
MODELS AFFECTED: FACTORY APPROVED:MODEL 680A, SERIAtNOS. 11195 THRU 11344.MODEL 690B, SERIAL NOS. 11350 THRU 11566.
MODELB90C. SERIAL NOS. 11600 THRU 11734.MODEL 690D. SERIAL NOS. 160U1 THRU 16033 AND 16035 THRU 15031.MODEL 695, SERIAL NOS. 95000 THRU 95084.MODEL 685A, SERIAL NOS. 96001 THRU 96061, 96069 THRU 96072. 96075, 96017, 96078,96082, 96085, 98088 AND 96089.
MODEL 595B, SERIAL NOS. 96201 AN1) 96202.
STC APPROVED:MODEL 690, SERIAL NOS. 11001 THRU 11019.MODEL 690A, SERIAL NOS. 11100 THRU 11194.
REASON FOR PUBLIC~TION: TO RECOMMEND COMPLIANCE WITH PARKER HANNIFIN CORP PRM NO. 36(REV. A) WHICH REDUCES BRAKE PISTON STROKE, THUS EXTENDING O-RING LIFg ADDS SELPAWUSTIND DRAKE FEATURE.
COMPLIANCE: PRIOR TO OR AT NEXT 100-HOUR INSPECTION
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILECOMPLYING WITH THIS SERVICE LETTER, CONTACTYOUR NEAREST CULFSTREAM COMMANDERAUTHORIZED SERVICENTER.
BY WHOM WORK WILL BE ACCOMPLISHED: A 6L P MECHANIC OR EqUIVALENT.
APPROVAL: ENOINF.ERING DESIGN ASPECTS ARE FAA APPROVED.
ESTIMATED MAN HOURS: TWO (2) HOURS.
PARTS DATA: PARTS REQUIRED TO COMPLY WITII TIIIS SERVICE LE~PTER MAY BE PROCURED THROUGHYOUR NEAREST CULFSTREAM COMMANDER AUTHORIZED SILRVICENTER FOR (220.00. REFERENCE THISSERVICE LETTER, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN ORDERING SERVICE LE1TgRNO. 361 KIT CONSISTING OF THE FOLLOWING:
Pd~ notla
BTY PART NO. DESCRIPTION
1 ea. 199-13000 Canveraion KitI ea. Complianee CardLee. ServiEe Letter Na. 567 Inntruetions
SPECI~LTOOLS: NONE.
Paselaf 3
SERVICE LE~EK NO. 367
INPTRUCTIONS: C-cnurloN
Cars must be taken and eye protection gear worn duringthis rework to avoid injury since we are dealing with
disassembly of a preloaded springstack.
Accomplish the following brake rework by installing Conversion Kit Pi~ 199-13000 as authorized by Parker Hannifin
Corp. PRM No. 36 (REV. A):
1. Chock main and nose wheel tires.
2. Apply a slight amount of pressure to brakes and set Parking Brako.
3. (WHILE WEARING SAFETY GLASSES) carefully Loosen the bolt which retains the enisting retract springs to
ibeback of the Hydraulic Pistons. (Typ. 8 places.) Remove and discard all parts.
4. Release Parking Brake
5. Remove Hydraulic feed line to Brake Assembly and cap.
6. Remove the 24 bolts which attach the beck plates to the Brake Cylinders, and remove brakes ham aircraft.
Screw one of the Back Plate attachment bolts into each piston in succession, and with hand pressure, pusheach
piston out of the Brake Cylinders. (MARK EACH PISTON AND BORE TO ENABLE~CT
REASSEMBLY.)
8. Remove O´•ril,Es from cylinder bores and pistons and discard.
9. clean eylinde~s and pistons using available solvent to aluminum.
10. Special attention should be given to the piston bores and pistons
A. Piston bores and "0" ring grooves should have foreign material loosened and Bushed from all surfaces,(The large diameter piston bore groove should not be polished with any abrasive material.)
8. The small diameter of the piston bore may be polished with steel wool or fine emery, but the finished
diameter shell not eroeed .565 min
C. The piston (lerge diameter) may be polished to remove shallow wear scratches andior nicks. The final
piston diameter, however, must be a minimum of 2.121.
D. Any prior rework to the above mentioned components which places them outside of the dimensionallimits defined, requires replacement of those components
11. Following cleaning and inspection of me cylinders anil pistons, instnll the new O-rings supplied in the Kit.
12. Lubricate the piston bares, O-rings and pistons with hydraulic nuld compatible with the aircraft system. Install
large O-ring in each cylinder groove and install small O-ring an each piston.
13. Lay the cylinder on a Rrm surface end insert piston into bore until the "0" rings prohibit further insertion. While
applying pressure with your thumbs, rotate the piston in a clockwise direction. After "O" ring squeeze is
overcome, the piston will slide freely into the bore. Push piston Bush to cylinder face. LRepeat 8 places.)
14. Install cylinders on aircraft
15. Install washers and cylinder tie bolts into cylinders and thru pressure plate. Typical 24 places.
16. Install (l)one insulator shim onto brake cylinder.
Page 2 of 3
SERVICE LETTER NO. 361
CAUTION: (The brake may have had two (2) shima per cylinderinstalled at disassembly. Reassembly, however, with the
new retract mechanisms requires that only one shim be
used~. The additional shims may be saved and used as
future replacements should ons become damaged.
I?. Install back plates and tighten (24 each) cylinder tie bolts. (FINAL TOR~UE 85-90 IN-LBS.)
18. Reattach hydraulic feed line and bleed brakes.
19. Apply brakes to hold pistons from turning. Install new retract mechanism into the back of each piston. Screw in
by hand, making sure that the stud botrome on the piston tail surface. (FINA4TOK~UE 30-40 IN-LBS.)
(PEFER TO ENCLOSED DRAWING FOR CORRECT PART SEBUENCING.)
20. Safety wire studs.
21. Apply decals supplied in kit lane per brats assembly) for reidentifieat~on, remove old decal.
22. Functional check brake system to assure that it is operating properly.
23. Fill out and mail Compliance Card
ELECTRICAL LOAD: NO CHANCE.
WEIGHT AND BI\LANCE: NO CHANCE.
SPARES AFFECTED: SPARES TO STOCK PARTS ONLY FOR THE 30´•10?C BRAKE ASSEMBLY.
PUBLICATIONS AFFECTED: The Pilot Operating Handbooks, Airplane Maintenance Manuals and Illustrated Parts
C;ltalog changes required by this document will be incorporated at the next scheduledrevision.
RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service Istter No. 367,dated 4 January 1985, entitled "Pnrker Hnnninn Corp. Product Reference Memo (PRM) No. 96 (REY. Al", accomplished
(date)
page 9 of 3
Sevvice Letter Guifs~reamAerospace
SERVICE LET~ER NO. 968
4 January 1986
nEAVY DUTY NOSE LANDING GEAA SPACER ASSEMBLY
MODELS I\FFECrrD: MODEL 690C, SERIAL NOS. 11121 AND 11128 THRU 11734.
MODEL 690D, SERIAL NOS. 15021 THRU 15033, 15035, 15036 AND 15037.
MODEL 69SA, SERIAL NOS. 88063 THRU 96061, 96083 THRU 96012, 96075, 98071, 96078,96082, 96085 AND 86088.
MODEL 69511, SERIAL NOS. 86201 AND 96102.
REASON FOR PUBLICATION: STEEL SPACER ASSEMBLY REQUIRED DUE TO AUTOMATIC STEERINGSYSTEM REACTION TIME.
COMPLIANCE: DURING OR PRIOR TO NEXT 100-HOUR WSPECTION.
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE
COMPLYING WITH THIS SERVICE LETPER, CONTACT
YOUR NEAREST GULFSTREAM COMMANDER
CAUTHORIZED SERVICENTER.
BY WHOM WORK WILL BE ACCOMPLISHED: A g P MECHANIC OR EQUIVALENT.
APPROVAL; ENGINEERING DESIGN ASPECTS ARE: FAA APPROVED.
ESTIMATED MI\N HOURS: TWO (2) HOURS.
PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE LETTER MAY BE PROCURED THROUGHYOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR 916.13. REFERENCE THISSERVICE LETTER AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN ORDERING SERVICE LETTERNO. 568 KB CONSISTING OF THE FOLLOWING:
QTY PART NO. DESCRIPTION
1 as. 16W8o´•1 Spseer Aasy6 ea. ANI)GOD1OL Washer2 ea. MS21042-3 Nut
1 se. MS14865-132 Cotter Pin
2ea. NAS43DD3-12 Spaesr2 se. NAS464-3-24A Bolt1 an. Camplienee Card1 se. 6srvice Letter No. 368 hstruetians
SPEC(ALTOOLS: NONE.
Pegs 1olS
´•i
SERVICE LETTER NO. 9BB
C
MARK SPROCKET TOOTHAND CHAIN LINK TO RETAINPROPER *LI(INMENT
EXISTIN~ CRAINIREF)
NA~40DD3´•12 SPACER
12 PLSI
NOSE GEAR COLLARS M821WZ´•S NUT
IREF) 12 PLS)
WASnERce PLO
FOLLOWUPI r7
I Ir~nll´•nonl
IREFI
EXlsTlNB SHIMISIIREF) IAEF)
NAF480´•J´•24~ BOLTTOROUE 20-28 IN´•LBS SPACER ASSY
lS PLD
EXISTINGWASHER(S1(REF)
NUT(REF)
COTTER PIN
NOSE
STEERING CYLINDERIREF)
Fi~un
Page 2 of 2
SERVICE LETTER NO 368
ACCOMPLISHMENT INSTRUCTIONS:
1 Remove radome from fuselage nose.
2. Cain access to nose landing Bear spacer assembly through nose gear wheel well.
3. Remove existing spacer assembly from nose gear collars as follows:
NOTE
To assu,e that the nose gear steering system stays in
a~ustmsnt, do not turn nose gear during replacement of
spacer assembly.
a Mark chain and gear on follow-up potentiometer assembly sprocltet to assure that same gear tooth an
sprocket is isinstolled in same chain link from which it was removed.
b. Slip chain on sprocket and allow potentiometer arm assembly to rotate against nose gear strut.
c Remove and discard existing bolts, washers, spacers and nuts that attach existing follow-uppotentiomster assembly and nose gear spacer assembly to nose gear collars (reBr to Figure 1).
d. Remove follow-up potentiametor assembly from nose gear
a. Remove existing cotter pin, nut and washers (note location of washers) attaching nose gear steeringcylinder rod end to spacer assembly and remove and discard existing spacer assembly. Retain existingshims for reinstnllation (refer to Figure i).
f install 160080-1 spacer assembly and existing shims between nose gear collars and connect spacerassembly to nose gear steering cylinder rod end with existing washer(s) (reinstall in same location notedin step a.) (refer to Figure 1)
a´• ~ioatall arislmg s.lb,uy sa~mbly oil nea. gaer u´•ulg boil (Zplaces), ANBGOD1(IL washer (6 places), NAS43DD3´•12 spacer (2 places) and M821042-3 nut (2 places(refer to Figure 11 Torque bolts 20 to 26 inch´•pounds.
h. Rotate nose gear 450 left and right from center to assure that steering cylinder rod end does not bindon new spacer pin install washer(s) and nut, finger tighten, then back nut off one (1) castellation andthen install new MS24668-132 cotter pin.
i. Rotate follow-up potontiometer assembly and reconneot chain to sproctet assuring that mark on sproeketgear tooth aligns with mark an proper chain link.
4 Reinstall radome an fuselage nose using existing hardware. Burnish baltiattach ureas to assure radome isgrounded to airframe.
6. Functional check nose gear steering system as outlined in Chapter 32 of the Airplane Maintenance Manual.
6. Fill out and mail Compliance Card
ELECTRICIL LCAO: NO CHANGE.
WEIGHT ANO BALANCE: NO CHANGE.
SPIAES PIFFECTEO: NO.
PUBLICATIONS I\FFECTED: The Illustrated Par~8 Catalog change required by this document will be incorporated atthe next scheduled revision.
AECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service Letter No.368, dated 4 January 1985, entitled "Heavy Duty Nose Landing Gear Spacer Assembly", accomplished (date)
Page 3 oTS
r´•.
~illService Letter Culfstream
Aerospace
SERVICE LETTER NO. 369
11Janualy 1986
LANDING GEAR CONTROL ASSEMBLY LUBRICATION
MODELS AFFECTED: MODEL 685, SERIAL NOS. 12001 THRU 18056.
MODEL 690, SERIAL NOS. 11001THRU 11079.MODEL BgOA, SERIAL NOS. 11100 THRU 11544.
MODEL B90B, SERIAL NOS. 11950 THRU 11566.
MODEL 590C, SERIAL NOS. 11600 THRU 11?29.
MODEL 590D, SERIAL NOS. 15001 THRU 15024.
MODEL 696, SERIAL NOS. 86000 THRU 95084.
MODEL 69SA, SERIAL NOS. 96001 THRU 96055.
REASON FOR PUBLICATION: POSSIBLE HAND ZIP OF LEAF SPRING WHICH COULD RESULT IN LOSS OF
SAFETY LATCH FEATURE
COMPLIANCE: WITHIN NEXT 100-HOURS TIME IN SERVICE.
NOTE
IF ANY PROBLEMS ARE ENCOUEF~ERED WHILECOMPLYING WITH TH1S SERVICE LETTER, CONTACTYOUR NEAREST GULFSTKEAM COMMANDERAUTHORIZED SERVICENTER.
BY WHOM WORK WILL BE ACCOMPLISHED: A d P MECHANIC OR EqUIVALENT.
APPROVAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED.
ESTIMATED MAN HOURS: ONE (1) HOUR.
PARTS DATA: MIL-G81322C GREASE MAY BE PROCURED LOCALLY.
SPECIALTOOLS: NONE.
PICCOMPL1SHMENT INSTRUCTIONS:
1. Jack airplane as outlined in the applicable Airplane Maintenance Manual.
2. Apply MIL-DdlS22C grease to not spring on landing gear control assembly. Grease is to be applied to the springsurface that comes in contact with the pin that actuates the spring (refer to Figure 1).
3. Cycle the landing gear control lever two (a) or three (S) times. After each cycle of the gear control lever, assure
that the safety locking mechanism on the landing gear control assembly functions properly. To assure that
Ianding gear control assembly is functioning properly, preeeed as follows:
a. Without touching or releasing the safety locking mechanism lever, try to pull up on the control lever.
b. If control lever will not go up without releasing safety locking mechanism, proceed to step 4.
o. If control lever will go up without releasing safety locking mechanism, cheek for correct grease
´•P’inb ´•nd rs~i´• lan(bll Br" mWI la~r ro UIU all.LI lai*.lnah´•nul. ill
landing gear control assembly is functioning properly. Safety locking lever must move freely without
Page 1 oft
ii
SERYICE LE~ER liP. S69
CENTER INSTRUMENTPANEL (REF)
~iPq
;lnY8e~I
A U!A4 4
TYPICAL GEAR CONTROL
SAFETY LOCKING I I LANDING GEAR
MECHAN18M LEVER I I CONTROL LEVER
(REF)\ I I /(REF)CENTER INSTRUMENT
PANEL (REF)
SPRING
(REF)
LUBRICATE WITHM~L-E81S22C GREASE O
0. a5" ABOVE AND BELOW PrN
pa ~EnO O
O O
VIEW A-A LANDING GEAR
LOOKING UP (REs)
rlsure i.
Page 2 ol S
SERVICE LE~ER NO. 369
d. If safety looking meehanism still does not function properly, replace existing landing gear control
aseembly with a new one.
4. After assuring that landing gear control assembly is functioning properly, removejacks from airplane.
5 Fill out and mail Compliance Card.
ELECTRICAL LOAD: NO CHANCE.
WEIGHT AND BI\L*NCE: NO CHANGE.
SPARES AFFECTED: All spare Lending Dear Control Assemblies (Part Numbers 640084-1, 540084-601 and 560013-1)must be pulled from shsl~staet lubricated and ehec~ed for proper operation
PUBLICPITIONS AFFECTED: The Airplane Maintenance Manual Interim Change Notice requiring lubrication of
lending gear control spring even twelve (12) months is included with this Service Letter.
RECORD COMPLIANCE: Malts an appropriate entry in airplane maintenance records as follows: Service Letter No. 369,dated 11January 1985, entitled "Landing Dear Control Lubrieetion", aeoomplishod (date)
Page 3 of 3
LettersoxCulFMlramAtms~eeCorporaIion
OXI´•blM E Nc O*lanoma 13123
SERVICE LETTER NO. 310
4 October 1885
FREON AIR CONDITIONER COMPRESSOR BELT COVER ASSEMBLY INSTALLATION
MODELSAFFECTID: THE FOLLOWING AIRPLANES ARE AFFECTED IF FREON A~R CONDITIONING
INSTALLATION WAS PROCURED FROM THE FACTORY:
MODEL 69OC, SERIAL NOS. 11124 AND 11156
MODEL 890D, SERIAL NOS. 15006, 15010, 16011, 16019, 15025, 15025 AND 15051.
MODEL 895A, SERIAL NOS. 0802?, 98038, 98041, 96048, 96048, 98054, 98068, 98061, 96059,96061, 96065, 96088, 980?1, 98081, 96088, 98089, 8~(181, 98098, 98094 AND 98095.
MODEL 89611, SERIAL NOS. 98201 AND 98202.
PEASON FOR PUBUC~TION: TO PROVIDE A COMPRESSOR BELT COVER TO PROTECT TRIM TAB CONTROL
CABLES IF THE COMPRESSOR BELT SHOULD BREAK.
COMPLIANCE: NEXT 100HOUR9 TIME IN SERVICE.
NOTE
IF ANY PROBLEMS ARE ENCOUP~f(ED WHILE
Q: COMPLYWF 1IT~ THL8 BEBnCE IETTgR, COIYT*CT
YOUR NEAREST OULFSTREAM COMMANDER
AUTHORIZED SERVICX~ER
BY WHOM WORK WILL BE ACCOMPLISHED: A 8t P MECHANIC OR EQUIVALENT.
ESTIMP~TID MAN nOURS: ONE (1) HOUR.
IIPPROVAL: ENGIP~ERINC DESIGN ASPECTS ARE FAA APPROVED.
PARTS BATA: PARTS REQUIRED TO COMPLY THIS SERVICE LETTER MAY BE PROCURED
TIII~OUGH YOUR NEARE9T GULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR 819.26.
REFERENCE THIS SERVICE LE~ITER, AIRCIIAFT MODEL AM) FACTORY SERIAL NUMBER WHEN ORDERING
SERVICE LET~R NO. S10 KIT CONSISTING OF THE FOLLOWING:
Plkrual´•´•taa4´•~laMnn*-
BTY PART NO. DESCRIPTION1 as. K1250188 Cover Aaey Kit
lee Compliance Card1 ea. Service Letter No. 310 Inetructioee
SPEOIAL TOOLS: NONE.
Page 1 of 2
SERVICE LETTER NO. 370
i. Gain access to Reon air conditioner compressor, located in aR fuselage, through baggage compartment door or
aff avionics access door.
2. Check Reon air conditioner compressor forinstallation of drive belt cover II cover is not installed, proceed to
step 3. If drive belt cover is installed, pmesad to step 4.
S. Install 1250iBB cover assembly on compressor as shown on kit drawing K12l01s0 dated November aB, 1984.
4. Fill out and mail Compliance Card
ILECTRICP~L LOAD: NO CIIANQE.
WEIGHT AND SALANCE: NO CHANDX.
SPARES I\FFECTIO: NO.
PUBLICI\TIONSAFPECTE0: NONE.
RECORD COMPLIANCE: Make an appropriate entry in ai~plans maintenance records as follows: Service Letter No.
3?0, dated 4 October 198B, entitled "Freon Air Conditioner Compressor Belt Cover Assembly Installation", accomplished(date)
C
page 2 of 2
~ervice Lettevwii* airwn
O*lahoin~ Ciry. OLI´•h.m´• .3123
SERVICE LE1TER NO. S11
24 April 1988
EXPAND TEMPERATURE RANGE OF ENVIRO SYSTEM IN AUTO MODE
MODELS AFFIOTED: MODEL 680C, SERIAL NO’S. ItBW THRU 11736MODEL 6W)D, SERIAL N(Y8. 15001 THRU 18042MODEL BBB, SERIAL NOB. 96000 THRU 86084MODEL 686A, SERIAL N(Y8. gB000 THRU 98100MODEL 68511, SERIAL NO’S. 86201 THRU 89208
REASON FOR PUBUCATION: TO EXPAM) UPPER TEMP&RATZTRE RANCE FOR MORE CABIN HEAT DURINGCOLD WEATHER OPERATIONS.
COMPLfAHCE: CUSTOMER OPmON.
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILEPERFORMING THIS SERVICE LETTER CONTACT THEGULRSTREAM AEROSPACE TECHNOLOGIES SERVICE
CENTER, ?901 N.W. 50TH, BETHANY, OKLAHOMA 13008.
BY WHO* WORK WILL BE ACCOIPUSHED: A B P MECHANIC OR E9UIVALENT.
APPROVAL: ENGINEERING DESIGN ASPECTS ARE F.A.A. APPROVED.
ESTlMATED MAN HOURS: TWO (2) HOURS.
PARTS DATA: ONE (1) EACH COMPLIANCE CARD.
SPECIAL TOOLS: NONE.
ACCOMPL)SHMENT INSTRUCTIONS:
1´• Remove Envim Control Panel (located below pilot’s in~trument penal) for Model Bg0C, Serial No’s. 11800 thru11?29, Model BW)D, Serial N~a. 16001 Lrulb024. Model 685; Serial Nb’n. 91000 thru 85084, Model BBM,8erial No’a. 88000 thru 98055: (lacated in center guadrant) for Model 680C, Serial No’s. ll?SO Wuu 11?96,Modal 89)D, Serial N~I1. 16026 Wru 16042, Mode! 885A, Serial Na’s. 98066 thru 98100, Model 886B, SerialNdB´• 86201 thru 88208 $BB RIBM 1)´•
a. Remove the two (2) 5.1 K Ohm ~-natt rralsters Ram the terminal of the temperature select pot Recormeetwires 8 and II to respective terminals oltampsrahua select pat (see Figure 2).
a. Reinstall Enviro Control Panel in the airplane.
4 F111 ontand mail Compliance Card.
ELECTRICAL LOAD: NO CHANCE.
WEI(IKC AND BAUANCE: NO CHANGE.
SPARES AFFeCTED: NO.
PUBLIC~ITION AFFECTED: The applicable Maintenance Manual Wiring Diagram and Illusbated Parts Catalogchanges required by this document will he ineolprated at neat scheduled revision.
RECORD COMPUANCI: MaLs an appmpriata entry in airplane maintenance records as follows: Service Letter Na.S?1, dated 28 April 1888, Entitled "Expanded Temperature Range .f Enviro System In Auto Mode" accomplished
(date)
Page 1012
SERVICE LETI~ER NO. 311
U1SS
MWHwunL IHcn Mnx
*um 8608 LOW
MODEL 6500, SERIAL NO’S. 11800 TIIRU 11128,MODEL 8g0D, SERIAL NO’S. 16001 THRU 15024,MODEL BBB.(IERIAL NOS. BSOM) TIRU 85084,MODEL 685A, SERIAL NOB. 86000 TKRU 86055
ec=cm~
CI17~
MODEL8800, 8ERWINOB, ll?SO THRU 11155,MODEL 890D, SERIAL N0’8, leoas THRU 16042,MODEL 0g5Al SERIAL NOg. 88558 THRU 88100
MODEL 8S5B, SERIAL NO’S. 88201 THRU 88208
Plgun 1
BEFORE R8515mR REMOVALAPTERAe815TOR REMOVAL
151I II
111
i ip~n2
PagsaoPa
_ _
jService Letteroa,~ml cini, orlsnoma 73123
Service Letter No. SL312
12 Ostobsr 1989
ENVIRO SYSTEM AMBIENT VALVE REPLACEMENT
MODELS AFFECTED MODEL 690C SERIAL NOS. 11602. 11603. 11614. L1618. i 1620. 11614. 1L636. i 1638. 11640.11662, L16j6. 11663, 11664. 11669. 11613. 11676. ilBi9. 11681. 11682. 11683. L1685. 11687,11693.11101.11103. 11709, 11721.
MODEL 690D SERIAL NOS. 15004. 15006. 15007, 1IOLL. 15014. 15015. 15016. 15020. 15021,15025, 15026.15028.15032, 15039. 15042.MODEL 695 SERIAL NOS. 95003. 95006, 95008. 95016, 95022.95024, 95034. 9044. 95048. 1)5058,85060, 95061. 95(162. 95065, 95070, 95079, 95084.YODEL 69SA SERIAL NOS. 96012, 96013,96025, 96032. 96033. 96055. 95058. 96066MODEL 6968 SERIAL NOS. 96062 AND 96207
REASON FOR PUBLICAT1ON: TO IMPROVE HEATING DURING DROUND OPERATION AT LOW AMBIENTTEMPERATURES.
COMPLIANCE: WITHIN NEXT 100 HOURSTIME IN SERVICE.
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYINGWITH THIS SERVICE LE1TER CONTACT THE OULFSTREAMAEROSPACE TECHNOLOGIES SERVICENTER, BETHANY.OKLAHOMA.
BY WHOM WOR~ WILL BE ACCOMPLISHED: A 81P MECHANIC OR EPUIYALENT
P~PPROVPIL: ENGINEERING DESIGN ASPECTS ARE F.A.A. APPROVED.
ESTIMATED MAN HOURS: ONE(1IHOUR.
FARTS DATA: REPLACEMENT AMBIENT VALVE MAY BE PURCHASED THROUGH YOUR NEARESTGULFSTREAM COMMANDER AUTHORIZED SERVICENTER TO OBTAIN A PARTS CREDIT.AMBIENT VALVE MUST BE RETURNED WITHIN 15 DAYS 130 DAYS INTERNATIONALLYI OFSHIPMENT DATE OF REPLACEMENT VALVE WITH A PROPERLY EXECUTED WARRANTYCLAIM AND A COMPLIANCE CARD. THIS OFFER EXPIRES 12 MONTHS FROM DATE OF THISSERVICE LETTER REFERENCE MODEL OF AIRPLANE AND SERIAL NUMBER WHENORDERING.
1 EACH PIN 1300470 AMBIENT VALVE1 EACH COMPLIANCE CARD
SPECIALTOOLS: NONE.
ACCOMPLISHMENTINSTRUCTIONS:
1. Gain aeeess to noweontrol velveaaaembly located leftofcenterline, top oPaft fuselage area through baggage door
2. Remove baggage compartmantoverheadand aR upholstery panels.
3. Remove clamp and ambient sir hose fmm Lhe noweontrol valve assembly.
4. Remove ambient air inlet iubei0nnge asrembly ileaeh 8-32 screwlsee Figure 1.
Page loE 3
SERVICELETTERNO.SL3?2
Icavno~ ICAVTION
Align mark check valve location and onentatlon between the ambient
valve and the now controlvalve. Location and orientation must not be
~hangadduringdiaassembly and reassembly.
5. Remove ambient vslvs((each 8-32screw) see Figure 1.
I CAUTION
Verify that the check valve location and orientation between theambient valve and the now control valve has not changed from
originallyaesembled.
B. Inlltall replacement ambient valve (4each 8-52 screw) seeFigure 1.Torque screws 12 to L8 inch-pounds.
Reinstall ambient air inlet tubeinanga assembly and motor support bracket to the flow control valve (4 each 8-32screw) see Figure i. Torquesrrews 12 to 15 inch-pounds.
8. Safety wire allscrews(8 each 8-32 screw)see Figure i.
9. Reinstall ambientair hose and damponthenow eontmlvalve.
10. Reinstail baggagecompartment aR andoverhead upholstsrypsnels.
11. Fill out andmail CompliancsCard.
ELECTRICALLOP.O: NOCHANGE.
WEIOHT*NDBALPIHCE: NOCHANGIE.
SPI\RESAFFECTED: NO.
PUBLIC*TIONS AFFECTED: NONE.
RECORD COMPLI*NCE: Make an appropriate entry in airplane maintenance records as follows: Service Letter No.
SL372, dated _October, 1989, entitled "Envim System Ambient Valve ReplaesmenC’ accomplished(dste)
PagePoFS
SERVICELEWERNO.ILS?1
AMBIENT nlR INLET
TUBEFL~NOEASSY
O
i j
O
nMaENT vnLvs nssv
CIECKYALYE
Flplra i.
PageSofS
PN/N
COMMANDER
SERVICE LETTER~RLINOTON. WA 9823´•183:
PHONE i380) *559797 F*X(~BO)rJ5111:
SeF/ice Letter No. 376
April 25, 200(3
Inspection of Main Landing Gear Clevis and Drag Brace Installations
Models Affected: All Twin Commander Models except for Models 500, 520, 560,
560A, 560E, 680, 680E, 700 and 720
Reason for Reports from the field of cracks found in Clevis P/N ED12758
Publication: and ED12526, cracks or distortion of the mounting bosses on the
M.L.G. outer body and cracks in drag brace assembly P/N
ES12404.
Compliance: Inspection recommended prior to further flight ii the landing pear
has not undergone inspection within the last 500 Hours.
Re-inspect at 500-Hour intervals.
By whom work shall Visual and dimensional inspection to be pe(formed by ALP
be accomplished: Mechanic or equivalent. Magnetic Particle inspection and
Fluorescent Dye Penetrant inspection to be performed by a
Level II N.D.T. Inspector.
Estimated Man-hours: Estimate 8 Man hours per landing gear assembly
Parts Data: As Required: 1 ea. ED12758 and 1 ea. ED12526 per MLG Assy.
Special Tools: None
Accomplishment Instructions:
1. Jack the aircraft in accordance with the applicable Aircraft Maintenance Manual.
2. Reduce the hydraulic system pressure to zero and ensure the landing gear control lever
is in the Down position.
3. Reduce the pressure in the landing gear nitrogen blow down storage bottle to "O" PSI.
Cautionl
Do not attempt to disconnect either end of the hydraulic-pneumatic actuating
cylinders until the pressure in the landing gear nitrogen storage bottle hat been
reduced to "O" PSI.
Page 1 of 3
Service Letter No. 376
4. Disconnect the actuating cylinders from the devises on the strut and secure the cylinders
out of the way.
5. Remove the bolts that secure the clevis to the outer body and remove the clevis.
6. Replace the devises with New or perform a Magnetic Particle inspection per ASTME
1444 or equivalent.
7. Inspect the M.L.G. clevis attachment bass for obvious distortion or elongation of the
mounting hole.
8. Measure the diameter of the mounting hole and determine that it does not exceed 0.877".
9. Perform a Fluorescent Dye Penetrant inspection of the clevis mounting boss in the area
illustrated on Figure 1.
10. Perform a Fluorescent Dye Penetrant inspection of the main landing gear drag brace
assembly in the area illustrated on Figure 2.
Il.lf no defects are noted during this inspection, reassemble, rig and perform a landing gear
retraction test in accordance with the Aircraft Maintenance Manual.
12. Fill out and mail Compliance Card.
13.if defects are found, contact Twin Commander Aircraft Corporation.
Electrical Load: No Change.
Weight and Balance: No Change.
Spares Affected: No
Publications Affected: No
Record Compliance: Make an appropriate entry in the airplane maintenance records
as follows:
"Ser/ice Letter No. 376, dated April 25, 2000, entitled inspection
of Main Landing Gear Clevis and Drag Brace Assembly
Installations" accomplished (Datel IAircraft Total Time) (Name)
(Cartiflcate No.~
Page 2 0(3
Service LettBi Nd. 376
Areas to be inspected i
Figure 1
Upper Brag Brace illustration
Area to Be Inspected
Figure 2
Page 3 of 3
COMPLIANCE RECORD
SERVICE LETTER NO. 376
INSPECTION OF MAIN LANDING GEAR CLEVIS ANO DRAG BRACE
INSTALLATIONS
MODEL AIRPLANE S/N REG. NO. TOTAL TIME (HOURS)
OWNER NAME
ADDRESS
TELEPHONE NO FAx NO
COMPLIANCE WITH SERVICE LETTER 376:
DAMAGE (cRACKs, WEAR, ETC.) FOUND: YES O NO O
IF YES, DESCRIPTION AND LOCATION OF DAMAGE (CW\CKS, WEAR, ETC.) FOUND:
DATE
WORK PERFORMED BY (PRINTED)
(SIGNATURE)
COMPANY
ADDRESS
TELEPHONE FAX
SF
Aircraft Technical Publishers Customer Service
101 South Hill Drive 6AM-5PM PST M-F
Brisbane, CA 94005 (800)227-4610
ATP Grid Index to Manufacturer’s Publications:
Twin Commander A/C
695, 695A, 6953
SERVICE INFORMATION
1) Applicable AD
2) Part Kit (1)
Issue Number 3) Part Kit (2)
Issue Date Issue Description 4) Compliance Time
SI-11SB AUTOPILOT SERVO CLUTCH 1)
03/20/1980 SETTINGS AND APPLICABLE FLIGHT 2)SEE ISSUE
MANUAL SUPPLEMENTS 3)
4)SEE ISSUE
SI-165 VOLCANIC ASH HAZARDS 1)
06/04/1980 2)
3)
4) EXPOSURE
SI-166 AIRESEARCH MFG. CO. SERVICE 1)
10/31/1980 BULLETIN NO. 5-2288 2) 103570-5
3)
4)SEE ISSUE
SI-167 SUNDSTRAND AVIATION 1)
01/05/1981 MECHANICAL SERVICE BULLETIN 2) 724722-21-003
7247222-21-003 3)
4) SEE ISSUE
SI-170 AIRWORTHINESS DIRECTIVE 1)
02/27/1981 81-02-03, AMENDMENT 39-4017 2)SEE ISSUE
3)
4)SEE ISSUE
SI-172 POWER BRAKE VALVE ADJUSTMENT 1)
04/24/1981 2)SEE ISSUE
3)
4) SEE ISSUE
01/20/2004 Copyright Aircraft Technical Publishers Page 1 of 6
GC 0853 SI SF
1) Applicable AD
2) Part Kit (1)
Issue Number 3) Part Kit (2)
Issue Date Issue Description 4) Compliance Time
SI-173 CABIN PRESSURE CONTROL SYSTEM 1)
07/15/1981 MODIFICATION 2)SEE ISSUE
3)
4)
SI-174 EXHAUST PIPE MOUNT REPLACEMENT 1)
07/15/1981 2)SEE ISSUE
3)
4)SEE ISSUE
SI-178 FLIGHT EQUIPMENT AND 1)
01/13/1982 ENGINEERING CORP. 2)SEE ISSUE
S.B. NO. 669-25-02 3)
4) SEE ISSUE
SI-179 PESTICIDE FUEL ADDITIVE 1)
02/01/1982 2)
3)
4) OPER DISCRET
SI-180A PARKER HANNIFIN CORPORATION 1)
06/17/1982 PRODUCT REFERENCE MEMO (PRM) 2)SEE ISSUE
NO. 25 (REVISION A) 3)
4)SEE ISSUE
SI-182 DOWTY ROTOL SE NO. 61-950 1)
06/01/1982 ALTERNATE GREASE (TEXACO LOW 2)SEE ISSUE
EP GREASE) FOR DOWTY ROTOL 3)
PROPS 4) SEE ISSUE
SI-183 IMPROVED AILERON SERVO 1)
07/09/1982 AUTHORITY -KFC 300 AUTOPILOT 2)SEE ISSUE
3)
070982 4)SEE ISSUE
SI-187 INSTALLATION AND/OR 1)
12/10/1982 MAINTENANCE OF ABRASION 2)
RESISTANT TAPE ON DOWTY-ROTOL 3)
PROPELLERS 4)
01/20/2004 Copyright Aircraft Technical Publishers Page 2 of 6
GC 0853 SI SF
1) Applicable AD
2) Part Kit (1)
Issue Number 3) Part Kit (2)
Issue Date Issue Description 4) Compliance Time
SI-189B APPROVAL AND INSTALLATION OF 1)
02/24/1984 TPE331-10-511K ENGINES 2)
3)
4)0PTIONAL
SI-191 TERMINATION OF FACTORY 1)
05/27/1983 FINANCIAL PARTICIPATION ON 2)
PARTS AND/OR LABOR ALLOWANCES 3)
ON CERTAIN SERVICE PUBS. 4)
SI-193 OIL VENT HOSE ASSEMBLY 1)
08/03/1983 REPLACEMENT 2)SEE ISSUE
3)
4) DISCRETION
SI-195 DOWTY ROTOL SERVICE BULLETIN 1)
12/09/1983 61-A995 (REVISION 1) 2)SEE ISSUE
3)
4)SEE ISSUE
SI-196 SCOTT AVIATION CUSTOMER 1)
02/15/1984 SUPPORT SERVICE LETTER NO. 2)SEE ISSUE
893-SL-01 3)
4) SEE ISSUE
SI-197A AIRWORTHINESS DIRECTIVE 1)
06/15/1984 84-10-06, AMENDMENT 39-4867 2) SEE ISSUE
3)
4) SEE ISSUE
SI-199 FUSELAGE STATIONS 386.85 AND 1)
05/25/1984 409.56 PULLEY BRACKET 2)
MODIFICATION 3)
4) DISCRETION
SI-200 EXHAUST GAS TEMPERATURE (EGT) 1)
07/16/1984 INDICATOR ISOLATOR 2)SEE ISSUE
INSTALLATION 3)
4) SEE ISSUE
01/20/2004 Copyright Aircraft Technical Publishers Page 3 of 6
GC 0853 SI SF
1) Applicable AD
2) Part Kit (1)
Issue Number 3) Part Kit (2)
Issue Date Issue Description 4) Compliance Time
SI-201 GARRETT SERVICE BULLETIN 1)
07/25/1984 TPE331- 73-0128 2) SEE ISSUE
3)
4) SEE ISSUE
SI-202 KING RADIO SERVICE MEMO 1)
02/14/1985 313, REVISION 1 2)
3)
4) SEE ISSUE
SI-203 INLINE PROTECTION FOR FUEL AND 1)
02/21/1985 OIL PRESSURE TRANSDUCERS 2)SEE ISSUE
3)
4) OPTIONAL
SI-204 R1 OVERBOARD ROUTING OF CABIN 1)
01/09/1987 EXHAUST AIR 2)
3)
4)
SI-205 EXHAUST STATIC PRESSURE HOSE 1)
04/08/1985 ASSEMBLY REPLACEMENT 2)SEE ISSUE
3)
4)SEE ISSUE
SI-206 NEGATIVE TORQUE SENSOR (NTS) 1)
04/12/1985 SWITCH RELOCATION 2) SEE ISSUE
3)
4)SEE ISSUE
SI-211 GARRETT TURBINE ENGINE 1) 87-24-07 R1
06/30/1986 COMPANY SERVICE BULLETIN NO. 2) SEE ISSUE
TPE/TSE331-74-0003 3)
4)SEE ISSUE
SI-212 GARRETT TURBINE ENGINE 1) 87-24-07 R1
06/30/1986 COMPANY SERVICE BULLETIN NO. 2) SEE ISSUE
TPE/TSE331-75-0004 3)
4) SEE ISSUE
01/20/2004 Copyright Aircraft Technical Publishers Page 4 of 6
GC 0853 SI SF
1) Applicable AD
2) Part Kit (1)
Issue Number 3) Part Kit (2)
Issue Date Issue Description 4) Compliance Time
SI-214 EMERGENCY AIRWORTHINESS 1)
06/30/1986 DIRECTIVE NO. 86-12-02 (GTEC 2)SEE ISSUE
SERVICE BULLETIN NO. 3)
TPE331- 72-0530) 4)SEE ISSUE
SI-219 DOWTY ROTOL G.A. PROPELLER 1)
02/27/1987 DE-ICING SLIP RINGS 2)
3)
4)SEE ISSUE
SI-220 INFORMATION CONCERNING ECU 1)
03/31/1987 FAILURE 2)
3)
4)
SI-222 DOWTY ROTOL PROPELLERS 1)
04/13/1987 BLADE GROUP INTRODUCTION OF 2)SEE ISSUE
ESSO BEACON 325 GREASE 3)
MODIFICATION NO.(C)VP3179 4)RECOMMENDED
SI-223 MAIN LANDING GEAR TRUNNION PIN 1)
11/30/1987 ACCESS COVER 2)SEE ISSUE
3)
4) DISCRETION
SI-225 SUNDSTRAND ECU AIR CYCLE 1)
06/02/1987 MACHINE OIL REPLACEMENT 2)SEE ISSUE
3)
4)SEE ISSUE
SI-235 AEROQUIP AEROQUIP GENERAL 1)
08/24/1989 AVIATION ALERT NOTICE RECALL 2)SEE ISSUE
ON AEROQUIP 601 HOSE 3)
BULLETIN NO. 001 4) SEE ISSUE
SI-236 RA INSPECTION AND REPLACEMENT OF 1)
08/02/1995 FLUID LINES 2)
3)
4) RECOMMENDED
01/20/2004 Copyright Aircraft Technical Publishers Page 5 of 6
GC 0853 SI SF
1) Applicable AD
2) Part Kit (1)
Issue Number 3) Part Kit (2)
Issue Date Issue Description 4) Compliance Time
SI-237 New production replacement 1)
04/14/1994 fuel cells 2)SEE ISSUE
3)
4)SEE ISSUE
SI-238 DEICER BOOT INSTALLATION 1)
01/16/1996 2)
3)
4) SEE ISSUE
SI-244 PROCEDURES FOR OPERATING IN 1)
01/27/1997 ICING CONDITIONS TO THE USE 2)
OF POWER SETTINGS BELOW FLIGHT 3)
IDLE FOR TURBOPROP AIRCRAFT 4) SEE ISSUE
SI-249 Installation of 300004-501 1)
05/18/2000 removable duct as part of SE 2)
214 3)
4) None Found
SI-251 PPG windshield moisture seal 1)
03/19/2001 installation and repair 2) CK163
procedure for installed Twin 3)
Commander Aircraft,contd. 4)See Issue
SI-252 Exhaust pipe seal installation 1)
04/03/2002 i ntructi ons 2) See Issue
3)
4) Recommended
SI-255 Picture window upper channel 1)
12/15/2003 inspection 2) 210-704-1
3) 310704-2
4) Recommended
SI-256 Main landing gear up-lock 1)
12/16/2003 assembly bolt 2)AN174C-21A
3)
4) See Issue
End of Index
01/20/2004 Copyright Aircraft Technical Publishers Page 6 of 6
GC 0853 SI SF
L --´•´•;ul-~-"1
JI? Rackweil intematlanal
Servic~ :1 ormMaaMnaml ~a na*nl *mm
m~m.gllmmlraB
ii
t’ 8~RV1CE INFORMATION NO. SI-119B
(SuprRedes 8ervtce information Na. 8I-110A dated 4 December 1918)20 March 1880
AUTOPILOT SERVO CLUTCH SETTINGS AND APPLICABLE FLIGHT MANUAL SUPPLEMENTS
MODELS AFFEF~ED!:;"’I’’I’(: MODEL 5005, SERIAL NO’S 3265 ATID rmBS., MODEL 680A, SERIAL NO’S
1lsos THRU 11348, MODEL 680B, SERIAL NO1S11350 AND SUBS., YODEL
880C, SERIAL NO’S 11BW AM) SUBS., MODEL 685, SERIAL NO’S 85000
AND SUBS., AND MODEL~OOI SERVUl)rO’S 7W01 AND 6UBS.
-38u::;;:-- r*´•-l:-: -Q:~:":-J--;.-´•-´•´•-´• ´•*´•-:--I1R´•~ rai?-( --´•~i;r;-
REASON FOR PUBLI~: TO PROVIDE A LLST OF SERVO CLIPI‘CH SETTINGS FOR AUTOMATIC
PILOTS INSTALLED ON ROCKWELL COMMANDER MODELS AFFECTED
AND THE REQUIRED FLIDHT MANUAL 8UPPLEMENTS.
COMPLIANCE: NOT APPLICABLE.
BY WHOM WORK WTLL BE ACCOMPLISHED: NOP APPLICABLE.
APPROVAL: NOT APPLICABLE.
e~TIMATED MAN HOURS: NONE.
PARTS DATA: NONE.
SPECIAL TOOLS: NONE.
INSTRUCTIONS:
YO1I
The follo~ving autopllots and servo clutch settings are ~pmved:
MODEL FLT.MANUAL AUTOPILOT AILEIODN ELEVATOR RUDDER
SUPP_L_EMENI mr-lrs nN-itj)
seas a a,R.C. Apszoe 27 gs) 16 gal3 aoneg~uell H-14 (No Clutahes on H-ll)
885 4 Bend(x M-´•IC 40 g 5) 10 5) 185 (?16)(Trim) 20 (t 2)
10 Bend(x FCS-810 SO (."3) 30 (2 S)(Trlm) 30 d* 3)
a80A 1 s..mx M-4D 45 2) ~5 (iO, -4) 182 C 18)(Tdm) 20 a)
4 SIprry SPZ-100 (Electmnlo Torque Limited)7 or 8 Collins AP-106 (8ee Collins Service ~tter 11-14)
6 King KFC 300 54 C’ 4) 56 (.t 4) 135 d 13)(see KPN006-O081-01 Manual)
BOOB 5 Bendlx M-4D 45 C 21 45 -4) 182 C 18)c (Tam) to
1 Collins APIOB (8ee Collins Service Letter ii-14)
I King KFC 300 54 C 4) 95 r 4) 135 g 13)(Ses gPN000-(1081-01 Manual)
.Depenmna on FHght Director installed.
Page 1 ot 2
BERYICE INFORMATION NO. 81-1198
MOD~ FLT.MANUAL AIL~KUN
SUPPLEMENT -cii;-i:.iir
ssoc KLng KFC-500 )6 (I 10i 61 ii 6) 135 (f ii)(Tdm) 55~3)
8 Collins AP-1OB (see ColUns Service Publieatlon SIL 3-80)
(Trim136~ 13)095 1 King KFC-)OO 80 e to, 51
8 ColHne AP-1OB Lsee Collins 8ervica Publication SIL 3-80)
700 18 Collills AP-10? (8ee Calllna 8srvlce Lader AP-IO? 5-~B)
8 King KFC-aoo 32 (f 3) 46 r 5)
ELECTRICAL LOAD; NO CHANGE.
WEIOm Ir BALANCE: NO CHANGE.
PUBLICATIONS AFFECTED: NONE.
RECORD COMPLIANCE: NOT APPLICABLE.
Pa~s 2 oi 2
i Rockwell intematlonal
i’ Stlrvjce onn*nNMol*wan
Mal Nonh *nnw
r SERVICE INFORMATION NO. 1-185:;4 June IsBO
VOLCANIC ASH HAZARDS
MODELS AFFECTED: ALL ROCKWELL INTERNATIONAL MODELS.
REASON FOR PUBLICATION: TO PROVIDE MAINTENANCE AND INSPECTION RECOMMENDATIONSFOR AIRCRAFT EXPOSED TO VOLCANIC ASH.
COMPLIANCE: UPON EXPOSURETO VOLCANIC ASH.
BY WHOM WORK WILL BE ACCOMPLISHED: A P MECHANIC OR EpUIYALENT.
APPROVAL: NOT APPLICABLE.
ESTIMATED MAN HOURS: AS REPUIRED.
PARTS DATA: AS REQVIRED FOR ROUTINE MAINTENANCE.
SPECIAL TOOLS: NONE.
ACCOMPLISHMENT INSTRUCTIONS:
The following are excerpts from A1Resaarch Phoenlx Telex dated Map 25, 1880:
Until such time as sufficient information is gathered 0 permit more accurate assessment of the immediate and
long-term effects of operating the angina in an ash-laden environment the following recommendations shouldbe carefully considared in addition 0 those outlined in your routine maintenance program.
Recommendations
I. Whenever possible avcdd operation in known volcanic ash-laden environment. Exposure to tNs foreignmaterial Ln high concentrations or lesser concentration for prolonged periods La considered damaging tothe engine sind will likely result in increased cost of ownarship.
2. If operation in ash-Iaden regions cannot be avoided the following is recommended:
a. Engine oil filters should be examined more iraglent~y to Lnaure that abnormsil blockage is not
occurring. Would an unusupl amount of contaminate be observed in the the filter and
engine oil should be changed.
b. If oparallon in ash-ladan environment is fairly the engine oil change interval shouldbe shortensd to:
100 Hours for TPESS1/TSESS1150 Hours for TFE1S1
c. Fuel system filter should be more irequentlg examined to insure that blockage is not occurring.
d. Air fillers in pneumatic circuits associated with the AiResearch and Bendlx fuel control on
Turtdne Propulsion Engines /PS fLlter/ should be ewmined and cleaned as raguired afte. each
Right where ash was encountered.
a. Use of thrust reversing should be avoided where possible on ash-coated runways.
ri. In ash fallout areas, inlet and exhaust covers should be installed as Boon as engine cooling will
parmit. This is to ave6d introduction of ash into the static engine.
Page 1 of 4
iggRVICE NO. 8I-185
ffoTf!
Detrimental effect on the engine from volcanic ash will be
proportional to the concentration of the ash and the periodof exposure.
Relaxatlon of these recommendations in favor of more tyFdcal, routine maintenance should begoverned by
experience. The rate at which erosion is occurring within the engine may be estimated by careful examination
of tan/prop blade and compresaor blade leading edges. Thlnn(lg, sharpedllg or roughrmng of these surfaces
is indicative of accelerated erosion.
The following are Eleerp~s frdm OenerR1 Aviation Airworthiness Alerta AC Na. 45-l8:
i. Introduction. The purpose of this special alert Is to provide safety
LnformaCian and recommended actions to preclude possible airworthiness
problems associated with aircraft exgonure to volcanic ash either in the
atmosphere or on the ground. The following recommendations are based on
the best available information at this rine and will be amended as further
information and facts are gathered.
2. sac*ground. Volcanic ash from Mount st. nelens has been analysed to
contain abrasive and corrosive materials such as sulfuric acid and floride
and chloride salts and acids. Oependinq on the location of the volcanic
ash fallout. the particle sises range froma8 small as .5 microns to 100
microns. Most aircraft screens will filter out material down to 15
microns bur will pass particles that are smaller.
The ash will probably be encountered as a fine powder, li)ie talcum
powder, light grey in color. When dampened it has been reported to set
similar to concrete. Due to adhesive action of the sulfuric acid.^the
acid tends to adhere to the interface between the particles and the
aircraft structure causing corrosion. Although volcanic anh may oar be
visible on the structure, sulfuric acid may still exist causing corrosion
and it i. recommended that all aircraft that have been exposed to volcanic
fallout be given a rent to determine the acidity levels. This can be
accomplished by Ule application of nitraliine paper available from many
pharmacies. If the Ph factor is or below, it ill recommended that the
following correctlveactions be ra~en as soon as practicable.
i. Rirfranne.
(1) safety precautions including safety glasses. gloves and
protective clothing should be adhered tot
(2) ~ircrsfL should be cleaned in the following sequence;
a. The aircraft .anufaciurer’s maintenance manuals should be
followed regarding the protection of aircraft systems during the cleaning
process. The procedures recommended by the manufacturer for the
Inspection and cleaning or purging of pltot static aysr´•n~s. instruments
systems, etc., should be followed.
b. If there is any volcanic ash coating on the aircraft
structure, It should be removed by hand brushing, sir vacuum cleaning
prior to performing any washing actions. If the aircraft is washed before
removing ash, It will form a corrosive paste,
c. The aircraft should be thoroughly cleaned, inside and out,
before wanhing.
d. The aircraft should be rinsed thoroughly with freah water
without. scrubbing to ensure that all parts of the aircraft have been amplyrinsed.
e. The aircraft should be given a rest at the completion of each
wash cycle to ensure a Ph factor of above The Ph factor may be
performed by taping nitraelne paper strips on various parts of the
structure and wetting with distilled water.
Page a of 4
-i; ´•;;´•´•-´•ii-;´•;
(IERY~CE MFORMATION NO. SI-165
r. it may be necessary to repeat the wash procedures on
continuous basis in areas where fallout continues. To ensure rhaL the
sulfuric acid is neutraliled, complete the wash cycle using a petroleumbase solvent.
g. It is recommended that regardless ai the Ph factor, aircraft
exposed to volcanic ash be given a water wash as assurance againstcorrosion.
h´• Close inspection for external signs of damaged seals.
especially landing gear and landing gear actuators.
d. Systems. For all aircraft exposed to volcanic ash an the ground or
air, system checti should include LnspecLlon of piLot-staLic probes.static ports, air conditioning outflow valves and filters. generator
cooling tubes and filters, vacuum lines and filters, end externallymounted sensors, such as long wire antenna, and angle-of-attack sensors,
to remove any ash conLa.inatlon. precautionary inspection should be done
on a random basis of electronic equipment subject To cooling air co assure
need for equipment removal for removal of ash contaminaLion.
5.
(i) General. A. noted above the nature of the volcanic ash is that
it is both abrasive lin the form of fine powder) and corrosive iin the
form or acid content). Both and reciorocatinil engines may
be af~ecred. Compressor and Furbine blades suffer erosion by abrasive
particle impact. Lubrication and other fluid systems are subject to
conramination by solids and chemicals, while moving parts are subject to
abrasive wear.
The abrasive nature of the material causes rapid mechanical
damage La moving parts. Experience has shown that engines operated with
oil contaminated with the ash has caused them to fail in as few as ?O
nours after exposure.
The acids associated with the ash are soluble in ails and as such
attack engine parts resulting in rapid deteriocaiion. Engines can also be
at~acred externally by the corrosive action.
Maintenance. Engine. which have been operated or subjected to a
volcanic ash fallout need:
a. Thorough external cleaning.
b. Cleaning or changing of all oil, fuel, and other systemsscreens and/or filters and draining all sump.. Flushing and cleaning of
conLaminated fluid systems should be accomplished following the enginerecommended procedures.
c. Cleaning and scavenging of any open ranks where the ash or
cheini;al action could collect and EancentraLe.
d. Oil and fluid draining and change.
e. Close inspection for external signs of damaged seals.
f. Cleaning and inspection of accessaries and components for
contamination such as vacuum filters and regulators.
g. Following cleaning, inspection, end fluid changes the proper
operation of the engine should be verified by run-up. Frequent oil and
fluid changes should be scheduled. ouring subsequent operationtemperatures and pressures should be monitored closely far changes which
may signal problems.
h. Spectrographic oil analysis is an indicator of engine wear
and contaminarion. Comparison of analysis of early samples after cleaningwith previous analysis;eporrs can serve as an inicator of an engine’sstability.
PageSofl
IERYICE INFORMATION NO. 81-185
Recurrent inspections. Rircrafr ovners and aperalore are uigcd To
:iosely moniror aircrafi and engines. including systems. on a Continuingti16i5 and take action as deemed necessary for aircrait exposed to volcanic
csh as assurance against corrosion.
Hay 21, 1980
Right into volcaluc ash can damage windshields and aide windows by pitting due to sand blasting effect.
ELECTRICAL LOAD: NO CHANGE.
WEIGHT AND BALANCE: NO CHANGE.
SPARES AFFECTED: NO.
PUBLICATIONS AFFECTED: The Airplane Maintenance Manual changes required by this document will
be incorporated at a future date.
RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service
Information No. 81-165, dated( June 1888, entitled ’Yolcanic Ash Hazards", accomplished (date)
Page4o14
Rockwell internanonal
Service Information omlhnunonlm
sml hnh i~l*nll ~nu
SERVICE INFORMATION NO. 81-188
91 Ootober lsBO
AIRESEARCH MFO. CO. SERVICE BULLETIN NO. 5-2288
MODELS AFFECTED: MODELS 080A AND 500B, SEIIIAL NO’S. 11100 THRU 11688 THAT HAVEREPLACED OUTFIXIW/8AFETY VALVES BETWEEN 1 JANUARY 1880
AND 51 OCTOBER 1880, AM) MODEL 8g0C, BEIIIAL NO’S. 11800 THRU
11648, AND MODEL 585, SERIAL NO’S. 85000 THRu 85051, 85055 THRU
85035.
REASON FOR PUBLICATION: TO RECOMMEND COMPLIANCE WITH AIRESEARCH MFO. CO. 8ERVICE
BULLETIN NO´• 5-2288.
COMPLIANCE: WITHIN NEXT 250 HOURS TIME IN SERVICE.
noT8
IF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYING WITH
THIS SERVICE INFORMATION LETTER, CONTACT YOUR NEAREST
ROCKWELL COMMANDER AUTHORIZED SERVICE FACILlTY.
BY WHOM WORK WILL BE ACCOMPLISHED: A B P ME~C OR EQUIVALENT.
APPROVAL: SEE AIRESEARCH MFO. CO. SERVICE BULLETIN NO. 5-2288.
ESTIMATED MAN HOURS: INSPECT FOR DATES ONE (1) HOUR.
REPLACE OUTFLOW/SAFETY VALVE(S) S1X (5) HOURS.
PARTS DATA: Contact your nearest Rooltwell Commander AuUlodeed Facility for replacement hdnoul/8a(etyValve part number 105510-5. A credit will be issued, for each Outnow/Safetu Valve, upon receipt of old
Valve part number 1035?0-5, a properly executed Warranty Claim and a Compliance Card.
SPECIAL TOOLS: FLASHLIGHT AND INSPECTION MIRROR TO INSPECT OUTFLOW/SAFETY VALVES FOR DATE 8TAMPS.
ACCOMPLISHMENT INSTRUCTIONS:
i. Remove Flight Director and Course Indicator from left instrument pana~ to facilitate inepeelon of
Outflow/Safety Va~ves.
2. Comply dth AiReaearch Mfg. Co. Service Bulletin No. 6-2288.
WOT8
When replacing Oumow/SPieQ Valve, refer to Airplane Maintenance
Manual for bolt Lorqulng information.
3. RelnetaH Flight Director and Course Indicator an left instrument panel.
4. Fill out and mail Compliance Card.
ELECTRICAL LOAD: NO CHANGE.
WEIGHT AND BALANCE: NO CHANGE.
8PARES AFFECTED: NO.
PUBLICATIONS AFFECTEDI NONE.
RECORD COMPLIANCE: Nlahre an appropriate entry in airplane maintenance recorda se follouls: Service
Information No. 81-108, dated 81 October 1BBO, entitled "1LlResearch Mfg. Co. Service Bulletin No. 5-2388,11accompllahed (date)
Pageloil
SERVICE BULLETIN
OUTFLOW/SAFETY VALVE Inspection for suspected faulty poppet
SECTION 1
PLANNING INFORMATION
A. Effectivity
This service bulletin is applicable to the 103570-5 Outflow/Safety Valvesused on GAO/Rockwell aircraft.
B. Reason
ALResearch has become aware of a potential problem which may be experiencedwith the outflow and safety valves listed in this service bulletin.
The problem area is centered around the outflow valve poppet assembly. It is
suspected that a small percentage of the poppet assemblies could fracture,and depending upon the type of fracture, could go as an undetected fault or
if a total fracture occurs it could lead to a valve failing closed.
Because of these circumstances, we are alerting our customers to perform an
inspection check of the outflow and safety valves as described in this servicebulletin.
C. Description
This service bulletin provides instructions for inspection of outflowlsafetyvalves for a suspected faulty poppet assembly. If valve has a functional testdate of 1 January 1980 through 91 August 1980 without a date stamp on poppet or
has a fracture of poppet, return valve to GAD/Roekue~l.
It is recommended that inspection of outflow safety valve be accomplishedwithin 250 flight hours after receipt of this service bulletin. Warrantyreplacement of outflow/safety valves under this service bulletin will ter-
minate as of 31 October 1981.
D. AF~roval
Governmental approval not required.
E. Manpower
Not determined.
Oct 1/BO Bulletin No. 5-2288Page 1 of 4
F. Materials Availability
Return outflow/safety valves to OAD/Rockvell through established channels.
G. Tooling Price and Availability
Not spplicsble´•
H. Weight and Balance
None
I. References
This service bulletin was prepared in accordance with ATA 100 requirements.
J. Other Publications Affected
None.
SECTION 2
ACCOMPLISHMENT INSTRUCTIONS
A. Access for Inspection
(1) Determined by Aircraft Manufacturer’s procedures.
B. Method of Valve Inspection
(1) Inspect all installed outflow/safety valves as follows:
(a) Visually check the functional test (FT) date appearing on cover of
outflow/safety valve (see figure 1) to determine if the ~T date falls
between 1 January 1980 through 31 August 1980´• If the FT date is
not within these dates and no pilysical damage is apparent, no further
action is required and outflow/safety valve is considered serviceable.
(b) If check of the FT date is between the specified date of 1 january
1980 and 31 August 1980, perform check of poppet assembly to determine
ii a date stamp appear, on surface of poppet (figure i), or ii poppet
is fractured. If poppet does not have a date stamp or is fractured,
remove and replace the outflovlsafety valve.
(c) If check of poppet assembly reveals a date stamp on poppet, regard-
less of an Ff date within 1 january 1980 through 31 August 1980 and
no physical damage is apparent, the poppet assembly is considered
serviceable and outflow/safety valve can remain in use.
Bulletin No. 5-2288 oct 1/80
Page 2 of 4
F T INK STAMPED DATE
WILL BE IN THIS AREA.
EXAMPLE: AUO 18 IsBO
I~
O
IDENTIF1CI\TION 01 F T DATE
Q
O
INI(STI\MPEO DATE WILL BE INPOPPET PART NO. MOLDED
THIS AREA NEXT TO POPPET PARTIN POPPET SURFACE
NO. OR WILL BE APPRoXIMATELY
1800 FROM POPPET PART NO.
EXAMPLE: APR1 lsBO
IOENTIFICATION 01´• POPPET DATE .II I´•.
Typical Outflow/Safety Valve
Figure 1
Oct 1/80 Bulletir. No. 5-2288 A´•PR"(´• nf L
Cc Reidentitication Instructions
None.
SECTION 3
MATERIPI~LINFORMATION
Not applicable.
Bulletin No. 5-2PBB oct 1/80
Page h of 4
oeneral Plviaum DM~n ROCkWBIIInternational
(405) 7886030
TWX: 8(08308810AB: *EROCOM
Cable: AEROCOM
-N OTICE
For Service Information No. SI-166, a credit of
one (1) hour will be issued for inspection of
Outflow/Safety Valves. If valve removal is required,
a credit of six (B) additional hours will be issued upon
receipt of a Warranty Claim form.
Rockwell internat~onal
Service Information an~l*mmoManrml Mnn aa;MI ~mua
BsnM( MUrmu nrB
SERVICE INFORMATION NO. 51-167
6 JANUARY 1981
SUNDSTRAND SERVICE BVLLETIN NO. SE 724722-21´•003
MODELS AFFECTED: MODEL 690C; 8ERIAL NO’S. 11600 THRU 11663 (EXCEPT 11626 d 11651) AND MODEL
595, SERIAL NO’S. 86000 THRU 96044 (EXCEPT 95031).
REASON FOR PUBLICATION: TO RECOMMEND COMPLIANCE WITH SUNDSTRAND SERVICE BULLETINNO. S8124722´•21-003
COMPLIANCE: WITHIN NEXT 100 FLIDHT HOURS (REFER TO SUNDSTRAND SERVICE BULLETIN NO.
88724122-21-009).
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE COM-PLYING WITH THIS SERVICE INFORMATION LETI~ER,CONTACT YOUR NEAREST ROCKWELL COMMANDER
AUTHORIZED SERVICE FACILITY
BY WHOM WORK WILL BE ACCOMPLISHED: A dr P MECHANIC OR EQUIVALENT.
APPROVAL: REFER TO 8UNDSTRAND SERVICE BULLETIN NO. 88724722-21-003
ESTIMATED MAN HOURS: TWO (2) HOURS.
NOTE
RaeLwsll International, General Aviation Division will allow
a credit of two (2) hours upon receipt of a properly enecuted
warranty claim and a compliance card while the airplane is
within the factory warranty period.
PARTS DATA: Contact your nearest Rockwell Commander Authoriled 8enica Facility furnishing them with the se-
rial number of the Enviromental Control unit installed in your airplane. Parts to comply with Sundstrand Service Bulle-
tin No. 88 724122´•11-003, will be supplied on a no charge basis until 31July 1981
NOTE
In order to furnish a matching unit data plate, the serial
number dthe ECU is essential and must be 1*mir8ed at time
oforderplacement.
SPECIALTOOLS: NONE
ACCOMPLISHMENT INSTRUCTIONS:
1. Gain access to Envimmental Control Unit, located in aft fuselage, through lower aff fuselage access door.
2. Comply with Sundstrand Service Bulletin No.SB 72472221-003.
3. Perform a prenight checkout of Envimmentsl Control System, Lrefer to Maintenance Manual, Chapter 21), ensuringsystem funotions properly and that there is no evidence of oil isalage.
4. Install acoess door on lower aft mselage.
5. Fill out and mail Compliance Card.
Page 1o12
SERVICE INFORMATION NO. 81-161
I
ELECTRICAL LOAD: NO CHANGE.
WEIGHTAND BALANCE: NO CHANGE
SPARES AFFECTED: NO
PUBLICATIONS AFFECTED: The airplane Maintenance Manual changes, and the Model 690C/695 Illustrated Parts
Catalog changes required by this document will be incorporated at the nert scheduled
revision.
RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service Informs´•
tion No. 81-161, dated 5 January 1981, entitled "Sunstrand Service Bulletin No. S8124122´•
21-M)S, accomplished (date)
Papeaola
SUNDSTRAND AVIATION MECHANICALsuaom~auo
UN1I01 SUND8TRIND CORPOR~TION
4747 HIRRISON I\YENUL.ROC1(FORD. ILLINOIS 81101
SERVICE BULLETIN
Envirolm~ental Control Unit Replacement of Fluid Level
Sight Plug with Oil Pill Tube
SECTION I-PLANNING
i. Effectivity: Sundstrand Parr Number 7247221\ Environmental Control Unit
I Il~del ECU-II 7, serial olrmbers 001 theou8~0)6, and 101 through 179 used
on Rockwell 840/980 aircraft.
2. Reason: Field experience has shown that the present method of oil filling
causes excessive oil spillage and possible incomplete filling of the
air cycle machine.
3. Description: This service bullerin provides instructions for removal of
the presently installed fluid level sight plug and ~ring and in-
stallation of an oil fill tube. This modification will result in
improved serviceability of the environmental control unit.
i 1 4. Compliance: Within the next 100 hours of flight operation.
5. Approval: None required.
6. Plsnpover: Approximately 1 manhour will be required to perform this
replacement procedure.
7. ~steriel Cost and Availability: Contact your nearest authori~ed Rockwell
Service Center for parts availability. Parts will be supplied at no
charge until July 31, 1981.
8. Tooling Price and Availability: No additional tooling, other than that
required for normal aircraft maintenance, will be required for this
replacement procedure.
9. Weight and Balance: No change.
10. References: Sundsrralld Engineering Order 037350.
11. Other Publications Af fecred: None.
at islao 3B724722 ´•n´•003Nov 15/80 (Revfsion 1) Page 1/2 of 7
FLUIO LEVELSIGnT PLUG57915
iO-RING1832481~901
PARTS TD BEREYOVED
IIR CICLEUIZCHINE724950C 11 I I I-----
VEWB
LUBRltnTKXI PLATE DENTRICITIOI( PLATE
1002164 717704
OENVIRoNMENTnL OCONTROL uNIT
LUBRICATION NO
YIR .PNDILSPEC YFR S~RNOCIWCITI I (CU(TMIER PN I I
INSPECT I I
CHANGE 118
AVIATION SUNDSTRAND AVIPITION
DIV OF SUNDSTRAND CORPolv of SVNDSTRAND CORP
ROCKFORD, ILLINOISROCKFORD, ILLINOIS ~O us se zl-oO,
O
S8-2177-~
~aetallarion of Oil PiII Tube 731721
Figure 1 (Sheet 1 of 2)
oct 11/80 S8724722 ´•21´•003Nov 15/80 (Revision I) Page 4
-~Zon. FILL TUBE
731721
FITTING731722
O-RINGM83248-1-907
VIEW 1
TUBE PLUGLlS24404D6
LOOP CLIMPMS21919DG8 LLY WASTIER
AN960PDIOL
WASTIERSCREWN*S1351-~-10P
LOOP CLAMPU521919H20
NUTY521043-3
OIL FILL TUBE731721
VIEW B I191NCH BELOW
IND P~RBLLELTO BOTTOM OFMPT D(CWNGER
S8-2178
Inet´•ll´•fion of Oil Fill Tube 731721
Figure I (Sheet 2 of 2)
S8724722 ´•2\´•003oct 15/80 Page 5
1O. Reidentify environmental control unit as follows:
A. Remove old identification plate (717704) from environmental control
unit.
WARNING: METHYL ETHYL KETONE IS TOXIC AND PLAMMABI.E. W NOT BREATHE
VAPORS. USE IN WELL VENTILATED AREA FREE FROM SPARKS, FLAME,OR HOT SURFACES. WEAR SPLASH GOGGLES. SOLVENT-RESISTANT
GLOVES. AWD OTHER PROTECTIVE GW\R. IW CASE OF EYE CONTACT,PLUSH WITH WATER AND SEEK MEDICAL ATTENTION. IN CASE OF SKIN
CONTACT, WASH WITH SOAP AND WATER.
8. Remove old adhesive by cleaning surface, where identification plate
(717704) was located, with methyl ethyl ketone, Federal SpecificationTT-H-261.
C. Piece dauble-bacled, pressure-sensitive tape on back of identification
plate (717704), and position identification plate on environmental
control unit as shown in Figure I of this service bulletin.
Il. Check lubrication plate (5002164) for time between oil inspections. If the
number in the INSPECT block greater than 25, replace lubrication plate as
follows:
A. Remove old lubrication plate (5002164) from envirowental control unit.
WARNING: METHYL ETHYL KETONE IS TOXIC AND FLI\HHIIBLE. DO NOT BREATHE
VAPORS. USE II WELL VENTILATED AREA FREE PROH SPARKS, FLAME,OR HOT SURFACES. WEAR SPLASH GOGGLES, SOLVENT-RESISTANT
GLOVES. AND OTHER PROTECTIVE GEAR. IN CASE OF EYE CONTACT,PLUSH WITH WATER AND SEEK MEDICAL ATTENTION. IN CASE OF SKIN
CONTACT, WASH WITH SOAP AND WATER.
R. Remove old adhesive by cleaning surface, where lubrication plate(5002164) was located, with methyl ethyl ketone, Federal SpecificationTT-M-Z61.
C. Place double-backed, pressure-sensitive tepe on back of lubrication
plate (5002164), and position lubrication plate on environmental control
unit as shown in Figure I of this service bulletin.
act Lrlao S8724722 ´•n´•o 03Nov 15/80 (Revision 1) Page 6
SECTION III- MATERIALS INFORMATION
pty Unit
Per List DlspositionlNew P/N ECU Price Key Word Old e/N InstructionsNew P word
7247228 N/~ NIA Environmental 724722A Modify and
(Note 1) Control Unit identify
None 1 N/A Fluid Level 57915 Remove and
Sight Plug discard
Same 1 N/A ~ring M83248- Remove old.1-907 install new
731721 1 N/A Oil Fill Tube None install
731722 N/A Fitting None install
MS21919DG6 1 N/A Loop Clamp None Install
nSZ1919H20 1 N/A Loop Clamp None Install
HS24404D6 1 N/A Tube Plug None Install
NAS1351-3-10P 1 N/A Socket Head Cap None Install
Screw
AN960PD10L 2 N/A Flat Washer None Install
HS21043-3 1 N/A Self-locking Nut None Install
Same 1 N/A Identification 717704 Remove old,
Plate install new
Same I N/A Lubrication 5002164 Remove old.
(Note 2) Flare identify.install new
Note 1: Environmental control units retrofitted according to this bulletin
are identified by the identification plate marked with the symbol8821-003 and part number 7247228.
Note 2: If the number in the INSPECT block is greater than 25, lubrication
plate must be replaced. The lubrication plate will not be sent with
the oil fill tube end associated components. If a new lubrication
plate i. required. order through the nearest euthoriaed Rockvell
Service Center.
oct 15/8088724722 ´•21´•003
Nov 15/80 (Revision 1) Page 7
S
_ _
Service Information GulFstreamnmericanunarol*1´•loa
Cannmand´•r Dlrilia
M)01 Norm Rostwall Avsnus.B~many´• Otlahonu 73(138
SERVICE INFORMATION NO. SI-l?O
27 FebNary 1981
AIRWORTHINESS DIRECTIVE 81-02-03, AMENDMENT 39-4017
MODELS AFFECTED: MODEL 690A, AIRPLANE SERIAL NOS. 11249, 11269 THRU 11344. MODEL 690B,AIRPLANE SERIAL NOS. 11350 THRU 11546, MODEL 690C, AIRPLANE SERIAL NOS. 11800 THRU 11860 AND
MODEL 685, AIRPLANE SERIAL NOS. 95WO THRU 96040.
REASON FOR PUBLICATION: TO RECOMMEND COMPLIANCE WITH AIRWORTHINESS DIRECTIVE 81-02-03.
(REFERENCE ZMR 151, PURITAN-BENNETI~OXYDEN MASK.)
COMPLIANCE: REFERTO AIRWORTHINESS DIRECTIVE 81-02-05.
MOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE COM-
PLYING WITH THIS SERVICE INFORMATION CONTACT
YOUR NEAREST GULFWREAM COMMANDER AU-
THORIZED SERVICENTER FACILITY.
BY WHOM WORK WILL BE ICCOMPLISHED: REFER TO AIRWORTHINESS DIRECTIVE 81-02-05.
APPROVAL: REFERTO AIRWORTHINESS DIRECTIVE 81-02-03.
ESTIMATED MAN-HOURS: 81-02-03.
PARTS DATA: REFERTO AIRWORTHINESS DIRECTIVE 81-02-03.
SPECll\LTOOL%: REFERTO AIRWORTHINESS DIRECTIVE 81-0203.
ACCOMPLISHMENT INSTRUCTIONS:
I. Comply with Airworthiness Directive 81-02-03.
ELECTRICAL LOAD: NO CHANGE
WEIGHT AND BALANCE: NO CHANCE
SPARES: REFERTOAIRWORTHINEIS DIRECTIVE 81-12-03.
PUBLICATIONS AFFECTED: NONE
RECORD COMPLIANCE: Make an appropriate entryin airplane maintenance records as follows: Airworthiness Di-
rective 81-02-05, Amendment 39-4011, effective 21 March 1981, accomplished (date)
Page lofl
PVRITANBENNEIT AERO SYSTEMS
Ain~orthinesP Dirretive
Vl,hale, IhII
81-02-0) PURITAN-BENNETT AERO SYSTEMS COMPANY; Amendment 39-4017. Applies to Puritan-Bennett Aero Systems Company oxygenmasks P/N 174039, 174010-01, 174010-03, and ZMR 100 series as
listed below.
for P 174039
S/N for P/N 174010-01 and 174010-03
146, 147. 109,00150 through 00194195 through 259
261 through 2’73
275 through 292
S/N for P/N 2?IR100 series
Compliance required as indicated, unless alreadyaccomplished
causing eitbeeTo prevent the regulator inlet valve from
leakage or positive pressure within the facecone, accomplishthe following;
(a) Within 120 days from the effective date of thisAirworthiness Directive, remove diaphragm assembly P/N F334-1001-1 and install diaphragm assembly P/N F334-1001-1 modifiedto include diaphragm and plate assembly P/N f334-1003-1.8evision E.
(b) After modification per paragraph (a) of this AD,permanently mark letter "M" at the end of or beneath the maskserial number. This serial number is located under the facecushion on the left-hand side of the hardshell on the 194039and ZMR100 series masks, and on the back surface of the headharness on the 174010-01 and 174010-03 masks.
(c) The modified diaphragm replacement of paragraph (a)of this no shall be accomplished by returning the mask to
Puritan-Bennett Aero Systems Company, 111 Penn Street, El
Segundo, California 90295. However, this replacement in theZMR100 series masks listed below may be accomplished in the
field in accordance with the following Puritan-Sennett Aero
Systems ATA Component Maintenance Manuals;
)5-10-25 for the ZMR1S0 mask
35-10-27 for the ZMR129 mask35-70-28 for the ZMR129-1 mask
35-10-29 for the ZMi~lls mask
Pagelofa
NOTE: Purftan-Bennett Aero Systems Company Service Bulletin
No. 1, dated April 15, 19801 pertains to the subject of this
Airworthiness Directive.
(d) Alternate inspections, modifications, or other
actions which provide an equivalent level of safety may be
used when approved by the Chief, Engineering and ManufacturingBranch, FRA western Region.
This amendment becomes effective March 20, 1981.
Page 2 of 2
.r
P~IIService
Commnndar Dlviuon6001 North Roe*wsll /Wsnu~.sathany. Oklahoma 73(3(18
SERVICE INFORMATION NO 51-172
i 24 April 1981
POWER BRAKE VALVE ADJUSTMENT
MODELS AFFECTED: MODEL 690C, SERIAL NOS. 11800 THRU 11663 AND MODEL 695, SERIAL NOS. 95000
THRU 95051.
REASON FOR PUBLICATION: TO ASSURE PROPER ADJUSTMENT OF POWER BRAKE VALVES.
COMPLIANCE: WITHIN NEXT 100-HOURS TIME IN SERVICE.
MOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE COM-
PLYING WITH THIS SERVICE INFORMATION LET~ER.CONTACT YOUR NEAREST DULFSTREAM COMMAN-
DER AUTHORIZED SERVICENTER FACILITY.
BY WHOM WORK WILL BE ACCOMPUSHED: A 8~ P MECHANIC OR E9UIVALENT.
I\PPROYIL: NOTAPPLICABLE.
ESTIMPITED MAN HOURS: ONE AND ONE-HALF (1.6) HOURS.
PARTS DATA: 1 EA. COMPLIANCE CARD.
SPECIALTOOLS: TWO (2) HYDRAULIC PRESSURE CAGES WITH O TO 1000 PSI CAPABILITIES.
ACCOMPLISHMENT INSTRUCTIONS:
1. Reduce hydraulic system pressure to zero and disengage parking brakes.
2. Remove pressure cap from tee fitting installed on brake line above each main gear brake assembly (refer to Figure1).
3. Install a hydraulic pressure gage, with O to 1000 psi range, at each tee fitting.
4. Connect a 28 volt de e~tarnal power source to the airplane electrical system at the external power receptacle.
5. Place battery switch in BA1TERY position.
MOTE
The au~ilian hydraulic pump should operate and a hydraulicpressure of 615 to 606 psi should be indicated on instrument
panel hydraulic gage.
6. With brakes released, observe tee mounted hydraulic pressure gages. Pressure should indicate zero. If any pres-
sure is indicated st either gage, proceed to step 8.
7. If pressure is zero, with brakes released, operate brakes with normal toe pressure on brake pedals to obtain 615
to 605 psi on tee mounted pressure gages. Remove tee pressure from brake pedals and brake pressure should im-
mediately drop to zero. If gages indicate zero pressure, proceed to step 13., but if any pressure is indicated on tee
mounted pressure gages, after release olbrakes, proceed to step 8.
8. Check all castellated nuts on rudder pedal installation to assure that no binding occurs when pedals are released.
Page 1eIS
SERYICE LNFORMATION NO. 81-1?3
i-
;I’2
ail~
LANDING GEAR (RLFI
LEFT INSTALLATION SHOWNINSTI\LL HYDRP~ULIC
RIGHT INSTALLATION OPPOSITEPRESSVRE GAGE ON
THISTEE
Fipuie i.
g~ Remove access door, located on lower lan aide of nose section st f\lselage station d.50, to gain access to power brake
valves.
10. Loosen adjusting Checknuts on power brake valves and slowly turn pressure adjusting setscrews rountercloeltwiss
until indicated pressure on tee mounted pressure gages drops to sere. Turn pressure adjusting setscrews eounter-
clockwise one additional full turn and secure adjusting chrknuts (refer to Figure 2).
11. After adjustment, operate brake pedals using normal toe pressure. A brake pressure of 515 to 605 pi should be
observed. Removetae pressure from brake pedals and brake pressure should immediately drop to sere.
12. Reinstall access door.
18. place battery switch in OFF position.
page 2915
BERVICE INFORMATION NO. 81-112
PREhSUREADJUSnNOCHECKNUT (REF)
PRESSURE ~DJU1TINO
SETSCREW IREF)POWER BRAKE YALYE IREFI
figure 2.
14. Remove hydraulic pressure gages from each brake line and cap tee Bttings.
15. Assure that hydraulic system is functioning properly.
16. Fill out and mail Compliance Card.
ELECTRICAL LOAD: NO CHANGE.
WEIGHT AND BPILINCE: NO CHANGE.
SPIRES AFFECTED: NO.
PVBLICATIONS P.FFECTED: NONE.
RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service Information
No. 81-1?2. dated 24 April 1981. entitled "Power Blake Valve Adiustment", accomplished (date)
page )ofS
_
%er\8ice information Gulfsh´•eamAmericanCOIPOR*TION
DmmndrMvklm
6WI Nad, Ros~vall ~vsnul.Fnh´•ny, O*l´•h~ma IJms
SERVICE INFORMATION NO. 81-115
16JulylsB1
CABIN PRESSURE CONTRM SYSTEM rODIFICATION
UM)ELS AFACTED: MODEL 8800, SERIAL NOS. 11880 THRU 11686 AND MODEL 886, SERIAL NOS. 86088
THRUssOB7.
RUSON FOR PVSLCPITION: TO DIMINISH CABIN RATE 8URGE UPON LANDING.
COMPLIANCE: AT OWNERS DLSCRETION.
*OTO
P ANY PROBLEMS ARE ENCOUNTERED WHILE COM-
PLYING WPPH THIS SERVICE INFORMATION, CONTACT
YOUR NEAREST GULLSBREAM COMMANDER AU-
THORIZED (IERVIC&NTER.
BY WHOM WORKWILLBE*CC(~PLISnED: A6L PMI~CHI\MC OREQUIVALENT.
APPROVAL: FAA DOA 8W-Z APPROVED.
ESTII~D MIN nOUR9: ONE (1) HOUR.
PARTS DITA: PART8 REqUIRED TO COMPLY WITH THIS SERVICE INRORMATION MAY BE PROCURED
THROUGH YOUR NEAREST OULFB~TREAM COMMANDER BERVICE~EI( AOR (20.88. REFERENCE THIS SER
VICE INFORMATION, AIRCRAIT MODEL AND FACTORY 8ERIIU. NUMBER WHEN ORDERING SERVICE
FORMI\1?ON NO. 81-118 KIT CONSI8TING OF THE AOLUIW~JO:
aTY PARTNO. DESCRIPTION
1 as. BOM)91´•LD?6 ResWetor
1 se. Compliana, Card
1 ea. 8ervi~a inf~nnation No. SI1?S inst~uction
SPE0IiL TOOLS: NONE.
Page 1 olJ
(IERVICE INFORMATION NO, 81-113
ACCOMPUSHMEM INSTRUCTIONS:
i. Push pilot’s seat as far aft as possible.
2 Push copilot’s seatas farforwardas possible.
3. Lean copilot’sseatback forward.
4. Pull pilot’s control wheel back and secure.
5. Cain secess to existing ANB164D nipple, looated under instrument panel on depressurieation control shutoff valve,by laying slang side of pilofs wat.
B. Disconnect existing tube assembly (Pi~ 880649´•33) from shutoff valve nipple (refer to Figure i).
Remove and discardexisting depressuri~ation control ahut~RValue nipple (P~ ANB18-4D1 (refer to Figure ii.
8. Apply tenon tape (3M No. 511 or eguivalent) to tapered threads of 8000S1´•(D-15 restrictor as follow.:
a. Place tenon tape two (2) threads in from end of tapered threads and hold tap firmly with thumb.
b. Stretch tap against threads and wind clockwise one (1) lap. Continue to hold tightly against threads until tapehas been broken.
NOTE
Do not attempt to tear tap sideways. Snap tape off in same
direction used for winding.
9. Install an ANB29-4 cap assembly (obtain locally) on end of 800037-4D-75 restrictar opposite tenan tape to facilitateinstallation of restrictor on existing shutoff valve,
10. Install 900037-41)´•76 restrictor on existing shutoff valve, remove AN929-4 cap assembly, malting sure that resCic-Dr doss not turn, and connect existing tube assembly to rnstrictor (refer to Figure i).
ii. Functionally check pressurieation system to assure there are no leaks.
12. Release pilot’s control wheel.
13. Fill out and mail Compliance Card.
ELECTRICAL LOAD: NO CHANCE.
WEIGHT AND BAU\NCE: NO CHANDE.
SPARES AFFECTED: NO.
PUBLICPITIONS AFFECTED: The Model B9OC/685 Illustrated Parts Catalog change required by this document will be
incorporated at the next scheduled revision.
RECORD COMPUINCE: Make an appropriate entry in ai~lane maintenance records as follows: Service InformationNo. 81-113, dated 18 July 1981, entitled’%abin Pressure Control System Madifioation", accomplished (date)
Page 2 al S
BERVICE MFORMATION NO. 81-115
WTFLOW/S~CETY(REF1
I-r::: n BULKHEI\DIREF)
i: iRELIOVIEXI~IN.*NBI04D NIPPLEP~ND REPLI\CE WITHBWOa74D´•ll RESTRICTOR
‘B
DEPRhSSURIZATION -CC-L~ //YM)NTROLBHUTDFF
VI\LVE IREF)
EX18TIN08808)8JJTUBE ASSY IREF)
Flpra i.
Page S of S
~j"llService
CORPOR*TION
Csmmada aCr,lonMKII Norm Roo)irmll ~vsnus.Bsmany. Olshoma 13W8
SERVICE INFORMATION NO. SI-l?l16 July 1981
EXHAUST PIPE MOVNT REPLACE~ENT
MODELS AFFECTED: MODEL 880C, SERIAL NOS. 11BW THRU 11687 AND MODEL 886. SERIAL NOS. 86000
TWR~ 86028, 86080 THRU 06081.
MOTE
PI 18 RECOMMENDED THAT 8ERVICE INFORMATIONNO. 81-1?4 BE ACCOMPLISHED WHILE COMPLYING
WITH SERVICE BULLETIN NO. 188.
RIASON FOR PUBLICATION: TO REDUCE TAILPIPE VIBRATION BY PROVIDING BETTER ISOLATION
BETWEEN TAILPIPE AND AIRFRAME.
COMPUAHCE: A~041NERSD18CRETION.
MOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE
COMPLYING WITH THIS SERVICE INFORMATION,CONTACT YOUR NEAREST DUL~AM
COMMANDER AUTHORIZED 8ERVICENTER.
BY WHOM WORK WILL BE ~CCOHPUSHED: A dr P MECHANIC OR EQUIVALENT.
APFROVAL: FAA DOA SWZ APPROVED.
ESTlMATED MAN HOVRS: FOURTEEN (14) HOURS.
PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE INFORMATION MAY BE PROCURED
THROU(IH YOUR NEAREST CIULF8TRF~AM COMMANDER EIERVICENTER FOR: KIT NO. 1 8404.11 OR KPI~ NO.
2 -8484.11. REFERENCE THIS 8ERVICE INFORMATION, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER
WHEN ORDERING SERVICE INFORMATION NO. 81-114 KIT CONBIEITING OF THE FOLUIWINGI:
Kit Ne. 1 Model 680C
KitNo. 2 Model 886
Kit Kit
No.l Na.e
4TY BTY PARTNO. DEBCRIPI~ION
2es. 8I0B61-RES Channel Aasya as. 010a61-REs Channel Aasy
II ea. 4ss. B1~BB1-RE11 Washer
18ea. 16aa. BIOBS1-RE1B Pad
las, dsa. 810882-68 specsr8ea. 24U)B´•1 Mount
4ea. 4sa. AN4-l2A Bolt
Bea. 8sa. ANBBO-10 Waahar
Page 1 o( 6
SFRVICe INIDRMATION NO. 81-114
UPPER COWLIN(ISHELL
EXHAUST PIPE
EXTENSION ASSY
EXHAUSTPIPEASSEMBLY
d
FORWARDFAIRING
LOWER
NOSE RING COWLING
ASSEMBLY SHELL
EXHAUST
PIPE
ASSY
CLAMPS
ENGINEEXHAUST
PIPE
DlnPHRPI(IM
BOLT
DOLLAR
ENGINE
r: EXHAUSTSEAL
WASHER
NUT
PI~Zm 1.
PasaolB
5WVICE lNPORMATlON PSO. 81-174
4sa. 4ea. ANBBOCIIGL Washer
18 as. 16 as. ANI)?O´•8 Washer
4sa. 4 se. MS20500-428 Nut
8 ea. 8 as. M8205001032 Nut
8ea. 8aa. MS210SgC1-08 Screw
8 as. 6sa. M82103BC1-10 Screw
1 sa. 1 ea. Compliance Card
1 ea. 1 se. Service information No. 51-174 instructions
9PECI~LIOOL9: NONE.
PICCOMPLISWMENT INSTRUCTIONS:
1. Remove leR and right engine exhaust pips assembly as follows (refer to Figure 1):
a. Remove the fonuardfairing.
b. Remove upper end lower engine cowling shells.
c. Remove exhaust pipe extension assembly.
WOTB
There are four (4) screws, accessible from inside the main
landing gear wheel well, that secure the exhaust pipesxtension assembly to the engine nacelle.
d. Remove both clamps from seal and Bid seal aft towards the diaphragm.
a. Remove nuts, washers and bolts that secure the exhaust pipe assembly to the engine exhaust pipe´•
f Support exhaust pipe assembly and remove nut, washer, bolt and spacer ham channel that is located on aft
inboard side of exhaust pip asssmbly.
8´• Turn exhaust pipe assembly slowly and remove from aft side of diaphragm.
2. Drill out rivets attaching existing left and right exhaust pipe assembly attach channels to nacelles and mark
centerline on existing channel (refer to Figure 2).
3. Neat existing channel into new channel assembly so that centerline of sxlsting channel is on centerline of new
channel assembly, position forward end of existing channel flush with forward end of new channel assembly and
clamp channels together. Referenoe.oenterline of holes in existing channel must be 0.44 inch from sft end of new
channel assembly (refer to Figure 3).
WOTE
Centerline is marked on each end of new channel assembly.
4. Drill four (1) 0.192 (+0.002) inch diameter holes through hales in existing channel into new channel assembly (refer
to Figure 3).
5. Drill existing hole. in nacelle to 0.182 (r0.002) inch diameter and install 610651-RES channel assembly (Model
6g0C) or 610661-RES channel assembly (Model 886) on nacslle using MS27038C1-08 screw (4 places), AN960-10
washer (4 places) and MS206001032 out (4 places) (rsfer to Figure 4).
page 9 of B
IERVICE INE~DRMATION NO. 81-1’14
LEFT INITALLATION SHOWN
RIGHT lN9TALLATION OPPOSITE
EXISTING FRAME IREF)
EXHAUSTPIPEEXTENSION (REF)
ii’
-E
EXHAUST PIPE (REF1
MARK CENTERLINE ON
EXISTING CHANNEL
Pllun 2.
1 o,-
ASSURECHANNELSARE FLVSH I\T
MIS END
aleo~´•ro.l8l"om.HOLE U PLS)
EXISTING CHANNELBIM~I´•RIS CHANNEL ASSY
OR
B(~BI´•REI CHANNEL ASIY
FlpnS.
PsgelolB
BERVICE INFO~N NO. 81-114
LEFT INSTALLATIONSHOWN EXHAUST pl/’" FIPICELLE IREF)
RIGHT INSTALLATION OPPOSITE EXTENSION IREFI
MSnM8C1´•108CReW*NB1OSW~HER
BIOBS1´•REIBPAD
IONE PAD INSIDE AND ONE
VIEW kA PADOUTSIDEL(1 PLS)
AN87a3WkSHER
IBETWE~N PAO
ANO MOUNTING BRIZCIET)
EXISTING FRAME (REF)
EXHAUSTPIPE1\ EXTENSION IREF)
t~
~ii
EXHAUST PIPE (REFI
ATOROUE BOLTSI IN´•LB9 OVER
RUNNING TOROUE
OF NUTS_
NACELLE IREF)
MU-12ABOLT
EXHAUSTPIPE nOB~(-RE(( WASHER IUNDER BOLT HEAD)4111&( MOUNT 12 REED)
M1BBOUIIL WASHER (UNDER NUT)MS2MW428NUT
I)PLS)
VIEW B-ll DlA.HOLE
MRU EXISTING RIVET LOCI\TIONI M9nmBC1~088CREW
~NB(HI´•(O WASHER IUNDER NUTIMSMMlOlm2NUT
IIPLS)
BIOBII´•RES OHANNEL IMODEL BBOC)OR
BIOB~IIREICH*NNEL IMODEL BB(i)
Flpral
PsgelolB
BERVICE MPORMATION NO. 66-1?4
8. Reinstall exhaust pipe assembly on airplane as &:iuwi (raBr to Figure i):
a, insert exhaust pip assembly through diaphragm and position for attaching to engine exhaust pipe
b. Align holes in forward miler and exhaust pipe assembly with thane in the engine exhaust pip and install bolts,
washers and nuts.
NOTE
Washers and nuts are installed on Forward side of R~ant
miler. Use wedge between outer akin assembly and exhaust
pipe assembly sprevent turning or twisting of exhaust pipeassembly during installation procedures. Tighten mts to a
torque value of 60 inch-pounds.
c´• 8snne aRend of exhaust pipe assembly to near channel assembly using 610852´•59 spacer (2 placesl, ANb12A
bolt (2 plama), 8108B1-REI1 washer (2 places), 242881 mount (1 places), ANBBOC418L washer (2 places) and
M920S(X)-1032 nut (2 places) (rsfer to Figure 1).
d. Slide pip extension as~mbly over exhaust pip assembly end position for securing to engine nacelle.
a. Install MB21038C1-10 sorew (4 places), ANI?OJ washer (8 places) and B1OBSI´•RE19 pad (8 places) that secure
the exhaust pipe extension assembly (refer to Figure 4).
NOTE
The B1~BS1-RE1D pads are furnished ´•niW1 no screw blee.
Use sharp tool, as required, to open a hole in center of padmesh.
f Unfold seal and position over Rent collar and secure by installing clamps.
B´• Install forward fairing.
h. Install upprand lowersnSineeawlin~shdle.
Fill outand Mail Compliance Card.
ELECTRICAL LOAD: NO CHANGE.
WEIGHT AND BPILANCE: NO CHANGE.
SPARES AFFECTED: NO.
PUBUCmONS IFFECTED: The Illustrated Parts Catalog changes required by this document will be inmrprated at
the next scheduled revision.
RECORD COMPLIINCE: Make an appropriate entry in airplane maintenance records as follows: 8ervice
No. 91-1?4, dated 16 July 1881, entitled’gxha~st Pipe Mount Replacement", accomplished (date)
Page Bol 0
Service Information GtdfstreamAmei,canEORI’ORITII)N
i6W1 Norm Roclwall ~usnue.
B~mlny´• O*l´•homa ’IJWB
SERVICE INFORMATION NO. SI´•178
13 January 1982
FLIGHT EOUIPMENT AND ENOINEERINO CORP. SERVICE BULLETIN NO. 669-25-02
MODELS P.FFECTED: MODEL 0gBA. SERIAL NOS. 86W1 THRU 8M)Z1.
REASON FOR FUBL(CATION: TO RECOMMEND COMPLIANCE WITH FLIGHT EQUIPMENT AND
ENGINEERING CORP. SERVICE BULLETIN NO. 668´•25-01.
COMFLIANCE: REFER TO FLIGHT EQUIPMENT AND ENGINEERING CORP. 8ERVICE BULLETIN
NO. 669-25-01.
BY WHOM WORK WILL BE PICCOMPLISHED: A L P MECHANIC OR EQUIVALENT.
APPROYAL: REFER TO FLIGHT EQUIPMENT AND ENGINEERING CORP. SERVICE BULLETIN NO. 668-25-02.
ESTIMATED MAN HOURS: 8M (6) HOURS.
NOTE
OULFSTREAM AMERICAN CORPORATION WILL ALLOW‘A CREDIT OF SIX (6) HOURS LABOR UPON RECEIPI~ OF
A PROPERLY EXECUTED WARRANTY CLAIM AND A
COMPLIANCE CARD.
PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE INFORMATION MAY BE PROCURED
THROUGH YOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED 8ERVICENTER FOR (100.00. A FULL
CREDIT WILL BE ISSUED UPON RECEI~T OF REMOVED ORIGINAL ROLLERS AND FITPWCS, A PROPERLY
EXECUTED WARRANTY CLAIM AND A COMPLIANCE CARD. REFERENCE THIS SERVICE INFORMATION,AIRCRAW MODEL AND FACTORY SERIAL NUMBER WHEN ORDERING). SERVICE INFORMATION NO 81-1?8
KIT CONSISTING OF THE FOLLOWING:
NOTE
Parts are for crew seats only.
C3TY PART NO. DESCIUPI~ION
Id ea. 51245 Track Fitting52 as. 83425 Track Roller
1 ea. Compliance Card
1 ea. Service Information No. 81-118 instructions
SPECll\LTOOLS: NONE.
NOTE
This modification applies only to the crew seats. Cockpitdividers must be removed in order to remove seats.
Pegslofi)
BERYICE INFORMATION NO. 81-118
i. Comply with Flight Equipment and Engineerng Corp. Serivee Bulletin No. 689-25´•02.
NOTE
Disregard step 3B. orService Bulletin No. 688-26-02.
2. Fill out and mail Compliance Card with Warranty Claim and all removed original rollers and fittings to Dulfstream
American Corporation, Commander Division, 5001 North RooLwell Avenue, Bethany, O~lahoms 13008.
ELECTRICAL LOAD: NO CHANGE.
WEIGHT AND BALANCE: NO CHANCE.
SPARES AFFECTED: NO.
PUBUCATIONS AFFECTED: NONE.
RECORD COHIPLI~NCE: Mslte an appropriate entry in airplane maintenance records as follows: Service Information
No. SI-118, dated 13 January 1982, entitled "Flight Equipment and Engineering Corp. Service Bulletin No. 669-26-02"
accomplished (dste)
Page i al 2 ~Y
F
-C~1. II. *s~u(11´• uL h´• 1.11 D*
SERVICE BUL LETIN
I M ODEL: 669_ ID nNo 669-if SINGLE PILOT SE ATS
NG: 6 6 9 -2 5 02 DATE Nov 16. Is a I
SUAJECT´• F -OOR TRACK FITTING AND
R OL L E R RE PL ACE MENT OF
r ORBG1S~IL 1As R@csived By
I. ATP i
669-25-02
PAGE I CF 4
FLIGHT EOUIPMENT
SERVICE BULLETIN1. planning Information
Elfec ti~i ty
The follo*ing 669-10 and 669-1B pilot seat assembliesare affected by this ser~ice bulletin modification,
nodel No. De a crip tion A ffe o ted se rial No
669-101 pilot Seat 22 576 thru 22589669-1DR Co-P ilot Seat 22609 thru 22622, 2353266P-1R. Pilot Salt 23372 thru 23380669-1FR Co-P ilo t Sea t 23L37 thru 23443
B. Reason
To eliminate interference betueen the bottom surface of.the seat base frame and the top surface of the aircraftfloor track.
C. Description
l~ha existing seat track iittlngs and rollers ire to De
replaced vith ~itting. and rollers that vill prc~idemore distance betueen the base frame and floor trick.4he nex fittines hr~s a thinner lip engaging the trackand the rollers are of a larger diameter.
D. Compliance
It is recommended that the vork outlined herein beaccomplished Pt the first opportunity Pinilpble.
E. blpro~P1
The only appro*al required and obtained, is the minimumPllovn~lt thickness of the seat track fitting 1ip tocomply vith required loads. Stress annlysis vas performedand Ppp~Cled by F´•l´•*´• D´•E´•R´•
F. nanpower
It is estimated that the time required to perform thismodification is 20 minutes per seat unit.
0. nnteriil
the sent trnck fittlnes and rollers vill be pro~ided byplight Equipment upon request at no charge.
F~il-llhL 1sa~. 16 19a1 As i-i~:ujvod By 669-25-02
L ATP i2
FLIGHT EOUIPMENT
SERVICE BULLETIN
Deli~cry dates after request far parts will be ppprox~-
mately three to Four weeks.
H. Tocline
No special tooling required.
I. Weight and balance
The affect to weight and balance is negligible,
2. A ccomplishmen4lnstru4´• tiona
A. It is recommended that the following modification be
accomplished during routine maintenance functions.
The sent unit is to be remored from the aircraft and
relocated at an appropriate work area.
Refer to Figure 1 for modification coordination,
i. the eristlnp track fittines, railers and
roller spacers by undoing the appropriate nuts
and withdrawing the sight cla~is bolts holdingthem tF the base Frame. Retain the steel spacers,
bolts, nuts and washers for reuse. Dispostion of
remo~ed fittinRs and rollers per section 3.1.
2. Install the new fittinps nnd rollers to the base
frame with the obo´•e retained spacers and hardware.
For identification purposes, the new fittinga hn~e
a lip thickness or .105/.110 inches and the new
rollers a diameter of .720/.?25 inches.
3. The assemblied sept unit should be checked in the
aircraft seat track to ensure smooth operation.With weight on the seat bottom cushion, loosen the
nuts holding the track fittinas slightly and re-
tighten firmly while the weight on the seat bottom
is mnintnincd.
3´• np terial Informati on
A. part Number Puan ti ty Das crirtion
312 L5 Pi ttin g- Tr ack
33L25 16 iloller- Track
As hec;jved ByNo~. 16 1911 ATP j 669-2 5-02
page 3ciz
FLIGHT EaUIPMENT
SERVICE BULLETIN
i. Disposition of Rernored Oprts
~11 rero´•e~ originrl rollers end flttings ´•ra to ~s
returned to Flieht E~ui´•.ent k Cnpinscring Core.
3915 I.U. PLth. Street, Hi´•mi, Flcride 331L2.
fi I;
ease FR~ncr
r BOLT
iROLLER LI~ND
THlc~
plLOT 5noWN
FIGURE I
1As Received By
Nn~. 1E 19EI ATP i 669-2 5-~2P´•ge L
Service Information CulFstreamAmericancoRpon*Tlonf 0ommae6n DlrWm
500( Nonh Auenus,_ Bamanv. O*l´•hama 73MS
SERVICE INFORMATION NO. SI´•~18
1 February 1982
PESTICIDE FUEL ADDITIVE
MODELS AFFBOTED: NODEL8 BgO. 890A, BBOB, BBOC, g96 AND 698A, W SERIAL IWMBERS.
REASON FOR PVBLICPITION: TO ALLOW THE ZiSE OF BIOBOR JP B~OCIDFI AS A FUEL ADDITIVE.
OOMPUANCE: AT OWNERS DISCRETION.
APPROVAL: FAA DOA 9W-2 APPROVED.
ESTIMPlleD MAN HOURS: NOTAPPLICABLE.
PARTS DATA: NOT APPLICABLE.
SPECIALTOOLS: NONE.
1. BIOBOR JF Biocide (Sehio or equivalent) 270 ppm maximum (2(1 ppm of elemental beron) may be added to the fuelfarpeaticidepurpoesa.
NOTE
me BrOBOR W must be premixed in La fuel prior a Rllingthe airplane Rtel tanks.
ELBCTR(CAL LOAD: NO CHANCE.
WEIGHT AND SALANCE: NO CHAN(IE.
SPARES AFFECTED: NO
PUBLICATIONS AFPEO7ED: The Pilot Operating Handbook, Airplane Flight Manual and Airplane MaintenanceManual Changes required by this document will be inaorporated at their next scheduled revision.
RICORDCOMPLIP~NCE: NOTAPPLICABLE.
Pagelell
Service Information CulfstreamAmericanconpon*TI~,N
Camnandsr Dlrllian
5001 North RocL~all Avanus.
Bsm´•ny´• O~lahorm l~ms
SERVICE INFORMATION NO. SI-1BOA
(8upersedes ServiFe Information No. 81-180, dated a February 1882, in is entirety)17 June 1882
PARKER nANNIFIN CORPORATION PRODUCT REFERENCE
MEMO (PRM) NO. 25 (RevlslOn A)
MODELS AFFECTEO: FACTORY APPROVED:
MODEL 8g0A, SERIAL NOS. 11186 THRU 11344.
MODEL 68011, SERIAL NO9. 11550 THRU 11566.
MODEL 680C, 8ERIAL NOS. 11600 THRU 11709.
MODEL 685, SERIAL NOS. 85000 THRU 88084.
MODEL 696A, SERIAL NOS. 86001 THRU 86023.
ST: APPROVED:MODELS 680, SERIAL NOS. 11001 THRU 11079.
MODEL 680A. SERIAL NOS. 11100 THRU 11184.
NOTE
ALTHOIIOH THE MODEL 680A AND 680B ARE N(YI~
LLSTED ON PARKER HANNIFIN CORPORATION PRM
NO. 25 (REVISION A), 1T 18 RECOMMENDED THAT THE
REWORK BE ACCOMPLLFIHED ON THE MODEL 680A
AND 68(111.
THIS SERVICE INFORMATION APPLIES TO
CLEVELAND BRAKE ASSEMBLY P/N 50-107 WITH
MANUFACTURERS DATE PRIOR TO DECEMBER 1881.
IF BASIC 8ERVICE INFORMATION NO. 9I´•180, DATED 3
FEBRUARY 1882, HAS NOT BEEN ACCOMPLISHED,ONLY PART I OF THIS SERVICE INFORMATION
8HOULD BE ACCOMPLISHED. IF BASIC 8ERVICE
INFORMATION NO. 81-180, DATED 5 FEBRUARY 1982,HAS BEEN ACCOMPLISHED. ONLY PART II OF THIS
8ERVICE INFORMATION SHOULD BE ACCOMPLISHED.
REISON FOR PUILICATION: TO RECOMMEND COMPLIANCE WITH PARKER HANNIFIN CORPORATIONI
PRODUCT REFERENCE MEMO (PRM) NO. 26 (REVIION A).
COMPLIANCE: AT OWNERS DISCRETION.
NOTE
1F ANY PROBLEMS ARE ENCOUNTERED WHILE
COMPLYWG WITH THIS 9ERVICE INFORMATION,CONTACT YOUR NEAREST CIULFSTREAM
COMMANDER AUTHORIZED SERVICE~ER.
BY WHOM WORK WILL BE *CCOMPLISHEO: A P MECHANIC OR IZ~UIVALENT.
APPROVIL: NOTAPPL1CABLE. I
HOURS: PART I-TWO(2) HOURS
PART II-TWO(2)HOURS I
Psee 1 ols
IERVICL WFORMATION NO. BI-1BOA
EX)STIN(I DISC
S~RINOI(REF1
TOROUE EXISTIN(I
STUD 10 TO ED IN´•LBS
TORDUE EXISIINO11ODtSOOSTUDI\SSY
INTO PISTON ASSY00 10 70 IN-LBS
PISTON PISW
IREFL
EXISTIN~ BR*I(EP~SSY IREFI
Figa i.
Page Z ol 9
BERVICE INFORMATION NO. SI-1BOA
PARTS DATA: PARTS REQUIRED TO COMPLY WITH PART I OF THIS SERVICE INFORMATION MAY BE
PROCURED THROUGH YOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR
888.21. REFERENCE THIS SERVICE INFORMATION, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER
WHEN ORDERING SERVICE INFORMATION NO, SI-18oA KIT CONSISTING OF THE FOLLOWING:
R*´•ulcalol;Nnpanoutnlla~.
qTY PART NO. DESCRIPTION
4 se. 068-03500 Insulator Shim
6 ee. 08616800 Dise Spring1 ea. PRM NO. 25 (Revision A) Instructions I1 ea. Compliance Card
1 as. Service Information Na. SI- 1BOA Instruction, I
SPECIALTOOLS: NONE.
ACCCOMLUSHMINT INSTRUCTIONS:
PARTI
1. Comply with Parker Hannifin Corporation Product Referense Memo No. 25, Rsvieion A. I
2. After rework has been accomplished identify brake aasemblies bystamping the date of rework (month and year)
with permanent ink.
3. Fill out and mail Compliance Card specifying that Pert I has been accomplished
PART II
C~UTION
Care must be taken and eye protection gear worn during this
reworkto avoid injury since we are dealing with disassemblyof a preloaded spring stack.
1. Apply a slight amount of pressure to the brake system and set parking brake. This will prevent piston rotation.
2. Loosen and slowly remove the stud assembly (Pi~ 110´•04900) from each piston (refer to Figure 1).
3. Slide existing fourteen (14) disc springs from each stud assembly. Placestud assembly in a vise and cheek
torque of ANIHSA bolt in stud assembly to assure that bolt has not loosened. If bolt has loosened, retorque bolt
in stud assembly 80 to 80 inch-pounds,
4. Slide dise springs back onto stud assembly and reattach stud assembly and springs to each piston. Torque stud
assemblies BO to 70 inch-pounds (refer to Figure 1).
5. Actuats brakes 2 to B times and visually inspect each assembly to assure that everything appears normal and
is seated properly.
6. Fill out and mail Compliance Card specifying that Part II has been accomplished
ELECTRICAL LOAD: NO CHANCE.
WEI(IHT FIND BALANCE: NO CHANGE.
SPARES AFFECTED: NO.
PUBLICPITIONS AFFECTED: The Illustrated Parts Catalog change required by this daeument will be incorporated at
the next scheduled revision.
No, SI-1BOA, dated 1? June 1882, entitled "Park HanniT~n Corporation Product Reference Memo (PRMI No.~"IRECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service
A), Part I accomplished (date) Part II accomplished (date)
Page 9 ol 3
O)(o
Revision A 5/5/82
21. 1981
Page 1
SUBJECT: 30-107 BRAKE ASSEMBLY
INSTALLATION OF TWO (2) ADDITIONAL 068-03300
INSULATOR SHIMS AND FOUR (4) ADDITIONAL
095-16800 DISC SPRINGS PER BRAKE ASSEMBLY
AIRCRAFT
EFFECTIVITY: ROCKWELL INTERNATIONAL AND GULFSTREAM AMERICAN
690, 695, 840, 900, 980, 1000 SERIES AIRCRAFT
UTILIZING CLEVELAND WHEELS BRAKES ASSEMBLY
NO.’S 40-107/30-107
SCOPE: PRODUCT IMPROVEMENT TO THE 30-107 BRAKE ASSEMBLY
TO ELIMINATE LOW SPEED BRAKE CHATTER REPORTED BY
SOME OPERATORS IN THE FIELD
Product Improvement Sequence: (For reference, see sketch)
r. dt the next regularly scheduled maintenance period, performthe following:
A. Shim Installation (068-03300)
i. Block main wheel tires to prevent aircraft move-
ment and release parking brake
2. Loosen the twelve (12) 103-14500 bolts and remove
the four (4) 074-03900 back plate assemblies from
each brake assembly
3. Install one (1) additional 068-03300 insulator shim
on each brake cylinder
4. Reinstall 074-03900 back plate assemblies, tighten103-14500 bolts and torque to 85-90 in-lbs.
Parker Hannlfln CorpwatlonIlroraH Wheel end Brake Dlvlslon
P.O. Box 158. Avon, Ohio 44011 VSA
(215) 8345221
~Aerospace
d ponslsle
O)(o
Revision A 5/5/82
SpeRp:~pe;521, 1981
Page 2
SUBJECT: 30-107 BRAKE ASSEMBLY
INSTALLATION OF TWO (2) ADDITIONAL 068-03300INSULATOR SHIMS AND FOUR (4) ADDITIONAL
095-16800 DISC SPRINGS PER BRAKE ASSEMBLY
B. Disc Spring Installation (095-16800)
i. Caution must be taken and eye protection worn
during this phase to avoid injury since we are
dealing with disassembly of a preloaded springstack.
2. Apply a slight amount of pressure to the brake
system and set parking brake. This will preventpiston rotation.
´•vision~ 3. Loosen and slowly remove the stud assembly (110-04900)from each piston. Slide the existing thirteen (13)disc springs from each stud assembly. At this point,check to see if the AN4H-5A bolt in the stud assemblyhas loosened. If so, retighten the bolt into theguide stud at 80-90 in-lbs.
4. Slide the disc springs back onto the stud assembly,installing the one (1) additional spring in thelocation and position shown in the sketch.
O 5. Reattach the stud assembly and springs to each pistonas shown in the sketch. Torque the stud assembly at60-70 in-lbs.
6.´• Actuate brakes 2-3 times and visually inspect each
assembly to insure that everything appears normal
and seated properly,
Make a log book entry referene7. vi end
return aircraft to service.Alrcralt Wheel and Brake Dlvis(onP.O. Box 158. Avon, Ohio 44011 USA
(218) 9346221
5 pDl,sl´•a7s
Revision A 5/5/82
September 21. 1981
PRM No. 25
Page 3
Loosen 103-14500 bolts
per Pare I.A.2
Tighten and torque per install additional
Pare I.A.4 068-0~300 insulator
shim per Para ~.A.3
Existing 095-16800
disc spring stack
13 each typ. 4 p
per brake assenbly
110-04900
Scud AesamblyTighten perPare l.B. 5
5A bolt
095-15900’ 11flat washer
Parker HanniBn CorporationInstall per pare 1.8.4 st top of
Aircratl Wheel and Brake Divisionstack and positioned as shown (typ) P.O. Box 158, Avon. Ohio 44011 VSA4 pieces per brake assembly (216) B34´•5221
L P0118~´•6)P
Service Infoumationeammsnda Divilim6(101 North Rochwall Auanua.Bamany´• Otlahoma 75008
SERVICE INFORMATION NO SI-182
1 June 1982
DOWTY ROTOL SERVICE BULLETIN NO. 61-950ALTERNATE GREASE (TEXACO LOW TEMP EP GREASE) FOR DOWTY ROTOL PROPS
MODELS AFFECTED: MODELS 680C. 6B0D. 895 AND bSA.
NOTE
CHECK PROPELLER LOG BOOK FOR ENTRY OFMODIFICATION NO. (c) VP. 2989. IF THISMODIFICATION NUMBER HAS BEEN ENTERED INYOUR LOO BOOK. YOUR PROPELLERS HAVE BEENSERVICED WITH TEXACO LOW TEMP EP GREASE.
REASON FOR PUBLICATION: TO RECOMMEND COMPLIANCE WITH DOWTY ROTOL SERVICE BULLETINNO. 61-950.
COMPLIANCE: REFER TO DOWTY ROTOL SERVICE BULLETIN NO. 81-950.
BY WHOM WORK WILL BE ACCOMPLISHED: A DOWTY ROTOL APPROVED PROPELLER SERVICE SHOP.
APPROVAL: REFER TO DOWTY ROTOL SERVICE BULLETIN NO. 61-950.
ESTIMATED MAN HOURS: NOT APPLICABLE.
PARTS DATA: REFER TO DOWTY ROTOL SERVICE BULLETIN NO. 61-9W.
SPECIALTOOLS: NONE.
~ZCCOMPLISHMEM INSTRUCIIONS:
1. Refer to Dawhr Rotol Service Bulletin No. 61-960.
ELECTRICAL LOAD: NO CHANGE.
WEIGHT FIND BIIPINCE: NO CHANGE.
SPARES AFFECTED: NO.
PUBLICATIONS APPECTED: The Airplane Maintenance Manual changes required by this document will beincorporated at the next Kheduled revision.
RECORD COMPLIANCE: Refer to Dowty Rotol Service Bulletin No. 61-950.
Page 1 of 1
I%QWBYI
SERVI%E BULLETIH
PBOPBLLE8S 8LADE ORO~ IATROWCT~ON O8 TEXACO U)U Te~tP BP DRPISBAS Al.TERAATIVE TLI AEROSBELt 7
noorPxcnTroN ~D L~C)IP ´•2983
i. PI~NlllffD
Aircraft (f)Propaller
Duliaerca~ A´•sricao Co~msndcr R306/3-82-P/76900, Soon, 695, 6951\
g. Reason
(1) A requear has been made for pniisaia. to use an alternative
grease.
C. Description
(1) This modiricarion introduces Telsco lor Te~p BP grease as an
alrernntive to Aaroshell 7 for usa in Lha propellers listedin Para.l.A.
Mote Both greases are to specification DTD)598 (WIL-C-23827A)bur ire not ra be intemiled in use.
D.
(1) Bacolrended.
I. Apprc~al
(1) This bulletin is appro~ed under authoritJ of CM Appro~´•lao.nar/~ms/,s.
I. ELan Pover
C. Ilslcrill
Act: applicabls8. Tooling
I. Ueight and balance
Occober 6181 61-950March 9/82 (Revisicn 1) Page 1 of Z
L2.
IDQPl~iYI
SERYICE BULLETIW
J. aefereaces
(1) Coaunder 6900, 6900, 895, 699A Op~srhaul ~Lsnual 61-10-16.
r. Other Publications Affected
(1) None.
2´• IISTB~CPIONS
A. B´•bodlnaor instructions
(1) Vhcn servicing the prapalloF´•, Texaco Low Temp 00 greese IlaTbe used as an alrsroari~e to 7 where specified in
the rcla´•ranr overhaulmanual.
Note These greases lust not be intermixed in use.
B. Werhod of identification
(1) Record nod.No.(c)VP.2983 in the propeller log boob.
2. EU~TBI(UL
A´• ~oas.
61-990 October 6/81 i
Rage 2 (Ra~ision 1) ni~tch 9/82
Senrice fnformation CulfstreamAmericancc~npon*rloNCMmmdsrDivYaSM1 slam RartuFII Annu´•.
BaNny. Oll´•Don~ 13008
SERVICE INFORMATION NO. SI-1BS
9 July 1882
IMPROVED AILERON SERVO AUTHOR17Y KFC 300 AUTOPILOT
MODELS AFpEOTBD: THE FOLLOWING EQUIPPED WITH KFC 300 AUTOPILOT:MODEL 69(ID, SERIAL Nh9. 111001 THRU 11004, 18006 THRU 16012.
MODEL 696A, SERIAL N~. 88001 THRU 98039.
REIS80NFORUBLCATTON: TO MAKE AVAILASLE AN IMPROVEMENT TO KFC 300 AUTOPILOT
INSTALLATION.
COMPLI~NCE: AT OWNER’S DISCRETION.
mlTe
a ANY PROBLEMS ARE WHILE
COMPLYING WITH THIS SERVICE INFORMATION,CONTACT YOUR NEAREST GULFSTREAM
COMMANDER AUTHORIZED SERVICENTER.
BY WHOM WORK WILL BE ICCOMPUSnED: KING RADIO CORPORATION AUTHORIZED SERVICE AGENCYOFCATEGORYVB.
APPROVAL: FAA DOW Sw-a APPROVED.
EST1MATED MW HOURS: FOUR (41 HOURS
PARTS DATA: AILERON SERVO P~ 066-0024-11 MAY BE PROCURED THROUGH YOUR NEAREST
AUTHORIZED KING RADIO CORPORATION DISTRIBUTOR OR SERVICE AGENCY. THE EXISTING AILERON
PFBVO PIN 066-0024-06 MAY BE MODIFIED TO A 0660024-11SEXVO BY KING RADIO CORPORATION.
9PECI*LTOOLO: NONE.
I\CCOMPUSHMENT1NSTRUmONS:
1. Gain access to ailsron servo, located just Eomard and above baggage Eompartment at fuselage station 223.98.through baggage compartmsnt doer.
2. Remove upperloruanl bsggage mmpartment liner to expose ailemn servo.
3. Disconnect electrical connector (irm an side oldlsmn servo.
a. Remove bolts that attach silemn servo and remove servo P/N (186-002408 (see Parts Data above).
6. Remove screws that altach cap to slip clutch and remove cap. Slip clutrh is located forward of silsmn servo
~splinedendofservo).
Page 1 of2
SERVICE INFORMATION NO. SI-lsS
6. Chanse slip setting 80(+ 10) inohpounda M 10) fReinstall cap on slip clutch using existing hardwsre.
g~ Instalt 0850024-11 aileron servo using existing hardware.
8. Remove wire Rom pin "C" on alleron servo c.nnaftori cap wire and ceil and stow wire.
10. Rsoonnect electrical connecter to new ailsmn servo.
11. Assure that Supplement No. 28 (Model 680D) or Supplement No. 32 (Model BgSA) is in the Pilot Operating
Handbook.
12. Check operation of new silemn servo as outlined in Normal Precednres of Pilot Operating Handbook
Supplement No. 28 (Model 680D) or SupplementNo. 82 ~Model 886A).
13. Reinstall baggage cempartment liner.
14. Fill out and mail Compliance Card.
ELECTRIC*L LO*D: NO CHANGE.
Wel(lHT ANO 8*LI\NCB: NO CHANGE.
SPARES AFFECTIO: NO.
PUBLICI\TIONS I\*FECTEO: The Illustrsted Parts Catalog change ra~uired by this document will be incorporated at
We next ssheduled revision.
RECOR~ COIPLIANCE: Malts an appropriate entry in airplane maintenance records as follows: Service Morrnation
No. SI-183, dated g July 1882, entitled *Improvsd Ailema Servo Authority KFC 800 Autapila, accomplished 3(date)
i
Page 2 of 2
Service InformationCulfstreamAerospace
SERVICE INFORMATION NO. 81-18110 Decembsr 1882
INSTALLATION AND/OR MAINTENANCE OF ABRASIONRESISTANT TAPE ON DOWTY-ROTOL PROPELLERS
MODELS AFFECTED: 690C, SERIAL NOS. 11BM) THRU 11121 AND 11129 THRU 11?2?.MODEL 990D, SERIAL NO8. 15001 THRU 16018.MODEL 686, SERIAL NOS. 86000 THI(U 86084.MODEL B9SA, SERIAL NOS. 86001 THRU B60l9.
REASON FOR PUBLICPITION: TO REMIND OPERATORS OF IMPORTANCE OP PROPERLY INBTALLINO ANDMAINTAININ(I THE ABRASION RESISTANT TAPE ON DOWTY-ROTOLPROPELLERS
COMPLIANCE: NOTAPPLICABLE.
BY WHOM WORK WILL BE ACCOMPLISHED: NOT APPLICABLE.
APPROVAL: NOT APPLICABLE.
ESTIMATED MAN HOURS: NOT APPLICABLE.
PARTS DATA: NOT APPLICABLE
SPECIAL TOOLS: NOTAPPLICABLE.
P~CCOMPLISHMENT INSTRUCTIONS:
Phis Service information is being issued to point out that abrasion resistant Ups was installed an the propeller blades
u, improve nbrasion resistance end ice shedding capabilities of Dowty-Rotol propeller. With the onset of winter, the
condition Jf this abrasion resistant taps should be closely monitored.
Service Bulletin Na. 189, entitled "Applicatian of Abrasion Resistant Tap on Dowty-Rot~ Propeller", was issued againstModel 690C. Serial Numbers 11600 thru 11118, Model 696, Serial Numbers 86000 Unu 86094 and Model 6861\, Serial
Numbers 96001 Lhru 96024- Operators of these aircraft should assure total compliance with Service Bulletin No. 188.
The operators of other affected PircraR should assure that the abrasion resistant taps is maintained per AirplaneMeintenanu, Manual Instructions
ELECTRIC*L LOAD: NOTAPPLICABLE.
WEICIHT AND BALANCE: NOT APPLICABLE.
SPARES AFFECTED: NOT APPLICABLE.
PUBLICATIONS AFFECTED: NOT APPLICABLE.
RECORD COMPLIAINCE: N(Y~ APPLICABLE.
Page 1
Service inf~rmatisnC~IIGulfsrreamAerospace
SERVICE INFORMATION NO. Sl-1898
(Supersedes Service Information No. SI-189A in its entiretyi24 February 1984
APPROVAL AND INSTALLATION OF TPE 331-10-511K ENGINES
MODELS AFFECTED: MODEL 695, SERIAL NOS. 95000 THRU 95084.sMODEL B95A, SERIAL NOS. 98001 THRU 96069.
NOTE
IT IS RECOMMENDED THAT SERVICE INFORMATIONNO. 81-193, ENTITLED "OIL VENT HOSE ASSEMBLY
REPLACEMENT", BE ACCOMPLISHED AT THIS TIME
(IFAPPLICABLE).
REI\GON FOR PUBLIC*TION: TO AUTHORIZE INSTALLATION OF TPE 331-10-6111 ENGINES AND PROVIDE
ELECTRICAL WIRING CHANGE REQUIRED WHEN INSTALLIND ENGINES.
COMPLUNCE: OWNER/OPERATOR OPTION. REFER TO GARRETT TURBINE ENGINE COMPANY SERVICE
BULLETIN TPE 331-72-0398
C No~a
IT IS ACCEPTABLE TO OPERATE AIRPLANE WITH A
TPE 951-10-501K ENGINE ON ONE SIDE AND A TPE
331-10-511K ENGINE ON THE OTHER SIDE.
IF ANY PROBLEMS ARE ENCOUNTERED WHILECOMPLYING WITH THIS SERVICE INFORMATION,CONTACT YOUR NEAREST GULFSTREAMCOMMANDER AUTHORIZED SERVICENTER.
BY WHOM WORK WILL BE I\CCOMPLISHED: A L P MECHANIC OR EQUIVALENT. 8EE OARRE’IT TURBINE
ENGINE COMPANY SERVICE BULLETIN TPE 981´•72-0398.
APPROVAL: ENGINEERING DESIDN ASPECTS ARE FAA APPROVED.
ESTIMATEDM~HOURS: TWO (2) HOURS TO ACCOMPLISH THE MODIFICATION DESCRIBED IN STEPS 3
THROUGH 11 BELOW. SEE OARRET~ TURBINE ENGINE COMPANY SERVICE
BULLETIN TPE 331´•72´•0598 BOR ADDITIONAL INFORMATION
PARTS DATA: NO PARTS ARE REQUIRED TO COMPLY WITH STEPS S THROUGH 11 BELOW. INFORMATION
REGARDING PRICE AND AVAILABILITY OF PARTS PERTAINING TO THE ENGINE ITSELF MAY BE OBTAINEDFROM A CARRETT APPROVED SERVICE CENTER. INCLUDED WITH THIS SERVICE INFORMATION IS
ONE (li COMPLIANCE CARD.
SPECIALTOOLS: ENGINE LIFTING TOOL AND HOIST. SEE GARRETT TURBINE ENGINE COMPANY SERVICEBULLETIN TPE331-12-0398 FOR ADDITIONAL TOOLING REPUIREMENTS.
ACCOMPLISHMENT INSTRUCTIONS:
1. Remove elisting TPE 331-10-5018 sngine(s) and install TPE 331-10511K engine(s) as outlined in Chapter 71
of the Airplane Maintenanee Manual.
Page lofS
8ERYICE 1888
~-240-9 A2I3
7‘0---""e-215-in
AI
p~-´•i
~ISCONNECT WIRE NO. 233 FROMKS3-l\l I\ND RECONNECT WIRE I DISCONNECT WIRE NO. 238 FROMTO KS-AI AND RECONNECTWIRE
TO KB´•l\l
A3
1~-235
Al
LEFT ENGINE RIGHT ENGINE
*o´•rl
CASHED LINE INDICATES ORIGINAL I´•M1K ENGINE)
CONNECTION OF WIRE hlOS. 233*ND 238.
Filura i.
Page 2 of S
SERVICE MFORMATION NO. 189B
z M~tll ilunp pert oumi~ 81066360L a4~nl m Ula *md´• *&Ro P*RI‘ on the nov an.ins RaTsrto step (16) page 20 of Garrett Turbine Engine Company 8ervice~Bulletin TPE 331-72-0398
3. Gain secess to power distribution panel through baggage compartment door. The power distribution panel is
locatedjust aft of the baggage compartment door.
i. Remove baggage compartment liner, as necessary, to snpose power distribution panel.
5. Remove or lower power distribution panel cover.
NOTE
On Model 695A, serial numbers 96066 thru 96069, the cover IIon the power distribution panel is hinged to the panel and
may be lowered. The relays to be rewired on these airplanesare mounted on the cover.
If the TPE IS1-lO-SolK engine is not replaced by a TPE
331-l0-511K engine, do not rewire the relay for the side
that still has the -SO1K engine.
B. For the left engine, disconnect wire No. 259 from Al of KSS relay and reeonnect wire to Al of KS relay (referto Figure i).
7. For the right engine, disconnect wire No. 236 ham Al of KS4 relay and remnnect wire to Al of K6 relay (referto Figure i).
8. Reinstall or close the power distribution panel cover.
9. Reinstall baggage compartment liner.
10. Assure that revision No. 7 (Model 696) or revision No. 10 (Madel 695A) has been inserted in the Pilot’s OperatingHandbook.
11 Fill out and mail compliance card specifying if ons or bath engines have been converted to -611K. Record total
airframe and engine hours, slang with engine serial numbers on compliance card.
ELECTRICAL LOAD: NO CHANGE.
WEIGHT ~ND SALANCE: NO CHANGE.
SPARES ~FFECTED: THE TPE S31-10-611K ENGINE 18 THE SPARES REPLACEMENT FOR THE TPE 331-10-
60iK ENGINE. THE TPE 331´•10-601K ENGINE WILL NO LONGER BE AVAILABLE.
PUBL1CATIONS I\FFECTED: The Model 695 and 696A Pilot Operating Hendbw~ revision has already been furnishedand Airplane Maintenance Manual and Illustrated Parts Catalog changes required will be
incorporated at the nent scheduled revision.
RECORD COMPLI*NCE: Make an appropriate entry in airplane maintenance records as follows: Service InformationNo. S1´•1898, dated 24 February 1984, entitled "Approval and Installation of TPE331-10-511K Eogines~’. accomplished
(date)
Page S of S
Ikw~llSerwice information Gulfstream
Aerospace
SERVICE INFORMATION NO. 81-181
21 May 1883
TERMINATION OF FACTORY FINANCIAL PARTICIPATION ON PARTS
AND/OR LABOR ALLOWANCES ON CERTAIN SERVICE PUBLICATIONS.
MODELS AFFECTED: MODELS 500, S00A, 5008, 520, 580, S80A, 1601, 580P, 880, B80E, 680F,688(F), 880FL, BLIOFL[P), 880T, 680V, 680W AND ?20, SERUALNOS. 1 TBRU
1854.
MODEL 681, SERIAL NOS. 8001 THRU 8012.
MODEL 885, SERIAL NaS. 12001 THRU 12068.
MODELS 680, 6B0A AND 680B, SERIAL NOi. 11001 THRU 11558.
MODEL 880C, SEIdAL NOS. 11880 THRU 11815 AND 11108.
MODEL 680D, SERIAL NOS. 15001 THRU 15006.
MODEL 885, SERIAL NOS. 85000 THRU 85084.
MODEL 885A, SERIALNOS. 86001 THRU 86052.
MODEL ?00, SERIAL NOS. 10001 THRU ?0828.
REASON FOR PUBLICATION: TD ESTABLISH A TERMWATION DATE FOR FACTORY FINANCIAL
PARTICIPATION.
*9 os la~ n7. IlsJ. TAB sOLLaVn*C BER~CB POBLIOLTI(WB WIU PROYID. B*CTC~P
PARTICIPATION ONLY UNDER THE FOLLOWING CONDITIONS:
(3 IF COMPLIANCE IS ACCOMPLISHED WITHIN ONE (1) YEAR FROM THE DATE OF ISSUANCE,AS STATED ON EACH SERVICE PUBLICATION, OR,
(b) IF THE AfRCRAFT 1S COVERED BY OULWTREAM WARRANTY APPLICABLE FOR EACH
SERVICE PUBLICATION.
WOTE
THE PART PRICES 4UOTED ON THESE SERVICE PUBLICATIONS ARE SUBJECT
TO CHANGE WITHOUT PRIOR NOTICE IT IS RECOMMENDED THhT CURRENT
PRICING BE OBTAINED AT TIME OF ORDER PLACEMENT.
SERVICE BULLETINS
ISSUE
NO. TITLE DATE
25 Improved Catauretor Air Straightener 8-5-54
Suppl. 141 Replacement of Aileron Bellerank Castings at W~ Stations 188 5-a4-5751 MadWoation Flight Instrument Btatie System Piping 2-18-5852 Installation of Close Fitting Carburetor Air Box Shaft and Mmaball Rod Ends 2-15-6855 Replacement of Propeller Blade Split Rings 2-18-5851 Horizontal Stabilizer Modlflcatlon 3-11-5858 InsuMlon of the Hydraulle and Engine Oil Shutoil Valve CLreult Breaker 1-8-596(1 Corrosion Inspeetton Rudder Torque Tube 8-21-5881 Carburetor Air Bon Repair 8-21-58
70 Installation oi Improved Condenser in Bendin 280 Series and 800 Series Magnetos a-8-81
88 Replaeement of Main LandingGear Uploclt Cheek Vsilve 8-22-80
PagelofS
SERVICE INFORMATION NO. SI-lsl
BULLETINS ~CONTU)
NO. TITLE DATE
?1 installation of Fuel InJector Pump Ice Shield 2-13-8175A Replacement of Main Landing Gear Uplock Check Valve Assembly 12-1-8176A Replacement of Engine Induction Alternate Air Butterfly Valves and Mounting Shafts 2-5-6278 installation of Fuel Drain Lines for Engine Cage Units 5-16-6283A Main Landing Osar Piston Upper Bearing Look Pin Replacement 6-25-8589 Cable Retainer ALleron Cable Drum 10-21-8491 inspection and Possible Replacement of 4630068 Magnesium Fuel Sump Casting 4-28-6193 Replacement of Pilot and Copilot Windshields 11-11-6796 Inspection of DC Bus and Contactor Box Wiring 2-20-68105 Replacement of Emergency Door Release PLaea~d 5-2-11118 Sealing Engine Control Cables 2-25-73119 Engine Oil Pressure Rose Support 5-8-75120 De-leer Decal Installation 3-8-13121 Woodward Governor Modi~ioailon 3-16-73122 Thermostat Protection for Anti-Ice Heaters 3-27-1512SA Replacement of Unfeathering Pump Supply Line B-B-73134 Engine and Engine Installation Hardware Improvements 4-23-73191 Installation of Cabin M Pressure Light System 11-21-’15133 Engine Baffles 2-4-14
134 Replacement of Bleed Air Check Valves 2-6-1413?A Engine Gage Replacement 6-8-75139A (b~ygen Mask and Storage Provisions 7-21-75143 Replacement of Openable Pilot and Copilot Side Windows 8-10-14144 Yerticail Stabilizer Trailing Edge Modllication 10-4-14141 Bleed Air System 11-21-7(151 Replacement of Fuel Sump 4-11-15154 Hydraulic Pressure Line Replacement 5-21-15
11I InatULUion ai SE* ud BlmC´•l PlsOlld´• C158 Failure of Flap Control Bracket 8-27-15157A Flap Control Bracket Modification 5-29-19LSB Trim Annunciator Lamp Cap Replacement 10-9-15
162 Reduction in Electric Elevator Trim Speed 10-21-16
183 inspect and/Or Replace Wing Spar Cap Rivets 1-21-11
188 Copilot Airspeed Limitation Placard Installation 5-5-78
L?1 Unfeatherng Pump Supply Hose Replacement 4-8-80
175 Oil Filter Adapter Replacement and Engine Mount Retainer Modification 1-21-80178A Ailemn Access Door Inspection and Replacement 2-1-81
183 Exhaust Pipe Seal Replacement 1-7-81
189 Application of Abrasion Resistant Tape to Dowty-Rotol Propeller 3-12-82
190A Exhaust Pipe inspection and Modification 8-22-82
191 Nose Landing Gear Centering Cam Replacement 1-29-82
193 Passenger Oxygen Dispenser Modification 10-28-827-2 Throttle Control Cable Inspection and/or Replacement (Model 700) 8-27-19
SERVICE LETTERS
ISSUE
NO. TITLE DATE
44 Nose Landing Gear Cylinder Assembly Spacer Installation 2-3-5653 Addition of Stiffener Clips to Lower Cowllngs and Aft Nacelles 10-1-56
80 Battery Relay Terminal insulation 8-22-5983 Recommended Change of Carburetor Air Box Control Arms 11-18-59
83 Installation of improved Generator Drive Pulley Retaining Nut 12-8-60
04 Installation of Correctly Calibrated Oil Dipstick and Improvement of Weight and
Balance Data 2-8-6195 Installation of improved Engine Exhaust System 3-1-61
98 installation of Fuel Flow Gage Pitot Vent 4-12-81
112 Replacement of Tee Fitting in Vacuum Line Aft of Fuselage Station 165. 88 10-21-81C104 Horizontal Stabilizer Modification 8-15-61
118 Inspection and Replacement of Engine Exhaust Stack Assemblies 12-11-61
11? Replacement of Vacuum Air-Oil Separator 12-11-81
171A Main Cabin Door Modification 1-14-68
PaSe2of3
SERYICE INFORMATION NO, SI-181
C ssRITs LBTTEA8 ICONm)ISSUE
NO. TITLE DATE
184 mst2llatlan of Improved Cabin Pressure Differential Switch 31-4-68
IsS Modification of EGT System Pitot Static Hose Installation 11-20-68
186 Main Landing Gear Uplack Arm Modification 11-22-BE
189 Propeller Attach Bolts 12-23-68
190 Installation of Improved Roller Bushing Main Landing Gear Door Latch Assembly 12-29-BE
Ist Engine Cowllng Chafing Strip 1-18-67
182 Deflector Installation Nose Landing Gear 1-is-81
189 Modification of Engine Tail Pipe Molmtlng 5-14-81
241 Negative Torque Sense System Test Light 5-26-72
248 Quadrant Face Plate 8-6-72
286 ALResearch Heated Pr and Py Pneumatic Lines 8-16-73
257 Wire and Fuse Size Change far Heated Engine Prime 12-14-72
258 Fuel Quantity Indicator Deca~ 1-2-73
ZBO Quadrant Face Plate 1-5-15
262 Fuel Vent Check Valve insti~llatlan 2-1-15
aa? Cabin Temperature Control 4-18-75
269 Increased Landing Gear Ektend Speed 1-17-73
211 Increased Landing Gear Entend Speed 8-24-73
272 Bob Weight Modification 11-14-15
215 Oil Cooler Flange Reinforcement Installation 12-13-73
a?? Replacement of Governor Reversa~ Linkage 4-23-74
500 Installation of OTSIO-52O-K Engines 1-21-15
SOS Fuel Flow Indicator Modification 1-22-75
S1OA lent Headrest Spring Retainer installation 10-28-16
S15 Improved Operation of Start Pressure Regulator 1-12-17
524 Replacement of Center Fuel Quantity Transmitter Gasket 1-18-79
SSO Wing Fuel Cell Support Installation a-25-80
JJS KIIIMmold Unit IECU) P´•ssiiu.e Su~lilb Rsoa~UbE.tlon or Blmesms* S-18-BO
334A Electric Start System Modification and Starter-Generator Ground Bus Bar Replacement 3-18-81
SSB Inter Turbine Temperature (ITT) Indicator Replacement 10-11-80
357 Engine Mount Bracket Modification 11-21-80
938A Aft Fuselage Thermostat Installation 3-13-81
339 Baggage Heater Annunciator Light Lens Replacement 1-15-81
540 Datsillptlan of Placard for Use of Alternate Engine 011 MIL-L-1808G 4-24-81
548 Replacement of limer Structural Cabin Window Glass 9-1-81
547 Replacement of inner Structural Cabin Window Glass 11-5-81SJ1 Parker Hpnniltn Corporation Product Reference Memo (PRM) No. 21 8-17-82
?-1 Annunciator Circuit Modification and Throttle Switch Wire Replacement (Model 700) 5-18-79
SERVICE INFORMATION LETTERSISSUE
NO. TITLE DATE
SI-128 Goodyear Service Bulletin No. Aero Commander 690A-32-1 3-16-76
SI-118 Flight Equipment and Engineering Corp. Service Bulletin Na. 668-25-02 1-15-82
SPECIAL PRICING PUBLICATION
SERVICE BULLETIN
ISSUE
NO. TITLE DATE
174C Reverse Power Limitation and Propeller Inspection, Harteell HC-BSTN-S(L/LT10282 ()()+4 5-20-80
NOTE
For Service Bulletin No. 174C, Factory Financial Participation will apply if the
parts are o~dered prior to June 30, 1989 and installed prior to August S1, 1983.
Page 3of3
c Service informationCulfstreamAerospace
SERVICE INFORMATION NO. 8I´•183
3 August 1989
OIL VENT HOSE ASSEMBLY REPLACEMENT
MODELS AFFECTED: MODEL69(L, 8&RUAL NOS. 11001 THRU 11019.MODEL 690A, SERIAL NOS. 11100 THRU 11344.MODEL 680B, SERIAL NOS. 11510 THRU 11566.
MODEL B9OC, SERIAL NOS. 11800 THRU 11664, 11686 THRU 11684 AND 11681 THRU11730.
MODEL 690D, SERIAL NOS. 15001 THRU 16021 AND 16025 THRU 16029.MODEL 695, SERIAL NOS. 95000 THRU 85082 AND 95084.MODEL B95A, SERIAL NOS. 95001 THRU 06056 AND 86088 THRU 96061, AND 96063.
REASON FOR PUBLICI\TION: TO. INSTALL LONGER VENT HOSE ASSEMBLIES TO PREVENT POSSIBLEENGINE OIL VENTINO OVERBOARD AT ENGINE SHUTDOWN.
COMPLIANCE: AT OWNERS DISCRETI~N.
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE00~6PLYMO ~TH THIB SIERYIOB
CONTACT YOUR NEAREST CULF8TREAMCOMMANDER AUTHORIZED SERVICENTER.
BY WHOM WORK WILL BE ACCOMPLISHED: A %i P MECHANIC OR EQUIVALENT.
APPROVAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED.
ESTIMATED MI\N HOURS: TWO (2) HOURS.
PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE INFORMATION MAY BE PROCUREDTHROUGH YOUR NEAREST OULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR 5314.14.REFERENCE THIS SERVICE INFORMATION, AIRCRAP~ MODEL AND FACTORY SERIAL NUMBER WHENORDERING SERVICE INFORMATION NO. 81-193 KIT CONSISTING OF THE FOLLOWING:
PAI(TNO. DESCRIPTION
2 ea. 5-0421B05-336 Hose Assy2 ea. AN960-10L Washer2 ea. MS21042L3 Nut2 as. MS21919H17 Clamp2 as. MSa1918H8 Clamp1 es. M821039-1-08 Screw1 ea. CamplianEe Card1 ea, srvioe Information No. 9I-1BS Instruetions
8PECIALTOOLS: NONE.
C *CWMPLISHLIEI~ INSTRUCTIOIIS:
1. Remove lower Eowling from left and right engines.
wee 1 or 4
SERVICE INFORMATION NO. SI-193
MODELS 690, 690A AND 6908cnurlo~
nSSURE TIIAT 91)921~109´•338 HOSE
A8SYOOESNOTCOMEINCONTACTWITH ENGINE AFTER IT HPIS BEEN MS21818H17 CLAMP
BECUREO WITH CLAMPS M821818H8CLI\MPMSZ1038´•1´•OB SCREWINBBO´•IDLW~sHER s´•0421H05-338
MS2((MZL3 NUT HOSE ASSY
~i
I ~wo>
i(_L!!
s a
c_
ATTACH ELBOW FITTING OIL TANK
MANIFOLD OAA1N ~SSYI IREF)MIVIIFOLD CRAIN
ASSY IREFI
VIEW LOO1(ING AT RIGHT SIDE of ENGINE (TYP)
Filura 1. Ihast 1 of 21
Page 2 oft
SERVICE INFORMATION NO. SI-1OS
MODELS 690C, 6900, 695 AND 695*
CAUTION
ASSURE THAT 80021H04´•338 HOSEnsSY WES NOT COME IN CONTACTWITH ENGINE AFTER II HA8 BEENSECUREPWITHCLP~MPS
EXISTINGMS2WBla88CReWAN911010LWA8HERM92(044N3NUT
Pis\ I ~M I ExlsnNa
MS?(BlsH12CLP~MP
Cii
EX~STIN(IMS21810nllCLAIP
r
TQOIL
OIL TANK(nEFI
80921H8IP18HOSE 1\89Y
M52l8(gH1ICLAMPM*NIFOLD DRAIN MSPIBIBHBCL*MP
Assv IREF) M92~(138´•1´•01SCREW~N880´•10LWnBHERM81101ZL3 NUT
VIEW LOOKING AT RIGHT SIDE OF ENGINE (TYP)
C
liica ~.(9lsst 2.1 21
Page 3 of 4
SERVICE INFORMATIOIV NO. SI´•193
Z Rrmo~ and Ixisnng oli rant hm that is routal tmm the oil tanX uanl i.rt to th. maniiold dFain Cassembly (refer to Figure 11.
NOTE
On Models 690C. 990D, 895 and 696A, retain eyistingclamps and hardware for reinstallation.
9. Install 8-04218(15´•336 hose assemblies on left and right engines and secure to engine using e.isting clamps and/or clamps furnished with this Service Information (reLr to Figure 1)
I CAUTION
To prevent heat damage to hose assemblies, assure thathose aaaemblies do not come in contact with engine sber
they are secured with clamps.
4. Reinstall lower cowling on left and right engines.
5. Fill out and mail Compliance Card.
ELECTRICAL LOAD: NO CHANGE.
WEICIHT AND EALANCE: NO CHANGE.
8PARES AFFECTED: NO.
PUBLICATIONS AFFECTED: The Illustrated Parts Catalog changes required by this document will be inro~oreted at
the nest scheduled revision.
RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service InformationNo. SI-1BS, dated 3 August 1985, entitled "Oil Vent Hose Assembly Replacement". accomplished tdate)
Page 4 of 4
~illc Service information GulFstream
Aerospace
Yk:I(VI(:R INI’ORMATION N(I SI´•I!IT,
Pl)r~ambar I On:I
DOWTY ROTOL SERVICE BULLETIN 61-A995 (Revision 1)
MODELS AFFECTED: MOl)ll. ((’III(:, HRHlnl. NOSr I IH(II) THHU 111:11.
MOl)~l:I. 69111), SEKI~I. NOY. 16(101 THKU Ih(llP. 161)11, 15016 I‘HKU 1601X, ANI) IOL)ZO
TnllU 15(111
MOl)lll. nlIF,, SERLAI. NOS, e601111THI(U YBOX4.
MOI)El.(iBSA. SF:KLAI. N08. UH(I(II, gB00a THKU 961)PI, !N(I)P:( ’PHHII ua,ss.
96(16:1, Rn064. 96089 ANI)H6012.
REASON FOR PUBLICATION: ’I´•0 IR(:OMMF.NI) (:OMI1I.IANCI: WITR I)OW’PY l(OPOI. Sgl(VI(:R HUI.I.E:’PIN (il-
nHBg (I1BVISION ii
COMPLIANCE: I(RPI’IK’PO IIOW’PY 1101‘0[. SRI(VI(:$ HUI.I.E’I~IN (il-hssllKRVISLON II.
MOTE
IF nNY I’KOTIIIIMY AIIR gN(:OUNTBKE:I) WHlllk:
(:OMI’I.YIN(: WITI( IIOWTY KOTOI. SPKVIUF:
IIUIITII:1´•IN LI-~re IKEYLqlON I) LDNThCT
NI(AKRS1‘ (:UI.ISTHBI\M (:OMMANI)RH nUTHOII%EII
SRI(VICRNTglL.
BY WHOM WORK WILL BE ACCOMPLISHED: A B I’ MECIIANIC 011 RUUIVIZI.RNT
APPROVAL: ItRP1IIHI‘O I)OWTY 1(0’1‘014 SBILVI(:R BU1.1.13TLN 61-A9U1II(F.VISION II.
ESTIMATED MI\N HOURS: 1(1(11~1:1(’1‘0 I)OW1’Y KOTOI, SEDVL(:F, IIIII.I.E1‘LN (il-ABOh IIIRVISION I I
PARTS DATA: I(I(PBI1TO I)OW’PY 1101‘01. SRI(VIC6 I(UI.I.RTLN 81-A9!)6(KF.VIS10N II.
SPECll\LTOOLS: NONR.
ACCOMPLISHMENT INSTRUCTIONS:
I. (:l,mllly wilh i)llwty 1~1011 Ssrvi.u i~ullutin 61-A0!)9 ilavilien I).
S L.*altx el’ illl Ehusks ixilti*llctl,ry ilncl alilurrx) ure ~I i,u rup,rten to ihr Pn~luet Bupl,.rt I)clwty Kotlll
I.imitl,d, 1:loua,at~!,´•, Rn.lsnd. I,y talul,hcmo 10491) 712421 or by telex 4:IBilfii7, yuotinl! thL. pn,p.llsr TYP"llUmIll?l., Sari,ll numbcl´•.’I´•Y.N,ilnd idsnti$inll tba *prina, i.a, insur ilr ilutcr. in tha avant I1I´•1I TaP(II´•tCd lililUle.
MOTE
Nl,rth ;Ind Cwntnd Amrricun Opsnltcll~ nl,suld rupllrtrnulta st i)llwty Kotol inol,rplll´•st*d by Clophene 111:(-4111-
R~:II) er i,y iclux XPOIH. Llulh Amurici,n OpunlClrx l~,uld
rapllrt rcnul(h II, I)llwty IlsC,I I.imitcd.
:1.
C
Pagelol2:
SI(KVI(:I LNF‘ORMA1’LON NO. YI-IHI
EL~CTRIC*L LO~D: N00tl*N(ilE CWEIGHT AND BA~ANCE: NO OHANOE.
BPARES nFFECTED: NO.
PVBLICI\TIONS *FFECTED: NONE.
RECORD COMPL(ANCE: Make im ,Ipp,´•opriilto cnlry in airplunr msintannnse racllnl* ax li,llowo: Y~I´•viea Inlilrm,lticln
NI,. SI-1!15. dalrd !I Ocecmbsl´• IOH:I, antillrd "I)owly i*hll Yarvies Bullatin gl´•AH06 illrvixisn II’~, neo,mplilh.dilnd i´•cli!r tl, I)owLy I(l,t~ll Yervicr ilulletin 61-A9H6 i~viuien II lilr I’n,pallrl´• Inlg ncx,k antry.
C
PaEe 2 of Z
D~QPli?ll ROTO L
iStRVICf BULUTI%
ALERT
PROPELLERS MALFUNCTION OF SPRINGS
i. PLANNING INFORMATION
A.
Aircraft (c) Propeller Types
Gulfstream Aerospace Comnander R306/3-82-F17
6900, 6900, 695 and 695A
Fairchild Aircraft SA-227AC (Metro II1) R321/4-82-F/8Fairchild Aircraft SA-227AT (Merlin IVC) R321/6-82-F/9Fairchild Aircraft SA-227TT (Merlin IITC) R324/4-82-F/9Jetstream 31 R333/4-82-F/12CASA 212 R334/4-82-F113
Note: Implement the instructions in this bulletin on all
propellers supplied during 1983 prior to and including
C Berlel No. ORG 61~7183 end on all propellers suppliedin previous years wiEh serial number suffixes /82 and
earlier.
B. Reason
(1) Two cases of feathering spring failures have occuired duringtesting end assembly of propellers at Ocvty Rotol Limited.
Such failure could result in inability to feather a propeller,hut is unlikely Co affect its normal operation. In order to
check that no undetected failures exist it is necessary to
carry out a featherinp check.
C. DescripCion
(1) This bulletin requires operators to carry ouC a groundfeethering check on installed propellers to ensure that the
feather position is achieved. Inability to feather is
recognised by a large angular error in the blade pitch.
n. Compliance
(1) STRONGLY insta lied propellers, within 200 hours or 1 month,RECDMMENDED whichever is the earlier, after receipt of this
bulletin.
uninscalled propellers, after fitmenr Co the
aircraft and prior to first flight.
Sapr. 14/53 61-A995
Nov ?1183 (Revision 1) Page 1 of 3
gBQPV~iill ROTOL
SE~RIICE BU:LLETI#ALERT
(1) This bullerin has been approved by the United ~inpdomCivil Aviation Authority. The technical
content. of the bulletin which affects airworthiness is
approved under the authority of C.A.A. Approval No. DAI/1O18/39.
F. nanpawer
(1) Approximately 15 minutes.
G. Material
(1) None.
H. Tooling
(1) None.
I; Weight
(I) None.
J. n.aerc.ceC
(1) Aircraft Operator’s Manual.
K. Other Publications Affected
(1) The above manual.
2. ACCOMPLISHMENT INSTRUCTIONS
A. Embodiment instrucrio_ns
Note: All engine operation Co be in accordance with aircraft
operating inatrucFians.
(1) Carry out a feathering Eheck in accordance with the following
procedure.
(a) With the aircraft stationary, start engine.
(b) Selectreverse pitch to disengage the starting latches.
(c) Position the power lever between ground idle and flightidle to allow engine conditions to normarise.
(d) Carry out a feather shuc down.
61-as95 Sept. 14/83
Page Nov 21/83 (Revision 1)
ROTOL
SERV~EE BULLETI#ALERT
(e) Note that the propeller blades move Co the feaeher
position.
(f) Operate the unfeather pump to re-engage the propellerstarting latches.
(2) Any propellers failing checks are to be investigaeed and
all springs replaced before
(3) Results of all checks (satisfactory and failures) are to be
reported eo the Prbduct Support Manager, Dowty Rotol Limited,
Gloucester, England, by telephone (0452) 712424 or by telex
43246/7, quoting the propeller Type number, Serial number,
T.S.N., and identifying the spring, i.e. inner or outer,
in the event of a reported failure.
Note: North and General American Operators should report
results to Dowey Rotol Incorporated by telephone703-450-5930 or by telex 824459. South American
Operators should report results to oowey Rotol Limited.
8. Method of Ideneification
(1) Record compliance with this bulletin in the Propeller Log Book.
3. MATERIAL INFORMATION
A. None.
Sepe. 14/83 61-A995
Nov 21/83 (Revision 1) Page 3
iwff~mation
SERVICE INFORMATION NO. SI-196
15 February 1984
SCOTT AVIATION CUS’60NIER SUPPORT SERVICE LETTER NO. 893-SL-01
MODELS AFFECTED MODEL 690A, SERIAL NOS. 11249, 11268 THRU 11344.
MODEL 69011, SERIAL NOS. 11380 THRU 11566.
MODEL 690C, SERIAL NOS. 11800 THRU 11125.
MODEL 690D, SERIAL NOS. 16001 THRU 11012.
MODEL 695, SERIAL NOS. 95000 THRU 95084.
MODEL 695A, SERIAL NOS. 86001 THRU 96041.
REASON FOR PUBLICATION: TO RECOMMEND COMPLIANCE WITH SCOTI~ AVIATION CUSTOMER SUPPORTSERVICE LETTER NO. 893-SL´•01.
COMPLIANCE: PRIOR TO NEXT FLIGHT AND DURING EACH PPIEFLIGHT INSPECTION UNTIL AFFECTED
MASKS ARE REPLACED.
CIF ANY PROBLEMS ARE ENCOUNTERED WHILE
NOTE
COMPLYING WITH THIS SERVICE INFORMATION,CONTACT YOUR NEAREST DULFSTREAM
COMMANDER AUTHORIZED SERVICENTEB.
BY WHOM WORK WILL BE ACCOMPLISHED: FLIGHT CREW ANDIOR A Bc P MECHANICOR
EQUIVALENT.
APPROVAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED.
ESTIMATED MAN HOURS: TEN (10) MINUTES.
PARTS DATA: NEW Pi~ 893-16´•172 SERIES SCOTT MASKS REQUIRED TO COMPLY WITH SCOTT AVIATIONCUSTOMER SUPPORT SERVICE LE1TER NO. 893-81.-01 MAY ns PROCURED THROUGH YOUR NEARESTOULFSTREAM COMMANDER AUTIIORIZID SERVICENTER FOR $168.20 EACH. FOR AIRCRAFT WITHFACTORY EQUIPPED (AFFECTED) MASKS, A FULL CREDIT WILL BE ISSUED FOR MODEL 690C, SERIAL NOS.11651 THRU 11725, MODEL 690D, SERIAL NOS. 16001 THIIU ls0L2. MODel. 695, SERIAL NOS. 95041 THRU 96084AND MODEL 6g5A, SERIAI. NOS. 96Mli THRU 90041 UPON RECEIPI~ OP REMOVED ORIGINAL PIN R93´•16~172SERIES CREW MASK WITH BI.ACK PLASTIC PLOW INDICATOR. A PROPERLY EXECUTED WARRANTY CLAIMAND A COMPI.IANCE CARD LF RECEIVED PRIOR TO 15 FEBRUARY 1SsS.WHEN ORDERIND REPLACEMENT
MASK, ORDER SERVICE INFORMATION NO. 51´•196 I(IT.
SPECIAL TOOLS: NONE.
I\CCOMPLIS*MENT INSTRUCTIONE:
L Comply with Scott Aviation Cuaronler Support Service Letter No 893´•SL-OL nnd refer to Fib~re L, for nowinrlicator.
Psge 1 of 2
SERVICE INFORMATION NO 51-196
2. Fill out and mail Complirnee Card.
CELECTRICAL LOAD: NO CHANGE.
WEIGHT AND BALANCE: NO CHANCE.
SP*AEB AFFECTED: ALL AFFECTED CREW MASKS MUST BE REMOVED FROM SPARES STOCK ANTRETURNED TO OULFSTRGAM AEROSPACE CORPORATION.
PUBLICATIONS AFFECTED: NONE.
RECORD COMPLII\NCE: Make an appropriate entry in airplane maintenance records as follows: Senrice Informatio~No. 51-196, dated 15 February 1984, entitled "Scott Aviation Customer Support Service Letter No. 89S-SL-01",accomplished~
FIOW INDICATOR (D,IREF1
-´•i-MASKS WITH SILVERIBL~CK COLORED
FLOW INDICATOR AND HOSE ~hCONNECTION CRIMP MARKS THAT AREPERPENDICULAR TO HOSE FIRE I\CCEPTABLE
OxvoEN MASKIREFI
FLOW INDICATOR
IREFI
MASKS WITHFLOW INDICATOR I\ND HOSECONNECTION CRIMP MARKSTHAT ARE PARALLEL TO NQTEHOSEARETOBEINSPECTE~AND REPLACED CHECK HOSE CONNECTIONS
AT PLUO´•IN END ALSO
FISUrO
Page 2 of 2
No. 893-SL-01November 8, 1983
SCOTT CUSTOMER SUPPORT SERVICE LETTER
Subject: Air Crew Oxygen Breathing System
Manufacturer: Scott Aviation225 Erie Street
Lancaster, New York 14086
Models: P/N 893 Series Air Crew Oxygen Breathing Systemsconsisting of a head harness, facepiece, mask mountedregulator and supply hose.
Applicabtlity: Assemblies manufactured prior to January 1982.
Reference: Sheet 89126-01 Operating and Maintenance Instructions,Air Crew Oxygen Breathing System, Series M893.
Background: There have been a number of reported field incidents of"broken flow indicators" and "hose seperatlons".
Certain environmental conditions experienced on theflight deel; of alrer~fr n~ay eauie dsgradatlan of
components at an accelerated rate. Bright sunlight,heat and ozone often take a toll beyond what would beconsidered "normal" wear and tear.
Discussion: Due to these factors, Scott Aviation is recommendingan inspection of earlier Model 893 Series MaskMounted Regulators to assure continued properfunctioning and service life.
Those 893 Series units having a black (plastic) flowIndicator and longitudinal (parallel to hose) crimpmarks on hose connection should be inspected prior tonext use and prior to each subsequent use untilreturned in exchange for current configuration masks.
Those units having a metal (silver colored) flowindicator and circumferential crimp marks on hoseconnections (Ferrules) Incorporate current methodsof manufacture. These units are not susceptible to
this environmental degradation.
SCOTT AvIATION A FIOGIE INTERNATIONAL COMPANYB225 Elis S1,8sl. Lancaatar. NY(4088 Tel: llBB83-51W Telex: 81-394
SERVICE LETTERi
PAGE 2
Supplier Action: Since indicator her been Cmade of metal and the hose ferrule crimping hasbeen circumferential.
Suggested OperatorAction:
Inspection Check List
i. Check black plastic flow indicator for signs ofcrazing, cracking or leakage.
2. Check all hose ferrules for signs of loosening,separation or leakage.
3. Perform a routine pre-flight test incorporatingdonning and breathing to assure proper overall systemfunction.
Service GulFstreamAerospace
SERVICE INFORMATION NO. SI-1O?A
(Supersedes Service Information Na. SI-197 in its entirety)15 June 1984
AIRWORTHINESS DIRECTIVE 84-10-06, AMENDMENT 39-4867
MODELS AFFECTED: MODEL 680T, 680V AND B8OW, SERIAL NOS. 1419 THRU 1850.
MODEL 681, SERIAL NOS. 6081 THRU 6012.
MODEL 690, 6BOA AND 69011, SERIAL NOS. 11001 THRU 11430, 11432 THRU 11542
CONVERTED FROM TPE331-S´•261K ENGINE TO TPESS1-6-252K ENGINE.
MODEL 690B, SERIAL NOS 11431 AND 11545 THRU 11566.
MODEL 690C, SERIAL NOS. 11800 THRU 11132.
MODEL 690D, SERIAL NOS. 16001 THRU 15033 AND 15037.
MODEL 695, SERIAL NOS. 85000 THRU 86084.
MODEL 685A, SERIAL NOS. 96001 THRU 96061, 96063 THRU 96072, 96075, 96078, 86085
AND 96088.
REASON FOR PUBLICI\TION: TO RECOMMEND COMPLIANCE WITH AIRWORTHINESS DIRECTIVE 84-10-06,AMENDMENT 89´•4861.
COMPLI~NCE: REFER TO AIRWORTHINESS DIRECTIVE 84-10-08, AMENDMENT 39-4867.
BI WtlOM YIDRI( IILL BE I\CCONPUS*..: URWORTIIINESB DIRECTNB Bl-10d6, *MCNDMENT
ESTIMATED MAN HOURS: REFER TO AIRWORTHINESS DIRECTIVE 84´•10´•06, AMENDMENT 39´•4867.
PARTS DATA: REFER TO AIRWORTHINESS DIRECTIVE 84-10´•06, AMENDMENT 59´•4867.
SPECIAL TOOLS: REFER TO AIRWORTHINESS DIRECTIVE 84-10-06, AMENDMENT 39-4861.
ACCOMPLISHMENT INSTRUCTIONS:
NOTE
Carefully review requirements of Gsrrett Tu~bine EngineCo. Service Bulletin TPE331-13´•0121, Revision 2, if priorCompliance with original Service Bulletin TPE331-73-0121
has been accomplished.
1. Comply with Airworthiness Directive 84´•1(1-06, Amendment 39-4867.
2 Fill out and mail Compliilncs Card.
ELECTRICAL LOAD: NO CHANGE.
WEI(1WT AND BALI\NCE: NO CHANGE.
SPARES AFFECTED: NO.
PUBLICATIONS AFFECTED: Refer to Airworthiness Directive 84-10-06, Amendment 39-4867
RECORD COMPLIP~NCE: Make an applopriab entry in nirplane maintenance records as follows: Service Information
No. SI´•1S?A, dated 15 June 1984. entitled "Aiwarthiness Directive 84-10-06, Amendment 39-4887". accomplished(date)
Pqeloll
Q AIRWORTHINESS DIRECTIVE
CUSDepamnent IVI*TIOH ITIN~LRDS.LTIOWIL nLD D(TrT
drronrpcnetan r.o. 21041M(UWDMI cml oruwou~ 11121
F~damtAvlatMn
Mrmnkhanon
anur~ i*I*I It* s~nrl Wlninunlia in ~h ih paril~l sal´•nl hn.((on R~LN´• Rn 3P.´•p~n I. rnI~ Wln~llnal.l*l~l´• nu ill´•r ix ih´• a~nhlnl Dl~nm ~nula ul´•l. ~n*rm~sluY11M xMEh r~in i~omali" nl´•sia
a~,,n illlalul,ia r~ rml nw* YI1IIEnll Ih*h U1*ICOnhllU I11 i´•aunn*nu ~llh´• hm*mhiru arrnmls*n
:wl,
84-10-06 GARRETT TURBINE ENFSNE COMPANY GTEC, formerl
RIRESEARCH MANUFACT’iiRIN~;CQMPANY OF ARIZONA): Amendment
~4sF;7. Aphlic~ble to;iT1 series of engine m~dels TPE331-25,-43, -47, -55, -1, -2, -3, -5, -6, -10 (except -10A), and -11
equipped with the following fuel pump assemblies:
P/N S/N
868531 7/-8 All.
869151-1/-3/-4/-5 All.
893573-1 through -7 All.
897380-1/-2/-3 series 1 2.
897380-4/-5 Series i, 2, 3.
897390-1/-2/-3/-4 Series 1 2.
897400-1/-2 Series 1 2.
897400-4 Series ii
Compliance is required as indicated unless alreadyaccomplished.
To prevent possible engine failure, accomplish the
following:(a) Inspect low-time engine fuel control/pump assembly to
determine drive shaft running torque as specified in Section
2.A.(2), "Accomplishment Instructions," of GTEC SE
TpE331-73-0121, Revision 2 dated April 18, 1984, or equivalentapproved by the Manager, Western Aircraft Certification Office,in accordance with the schedule below:
Fuel pump assembly time: since new or since last
as sembled; or engine total time since new or since last
overhauledi whichever is known to be least,
Hours Inspect not later than
Less than 200 the next 100 hours in service
200 or more, the next 200 hours in service
and less than 1,000
1,000 or more next fuel pump disassembly
NOTE; Engine Logbook Records should indicate if a new or
reassembled fuel pump assembly has been installed on the enginesince new or returned from overhaul.
Remove from further service fuel pump assemblies havingunsatisfactory running torque inspection results unless
2 84-10-06
modified as specified in Section 2, "Accomplishment~nstructions, in SE TPE331-73-0121, Revision 2, or equivalent
approved by the Manager, Western Aircraft Certification Office.
Fuel control/pump assemblies having satisfactory inspectionresults may he continued in service until fuel pump disassembly
per Paragraph (b) below.
(b) Upon clisassembly of fuel pump for any reason,
reassemble to an approved parts configuration as specified in
Section 2, "Accomplishment Instructions," of SE TPE331-73-0121,
Revision 2, or equivalent approved by the Manager, Western
Aircraft Certification Office.
(C) Special flight permits may be issued in accordance
with Federal Aviation Regulation FAR 21.197 and FAR 21.199 to
ferry aircraft to a maintenance base in order to comply with
the requirements of this AD.
(d) Alternative means of compliance providing an
equivalent level of safety may be used when approved by the
Manager, Western Aircraft Certification Office, FAA, Northwest
Mountain Region.(e) Upon request of the operator, an FAA Maintenance
Inspector, subject to prior approval of the Manager, Western
Aircraft Certification Office, FAA, Northwest Mountain Region,may adjust the compliance schedule specified in this AD to
permit compliance at an established inspection period of the
operator if the request contains substantiating data to justify
The manufacturer’s specifications and procedures identified ithe adjustment for that operator.
and described in this directive are incorporated herein and
made a part hereof pursuant to 5 U.S.C. 552(a)(1).All persons affected by this directive who have not already
receivedthis document from the manufacturer may obtain copies
upon request to Garrett Turbine Engine Company, 111 South 34th
St., P.O. Box 5217, Phoenix, Arizona 85010; telephone (602)231-1000. This document also may be examined at FAA Rules
Docket 83-ANE-29, New England Region, Office of the RegionalCounsel, 12 New England Executive Park, Burlington,Massachusetts 01803.
This amendment supersedes Amendment 39-4840 (49 FR 13487),AD 84-07-08.
This Amendment 39-4867 becomes effective May 30, 1984.
FOR FURTHER INFORMATION CONTACT:
Bob Liddiard, Aerospace Engineer, ANM-174W, Western
Aircraft Certification Office, Northwest Mountain Region, P.O.
Box 92007, Worldway Postal Center, Los Angeles, California
90009, telephone (213) 536-6380.
I~_ __
SerpliceGulfstreamAerospace
SERVICE INFORMATION NO. SI-199
26 May 1984
FUSELAGE STATIONS 386.85 AND 409.56 PULLEY BRACKET MODIFICATION
MODELS AFFECTED: MODEL 686, SERIAL NOS. 12000 THRU 12066.
MODEL 690, SERIAL NOS. 11001 THRU 11019MODEL 690A, SERIAL NOS. 11100 THRU 11349.MODEL 690B, SERIAL NOS. 11360 THRU 11566.MODEL B90C, SERIAL NOS. 11600 THRU 11732.MODEL 39011, SERIAL NOS. 15001 THRU 15025, 15029 THRU 16032 AND 16037.MODEL 695, SERIAL NOS. 86000 THRU 95084.MODEL 695A, SERIAL NOS. 98001 THRU 96055, 96059 THRU 96061, 96064, 96085 AND96012.
REASON FOR PUBLICATION: TO ELIMINATE THE REQUIREMENT FOR REPETITIVE INSPECTION OFRUDDER CABLES PER SERVICE BULLETIN NO. 195A.
COMPLIANCE: AT OWNERS DISCRETION.
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILECOMPLYING WITH THIS SERVICE INFORMATION,CONTACT YOUR NEAREST DULFSTREAMCOMMANDER AUTHORIZEO SERVICENTER.
BY WHOM WORK WILL BE ACCOMPLISHED: A L P MECHANIC OR EQUIVALENT.
APPROVAL: ENGINEERINC- DESIGN ASPECTS ARE FAA APPROVED.
ESTIMATED MAN HOURS: MODELS 685, 690, 690A AND 6908 THIRTY (30) HOURS.MODEL 6900, SERIAL NOS. 11600 THRU 11718 FORTY FIVE (45) HOURS.MODEL 690C, SERIAL NOS. 11119 THRU 11132 THIRTY (SO) HOURS.MODEL 690D THIRTY (30) HOURS.
MODEL 696 FORTY FIVE (46) HOURS.MODEL 695A, SERIAL NOS. 96001 THRU 96013 AND 96018 FORTY FIVE (46)HOURS.MODEL 695A, SERIAL NOS. 96014 THRU 96011 AND 96018 THRU 96012 THIRTY (30)HOURS.
PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE INFORMATION LETI‘ER MAY BEPROCURED THROUDH YOUR NEAREST CULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR(208.46. REFERENCE THIS SERVICE INFORMATION LE~PTER, AIRCRAFT MODEL AND FACTORY SERIALNUMBER WHEN ORDERIND SERVICE INFORMATION NO. 51-199 KIT CONSISTIND OF THE FOLLOWING:
prln lual´•a lo~h´•ny´• mtn~M notlu
Page 1 of 8
SERVICE INFORMATLON NO. 81-186
BEFORE CHANGE AFTER CHANGE
~USELAOE 5rPI. 386.85EXISTING ANGLES
ANGLES IVY/ IREFIIREFI lit~
c i"
M92456648 PULLEY
PULLEY ~iJ IAEPIIREF)
\C C
Gj~J, InEF1
EXISTINGWEB
c i -r- ExlsnNo WEB
h InEFI
530087´•REllDOUBLER
aBrREFI
BInEFI
IREF)LEFT INSTALLATION SHOWNRIGHT INSTALLATION OPPOSITE Fieura i.
CPUZ1LAOI STA. 386.85
De’lAll P. DImll B
EXISTING NAS427K11
GUARDPIN
InEFI
i i IREPI
HUCK BOLT i
t laPLsl (nsPI
i,TOOLTIOOB´•3.f DOUBLER
LOCATE AND DRILL
DII\.HOLE
´•I(0.211(1"/0.2172" DIA. HOLE
MS21044Nd NUTANBBOD41BWI\SHERI\N4´•llA BOLT
SHADED AREA
INDICATES AREA C-~ HLZZOPBBbPINTO BE REMOVED
i IHI SHEI\AI MS2QBB´•48 PULLEYTO INSTALL HLBJ-S COLLAR
PULLEY ANGLE0.2142"10.2112" DIA. HOLE
HL220PBB´•8 PINIREF)
0.2112"10.2112" DIA. HOLE (HI SHEARIHLZZOPBB´•SPIN ~NBBOOIOWASHER
(HI hHEAR) IUNDER HEAOInL83´•BCOLLPIR HLII´•B COLLAR
VIEW LOOKING AFT
Figure
Page 2 of B
SERVICE INFOIIMATION NO. 91-399
$TY PART NO. DESCRIPTION
4 ea. ANB-4A Bolt
2 ea. AN(´•11A Bolt
2 ea. AN6-22A Bolt6 ea. AN960D10 Washer8 ea. AN960D416 Washer4 ea. AN860´•616 Washer
6 ea HL220PBG-5 Pin6 ea. HL93-6 Collar4 ea. MS2104JN3 Nut
2 ea. MS21044N4 Nut2 en. MS21044N6 Nut2 ea. MS21051L3 Nutplate6 ea. M621256-1 Turnbarrsl Locking Clip2 ea. MS24566-4B Pulley2 ea. MSP(SB6-SB Pulley2 ea. MS35207-265 Screw
12 ea. NAS1080-6 Collar
12 ea. NAS1465-S Huckbolt2ea. NAS43DD6-60 Spacer1 ea. 53(1481-RE6 Anglei ea. 530481-RE6 Angle1 se. 530487-REll Doubler
1 ea. 530487-RE12 Doubler2 ea. 530487-BE19 Spacer2 ea. 530487-B316 Spacer1 se TS0063 Drill Template1 se. Compliance Card1 ea Service Information No. 9I´•lsD instructions
SPECIAL TOOLS: HUCK GUN AND TS006´•9 DRILL TEMPLATE.
ACCOMPUSHMENT INSTRUCTIONS:
I. Gain secess to rudder pulley brackets, located at fuselage stations 386.85 and 409.56, through aft fuselage access
doors or through baggage eompartment door.
2. Remove tail cans and remove left and right inspection panels, located on aft fuselage just below horizontal
stabilizer, to gain access to rudder and elevator control cables.
1 caurmtlEAUTION
Clamp cables forward of station 386.85 to prevent cables
From slipping alforward pulleys or cable drums. Stow and
protect cables from kinking or bending damage while
accomplishing this modifieatian.
3. ~Disconnelt left and right rudder cables st tumbarrsls or at rudder horn assembly.
1. Disconnect leR and right elevator cables at turnbarrels or st elevator idler tube link assemblies to facilitate
modification of rudder pulley bracket aslemblies.
5. Modify left and right pulley bracket assemblies at fhselage station 386.85 as follows:
a Remove and discard existing left and right pulleys and attaching hardware. Retain existing NAS427Kllcable guard pins far inter reinstallation (refer to Figures 1 and 2).
h. Using 530481-HEll and 530487-AEll doublers as templates, mark and lengthen existing pulley cutoutsin existing same web to four ii) inches (refer to Detailk, Figure 2).
Page 9 of 8
SEBVICE INFORMATION No. SI-189
,UIII*Ol 11*´•
EXISTINGCABLE ounnr, PIN
IREPI LEFT INSTALLATION SHOWNRIGHT INSTALLATION OPPOSITE
ExlsrlNaPULLEY D
EXISTINGCABLE GUARO
PIN BRACKET
IREF)
BEFORE CHANGE
figure 3.
O408.68
VERTICAL BRACKETIREFL
C,
REMOVE PER --r V
srEPa.~.
1.501’ ,8´•´•
HORIZONTALBRACKET
IREFI
VIEW LOOKING DOWN
Pigu,s 4.
Page 4 or B
SEIIVICE INFORMATION NO. S1-189
CAUTION
Care should be taken when drilling out rivets in pulleyangles to prevent elongating holes in brace, web andangles if proper hole sizes and minimum 1.5 edge distancecriteria cannot be maintained in brace, web and angles,replafement of Chase parts may he required.
c. Carefully drill out and remove nine existing rivets that attach existing.‘pulley angles (refer to DetailA. Figure 2).
d. Locate, drill and install 530487-REll doubler (leR side), 630481-8112 doubler (rightside), 530487´•RE13
spacers and 530487-8115 spacers using NAS1(65-5 huckbolta, NAS1OBO collars. HL220PB6´•6 pins,AN860D10 washer and nL93-B collars(refer to Detail A, Figure 21.
a. Using TS006-3 drill template, line drill 0252 (10.002) inch diameBr hale through existing angles (I´•eBrto Detail 8, Figure 2).
NOTE
Use end of tool with short drill bushing that is markedyr383.
f Deburr holes and touchup paint with zinc chromate primer,
g. Install MS24566´•4B pulley, on left and right side using ANI-11A bolt. ANSM)D4L6 washer and
i MS21044N4 nut (I´•eB1´• to Detail B, Figure 2).
6. Modify i~rt right pulley bracket assemblies at fuselage station 40966 as follows:
a, Remove and discard existing NAS427K12 cable guard pins irefer to Figure 51.
b. Remove and discnl´•d existing left and i´•ipill pulleys and attaching hurdwal´•e ircLI to Figure 3).
c. Drill out rivets and discard existing cable guard pin bracket irerer to Figure 3).
d. Trim forward nange on existing left and i.ight horizontal brackets os shown on Figure 4 and deburl´•edges of
e Using TS006´•3 drill teml,lote, drill 0.3111~0.002) inch diameter irole through left and right verticalbrackets IreWr to Figure 51.
NOTE
Use rad of tool with long drill buslling that is markedY=409.
f Clamp 530481-KIC, angle tlelt aide) ond 530187-llB6 angle (rigbt sider to bottom side of existingbol´•i~ontal h´•oekets and,ncrk hole location on angles (refer to Pigul.e 51.
g Measure vertical dimonsio,~ on angle, ol,tained in step 1:, and transfer ciimensios to opposite end of angleand drill 0.377 it0.002) inch diameter hole in 530487-R&5 and 53U487-HE6 angles (re~8r to Pigulr 51.
h. Touchup paint on brackets and angles with zinc chromate primer
Install MS210511.3 nutplnte over existing cable guard hole in vel.ticai bracket (I.rLI to Figure 61.
Page 5 of 8
IERYICE INFORMATION NO. SI-199
*poslnoN OF ANGLE ASSHOWN 18VERTICAL BRACKET FOR OBTAINING VERTICAL DIMENSION(REFI OF HOLE LOCATION. ANGLE WILL BE
TURNED AROUND 1800 ON FINAL INSTALLATION
HORIZONTAL 3RPICKET
(REF)VERTICAL BRACKET
HORIZONTAL BRI\CKET
53M87´•RES ANGLE
POSITION ANGLE APPROXIMATELY
TO LOCATE VERTICAL
DIMENSION ON ANGLE
i. USING TSOOBJDR(LL TEMPLATE.LOCATE AND DRILL P.3711/~´•379´•´•DIA. HOLE THRU VERTICALBRACKET PER STEP 8.a.
2. CL~MPS30(s7´•RES AND ´•REB
ANGLES ON HORIZONTAL BRACKETS
AND MARK HOLE LOCATION ON
ANGLES PER STEP 6.1.
TS00830R(LLTEMPLATE VIEW LOOKING INBD
0.375" DIA. HOLE WILL FALL ON EDGE
OF HORIZONTAL BRACKET FLANGE
TRANSFER THIS MEASURED
DIMENSION TO OTHER ENDANO DRILL HOLE AS SHOWN.
53M87-RE6fl.o´•´• FLANGE
ANGLE i.
0.375"10.379" DIA.HOLE
DIMENSION MARK
MADE PER STEP 8.1.
PiBurs 5.
Page a ot 8
SEAYICE INFORMATION NO. SI-188
CHOLESINBRACKET
ACCEPTAQLE
L’/d *N ADDITION OF ONE Ill WASHER
MAY BE INSTALLED UNDER BOLTHEAD OR NUT PROVIDED P,MINIMUMOF ONE lijfjiREl\O EXTENDSTHROUGHTHENUT.
630181-866 ANGLEIREF)
MS21044N8 NUT. ANBBOB1BWASHER
EXISTING HOLE
IREFI
AFTER CHANGE
M82468868
FiYCC-I-----; liZO.ls0’7o.194’~ DII\.
HOLE
ANJ-~BOLTANBBOOIOWASHER
ANB-22ABOIT’ 1 111 MS21041N3 NUT
12 PLSI0.50~
EXISTING HOLE
MSZ1D61L3 NUTPLPITEMSJ6207286SCREW
WITH MS20PIOAD3 RIVET
I? PLSI
-O- o\
M824SBBaBPULLEY iIREFI
IF INTERFERENCE EXISTS BETWEENRIVET AND ANIBO´•BIB WASHER. REPLACE
RIVET WITH RIVET II\CCEPTABLETO USE MSZ04ZBAOS RIVET AND SHAVE
HEAD OF RIVETI.
630dBI´•RES PINGLE
LEFT INSTALLATION SHOWN
RIG HT I NSTALLATIO N OPPOSITE
sm.
~oe.se
Figure 6.
Page 1 of 8
SERVICE INFORMATLON NO SI-199
i ineisll M6a(86-Ln lulby ~ind 590(87´•1116 ´•Wlo (Idt aids), 69D~87REB allgle inght aid.) ulin~ ~N6´•22A bolt, NAS4SDD6-60 spacer, AN960´•616 washer (2 places) and MS21044N6 nut il´•efer to Figure 6)
NOTE
Do not drill hulea in 0.75-inch nange ofangle Far attachingangle to hori2ontal bracket at this time. Holes will bedrilled after assurance alprapsr alignment of pulleys.
k. Reconnect left and right rudder cables at turnbarreis or at rudder ham assembly and apply slighttension on cables to assist in alignment.
i. Assure that pulley is properly aligned to allow cable to operate smoothly over pulley. This can heobtained by positioning ofangle Clamp angle into place end drill two 0.192 I+OU02) inch diameterholes through horizontal bracket and angle (refer to Figure 6).
NOTE
Use pilot hole in aft end of angle for ah fastener and Locateforward fastener from existing tooling hole in horizontalbracket.
m. Attach angle to horizontal bracket using AN9-4A bolts, AN960D10 washers and MSa1044N3 nuts (reiel.to Figure 6).
n. install MS35a01-265 screw (used as cable guard) in nutpiate installed in step i. (rsfer to Figure 6)
7. Reconnect left and right elevator cables at turnbarrels or at elevator idler tubs link assemblies
8. ReinataB guard .ins at hualsls 386
9 Check rigging and tension of rudder and elevator controls as outlined in the applicable Airplane MaintenanceManual and functional check system.
10 Reinstail tail cone and inspection panels on airplane.
11. Fill nut and mail Compliance Card.
ELECTRICAL LOAD: NO CHANGE.
WEIGHT AND BALANCE: NO CHANCE.
SPARES AFFECTED: NO.
PUBLICATIONS AFFECTED: The Illustrated parts Catalog Changes required by this document will be incorporated atthe next scheduled revisisan.
RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service InformationNo. SI-199, dated 25 May 1884, entitled "lluselage Stations 386.85 and 409.56 Pulley Bracket Modification.., accomplished
(date) Note in maintenance records that repetitive inspection per Service Bulletin No. 195A is herebywaived.
Page 8 of B
I __
Service inlf~rmation GulfstreamAerospace
SERVICE INFORMATION NO. SI-20016 July 1884
EXnAUST GAS TEMPERPITURE (EOT) INDICATOR ISOLATOR INSTALLATION
MODELS AFFECTED: MODEL 695, SERIAL NOS. 95000 THRU 96084.MODEL BSSA, SERIAL NOS. 96001 THRU 96061, 46065 THRU 96072, 96015. 96078, 96088AND 96088.
REASON FOR PUBLICATION: AS THE EGT HARNESS AGES, IT BECOMES SUSCEPTIBLE TO BREAKDOWN OFINSULATION BETWEEN THE THERMOCOUPLES AND THE OUTSIDESHIELDING OF THE HARNESS. THE ISOLATOR WILL ELECTRICALLY ISOLATETHE HARNESS FROM THE INDICATOR AND PREVENT ERROR CAUSED BY THEBREAKDOWN.
COMPLIANCE: AT OWNERS DISCRETION.
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILECOMPLYINCI WITH THIS SERVICE INFORMATION,CONTACT YOUR NEAREST GULF8TREAMCONM*NOER hmBORIZED BERVICENTER
BY WHOM WORI( WILL sE ACCOMPLISHED: A P MECHANIC OR EQUIVALENT
APPROVAL: ENGlNEdRINO DESIGN ASPECTS ARE FAA APPROVED.
ESTIMATED MAN HOURS: THIRTY (801 MINUTES.
PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE INFORMATION MAY BE PROCUREDTHROUDH YOUR NEAREST DULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR $888.60.REFERENCE THIS SERVICE INFORMATION, AIRCRAFT MODEL AND FACTORY SERIAI. NUMBER WHENOHIIEKINC´• SERVICE INFORMATION NO SI-200 KA CONSISTIND OF THE FOLI.OWIND:
n~Un
~TY PART NO. DESCRIPTION
2 ea. 400188´•5 tMaricopa Controls) Isolator1 as Compliance Card1 ea. Service Inlormstion No. SI-200 Instructions
SPECIAL TOOLS: NONE.
L. Loosen screws attaching EGT indicator to center instrument panel and pull EGT indicator out.
2. Disconnect electrical connector Emm ECT indicator and connect 400266´•3 isolator to EDT indicator (re~er toFigure 1).
3 Connect airplane electrical connector to 400288´•5 isolator (reBr to Figure 1).
Page 1 oE2
FIERYICE INFOHMATION NO. SI´•200
4. Insert isolator thru panel and reinstall EGT indicators on center instrument panel and lighten sorews.
Ci. Assure that EGT indicators are functional and working properly.
B. Fill out and mail Compliance Card.
ELECTRICAL LOAD: NO CHANCE.
EXIGTINB I\IRPLANEELECIRICAL COIINECTOR
(REF1
EXI~TINO IXHAUST (11\8
TEMPERATURE IND1CI\TORIREPI
Am ´•I.
WBIOHT AND BILANCE: The weight and balance change resulting Rom installation of this Service information is as
follows:
WEIOHT(LBS) H´•ARM (INDHES) H-MOMENT IIN-LBS)+l.ls ?0.0 +81.0
SPAAES AFFECTED: NO.
PUBLICATIONS AFFECTED: The illustrated Parts Catalog change re~uired by this document will be incorporated at
the next soheduled revision.
RECOAD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service Information
No. 61-200, dated 16 July 1984, entitled "llhsust Oas Temperature (EDT) Indicator lsalator Installation", accomplished(datel
L
2 of 2
c Service informationGulfstreamAerospace
SERVICE INFORMATION NO. 81-20126 July 1984
OARRETT SERVICE BULLETIN TPE331-73-0128
MODELS AFFECTED: MODEL 695, WITI-I ESOINE SERIAL NUMBERS PRIOR TO P58962.MODEL 69SA, WITil ENDINE SERIAL NUMBERS PRIOR TO P39552.
NOTE
Regardless of engine serial number, verification of fuelmanifold part number should be accomplished. (Refer toDarrett Service Bulletin TPE331-13-0128, paragraph2.A.(2).)
REASON FOR PUBLIC~TION: TO RECOMMEND COMPLIANCE WITH GARRETT SERVICE BULLETIN TPE331-19-0128.
COMPLIANCE: REFER TO OARRETT SERVICE BULLETIN TFE991-13:0128.
BY WHOM WORK WILL BE ACCOMPLISHED: A B P MECHANIC OR EQUIVALENT.
C/ EBTIM~TED.IIN nouns; ~eR TO UANR.~ SERVICE BOLl~eTIII TP&991-?SoL1B DIITED is NOVEMBER
PARTS DATA: ONE EACH DUPLICATE CERTIFICATE OF COMPLIANCE
SPEICALTOOLS: NONE.
~CCOMPLISHMENT INSTRUCTIONS:
NOTE
Carefully review the requirements and thoroughlyunderstand the procedures outlined in Garrett ServiceBulletin TPE931-13-0128.
1. Comply with Garrett Service Bulletin TPE331-7S´•0128.
2. Fill out and mail the CERTIFICATE OF COMPLIANCE and DUPLICATE Certificate of Compliance.
ELECTRICAL LOAD: NO CHANCE
WEIGHT AND BALANCE: NO CHANCE.
SPARESAFFECTED: REFER TO DARREW SERYICE BULLETIN TPE391-13-0118, MATERIAL INFORMATION,FOR SPARE PARTS REqUIRED,
PUBLICATIONS AFFECTED: REFER TO OARRETT SERVICE BULLETIN TPESS1-13-0128.
RECORD COMPLIANCE: Make an appropriate entry in the airplane maintenance records as follows: ServiceSlao~, d´•t~ P6 duly LBBC sntillai .O.mtl Sar*iE´• BullsLm TPE881´•n~ll(i.. n~mpllahid
Page 1 of 1
/~3 SEaaylGE IULLETBNGARRETT TURBINE ENGINE COMPANY
.CINF rUFL (WD (OHTR~L DLITRIBUTION In~pecr hi.l Naniiold~ far iealage
i. Planning Information
A. Effectivity
This service bulletin is applicable to the following turboprop aircraftengines.
Prior toPart No. Model No. Serial No. Application
3101470-1 TPE331-8-401S Conquest II3102510-1 TPE331-8-4025 Conquest II3102510-2 TPE331-8-403S Conquest II3101470-2 TPE331-8-404S Conquest II3102170-1/-2 TPE331-10-501C CASA 212-2003102190-1 TPE331-1O-501K Jetprop
Commander 695/980 JetpropCommander
695/1/10003102180-1 TPE331-10-501M Mltsubishl
Marquise/solitaire
3102170-5 TPE331-10-511C CASA 212-2003102190-2 TPE331-10-511K Jetprop
Commander 695/980 JetpropCommander
695A/10003102180-2 TPE331-10-511M Mftsublshl
Marqulse/Solitaire
3102170-3 TPE331-10R-501C CASA 212-2003102170-4 TPE331-10R-502C CASA 212-2003102170-6 TPE331-10R-511C CASA 212-2003102170-7 TPE331-10R-512C CASA 212-2003103090-1 TPE331-10U-501E No Current
Application3102050-1/-2 TPE331-10U-501G Merlin IIIB3102050-3 TPE331-1OU-502G Merl in IIIB3102940-1 TPE331-10U-5036 Merlin IIIC3102050-4 tPE331-10U-511G Merlin IIIB3102050-5 TPE331-10U-512G Merlin IIIB3102940-2 TPE331-10U-5136 Merlin IIIC3103230-2 TPE331-10UA-501G Metro II3103230-1 TPE331-10UA-511G Metro II3102600-1 TPE331-1OUF-501H Jetstream 313102600-2 TPE331-10UF-511H Jetstream 313102540-1 TPE331-llU-601G Metro III/i Merlin IVC
Nov 18/83 TPE331-73-0128
Page 1 of 8Copyright 1983 by The Garrett Corporation
[F~ SEW?IIGE BULLETIIa
GARRETT TURBINE ENGINE COMPANY
Prior toPart No. Model No. Serial No, Apollcation
3102540-2 TPE331-llU-6026 Metro III/Merlin IYC
3102540-3 TPE331-11U-611G Metro III/Merlin IVC
3102540-4 TPE331´•llU-612G Metro III/Merlin IVC
3102920-1 TPE331-11UA-601W Pucara 1A-663102920-2 TPE331-llUA-611W Pucara IA-66
*Effectlvity may be determined by visually checking the manufacturer’spart number on fuel manifolds,
8. Reason
To inspect fuel manifolds that have shown a potential to leak at weldedjoints.
C. Descriptfon
This service bulletin provides instructions for inspection of andreplacement (if needed) of Manifold Assemblies, Part No. 3102469-1
1.0. Tag, Pdrt No. 28882).
D. Compliance
Recommended. Garrett recommends that this service bulletin be accom-
plished at next exposure of affected part and every 100 hours (if noleakage occurs) until fuel manifold is replaced with a manifold whichhas a manufacturer’s part number other than Part No. 28881. InspectionIs no longer required following replacement of fuel manifold.
E, Approval
The inspection authorized by this service bulletin has been found tocomply with applicable Federal Aviation Regulations and is FAA approved.
F. Manhour Requirements
An estimated one manhour is required to accomplish this inspection afteraccess to part is obtained.
G. Material Price and Availability
Information regarding price and availability of parts may be obtainedfrom a Garrett authorized Servf ce Center or the aircraft manufacturer’sappointed service factllty. (Refer to Service Information Letter(S.I.i.) P331-27 far a complete listing of these f~cllities.)
Nov 18/83 TPE331-73-0128
Page 2
I~ilti 5EXM36~ BULEETPMGARRETT TURBINE ENGINE COMPANY
CH. Tooling Price and Availability
No special tooling required except that already listed in referenced
manual(s).
I. Weight and Dalance
No change.
J. Publications References
The sources of information used in the preparation of this service bul-letin include Garrett engineering documentation and the followingpubiication(s).
IllustratedPart/ Overhaul Maintenance PartsModel No. Manual Manual Catalog
TPE331-8-401S NA *72-00-13 72-00-11TPE331-8-402S NA "72-00-13 72-00-11TPE331-8-4035 NA *72-00-13 72-00-11TPE331-8-404S NA f72-00-13 72-00-11TPE331-1O-501C NA "72-00-28 72-00-21
C TPE331-10-101K NEI ’12-00-29 1P-00-21TPE331-1O-501M NA *72-00-27 72-00-21TPE331-1O-511C NA *72-00-28 72-00-21TPE331-10-511K NA *72-00-29 72-00-21TPE331-10-511M NA *72-00-27 72-00-21TPE331-1OR-501C NA *72-00-28 72-00-21TPE331-10A-502C NA *72-00-28 72-00-21TPE331-10R-511C NA *72-00-28 72-00-21TPE331-10R-S12C NA *72-00-28 72-00-21TPE331-10U-501E NA *72-00-42 72-00-41TPE331-10U-501G NA *72-00-23 72-00-21TPE331-10U-502G NA *72-00-23 72-00-21TPE331-10U-503G NA *72-00-30 72-00-21TPE331-1OU-511G NA *72-00-23 72-00-21TPE331-10U-512G NA *72-00-23 72-00-21TPE331-10U-513G NA *72-00-30 72-00-21TPE331-10UA-501G NA *72-00-45 72-00-44TPE331-1OUA-511G NA X72-00-45 72-00-44TPE331-1OUF-501H NA *72-00-42 72-00-41TPE331-10UF-511H NA *72-00-42 72-00-41TPE331-11U-601G NA *72-00-25 72-00-24TPE331-1lU-602G NA *72-00-25 72-00-24TPE331-llU-611G NA *72-00-25 72-00-24TPE331-llU-612G NA "72-00-25 72-00-24TPE331-llUA-601W NA *72-00-25 72-00-24TPE331-ilUA-611W NA *72-00-25 72-00-24
*Affected Chapter/Sectlon/Subject 73-10-09.
Nov 18/83 TPE331-73-0128
Page 3
$ERVICE BULLETI~GARRETT TURBINE ENGINE COMPANY
K. 9,,,,, Bullefin CNone.
L. Other Publ~catlans Affected
Same as those listed under ’Publlcatlons References’.
Nov 18/83 iPE331-73-0128
Page 4
SE~VICEB
GARRETT TURBINE ENGINE COMPANY
i. Accomolishment Instructions
NOTE: Manuals listed in Section 1 provide applicable disassembly,cleaning, inspection, reassembly, and testing instructionsand shall be referred to during the accomplishment of thefollowing instructions.
Paragraph A provides instructions for inspection of fuelmanifold assemblies, Paragraph B provides instructions for
removing and replacing of fuel manifold.
Inspection is applicable to only those Fuel Manifolds, PartNo. 3102459-1, that I.D. tag indicates Manufacturer’s PartNo. 28881.
A. Inspect Fuel Manifolds, Part No. 3102469-1 for Leakage
NOTE: Do not remove any items that would prevent engineoperation. Engine to be operated in performance offuel manifold leak check.
(1) Remove aircraft mounted equipment to gain access to affected partIn accordance with Aircraft Maintenance Manual.
(2) Check I.O. tag an fuel manifolds far manufacturer’s Part No. 28881.If I.D. number is not 28881, no additional action is required,proceed to step (6).
(3) Start and operate engine at propeller governing mode in accordancewith Engine Maintenance Manual. Observe fuel manifolds duringstart, if leakage is noted, abort start.
(4) Inspect fuel manifolds for leakage, paying particular attention towelded areas.
jSJ If no leakage is noted, reassemble aircraft mounted equipment inaccordance with Aircraft Maintenance Manual. if any leakage isnoted, replace fuel manifolds. Refer to Paragraph B for replace-ment instructions.
(6) Upon completion of aircraft reassembly, check and ensure proper en-
gine operation in accordance with Aircraft Flight Manual.
(7) Upon completion, make entry in engine log book noting engine oper-ating time land serial number of installed component if applicable)and compliance with this service bulletin land service bulletinrevision number if applicable).
(8! Reidentification of equipment not required.
(9) Complete attached Compliance Certificate and mail.
Nov 18/83 TPE331-73-0128
Page 5
SEWVB@E BULIE’BI~P
O\RREST TURBINE ENGINE COMPANY
NOTE: Return removed fuel manifolds to Garrett TurbineEngine Company, Phoenix, Arllona for exchange.
8. Remove and Replace Fuel Manifolds, Part No. 3102469-1
(1) Disassemble engine as needed to gain access to and remove affectedpart in accordance with Engine Maintenance Manual.
(2) Install and leak check replacement fuel manifold, which has a
manufacturer’s part number other than Part No. 28881, in accordancewith Engine Maintenance Manual.
(3) Reassemble engine in accordance with Engine Maintenance Manual.
Nov 18/83 TPE331-73-0128
Page 5
SERIB@EGARRETT TURBINE ENGINE COMPANY
3. Material Information
NOTE: Applicable illustrated parts catalogs and spare parts bul-letins dated later than the original issue date of thisservice bulletin may introduce different parts forinstallation, Refer to these documents before orderingparts.
Expendable parts discarded in gaining access to the af-fected area of the equipment are not included.
The following parts are required to accomplish the instructions outlined inthis service bulletin.
Unit
List instructfuns-New PN Ouantltv Price" Key Ward Old PN Disposition
a3102469-1 1 or 2 Fuel Manifold #3102469-1 0, T
Disposition Code O. New part is available on exchange basis. Contact your ser-vice agency for details.
Ol.llorit~on C~de T. Return Part to barrett Phoenix, Ar(lona far exchange.
bWith manufacturer’s Part No. 28881
~With manufacturer’s part number other than Part No. 28881
*Refer to Section 1, Paragraph G for information regarding price and availabil-fty of parts.
Nov 18/83TPE331-73-0128
Page 7/a
DUPLICATE
Certificate of Compliance
To: Operator Dr SeNice Center Pslforming Modification.
Upon modification of equipment, pleare fill in the information requertsd below, then fold, ~taple, end drop the
completed certificate into the mail.
Owner/Operator
Engins/squipmsnt Part No. Model No.
Serial Na.
No. 1 Na. 2 Na. 3 No. 4
TSN/TSO
No. 2 Na. 3 No. 4
Cycler
No. 1 No. 2 No. 3 No. 4
I certify that the above engine/equipment her been modified in accordance with the following Service Bulletin(l).
SE No. Rev No. SE No. Rev No.
SE No. Rev No. 33 No. Rev No.
SE No. Rev No. Ss No. Rev No.
Signature Dare
Title
CulfJlream AemspareCorpontion
clots i,´•al) q
~IService informationGulfstreamAerospace
SERVICE INFORMATION NO. 81-20214 February 1986
KING RADIO SER\IICE MEMO #319, REVISION 1
MODELS PIFFECTED: THE FOLWWING MODELS, IF EqUIPPED, WITH KING KFC 200, KFC 260 OR KFC 300AUTOPILOT SYSTEM INCORPORATING KSA 570, KSA 571 OR KSA 312 AUTOPILOTSERVO’S:
MODEL B90A, SERIAL NOS. 11100 THRU 11544.MODEL BgDB, SERIAL NOS. 11560 THRU 11566.MODEL 690C, SERIAL NOS. 11600 THRU 11734.MODEL 690D, SERIAL NOS. 15001 THRU 16033 AND 16086 THRU 18057.MODEL 695, SERIAL N0S. 86000 THRU 95064.MODEL 69SA, SERIAL NOS. 96001 THRU 96081, 96084 THRU 86068, 96070 THRU 96073,96011, 86092, 96088 THRU g90B1 AND 98095.MODEL 700, SERIAL NOS. 10001 THRU 70092.
REASON FOR PUBLICATION: TO RECOMMEND COMPLIANCE WITH KIND RADIO SERVICE MEMO #313,REVISION 1 DATED DECEMBER 6, 1984.
COMPLIANCE: REFER TO KING RADIO SERVICE MEMO #513, REVISION 1 DATED DECEMBER B, 1884(ATTACHED).
WOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILECOMPLYING. WITH THIS SERVICE INFORMATION,CONTACT YOUR NEAREST WLFSTREAMCOMMANDER AUTHORIZED SERVICENTER.
BY WHOM WORK WILL BE ICCOMPLISHED: A p MECHANIC 08 EPUIYALENT.
ESTIMATED MAN HOURS: REFER TO KIND RADIO SERVICE MEMO #313. REVISION t DATED DECEMBER B.1984.
PARTS DATA: REFERTO KING RADIO SERVICE MEMO *S1S. REVISION 1 DATED DECEMBER 9, 1984.
SPECIAL TOOLS: NONE.
ACCOMPLISHMENT INSTRUCTIONS:
1. Cain access to King Autopilot servos la.sted in aR fuselags.
2. Comply with King Radio Service Memo #513, Revision 1 dated Dseember 6, 1984.
3. Fill out and mail Complianee Card.
ELECTRICAL LOAD: NOCHANGE.
WEIOHTAND BALANCE: NO CHANGE.
SPARES P.FFTCTED: ALL KSA 310, KSA 311 AND KSA 512 SERVOS MUST BE PULLED FROM 8PARES SHELFBTOCK *NO INSPBCPEO PER KI~NO R*DiO SBBYICI: LL&MO XSLS, 8&YISION 1 D*TEDDECEMBER B, 1984.
Page 1 01 2
-----´•---´•--i-´•------´•- ------´•----´•--i- --´•-´•i
I’ EIERVICE INFORMA~ION NO. 9I-202
PUBLICITIONS AFFECTED: NONE.
RECORD COIPLII\NCE: Make an appropriate entry in airplane maintenance records as follows: Servioe InformationNo. SI,2D2, dated 14 Wbruary 1985, entitled "King- Radio Service Memo #S1S, Revision i", complied with or not
applicable (date)
Fake 2 of 2
SERVICE MEMOC: 7RADIO
saav,ceSILES SERVICIJ neMO 1313 Revised
SUBJECTI Improper Assembly of IISA 370, RSA 371, end
RSA 372 Clutch Assemblies
R possibility exists that improperly assembled clutch assemblies
of ~SR 370, RSA 371, and RSA 372 Servos will not allow the servo
to disengage. The result will be an increase in the frictionforces the pilot has to overcome when manually controlling the
aircraft. The serial numbers of the affected servos are detailed
on Service ~emo t313 Addendum Revised, RPN 600-8313-51.
To eliminate the possibility of improper assembly in the future,the clutch has been improved. Service Fulletins KSA 370-5,55A 371-3, and RSA 372-1 identify the change to the clutch
assembly.
Ring desires to replace all servos which may he improperlyfrom the i date of thissssembleb. ver ninety (90) E;li; pay_rg~olYA c~ir(bta]letion. andservice memo revision, Ring
freight charges for exchanging gpy´•qt~ybmE serial number
appears on the serial in Service nemo (313
C Iddendu. Revised. Gre~iun freight charges one-rayand normal surf bel or eouivelent) freight chargesfor the return Ring will also cover the cost of inspectingan aircraft to determine if any of the listed servos are installedsubject to the following constraints;
A. The aircraft must have been delivered from the manufacturer or
field installaticn completed after August 31, 1981, and haveRSA 370, ISA 371, or nSA 372 Servos installed.
oR
The aircraft must have undergone maintenance and had a
RSA 370, RSA 371. or RSA 312 Servo changed out after
August 31, 1981.
R. inspection must take place within ninety (90) days from dateof issuance of this service memo revision.
To ensure payment for an inspeCtion (including servo removal 4odinstallation as required), submit the following:
i. Proof of new aircraft delivery from the manufacturer or fieldinstallation after August 31, 1981.
on
Proof that replacement servos were installed after
August 31, 1981 (log hook entry or shop order).
Date: 1982 Sn )313 Rev.i. December 5, 1904
SM0007-13 KPN 600-8313-01 Page: 1 of 2
2. An Ae~ standard warranty claim which indicates:r:
a. Peasonable actual time to accomplish inspection (includingremoval end installation as required).
b. Aircraft serial number end registration number.
c. Serial number of all servos inspected.
3. Copy of log book entry detailing the inspection or servo
replacement.
King will not pay for both an inspection and then an additional
labor charge to remove and reinstall the servos at a later date.
This offer to exchange servos and accomplish inspection expiresninety (90) days from the date of issuance of this service.memorevision. King will replace the affected serial number servos at
no charge after ninety days but labor charges will not be paid.
Date; Cay 14. 1982 SC 1313 ~ev.
Pev. i. December 6. 1989
Sn0007-13 leN 600-8313-01 Pager 2 of 2
4
SE RVICE MEIVIOC \Rnoio
SERVICE
SnLEs/ SERVICE neno No: 313 aadenaum aevisea
SVeJECT: Servo Serial Number Gist
KSA 370 RSA 371 8SA 372
3331 2031 1093 11823337 2032 1094 11833339 2043 1117 1184
3343 2044 1120 11853348 2045 1121 11863369 2046 1123 1187
3373 2047 1124 11903376 2048 1126 11923377 2049 1128 11943381 2050 1133 11953383 2051 1134 11983388 2061 1136 11993389 2063 1138 12053391 2064 1139 12083393 2073 1140 19103414 2083 1142 12153(11 2087 1147 12183424 2089 1152 12223427 2092 1158 12263429 2103 1159 12273438 2109 1160 12313445 2111 lie) 12333449 2113 1164 12373498 2134 1165 1238
2137 1166 12411174 12611177 12641179 1265
Date: Hey 14. 1982 Sn 1)13 rdnendum PevisedPev. i. Decembec 6. 1984
Sn0007-15 RPN 600-8313-51 Page; 1 of 1
5
)P"9~
s~-
ServiceGulfstreamAerospace
SERIVCE INFORMATION NO. 81-203
i: 21 February 1885
INLINE PROTECTION FOR FUEL AND OIL PRESSURE TRANSDUCERS
MODELS AFFECTED: MODEL 690C, SERIAL NOS. 11800 THRU 11?36.MODEL B90D, SERIAL NOS. 16001 THRU 15042.MODEL 696, SERIAL NOS. 96000 THRU 95084.MODEL BBSA, SERIAL NOS. 96001 THRU 86100.MODEL 6858, SERIAL NOS. 93063, 96069, 960?5, 960?8, 88085 AND 96201 THRU 96201.
REASON FOR PUBLICATION: SNUBBING OF FUEL AND OIL PRESSURE TRANSDUCERS, CONDUCIVE TOLONGER TP\ANSDUCER LIFE.
COMPLIANCE: AT OWNERS OPTION.
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILECOMPLYING WITH THIS SERVICE INFORMATION.CONTACT YOUR NEAREST GULFSTREAMCOMM*NI)ER I\UTHORISEDSERYICEKSER
sv WHOM WORK WILL Bf ACCOMPLISHEO: A g.P MECHANIC OR EQUIVALENT.
APPROVAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED.
ESTIMATED MAN HOURS: TWO (2) HOURS.
PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE INFORMATION MAY BE PROCUREDTHROUGH YOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR (8~0.15.REFERENCE THIS SERVICE INFORMATION, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHENORDERING SERVICE INFORMATION NO. 81-203 KIT CONSISTING OF THE FOLLOWING:
&TY PART NO. DESCRIP~ION
1 an. AC-1E Snubber4 se. 8-0421g02-116 Haee Asay2ea. S-0d21E08´•116 Bose Assy2 ea. 8-0421308-352 Hose Aasy18 in. 840005 (Code 3719200) Fuel Pressure IdentiBoation Tepe18 in. .940006 (Cede 311931(3) Oil Pleasure Identification Tape1 ea. ComplianceCard1 ea. Servi~e Information No. 81-203 Instructions
SPECIAL TOOLS: NONE.
ACCOMPLISHMENT INSTRUCTIONS:
1. Remove upper eowling from left and right engines.
Pagsloi4
8ERVICE INFORMATION NO. 81-205
-4-´• ;i’
i-- (j-0421E08-580C:,on. PRESSURE BOSE A89Y
;I
EXISTING 8-042lE0B-243f~ ,FUEL PRESBURE ROSE A88Y
i... (ReF)
j;´•
!7~.-ii
iii:i´•l--´•i:. ii´•~a;´•
WGr;i,.
alli
r
8
~UEL PRESSURE BOSE ASSY
BEFORE CHANGE.;,.,...i
:´•i:´•;L i:
S-- r
OIL PRESSURE BOSE A8SY
8-0421308-380
(RLF);isZ:.
’iL
4h~-lh i~d
i
~I´•
ic~"
,i
LEFT ENGINE SHOWNi R~i
RIGHT ENGINE TYPICAL
Figure 1.
Page 2 ol 4
:r-----´•----´•I--´•´•--;-´•´• ´•-i-.-i~l _,._~.
(IERYICE INFORMATION NO. 81-a09
a -0sa1E0e -Ile AL~-IE 8NOBBERFUEL PRESSURE 8-0411103-138
ROSE ASSY OIL PRESSURE HOSE ABSY
s-o*zlsoz-llas -o,21sas-aszOIL PRESSURE FUEL PRESSURE HOSE ASSEMBLY
ROBE
:j )APPLy 840005 OIL PRESSUREIDENTIBICATION TAPE
i´•: IDENTIFICATION TAPEAPPLY840005 PUBL PRESSURE
r´• (2 PLS)
iiit
i;(i)i:4s-a421Eo8-lle
’’‘e’´• FUEL PRESSURE-’IHOSE k58Y
s-o4alEos-a5zOIL PRESSURE
ROSE ASBY
AFTER CHANGE
o´•
dz~76 n
li-´•
4x,:.iiz~i;
LEFT ENGINE SHOWN
RIGHT fN G IN E TYPICAL i~_.
Figure 2.
Page Sell
SERVICE INFORMATION NO. 51-203
a Rrnlur..nd dia.aFd pliami. oil ho´•s aumbl" (RN 90121EM980) rod fu. prsa~uls hose ouambl~(PIN 5-0421E08-2431 from left and right engines (refer to Figure 1).
8 Install AC-1E snubber between S-0421E02-116 hose assembly and S´•0421E08-116 hose assembly. Connect theothe,´• end of 5-0421102-116 hose assembly to fuel pressure transdueer fitting on engine firewali assembly andconnect the other end of 5-0421E08-116 hose assembly to fitting an engine (refer to Figure 2).
4. Install AC-IE snubber between S-0421E02-116 hose assembly and 5-0421108-252 hose assembly. Connect theothel´• end of 5-0421302-116 hase assembly to ail pressure transducer fitting on engine Arewall assembly andconnect the othel´• end of 8-0421808-262 hose assembly to fitting on engine. Use existing clamps and hardwareto secure hose assemblies (refer to Figure 2)
5 Apply 940005 fuel pressure identification tape to both ends of applicable 5´•0421102-116 fuel pressure hoseassemblies (refer to Figure 2).
6. Apply 0~10005 ail pressure identification tape 0 both end. of applicable 5-0421302-116 oil pressure hoseassemblies irefer to Figure 21.
7 Functional check to assure no leaks are evident.
8. Reinstall upper cowling´• on left and right engine..
9. Fill out and mail Compliance Card.
ELECTRICI\L LOAD: NO CHANGE
WEIGHT AND BP.LANCE: NO CHANGE.
SPARESAFFECTED: SPARES TO PROVIDE NEW HOSE ASSEMBLIES IN LIEU OF 5´•0421B08-245 AND/ORS-0421E08-380 HOSE AISEMBLIES.
PUBLICllnON6 LlfEDIED: Tbs *i~iane Neinteoan.a ibsnu.l .od illusbotsd Pehs Ontol~ chansal .a~juind bgthis document will be incorporated at the next scheduled revision.
RECORD COMPLI*NCE: Make an appropriate entry in airplane maintenance record. as follows: Se.vice InformationNa. SI´•203, dated 21 February 1985. entitled "lnline Protection for Fuel and Oil Pressure Transducers", accomplished
(date)
Page40f4
SE RVICE PUB LI CATIONS
YeVISlOn notice Gulfs~reamAerospace
SERVICE INFORMAT?ON NO. 8I´•20´•1REVISION NO. 1
8 January 1881
OVERBOARD ROUTING OF CABIN EXHAUST AIR
This Revision Notice i. being isausd to delete Model B90C, 8erial Nos. 118(10 thru 11111 and Model 685, Serial Nos.95000 thru 85084. Model and Serial No, ef~ectivities are changed to read as follows:
IODELSIFFECTED: MODEL 6900, SERIAL NO8. 11112 THRU 11?55.MODEL 690D, SERIAL NOS. 15W1 THRU 15042.MODEL 696A, SERIAL NO8. 98001 TEED 98100.MODEL 6968, SERIAL N0S. 96063 96069, 96016, 960?8, 88085 AND 86201 THRU 96205.
Page 1 of 1
_´•
Service informationGuffstreamAerospace
SERVICE INFORMATION NO. SI-204
July 7, 1986
OVERBOARD ROUTING OF CABIN EXHAUST AIR
MOOELS ~FFECTEO: MODEL 690C, SERIAL NOS. 11600 THRU 11136.MODEL BBOD, SERIAL N0S. 16001 THRU 15042.MODEL 695, SERIAL NOS. 86000 THRU 95084.MODEL 696A, SERIAL NOS. 88001 THRU 96100.MODEL BgSB. SERIAL NOS. BBO03, 8069, 95075, 96078, 96085 AND 96201 THRU 96203.
REI\SON FOR PUBLICI\TION: TO ROUTE AIR FROM CABIN OUTFLOW VALVES DIRECTLY OVERBOARD ANDELIMINATE HUMIDITY, FROM CABIN, FORMING FROST ON ELECTRONICEQUIPMENT LOCATED ON UPPER NOSE DECK.
COMPLIPINCE: AT OWNER’S OPTION RECOMMENDED FOR AIRPLANES BASED IN OR FREPUENTINGHIGH HUMIDITY AREAS.
NOTI
IT )ih~ PROBL&LaB *RS BNCLIUNTBRFD WHaECOMPLYING WITH THIS SERVICE INFORMATION,CONTACT YOUR NEAREST OULFSTREAMCOMMANDER AUTHORIZED SERVICENTER.
BY WHOM WORK WILL BE ACCOMPUSnEO: A L P MECHANIC OR EQUIVALENT,
PIPPROVAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED.
ESTIMITEO MIN HOURS: THIRTY-FIVE (55) HOURS.
PARTS D*TA: PARTS REQUIRED TO COMPLY WITH THIS SERV1CE INFORMATION MAY BE PROCUREDTHROUGH YOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR )820.04REFERENCE THIS SERVICE INFORMATION, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHENORDERING SERVICE INFORMATION NO. SI´•204 KIT CONSISTNNI OFTHE FOLLOWING:
qTY PART NO. DESCRIPTION
2 ea. ANI-SA Bolt4 ea. AN?S’ITW10? Clamp
12 ea. AN960D06 Washer2 ea. AN860D10 Washer2 ea. MSZ1047L3 Nutplste6 ea. MS21069L06K Nutplats
I~ra MS96206-229 Sc~ewI se. NCllS´•13-29-4 DuelI as. NC225´•13-52´•4 Duet
C
Page 1 of 11
SERVICE INFORMATION NO. SI-204
Is.. Doubler*~y C1 se. 310181-126 Doubler
1 ea. 830156-11 Strip Assy1 se. 880018-503 Vent
1 as. 880113-5 Doubler
2 se, 880114-3 Shroud HalfAssy2 ea. 880714-5 Shroud Half Assy1 se. 8801165 Shroud Assy1 se. Compliance Card
1 ea. Service Information No. SI-204 Instructions
SPECllLTOOLS: NONE,
nCCOMPLISHMENT lNSTRtlCTlONS:
I CIYII.N~IC*VTION
Care should be taken so as not to damage outnow valves
and hoses when performing this modification.
i. Remove upper door assembly from fuselage nose section to gain secess to outnow valves located on forward
pressure bulkhead (rsfar to Figure i).
i. Remove left side and left lower aeeeas doom from fuselage nose section and remove duct to facilitate installation
of e~hauat vent (refer to Figure 1).
i. RBm~YD LR lond"p llsht nsl´• as ~uilm*i in Ch´•pts SS ~Lh´• AliplnnL Msintanaors ManualRemoval of landing light is to facilitate installation of 880113-3 doubler.
4. Remove outnow valves as outlined in Chapter 21 of the Airplane Maintenance Manual.
5. Disconnect flex duct from ram air check valve and remove flen duct from fuselage nose section.
6. Locate and make a cutout in lower left fuselage nose shin for installation of 880113-3 doubler, 510944-13 doubler
assembly and 880018-603 vent. Cutout for vent and doublers is to match enisting vent and doubler cutout on
lower nght side offuselage nose (refer to Figure 1).
7. Locate and drill 880115-3 doubler, 310944-13 doubler assembly and 880018503 vent on lower left fuselage nose
skin (refer to Figure 2).
8. Dimple fuselage akin, 880115-3 doubler, 510944-13 doubler assembly and 880018´•503 vent to acceptMS20426AD4 rivet heads (refer to Figure a).
9. Install 880113-3 doubler, 310944-13 doubler assembly and 880018-603 vent on lower fuselage nose skin usingMS20426AD4 rivets (reBr to Figure 2).
C
page 2 of 11
SERYICE INFORMATION NO, 51-204
(-1 10. Ii rlprso Dwr unit is inltdlaiun nEsa dsi* in una uhers 31nls1-121 dmbl~r i´• to to in.tailpd, r.l~ile
s~e,ra power unit as shown in Figure 3.
NOTE
It is aceeptable to leave the original stereo power unit
attaching holes open in nose deck.
11. Remove existing rivets in area where 810181-126 doubler is to be installed (reEer to Figure 4).
12. Relocate 0.250-inch diameter hole in nose deck for routing landing light wire (refer to Figure 6).
13 Position 31[)181-125 doubler on nose deck, locate and make a cutout in left side of upper nose deck (refer to
Figure 41.
14. Drill and install MS2104?L3 nualate (2 plaees) on leR side of upper nose deck. Holes for nutplates are to matchholes in 310181-125 doubler (refer to Figure 5).
15 Locate, drill and install 310181-125 doubler on left aide of upper nose deck (refsr to Figure 51
16. Locate, drill and install M821o89LoBK nutplate (8 places) on aEt side of forward pressure bulkhead. Brush coat
seal around rivets and nutplates using sealant and sealing procedures outlined in Chapter 20 of the AirplaneMaintenance Manual (refer to Figure 6).
17. Reinstall out0ow valves as outlined in Chapter 21 of the Airplane Maintenance Manual.
18. Functional check outnow valves as outlined in Chapter 21 olthe Airplane Maintenance Manual.
19 Touch up paint on nose deck, as necessary, using zinc chromate primer.
to. Instail 880714-5 ahmud ball aaasmbly is pls~rsi end 881116 ahraud hall ssssmbly IZ jllBF~S) Un FDFWBFd
pressure bulkhead using M535206´•229 screw (12 places) and AN9jOD06 washer (12 places) (refer to Figure 7).
21. install 880116-3 shroud assembly on left side of upper nose deck using AN3-6A bolt (2 placesi and AN960D10washer (2 places) (reEer to Figure 7).
22. install NC22S´•13-29-4 duet and NC22S´•13´•52-4 duet on shroud assemblies using AN737TW107 clamps (reEer to
Figure 7).
23. Reinstall left landing light on fuseless nose as outlined in Chapter 33 of the Airplane Maintenance Manual.
24. Reinstall hex duet on ram air check valve and lower left secess door using existing hardware.
25. Reinstall left side and left lower access doers an fuselage nose section using existing hardware
26. Reinstall upper door aa~iembly on fuselage nose section using existing hardware.
27. Touchup paint on fuselage nose section as necessary.
28. Fill out and mail Compliance Card.
C
Page 3 of 11
SERVICE INFORMATION NO. SI-204
REMOVE THISDOOR ~gsy
-"9
LOWER LEFT
J
ACCESS DOOROPENIN(I IREFI
REMOVE THESEACCESSDOORS
AFTEDOEOFFUSELPIOE SKIN
~n C_
’a.so´•´•
CUTOUT IN SKIN TOMATCH CUTOUT IN b~ssmls´•s DOUBLER I ~J I
’’L´•,
TRUE DIMENSIONALONGCONTOUROF FUSELP~(IE SKIN
’7.75"
STA STALOWER EDGE OF 5.50
VIEW LOOKING UP SKIN
AT FUSELAGE NOSE
Fieurs 1.
PaCe 4 of 11
SERVICE INFORMATION NO. SI-204
C a-~
--i-´•,
Osr,´•4.W S.BO
MSZOIZBPIM RIVET880713´•3 DOUBLER I3JPLs)(TRIM AS NECESSARY)
;I -t- c t´•1.26"
_
880010603 VENT
t- f(I 31(Wd4´•13DOUBLERAS8Y
rl CI_I+
I-; f \’Rt
;I+ c+III-’-
MF2042B~D4 RIVET118 PLSL
c~Y´•
ExlsnNo HOLEMSzol28aon nlvET
I1PLSI j.
NOII
THE 880713-1 DOUBLER IS
CVIIW LOOKINGDOWN LIFTZIOE INSTALLED ON THE INSIDE
AT LOWER FUSELAGE 5KINSURFACE OF THE SKIN
Filule 3
Page 5 of 11
SERVICE INFORMATION NO. SI-204
r.
STA
~t6.50´•1 -1 830135´•11 STRIP
~lil s.la .y/ aJo~NOSE DECK
IRE FI
EXISTING STEREOWWER UNIT
(REFI
-I---
i’ InEFI
Lt~CTc~++
LEFT NOSE SEAM
ASSY FI\STENERSIREF)
B li~in
VIEW LOOKING DOWN
ON NOSE DECK
Fieura 3.
Page 6 of 11
SERVICE INFORMATION NO. 51´•204
sra´•12.0
EDGEOFCUTOUT ~1I7IREFI
t t+FUIELAOE
t h +5 t f ~kOES:IOECKEDGE OF I I A\)CCUTOUT +T~
o.85´•´•n
+iIREFI
:i EOGEOFCUTOUT
iIREFI
Jilt3.15~´•
f llJ C,
C’ 310101-121t ;i i IREFIOOUsLER
-VS5- X
310181´•126 DOUBLER
iEOOEDFCUTOUTIAEF1
C VIEW LOOKING DOWN
ON NOSE DECK
VIEW A-AFi(lur´• 1.
Page 7 of 11
SERVICE INFORMATION NO. 81-?04
-\eVIEW LOOKING DOWN
ON NOSE DECK
’~I,IF FLITE PHONE iS
O INSTALLED PICKUP EXISTINGHOLE AND DELETE EXISTINGSPACER AT THIS LOCATION
STI\ QFusELaaE
´•tz.a
NOSE DECKIREFI
MS20428A04RIVET i
f ~Ba a
a
´•Ilcl.m6.751´•
el L I I J.o.lse~o.zololn HOLE
f NOSE DECK
Q a PLSL
a
a
aTHIS HOLE IN
NOSE DECK 2.5(1" AFTnhlo aN sAmE suTr
LINE IRL1 AS EXISTING
MS204281\D4 RIVET 0.2~0´•´• DIA HOLE
FLUSH HEAD IN NOSEi. ILANDIN(I LIGHT WIRE
DECK ITHESE TWO tnOLEl
EXISTING RIVETS DO ZNOT PICKUP DOUBLERI
Icll~310181-125 DOUBLER
LEGEND: flNDIC~TE)EXISTINOHOLE IMU*IO~D4 RIVET)EXCEPT AS NOTED.
O IF THIS RIVET HOLE INTERFERES~L INDICATES ADDED WITH LANDING LIGHT WIRE HOLE.
MS?W281\04 RIVETS FLUSH PLUG HOLE IN DOUBLER
I\NO RELOCATE HOLE. MI\INTI\INja INDICATES ADDED EDGE DISTANCE OF 1 x Dll\.
MS20470~D1 RIYETS- OF RIVET PLUS O.DB’~.
Figure 5.
pago 8 of 11
SERVICE INFORMATION NO. SI-2U4
AtRcnnFT
I)IA. HOLE
MSZIOBBLOBK NUTPL*TEoN *FT SIDE OF BULKHEAD
(3 PLSI
6~"’ I.ss´•´•
c 1-I-UPPER OUTFLOWAAFETYYALVE HOLE LREFI
0
LOWER OUTFLOWISAFETYVI\LVE HOLE IREFI
C:, r/-3´•16 O
~.g´•´•Ij
r%
D1A. HOLEMSZIOBBLOBK NUTPLATE
ON AFT SIDE OF BULKHEAD
C VIEW L001(ING AFT AT LEFT
SIDE OF FWD PRESSVRE BULI(HEAD
Figure 6.
Page 9 of 11
SERVICE INFORMATION NO SI-204
SIOl(a38HROUDHALF ASFY
880114´•SSWROUDAN737M1107 CLAMP I HALF A9SY
PPLSI
FWDPRESSUAEBULKHEAD
IRBF1
NC228´•13-28´•4
DUCT
i ~C I~-’ 880714´•3 SHROUDHALFASSY
i ,,,,,,,,,,,,,,.s3szoa´•22escREwNC22S´•13-S211DUCT
r
I11PLSI
i880715-39HROUDASEY
I\N3´•S~ BOLTi\NBB0010WAIHER I I FUSELAOB NOSE
(2 PLB) I DECK IREFI
Fi(lYn 7.
Pnge 10 of II
SERVICE INFORMATION NO. 81-204
j EL.CTRICIL LD~O: NO CH*NDE.
WEIGHT AND IPIL~NCE: The weight and balance ehanpe due to instailation olthia Se~vice information is as Follows:
WOICIHT (LR8) H´•ARM (INCHESI II-MOMENT+6.19 48.96 264.0
SP*RES AFFECTED: NO
PUBLICATION8 AFFECTED: The Illustrated Parts Catalog change required by this document will be incorporated atthe nert scheduled revision.
RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Ssrvice InformationNo. SI-204, dated July 1986, entitled "Overbaard Routing of Cabin Exhaust ae~ompliJhed (date)
i
Paec 11 or ii
Service InformationC
SERVICE INFORMATION NO. Sb106
8April 1985
EXHAUST STATIC PRESSURE nOSE ASSEMBLY REPLACEMENT
MODELS AFFECTED: MODEL 895, SERIAL NOS. 91000 THRU 65084.
MODEL 8964 SERIAL NOS. 98001 THRU 96200.
MODEL BB~B SERUALNOS. 96063, 96069, 96075, 96018, WW)66, 96201 THRU 96999.
REASON FOR PUBLICATION: TO REDUCE THE POSSIBLE FAILURE OF TAE EXHAUST STATIC PRESSURE
HOSE ASSEMBLIES DUE TO HEAT HARDENWG.
COMPLIANCE: AT OWNER’S DISCRETION.
NOTE
[F ANY PROBLEMS ARE ENCOUNTERED
COMPLYING WITH THIS SERVICE INFORMATION,CONTA~T YOUR NEAREST GULFSTREAM
BY WnOM WORK WILL BE ACCOMPLISHED: A d P MECHANIC OR EQUIVALENT.
APPROVAL: ENOINEERINO DESIGN ASPECTS ARE FAA APPROVED.
ESTIMATED MAN FIOURS: TWO (2) HOURS.
PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE INFORMATION MAY BE PROCURED
TMROUOH YOUR NEAREST OUI.FSTREAM COMMANDER AUTHORIZED SERVICENTER FOR 8187.74.
REFERENCE THIS SERVICE INFORMATION, AIRCRMT MODEL AND FACTORY SERIAL NUJIBER WHEN
ORDERING SERVICE INFORMATION NO. S1a05 KIT CONSIST~O OP THE FOLLOWWO:
9TY PART NO. DESCRIPTION
2 se. 830378´•653 Tube Aaay2 ea. AN818~41 Union
4 se. ANSBO-1OL Washer
4ea MS21WW Nut
(es. MSa1919H4 Ckmp4 ea. MSa1819812 Clamp4 ea. M911039CI´•o8 Scnwa ea. s-otnmoz´•oao Aasy1 ea. Card
1 ea. S´•rvies Informstioll No. SI-a(M InsPueti~os
(a
PaSe1 of 1
Clly..
SERVICE INFORMATION NO. SI-Z05
BEFORE CHANGE
F1REW~LL
HOSEaFsY (REFI
REMOVE EXISTIN(ISW21EOBQn EXHPIUSISTATICHOSE ASSY
EN(IINE TUBEASSY (REF)
TEMPERATURECONTROL (REF)
VIEW LOOKING AT LEFT SIDE
TYPICAL BOTH ENGINES
Figure 1. (2hes)l~( 2)
P~e 2 d 4
SERVICE INPORMAT~ON NO. 8b205
AFTER CHANGE
FlnEwaLL IREF,
S0421E02´•080HOSE ASPY
L~n) cLnw cs
~N9BO´•1OL WPSHER
M821042L3 NUT
nOSE489Y IREFL
P1N81841 UNION
80376883 TUBE ~SSY
ENOINBTUBE~ISY(RBFL
IEMPERI\NReCONTROL IRIFI
VIEW LOOKING AT LEFT SIDE
Ms2181sn4 CLaMP (21~ TYPICAL BOTH ENGINESM927~9C1´•08SCREW*NgBOIOLW1\8HeRMta1042WNUT
Fipur´• 1.(5h´•´•t2 or 2)
Pnge3~14
EIERVICEINPORMATION NO. 91-205
SPECIAL TOOLS: NONE.
INSSRUCTIONS:
1. Remove upper and right side cowling from leR and right engines.
2. Remove and discard existing left and right e~hauat static pressure hose assemblies PIN 9-0421308-211 (rsPer to
Figure 1, Sheet I of z).
5. Install C04alE02-080 hose assembly, AN816U uniah and 650516883 tube assembly on left and right engines(refer to Figure 1, Sheet 2 of 2).
4. Secure the 9´•0821301´•080 hole assembly to the existing pitot hose assembly using MS2191PH12 clamp (2
places), M8210S8C1-08 screw, ANBGO-1OL washer and MSZ10112LS nut (refer to Figure 1, Sheet 2 of 2).
5. Secure the 650578-858 tube alsembly to existing engine tubs assembly using M821919B4 clamp (2 places),M921098C1-08 screw, ANOBQ1OL waahsr andM821042LS nut (refer to Figure 1, Sheet 2 of 2).
6. Functional cheek for leaks.
Reinstall upper and right side Eowling on left and right engines.
8. Fill out and mail Compliance Card.
ELECTRICAL LOAD: NO CHANCE.
WEILIHT FIND BALANCE: NO CHANGE.
9PI\Re9 AFFECTBO: NO.
PUBLICATIONS AIPECTEED: The Illustrated Parte Catalog change rsquirsd by this document will be incorporated at
the next scheduled revision.
RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Service information
No. 91205, dated 8 April 1958, entitled Exhaust-Static Pressure Hose Aesembiy Replacement", accomplished(dats)
Page 4 of 4
’r. r-
~SllService :Infovmation Culfslream Rerospaee Corpanrion
OLUnom CiN. OXlbhMu 73121
SERVICE INFORMATION NO. SI-10612 April 1985
NEGATIVE TORQUE SENSOR (NTS) SWITCH RELOCATION
MODELS AFFECTED: MODEL 880, SERIAL NOS. 11001 THRU 110?9.
MODEL 690A, SERIAL NOS. 11100 THRU 11344.
MODEL 59011, SERIAL NOS. 11360 THRU 11566.
MODEL 590C, SERIAL NOS, 11800 THRU 11999.
MODEL 690D, SERIAL NOS. 1601 THRU 15999.
MODEL 696, SERIAL NOS. 96000 THRU 95054.
MODEL 695A, SERIAL NOS. 96001 THRU 96200.
MODEL 6968, SERIAL NOB. 96063, 96059, 96015, 96018, 96088 AND 96201 THRU 95999.
REASON FOR PUBLICATION: TO RELOCATE NTS SWITCH TO A MORE SECURE AREA PREVENTINGPOSSIBLE SWITCH WIRE FAILURE.
COMPLIANCE: AT OWNER’S DISCRETION.
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILECOMPLYING WITH THIS SERVICE INFORMATION,CONTACT YOUR NEAREST GULFSTREAMCOMMANDER AUTHORIZED SERVICENTER.
BY WHOM WORK WILL Be ~CCOMPLISHED: A B P MECHANIC OR EPUIVALENT.
APPROYAL: ENGINEERING DESIGN ASPECTS ARE RAA APPROVED.
ESTIMATED MAN HOURS: FOUR(B) HOURS.
PARTS DATA: PARTS REQUIRED TO COMPLY WITH THIS SERVICE INFORMATION MAY BE PROCUREDTHROUGH YOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED SERVICEESPE~R FOR: KIT NO. 1 1281.46OR KIT NO. 2 5358.49. REFERENCE THIS SERVICE INFORMATION, AIRCRAFT MODEL AND FACTORY SERIALNUMBER WHEN ORDERING INFORMATION NO. SbloB KIT CONSISTING OF THE FOLLOWING:
hla ~vllmmn
Kit Na. 1- Models 880, 6g0A:snd 690B,Kit No. 2 Models 590C, 890D, BgB.-BgbA end 69511.
Kit Kit
No. 1 N~.,2BTY QTY PART NO. DESCRIPaON2 ea. a os. 6305’16-851 Tube Assy2 ea. 2 os. 800040-415 Restrictor2 ea. 2 ea. ANB288*L Nut2 os. 2 os, AN785~-4 Tee
2 ea. 2 os. AN8t14 Plug8 ea. 8 ea. SOS10904T O´•RingZ ea. 2 os. 80811-804 Backup Ring2 so. 8104961E1 Hose Artsy
2 ea. 80421306244 Hose Asuy1 ea. 1 ea. Compliance Ca~d1 os. 1 os. Se~iea IDlonnation No. 51´•206 Instructions
Pi~e t oi 4
SEILVICE INFORMAT?ON NO. 91´•206
d LEFT ´•INSTALLATION 9HOWNRIGHT INSTALLATION TYPICAL
laslrloa soxEXlsTINoIRIP)
a
i
rvplcnLEN(IINB I\SPY
(ReFI
ehlalNE EXISTING
"*"’:k9~9 ’6C/
MODELS 890. 690AAND 6909
EXISTING BETAPRESSURISWITCH
IREF)eXlsTINo otLIUPPLYHOSE(dePi
ExmlNoloNlnoN BOX
IREFI
EN(IINE MI\NIPOLD(REF)
eXlsTINOANB2aBd NUT
fRNPFIBWOBZ´•445 RfSTRICTOR
EXISTING~N81Sd UNION
(ReFIExlsnNa sernPnEsnuRa swncHIRePI
exlSrINo olL EXlsnNoQUPPLY WOSE ~N84(d ELBOW
IREP) IRfiF)
MODELS 6900. BgOD. 695. 695AAND 8958BEFORE CHANGE
Pl(iure i.
PageDol(
SERVICE INFORMATION NO. SI-POB
LEFT INSTALLATION SHOWN
RIGHT TYPICnL
bi
i ’R""
TYPICALENIIINB A8SY
L;
d.
aEN(IINE MANIFOLDIRE Fl
EXI8TIN(IBOX
IREFI
SaS1DB04TORINOISAFETY WIRE PLU(II
~311´•BM 840KUP RIN(I9(100404´•71 RESTRICT~R
ANBZ88´•4 NUTBOI10´•BMTO´•RING
83MB´•861TUBE A85Y
Om(DB04TO´•RIN(iEX1STINB NTS SWITCH
(SAFETY WIRE SWITCH)
EX18TIN(I BETAAN714 PRESSURE SWITCH
ISAFETY WIAE SWITCHI
810484RE~1 HOSE ASSY(MODELSBBO. BBO*, AND BBOB)
gW21EO~´•244 HOSE A89YIMODELS 8800. 8900. 889. 896* AND 8888)
ALL MODELS
AFTER CHANGE
iieurs 2.
Psga3o14
SERVICE INFORMATION NO. SI´•208
SPECIAL TOOLS: NONE.
ACCOMPLISHMENT INSTRUCSIONS:
i. Remove lower cowling from left and right engines.
2. Disconnect electrical connectors ham NT9 switch and Beta Pressure switch (refer to Figure i).
S. Remove and discard existing oil supply hose assembly (refer to Figure i).
4. Remove existing NTS switch and Beta Pressure switch and retain both switches for reinstallation (refer to Figurei).
5. On Models 6B0C, 680D, 895, 696A and 685B, remove and discard existing elbow (P/N AN941-4), restrictor (PIN
900092416) and nut (P~ ANB289-4) fi´•om engine manifold (refer to Figure ii.
B. Remove and discard existing union (PIN AN811~4) from engine manifold (refer to Figure i).
7. Discard existing aringll and ring(sl.
8. install ANB144 plug and SoS10904T a´•ring in engine manifold port that NTS switch was originally installed
in. Safety wire plug (refer to Figure 2).
9. Install AN?83´•4 tee, S-031090PT o-ring, 90911904 backup ring and ANBls9-4 nut on engine manifold. Position
"branch" of tee facing forward along ignition box (refer to Figure 2).
10. Install existing NTS switch and S0310-904T oring in AN?83´•4 tee and safety wire switch (refer to Figure 2).
11. Install 800040-475 restrictor and S0910-804T oring on engine manifold (refer to Figure 2).
12. Install 830518-667 tube assembly on 800040-418 restrictor (refer to Figure 2).
13. Install existing Beta Pressure switch on 830378667 tube assembly and safety wire switch (refer to Figure 2).
14. Install 810494-RE1 hose assembly (Models 690, BgoA and 6808) or 5-0421105´•244 hose assembly (Models 890C,
690D, 885i 696A and 695B) and secure hose assemblies with existing dames and hardware (reEsr to Figure 2).
15. Reconnect existing electrical connectors to NT8 switch and Beta Pressure switch and safety wire connectors.
NOTE
Due 0 relocation of NTS switch, NTS switch connector may
not reach switch. Butt spliced extension of electrical wiringis acceptable.
16. Cheek installation far leaks by running anginas.
17. Function check both NTS and Beta systems,
18. Reinstall lower cowling on left and right engines.
19. Fill out and mail Compliance Card.
ELICTRICAL LOAD: NO CHANCE.
WEIGHT AND B~WNCE: NO CHANGE.
SPARES AFFECTED: NO.
PUBLICATIONS APPECTED: The Airplane Maintenance Manual and Illustrated Parts Catalog changes required bythis document will be incorporated at the next scheduled revision.
RecORD COMPLI*NCE: Make an appropriate entry in airplane maintenance records as follows; Service information
No. SI-208, dated 12 April 1986, entitled "Negative Torgue Sensor (NT9) Switch Reiocation", accomplishedidate)
ppgsdoi(
Service InformationGulfstreamC: Aerospace
SERVICE INFORMATION NO. 8I-211
30 June 1886
GARRm TURBINE ENGINE COMPANY SERVICE BULLETIN NO. TPETTSE331´•74-0003
MODELS AFFECTED: MODELS 680T, 680V AND 880W, SERIAL NOS. 1413 THRU 1850.
MODEL 681, SERIAL NOS. 8001 THRU 60?2.
MODELS 690, 690A AND BBOB, SERIAL NOS. 11(101 THRU 11868.
MODEL 69OC, SERIAL NOS. 11600 THRU 11?36.
MODEL 690D, SERIAL NOS. 16001 THRU 16042.
MODEL 685, SERIAL NOS. 86000 THRU 95084.
MODEL 695A, SERIAL NOS. 88001 THRU 88100.
MODEL 695B, SERIAL NOS. 88201 THRU 86208.
REASON FOR PUBLICATION: TO RECOMMEND COMPLIANCE WITH DARRET~ TURBINE ENGINE COMPANY
(OTEC) SERVICE BULLETIN NO. TPEITSE831-740003.
COMPLIANCE: REFER TO CTEC SERVICE BULLETIN NO. TPEiT8E9S1-14-oo03.
BY WHOM WORK WILL BE ACCOMPLISHED: REFER TO GTEC SERVICE BULLETIN NO. TPE~8E331-?(-0003.
*PP.W*L: RaPBRTOGTBC SERYICE BULLETM NU.TPEnsEIll-?ld00S-
ESTIMATED MPIN HOURS: REFER TO GTEC SERVICE BULLETIN NO. TPEiT8E931-14-000S.
PARTS DATA: REFER TO GTEC SERVICE BULLETIN NO. TPE11~9E331-14-0003.
SPECIAL TOOLS: REFER TO (ITEC SERVICE BULLETIN NO. TPEi~SE331-14-000S.
ACCOMPLISHMENT INSTRUCTIONS:
1 Comply with Garrett Turbine Engine Company Service Bulletin No. TPEI~SE331-?il-0003.
2. Fill out and mail Compliance Card.
ELECTRICAL LOAD: NO CHANGE.
WEIGHT AND BALANCE: NO CHANGE.
SPARES AFFECTED: NO.
PUBLICATIONS AFFECTED: NONE.
RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Senriee InformationNo. SL-2I1. dated 30 June 1986, entitled "Garrett Turbine Engine Company Service Bulletin No. TPEPI~SE331-14-0003,"
accomplished (date)
i
Page 1 of 1
I~ SERVICE BULLETI#1,
GARRETT TURBINE ENGINE COMPANY
REVISION TRANSMITTAL SHEET
This sheet transmits Revision 3 to Service Bulletin No. TPE/TSE331-74-0003titled ENGINE IGNITION Replace Ignition Unit.
This is a COMPLETE revf sion. This bulletin has been reprinted in its entirety.Please remove and discard all pages of prior issues and replace with pages ofthis revision.
Reason for Revision:
NOTE: Equipment modified in accordance with a previousissue of this service bulletin does not requirefurther rework.
This service bulletin is revised to add duty cycle information, toadd engine models and to update format.
Section 1
Paragraph A is revised to reflect latest engine applications.C
Paragraph B is revised to reflect latest duty cycle limits.
Paragraph C through L are revised to reflect latest fo~mat.
Paragraph J is revised to add engine models.
Section 2
Accompl i shment Instructions are revl sed to reflect latestformat.
Section 3
Material infolmatlon is revised to reflect latest prices andformat.
.ist
oate oate
1 ~lar 24/06 6 Mar 24/062 Mar 24/86 7 Mar 24/863 Mar 24/86 8 Blank4 Mar 24/86 9 Mar 24/865 Mar 24/86 10 Blank
C
Mar 24/86 TPE/TSE331-74-0003
Page 1 of 2Copyright 1986 by The Garrett Corporation
2´•
SERVICE BULLEBIWGARRETT TURBINE ENGINE COMPANY
Plsulour Revirlonr:
Revision 1 dated June 22/82Revision 2 dated Dec 2/82
Ma r 24/86 TPE/TSE331-74-0003
Page 2 of 2
I~ SERVICE BULLB~WWIGARRETT TURBINE ENGINE COMPANY
CENGINE IGNITION Replace Ignition Unit
NOTE_: This Service Bulletin is revised to add duty cycle information.
A. Ef fectl vl ty
This service bulletin is applicable to the following turboprop aircraftengines.
Prior to
Part No. Model No. Serial No. ~eplicatlon
R 865912-1A-61 TPE331-25AA Mitsublshl MU-LB-1A-7/-1A-8/-1A-9
R 865912-10-51 TPE331-25DA Falrchlld Porter PC-6/-10-6/-10-71 C-n2-10-8
R 865912-1F-51 TPE331-25FA Porter/Volpar-1F-6/-1F-71
-1F-8R 867940-1-41 TPE331-43A Turbo Commander 680T
R 867970-1-5/ TPE331-47A Turbo 18
-1-7 680V
-1-6/-1-7/-1-8
R 893290-1-1/ TPE331-25AB Mitsubishi MU-2B/-2D-1-2
R 893310-1-1/ TPE331-2508 Fairchlld Porter-1-2
R 893270-1-1/ TPE331-43BL Turbo Commander 680W i
-1-3/-1-4/ 581-1-5
R 893330-1-1/ TPE331-55B Jetllner 600 (Oove)-1-2
R 893130-1-1/ TPE331-1-100F *14003 Pilatus Porter
R 893400-1-1/ TPE331-1-1O18 *93073 Turbo 18/-2 Turbollner
R 894120-1-1/ TPE331-1-101E *95005 Jetliner-2 600 (Oove)
896760-1/-2/ TPE331-1-lOlF *98042 Peacemaker-3/-4
R 3101850-1 TPE331-1-101Z *34032 S2R TurboR Thrush/MarshR Turbo Ag Cat
893250-1-1/ TPE331-1-151A "93258 Mitsubishi-2 MU-20P/-2F/-2G
C R 869595-1-1/ TPE331-1-151G *91198 Merlin IIB-2
Apr 14/82 TPE/TSE331-74-0003Revision 3, Mar 24/86 Page 1 of 10Copyright 1986 by The Garrett Corporation
/~ISEWVICE BULLETBWGARRETT TURBINE ENGINE COMPANY
Prior toPart No. Model No. Seria~. Application
3101260-1/ iPE331-1-151K *26102 Century Turbo-2 Commander
R 869480-1-1/ TPE331-2-201A *90373 Skyvan
894820-1-1/ TPE331-2-201C *08024 CASA 212
R 894980-1/-2 TPE331-2UA-203D *97004 GooseR 894040-1/-2 TPE331-3U-303G *03451 Merlin III/
or or
895880-1/-2 TPE331-3UW-303G *05067 IVA/Metro/Metro II/Metro IIA
3101800-1 TPE331-3U-303V *32015 CenturyJetstream III
R 3102550-1! TPE331-3U-304G f03743 Merlin III/R -2/-3/-4
IVA/Metro/Metro II/Metro IIA
R 894870-1/-2! TSE331-3U-303N +07024 Helitec CorpR -3/-4 S55T
815950-1-1/ TPE331-5-251C *22370 CASA 212-100-2/-3
R 895720-1/ TPE331-5-251K *40101 Jetprop Commander-2/-3 690/590A/6908
3102200-1 TPE331-S-252D *39011 Dornler 228R 3102520-1 TPE331-5-252K *40461 Jetprop Canmander’
690A/69083101840-1 TPE331-5-252M *33092 Mitsublshi
MU-2N/-2PR 3102520-2/-3 TPE331-5-254K "40393 Jetprop Commander
iR 6900/6900R 895720-4 TPE331-5-255K "40101 Jetprop CommanderR 690/690A/690B
896150-1/ TPE331-6-251M *20602 Mltsubishi-3/-5 MU-2J/-2K/-2L/-2M
3101630-1 TPE331-6-2528 *27263 Beech 81003101300-2 TPE331-6-252M *30048 Mltsublshl
MU-2J/-2K/-2L/-2M3102450-1 TPE331-6A-251M *44250 Mitsublshi
MU-2J/-2K/-2L/-2M3101300-3 TPE331-6A-252M *30066 Mitsubishi
MU-2J/-2K/-2L/-2MR 3101470-1/-3 TPE331-8-401S *31705 Conquest iIR 3102510-1/-5 TPE331-8-402S *31604 Conquest iIR 3102510-2/-9 TPE331-8-403S *31604 Conquest IIR 3101470-2/-4 TPE331-8-404S *31705 Conquest II
3102170-1/-2 TPE331-10-501C *37160 CASA 212-200 i
Apr 14/82 TPE/iSE331-74-0003Revision 3, Mar 24/86 Page 2 4
Ib~ SERYICE BUUE~#GARRETT TURBINE ENGINE COMPANY
Prior to
Part No. Model No. Serial No. Application
R 3102190-1 TPE331-10-501K *38220 Jetprop CommanderR 695/695A/6958
3102180-1 TPE331-10-501M *36393 Mitsubishi
Marqui se/Solitaire
R 3102170-5 TPE331-10-511C *37160 CASA 212-200R 3102190-2 TPE331-10-511K *38220 Jetprop CommanderR 695/695W6958R 3102180-2 TPE331-1O-511M *36393 Mitsubishi MarquiselR SolltareR 3102050-1/ TPE331-10U-501G *35250 Merl in IIIB
R 3102050-3 TPE331-10U-502G *35250 Merl in IIIBR 3102050-4 TPE331-10U-511G *35250 Merlin IIIBR 3102050-5 TPE331-10U-512G *35250 Merl in IIIB
R 3102500-1 TPE331-10UF-501H *42007 Jetstream 313102600-2 TPE331-10UF-511H *35250 Jetztream 313102600-5 TPE331-10UF-512H *35250 Jetstream 31
3102600-6 TPE331-10UF-513H *35250 Jetstream 313102600-7 TPE331-10UR-513H *35250 Jetstream 313102920-1 TPE331-llUA-601W *47011 Pucara IA-66
*Praduction incorporation Point.
R **Improvements provided by this service bulletin are optional and haveR not been incorporated into production units.
8. Reason
(1) Problem: The present ignition unit duty cycle is limited in ac-
cordance with the aircraft flight manual based on vendor
recommendations.
(2) Background: Ilhen the aircraft flight manual limits are exceeded,the ignition unit is subject to failure.
(3) Action: A new ignition unit has been developed with an extended
du ty eye le.
R (a) Above +50F (~10C) ambient temperature, the ignition unit maybe operated up to one hour continous duty. The total time"on" shall not exceed one hour without one hour "off". The
R one hour "on" may be either continuous or intermittent.
R (b) Below ~50 (~iOC) ambient temperature, the ignition unit may beR as required without limitation provided service bul-R n TPE331-75-0004 has been complied with.
i.
Apr 14/82 TPE/TSE331-74-0003Revision 3, Mar 24/56 Page 3
I~j SEWIIIGEv
GARRETT TURBINE ENGINE COMPANY
C. ption
This service bulletin provides instructions for installation of IgnitionUnit, Part No. 868962-3 which has a longer continuous duty cycle.
D. Compliance
Optional. Thi a service bul leti n may be accompl i shed at operator’soption.
E. Approval
The change to the engine type design authorized by this service bulletinR complies with applicable Federal Aviation Regulations and is FAA
approved.
F. Manhour Requirements
No additional manhours are required to accomplish this change when aR maintenance action necessitates access to the affected part.
G. Material Price and Availability
Information regarding availability of parts may be obtained from a Gar-R rett authorized Service Center or the aircraft manufacturer’s appointed
rervice fadllt)i. iiiefer to Service Infor~nation Letter (S.I.L.)P331-27for a complete listing of these facilities.)
Refer to Section 3 for information regarding price of parts required toaccomplish this bulletin.
H. Tool i ng Price and Availabili ty
R No special tooling is required except that already listed in publica-R tlons referenced in Paragraph J.
I. Weight and Balance
No change.
J. Publications References
The sources of infonnation used in the preparation of this service bul-letin include Garrett engineering documentation and the following.
Apr 14/82 TPE/TSE331-74-0003Revision 3, Mar 24/85 Page 4
Ic~iSERVICE BULL~IWGARRETT TURBINE ENGINE COMPANY
Illustrated
Part/ Overhaul Maintenance Parts
Model No. Manual Manual Catal oq
TPE331-25AA NA *72-00-85 72-00-84
TPE331-250A NA *72-00-85 72-00-84
TPE331-25FA NA *72-00-85 72-00-84
TPE331-43A NA *72-00-85 72-00-84
TPE331-47A NA *72-00-85 72-00-84
TPE331-25AB NA *72-00-88 72-00-87
TPE331-250B NA "72-00-88 72-00-87
TPE331-438L NA *72-00-88 72-00-87
TPE331-558 NA *72-00-88 72-00-87
TPE331-1-10OF NA *72-00-92 72-00-91
TPE331-1-1018 NA *72-00-92 72-00-91
TPE331-1-101E NA *72-00-92 72-00-91
TPE331-1-1O1F NA "72-00-92 72-00-91
TPE331-1-101Z NA *72-00-92 72-00-91
TPE331-1-151A NA *72-00-92 72-00-91
TPE331-1-151G NA "72-00-92 72-00-91
TPE331-1-151K NA *72-00-92 72-00-91
TPE331-2-201A NA *72-00-92 72-00-91
TPE331-2-201C NA *72-00-92 72-00-91
TPE331-2UA-203D NA *72-00-92 72-00-91
TPE311-3U-3r)30 NR *12-00-98 12-00-91
TPE331-3UW-303G NA *72-00-98 72-0~-97
TPE331-3U-303V NA *72-00-98 72-00-97
TPE331-3U-304G NA *72-00-98 72-00-97
TSE331-3U-303N NA *72-00-98 72-00-97
TPE331-5-251C NA *72-00-95 72-00-94
TPE331-5-251K NA *72-00-95 72-00-94
TPE331-5-252D NA *72-00-95 72-00-94
TPE331-5-252K NA f72-00-95 72-00-94
TPE331-5-252M NA *72-00-95 72-00-94
TPE331-5-254K NA *72-00-95 72-00-94
R TPE331-5-255K NA *72-00-95 72-00-94
TPE331-6-251M NA *72-00-95 72-00-94
TPE331-6-2528 NA *72-00-95 72-00-94
TPE331-6-252M NA *72-00-95 72-00-94
TPE331-SA-251M NA *72-00-95 72-00-94
TPE331-6A-252M NA *72-00-95 72-00-94
R TPE331-8-401S NA *72-00-13 72-00-11
R TPE331-8-4025 NA *72-00-13 72-00-11
R TPE331-8-403S NA *72-00-13 72-00-11
R TPE331-R-404S NA *72-00-13 72-00-11
R TPE331-10-501C NA *72-00-28 72-01-17
R TPE331-10-501K NA *72-00-29 72-01-18
R iPE331-10-501M NA *72-00-27 72-01-16
R TPE331-10-511C NA *72-00-28 72-01-17
R TPE331-10-511K NA *72-00-27 72-01-18
j R TPE331-10-511M NA *72-00-27 72-01-16
Apr 14/82 TPE/TSE331-74-0003Revision 3, Mar 24/86 Page 5
SEIVICE BULLETI#GARRETT TURBINE ENGINE COMPANY
IllustratedPart/ Overhaul Maintenance PartsModel No. Manual Manual Catalpg
R TPE331-1OU-501G NA *72-00-23 72-01-15R TPE331-1OU-5O2G NA *72-00-23 72-01-15R TPE331-10U-511G NA *72-00-23 72-01-15R TPE331-10U-512G NA *72-00-23 72-01-15
TPE331-10UF-501H NA *72-00-42 72-00-41R TPE331-1OUF-511H NA *72-00-42 72-00-41R TPE331-1OUF-512H NA *72-00-42 72-00-41R TPE331-1OUF-513H NA *72-00-42 72-00-41R TPE331-10UR-513H NA *72-00-42 72-00-41
TPE331-llUA-601W NA *72-00-25 72-00-24
*Affected Chapte r/Secti on/Subject 74-10-01.
K. Service Bulletin References
R The following shall be accomplished prior to or concurrent with thisR service bulletin. The accomplishment instructions outlined in each ser-R vice bulletin stand alone; therefore compliance with this service bul-R letln doer not indicate compliance with any other service bulletin.
Service 8ulletln No. Service Bulletin Title
R TPE/TSE75-0004 ENGINE AIR SYSTEM COMPONENTSR Rework Anti-Ice Shield Assembly
L. Other Publications Affected
Same as those listed under "Publlcations References".
Apr 14/82TPE/iSE331-74-0003
Revision 3, Mar 24/a6Page 6
SERVICE BULLETINGARRETT TURBINE ENGINE COMPANY
2. inrtructlonr
R NOTE_: Publ i cations ii sted in Section 1 provide applicable di sassembly,R cleaning, inspection, reassembly, and testing instructions and shallR be referred to during the accomplishment of the followingR instructions.
R A. Replace Ignitron Unit as Follows
R (1) Gain access to and remove Ignition Unit, Part No. 868962-2 in ac-
cordance with Engine Maintenance Manual.
(2) Install replacement Ignition Unit, Part No. 868962-3 in accordancewith Engine Maintenance Manual.
R (3) Reassemble engine in accordance with Engine Maintenance Manual.
R (4) Check and ensure proper engine operation in accordance with Air-R craft Flight Manual and/or appropriate aircraft documents.
R (5) Make entry in engine log book noting engine operating time landserial number of installed canponent if applicable) and compliancewith this service bulletin land service bulletin revision number if
applicable).
R (6) Reidentiiicatlon of equiprrnt net reguired.
R (7) Complete Compl i ance Certificate fo rm and ma ii. Contact local Gar-R rett authorized service center to obtain forms, if required.
i
Apr 14/82 TPE/TSE331-74-0003Revision 3, Mar 24/86 Page 7/8
I~ SER\IIICIE Blllhl~TI#GARRETT TURBINE ENGINE COMPANY
3. Mater~al infarmatlan
R The fol lowing parts are requi red to accomplish the 1 nstructf ons outl i ned i n
R this service bulletin.
R NOTE: Applicable illustrated parts catalogs and spare parts bul-R letlns dated later than the original issue date of thisR service bulletin may introduce different parts farR installation. Refer to these documents before orderingR parts.
R Expendable parts discarded in gaining access to the af-R fected area of the equipment are not included.
R The following parts are required to accomplish the instructions outlined inR this service bul letin. The Unf t Net Price applies to Canmerci al Ai rllnesR only.
Unit
List Instructlons-New PN Ouantity Pri ce Key Word Old PN Disposition
R 868962-3 1 82,6 28.00 Ignition 868962-2 F
Unit
R Di EPOZltion Code F. Dispose of old part according to company practices; replaceR with like part.
Disposition Code K. Old and new parts are interchangeable.
*Thfs price is F.O.B. Garrett Phoenlx, Arrzona and will remain fl~m throughR September 17, 1986.
Refer to Section 1, Paragraph G for information regarding availability of parts.
Apr 14/82 TPE/TSE331-74-0003Revision 3, Mar 24/86 Page 9/10
II
Service snformatisn GulfstreamAerospace
SERVICE INFORMATION NO. 81-212
30 June 1986
GARRETT TURBINE ENGINE COMPANY SERVICE BULLETIN NO. TPETTSEBJ1-75-0004
MODELS AFFECTED: MODELS 690, 690A AND 690B, 8ERIAL NOS. 11001 THRU 11566.
MODEL 690C, SERIAL NOS. 11600 THRU 11?35.
MODEL 690D, SERIAL NOS. 15001 THRU 16042.
MODEL 695, SERIAL NOS. 95000 THRU 95084.
MODEL 695A, SERIAL NOS. 96000 THRU 96100.
MODEL 6968, SERIAL NOS. 96201 THRU 96208.
REASON FOR PUBLICATION: TO RECOMMEND COMPLIANCE WITH GARKF.TT TURBINE ENGINE COMPANY
(rrTECI SERVICE BULLETIN NO TPEiTSES31-75-4004,
COMPLI~NCE: REFER TO GTEC SERVICE BULLETIN NO. TPEPI~SE331-75´•0004.
BY WHOM WORK WILL BE ACCOMPLISHEO: REFER TO GTEC SERVICE BULLETIN NO. TPEITSE331-76-0004.
APPROVAL: REFER TO GTEC SERVICE BULLETIN NO. TPEiTSES31-76-0004.
ESTIMATED MAN HOURS: REFER TO GTEC SERVICE BUI.I.ETIN NO. TPEiTSE331-75-0004.
PARTS DATA: REFER TO GTEC SERVICE BULLETIN NO. TPERSE381-75-0004.
SPECIAL TOOLS: REFER TO GTEC SERVICE BULLETIN NO. TPEiTSE331-75-0004
ACCOMPLISHMENT INSTRUCTIONS:
I Comply with Garrett Turbine Engine Company Service Bulletin Na. TPERSE~1-76´•00011.
a. Fill out and mail Compliance Card.
ELECTRICAL LOAD: NO CHANCE.
WEIGHT AND BALANCE: NO CHANGE
SPARES AFFECTED: NO.
PUsLICPITIONS AFFECTED: NONE.
RECORD COMPLIANCE: Mabe an appropriate entry in airplane maintenance records as follows: Service Information
No. SI´•P12. dated 30 June 1986, entilled’~Garrett Turbine Engine Company Service Bulletin No. TPEiTSES31-15-0004,’’
nci:limi,lishod tdate)
C
Page i of 1
SERYICE BULLETINGARRETT TURBINE ENGINE COMPANY
CREVISION TRANSMITTAL SHEET
This sheet transmits Revlsf on 1 to Service Bulletin No. TPE/TSE331-75-0004,
This is a COMPLETE revision. This bulletin has been reprinted in its entirety.Please remove and discard all pages of prior issues and replace with pages ofthis revision.
Reason for Revision:
NOTE: Equipment modl ff ed in accordance with a previous issue of thisservice bulletin doer not require further rework.
This service bulletin is revised to provide additional optional rework procedureto allow the use of rivets to plug holes and to add engine models.
Section 1
Title is revised to delete part numbers.
C Paragraphs R and J are reviled to add Engine Models IPE331-1-100Fj-10LIF-512H/-lo~F-513H/-lauR-513H.
Paragraph 0 is revised to add Part No. 895298-5.
Paragraph K is revised to add service bulletin compliance requirement.
Section 2
Accomplishment instructions are revised to add optional rework procedure.
Step 2.A. Is revised to delete reference to Part No. 868780-1 and addPart Nd. 896298-5.
Step 2.A.(3) provides for location of rework area.
Step 1.A.(4) provides optional rework procedure using rivets.
Step 2.A.(5) provides rework procedure by welding.
Step 2.A.(6) provides for inspection of rework.
Step 2.A.(7) provides far reldentlflcation of Part No. 868780-2 to868780-3.
Section 3
C Material information (r revised to add unit prldng infarmatl.n.
Jan 14/85 TPE/TSE331-75-0004Page 1 of 2 2Copyright 1985 by The Garrett Corporation
´•SEWCE BULLIE’BINGARRETT INE ENGINE COMPANY
List of Effective Pages:
Page No. Date Page No. Date
1 Jan 14/85 7 Jan 14/852 Jan 14/85 8 Jan 14/853 Jan 14/85 9 Jan 14/854 Jan 14/85 10 Jan 14/855 Jan 14/85 11 Jan 19/856 Jan 14/85 12 Blank
Previous Revisions:
None
Jan 14/85 TPE/TSE331-75-0004 14o,,, ,f
j~ SEP\IIGE BULUETIIGARRETT TURBINE ENGINE COMPANY
R ENGINE AIR SYSTEM COMPONENTS Rework Anti-Ice Shield Assembly
1. Planni nq Informa ti on
A. Effectivi ty
This service bulletin is applicable to the following turboprop aircraft
engines.
Prior to
Part No. Model Na. Serial Na. Application
R 893130-1-1/-2 TPE331-1-100F **Not Avail Pilatus Porter
893400-1-1/ TPE331-1-1O1B **Not Avail Turbo 18/Turbollner
894120-1-1/ TPE331-1-101E **Not Avail Jetliner 600 (Dave)
896760-1 TPE331-1-1O1F **Not Avail Peacemaker
thru -4
3101850-1 TPE331-1-101Z **Not Avail S2R Turbo Thrush/Turbo Ag Cat
893250-1-1/ TPE331-1-151A **Nat Avail Mitsublshl
-2 MU-2DP/2F/2G
869:85-1-1/ iPE931-1-1510 **N~t Avail Meil(n LIE
3101260-1/ TPE331-1-151K **Not Avail Century Turbo
Commander
869480-1-1/ TPE331-2-201A **Not Avail SLyvan-2
894820-1-1/ TPE331-2-201C **Not Avail CASA 212
-2
894980-1/-2 TPE331-2UA-203D **Not Avail Goose
894040-1/-2 TPE331-3U-303G **Not Avail
or or IV/IVA/Metro/895880-1/-2 TpE331-3UW-303C **Nat Avail Metro II/
Metro IIA
3101800-1 TPE331-3U-303V **Not Avail CenturyJetstream III
3102550-1/-2 TPE331-3U-3040 **Not Ava ii
IV/IYA/Metro/Metro 1I1Metro IIA
894870-1 TSE331-3U-303N **Not Avail Helltec Corp S55T
thru -4
896950-1-1/ TPE331-5-251C **Nat Avail CASA 212-100
-2/-3895720-1/ TPE331-5-251K **Not Avail Jetprop Commander
-2/-3 690/690A/69083102200-1 TPE331-5-2520 **Not Avail Oornier 228
i 3Ln2520-L rPE331-5-252K ’´•NOt Avail
Feb 28/84 TPE/TSE331-75-0004Revision 1, Jan 14/85 Page 1 of 12
Copyright 1985 by The Garrett Corporation
I~ SEIVICE BUUEBBMGARRETT TURBINE ENGINE COMPANY
Prior to
Part No. Model No. Serial No. Application
3101840-1 TPE331-5-252M **Not Avail Mitsubishi
MU-2N/2P3102520-2/-3 TPE331-5-254K **Not Avail Jetprop Commander
6900/6900895720-4 TPE331-5-255K **Not Avail Jetprop Commander
690/690A/6908896160-1/ TPE331-6-251M **Nat Avail Mltsublshl
-3/-5 MU-2J/2K/2L/2M3101630-1 TPE331-6-252B **Not Avail Beech 8100
3101300-2 TPE331-6-252M **Not Avail Mltsubishl
MU-2J/2K/2L/2M3102450-1 TPE331-6A-251M **Not Avail Mitsubfshi
MU-2J/2K/2L/2M3101300-3 TPE331-6A-252M **Not Avail Mltsubishi
MU-2J/2K/2L/2M3101470-1 TPE331-8-4015 **Not Avail Conquest II
3102510-1 TPE331-8-402S **Not Avail Conquest II
3102510-2 TPE331-8-403S *"Not Avail Conquest II
3101470-2 TPE331-8-404S **Not Avail Conquest II
3102170-1/-2 TPE331-10-501C **Not Avail CASA 212-200
3102190-1 TPE331-10-501K "*Not Avail Jetprop Commander
69515’15A/695B3102180-1 TPE331-10-501M *"Not Avail Mitsubishi
Marquise/Solitaire
3102170-5 iPE331-10-511C **Not Avail CASA 212-200
3102190-2 TPE331-10-511K **Not Avail Jetprop Commander
695/695A/69583102180-2 TPE331-10-511M **Not Avail Mitsuhlshi
MarqulselSolitaire
3102170-3 TPE331-10R-501C **Not Avail CASA 212-200
3102170-4 TPE331-10R-502C **No t Ava 1 1 CASA 212- 200
3102170-6 TPE331-10R-511C **Not Avail CASA 212-200
3102170-7 TPE331-10R-512C **Not Avail CASA 212-200
3103090-1 TPE331-10U-501E **Not Avail No Current
Application3102050-1/-2 TPE331-10U-501G **Nat Avail Merlin IIIB
3102050-3 TPE331-10U-502G **Not Avail Merlin IIIB
3102940-1 TPE331-10U-503G **Not Avail Merlin IIIC
3102050-4 iPE331-10U-511G **Not Avail Merlin IIIB
3102050-5 TPE331-10U-512G **Not Avail Merlin IIIB
3102940-2 iPE331-10U-513G **Not Avail Ilerlin IIIC
3103230-2 TPE331-10UA-501G **Not Avail Metro II
3103230-1 TPE331-10UA-511G **Not Avail Metro II
3102600-1 TPE331-10UF-501H **Not Avail Jetstream 31
3102600-2 TPE331-10UF-511H **Not Avail Jetstream 31
R 3102600-5 TPE331-10UF-512H **Not Avail Jetstream 31 jR 3102600-6 iPE331-10UF-513H **Not Avail Jetztream 31R 3102600-7 TPE331-10VR-513H **Not Avail Jntstream 31
Feb 28/84 TPE/TSE331-75-0004Revision 1, Jan 14/85 Page 2
~j SEWYICE BUILLETIRGARRETT TURBINE ENGINE COMPANY
Prior toPart No. Model No. Serial No. Application
3102540-1 TPE331-l1U-601G **Nat Avail Metro III/Merlin IVC
3102540-2 TPE331-llU-602G **Not Avail Metro III/Merlin IVC
3102540-3 TPE331-l1U-611G **Not Avail Metro III/Merlin IYC
3102540-4 TPE331-llU-612G **Not Avail Metro III/Merlin IVC
3102920-1 TPE331-llUA-601W **Not Avail Pucara IA-663102920-2 TPE331-llUA-611W **Not Avail Pucara IA-66
**Improvements provided by this service bulletin have been approved fornew production and existing units. Serial number effectivity will beprovided when determined by production schedules.
B. Reason
(1) Problem: Engines have experienced overheating of the ignition unitduring engine anti-ice system operation.
12) Rction: Reworl the anti-l~e shield to ell.lnate anti-ice rynte.air from impinging on ignition unit during anti-ice systemopel’ation.
C. Description
This service bulletin provides necessary procedures far the rework ofR Anti-ice Shield Assembly, Part No. 868780-1/-2 or 896298-1 through -5.
D. Compliance
Recommended. Garrett recommends that this service bulletin be accom-
plished at the operator’s convenience but not later than the next accessof affected parts.
E. Approval
The change to engine components authorl2ed by this service has beenfound to comply with applicable Federal Aviation Regulations and is FAAapproved.
F. Manhour Requirements
An estimated two manhours are required for this change when accomplishedat the maintenance level.
C
Feb 28/84 TPE/TSE331-75-0004Revision 1, Jan 14/85 Pin.
(O
SERIIIGE BULLETINGARRETT TURBINE ENGINE COMPANY
G. Material Price and Availability
Information regarding availability of parts may be obtained from a
Garrett authorired Service Center or the aircraft manufacturer’s ap-pointed service facilf ty. Refer to Service informatf on Letter (S.I.L.)P331-27 for a complete listing of these facilities.)
Refer to Section 3 for information regarding price of parts required to
accomplish this bulletin.
H. Tooling Price and Ava ilabfl i ty
No special tooling required except that already listed in referenced
manual(s).
I. Weight and Balance
No change.
J. Publications References
The sources of information used in the preparation of this service bul-
letin include Garrett engineering documentation and the followingpubllcatlon(s).
Illustrated
Part/ Overhaul Maintenance PartsModel No. Manual Manual Catalos
R TPE331-1-100F NA *72-00-92 72-00-91TPE331-1-101B NA *72-00-92 72-00-91TPE331-1-101E NA *72-00-92 72-00-91
TPE331-1-101F NA *72-00-92 72-00-91TPE331-1-101Z NA *72-00-92 72-00-91
TPE331-1-151A NA *72-00-92 72-00-91
TPE331-1-151G NA *72-00-92 72-00-91IPE331-1-151K NA *72-00-92 72-00-91
TPE331-2-201A NA *72-00-92 72-00-91
TPE331-2-201C NA *72-00-92 72-00-91TPE331-2UA-2030 NA *72-00-92 72-00-91TPE331-3U-303G NA *72-00-98 72-00-97
TPE331-3UW-303G NA *72-00-98 72-00-97
TPE331-3U-303V NA *72-00-98 72-00-97
TPE331-3U-304G NA *72-00-98 72-00-97TSE331-3U-303N NA *72-00-98 72-00-97TPE331-5-251C NA *72-00-95 72-00-94
TPE331-5-251K NA *72-00-95 72-00-94TPE331-5-252D NA *72-00-95 72-00-94TPE331-5-252K NA *72-00-95 72-00-94
TPE331-5-252M NA *72-00-95 72-00-94
iPE331-5-254K NA *72-00-95 72-00-94TPE331-5-255K NA *72-00-95 72-00-94
TPE331-6-251M NA *72-00-95 72-00-94TPE331-6-252B NA *72-00-95 72-00-94
Feb 28/84 TPE/TSE331-75-0004Revision i, Jan 14/85 Page 4
I~ SELIIICE BULLETINGRRRETT NRBIIE FNOINf COPIPANI
IllustratedPart/ Overhaul Maintenance PartsModel No. Manual Manual Catalqg
TPE331-6-252M NA *72-00-95 72-00-94TPE331-6A-251M NA *72-00-95 72-00-94TPE331-6A-252M NA *72-00-95 72-00-94TPE331-8-401S NA *72-00-13 72-00-11TPE331-8-4025 NA "72-00-13 72-00-11TPE331-8-403S NA *72-00-13 72-00-11TPE331-8-404S NA *72-00-13 72-00-11TPE331-10-501C NA *72-00-23 72-00-21TPE331-10-501K NA *72-00-23 72-00-21TPE331-1D-501M NA *72-00-23 72-00-21TPE331-1O-511C NA *72-00-28 72-00-21TPE331-10-511K NA *72-00-29 72-00-21TPE331-10-511M NA *72-00-27 72-00-21TPE331-10R-501C NA f72-00-23 72-00-21TPE331-10R-502C NA *72-00-23 72-00-21TPE331-10R-511C NA *72-00-28 72-00-21TPE331-10R-512C NA *72-00-28 72-00-21TPE331-10U-501E NA *72-00-42 72-00-41TPE331-10U-501G NA *72-00-23 72-00-21TPE331-10U-50ZG NA "12-00-23 72-00-21TPE331-10U-503G NA *72-00-23 72-00-21TPE331-10U-511G NA *72-00-23 72-00-21TPE331-10U-512G NA *72-00-23 72-00-21TPE331-10U-513G NA *72-00-30 72-00-21TPE331-10UA-501G NA *72-00-45 72-00-44TPE331-10UA-511G NA *72-00-45 72-00-44TPE331-10UF-501H NA *72-00-42 72-00-41TPE331-~OUF-511H NA *72-00-42 72-00-41
R TPE331-10UF-512H NA *72-00-42 72-00-41R TPE331-iOVF-513H NA *72-00-42 72-00-41R TPE331-10UR-513H NA *72-00-42 72-00-41
TPE331-llU-601G NA *72-00-25 72-00-24TPE331-llU-602G NA *72-00-25 72-00-24TPE331-llU-611G NA *72-00-25 72-00-24TPE331-ilU-612G NA *72-00-25 72-00-24TPE331-llUA-601W NA *72-00-25 72-00-24TPE331-liUA-611W NA *72-00-25 72-00-24
*Affected Chapter/Sectian/Subject 75-10-02.
Feb 20/84 TPE/TSE331-75-0004Revision i, Jan 14/85 Page 5
SERVIClOi BULLETINGARRETT TURBINE ENGINE COMPANY
CK. Service Bulleti n References
R (Anti-Ice Shield Assembly, Part No. 868780-1) The following serviceR bulletin shall be accomplished prior to or concurrent with thisR bulletin. The accomplishment instructions outlined in each bulletinR stand alone, therefore compliance with this bulletin does not indicateR compliance with any other bulletin.
Service Bulletin No. Service Bulletin Title
72-0323 ENGINE ANTI-ICE SHIELO ASSEMBLY
Replace/Rework Anti-Ice Shield As-
sembly
R The following service bul letf n(s) should be revf ewed by the operator forR possible incorporation at this time.
R Service Bulletin No. Service Bulletin Title
R 75-0005 AIR ENGINE ANTI-ICING Rework or
R Replace Antl-Ici Shield Assembly,R Part No. 896298-2tlth -6, Part No.R 896298-3 with -7, and Part No.R 896298-4 with -8
L. Other PublicaTlanr Rfiectpd
Same as those listed under "Publlcatlons References".
Feb 28/84 TPE/TSE331-75-0004RevlElon i. Jan 1(/85 Page 6 j?
14~ SERVICE BULLE’BINGARRETT TURBINE ENGINE COMPANY
2. Accomp1 i shment Instru cti ons
NOTE: Manuals listed in Section 1 provide applicable disassemhly,cleaning, inspection, reassembly, and testing instructions
and shall be referred to during the accomplishment of the
following instructions.
Table 1. Materials and Compounds
Material or Compound Manufacturer
NOTE: Equivalent substitutes may be used for listed items.
Enamel, light green epoxy Grlggs Paint, Subsidiary of Domcom Cist,(Type L, Class A) 3602 S 16th Place. Phoenix, AZ 85040
(With Catalyst C1178)
Filler rod (4043) Cabot Corp, Stellite 01v, 1020 West Park
Ave, P.O. Box 746, Kokomo, IN 46901
C Powder (Irldlte no. 11-2) Rlehardron Chen~ieai Co. Rllied KeliteProducts Dlv, 400 Mldland Ave, HighlandPark, MI 48203
Primer, glass green epoxy Grlggs Paint, Subsidiary of Domcom Cist,
(Type I, Class A) 3602 S 16th Place, Phoenix, AZ 85040
(Wlth Catalyst C1178)
l,l,l-Trichlaraethane Commercially available
(M1L-T-81533)
R A. Rework Anti-Ice Shield Assembly, Part Na. 868780-2 or 896298-1 ThroughR -5
(1) Clsassemble engine as required to gain access to anti-ice shield
assembly in accordance with Engine Maintenance Manual.
(2) Remove anti-ice shield assembly in accordance with Engine Mainten-
ance Manual.
R (3) Locate and identify three 1/8 inch diJlneter holes to be reworked.R (See figure 1.)
Feb 28/84 TPE/TSE331-75-0004Revision 1. Jan 14/85 Pace 7 iD
I~ SER\IIGE BULLETINGARRETT TURBINE ENGINE COMPANY
e, o
THRsl 1/B INCII DlhMBIRHOLEIIO 81 WI1OID OP
RIVnlD
vlw
R
o O
Omnlr 1/8 INCH
DIIIMITIR HOLII
TO III WI1DID OR
O o,lv,,,
vim B18-5625
View A PN 868700-2View B PN 896298-1 thru -5
Rework Anti-Ice Shield AssemblyFeb 28/83 Figure 1 TPE/TSE331-75-0004Revision 1, Jan 14/85 Page 8
BULL~BINGARRETT TURBINE ENGINE COMPANY
R NOTE: Anti-ice shf eld assembly may be reworked by in-
R stalling rivets in holes, or by welding holer
R closed.
R (4) Rework anti-ice shield assembly using rivets as follows.
R cpurIo_N_: ENSURE THREE 1/8 INCH DIAMETER HOLES TO BE
R REWORKED ARE LOCATED BETWEEN ~TWO PARGE HOLES AS
R SHOWN IN FIGURE 1.
R (a) Install Blind Rivets, Part No. 627-510-9420 or Solid Rivets,
R Part No. MSZ0470A4-4 in holes shown in Figure i, with formed
R heads of rivets on outboard surface of anti-ice shield
R assembly.
R (b) Upset rivets in accordance with standard shop practices.
R (5) Rework anti-ice shield assembly by welding as follows.
(a) Remove gaskets from anti-ice shield assembly in accordance
with Engine Maintenance Manual to prevent damage duringrework.
C (b) weld ~rea ia clean and remove pdlnt prior ta
CAUTION: ENSURE THREE 1/8 INCH DIAMETER HOLES
WELDED ARE LOCATED BETWEEN TWO LARGE HOLES
AS INDICATED IN FIGURE 1.
(c) Puddle weld to fill three 1/8 inch diameter holes in accord-
ance with AMS4190 using aluminum filler rod (4043).
(d) Hand finish to blend weld areas smoothly to adjacent surfaces
both inside and outside of anti-ice shield assembly.
(e) Prepare chromate conversion coating solution as follows,
NOTE: Prepare chromate conversion coating solution
in small batches. Use only freshly preparedsolutions.
1 Dissolve one ounce of powder (Irldlte 14-2) In each quartof distilled or de-ironized water.
2 Maintain solution at 21 to 27C (70 to 80F).
(f) Coat bare areas with chromate conversion coating solution.
Allow area to remain wet for one minute.
(g) Rinse parts with water at 27 to 430 (80 to llOF). Blow off
excess water with low pressure air (20 pslg maximum), then dryin oven at a temperature not to exceed i1C (160F).
Feb 28/84 TPE/TSE331-75-00041 In,aE p~,. q
SIERVICE BUU~TINGARRETT TURBINE ENGINE COMPANY
L-(h) perform fluorescent penetrant inspection in a~cordance with
MIL-I-6866.
(1) Thoroughly clean area for paint touch-up using 1,1,1-Trfchloroethane (MIL-T-81533).
(j) If anti-ice shield has been previously painted. touch-up paintusing gloss green epoxy primer and light green epov.y enamel in
accordance with Engine Maintenance Manual.
(k) Relnstall gaskets on anti-fee shield assembly in accordance
with Engine Maintenance Manual.
R (6) Inspect rework.
R (7) Reidentlfy Anti-Ice Shield, Part No. 868780-2 to Part No, 868780-3
R by removing -2 (868780-2) and entering a -3 (868780-3) using an ink
R stamp or stencil.
(8) Install reworked anti-ice shield assembly in accordance with EngineMaintenance Manual.
(9) Reassemble engine in accordance with Engine Maintenance Manual.
(10) Upon completion of engine reassembly, check and ensure proper en-
gine operation in accordance with Aircraft Flight Manual.
(11) Upon co~npletion of this rework, make entry in engine log book not-
ing engine operating time tend serial number of installed componentIf applicable) and compliance with this service bulletin land ser-
vice bulletin revision number if applicable).
(12) Reidentlflc~tion of equipment not required.
(13) Complete Compliance Certificate form and mail. Contact local Gar-
rett authoriled service center to obtain forms, if required.
Feb 28/84 ~PE/TSE331-75-0004Revision i, Jan 14/85 Page 10
13
F~jlSERVICE BULLELlPIj
GARRETT TURBINE ENGINE COMPANY
R 3. Material !nPo~atlon
R NOTE: Applicable illustrated parts catalogs and spare parts bul-
R letlns dated later than the original issue date of this
R service bulletin may introduce different parts for
R installation. Refer to these documents before orderingR parts.
R Expendable parts discarded in gaining access to the af-
R fected area of the equipment are not included.
R The following parts are required to accomplish the instructions outlined in
R this service bulletin.
R Unit
R List Instructlons-
R New PN Quantity Prlce* Key Word Old PN Olspositfon
R NOTE: Rivets are not required if reworl is accomplished by welding.
R MS20470A4-4 3 ~0.08 Rivet
R or
R 627-510-9420 3 2.10 Rivet
CR *Thls price is F.O.B. Garrett Phoen(x, Arizona and will remain fins throughR May 14, 1985.
R Refer to Section 1, Paragraph G for information regarding availability of parts.
Feb 28/84 TPE/TSE331-75-W04Revision i, Jan 14/85 Page 11/12 \’i-
Sevvice Informaftie4n GulfstreamAerospace
SERVICE INFORMATION NO. SI-214
30 June 1986
EMERGENCY AIRWORTHINESS DIRECTIVE NO. 86-12-02
(OTEC Service Bulletin No. TPE331-72-0630)
MODELS AFFECTED: MODELS 680T, 680V AND 680W, SERIAL NOS. 1413 THRU 18501
MODEL 681, SERIAL NOS. 60(11 THRU 6072.
MODELS 690, 690A AND 6908, SERIAL NOS. 11001THRU 11566.
MODEL 690C, SERIAL NOS. 11600 THRU 11735.
MODEL 690D, SERIAL NOS. 11001 THRU 15042.
MODEL 696, SERIAL NOS. 96000 THRU 96084.
MODEL BB5A, SERIAL NOS. 96000 THRU 96100
MODEL 6958, SERIAL NOS. 96201 THRU 96208.
REASON FOR PUBLIC~ITION: TO RECOMMEND COMPLIANCE WITH EMERGENCY AIRWORTHINESS
DIRECTIVE NO. 86´•12-02.
COMPLIANCE: REFER TO EMERGENCY AIRWORTHINESS DIRECTIVE NO. 86´•12-02.
BY WHOM WORK WILL BE I\CCOMPLISHEO: A a p MECHANIC OK EQUIVALENT AND AN APPROVED TPE331
O1L AND FILTER ANALYSIS FACILITY.
REFER TO GTEC SERVICE INFORMATION LETTER P331-97,
REVISION 5 DATED MAY 23, 1986, FOR APPROVED TPE931 OIL
AND FILTER ANALYSIS FACILITIES.
APPROVAL: REFER TO OTEC SERVICE BULLETIN NO. TPES31-72-0630
ESTIMATED MAN HOURS: REFER TO OTEC SERVICE BULLETIN NO. TPES31-72-0530
PARTS DATA: REFER TO GTEC SERVICE BULLETIN NO. TPE331-72-0630
SPECI~LTOOLS: REFER TO GTEC SERVICE BULLETIN NO. TPE331 -12-0630
ACCOMPLISHMENT INSTRUCTIONS:
1. Comply with Emergency Airworthiness Directive No. 86-12-02
NOTE
Darrett Turbine Engine Company Service Bulletin Nos. TPE331-72-
0533 and TPE331´•72-0534, referenced in Service Dulletin No. TPE331-
72-0530, may be obtsined from Garrett Turbine Engine Company. P O.
29003, Phoonix, Arizona 85038.
2. Fill out and mail Compliance Card.
ELECTRICAL LOAD: NO CHANGE.
WEIGHT AND BALANCE: NO CHANGE.
SPARES AFFECTED: NO.
C PUBLIC/ITIONS*FFECTED: NONE
RECORD COMPLIANCE: Make an approprinte entry in oi~lsne maintenance records as follows: Servior Information
No. 5I-214, dated 30 June 1986, entiiled’~Emergeney Airworthiness Directive No 86´•12-02," aceompliahed(dnte)
Page 1 of]
Q EMERGENCY AIRWORTBINESS DIRECTIVE
uSDeoortmenl
dTnm~atatm :VdlT~: ~PIRDI 1(ITION11 A(LO~ OITICT
~sd´•rm ~iv*mon MUIMIIL CIT( MiUrrml 1111~
Mm(n(~fmtMn
"is en´•cqency priority letter airworthiness directive86-12-02 applicable to operators of Garrett Turbine Engine
c;npany :~ode?s TPE33: :5RA. -:5AB, -25DR, -25D6, -25FA, -43A,-47A, -558, -1, -2, -:UA, -3U, -iUW, -5, -6, -6R, -8,
-:UC, -1OR, -10U, -?OVA, -10UF, -1OUG, -:OUGR, -10UR,-11UR, -ii, and TSE331-3U turboprop and turSoshaft
engines is effective immediately upon receipt of this priority:etter. This priority letter AD is required to preventpossible failure of the beryllium-copper nut on the turbine endof the tiebolt shouldered shaft and resultant major damage tothe engine. This priority letter AD requires accomplishing aspectrometric analysis of oil samples collected in accordancewith a schedule as provided herein after receipt of thisletter.
Pursuant to the authority of the Federal Aviation Act of 1958,delegated to me by the Administrator, the following priorityletter AD is issued.
86-12-02 GARRETT TVRBINE ENGINE COMPANY: Letter issued June6, 1986. Applies to Garrett Turbine Engine Company ModelsTPE331-25 AA, -25 AB, -25DA, -25 DB, -25 FA, -43A, -4 3BL, -47A,-558, -1, -2, -ZUA, -3U, -3UW, -5; -6, -6A, -8; --IU; -IDG;
OR, -iOJ. -10UA, -1OUF, -10UG, -10UGR, -1OUR, -11U, -11UA,-12, and TSE331-3U turboprop and turboshaft engines.Compliance required as indicated unless alreadyaccomplished.To prevent the failure of the beryllium-copper nut on the
turbine end of the tiebolt shouldered shaft and resultant majordamage to the engine, accomplish the following:(a) Engines with less than 100 engine operating hours
since new or since installation of a turbine oil scavenge pumpassembly for any reason are to have an initial oil sample takenand processed in accordance with the instr uc t ions provided inparagraph i of Garrett Service Bulletin No. TPE331-7 2-0530,dated May 9, 1986, (SB 0530) or FAA approved equivalent. ThisIs to he accomplished at not less than 20 hours or more than 25hours since new or after the installation of that pumpassembli´•, or within 5 engine operatinci hours after receipt ofI~is priority letter AD, whiche ve; occurs later unless;ragraph (e) below has been accomplished. Additional oil.~illnlcs are to he taken and processed at not note than 25
hour intervals therea:ter until a total or 1ODoperating hourS has been accumulated since new or sinceins~allztion of that pump assembly or until paragraph (e) belownas been accomplished.
ibi Enginei with :UO or moie, ilut less iban 500 eng;neoperating hours since new or since installation of a turbinesil scav-nge pump assemblY for any reason on the date of
DIRECTIVE
RECEIVED gy bhT$
ri I b? L R I fl R
V Y ~u s l\al-4k As
RECEIVED svbh7P1 86-12-02
receipt of this priority letter AD, are to have an oil sampletaken and processed in accordance with the instructions
provided in paragraph i of SE 0530 within the next 50 engine
sps:ating hours after receipt of this priority letter AD. This
i-joastion is not required if paragraph (e) below has been
?i;bmplis~ed.IIOTE: Garrett recomnends chat oil samples continue to be
tJken at Leaulac intervals after accomplishment of this
prioritl: letter RD in accordance with the Spectrometric Oil
Ana;vsij Trogran (SOAl) described in Garrett Service
Information Setter No. P3)1-97. While the FAA encourages these
programs, thev are not mandatory per this priority letter AD.
ic) if oil sample analysis indicates beryllium content of
oil is in excess of O.; (two-tenths) parts per million,
accomplish paragraph (e) before further flight.(d) if oil sample analysis indicates beryllium content of
oil is in excess of 0.1 tone tenth) parts per million, but
equal to or less than 0 i (two-tenths) parts per million,:thin the next five engine operatingaccomplish paragraph (e) wi
hours.
(e) Engines which exceed the limits for beryllium content
in the~engine oil are to have the torsion shaft inspected, the
turbine oil scavenge pump r ewo r k ed or r epl ac ed the
beryllium-copper nut replaced, the turbine oil scavenge pump Cdrive spur gear shaft assembly inspected, and the engine oil
and filter changed in accordance with paragraph Z of SE 0530 or
FXx approved equivalent approved by the Manager, Western
Aircraft Certification Office. The inspection of the torsion
shaft does not apply to the following engine models which have
"strain-gage" torque sensors:
TPE331-10G TPE-331-10UG TPE331-1OUGR
TPE331-lLU TPE331-llUA TPE331-12
Aircraft may he ferried in accordance with the provisionsoi Federal Aviation Regulations (FARs) 21.197 and 21.199 to a
base where the AD can be accomplished. Upon request, an
ecuivalent means of compliance with the requirements of this hD
Ray be approved by the Manager, Western Aircraft Certification
ofiice, P.O. Box 92007, Worldway Postal Center, Los Angeles,California 90009-2007. Upon submission of substantiating data
Sy an owner or operator, through an FRA ~aintenance :nspector,
~ne !I.anager, Western Aircaet Certification Office may adjust
tne compliance time speciried in this Ao.
priority latter RD i; effective innediately upon
r´•ceipt.
?Ua-gER COLSACT:
Mr 3ili MorinS, Propuljion Sec.ion, j9?007, :as Xnoeles. Ciii:-´•:niaC-rtification Oe:i;e. ?.O. 90n
9C603-:007, telep~oni (:1?1 ;9T-l?a:.
BULLETI#GARRETT TURBINE ENGINE COMPANY
FNGIIII I.eanp)lih i*-rial Berllliu. S~ecironrlR c Oil b´•lairFrog ran (SOAP) In s pect 1 on
I. Planni no I nformat i on
A. Effectivity
NOTE: This service bulletin is no longer applicable to the followingturboprop aircraft engines when Service Bulletins, TPE331-72-0533
and TPE331-72-0534 have been complied with.
Service Bulletin TPE331-72-0534 is NOT applicable to enginesIdentified with an asterisk
This service bulletin is applicable to the following turboprop aircraft
engines.
PRIOR TO
PART NO. MOOEL NO. SERIAL NO. APPLICATION
865912-1A-6/-1A-71- 1A-8/ TPE331-25AA Al 1 Mi tsubl r hi M]-2B
-1A-9
893290-1-1/-2 TPE331125A8 Al 1 Mi tsubl s hi MU-ZB/-2Ds65912-lo-5/-lo-6/-10-7/ TPE331-250A All Falrchild Porter PC-6/
-1D-s C-H2
893310-1-1/-2 TPE331-250B All Fairchlld Porter
865912-1F-5/-1F-6/- 1F-7/ TPE331-25FA All Porter/Vol par-1F-8
867940-1-4/-1-7 TPE331-43A All Turbo Commander 680T/680\r
89327 O- 1-1/-1- 3/- 1-4/ TPE331-438L All Turbo Commander 680W/-1-5 681
867970-1-5/-1-6/-1-7/ TPE331-47A All Turbo 18
-1-8
893330-1-1/-2 TPE331-558 All Jetllner 600 (Dove)893130-1-1/-2 TPE331-1-100F All Pllatus Porter
893400-1-1/-2 TPE331-1-101B All Turbo 18/Turboliner894120-1-1/-2 TPE331-1-101E All Jetliner 600 (Dove)896760-1/-2/-3/-4 TPE331-1-1O1F All Peacemaker3101850-1 TPE331-1-101Z All S2R Turbo Thrush/
Turbo Ag Cat
893250-1-1/-2 TPE331-1-151A All Mltsublshi MU-Z0P/-2 F/-26
869595-1-1/-2 TPE331-1-151G All Merlin 1IB
3101260-1/-2 TP E3 31-1- 151K Al i. Century Tu rbo
Ccmmander869480- 1- 1/-2 TPE331-2-201A All Skyvan89482 O- 1-11- 2 TPE331-2-201C Al 1 CASA 212
894980-1/-2 TPE331-2UA-2030 All Goose
894040-1/-2 TPE331-3U-303G AllIVA/Metro/Metro II/
ORle; IMAL. ns
Metro III
May 9/86 RECFI\’Fr 1\´• BTP TPE331-72-0j30
Page 1 of 1?
Copyii~ht 1986 by TPC Gdrrett Corporation
le~ SERIIICE BULLE’BBHGARRETT IURBINE ENGINE COMPANY
PRIOR TO
PART NO. MODECO. _SSBIAL_NP. APPLICATION
3101800-1 TPE331-3U-303V All Century Jetstream III
3102250-1/-2/-3/-4 TPE331-3U-304G All
IVA/MetrO/Metro IIMetro IIA
895880-1/-2 TPE331-3UW-303G All
IVA/Metro/Metro II
Metro IIA
894870-1/-2/-3/-4 TSE331-3U-)03N All Helitec Corp 555T
896950-1-1/-2/-3 TPE331-5-251C All CASA 212-10089572 0-1/-2/-3 TPE331-5-251K Al 1 Jetprop Commander 690/
690A/690B3102200-1 TPE331-5-252D WP-39244 Oornler 228
3103330-1 TPE331-5A-252D #P-640O3 Darnler 228
3102520-1 TPE331-5-252K All Jetprap CaniMnder
690A/69083101840-1 TPE331-5-252M All Mitsubishi MU-2N/-2P3102520-2/-3 TPE331-5-254K All Jetprop Commander
6900/6900895720-4 TPE331-5-255K All Jetprop Commander 690/
690A/690B896160-1/-3/-5 TPE331-6-251M All Mitsubirhl MU-ZJ/-2h/
-2L/-2M3101630-1 TPE331-&2528 All Beech 8100
3103300-1 TPE331-6-252L All Merlin IIB3101300-2 TPE331-S-252M All Mi tsubi shi MU-2J/-2 K/
-2L/-2M3103340-1 TPE331-6-252T All Skyvan3101630-2 TPE331-6-253B All 8eech 8100
3102450-1 TPE331-6A-251M All Mltrubishl MU-2J/-ZK/-2L/-2M
3101300-3 TPE331-6A-252M All Mitsubishi MU-2J/-2K/-2L/-2M
3101470-1/-3 TPE331-8-401S All Conquest II
3102510-1/-8 TPE331-8-402S All Conquest II
3102510-2/-9 TPE331-8-403S All Conquest II
3101470-2/-4 TPE33I-8-404S All Conquest II3102510-4 TPE331-8-406S All Conquest II
3102170-1/-2 TPE331-1O-501C Al 1 CASA 212-2 003102190-1 TPE331-10-501K All Jetprop Ccmr~nder 695/
695A/69583102180-1 TPE331-10-501M Al 1 Mi tsubi shl Ma rqul se/
Solitaire3102170-5 TPE331-10-511C All CASA 212-200
3102190-2 TPE331-la-511K Al 1 Jetprop Comma nder 695/695A/6958
3102180-2 TPE331-1O-511M All Mi tsubi shi Ma rqu i s e/Solitaire
’3103440-1 TPE331-10G-5115 All Na Current Application3102170-3 TPE331-10R-501C All CASA 212-200 j3102170-4 TPE331-10R-502C All CASA 212-2003102170-6 TPE331-10R-511C All CASA 212-200
TPE331-72-0530
May 9/86 Page 29
I~14 SERYICE BULLETINGARRETT TURBINE ENGINE COMPANY
C
PRIOR TO
PART NO. MODEL NO. SERIAL NO. APPLICATION
3102 17 0- 7 TPE 331- 1 OR- 5 12 C #P-37513 CASA 2 12-2 00
3102170-8 TPE331-10R-513C All CASA 212-200
3102050-1/-2 TPE331-10U-501G All Merlin 1118
3102050-3 TPE331-10U-5026 All Merlin IIIB
3102940-1 TPE331-10U-503G All Merlin IIIC
3102050-4 TPE331-10U-511G All Merlin IIIB
3102050-5 TPE331-10U-512G All Merlin IIIB
3102940-2 TPE331-1OU-513G All Merlin IIIC
3103230-2 TPE331-10UA-501G All
IVA/Metro/Metro II/Metro IIA
)103230-1 TPE331-10UR-511G All
IVA/Metro/Metro II/Metro IIA
3102600-1 TPE331-1OUF-501H All Jetstream 31
3102600-2 TPE331-10UF-511H All Jetstream 31
3102600-5 TPE331-10UF-512H All Jetstream 31
3102500-6 TPE331-10UF-513H bP-42150 JetZtream 31
*3103310-1 TPE331-10UG-513H #P-63123 Jetstream 31
TPE331-IOUGR-513H R11 Jetrtrea. 31
3102600-7 TPE331-10UR-513H All Jetstream 31
*3102540-1 TPE331-1lU-601G All Metro III/Merlin IVC
*3102540-2 TPE33r-11U-602C All Metro III/Merlin IVC
*3102540-3 TPE331-llU-611G 6~-44486 Metro III/Merlin IYC
’3102540-4 TPE331-llU-612G #P-44470 Metro III/Merlin IVC
"3102540-6 TPE331-llU-612G #P-44474 Metro III/Merlin IVC
*3102920-1 TPE331-11UA-601W All Pucara IA-66
’3102920-2 TPE331-11UA-611W Al 1 Puca ra 1A-66
’3103400-1 TPE331-128-701A #P-65003 No Current Appl i catf on
t8roduction Incorporation Point
8. Reason
(1) Problem: Under certain adverse conditions cavitation of oil in the
turbine hearing support assembly can cause erosion pittlng of the
Beryllium Copper nut on the turbine end of the shouldered shaft.
Excessive plttfng may cause failure of the 8eryllium Copper nut and
can result in major damage to the engine.
(2) BacLground: Tm, recent Beryllium Copper nut failures were at-
tributed to erasion pitting. Both failures occurred at less than
100 operating hours since overhaul and/or hat section inspection.
(3) Action: Erosion pitting of the Beryllium Capper nut can be detected
C by accomplishing a zpectron~tric analysis of oil sampler collectedIn accordance with the Engine Maintenance Manual at an acceleratedschedule as detailed in this service bulletin.
TPE331-72-053n
~nv 0/~5 P~o" 3[p
SERYICE BULLIETIHGRRRETT TVRBINE ENGINE COMPANY
C.. Descrr pti on
This service bulletin provides an inspection schedule for accomplishingan accelerated spectroo~tric oil analysis program.
D. Compliance
NOTE: Canpllance with this service bulletin is no longer required when
Service Bulletin, TPE331-72-0533 and TPE331-72-0534 have been
compiled with.
Service Bulletin TPE331-72-0534 is NOT applicable to enginesidentified with an asterisk in Paragraph A.
Recommended. Garrett recommends that this service bulletin be acccm-
pllshed in accordance with the following schedule.
(1) Less than 20 engine operating hours time since new, overhaul, or
any maintenance to turbine bearing support area, initial sampleshall be taken at 25 engine operating hours; and at 25 engine oper-
ating hour intervals thereafter until 100 engine operating hours
a re accumu la ted. Resume normal SOAP schedule after 100 engineoperating hours.
(2) n.re than 20 engine operatrng hour. and le~r than 100 engine oper- Cating hours time since new, overhaul, or any maintenance to turbinL
beanng support area; initial sample shall be taken within five en-
gine operating hours of receipt of this service bulletin; and at 25
engine operating hour intervals thereafter until 100 engine operat-
ing hours are accumulated. Resume normal SOAP schedule after 100
engine operating hours.
(3) More than 100 engine operating hours and less than 500 engine oper-
ating hours time since new, overhaul, or any rraintenance to turbine
bearing support area; a sample shall be taken within 50 engineoperating hours of receipt of this service bulletin.
E. Approval
FAA a pproved.
F. Manhour Requirements
An estimated 15 minutes are required to obtain and package each oil
sample.
6. Material Price and Availability
Information regarding price and availability of parts may be obtained
from the Garrett General Aviation Services Company, Oistribution Center,
2340 East University, Phoenix, AZ 85038.
TPE331-72-0530
~ay 9/86 paoe 7
SERVICE BULLEVIHGARRETT TURBINE ENGINE COMPANY
H. Tooling Price and Availability
No special tooling is required except that already listed in publica-tionr referenced in Paragraph J.
i. Weight and Balance
No change.
J. Publications References
The sources of information used in the preparation of this service bul-
letin include Garrett engineering docunentation and the folloving.
Engine Engine Illustrated
Partl Overhaul Maintenance Parts
Model No. Manual Manual Catalaq
TPE331-25AA NA 72-00-85 72-00-84
TPE331-25AB NA 72-00-88 72-00-87
TPE331-250A NA 72-0~85 72-00-84
TPE331-25D8 NA 72-00-88 72-00-87
TPE131-25FA NI\ 72-00-85 72-00-84
CTPE331-43A NA 72-00-85 72-00-84
TPE331-43BL NA 72-00-88 72-00-87
TPE331-47A NA 72-00-85 72-00-84
TPE331-55B NA 72-00-88 72-00-87
TPE331-1-100F NA 72-00-92 72-00-91
TPi331-1-101B NA 72-00-92 72-00-91
TPE331-1-101E NA 72-00-92 72-00-91
TPE331-1-10~F NA 72-00-92 72-00-91
TPE331-1-101Z NA 72-00-92 72-00-91
TPE331- 1-151A NA 72-00-92 72-0~sl
TPE331-1-151G NA 72-00-92 72-00-91
TPE331-1-?51K NA 72-01~92 72-00-91
TPE331-2-201F, HA 72-00-92 72-00-91
TPE331-2-201C NA 72-00´•92 72-0~91
TPE331-2UA-2030 NA 72-00-92 72-00-91
TPE331-3V-303G NA 72-00-98 72-00-97
TPE331-3U-303Y NA 72-00-98 72-00-97
TPE3)1-3U-304G NA 72-00-98 72-00-97
TPE331-3UW-303G NA 72-00-98 72-00-97
TSE331-3U-303N NA 72-00-90 72-00-17
TPE331-5-251C NA 72-00-95 72-00-94
iPE331-5-251K NA 72-00-95 72-00-94
TPE331-5-2520 NA 72-00-95 72-00-94
TPE331-5A-2520 NA NA NPI
TPE33!-5-252K NA 72-00-95 72-00-94
TPE331-5-252M NR 72-0~95 72-00-91
TPE331-5-254K HA 72-00-95 72-0rr9i
TPE331-5-25SK NA 72-00-95 72-0~94
TPE331-6-251H NA 72-00-95 72-00-94
TPE331-6-252[1 NR 12-0~45 12-ii0-95
TPED3i-S-2j2L NA 72-01-95 72-C1-9’
11":331-72-053’
9!P~ i
’i
I~ SERVICE BULIETIRGARRETT TUABINE ENGINE COMPANY
Engine Engine lilurtrated IPart/ Overhaul Maintenance PartsModel Na. nanual Manvai ~TTPE331-6-25ZM NR 72-00-95
TPE331-6-252T NA 72-01-95 72-01-94TPE331-6-253B NA 72-00-95 72-00-94TPE331-6A-251M NA 72-00-95 72-00-94TPE331-6A-252M NA 72-00-95 72-00-94~PE331-8´•4015 NA 72-00-13 72-00-11iPE331-8-4025 NR 72-00-13 72-00-11TPE331-8-4035 NA 72-00-13 72-00-11TPE331-8-404S NA 72-00-13 72-00-11TPE331-8-406S NA 72-00-13 72-00-11iPE331-1O-501C NA 72-00-28 72-01-17TPE331-10-501K NA 72-00-29 72-01-18TPE331-10-501M NA 72-00-27 72-01-15TPE331-10-511C NA 72-00-28 72-01-17TPE331-1O-511K NA 72-00-29 72-01-18TPE331-10-511M NA 72-00-27 72-01-15TPE331-10G-511S NR 72-00-48 72-00-47TPE331-10R-501C NA 72-00-28 72-01-17iPE331-1OR-502C NA 72-00-28 72-01-17TPE331-10R-511t NA 72-00-28 72-01-17TPE331-10R-512C NA 72-00-28 72-01-17TPE331-10R-513C NA 72-00-28 72-01-17TPE331-10U-501G NA 72-00-23 72-01-15iPE331-10U-502G NA 72-00-23 72-01-15TPE331-10U-5036 NA 72-00-30 72-01-19TPE331-10U-511G NA 72-00-23 72-01-15TPE331-1OU-512G NA 72-00-23 72-01-15TPE331-1OU-513G NA 72-00-30 72-01-19TPE331-1OUA-5016 NA 72-00-45 72-00-44TPE331-10UA-511C NA 72-00-45 72-00-41
TPE331-10UF-501H NA 72-00-42 72-00-41iPE331-10UF-511H NA 72-00-42 72-00-41TPE331-10UF-512H NA 72-00´•42 72-00´•41TPE331-10UF-513H NA 72-00-42 72-00-41TPE331-10UG-513H NA 72-00-42 72-00-41TPE331-~OUGR-513H NA 72-00-42 72-00-41
rPE331-10UR-513H NA 72-00´•42 72-00-41TPE331-llU-601G NA 72-00-25 72-00-24T PE 331-1 1U- 6 026 NR 72-00-25 72-00-24TPE331-llU-611G NA 72-00-25 72-00-24TPE331-1lU-612G NA 72-00-25 72-00-24TPE331-llUA-601W NA 72-06-25 72-00-24
TPE331-llUA-611W NA 72-00-25 72-00-24
TPE331-128-701A NR NA NA
iPE331-72-0j30
I~lay 9/86 Pnge 6
9
i~ SERVICE BULLEBIWGRRRETT TURBINE ENGINE COMPANY
K. Service Bulletin References
Review of the following should be accomplished by the operator for poss-ible incorporation at the tirn~ this service bulletin is accomplished.
Service BulletinNQ. Service Bulletin Title
72-0533 ENGINE TURBINE SECTION Replaceor Rework 011 Scavenge Pump Assembly
72-0534 ENGINE REDUCTION GEAR AND SHAFTSECTION Inspect Torsion Shaft
L. Other Publications Affected
Same as those listed under "Publications References".
C
May 9/86 TPE331-72-0530
Pa?e 718
Ir,
I~ SEIUICE BULLETIRIGARRETT TURBINE ENGINE COMPRNY
CA. Obtain’Oil Sample for Analysis
N91E: Do C(O_I submit engine oil filter with oil samples for this service
bulletin.
(1) Obtain an oil sample for SORP analysis in accordance with EngineMaintenance Manual using container provided in Kit, Part No.
831022-1.
(2) Fill out data sheet provi ded wi th Ki t, Pa rt No. 831022- i.
(3) Package the oil sample to prevent leakage in accordance with EngineMaintenance Manual.
(4) Forward oil sample and data sheet to Garrett Turbine Engine Com-
pany, P.O. Box 5217, Phoenix, AZ 85010 (Attn: S.O.R.P. Program, SB#
72-0530) for analysis, or any Garrett authorl~ed laboratory capableof detecting Berylllum in the oil.
(5) If the result of the S.O.A.P. analysis is 0.1 to 0.2 PPM Beryllium,accanpllsh the following within five engine operating hours of
receipt of analysis results. If the result of the S.O.A.P.
analysis is more than 0.2 PPM Beryllium, accanpllsh the followingprior to the next flight.
(a) Contact Customer Support Department of Ga rrett General Avia-
ti on Servi ces Conpa ny. (Telephone 602-225-25903
(b) Inspect torsion shaft in accordance with Service Bulletin,TPE331-72-0534.
(c) Rework or replace scavenge pump in accordance with Service
Bullerin, 72-0533.
(d) Inspect spur gearshaft assembly (scavenge pump drive) as
fol lows.
1 Visually inspect for evidence of damage to spllnes or gearteeth. Damage is not acceptable.
2 Visually inspect for evidence of wear on the scavenge pump
end of the gearshaft. Wear is not acceptable.
2 Measure gearshaft for corrett length.
May 9/86 TPE331-72-0530
Page 9
SERVI@IE BULLEBH#GARRETT TURBINE ENGINE COMPANY
Shpit Length
TPE331-25AA 4.21 to 4.24 inch (Used with 865046-2
scavenge pump only)TPE331-25DA 4.21 to 4.24 inch (Used with 865046-2
scavenge pump only)iPE331-25FA 4.21 to 4.24 in ch (Used wi th 865046-2
scavenge pump only)TPE331-43A 4.21 to 4.24 inch (Used with 865046-2
scavenge pump only)TPE331-25AA 4.11 to 4.14 inch
TPE331-25AB 4.11 to 4.14 inch
TPE331-250A 4.11 to 4.14 inch
TPE331-25DB 4.11 to 4.14 inch
TPE331-25FR 4.11 to 4.14 inch
TPE331-43A 4.11 to 4.14 inch
TPE331-43BL 4.11 to 4.14 inch
TPE331-47A 4.11 to 4.14 inch
TPE331-55B 4.11 to 4.14 inch
TPE331-1 4.11 to 4.14 inch
TPE331-Z 4.11 to 4.14 inch
TPE331-3 4.11 to 4.14 inch
TPE331-5 4.11 to 4.14 inch
TPE331-5A 4.78 to 4.82 inch
TPE331-6 4.11 to 4.14 inch
TPE331-8 ´•1.11 to 4.11 inch
(Ured vith hydraulicTPE331-10 (Pre 72-0466) 4.71 to 4.74 inch
torque sensor)TPE331-~OUA (Pre 72-0466) 4.71 to 4.74 inch (Used with hydraulic
torque sensor)TPE331-10 (Post 72-0466) 4.67 to 4.70 inch (Used with hydraulic
torque sensor)TPE331-10UA (Post 72-0466) 4.67 to 4.70 inch (Used with hydraulic
torque sensor)TPE331-10UG (Pre 72-0466) 4.78 to 4.82 inch (Used with torque ring)TPE331-1OUGR (Pre 72-0466) 4.78 to 4.82 inch (Used with torque ring)TPE331-ll (Pre 72-0466) 4.78 to 4.82 inch (Used with torque ring)TPE331-ilU (Pre 72-04661 4.78 to 4´•82 inch Ured u(th toryue ringiTPE331-10UG IPort 12-04~61 4.111 to 4.18 inch Ured w~th torque ring
TPE331-10GR Post 72-0466 4.74 to 4.78 inch Used with torque ring)TPE331-11 (Pos t 72-0466) 4.74 to 4.78 inch (Used with torque ring)TPE331-llU (Port 12-0466) 4.111 to 4.18 inch (Ured with torque ringiTPE331-12B-701A 4.74 to 4.78 inch (Used with torque ring
4 If spur gears’lft assembly fails.any of the precedingsteps, replace in accordance with Engine Maintenance
Manual.
Mav 9/86 TPE331-72-0530
Page 10
SEWVICE BULkEllstBGARRETT TURBINE ENGINE COMPANY
I "p’acE Beryllium Cap.er nut in ac~ardance vifh EngineMaintenance Manual.
(e) Change engine oil and filter in accordance with Engine Main-
tenance Manual.
(6) After each special oil sample cycle is canpleted, enter compliancewith this service bulletin in engine log book noting engine opera-
tion time and compliance with this service bulletin.
(7) Refdentiffcatlon of equipment is not required.
(8) Complete Compliance Certificate form and mail. Contact local Gar-
rett authorized service center to obtain forms, if required.
C
May 9/86 :PE3?1-72-05jn
Page i!
18
~ilSE"VleE BULLETIRGARRE~T TURBINE ENGINE COMPANY
C3. Ma teri a 1 informatl on
Unit
List Instru~tions-New PN Ouantity price" Key Uord Old PN Oisposition
831022-1 AR 112.00 Kit
’Refer to Sectron 1, Paragraph G for information regarding price and availabil-ity of parts.
May 9/86 TPE331-72-0530
Page 12 ILt
~illService InformationGulfstreamAerospace
SERVICE INFORMATION NO. 51-219
21 February 1987
DOWTY ROTOL SERVICE LETTER NO. E.123 REV. 2
MODELS AFFECTED: MODEL 690C, SERIAL NOS. 11600 THRU 11?35.
MODEL 690D, SERIAL NOS. 15001 THRU 16042.
MODEL 695, SERIAL NOS. 95000 THRU 95084.
MODEL 696A, SERIAL NOS. 96001 THRU 96100.
MODEL 69SB. SERIAL NOS. 96062, 96063, 96069, 96015, 96018, 96085 AND 96201 THRU
96208.
REASON FOR PUBLICATION TO RECOMMEND COMPLIANCE WITH DOWTY ROTOL SERVICE LEWER NO.
E.12S REV. 2.
COMPLIANCE: REFER TO DOWTY ROTOL SERVICE LEITER NO. E.123 REV. 2.
BY WHOM WORl( WILL BE ACCOMPLISHED: A P MECHANIC OR EqUIVALENT.
ESTIMATED MAN HOURS: TWO (2) HOURS.
PARTS DATA: NONE.
SPECIAL TOOLS: NONE.
ACCOMPLISHMEM INSTRUCTIONS:
1 Comply with Dowty Rotol Service Letter No. E. 113 REV. 2.
2. Fill out and moil Compliance Card.
ELECTRICAL LOAD: NO CHANGE.
WEIGHT AND BALANCE: NO CHANCE.
SPARES AFFECTED: NO.
PUBLIC~TIONS AFFECTED: The Airplane Maintenance Manual chenge required by this document will be
incorporated st the next seheduied revision.
RECORD COMPLIANCE: Make an appropriate entry in airplans maintenance records as Follows: Service Informntion
No. 51´•219, dated 27 February 1981, entitled "Dowty Ratol Service Letter No. E. 125 REV. 2,~ accomplished(date)
Pale I ot 1
LIMIISD
K()~fOI.
SERVICE 1ETTER
SERVICE LETTER NO: E.123 REV.L.
DATED: 14TH JANUARY,1987.
ATTENTION: CHIEF INSPECTOR.
SUBJECT: G.A.PROPELLEROE-ICING SLIP RINGS.
PROPELLER TYPES: R.306 OULFSTREAM COMMANDERR.321) FAIRCHILD METROR1324) 6 MERLIN.R.333 BAE JETSTREAM 31R.334 CASA 212
R.339) PIPER CHEYENNER.341)R.352 FOKKER F5OR.354 SAAB SF.340.
Because of the problems brought about by lubricant contamin-ation of slip ring feces, this Service Letter is issued toadvise Operators of the necessity to clean Frequently thisitem, as fallowa:-
i.
For aircraft in regular ’Normal’ service, at wee~lyintervals, clean slip rings by rubbing vigorously with aclean lint-free cloth moistened with Arklone. M.E.K. orToluene. If slip rings are very dirty or pitted, polishlightly with a fine grade silicone carbide paper or glasspaper.
/cont’d...
2.
IBQW~ILIMITID
SE RV ICE 1E TT ERPACE 2 No. E.1~3 REV.E.
2.
After cleaning slip rings as necessary, proceed as follows:
A. Using a clean linen cloth apply ’Cramolin CleaningFluid’ to the slip ringe. Where necessary, rub for
approximately 1 minute to allow the oxides to become
saturated.
B. Leave surface for a further 30 seconds to complete
the saturation process.
NOTE: After applying ’Cramolin Cleaning Fluid’
the surface may turn green. This is normal
and is not the result of corrosion but
indicates that oxides are being dissolved.
C. Wipe the slip ring surface with a clean linen cloth
until it is clean and shiny,
D. Using a clean linen cloth, apply a thin film of
’Cramolin Special’ to the slip rings.
E. ’Cramalin Cleaning Fluid’ and ’Cramolin Special’ may
be obtained from:-
CAIG LABORATORIES INC.,
P.O.BOX J,1175-0 INDUSTRIAL AVENUE,
ESCONDIDO,CALIFORNIA 92025.
Telephone No. 619-745-4341.
Thi s Letter should read i n conjunl´•ti on w i th Arcrn rl
Maintenance Manual .1026, tl-1(-30, pages 304-n04/1
issued by: SERVICE MANAGER,DOWTY ROTOL LIMITED,
CHELTENHAM ROAD,GLOUCESTER GLE 99H.
r Ser~iceGulfstreamAerospace
’SERVICE INFO~IATION NO. 81-220S1 March 1881
INFORMATION CONCERNING ECU FAILURE
MODELSPIPFECTEL): MODEL 880C, 8ERIAL NOS. 11800 THRU 11’195.MODEL 880D, SERVLL NO9. 15001 THRU 11042.MODEL 888, SERIAL NOS. 85000 TXRU 81084. n
MODEL 885A, SERIAL NOS. 98001 THRU 86100.MODEL 88511, SERIAL N08´• 88082, 88069, 98088,880?5, 880?8, 88085 AND 88201 THRU 88208.
REASON FOR PVBLICAIION: SEVERAL RECENT ECU FAILURES HAVE DEMONSTRATED A NEED TO~i?""/ REEMPHASIZE THE 8YMPTOhIS OP AN ECU AILURE AND THE APPROi
i PRUTE ACTION BY THE PILOT AS SHOWN hi THE APPLICABLE APM/POA.
COMPLIANCE: N(YI´• APPLICABLE.
BY WHOM WORK WILL BE *CCOMPLISHED: NOT APPLICABLE.
APPROVAL: ENGhTEERINO DESUIN ASPECTS ARE FAA APPROVED.
~1N HOUAS: Nor *PPLIC*BLB.
PARTS DATA: NOT APPLICABLE.
SPECIALTOOLS: NONE.
ACCOMPLISHMENT INSTRUCTIONS:
The following provides a brief description of the symptoms which may accompany a mechanical failure ofthe Environmental Control Unit (ECU). Also listed are typical procedures that may be used in the eventof a mechanical failure of the ECU which will allowsale handling of the airplane. This document ispublished to bring to the attentlan of the pilot the type of information an this sublfft that is avall8ble inthe Pilot’s Operating Handboo~ and does not override the speclllo data in the Pilot’s Operating Handboor.
ENVIRONMENTAL C~TROL UNIT FAILURE
A mechanical lailure of the ECU will result in a complete loss of cabin temperature control. The cabinpreslrieatlon system will continue to Operate; however, cabin temperature will increase significantly.An ECU failure may be accompanied by an odOr of hot oil and hot air ducts, followed shortly thcrea(terby light smoke from Uls airoutlets. A noticeable increase in cabin temperature will occur. Il.theseindications are observed,check the airflow from an overhead outlet. Hot air coming from an overheadoutlet indicates a failure of the ECU, since only cool or cold air comes from the overhead outlets during.normal operation.
If an ECU failure occurs and it is deemed necessary to daprseeurlae, proceed as follows:i. PASS OXY Switch ON, if carrying passengers in any sent other than Ni cockpit seat.2. Oxygen Masks DON. Verify all occupants are receiving oxygen.S. ENVIR MASTER Switch ENVIR MASTER position to close ECU shutoff valve. Cabin willaapressuri~e when valve closes.4. Valve YERIPY CLOS~D by checking for airflow from environmental outlets. U.irflow
5. Bleed Air Selector IIOTH CLOSED. Bafh valve lights illuminated.
ORIGIINBLL As
RECEIYED 8Y ATP P´•pr LIZ
BERYICE INFORMATION NO. SI-220
*0´•r CPlacing Bleed Air Selector to BDTH CLOSED will renderthe alrdriven artillclal horieon and the wing and empe-nnage delcer boots inoperative.
B. Desoent- INPTIATE bbelow 12,0Wleet, ilpossible.
Ram air va~ves will open when cabin depres~urleasl This will aid in clearing the cab~n of smoka andfumes and will reduce cabin temperature.
Do not attempt to use ECU until mallunclion has been corrected.
ELECTRICAL LOAD: NO CHANGE.
WEIQHT AND BALANCE: NOCHANOE.
SPARES AFFECTED: NO.
PUBUCAnONSIFPeCTeD: ~I-NONE.
RECORD COMPLI\NCE: NOT APPLICABLE.
"I.I
C
Pnce 2 of 2
iD:´•
A~space
LIERVICE-IN~ORMATION Npi 51222
IRApril 18X5
ooWTv RCTOt SERVICE BULLETIN 61-1d49(6140066408026 QnlB)
i.
MODEL~FFECTED: MODFIL BBOC, SERI~L´•NOS_11BW THRU 11156;
:XgX~t´• 08811;~I,NOt~awl TNRUIIWL
MODEL B8SA,R86B18ERIA4 ~$gBOBL-gBOB4 88008,886?6: 96~8,:BOOR6 A~ 90201 THRII
86206.
84806 FOR PUBUCI\TION: T1PqS~COMMEND OOMPLIANCB:WITH:~ BVLLETIN 6i
~TO DO~ ROTOL
Bv W~lwonK WILL Be *C~PHEDI A 4 08 EQUIVALFINI:
appRovari REFERTO:DOWTY-ROT04 BERVICEBULLWIN 81´•1048´•
´•_ :EsnMarEo 11411 nOuAs: DOUrpy ROTOL BIRVICPE OVLLETIN 81-1048.,1:
:~i:: pARTS:Dlml DOWTY ROTOL BBKVIGk BULLERN B1-i~g.
N~
ii ServioelBullet(n 81´•1048.
2, i ~il out and mail Campli.nee Card.in
eLEcrRlcaL Loaa: NO CW~N(IB.
WEBMTIND:BAL*NEB: NO CHANOB.
BNO.
PueLlcnnons AFFECTID: Th. Alrplsne: Maintonn~oe MqnuAl hb.~ rrqulrrd by this document will hrincorporated at tke nout sohbduled revl.lan.
RECORO;OOMPLIP~NCE: MBkS nn appmprlata Bntrvrn slrplsne ~ee insmaliollNo. 81-222’,´•dsted 15 April 1BB1. entitled IDowty Rati;l Servioe Ra116tln B1;1MBZmawnplish;d ´•.::(date):’:
oR8csg~atAs RBcojued Ry
ATPi
i i
IDQPilT~I’I ROTOL
StRVICt BULL[IIN
OF ESSO BEACON 325 GREASE
MOULFICATION No.(c)VP3179
1. PLANNING INFORMATION
A. Effectivity
Ai rcraft (c)Propeller
Gulf stream Aerospace Commander R306/3-82-F/7Fairchild A/C Corp. Metro III Merlin IVC R321/4-82-F/8Fairchild A/C Corp. Merlin IILC R324/4-82-F/9FMA IA66 R316/4-82-F/6jetstream 31 R333/4-82-F/12CASA 212 R334/4-82-F/13Embraer Xingu 111 R338/4-82-F/14
B. Reason
(1) Evaluation of Esso Beacon 325 grease has produced evidence thatit is far less susceptible to oil separation than Aeroshell 7and is therefore less likely to leaL during service.
C. Oescription
(1) This modification introduces Esso Beacon 325 grease to bestocked and used as a preferred alternative to Aeroshell 7 andTexaco Low Temperature EP grease.
NOTE Esso Beacon 325, Aerosheil 7 and Texaco Low TemperatureEP grease are not to be intermixed.
O. Compliance
(1) Recommended at next overhaul or repair.
E. Approval
(1) The modification to which this bulletin relates has beenapproved by the United Kingdom Civil Aviation Authority. Thetechnical content of this bulletin is approved under theauthority of CAA Approval No.DA1/1018/39.
F.
(1) Normal time.
Feb 10/8761-1049
Page 1 of 3
BD~TiYI ROTOt
S[RV~Clt´• :IIHflll
G. Material
(1) No modification kit is issued. The grease should be purchasedas and when required.
H. iaolinq
(1) None.
i. Weight
(1) None.
3. References
(1) Dowty Rotol Component Maintenance Manual 61-10-16.
(2) Dowty Rotol Component Maintenance Manual 61-10-19.
(3) Dowty Rotol Component Maintenance Manual 61-10-20.
(4) Dowty Rotol Component Maintenance Manual 61-10-24.
(5) Dowty Rotal Component Maintenance Manual 61-10-25.
(5) Dowty Rotol Component Maintenance Manual 61-10-27.
(7) Oowty Rotol Maintenance Manual Publication No. 1002.
(8) Dowty Rotol Maintenance Manual Publication No. 1008.
(9) Dowty Rotol Maintenance ManUal Publication Na. 1009.
(10) Oowty Rotol Maintenance Manual Publication No. 1013.
(111 Dowty Rotol Maintenance Manual Publication No. 1014.
(12) Oowty Rotol Maintenance Manual Publication No. 1019.
K. Other Publications Affected
(11 The above manuals.
til-lO49 Feb 10/87Page 2
IBQIFlfYI ROTOL
StRYICI BULLtllN
ACCOMPLISHMENT INSTRUCTIONS
A. Embodiment Instructions
(1) On build of blade group use E550 Beacon 325 grease for all loca-tions illustrated in the component maintenance manual with theexception of the blade mating faces of the blade bearings bottomraces. At these locations the grease detailed in the componentmaintenance manual is to continue in use.
Method of identification
(1) Record Mod. No. (c)VP3179 in the propeller log book.
3. MAIERIAL INFORMATION
A. The modification will be embodied in future production by the manu-
facturer. Stocks of pre-modification greases will not be maintained.
New List Old InstructionsPart No. qty. Price Keyword Part No.
Esso Beacon A/R N/A Grease Aeroshell 7 or
325 Texaco Low
Temperature EP
Feb 10/87 61-1049
Page 3
Li
~IIi.
Infoi mationCa ´•~Gulfstream
~1:"´•-´•
;-~iERVICE INFORMATION NO. 51-223
90 November 1981
E;inlN LANDING GEAR TRUNNION PIN ACCESS COVER..-´•´•i,;-
MODELS AFFECTED: MODELS 880T, 680V AND 88(1W, SERIAL NOS. 1418 THRU 1R~O.
MODEL 681, SERIAL NOS. 6001 THRU 6072. gjMODELS 690, fiSOA AND 89011, SERIAL NOS. 11001TIIRU 11548, 11550 THRU 11586.
"MonnL s~ac, aRlhr NOS. IIBODTIIRU 11195
MODEL 6I)OD, SERIAL NOS. 15002 TIIRU 16042.
MODEL 695, SERIAI. NO9. 9500L) THRU 95084.
MODEL B(IBh, SERIAL NOS. 04001 THRU 96100.
MODEL 695R, SERTAI,’NOS. 96062, 96063, 98069, 98075, 96078, 96088 AND 96201 TIIRU
86208.
REASOu FOR PUBLIC;TION: TO PROVIDE AN ACbESS HOLE 1N .NDINE NACEWIE FOR EASIER REMOVAL
OF MLD TRUNNTON PIN.´• THIS WILT, ALLOW rOR REMOVAL OF MAW GEAR
WITHOUT LOWERING ENQINE NACELLE WHEN COMPLYIND WITH TIIE FIVE
(5) YEAR OMR I~NSPEFPION.
COMPLIANCE: AT OWNERS DISCRETION.
al~l NOTE
IF ANY PROBLEMS hPE ENCOUNTERED WHaB COMPLYING
WITH THIS SERVICE INFORMATION, CONTACT YOUR
NEAREST CULFSTREAM COMMANDER AUTHORIZED
SERVICENTgR.
BY WHOM WORK WILL BE PICCOMPLISHED: A P MECHANIC OR E4UIVAI;ENT.
APPROVAL: F,NDINgERING DESICrN ASPECTS ARE F~h APPROVED.
ESTIMATED MAN HOURS: MODELS 680T, BR0V, 680W, G81, 690, 690A AND 690n TWELVE (12) H01~R9.MODEL 690C, SERIAL NOS. 11800 THRU 1168?- TEN (10) HOURS.
MODEL 695, SERIAL NOS. 85000 THRU 95081- TEN (10) HOURS.
MODEL B9Bn, SERIAL NOS. 96001 THRU 88003 TEN (10) HOURS.
MODEL 890C, SERIAL NOS, 11688 THRU 11135 FIVE (5) HOIIRS.
MODEL 890D FIVE (6) HOURS.
MODEL 695, SERIAL NOS. 85082 THRU 95084 FIVE (5) HOURS.
MODEL 095A, SERIAL NOS, 96004 THRU 86100 FIVE L5) HOURS.
MODEL 695B FIVE (6) HOURS.
PARTS DATA: PARTS REQUIRED TO COMPrlY WITH THIS SERVICE INFORMATION ARE TO BE
PADRICATED LOCALLY. TB8 NAS13981vm-2 BLIND RIVETS ARE TO BE PROCURED LOCAIlLY.
SPECIAL TOOLS: NONE.
ORIOIMqlL 1
C As Racdivsd ByAIP i
-::1;::
iSERVICE INFORMATION NO. SI-22S
~s;"´•l-"e*;i~s‘a´•V´•
i ")Odl-’´•i
:iom
:::::-;l-riiLP 1; i ´•II´• liBO’Ci~i-’i´• i;,;il
CUT 2.0" Dln. HOLE IN NPICELLESKIN. HOLE TO BE IN´•LINE WITH
MAIN LI\NOING GEAR TRUNNIONPIN I\LLOWINO ACCESS FOR REMOVALAND REPLACEMENT
NP~S1388MI´•2 BLIND
;XRIVET 18 PLSI SEAL ACCESS COVERWITH PRC l000 IORE(IUIVPILENTI FIREWPILL
J.sa ola, ACCESS COYER~ .8EALANTMAKE FROM 0.016" TYPE
521 ~MS6610 CRES STEEL
IIN FLI\TI
I’J.
iy´•
a*o´•´•TYP
2.76´•’appnax.or:SKIN
APPROX.
FROM EDGE
N~CELLE SKIN IREFI
LEFT INSTALLATION SHOWNRIGHT INSTALLATION OPPOSITE
---:i CW.
i;
SERVICE INFoRMATION NO. SI´•223
CCaMPLISHMENT INSTRUCTIONS:
1 Fahricate a B.BO´•inch diametsr access cover using O.O1B-inoh type 321 AMS5510 corrosion resistant steel sheet stock
Lreter to Figure 1).
2. Remove lan and right engine exhaust pipe aasembliea as outlined in the Airplane Maintenance Manual.
t C*(nlON
The main landinggear trunnion pin is very close B We nacelle
akin; therefore, caution should be taken to prevent damaging the
trunnim pin when cutting hole in nacelle.
S. Cut a a.0-inch diameter hole in outbaard side dleR and right naeelle as shown in Figure 1.
i. Locate, form and drill access rovar, fabricated in step 1., on angina nacelle (re9er to Figure i).
5. Apply PRC1000 flrswall sealant or an aluivalant sealant between access cover and nacelle skin and installaccess cover on nacelle using NA81SgsM4-a blind rivet (8 places)(refer to Figure i).
B. Reinatall left and right engine exhaust pipe assemblies asoutlined in the Airplane Maintenance Manual.
7. Fill out end mail Compliance Card.
ELECTRICAL LOAD: NO CHANGE.
WEIGHT AND BAL~NCE: NO CHANGE.
PPI\RES AFFECTED: NO.
C´•Ir UBLICATIONS AFFECTED: NONE.
RECORD CD*PLUNCE: Make an appmpri´•te entry in airplane maintenance records as follows: Service InformationNo. SI-225, dated SO 188?, entitled "Main Landing Oear TNnnion Pm Access Cover." accomplished
(date)
ORIGINALAs Reii~ived By
A;I~P 1
PageSofS
~I:Service information Culhnr~mAnospPaCarpmrim
"dla%~
SERVICE INFORMATION NO. SI´•n6a dune 1987
SUNDSTRAND ECU AIR CYCLE MACHINE OIL REPLACEMENT
YODELS IFFECTID: MODEL BW~, SERIAL NOS. 11809, 11815, 11829, 11840, 11876, 11871, 11879 AND 11709.
MODEL 89011, 8EIUAL NOS. 15002, 15021, 16056 AND 16087.
MODEL 895, SERIAL NOS. 96054 AND 96066.
MODEL BgSA. SERIAL NOS. 98001, 90020, 98089, 88098 AND 98100.
MODEL 8958, SERIAL NOS. 98075, 98078, 98085, 98208 AM) 98205.
REASON FOR PVBUCA7H)N: THE ECU AIR CYCLE MACHINE WAS SERVICED WITH THE ~NCORRECT TYPE
OF OIL BY LIZTNDSTI~AM) CORPORATION. THIS 8ERVICE INFORMATION IS
BEING ISSUED TO ENSURE THAT THE CORRECT TYPE: OP OIL IS USED IN THE
AIR CYCLE MACMNE.
COHPLI~NCI WITHIN 1IWTY (SO) DAYS AFTER RECEIP~ OF THIS SERVICE INFORMATION LET~ER.
BY WIOOM WORN WILL Be A P KECHANIC OR EQZTIVALENT.
APPROVIL: ENDINEER~N(I DESIGN ASPECTS ARE RAA APPROVED.
d .9M11760 Y** .OYRI: IbRO~RS.
NOTE
A credit of SSO.M) rill be laaued to We author~ad OuVstraam
Commander Se~iCsntar. Wat performs the aorL, upon reosip~ of a
properly sllaoutad Warrenty Claim and a completed ComplianceCard, provided Wat Wa Warranty Claim and Compliance Card an,
sent in ~ithln seven (7) mrling days aRar We aork has been
aemmplishsd
PP~RTS DATA: The MIhil Jet 254 oil (appmximately 7.8 ounEee or apprrlmatoly 220 E´•E´•) may be procured IOFd~ly´•
SPECllLTOOLS: NONE.
~CCOIPUWMENT INSTRVCTIONS:
1. Cain access to ECU Air Cycle Machine LACM) located in aR fi~aelage.
2. Chwk for aerial number of Air Cycle Maddne on Ah Cycle Machine identi8cation plate.
a. If aerial number of ACM matches aerial number, noted in Figure 1., lor your airplane model and aerial number,proceed to step 5.
4. Ifaerial number of ACM does not match aerial number, noted in Flaue 1., for your airplane modal and serial
number, fill out and mail Compliance Card noting aerial number of ACM inatalled on your airplane. Proceedto Record Compliance.
Page lofS
SERVICE INFORMATION NO. 91-225
ACM I MODEL 5WH: MODEL 89oD MODEL Bg5 I MODEL BS5A MODEL 89611S~ SM 8/N 9/N 9/N SRJ
151 11809
642 11615
296 11629
292 11816
AS05 lien
206 11679
207 11109
671 15002
285 16021
149 16056
220 15037
887 96054I
245 95065
196 98001
487 1 I I 1 98020
1BB 98095
567 98100
300 98076
188 98078
149 98086
118 98203
652 88206
281 in Dapartmsnt of Astatian Auatralls Stook
Fl9un(.
Pogo 2 of 3
SERVICE INFORMATION NO. 81-225
5 Drain and replace existing oil in Air Cycle Machine with iMobii Jet 294 oil lapproximately 7.5 ounces or
approximately 220 c.c.1 as outlined in Chapter 21 of the Airplane Maintenance Manual.
NOTE
The oil pan on the ACM is accessible while the unit is still
installed on the airplane.
B. Fill out and mail Compliance Card.
ELECTRICAL LOAD: 110 CHANGE.
WEIGHT AND BALANCE: NO CIWNOE,
SPARES AFFECTED: NO.
PUBLICATIONS AFFECTED: NONE.
RECORD COMPLIANCE: Malts an appropriate entry in airplane maintenance records as follows: Service InformauonNa. SI-229, dated 2 June 1987, entitled "Sundstrand ECU Air Cycle Machine Oil Replacement." accomplished
tdate,
Page 3 of 3
Q~IIService Information Whnmnaoapreffhmcqlin
Service Information No. 56255
14 AuguM 1089
AEROQUIP GENERAL AVIATION ALERT NOTICERECALL ON AEROQUIP 601 nOSE
BVLLmN NO.W1
UODeLSAPPECTED: Models 590 WOA. BOqS. 90111, 9dOE, 9806, 880, 8906, 6896. 8506(6). BBOFL.8sopun, 680r, and ?a0 Serial Nos. 291 thrn 189cl, Model 9008 Serial Nos. 3090
thru 3529, M~del 886 8alpl Nos. 1Mol thru 12068, M~dela 890. 890A. 890B. BWKC Serial Nos.
11W1 Uua 11156. Model BgOD Serial Noa 18001 thru 15W2, Models 895, BSSA 605B Serial
Nos. 89990 thN 98909.
REASON FOR PUBUCIT~ON: TO COMPLIANCE lRIIH AWOQUIP GENERAL AVIATION ALERTNOTICE. RECALL ON AEROQI~ 601 HOSE, BULL&IW NO. 901.
NOTICI
INVICSI~OATION REVEAL AEROPIRP 801 HOSE
INSTALLATION ON ABOVE LISTED OULFSTREAM
COMMANDER THEREFORE AEROQUIPGENERAL AVIATION ALERT NOTICE RECALL ON AEROQZIIP801 HOSE BULLETIN NO. 901 OOBS APPLY
couFulNce: REFER TO AEROOUIP GENERAL AVIATION ALERT NOTICE RECALL ON AEROqULP 801
HOSE. BULLEIW NO. 991.
BY wnor worts Mu BE A p MECHANIC OR EQUIVALEPIT.
APFROYIL: REFER TO AEROPUIP GENERAL AVIATION ALERT NOTICE RECALL ON AEROQUIP 801 HOSE,BULLETIN NO. 901.
ESTBlATEDUANi(OVRSl REFER TO AEB09~ GENERAL AVIATION ALERT NOTICE RECALL ON
AEROPUIP 601 HOSE, NO. 001.
PIRTSDATA: REFER TO MROQUIP GENERAL AVIATION ALERT NOTICE RECALL ON AEROQUIP 601
HOSE. BZTLLETINNO. 901.
SPeCllLT00~5: REFER TO AEROQUIP GENERAL AVIATION ALERT NOTICE RECALL ON AEXOSUIP 801
HOSE, BULLETIN NO. 901.
*CCOUPUSnMan INSTRVCTK)IIS:
I. CMopb ´•rith As~ulp aswral Aviation Ale~ Notice Recall on Aemquip 801 Hwe, Bulletin No. 901.
a. Fill rutend mail Compliance Card.
ELECIRICIL IOAD: Nochange.
welo~ AND BAWnCEr Nochangs.
SPARES No.
PUBWWITMN8 IFFeCTrD: None
ReCORD Mate an appropriate aRJ in ahpns maintenance roarda as Ulas: Servloa InmrmaHon No.
SI-aS8 dated al Auguat. 1889 entitled IAsmlulp (isneral Aviation AlertNotice Recall on Aemquip 801 Hose, Bdlatin
Ne 001" aecompllahsd (dete)
Page 1 of 1
Como,´•l~n sullatlnM1(4\1´•10(10´•11 D1II´•IPn
*ugusl 1888~´•o´•on Flint
JmSoumE´•~l*r´•nu~´•d´•on. M1(9205´•19~2nhone 517´•7818121IU 517´•387-~118I´•m: 711412
~Li\eroquip
GENERAL AVIATION ALERT NOTICE
RECALL ON AEROQUIP 601 HOSE
Aarogulp is pre´•ently recslllns COltaln PPBC’lied 601 hose iTha 601 type nose assemblies could be IdBntlfled
a´•.emller Tne suspect hose aosamblles cOnslslof /L.l.quip Mth one 01 the following Aeroquip part numbers.
80( hose with rubber cure dates from 1084 inrough 3087.
Thl. hose could have been installed on any General Aviation or601WOI´•´•III 00112(1-´•-Ui´• ~201(1-i-UI´•
experlmsnlal aircraft from Plpnl 1984 throush May 1988.B0l00li´•´•´•1´• 601113´•´•´•´•´• ~ZO(1Z´•´•´•xii´•
~01002´•s´•´•n ~OttsO´•-´•i´•i OZOttJ´•´•´•uui
6010031-1111 00tl~(´•´•´•´•u´•
60100611111 L101371´•I´•´•´•~I
´•I sa~mz..,..
60101911111 601´•8’1´•´•´•´•1 ~10((1´•´•11´•´•
gnl* n´•lna oolon~ losl´•ll ~10100´•´•´•u´•I ~10119´•1´•11´•1
401040-1-1111 020102´•´•-´•´•´•´• ~ZMm-I´•uu´•
Aerooulo requsas that any aircraft ownersloperatorr wno ~01011´•´•´•´•´•´•´• 620(031´•´•1´• ~20121´•´•´•´•1´•´•
have ´•n.lalmd hoses durtnp the aboveldcntlfi.d time LHriod (120101~1-u´•´• (120122.1.1´•11
601064.1.lu11 IPO(D6´•´•-llII 820113´•´•´•´•LI´•notna loll-ulno
.0(01.1´•´•´•´• ´•I010L1´•1´•11 62012.´•1´•1´•´•´•
´•ImmOdl**l~ inrFre’ ´•"e aircraft for sly 4arwulp hoses .0106~´•´•´•u´•I LW~?)´•´•´•r´•´•´•
/\erooulp.orOouced *o)e assemblies are identified with a 601067.1.1111 ~10101)-´•.1´•´•´• 620126.1.1111
metal idantlt;sallon b,nd IIO(W(i´•´•´•´•´•´•l 620109´•´•´•´•´•´•´• 620(~L-´•´•´•I´•1
00(0(1,´•´•´•111 620110´•´•11´•´•
IWnfdladwlmsnAE701´•i´•lu
part number are nor suspect and mould nor be removed´•’"O"V’´•
´•´•.´•m´• unless. U.M1 inrpection and/or performance ot routineloll Isr-
u~n X LDCulol maintenanee. a problem with the hose io identi(ied.
´•’´•´•*Y’""´•)t the hose assembly has no bandor it is illapibla aM’L’´•’’’’ 81´•´•´•´•1-´•11´•
10*1-I 1I1´•´• can be Y.ntai.d.O an Aaroqulp ness. the hose snam-
bly should be removed and replaeed if it was installed
9YsRE9 ´•´•´•´•P~- from ~pnl 1984 througn May 1988
(11IIII.UII ´•This notica does nor apply to Oulhtrsam Alroaft. pell
H.liCDgt.r 01 MCDonneII Dougla. nelicooter Model 600.
Separate ~´•Nica bulletins will )´•.asuad for operators of
OuHmwmAircish doll WEmsrsnd McL~nndl DouglasHOIIEW101 Model 900.
´•AnV *srogun 601 type hose assambliasthat are identified
with 1 094 throu0h 3(187 hosefula date are suspeCt endWhen the suspect hose aeeembltes have been IdenlltiW.
should be removed The cure dates may be rhowncontact one of the authorilad Aeroquip distributors idantlfied
CD1084 through CD3C187on the reverse side of ih~ A).n Notice. and prwids that
ed the hose cure data. are Mt Ihom. then AHoguip Aaoquip distnbuutw unfh ihtollouing iotorm´•lion:
801 type hope assemblias identified with an assembly Ownar.. Name
date of A208q throuan A2(18B should be removed. It Address:
assambty date I. shown m month and year. remove all phone Number:
assemblies with assembly date A.rl 1984 throu0h May ACE,sh R´•gkn´•lion Number:1988. Nose Assembly. part Number a Description:
Can~ou´•d
IIIIIUIOVI OOMPINI
a
The sulh~rilad*sralu,p d,rtributor will send vou reolecernent it there are any qus~tion´• or it vou are uns~k toconfecf one olho´•e susmblin. Complete in´•tructien~ ln(ormin0 you how 1c the wthoriled *aroqui. dinributn´•, then eonfaft *´•roqulp st
return the suspect hose lotheAeroquip di´•tributor 19095411888will he included with the replacement h~´• w~´•mMUI. You
~III n´• ~rl.b.or b. m~ m*am´•m hu
´•~tsmblis´• snd ~YDleqbCnlly Ered1te6 (O( the lull amount
when the dl,tribulor rK´•lv´•l the removed IueoectIkie otter tor nocherge reoles´•mant hoee n.smbllsl
asaembller.
AEROQUIP HOSE SHOPS
Asro Hardware 8 Supply. Inc. Herbe,AIrcratt Service. Inc. Vsr(la EOtsrprisso. Inc
4301 NW. 3816 Street 124 Center Street 2350 South Aimon skd.
Miami Springp. FL 33( 86 El Sagundo. CA 90245 Chandler. At 89249
Phone: 305-888-2411( Phone: 213´•322´•9575 Phone: 802´•883´•8936
Plimano Hosal Unlimited. inc. Nals~n´•Dunn. Inc.
5801 wan Harry 818 Dooll* Drive 940 South Vail Avenue
P.D. Box 12370 San Laandro. CA 94577 Monabell~. C* 90840
Wlohits. I(S 87277 Phone: 415-832-4177 Phone: 212´•724-3’105
Phone: 3189432377
Piedmont Aviation Supply Alama Accelawin. Inc.
FDurnier Rubbsc~ B SuWh Com~sny 3820 North Libnty Street t08UV´•nd´•la
1341 Nonon Avenue Win´•t~nS´•l´•m. NC 27102 San Antanio. TX 78218
P.D. Box 285 Phone: 919´•~87´•8993 Phone:
Columbua. OH 43218
Phone. 814´•294´•8S43 Superior Air Pane. Inc.
oll´•r rX 76244
Phone: 800-84&4873
j
~I ~´•lr
Service Information CIIRC~*FT COePOR*TIONno. Bac 9369
Aaetaa, WA 88PJTel: (2oB1CFr8T87 Far:(206)4351112
Service information number 236, rev A
August 2, 1995
INSPECTION AND REPLACEMENT OF FLUID LINES
Models affected: All Twin Commander airplanes
Reason for publication: To recommend replacement of all hoses installed in enginecompartment after a maximum of 10 years time in service and to recommend inspection of ail
other fluid hoses and lines annually.
Compliance: Twin Commander Aircraft Corporation recommends the part replacement and
inspection intervals stated in this publication.
By whom work will be accomplished: A P mechanic or equivalent
Approval: This Service information is FAA approved.
Estimated man hours: 2 hours per side
Special tools: None
Accomplishment Instructions:
Replace all engine compartment hoses with new hoses after a maximum of 10 years in
service. This applies to all hoses’installed forward of the engine compartment firewall. Inspectall tubing and tittings. Replace or repair any wom, damaged, or corroded fittings and tubes.
Inspect all fuel, oil, and hydraulic hoses, tubes, and fittings in the airplane at every annual
inspection. Replace any worn or damaged hoses, regardless of age. Replace or repair any
worn, damaged, or corroded frttingr*and tubes.
Note: Replacement hoses may differ in construction and outside diameter from originalhoses. Be sure that clamps properly secure the hoses. It may be necessary to change to
different size clamps.
Electrical load: No change
Weight end balance: No change
Spares affected: No
Record compliance: Make an entry in the airplane maintenance records as follows: "All
engine compartment hoses replaced date i in accordance with SI-236A, dated 8-2-95".
Senrice information *IRCRIFT CORPOR*TION
P. O. B~xS3aJ
~lneton, WA 88223 Tsl: ~06)4358797 Fax:
SERVICE INFORMATION NO. Sl-237
14 Fsbruaryl984
NEN PRODUCTION REPLACEMENT FUEL CELLS
"PERMAFLM"m~
MODELS AFFECTED: All models of Twin Commander aircraft. except Models 520. 560. and 700
REASON FOR PUBLICATION: To provide aircraft owners and maintainers with pad numbers for use when
ordering new and improved Twin Commander PERMAFLEXTM Factory Authorl2ed
fuel cells to replace obsolete Engineered Fabrics fuel cells.
COMPLIANCE: When replacement of existing fuel cells becomes necessary.
BY WHOM WORK WILL 8E A P mechanic or equivalent.ACCOMPLISHED:
APPROVAL: Not applicable.
ESTIMATE MAN HOURS: Not applicable.
WEIGHT BAL4NCE: When installing new fuel cells, calculate the fuel system weight change using the
values stenciled on the fuel ce~ls. If the weight change exceeds 5 tbs., incorporatethe weight change in the weight and balance section of the aircraft flight manual.
NOTE: IF ANY PROBLEMS ARE ENCOUNTERED WHILE COMPLYING WITH THIS SERVICE INFORMATION, CONTACT
YOUR NEAREST FACTORY AUTHORIZED SERVICE CENTER.
NEW rM FUEL CELL REPLACEMENT PART NUMBERS:
OLD NEW OLD NEW
Tcne P/N Tcne P/N 1%AC P/N Tcne P/N
630069-501/ ;502 511/-512 630302-1/ -2 -503/ -504
63ooaa´•so7 -508 -509 i 610 630302601 -502 -505 j -506
630061-5011 -502 -511/-512 63o3a4-1/ -2 -503/ -504
630061-507/ -508 ´•509/ -510 630304-501/ -502 -505/ -506
630082-507 -511 630307-11 -2 ´•5011502630063-501/ -502 -511/-512 630308-1/ -2 -501/602630063-507/ ´•508 ´•509/ ´•510 630353-1/ -2 -505/ ´•506
630084501/ 502 ´•515/ -516 630353-503/ 504 -507/ -508
830064-507/ -508 5111-512 630354-1 -503
630064-509/ -510 513/-514 630354-501 -505
630204-501 -503 630355-1/ -2 ´•5031 -504
630296-1/ -2 -503/ -504 630355-501/ -502 -5051 -506
630296-501/ -502 -505/ -506 630356-1/ -2 -501/ -502
6303011 i -2 -503 -504 630393601 -502 -503 j 604
630301-5011 -502 -5051 -506 630397-1/ -2 -5031 -504
63a397-so1! ’502 -5051-506
NOTE: FOR FUTURE REFERENCE WHEN ORDERING AND REPLACING EXISTING FUEL CELLS WITHNEW ’PERMAFLEX"rM FUEL CELLS. PLEASE PLACE A COPY OF THIS DOCUMENT IN THE FRONT OF YOURILLUSTRATED PARTS MANUAL AND YOUR MAINTENANCE MANUAL.
jr~w
Service I nfbrmation AIRCRAFT CORPORAT~ION
P.O. Box 3388, Arlington, WA 98223435-8797 fax1360)435-1112
Service information 238
January 18, 1996
DEICER 8007 INSTALLATION
Models affected: all airplanes with deice boots.
Summary: This information updates the maintenance manual instructions for installing deiceboots.
Compliance: When deice boots are replaced.
By whom work will be accomplished: A 8 P mechanic.
Approval: This Service information is FAA approved.
Instructions:
Follow the instructions in the maintenance manual when installing deice boots, with the
following updates and clarifications.
1) Cement 1300L is equivalent to EC-1403 and may be used in its place.2) Toluol may be used anyplace that MEK is called for.
3) ProSeal 890 may be used in place of EC1031 and EC801 fillers.
4) Boots manufactured by Aerazur do not require leer or conductive paint.5) It is important that the mounting surface of the boots and the airplane be thoroughly
cleaned.
a) It is important that the curing times and temperatures be observed: 24 hours at
temperatures of BO"F and above, or 72 hours at temperatures below BOOF.
7) Boots on the right side of the airplane must be the same, except for being opposite, as the
corresponding boots on the left. In particular, they must have been made by the same
manufacturer.
8) It is recommended that when a boot on one side of the airplane is replaced that the boot
on the other side be replaced at the same time.
Page lbl
~s TW/N
COMMANDERSERVICE IN FORMATION
teolo asM DR NE
ARLINGTON. WA 98213-7832
PHONE (380) 435-8797 FAX (350)4351112
Service Information No, 244
January 27, 1997
PROCEDURES FOR OPERATING IN ICING CONDITIONS
AND TO THE USE OF POWER SETTINGS BELOW FLIGHT IDLE
FOR TURBOPROP AIRCRAFT
MODELS AFFECTED: Models 680T, 680V, 680W, 661, B90, 690A, 690B, 690C.690D,695,695A,895B
REASON FOR PUBLICATION: To provice aircraft owners and operators with the FlightManual/Pilot’s Operating Handbook insertion regardingprocedures for operating in icing conditions and to the use
of power settings below flight idle.
COMPLIANCE: Prior to next flight.
BY WHOM WORK WILL BE ACCOMPLISHED: Owner/Operator/Flight Crew
APPROVAL: Flight Manual/Pilot’s Operating Handbook revision is FAA
approved.
ACCOMPLISHMENT INSTRUCTIONS:
i. Removal of obsolete pages and insertion of revised Flight Manual/Pilot’s Operating Handbook
material in appropriate sections of manual.
2. Complete attached postage paid Compliance Card and return to Twin Commander Aircraft
Corporation.
Page 1 at 1
COMPLIANCE RECORD
SERVICE INFORMATION NO. 244
PROCEDURES FOR OPERATING IN ICING CONDITIONS
AND TO THE USE OF POWER SETnNOS BELOW FLIGHT IDLEEOR TURBOPROP AIRCRAFT
MODEL AIRPLANE SIN REO. NO. TOTAL TIME IHOURS)
OWNER NAME
ADDRESS
TELEPHONE NO FAX NO
COMPLIANCE WITH SERVICE INFORMATION NO. 244
Please fill in date below that revisions were filed in appropriate Flight ManuaNPilot’s
Operating Handbook.
DATE
WORK PERFORMED BY IPRINTED)
ISIGNATURE)
COMPANY
ADDRESS
TELEPHONE FAX
Z
TW/N
SERVICE INFORMATION A/RCR4FTCORPOR4T~’/ONARLINGToFI AIRPORT
f 9010 59TH DR. N.E.
ARLINGTON, WA 98223-7832
PHONE (360) 435-9797 FAX(360)435-11~2
Service information No. 249
May 18,2000
Installation of 300004-501 Removable Duct as Part of SE 214
Airplanes Affected: Those airplanes for which Service Bulletin 214 is required.(690D and 695A: all serial numbers except 15037, 15041, 15042,96064, 96072, 96088.
6958: serial numbers 96063, 96069,96075, 96078, 96085, and
96204 through 96208.)
Twin Commander Aircraft recommends that the Removable Duct, 300004-501, be installed
at the time of the first inspection that is done in accordance with item r~l on Service Bulletin
214. Inspection item on pages 7, 8, 9, and 10, refers to figure 25 on page 59 and is requiredat or before 7500 hours of operation. Making the duct removable will simplify future re-occurringinspections.
Kit SB214-4-501 contains the parts and drawings for this installation. It can be ordered from anyfactory-authorized Twin Commander Service Center.
HTW/N
CO~MIMANDERSERVICE INFORNIATION A/RCR4FTCORPOR4T~’/ON19010 59TH DR NE
ARLINGTON, WA 98223-7832
PHoNE(360)435-9797 FAX(360)435-1112
Service information 251
March 19, 2001
PPG Windshield Moisture Seal Installation and Repair Procedure for Installed Twin
Commander Aircraft Corp. Windshields
Models Affected: 690A/B/C/D, 695, 695A/B With Part Number 360043-1/-2, -3/-4, -7/-8,-11/-12, -11SS/-12SS Windshields
Reason for Publication: To Insure Maximization of Windshield Service Life by Installation of
Moisture Seal (Hump Seal) per Twin Commander Aircraft Corp.Custom Kit No. 163
Compliance: At next Scheduled Inspection.
Who Will Accomplish Work: A&P Mechanic or equivalent.
Approval: Engineering design aspects of Custom Kit No. 163 are FAA approved.
Estimated Manlhours: 12 Man Hours
Parts Data: Custom Kit No. 163 is available from authorized Twin Commander Aircraft Corp.Service Centers. Order Kit Part No. CK163
Record of Compliance: Make an appropriate entry in the Aircraft maintenance records as
follows:
Custom Kit No. 163 Moisture Seal Installation dated August 4, 1998
Accomplished _(date)
Complete Service Information Letter No. 251 Compliance Form and return to Twin Commander
Aircraft Corp.
COMPLIANCE RECORD
SERVICE INFORMATION 251
PPG WINDSHIELD MOISTURE SEAL INSTALLATION AND REPAIR PROCEDURE FOR
INSTALLED TWIN COMMANDERIAIRCRAFT CORP. WINDSHIELDS
MODEL AIRPLANE S/N REG. NO. TOTALTIME (HOURS)
OWNER NAME
ADDRESS
TELEPHONENO FAX NO
COMPLIANCE WITH SERVICE BULLETIN 251:
MOISTURE SEAL INSTALLED YES O NO B
DATE
WORK PERFORMED BY (PRINTED)
COMPANY
ADDRESS
TELEPHONE FAX
*L
M~N
COIMIMANDERSERVICE INFORMATION A/RC~9AFTCORPOR4TIONi 9010 59TH DR NE
ARLINGTON, WA 98223-7832
PHONE (360) 435-9797 FAX(360)435-1112
Service Information No. SI-252
April 3, 2002
Exhaust Pipe Seal Installation Instructions
Models Affected: 690A, 690B, 690C and 690D Ecluipped With TPE 331-10T Engines.695, 695A and 695B
Reason For ]Pubiication: To provide detailed instruction for the replacement of exhaust pipe seals.
Compliance: Recommended Procedure
Approval: Twin Commander AircraR Corp.
By Whom Work Shall
Be Accomplished: A&P Mechanic or Equivalent
Parts Data: 1 ea. 144-01-10045-01 Seal
18 ea. MS24693C26 Screw
18 ea. MS21046C06 Nut
18 ea. NAS1169C6 Washer
Special Tools: None
Instructions:
1. Remove Exhaust Pipe from the Aircraft.
2. Remove Old Seal and Scrap.3. Remove any burrs or sharp edges fkom the interior of the exhaust stack seal area.
4. Remove any burrs or sharp edges from the exterior surface of the exhaust stack seal area and from the
aft edge of the -65 Flange assembly.5. Clean the surfaces in the area of seal (items 3&4 above) with an abrasive pad or emery cloth. Remove
dust with a cloth wetted with isopropyl alcohol or methanol.
6. Locate the split in the metal insert in the tail of the New Seal and mark the end locations with ink, soR
pencil or equivalent.7. Fit the New Seal inside the exhaust pipe with the tail end of the seal oriented forward. (ref. Figure 1)8. Position the seal so that it is even with the forward edge of the exhaust pipe. (ref. Fi~re 1)9. Position the seal so that the split in the metal insert of the seal (ref. Item 6 above) is about ’/2" from an
existing fastener hole.
10. Clamp the seal to the exhaust pipe using padded clamps spaced between some of the existing fastener
holes.
Page lof3
rw/N
COIMIMANDER
SERVICE INFORMATION14010-59THDRNE
ARLINGTON, WA 98223-7832
PHONE(360)435-9797 FAX(360)435-1112
Service Information No. SI-252
April 3, 2002
Caution i
Do Not Clamp Bulbed Section of the Seal!
Exercise Care to Prevent Damage to the Seal or Exhaust Pipe!
1 1. Verifjr that the forward edge of the tail side of the seal is even with the forward edge of the pipe and that
the metal insert is Centered over the existing fastener holes.
12. Drill through existing fastener holes, seal and seal metal insert using a 9/64" or .140" drill bit.
13. Add one new hole to secure the other end of the seal metal insert. Locate the hole .20 to .25" in from the
edge of the pipe and about ~z" from the end of the metal insert.
14. Secure the seal to the exhaust pipe using MS24693C29 Screws, NAS1169C6 Washers and
MS21046C06 Nuts with screw heads and washers inside of the pipe at each hole location. (ref. Figure-i)15. Apply "Fel Pro C5A" or Silicone #5 grease to the seal and sealing surface of the -65 Flange Assembly.16. CarefUlly fit the exhaust pipe over the flan,oe assembly by applying forward force while simultaneously
rocking the pipe side to side and up and down.
17. Secure the exhaust pipe to the nacelle. 2 Places)
Note: If the exhaust pipe has been re-polished while it was removed for the seal replacement, pleaseobserve the following recommendations.
In order to preserve the shiny polished appearance of the pipe precautions must be taken to ensure that the
surface is not exposed to contamination.
Twin Commander Aircraft Corp. recommends that the pipe be handled with clean cotton gloves and that the
polished surfaces be masked with a protective covering during the fit and installation process.
Work surfaces that may come in contact with the pipe should be clean and dry.
When the exhaust stack is installed and any cleaning activity adjacent to the pipe has been completed the
protective covering may be removed.
Prior to the first engine run after installation the pipe should be thoroughly cleaned with Isopropyl Alcohol
or Methyl Ethyl Ketone.
The Key to Maintaining the Polished Surface Begins at Installation!
Arllv Contamination Present On The Surface At The First Ex~osure To Heat Will Degrade The
Annearance Of The Exhaust Stack Over Time
Page 2 of3
I_
TWIN
COMMA IVDERS E RVICE I N FORMATI ON
ARLINGTON. WA 98223;1832PHONE (360) 435-9797 FAX(380)435-1112
Service leformntion No. SI-252
April 3, 2002
Exhaust Pipe Seal Instnllntion
onIaINaLAr sv
arp Figure 1
Forward Edse of Exhaust Pipe I Tail ofBulb Seal
MS24693C26 Screw NAS1169C6 Washer MS21046C06 Nut(l8 Places)
Page 3 oT3
~--e L-- I I I I_
I
TW/AI
NDERSERVICE INFORMATION A/RCRAF;TCORPOR4TIO19010
SSTH DR NE
ARLINGTON, WA 98223-7832
PHONE(360)435-9797 FAX(360)435-1112II I
Service Information No. Sl-255
December15,2003
Picture Window Upper Channel Inspection
Models Affected: 690, 690A, 690B, 690C and 695
Reason for Publication: Reports of cracking in the 310704-1 and -2 Upper Frame Channel discovered duringtrouble shooting pressurization leaks or window replacement.
Compliance: External visual inspection is recommended at the next 100/150 Hour Inspection and
each 100/150 Hours thereafter.
Internal detailed visual inspection recommended at window replacement, while area is
accessed for compliance with Service Bulletin No. 223, window replacement or when
troubleshooting pressurization leakage at the wing root area.
Approval: Twin Commander Aircraft Corporation
By Whom Work Shall A&P Mechanic or EquivalentBe Accomplished:
Parts Data: New 310704-1 and -2 Channels are available through Twin Commander Aircraft
Corporation Authorized Service Centers. The new channels are manufactured from
.063" thick material with a specified grain direction to improve fatigue life.
Instructions: External Visual Inspection:
Visually inspect the external skin lap directly above the picture windows for evidence
of working fasteners or gaps in the skin lap. If evidence of working rivets or gaps are
found, proceed to the internal detailed visual inspection.
Internal detailed visual inspection:
Remove interior panels as necessary to gain access to the channel through the
lightning holes and removable door of the inner skin. Visually inspect the outboard
flange radius of the channel for cracks. This will require the removal of accumulated
sealant in an area of limited access. Cracks typically occur between rivets on the
outboard flange of the channel.
Caution!
Care shall be exercised during sealant removal to ensure that no damageoccurs to surrounding structure. It may be necessary to remove inner skin
panels to facilitate sealant removal.
If damage is noted in the area accessed above, remove inner skin sections as
required to inspect the full length of the channel.
Remove and replace the channel if any damage is noted.
I’age 1 of I
-~C ´•r LI I _I
~nN
COMMANDERSERVICE INFORMATION
19010 59TH DR NE
ARLIN GTON, WA 98223-7832
PHONE (360) 435-9797 FAX(360)435-1112I I~I
Service Information No. Sl-256
December I~, 2CH)3
Main Landing Gear Up-lock Assembly Bolt
Models Affected: SO0/A/B/U/S, 560F, GSOF/FWFLP/FP, 680T/V/W, 681, 685, 690/A/I)/C/L) and 695/1\/1~
Reason for Publication: Recent field reports have indicated failures of the AN174C-21A Uolt installed at the pivot
point of the up-lock arm. Refer to Item 10 of the illustration below. Rilurc of the bolt
result in the landing gear not achieving or maintaining an up and locked position with a
landing gear unsafe indication.
a 134
I? ~cp&s
´•1
SL~ a A
It 10
Compliance: At the next scheduled inspection and at 5 Years or 3000 Hours thereafter, perform an
inspection of the bolt.
Approval: Twin Commander Aircraft Corporation
By Whom Work Shall
Be Accomplished: ASrP Mechanic or Equivalent.
Parts Data: Replacement Rolts may be procured locally (P/N AN174C-21A).
Instructions: Remove the left and right main landing gear up-lock bolts and inspect for cracb, L~OITOSi011
and straightness. Tile inspection method (Magnetic Particle, Fluorescent I’enctranl, clc.) sll:lll
be determined by the inspection personnel performing the inspection. if the holt is acccpla\,lf,reinstall and verify proper up-lock operation. If the bolt fails to pass inspection, replate tile
bolt, verify proper up-lock operation and notify Twin Commander Aircraft Corporation.Please provide the aircraft serial number and time in service of the bolt. If you are unable to
determine the time in service of the bolt, provide the aircraft total time.
Record of Compliance: Make an appropriate entry in the aircraft maintenance records referencing Service
Information No. SI-256 compliance.
Pnge I of I
SRA
Aircraft Technical Publishers Customer Service
101 South Hill Drive 6AM-5PM PST M-F
Brisbane, CA 94005 (800)227-4610
ATP Grid Index to Manufacturer’s Publications:
Twi n Commander A/C
695, 695A, 695B
SERVICE ALERT
1) Applicable AD
2) Part Kit (1)
Issue Number 3) Part Kit (2)Issue Date Issue Description 4) Compliance Time
4/19/94 FLIGHT CONTROL SYSTEM RIGGING 1)
04/19/1994 AND TRIM TAB FREE PLAY CHECK 2)
3)
4)SEE ISSUE
End of Index
04/05/2002 Copyright Aircraft Technical Publishers Page 1 of 1
GC 0853 SI VA
jrC~w’wtrlllYAYIIAI~
CIIA F T C O R P O ~d TIO NSERVICE ALERT
1991 1Revised; April 19, 1994
FLTOHT CONTROL 8YSTEM RTOOTNC AND TRII TAB FREE PLAY CHECI.
NOTE: This Service Alert supercedes the January 4, 1994 Service Alert.
Changes have been made to this service Alert regarding control surface balance.Also, references to Section 3? of the applicable Maintenance Manual have been
added. Revised text is identified by a black line in Ehe right hand margin.
MODELS AFFBCTEDI 685, 690, 5901, 6908, 690C, 6900, 695, 6951L, 6951
REASON WR PWLlCCATTONI Reports have been recently received from the field
concerning aileron trim tab free play in excess of Ehe established service
limits. Service Bulletin 186, which was issued 23 December 1981, defined
~he actions required to assure that no excessive free play exists on aileron,eleva~or and rudder trim tabs.
Excessive trimtab free play can cause vibrations which can lead to structural
damage and possibly to loss or the airplane. Also, it is equally importantthat the entire flight control system be kept adjusted within the limits
specified by the applicable Airplane Maintenance Manual.
This Service Alert is being issued to re-emphasire the importance of ensuringthat trim tab free play on each control surface is within limits specified bythe applicable Airplane Maintenance Manual. Also, a complete check of the
flight control system rigging is required.
COMPLTANCEr
Initially; within the next 50 flight hours or six months time in service,whichever comes first.
Repetitive; At each annual or other scheduled inspection, except for
checking control system balance. Balancing needs to be
accomplished when any change is made which may affect the
control surface balance, such as painting or repair.
BY wHOM WORE l8lLL BE ACCOMlPLTSREDI R&P Mechanic or s~uivalenC.
APPROVAL: N/A
9PBC~AL TOOLS i As nOEsd in the applicable Maintenance Manual.
RELATED
1) Airplane Maintenance Manual applicable to each airplane model.
2) Service Bulletin No. 186, dated 23 December 1981, Trim Tab Free
Play Measurement.
ACCOMPLISHMEPP~ i
Conduct a complete inspection of the flight control system rigging in accordance
with Section Vrr or Section 27 of the applicable Maintenance Manual. Give
particular attention to control surface balance, cable tension, control surface
movement limits, and trim tab movsmen~ limits.
Comply with the inetruetions outlined in the section "Control Surf~ce ITrim Tab Free Play" in Sec~ion VII or Section 27 of the applicable Maintenance
Manual.
IWIHCOMUIIIDER ~IRCA*PTCORPORI\TIO 1WXI)-SO11( 01. N.E. Irllnglon. WI\ 98113 Talqnons(2PO) 436811 F´•x No. (208) P3Cll(a
CK
Aircraft Technical Publishers Customer Service
South Hill Drive 6AM-5PM PST M-F
Brisbane, CA 94005 (800)227-4610
ATP Grid Index to Manufacturer’s Publications:
Twi n Commander A/C
695, 695A, 6958
CUSTOM KIT
1) Applicable AD
2) Part Kit (1)Issue Number 3) Part Kit (2)
Issue Date Issue Description 4) Compliance Time
132 R1 ENTENDED RANGE FUEL SYSTEM 1)
07/13/1982 MODIFICATION 2)SEE ISSUE
3)
4) SEE ISSUE
133 IMPROVED SIDE WINDOW DEFOG 1)
09/15/1981 SYSTEM 2)SEE ISSUE
3)
4) SEE ISSUE
134 IMPROVED INLET AIR SUPPLY 1)
01/11/1982 SYSTEM FOR YOUR JETPROP 2)SEE ISSUE
ENVIRONMENTAL CONTROL UNIT 3)
4)SEE ISSUE
135 COMMANDER AURAL MACH OVERSPEED 1)
09/29/1982 WARNING SYSTEM 2) SEE ISSUE
3)
4)SEE ISSUE
136 IMPROVED TAIL LIGHT/STROBE 1)
1111511984 LIGHT SYSTEM 2) 310052- 509
3)
4) SEE ISSUE
137 WINDSHIELD ANTI-FOG SYSTEM FOR 1)
01/18/1985 YOUR GULFSTREAM COMMANDER 2) SEE ISSUE
JETPROP 3)
4)SEE ISSUE
04/05/2002 Copyright Aircraft Technical Publishers Page 1 of 2
GC 0853 SI CK
1) Applicable AD
2) Part Kit (1)
Issue Number 3) Part Kit (2)
Issue Date Issue Description 4) Compliance Time
138 R1 AUTOMATIC ENGINE IGNITION 1)
06 14i 1987 SYSTEM 2)SEE ISSUE
3)
4) DISCRETION
140 R1 NOSE GEAR STEERING 1)
05/18/1988 MODIFICATION 2)SEE ISSUE
3)
4) DISCRETION
141 ENVIRO AIR CONDITIONING AND 1)
07/17/1992 PRESSURIZATION SYSTEM 2)SEE ISSUE
INSTALLATION 3)
4) DISCRETION
158 ADDITION OF INBOARD DE-ICE 1)
01/08/1996 BOOTS 2) CK158-501
3) CK158-1
4) DISCRETION
163 PPG windshield moisture seal 1)
08/04/1999 installation and repair 2) CK163
procedure for installed Twin 3)
Commander windshields 4)See Issue
End of Index
04/05/2002 Copyright Aircraft Technical Publishers Page 2 of 2
GC 0853 SI CK
SERVICE PUBL1CATIONSCulfstrramnmerican
revision notice Coamandar Divi~ien6001 N~rh R~cLwall Avsnus.Bsfhany. OLI´•horm 13008
CUSTOM I(IT NO. 152
REVISION NO. 1
19 ~uly 1981
EXTENDED RANGE FUELSYSTEM MODIFICATION KIT
APPROY*L: FAA DOA 8W-2 APPROVED.
Page 2 at 20 PARTS DATA
CBANGE: Part Number of Hose
WA8: 650584-35 Aose
NOW: 650384-31 Hose
Page 1 of 1
tB 118´•~L sljslC~mmnda,Oirilion
CUSTOM KIT NO. 192 2 MARCH 1981
RN EXTENDED RRNGE FUEL S’bSTEM MODIFICA-
TION KIT FOR YOUR GULFSTREAM COMMRNDER
J~TPROPS.
Olncreases usable fuel capacity from 425 gallonsto 474 gallons for a range increase of approxi-mately 240 nautical miles.
EFFECTIVITY: MODEL’890C (EIOHT FORTY), SERIAL NUMBERS 11800 THRU 11999
MODEL 895 (NINE EIGHTY), SERIAL NUMBERS 95000 THRU 95040
Obtain this kit and tull details trom your nearest Dulfstream Commander SetvlCenter.Price: $8500.00, plus insfallation
Pd~s ´•uWnf ~ifhoulnolra
C
ORIGINALAS RECEIVED BY ATP. COPY ON ORDER
4
L
Udfucrcnlnnmrricn,
9 ATi~A/’ s,~ ~sen/
OOSiYlM KIT NO. 1822 Mnneb 1981
EXTeNDED RANGE FUEL SYSTEM MODIFICATION KIT
MODELS *RECTED: MODKL SS(lO, SERIAL NO~ 1IMLO THRU 11989 AND MDDEL 696, SERIAL N05. 96000
THRV 85MO.
REASON FDR PUBUCATION: M PXOVIDB MCREAB&0 PUELOAFAClTY.
COMPLII\NCI?: AT OWNEW D18CR6T10N.
NOTE:
a´• ANY PROBLRMII ARE ENCOUNTERED WHILE
~FPALLINO TH18 CVBT(IM KPI~. YOUR
NEAREST OULFSTR&~M COMMNYDBR ~IITHOHIZBO~LERVLCeNTERPACnPI"I.
BY WHOY WORK: WILL BE A k P MeCHANIC OR EPUrVAI.ENT.
*PPROVAL: PM DOA aw-a APPROVER.
eSTlmnm~MANHOuRs: FORTY SeVEN (II) HOUR8 (USINC´• WFF CILIBRA.I\IOK PROCED~LE) TWU(1.Y TWO
(821 HOURS (U8WC DRY CALLBRATION PROCEDIIR&)
PARIS DATI\: PaN rsollired to install Wia Custom Kit may ha pmursd thruuEh your ncare~l CulIdrrsm Connan-
d~r SuviC´•ocar Farlligl Tor 88580.00.
Oultom KIC No. 132-1 Model 590C Airplana, uial n~a 11008 thru 11853 and hloCI 096 Airpl´•nw. ari´•l n~s 88800
Ulru85MO.
Oosrom KtlNo. 199-2 Madsl sfloc Ai~lanlq wrial no’s 11861thN IlsPg.
Rdmlrr the ´•ppliuble eulllom kl~ n(daM) model and ractary rrial oumbrr v~hsn ord*rine Curlorm Kif No. 1~P´•l or
111-2, eun~l(lnlt ortho rollowing:
K~NrlSa-I
PTY OTY PAWTNO. DESCRIP1ION
1 u. 1 as. 110156-060 DEcnl
)c´• 2 ea. 6300821
2nl. 1.4´• 69MSl´•b01 OnrhetZoa. 1 e´•. 860082505 Gasket
II En 2~u. b30821´•M)1 P)aLI
)sC 2,. 630310-1 Tulr1 sn, lea, 630351.1 (:EIIIUI FIIII CCII1Ln. 8311931L101 Csncar Flrl Cell
AS2 se. Zen. Rl(lY58´•S Piller illnck
b a3o3aa´•s(IECEIVED HY Aq´•p
lan. lull. 6309688 Filler ill~rk
11L 1 r´•. 630368-7 Filler (Ila~L1 cn. len. 6311358-8 Filler Hl~sL
1 el. )pU. 530JJB-18 Fill*r nLrk ~i ’i
CLIS1~M 101NO. 1SZ
(177 Q1’Y P*IO.NO´•Kit h’~ 132-1 KilNo 132-2
1 I´•. la. 630965-80 Pil*r Black
I.a. 1 nn. 83(IS6BgS Filler Black
1n. lee, g~a96e9( sillar Black
Pea 2c´•. 630568-96 Flll.rBlak
Jar. 6 an. 830969-80 Fillsr Black
2s´• 690309-609 Pu´•l 9u´•n~iB Monitrr
2an. 2 sc. 630972-501 TmnsmitUr
II. 2sn. 630913-601 Tr´•namilLer
241- 2re. 590370-001 Tube *ay2 er. Pa. 890976809 Tuba hs~y2 an. 2ca. 690376-606 ~btl Asalee. 1 a. 69091&121 InUrconnr(
I I´•, lee. 6801)78-522 b~rrnnnnal
lu´• 1 ca. b30518619 inta~onnat
t a. I a. 030378-654 IntcrmnnaclI a. 61~880´•680 IntElronn~(
Is´•. I a. 630950-550 incarrannac~
lot. I se. 8110980-Mn lnlcmonnace
1 01. 1 a. BIlh980´•6SB Lnhrronnrl
2oa. Pa. RYOBR0~519 intamnnad
a ´•o, aaa. BBOBMd6 Bore
630583-501 lusl Call
lu. 650588502 Fuel Call
(aR Rannle-l a
030416-305 Valva Arsy2a. 2on. 690416-601 a
6904161606 VIIV(I
lan. 090417-8 l\daptarAayt a. 690417-16 Block
20´• a M´• 6YM1&? Sernn AsoyI.a. 1 a. 65041829 Aq
I´•a. 1 a.. 650116-24 Angle hney1 a. 630119-5 RracLst
1 let BJM1B-li ORIGINAL 1
loe 050410-15 Ang´•l* ~Asly As Received BYlee. 111l 68WLB-19 Ane~s AayZ~a. Pat W0l9Bl14 Clump ATP2an, esa. AN8C8A &.h jsla. 32laa MI4HBA Bait
244. Pa ANla7TW30 Clamp4sa. AN787TWJ8 Clamp
2an. Pa. M81~-4D Unia,
(LU´• I a. AISBOCBL H’aahar
RUI. 544. ~N9BbDR6ss. 944. AN86~CIOL Wanlar
a.. O~l´•m*C nJlaa. YBsa. ANSBOL’II(I Walhor
418. 1~- MS95´•8)6-eP8 kmx~ RSBsl. Bsn. Myss2062cs AECr~
-i i riP6crr g~. ´•MSl~l(n´•?B1 Scnnr2 a. Pen. MSS64RO-1P Ommm~t
(e´•. 1´•´•. MSBO2J-01 Clamp91a. 844. S0310al?HT O´•R)nRIle´• 12 a. Vrlrm Pile (2"12’1
Ipt. 1 pi. MILS´•~983 Cement.
lroll I mil T.p. BST ’lapa (Ztrido a U.UII~ Ihictl
IOR. 10 R. Clen. Yl(s(l Wire (0.01Z~I
1*´•. 630351 HlurprinlIn. Ian. 690968 larprinllee lan. 680381 Rlllllrit,~
Isa BWJLI~ Ulucprinl1 ca 630(11 i(lllcplilll
CU(I’POM KI1‘ 110. 131
i(iINe 1~2-1 HI( No. I)PY
qru OT1 YnlllNO- UI:.CAJI?I(IN
lee 1 na 6J0C18 Blue~int
1 ea. B~DI1B BlueprilaIna. 1 MI. 800706 Bluapin(I M- 1 U1´• 890120 Blueprint
1 os. 800612 Blueprint (!’~sL16b 15.1)
IRe* AS1
Isa 1 cc. 851055 BlueprintLcn. Custom KitNo. 139 Inptrudiurl;
SPECII\L TODLS: NOh´•e
ACCWPL15I1MEMmsTRVCT)(INS;
Ihli~el.irpl.n. as nutlined in Chnptor is orthe Airplane M*(nLanan~e i~nll´•l
CPIUTIOM
Do nut uu airplane hal boo~r nump to drain bel mnn
airplane llacommend use of s´•tarn´•lly au~erad pump to
prevent possible damage to airplane pump.
i llemove ruael.~e hood doors that are lo~nted on top ollu.clage and ilnn,dlolcdl:. o*sr wine area.
9. Rrmurs asoeudeora fmm wtsr wingaren.
Romnvs roru;ard and aR i.bosd Turl UnL i~r dears hom (aft and right ~inr.´•
5. Hsmove lorrml and in oulla´•rd ~ualUnk nceeaa doers hem ieh and right clnl
(Ba 8. Rernara and diacord existing leg and right aR inbosrd fuel tranamitrun (Plh’ 531131211 II.ILI to Figllrr Il
7 and dl~nrd erIs(ing idt.nd right lomard autlunrd 11101 LranrmiUan tPIN 838373-11 tmler Lu FipM ii.
5. Remorr and dinurd (u)ldllp illel tank int´•rmnnat ~4 ad´•ple’ tP~ 830117´•51 and rsl´•W harduard trolw to
AgunSI.
9. Runova and dluud uhtinl IeR inboa´•d all NIIIP IUeI CoI) iWN BSOSOS-ll´• right inbonrd aft ´•unlp M loll tPIPI
690985-21. oni´•tin. gmmmcta and valve .ea.mbliar (Ph’ 690561´•9011 (rrl.r to Figure 2). Bump i\Iei
r.lls. Pnv RBOB93´•W11-M12 do Mt have to be removed.
NOZ5
RrBr 1.Ch.lua~ 28 o( the Airplane Maintenana ~u.ull rm
Rmavnl o(luol~dll.
to. Remove and di~rd erirting plupr 11~1! s´•0116-111~m laR and right loru´•ad in)a.rd LII nllr ImT´•r to Fieun 21.
L1. Rcmnv. and dix´•rd Lri´•ting tube aamb(ln IPm’ 690375-589. -585. -585. ´•587 and -5581. wrren uaemblin (Plh’
590(18-9 and ´•II and related to Figure 31.
NOTE
II is not Dla!´•anry to remove tuha..lamhlial P;S 8989)8-589.
.585. ´•1B(i. and ~n asremhiies pIF183Mltl´•3. -4 and related
hard*;areat this time however. there parts nholllcl he rc-
Il,uvad u~h.nav.r arI.rsr to the I~w´•rd inhanrd and nuthnard
assemblies P L ti)eSi6-IB?. ´•JI(B
and rrl*~rd ilntdl*ra murt he r*ll,av~d during this
Q 64~-´• h- AS
RET1..´•TP 4 j
(:I)SIOH l(lT NO- JZ
STEPS 6 AND 7 a~abd, n
O a
:i-
B
l_e
r,
EXISTING LEFI INSTALLnTIOFI SI-IOWN
EX IS TIN G R I G I-1T IN 5 TA LI.A T I O N O PPO SITE
r I
1:115 ITIM KJ’I NO. 132
SI’EPS 8. 9 AND 10
EXISTING RIGHT IMSTALLATIOH OPPOSI~E
EXISTING I.~FI INZTALLATION 4nOWRI
I‘-
´•-r
-~S a
~e
i. CVVLPI)
1( 2. I´•P151(A ROL~II
St~II. (iJU111´•l HOIE. LH
0*~a
II
5. 63Mll-ll H(lkE. RHe, owl ~s ne cLnmr. ou~au
I.NMII´•5*D/U´•IIRtJOm(-MI V~CVF I~FI
~5’I1.61UW~IIIN RIICONHECT12 ~IJr’lW CIIINNIL
I~ LIICONNICT
f:~ Ib.l;)(ll!Bl 1:(ILL CTLL. 1.11h)l\)llllllFI nI´•ll. Hn
R-b ASIC. S O(lli110~ :IVII((IR OI(I)MML:III-C(JT~ll(l!i IIIIOIICR (:HUMMET
III, nulunn il()L I
RE(:iil.i-i´• ~Y P~P .I*.n:?:ln WIISIEH
1?. -01161 PI illi 7 i\T(
cvsmhl KIT NO. 152
STEP 11
1. sJmlbscn rust nMa mseoz~s CLnUp
i. ~Nlm* BOLTANBWCIOLWI*WEA
6 6330178~511181 ~JY.LHmm16YC´• TUBE AIEY. AH
/BBIDln~WI´•Un.LnQ(UISML8 TUDL A6n. RH
>1
E
I,yr~,Z´•-\C~\j
4)
(3P
,i 8~r 15 NOT N(CF6SARY TO REI1IOVti
ITLMI i. 2.4 I)NO 6 UNI1L I\CCEII
EXISTING LEFT (NIWLIATION ZIIOWN(IUI’ROIRD CELLS II RE(IUIRBD:
EYI~TINO IPISIALIAIION OP)OIRE
CIIS’IDM ~aT NO. 131
12 in*tilll B~OlL7´•9 aulnpm. u*,mbly in(rr II n(lue II ´•nd 83041715 blue~ p.r (Illleprill 630117, nun(a 5. 6 ´•nd 7.
eB, I~ 6~0119-1( hr..l.l´•umhll. Cs.(l(llJ und. n´•uml,b and 83~411-1.lnll.
14. Inntall 830358 8llur bloeks and i-inch Valrro Pile pada mr r´•nt´•r wing fi~al coils nor hluepnnl 630958
16 IluUII hlSZL2R84h’gmmmstl parblurprint 630384.
NOTE
rrs MSI11BBBN rsplnca Le Nbkr gromm´•b that
wore remaWd in ~P O´•
Id in~nll MLi96UIB?1 LPOm*n´•( nor blueprintS30581, ulne 8.
17 Vlho.ump ~ual eJl. ware mmonnI ira~r La step 8), install 8S0998-M)L and 690303-502 sump i~d E.lla..nd 63051~-
I nnd R9a964´•W1 ~ucll cslla par blu3rln( 630384, Shco(2, 68Lhru 42.
HOIL
Ibtrr to Chrplsr 26 o~ L0 Al~lnnr MainPnNlcu Manu´•l BI
fn´•Ullntion alLel esllo.
Is. inNlfl 640978 830388 630416 valve alunnblies. p´•ske( and F~Oa216M
plate par bleop*lnt 630984 (rrl~ to Piauna 51,
ID. Install 830919-1 tuhr and AN~STPWS(I ellmp parhluqrinl 690381, ~ona 6 (r~r8r fa Ffpn: 51.
20. Install 6W~97680L. -803 and -W16 Cube urmblin. ANB:OID unions, 69011R1 rmn aremblin and 850(18~a3
.nd.a4 an81e na~mblies per biueorlnt 690418. Mnen 19 nlld 90 (rrTer to iFLguro 81.
21. 630372-501 (nntmilton linhon.d nnl and RI~P17S-MI Llnntmillen loutboyd (amald) per blusluint 690362
96441 S,~nea 4 th~u 3 (r~ar to FiRurs 61.
norE
A sdunnatic o(Ur oxtdndsd M n/nul,n it IlludraLsd in Fil-
urr 7.
22. Ibnuve nPhaletan su ncmauuy Login H*aa 10 ~Wn. tirl quantity monitors Uul are mounted on tba
21. Ranuva md dlsOud ~Wns lird quan(ifdt m0nl(orn~m Fillurr 41.
24. I~utslll 830989-808 luel OurnlilY monitor (P plsco´•) nor bluo~rlo( 800708
26. Relostali r0caudamon nn~nruinl.
28 f~(nd\ll nEFessdOora.
27. Rsin´•hll fue(tank aoeeuJoora.
28. InlUIII th*.ut out pnrtlnn of~ IIOLBJ´•BBII drsl on axllinll quanmnl console dacnl IrsOlo Fipln 6).
Rc~v(lr e.*t(ng Rrl tr.n´•rsr pumpB no’ Uu´•p’i"t 500679, Sh*ct 15.1 IRFFlninn A91
OR:’ "e As
~3, .i,oRECEIVi
q7
CVSglTnM l(lT NO. 152
c..ranr~.o6RIWHT
FUII CF;LL
eLeCFRIUILCONNECmRCL~M(´•
rPUEL INTEACONNECTVI\LYE
LIFT/I CENTER W1NO
PVELCeLL
OR’N"
d
4
Figur´•
90. Calibmt. lual 9uaotih system udng the wet method or the dn method. To c.llsm(s the Tuel luMtlN systemuulne the wet method. pmcaed an bll.wa:
Jack airplane in acmrdnno8 vlth ploeeduras outlined in Ch.ptar nrth. ~Lrplln. Mainlcnnna ~nudf, p*hing isleraplng (pllsLnml under tail rsctinr. ofelrplsne.
NOIB
Whun aidano is placed MLUL´• sad elaelnEal power i. Oh.,the h.urmlEter wfll np*mta. To pmvant operation at~hourme´•tar. trip the ap~mpri(o circuit breaker.
b.
M~d;lrplana, both h.ri~ntolly end lon~hldlnnlly,.´• aullincd la ChnpteT 8 Oltha i~irpl.ne L(olntnnnnEc
c. Oblain a m~ane b d.brmine the weight(ln naundH)ol the fuel put into and tnk.n out olthe.irplsw.
NOTE
Wright nTli~el added or t´•smuvsd .holl be accurals vilhint2.6 iba. Rm~rd q,lanrlty in pnunds. fuel *R,psro~urr indr(lrers hhrcnhal(, hnd epeelne gnvity olLsl used
En.u´•o(L* Tuclinl.runlul .slni.duad ~aR´•nllriUO(O1Ble- I;:iis\k ns
h´• irpnFolil ~tlnE oyy~*"dRECEIYEn aY MTP IOfuc.i for (Ipl´°"e irvlol (o Chapl;l 12 of the Aill,lp.~ ~*inlr
CIIS?DM KI’1‘ NO. 139
8RILIHTEENrER WINGFUEL CELL
VILVE
h~mM´•lLERCINIERW(N~FVELCELL
--P-
NYING n~ CHE(X
VNVE
c~JBPaTJ~W11601AFT INBOARDCELL
FWo FLEX TUQLINBOARD ~´•7clA i VPZr con~ulcron
CELL~--RZ// ITYPICALI
Oapr
wnaanD
VENT CELL
INTERCWNECTLINES
DLU*P NBE
CONNECTOI(
PWD
;NT.ACONNLCTLINI
LINE VENTLINL
NI~ILLE
FUELL FELL
Oarcl i ~L,LEFT INSTALLATION SI-(OWN
Lj IMIGHT INSTALLATION OPPOSITE
COS?DM ICITIIO. 191
~i69p~NEL IHEF)
O WMOV~ EXIPITIN(I NEL OUANTIN MJNlmA Ar‘.)
(NS+*LL (9~88605 PVIL QUnNnTY MDM1TOR
d
~f3
IlfiX1II3rZil
i ~7f i~/m´•
00(r7
~un EYISTINCI ~CREIH"’~’1 00 (HEF)
EX1S~T1NOOEW\L--IRLF) CUIOUT THAT WRTION
O, oe uEEn~*N ito,asaoAli aoanrro. AEMWEscnew 4ND SFCURE
CUTOUI POATION OF
DLC*L VSINO CONIACT
CEMINT.REINSTALL
___U~F..:.._..i scRla.
il-... ..-_...14
CIIS’R)M 107 NO. IS1
d ilrmova nl)er eRpa Bust linl( Ue~r nnd add 290 W.llun´• (194 lautldl ulB 1 ihrig.li arluo) to sach L´•nk.
lora
ITalrplanu fuel tnnka luva boom dmiMd n(bo~, unllubla end
undrainabla 0141 (6.2 pllans -3(.89 pounds st 6.1 IWnl),maurs UI´•l l.a.all.ns (8 peunde at 6.1 ibdbd) is added to
each tonk bdon add)ylaD ilallon. par LML
s´• Walt 15 Mnutn nnd drain W until 16 B.llan. (LO?.a lbsnt 6.7 ibsignl) pr tn,lk is ranlosd. Wait on addl-
GanJ 16 n(nute~ and eheck h.l indle´•lon Tor ism (0) indieotion 1+O. -5 ibn). Alu.l empty sdiuotment
KIOW on c0ntlol monitor boxn.nd rare the Twl quan~ty Lndlcawnl La Eara (a)(* 0, 6 iba) ii r4ulm3-
NOTE
Amount olruil romnining in ea.h Rrl tonk is equiv´•lcnt to
unlulable.nd undrplnsblo fual (5.2 plloas) per LanL.
I. FLU Unka to loll st top dnllcr nook (pdn(
NOTE
To nll wilt W1. nn ´•rers~c.lZ1’1.0 gnlbn. or 1681.0
polmds ollual (wLight o(kel 8.1 pounds per gallcn).
II´• ndjun lull ´•~iudmcnr wrow in mnMI monitor bores so (haL Tusl qusntl(y indicstors (ndicet+ or illsl
rddod (poulldn).
NOTE
During the allowing poowiuree. do not nske neuaunane of
Be amply or Tull ´•9iustmone sfrrv´• on Uls mnlml monitor
CnUTION
Do not ula ´•Irdulr bal boost prnp to drsin lusl fmm
´•irllDM´• Rcmmmend use ol*x(amdly pl~orrd pump to
prsvonI p~ibls d´•rnaRo to oirplans pump.
h. Drain tirsl i)om dthnr side, drainintl to on even (ncremnnt (i.n. 1687.8 dnin´•d to IWO). Continuo to d~h in
100 pounb inmaaentU raoFd(ng .Q111 iraibhsdrainad md (nnlcat~r raadinR´•.
NOTE
Plot Ura dllFnnMs between ladlsscor matinn nsirut notus(
Lsl pounds rsmo*ed on cnlibm(ion eh´•rt (rtBr to PiRura 91.
Lf the dil~rrnee between indlretor reedlnga and rclusl fuel
pound´• is greeter thou the i(n\la ntnblilhod M ~nlibr´•tinn
rberl. II is raoommcnded th´•t t´•nL be tilled end ml(bmlion
pmoadunn steMd Oom the beginning. ICarmr is indicltd
in uppr h.l(or H obert, ndju´•t U1o LII
mant serov in Control monitor bor M as to ´•Y´•IARB LhC
OR F (T1 n F d) L ,i. ´•hauld brios indr´•Ur (h limiu
oltba Lalibn~on rhm. LI the some indic´•tion aeun spin.
LL t,l !IYP B PU indirntr elsctric´•l wiring nr Can´•mlttsr )roba mal-
RECU\r~ tunaion. Iln(ore pmned(ns ~rUler, hadl uinn´• ~untinuih
end trannmitcar probs´•, rrpairing or rrpl´•ring os mluirad.n.pant nll ann dro)n pmrrdurm.
i. Drain Tual to level where ~uel low level w.minp light illuminntn. fitnp rcrurli.g Rnn racurd ilcuud welyhldroinEd and i,ldicp~,r reading.
NOTE
b ah.ll~ )sB puundl IraO Uund´• or anu.l 14
j to dcRcl until rl,lpy by rciulll iS 2 r.~n*ininl: In I.nL Ilnllrlil~:lhlr ~´•´•d ~louahlr hll´•l, ihr
indi~.lor rcadinl:!:l1.111 lil´• III I II
(:IIS1UI( K17 NO 131:
)I)LL ru~u
3:iiUto ~Iz I :i.
oI :::I i:
oul i:i1; i
8
g
liii
rit iii::
iliii illii
o:
I~o i ~i´• ~t-
ACTUAL FUEL POUNDSla0(t~olb) ~snai
R(lun O.
NOtL
R.xuru th´•~ Uc indi~ator rn,din~.re within La
oul)ilud in rtop i..nd It Ilo~ rap*l 611 .nd dtrin pmne
dun~ u.Lrl indiulor laadinp on v((hin lallral~ce
L Alid lu,pn~nd´• ~hd t.the tide Q´•t hn betn ulibr´•Ud
HOT´•
.nlc ndditio. al hlol vill nlin~li.h c)lr low irvrl ualnisl
lila. ,1L AsH~L atcp´• h. (hnlj LI th~ clllllr ~!d´•
(31~r\kt´•´•‘
tn. H..(wl.irplnnr.´• ~ullilled in n,.pler I% ´•ITDle Mntl~tmn*oo L(;~nu*l. RECEIV~o BY ATPQ
11 nirpl;lnn rrunl I;I’L1; x´•i.ullillt.n il,l.l.;ll,(.rr I ol 11,1´• hirl.l;ln~. M:lll~l´•iiililll´• hllllll.l.
I.. I(( (111 1/111111 illr:llnr \1)II.II ;´•ilJI!´•´•ll 11 (11)1)11 1:111111)11
C(IO’1´•OM KII’ NO. 1]2
1, Il)ry Melhudl. (H*lrr y Pil.l~!a 1U d II) Turulibr´•t~cUlekol 9Y""Llly ay
wm, ymroed u* lullu~.
(11 Test Gcluipnlen~ The Bllmuil~ itellu .IlasltpuipnPnl art rcqulrrd when tasting or dallbra(ln(l tho Tuel gual
Uly syslcm and its eonlpananta:
(sl Pu* pur.lW Tcsi Sat- GTli-l or GTF-a 4 Gull Airhorno LNwman~. Inc.),or s~uivelenl
(bl Calibration harneasoa
Ici 28 vdo ne plwcr supply
NO~t:
The *a may ha shop bhrluted in aa~ord´•ncl with
illustrations in Fylra 12.
(2) (IloRr to Pipuma 11612~ To
pralorman as rosovr:
I´•~ nl´•mnn~.irpl.na hirna Tmm Uu,lan mntml mon)(ol lo~ anJ the h*mak
(bl Cnnnnct Coax hand irona mnLlol monitor has to eoa. urnln´•l (261 .f MDICATOR ´•´•~ion an DTP~B (taat
´•9ulpmo~O-
(r) CMNet aoax A isa´•l from ulrplnn´• uirinp to co~. A t´•rminal (21) ol*IRCiAPP TI\NK UWPIS udlol on
DTP-Z((ssta(u(pmcno.
(d~ CMM* UN911 land liom mnLlol mmli(m ban to Uh´•SH Larndn´•I (281 ol INDICAmR IHtion on GL1U
(Ms~uipmenl).
~S1CcaMfl. UWH B land fmn ´•trplsM ~irillp 14 UNSH B annln.l (12) oTAtRCR~FT TANE UNITS racUa,
on OTF´•a (Lartcquipmsnt)´•
WOTC:
Ensure that eovor on Lha roccpt.rle INDICATOR
COfrIP 1241 is inutnllcd The proter*lm mrar hns a nonnledpin ´•rbim ipaund( the unuead ampansncl,. ´•rrtioll to din(-
nptaany etmy PIJIYP "h" not in Ene.
(II Sd D18RAY rwitch (9) to IIES tM&01 position nnd sat RANGE tMBQI avitrh ~1SI to lW-Kpaaitioo.
(B) SdR&SLSTAN~E FUNCRDN sr)tsh 11211a A;B lai(ion nnd than to AOND paitla.
nora
Ro.dinn~.n dlgltnl O(lplay ´•houm not ha (eee th;ln IW
msgahms
(hl 9ct CAPADI~ANCE YUN~ION sd~h (2) to NC TE8T ZNSH ~lriliun on ant DISI’W\Y SglleCT swlloh
(81 to CAP (PFI pmtloo.
HQTn
Digital airpl.r (8) should (nd(cpU latcrrn M W pl and 88.88
p~
(il Apply 28 vn116 DC p~war to Tucl quantity
01 Sat (:APACl.PANCE FI1WCnON ´•uillh 12) to SL~N SET )’)(OUI~ ju,´•.rion anil ´•djul SI~UIJI10)( tPR
~ROR6 nno .djualmmnttonn.rol 1151 nlld rut didul diapl´•~ B,r C*).( D~
t;s´•i L. ns 17
rF
(:USTOM KI‘P NO. 13P
tF~warrnao
I´•UIL (IAVOIHO
FUEL e~Y
PROBES
Xv 14200
wer wlNo aurso
-xnl~l.w
ruc~anvolNunAHNESLDUTBD
FOELeELLOIWINO
I1*RNEBII INBO
FL~L D(IELLO
IYETWINO INBD OcoNNecraR
nrrrsrssunfceara~rvlaaFUEL
-GCELL IN80
MNNECtOn
FUEL O*UalN(IH*RNETtCENTII(
6
~q !7
C’UG~DM t(IT NO. IPZ
I I
OwvkelrAm:r RELilliTANCE
i,,,Ynoa CJ I C1II*~ I rnaCno*
IVX S(MULAmRO IPF)
Il~x´• F(mER
WII( C~*l U*YII CO*I P~ac cl*x clI u*n*r eo~´• CDvE
Battnn
1_ AS
TFSI SE~ 6$s
RECE~IEU BY W~ P Fieu´•a n.
ILI Jrsk rirplan~´•in amordanea viL pmeedurrs outlinad in Chnpta. 1 ol the Ai~plnne Mainbnanm Manual,placin6 tsluroeing La)latand under tail aobi.o oEairplane
nOre
When airplane isplsnd on ICCL4 and sleQTcal porer is ON,the hounnelar will npnDde. T. prsvanl o~sratia. dhourmc´•tar,tllp Us appmprlste olrrult breaker.
0) Ia,velnirplano, buW1 huriwnWlly and lunyihldinally, nn.uUinad in Chantor 6 at tbs Ai~nlnna h(nintonanreManual.
rml Rcmn~s nllsra~pa bum winl tanks and add 20.0 ilnll.na (1SI plunds at 6.7 ibs/ljsl) allilal B a´•ch tank.
HO+B
IT ~lrphne Lnl tanks have been drained or hath unllsable andundrsin~blsrua) (6.9snI)au -5(.84 pMmd´•ntS.7 ibsipnl),ansoro Uat 1.1 galIe,(a 01 pounds at 8.1 IhslOaIl is added W
eseh mnk haare addlnl! 80 gslLna ~BI tank.
(nl ~dt 16 minuter and drain RrLI Ilnitl IR 8aIIons(lO?.a ihn at. R.? IhUgall lur IRd is ranluvad W.L an
additional 15 tnino(os and theek lupl indicators (or ~m (01 indiwliun(+0. -6 ib.l Adjnn( cmp~ .diull-men~ on control monitor bolar and rcro Uc Lrl qurntily indientnra to u:m (O) (+O, -6 ib´•l ii nt-
~Yiird 6Here
i~,nnunl.( nl*I ~,IIRillinb ill ulnk is clui~aluoc I, Ilnu*.bls ~2.0*´•a IIL~J (i?l!.~llmX)
F’
CUR’POM KI~P NO. IJ1.
reor~drarra
yl*aa~M1 ymna*ru*ln~O 000
RO-5(IUCOAX25110N(1
;~u INcrualNomaaEctoR
9 fl f tim~RnANEWIR1NC
HI\RNE~S; M~Otdlt-IWPER MIL´•WQO~ DR HIIDU~OBPIR h(lLrrBIDL~ ~IPrRnX 26*´•’ L(I.
86M)IXNnIh~OP
OONNecmR
0 P
E E
It It
H H
roooNnia AlronlR*LaNEMONITOR ~IIUNB
B~
~1 1, ~C3B2RBNE/i´• o
UNSHO
h,KoabrPsm:
~ca4czlRNe
00NNECtOn OONNECIOR
CONNECTOR
%k nsFieur´• 12 i-0
Ht~
(0) CAPACITANCR FVNCTION muitch (8) to IND T~8T A~posl(icm.
Ip) ~iUIIIL EMI?´•Y pnrm~l.metar an control inon(tar box for O Ibu: indlr~tlan on (uJ quatlry indicator, for ion
fbeltank, locaccn a yudastlt mnMI penal.
(yl Set Ch~hCITnNCE PONCTION Nribh ca, to INT’12ST nC rrtoee yl.u imrl~ion.
rr) Adlnat the PULL poten(i.mltsr an ~untrol mol´•itol b.r Tar fWn ILa indicrtian on fuCI yu.n(iB indie.lor.
far ioftlunt Lnnk.
(a~ RPPClr atnps to) thru bl us(il no funhor adjurtnlcl,lr are mluirnd
QiP n,, *I lh, ul.~ .I.,. 1.,1 lh, at ru, laollr e,~
52 Ilrin.LIII llllIloIPlery- 2´•\ 17
33. I(n:lsl´•~ Lllcl´•o ~rr s~l il´•;lk i ill 1)11´• Ri.´•l :´•~:lr´•li
CUS~POM KI’P NO. 161
HEmn*a nllplo"e rmmjnckl or aullinud *I Ch*pbr ul L)Ia A(rpl.ne Mnlnlannreo Mn.uol.
IICCRICI~ LOla
WBOH~ I\NO BALINCE: nM w*pbt snd b´•lma cha~y n~qulnd du+ (D (ns(allst(~l orthi´• Cu~m Kit at Dllau~:
WEI(IHTO;BS) H´•ARMtINCWF~O HMOMENTLW-LBSI+98.*0 +216.85 85118
8PARE8 AFFECTEO: NO
PURLICI\T1ON *FPECrET): ThL M~del B9OC nnd 896 nirplnn. Mlintsnan~e Mnnual. and Ls g9UC1696 illuat.s*dPart´• Cnlab. ch´•nlel mlulml by thlr documsne uill be (nmrpor´•Ud st Wlb na.L abrlulcd nvi´•ion.
ACKIRD COM~UANCB: MaLa an ´•pp~pr(´•U entry in ´•irpl´•n. Minm.nse rrcord. u T.lla´•n;: Cuacor. Kit Na.166. dlW 2 M~rch tO9L. ~nn8´•d "enended Rnd (lyalen, Modltlcall.o RLt´•.
f) 6a i G i Al, As
RECEIVED BY aTPZ Z
~IICulfstreamAmerican
coal*,u*noa
ComMndw Divilion
6WI North RIX;*UII ~´•nYI.8´•m~ny. OLI´•honu 75001
CUSTOM KIT NO. 133 15 SEPTEMBER 1981
Update Your Commander Jetprop NOW With
An Improved Side Window Defog System
a Utilizes Conditioned Air To Prevent Pilot and Copilot Side
Window From Fogging.
a Provides Pilot and Copilot Removable Inner Windows Which
Eliminate Cold Air On The Crew’s Shoulder.
Etfeotlvlty: Nit No. 1 ModeIe 6801 end 6908, 8eriai Noe. 11288 Thru H586.
Nit No. 2 Model 600C (8lpht Porty), 8´•rl´•I No´•. 11800 Thru HBJO end Model 695
(Nlne Eighty), serial Not. 91000 Thru 85040 Not Equipped With Pilot
end Copilot Inner Wlndowe.
Nit No. 3 Model 88(IC (Elpht Porty), 8erlei Noe. 11600 Thru 11(60 end Model 685
(Nlne Eighty), 8´•rlal Noe. 96008 Thru 86010 EquippedWith Pilot end
Copilot Inner Wlndowe
Old´•r thl´• kit org6t tuN d´•NIII´• Imm your ns´•n´•1 Oun´•lnem Commender ServlCen(sr
Prloe: Kit No. 1 -)828.L18, pine in~tallltlon.
Kit No. 2 Y38.43.~plu´• Inetellatlon.
Kit No. 3 -8321.34, plue In´•tall*lon.
-I
GubtreamAmericancoawa*~lo*
)W1 Norm Raxnll
B´•mlny. O*l´•honu IJW8
CUSTOM KIT NO. 133
15 September 1881
IMPROVED SIDE WINDOW DEFOO SYSTEM
MODELS AFFECTED: MODELS 690A AND 6908, SERIAL NOS. 11269 THRU 11566, MODEL B9OC. SERIAL NOS.
11600 THRU 11650 AND MODEL 695, SERIAL NOS. 95W0 THRU 96040.
REASON FOR PUsLICATION: TO PROVIDE IMPROVED SIDE WINDOW DEFOO CAPABILITY
COMPLIANCE: AT OWNERS DISCRETION.
wore
IF ANY PROBLEMS ARE ENCOUNTERED WHILE
INSTALLING THIS CUSTOM KIT, CONTACT YOUR
NEAREST DULFSTREAM COMMANDER AUTHORIZED
SERVICENTER.
sY WnOM WORK WILL BE ACCOMPLI.HED: A Bi P MECHANIC OR E9UIVALENT.
APPROVAL: FAA DOA SW-2 APPROVED.
ESTIMATEO MAN nOURS: KIT NO. 1 TWENTY (20) HOURS.
KIT NO. 2 SIXTEEN (18) HOURS.
KIT NO. 3 FIFI~EEN (15) HOURS.
PARTS DATA: PARTS REQUIRED FOR INSTALLATION OF THIS CUSTOM KIT MAY BE PROCURED THROUGH
YOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR: KIT NO. 1 5828.86: KIT
NO. 2 -8438.43 KIT NO. S 9321.34. REFERENCE THIS CUSTOM KIT, AIRCRAFI~ MODEL AND FACTORY
SERIAL NUMsdR WHEN ORDERIND CUSTOM KIT NO. 139 CONSISTING OF THE FOLLOWIND:
Kit No. 1 Models 6BoA and 690B.
Kit No. 2 Models 690C and 696 not equipped with pilot and copilot inner windows.
Kit No. 9 Medals 690C and 896 Equipped with pilot and copilot inner windows.
Kit Kit Kit
No. 1 No. Z No. 3
~TY qTY 9TY PART NO. DESCRIPTION
1 ea. 1 se. 1 se. 510390-81 Channel
1 ea. 1 ea. 1 ea. 310380-82 Channel
2%s. 8818046 Bumper1 ea. 862058-451 Frame Assy1 ea. 882058´•462 Rama Assy1 ea. 1 ea. 862058-3 Inner Window
1 ea. 1 ea. 862058-4 InnerWindow
2 as. 8880585 Escutehaon
2 as. 2 ea. 2sa. 880183-39 Nipple Assyt as. 1 se, f se. 880616´•1 Plenum Assy1 os. 1 se. 1 se. 880816-2 Plenum Assy1 se. 1 ea 1 ea. 880616-1 Tube Assy1 as. 1 se. 1 ea. 880816-2 Tube Assy2 os. 2 ea. 2 ea. 8808801 Tubs Plug
1 se. ADSIABS Pop Rivet
ppe0ldla
CUSTOM KIT NO. 191
RIGHT INSTALLATION SHOWN
LEFT INSTALLATION OPPOSITE
roplLon
9106 WINDOW
3~IREF)
64 i´• EXISTINGHARDWARE
1(REF)
I ~i,.INTERIOR
9106 PANEL
IRE FL
EXISTING 898869-1
HEATER AsSY
(REF)
EXISTING 8W)575´•2EXISTING W7Slm08 C#IX PLENUM 1\8SY
CLAMPS rPLB y IREF)(REF)
EXISTING 980676681
DUCT ASSY
(REF)
ELECTRICAL WIRING
u,,,,,,, i i EXISTINGNTa34´•(1 HOSE HARDWARE(REFL
MODEL 6908 SERIAL NOS.
(1617 THRU 11888 AND
dMODELS Bsoc AND 896
EX(mN01N757TW48CLAMP12PLI)
IREF! /V ‘EXISTIN.880676´•2 PLENVM ASSY
(REF1
EXISTING
9906781 DUCT ASSY
IREF)
EXISTINGNT30Cn HOSE
IREFI
MODEUI~90A AND 6808 FILn i.SERIAL N09. 11298 THRU 1(818
ppgs 2 of 12
CU8TDM KIT NO. 133
4 as. 4es. 4 ea. AN860D6 Washer
2 ea. 2 as. 2 ea. AN737TW46 Clamp4 ea. 4es. tea. MS21042L06 Nut
4 ea. 4ea. MS21180-A26 Rivnut
4 se. 4ea. 4 ea. MSSS206-228 &rew3 ea. B ea. 8 ea. HL86-5 Collar
6 se. 6ea. 6 ea. HL2[1-6-4 Pin
2ea. 2 ea. 2 ea HLPO-S-S Pin
2 ea. Z ea. 2 ea NT3S-4-11 Hose
2sa. 2 ea. 2 ea. NW2W28-4-68-6 Duct
4 ea. 4 se. TFP-1006 (Itud
4aa. 4 ea. TFS-1OB Button
1 ea. 1 ea. 1 ea. Compliance Card
1 ea. 1 ea. 1 ea. Custom Kit No. 133 Instructions
SPECIALTOOLS: RIVNUTPULLER.
C.CCOMPLISHYENT INSTRUCT)ONS:
i. Remove pilot’s seat, WPiJO~B Beat and ham from the airplane. It may be neoessary to remove the levetory seat.
2. Remove leR and right ca;~pit interior side panels and sound proofmg to gain access to pilot and copilot side window
defog system.
3. Remove interior window frames from pilot and copilot aide windows.
4. On Models 680A and 6g0B, serial numbers 11289 thru 11616, proceed as follows (lafer to Figure 1):
i a. Remove end discard existing leR and right hoses (P~ NTS3-4-21).
NOTE
Retain existing clamps (Pn~ AN?9?TU016) for later
installation at step 1S, or step 14.
b. Remove and discard existing leR and right duet sssembliea (P/N 880616-1) and plug duet attaching holes (2
places) with MS20410AD4 rivets.
c. Remove and discard existing lan plenum assembly (P~ 880515-1) and right plenum assembly (P~ 880515-2).
NOTE
Retain Plenum assembly attaching hardware for new plenumassembly installation at step 12.
d. Proceed to step 6.
5. On Model 880B, serial numbers 11611 thru 11686 end Models 680C and 685, proceed as follows (refer to Figure 1):
a. Remove and discard existing left and right hoses (Pn~ NTS3-411).
NOTE
Retain existing clamps (Pn~ AN?S?TW48) for laterinstallation at step iS. or step 14.
b. Remove and discard existing heater assemblies (P~ 880662-1).
Page 3 of la
KIT NO. 1SS
0.128" DIA. HOLE
(I PLS)1.OB" DIA. HOLE
lb0" DIA.
TYPLI
B.2a´•´•1
ExisnNo INTEncosmLIREF)
88019359 NIPPLE ~S8Y
N~S113B82 BLIND
RIVET. UPLS)
PR12Z1 TYPE ´•´•B" OR
ATY 183 GEALANT BETWEEN
NIPPLE ASSY AND INTERCOSTAL
coplLora aln
VALVE IREF)
AlR BOX AS(rY
IREFI
L´•--~.6
8TA\ I 8T"
23.50VIEW LOOKING OVTBD
RIGHT INSTALLATION SHOWN
LEFT INSTALLAIION OPPOSITE
Fkura 2.
Pass 1 01 12
CUWOM KfT NO. 195
c. Assure that wire ends are individually capped, coiled and secured.
d. Remove and discard existing lan and right duet assemblies (PIN 880516-501) and plug duct attaching holes (2places) with MS1OI?0ADI rivets.
e. Remove and discard existing left plenum assembly (P~ 880575-1) and right plenum assembly (Pn~ 880575-21.
NOTE
Retain plenum assembly attaching hardware for new plenumassembly installation at step 12.
f Remove interior upholstery fiom aft pressure bulkhead to expose terminal board located on right side ofbulkhead.
8´• On Model 690B, remove fuse "F33" and on Models 690C and 685, remove fuse "F24".
h. Proceed to step 6.
6. Cut a 1.06 inch diameter hole in existing leR and light intereostals (refer to Figure 2).
NOTE
Intereostals are located on top of pilot’s and copilot’s sir boxassemblies.
7. laeate and drill 0.128 inch diameter hole (4 places) in left and right intermstale for installation of 880183-39 nippleassembly (refer to Figure 2).
8. Install 880183-39 nipple assembly on left and right interoostals using NA81198B2 blind rivets. Seal betweenintermstal and nipple assembly with PR 1221 Type "B" sealant or RTV 182 sealant (refer to Figure 2).
9. Remove rivets as necessary to nest 310590-81 and -82 channels in existing left and right frames at fuselage station37.00. Using 51038081 and -82 channels as templates, merit 1.03 inch diameter hales on leR and light framesand drill eight (8) attaching holes using a No. 50 drill bit. Remove Ohannels and out 1.03 inch diameter holes inframes (refer to Figure 3).
10. Install 910590´•81 channel on left tiame and 110880-82 channel on right fiame st station 31.00 using rivets, Hi-Lok
pine and collars. 8eal coat outboard Range of channels prior to nestling in frame and seal around channels, framesand rivete per sealing procedures outlined in the appliosble Maintenance Manual (rsfer to Figure 3).
11 Drill and install 880876-1 tube assembly on left frame end 880618-a tube assembly on right frame at station 31.00
using screws, washers and nuts (refer to Figure 4).
12. Install 880516-1 plenum assembly on pilot’s aide Rod 8806162 plenum assembly on copilots side using existingscrews, washers and nuts. 8eal around Range of plenum assembly with PR 1221 Type "B" sealant or RTY 162sealant (refer to Figure 4).
13. Install NW2WZS´•4-Bg6 duct using existing or new AN?9?TW46 clamp (2 places) (refer a Figure 4).
14. At left and right fuselage station 25.50, where existing duct runs through Rama, install NT33-4-l1 hose and880680-1 tube plug on existing duct using existing or new AN?3?TW46 clamp (2 places) (refer to Figure 4).
NOTE
Install hose between 880680-1 tube plug and existing duct
through f~ame.
15. Assure that defog system is functioning properly and no leaks are evident.
16. Reinstall existingsoundpmoSng material.
I?. Far Models BBOA and 690B, proceed to step 20.
Page 5 of 19
CU8TOkl X~T NO. 199
RIO HT INSTALLATION SHOW N
LEFT INSTALLATION OPPOSITE
21.60
STA31.00
EXTERIOR SKINIRE Fl
EXlsTIN(I (IUSSET mszt~,aaoa RIVETSIREFI
_ THRU 83IN AND FRAME
DEAL PER MAINTENANCE0.18W´•´•10.1825’´• DIA. HOLE -1\ a ,MlvrunLI
HL2089 rlN
HLBB6 COLLAR
f
~.60´•´•
0.1(100"10.(826" DIA. HOLEnL20M PIN iW
HLB85 COLLAR m\ ~L APPLY 8E~LI\NT TO OUTED
t FLANOE OF CHANNEL PRIOR
TO IN8TALLINO IPER SEALINGPROCEDURES OUTLINED IN
AIRPLANE MAINTENANCE MANUALL.
t 1.03" DIAHOLE
MS2010AD4
RIVET 18 PLS)
31098082CHANNEL
VIEW LOOKING FWD AT
FRAME STA. 37.00
npas.
Pnga 9 ol 12
CU8TOM KIT NO. 1SS
880575´•2 PLENUM nsSYSEAL ALL AROUND
WITH PRlnl TYPE "8’~
OR RTV 182 SE~LPINT87/12S.M)
EXISTING DUCTNTU´•4´•II HOSE AIREFL
880(180-1PLUD
EXISTING HARDWARE(REFL
8808~8´•2
TUBE ASSY
srA\ Ism87.001 \52.67
RIGHT INSTALLATION SHOWNMN137TWOB CLAMP
(2 LEFT INSTALLATION OPPOSITENwzw2ssaaa
DUCT AFTER CHANGEAJR BOX ASSY
IREFIVIEW LOOKING OUTBOARD
PIT RlOnT SIDE
B(M8DB2 CHANNEL
(REF)8197"m.l52" DIA. HOLE
MS(52W´•228 8CREW
IN9BOW WASHERM8210~2LOB NUT
.PLSL
8808782 TUBE
f nssv inen
B
VIEW A-A
Fl~ula 4.
P~e? a) 12
CUSTOM KIT NO´• 133
Is. For Models 690C and 895 equipped with factory installed inner windows, reinstall elisting window frames and
inner windows and proceed to step 21
19. For Models 890C and 686 not equipped with factory installed inner windows, modify existing left and right window
frames by installing inner windows as follows (refer to Figure 5):
a Position 862058-3 left inner window and 862058-4 right inner window frames and scribe lines for 0.40-inch
wide by 6.20-inches long slot in tap of framee.
NOTE
Spot laced area on lower holes of inner window should be
positioned on the outboard side (toward outer window).
b. Cut 0.40-inch wide by B.20-inches long slot in top of window frames.
c. Install 862058´•6 escutcheon on window frame using AD34ABS pop rivet (1 places) and EC1403 or an
equivalent contact cement.
d. Install existing left and right modified window frames on airplane using existing hardware.
a. Position 862068-3 left inner window and 862058-4 right inner window in existing window frames and mark
center of lower holes in inner windows on window frames for inetallation of MS27130-A25 rivnuts.
f Drill 0.253 (t0.003) inch diameter holes, marked in step e., in lower corners of window frames and install
MS27130-A25 rivnut (2 places).
g install TFP-1006dudin rivnuts
h. Unscrew net portion of TFS106 button and install button (2 places) on inner windows.
i. Install innerwindows inwindowframes.
i. Proceedto step 21
20 On Models BgOA and B90B, proceed as follows:
a. Rim and fit, as required, 882068-451 and 862058-452 frame assemblies on airplane (refer to Figure 6)
NOTE
Usa existing frame assemblies as models for trimming and
fitting new Rsme assemblies.
b. Install 861904-6 bumper on 862058-451 and 882068-462 frame assemblies using EC1403 or an equivalentcontact cement (refer to Figure 6).
c install 862068-461 and 862088452 frame assemblies on airplane picking up existing attach points and usingexisting hardware. Assure that 880515-1 and 880616-2 plenum assembly outlets are not restricted or covered
by installation of frame assemblies.
d. Position 862068-5 left inner window and 862058-4 right inner window in new window frames and mark center
of lower holes of inner windows on window frames for installation of MS27130-A25 rirnuts (refer to Figure 5).
a. Drill 0.259 (+0.00S) inch diameter holes, marked in step d., in lower corners of window frames and install
MS21130A25 rivnut (2 places) (refer to Figure 5).
f Install TFP-100Bstud inriMute(rsfertoFigure 5).
g. Unscrew net portion of TFS-1OB button and install button (2 places) on inner windows. (refer to Figure 6).
b. Install inner windows in window frames (refer to Figure 6).
Page 8 of 12
CU8TOM KIT NO. 1.88
VIEW LOOKING OUTED AT LEFT SIDE0820686 ESCUTCHEON
RIGHT SIDE OPPOSITE
AD3UI8s POP RIVET
BBMS8´•J INNERWINDOW
MIRRI CENTER OF INNER WINDOW
ON FRAME ASSY (2 PLS1
A
A
882088481 FRAME
0.280"/0.268" olA. HOLE new (REF)
MSnlS~A28 RIVNUTSTUD
12 PLS) 862058´•3 INNER
WINDOW IREF)
TFS1L~ BUTTON
Ba~soob BUMPER rVli~llL, ~12 PLS)
OUTER WINDOW IREF)
882068451
FRAME ASSY (REF)
-18.00
A-A
FCn 6. IRrt 1 ot 2)
Page 8 ol 12
CUGITOM KIT NO. ISS
881801´•5 BVMPER
INSTALLS ON FLPIN(IE OF
FRAME PIS?IY IALL AROUNDIWITH ECUO~ OR AN
EaUIVALENT CONTACT
CEMENT
E~rmBUMPER SHOULD 6EI\L
AGAINST WINDOW
WHEN INSTALLED
PICK VP ALL
EXISTING ATTACHPOINTS
TRIM EXCESS MATERIAL FROM
mts FLAN(IE (ILlL AROUND)FOR PROPER FIT pg REOUIRED
882058462 FRAME ASSY ISIIOWNI882058451 FRAME ASSY IOPPOSITEI
ACn B.
Psge H ol I2
CU8TOM KIT NO. 133
21. Reinstall interior side panels.
22. Reinstall pilot and copilot seats and bars and iavatory seat (if removedi.
23. Fill outandlllail ComplianceCard.
ELECTRICAL LOAD: Models 690A and 690B, Serial Numbers 11269 thru 11516 -NoChange. Model 690B, Serial
Number. 11517 thru 11566 and Models 680C and 695 Reduced by 10 Amps.
WEIGHT AND BALANCE: NO CHANGE.
SPARES AFFECTED: NO.
PUBUCATIONS AFFECTED: The Pilot’s Operating Handbook, Airplane Maintenance Manual and illustrated Parts
Catalog changes requiredby this document will be incoporated at the nert scheduled revision.
RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Custom Kit No
183, dated 15 September 1981, entitled "lmproved Side Window Defeg System", accomplished (date)
Page 12 of 12
Culfst~amAmericanCORPOR*TIDN
ConMndn Md~n
M~I Norm Awnu´•.t~mlny. MI´•hw 13008
CUSTOM KIT NO. 134 11 JANUARY 1982
IMPROVED INLET AIR SUPPLY SYSTEM FOR YOUR
IETPROP ENVIRONMENTAL CONTROL UNIT.
C
Improves Efficiency Of Environmental Control Unit By
Ducting Only Outside Air Across Heat Exchanger.
EFFECTIVITY:
MODEL 880C (EIOHT FORTY), SERIAL NOS. 11800 THRU 11718
MODEL095 (NINE EIGHTY), SERIAL NUMBERB 95000THRU85086
Order thle kit from your nearest Oul(atream Commander Authorl~ed ServlCenter
Prlee: 8187.82, plus in~tsllatlon
~3"11GulfstreamAmerican
coaPon*TloN
Commanda Mrl~aSW1 North Ratwall Auenua,Bamany, OLlahoma 13W8
CUSTOMKITNO.1SI
11Januarylss2
IMPROVED INLET AIR SUPPLY FOR ENVIRONMENTAL CONTROL UNIT
MODELI*FFECTED: MODEL 690C, SERIAL NOS. 11600 THRU 11118 AND MODEL 695, SERIAL NOS. 95000 THRU
95086.
REASON FOR PUBLICPIT(ON: TO IMPROVE EFFICIENCY OF ENVIRONMENTAL CONTROL UNIT (ECU) BY
DUCTWGONLY OUTSIDE AIRACROSEL HEATTXCCANNEER
COMPLI*NCE: ATOWNERDISCRETION.
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE INSTAL-
LlNG THIS CUSTOM KIT, CONTACT YOUR NEAREST
GULFSTREAM COMMANDER AUTHORIZED SERVI-
CENTER.
BY WHOM WORK WILL BE PICCOMPLISHED: A&PMECHANICOREQUIVALENT.
APPROVAL: FAADOASW-BAPPROVED.
ESTIM*T.DM**.OUR.: SEVEN(1)HOUAS
FARTSDATA: PARTSRE9UIRED TO INSTALL THIS CUSTOM KIT MAY BE PROCUREDTHROUDH YOURNEAR-
EST GULFSTREAM COMMANDER AUTHORIZED SERV1CENTER FOR 818?.62. REFERENCE THIS CUSTOM KIT,AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN ORDERING CUSTOM KIT NO. 134 CONSISTING OF
THEFOLLOWING:
QTY PARTNO DESCRIPTION
tea. 310968-A3 GrillAssylea 880682-3 ClosureAssytea. 880682-1 ShroudAssytea. 880682-15 Angletea. 880682´•19 SealAssy8ea. AN9-3A Bolt
32ea. CR9248-4-3 Rivet
8ea. ANS60D10L Washer
2ea. MS21042L3 Nut
lea. ComplianeeCardLee. CustomKitNolS4 InstNotions
SPECIALTOOLS: NONE.
ACCOMPLISHMENTINSTRUCTIONS:
1. Ren~ve loweraftfuaalage aecessdoorto gainaccessto EnvimmentalControl Unit (ECU).
2. Remove baggage eompartment liner, as necessary, to facilitate inatellation of 880682-3 closure assemhly on ECU
heatexchanger.
Page IdS
CUSTOM KIT NO, 194
S. Remove and discard existing ECU air intake grill assembly that is located on right side of fuselage just aR of
station 290.0.
4. Enlarge existing cutout in fuselage skin and drill holes for installation of 310966-AS grill assembly (refer to
Figure i).
NOTE
Use 310966-A3 grill assembly as template to locate cutout.
5. Remove two (2) screws from top of heat Exchanger that secure pressure switch and tube assembly to heat
exchanger.
6. Temporarily install 880682-3 closure assembly on ECUheat exchanger picking up two (2) existing holes on topof heat exchanger and using existing hardware (refer to Figure a).
NOTE
If holes in 880682-3 closure assembly do not match holes in
heat exchanger, it may be necessary to drill new holes. Assure
that proper edge distance is maintained.
7. Temporally install 880682-7 shroud assembly on 880882-3 closure assembly with AN3´•3A bolt (2 places) and
AN960D10L washer (2 places) (refer to Figure 2).
8. Temporarily install 880682-15 angle using ANI-BA bolt (4 places) and ANSB0D10L washer (4 places) and assure
of proper alignment of assemblies (refer to Figure 2).
9. Drill two (2) 0.199 inch to 0.204 inch diameter holes in heat exchanger to match two (2) lower holes in 880681-3
doauraasarmbly(r~LrtonWre21
10. Remove 880682-15 angle, 880682-1 shroud assembly and 880682-3 closure assembly.
11. Install 880882-19 seel assembly on fuselage frame at station 280.0 using EC140S or an equivalent contact
cement (refer to FiBure a).
12. Install 880682-3 closure assembly on ECU heat exchanger using existing hardware, AN3-3A bolt (2 places),AN9B0D1OL washer (2 places) and MS21042L3 nut (2 places) (refer to Figure 2).
13. Install 880682-1 shroud assembly on 880682-5 closure assembly using AN3-3A bolt (2 places) and AN960D10L
washer (2 places) (refer to Figure 2).
14. Install 880682-16 angle using AN3-3A bolt (4 places) and AN960D10L washer (4 places) (refer to Figure 2).
15. Clean 880682-1 shroud assembly, fuselage skin and lonpmns in area of shroud assembly, in preparation for
sealing, in accordance with procedures outlined in Chapter 20 oPAirplane Maintenance Manual.
NOTE
pay particular attention to the WARNING with regards to
use of solvents.
16. Seal around longemns and 880682-1 assembly with Pro-Seal 700 or equivalent sealant in accordance with
procedures outlined in Chapter 20 of the Airplane Maintenance Manual (refer to Figure 2).
17. install 310968A3 grill assembly on fuselage skin using (3B2248-4-3 blind rivet (80 places) (refer to Figure 1).
18. Reinstall baggage compartment liner.
19. Reinstall lower alt fuselage access door.
to Ca,
Pasezats
CU8TOM KIT NO. 134
B
00
29412
1.67"
IIOB1~B/U(IRILL ~8SY I I FUSELA(IE SKIN (REF1
FI+ t +~;tLi
_t_--- E AlR INTAKE
DASH LINE INDICATESt +-+++t-"’
PIFT END OF ORIOIN~L
CUTOUT
FUSEL~(IE SKIN IREF). ~C L 0´•ZBI IPIP)
CR22484J BLIND RIVET
(SOPLI1VIEW LOOKING OUTED
AT RIGHT SIDE
nosaa´•A3aRILL
IREF)
VIEW CC
ngun i.
Pnee S of 5
CUSTOM KIT NO. 134
~oso
NO. BLON(IERON
IREFI880882´•7 SHROUD I\S6Y
.U~LaoE.K1W amaa~s*NaLL
ANIJABOLTANBBODIOLWASHER
880682´•7 1 X R (4 PL9SHROUDASSY
1 nN33nsoLI
(RlFI 0.188’´•10´•2~´•´• DIA´• HOLEINECUnEATEXCnANOERTO MATCH 81~823 CLOSURE A8SY
ANBBOD(()L WASHER1 B LON(IERON MS21042L3 NUT
IREFL 880BBZSCLOSURE
NEST LOWER FLAN(IE OF W U nN3~ BOLT880882-7 SHROUD nSSY 1 llANBSODIBLWASHER
TUBE iSSY IREFIBENYEEN FUSELAGE SKIN IIPLS)
\ECU HEAT EXCHANGERAND NO. 10 LONOERON AND
TO ALLOW FOR MOISTURE
DRAINAGEDO NOT
880882´•18 SEAL ASSYI
_mrrli I II iN0.10
VIEW 8-8SWITCH IREFI
EXISTING HDWE (REFI0.199’~0.204" DIA. HOLE IN
ECU HEAT EXCHANGER TO
VIEW LOOKING DOWN MATCH 8880823 CLOSURE AS5Y
I\N35*80LT~NBBOD1IILWA8HER
MS21042L3 NUT
0.76’~9000
NO. 8 LONOERON
IREFI /i I asoea2ns SEAL AssvBOND TO FRAME AS8Y
IVITH 001403 CONTACTCEMENT
FRAME ASFY IREF)
NO.8
(0801
8008827 SHROUD ASSY
(REFI
VIEW A-A ~i ,´•.fVIEW LOOKING AFT AT STA 290.0
Fisun 2.
PagalofS
CU8TOM MT NO. 134
ELECTRICAL LOAD: NO CHANGE.
WBOHT FIND BALANCE: NO CHANGE.
SPARES AFFECTED: NO
PUsLICATIONS AFFECTED: The Illustrated Parts Catalog changes required by this document will be incorporated at
the next scheduled revision.
RECORD COMPLII\NCE: Make an appropriate entry in airplane maintenance records as follows: Custom Kit No 134,
dated 11 January 1882, entitled ‘~Improved Inlet Air Eiupply for Environmental Control Unit", accomplished(date)
Page 5 of 5
C~IIB~ GulfB.reamAemspaceCoI)aaran
1001 NP´•th Roi*wsll Balhiiny. OLlilhoms 13008
C~mm´•nd´•rO*ilion
CUSTOM KIT NO. 135 29 SEPTEMBER 1982
AN AURAL MACH OIIERSPEED WARNING SYSTEM
FOR YOOR COMMANDER JETPROP
The Commander Aural Meeh Warning System is a fully automatio airspeed moni-
taring system.
The system compares airplane pitot pressure and pressure altitude. The sense
s~vitch is pre-set to aurally alert the pilot of airspeeds exceeding 243 KIAS.
n This system, which provides a warning in the event of an inadvertent
overspeed of the airplane, is an additional safety feature introduced to
offset the low drag feature that allows the Commander Jetprops to
easily increase airspeed during letdown.
U This system has been incorporated in our Model Bg5A (One Thousandl
C and all other L98 nodsi´• e´• a iland´•~ instdMlon.
EFFECTIVITY:
Kit No. 1.- Madel690,SeriolNos 11001thru 110?9.
Model BSL)A, Serial Nos. 11100 thru 11344.
Model 89011, SerialNos. 11360 thru 11566
Kit No 2.- Model 690C, Srriol Nos. 11600 thru 11709
Model 696, Serial Nos. 95000 thru 95084.
Order this kit Rom your nearelt Dulfstreom Commnnder Authorized ServiCenter.
Price: Kit No. 1- $11411.69 plus (nstallation
Kit Na 2 (1?66.49 plus installation
Pd~´• (IY11´•n To ohilosD Wllh~Y(
8Gulfstream Aerospace Corporation
6001 N~nh Bllhlnyl OLlan~m´• l~ms
CUSTOM KIT NO. 136
29 September 1882
COMMANDER AURAL MACH OVERSPEED WARNING SYSTEM
MODELS *FFECTED: MODEL 690, SERIAL NOS, 11001 THRU 11079.
MODEL 690A, SERIAL NOS. 11100 THRU 11344.
MODEL 690B, SERIAL NOS, 11350 THRU 11566.
MODEL 690C, SERIAL NOS. 11600 THRU 11709.
MODEL 695, SERIAL NOS. 95000 THRU 95084.
REASON FOR PUBLICATION: TO PROVIDE AN hURAL MACH OVERSPEED WARNING SYSTEM.
COMPLIANCE: AT OWNER’S DISCRETION.
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE IN-
STALLING THIS CUSTOM KIT, CONTACT YOUR NEAR
EST GULFSTREAM COMMANDER AUTHORIZED SER-VICENTER.
BY WHOM WORK WILL 88 I\CCOMPLISWED: A 8r P MECHANIC OR EqUIVALENT.
I\PPR~VI\L: ENDINGWND DESION*SPBCTS *RB FI*~PPROYEO
ESTIMATED MAH HOURS: KIT NO, 1- TWENTY (20) HOURS.
KIT NO. 2 THIRTEEN (13) HOURS.
PARTS DATA: PARTS RE9UIRED TO COMPLY WITH THIS CUSTOM KIT MAY DE PROCURED THROUGH
YOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED SERYICENTER FOR: KIT NO. 1-)1.144.69 OR KIT
NO. 2 )1766.49. REFERENCE THIS CUSTOM KIT, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN
ORDERING CUSTOM KIT NO, 136 CONSISTING OF THE FOLLOWING:
RIO´• nOllC´•´•
Kit No. 1- Models 690, 690A and 69011.
Kit Na. Z Madols 690C and 695.
Kit Kit
No.l No.2
lyru 9TY PART NO. DESCRIPPION
1 ea. 1 ea. 800144-3 Bracket Assy1 ea. 800144-1 Tube Aasy1 ea. 800744-11 Tube Assy1 se. 800744-15 Tube Assy1 es. 800144-11 Tube Assy
1 se. 1 ea. K800759-K7 Aural Annunciator Unit
1 ea. 1 ea. K800159-K3 Deeal
1 os. AN804-4D Tee
1 se. 1 ea. AN815-4D Union
1 ea. AN815-5D Union
1 ea. AN824-4D Tee
1 ea. AN824-5D Tee
Page 1 ol 20
CUSTOM KIT NO. 195
Kit Kit
OTY BTY PART NO. DESCRIPTION
No. 1 No. 2
2 ea. AN831-4D Elbow
1 ea AN919-3D Reducer
2 ea. AN924-40 Nut
1 ea AN929-4 Cap AssyLea. AN929-5 Cap Assy
2 ea. AN960D716L Washer2 ea. 2 ea. AN960D8L Washer
1 ea. 1 ea. DRA45C-45 Switch (Sense)1 ea 1 ea. M792811-13 Terminal
2 ea. 2 ea. M792811-15 Terminal38 R. 38 ft. M8104419-22-9 Wire
9 ft. M1L-H-6593-4 Hose
2 ea. 2 ea. MS25181-2 Butt Splice8 ea. MS214o4´•4D Fitting1 ea. 1 ea. MS3106E14S-SS Connector
20 ea. 10 ea. MS3367-1-9 Tiedown Strap2 se, a ea. MS35206-257 Screw
Lea. 1 ea. MS35489-1 Grommet1 ea. 1 ea. PB-126 (White) Switch (Test)1 ea. 1 ea. 5´•0309-804 O-RingLea. 1 ea. 5-0309-905 O´•Ring4 es. 4 ea 320555 quick Disconnect
2 ea. 4RBX-D Tee
6 in. 6 in #6 Yinyl Sleeve1 ea. 1 ea. Compliance Card
1 ea. 1 ea. Custom Kit No. 135 Instructions
SPECIALTOOLS: TUBE BENDING E4UIPMENT AND TUBE FLARING TOOLS FOR KIT NO 2
nCCOMPLisHMENT INSTRUCTIONS:
To install the Aural Mach Overspeed Warning System, follow the installation procedures for your airplane model and
serial number.
I. The following procedures are applicable to Models 690, 690A and 690B (refer to Figure i):
a. Remove bar behind copilot seat (ifinstalled) and remove copilot seat.
b. Remove nose compartment access door to gain secess to forward side of forward pressure bulkhead
c. Remove insulation banded to aft side of forward pressure bulkhead in area where holes for routing pitotline, static line and electrical wiring are to be drilled. Remove only enough insulation as necessary to
expose area where holes are to be drilled.
NOTE
Eleetrical wiring required with this installation may bemuted through forward pressure bullhead with any
existing wire bundle rather than drilling an additional hole
as outlined in step e, below.
i ´•´•-OK1CAUTION
Install a stop on drill bit in order to penetrate the bulkheadbut not the insulation. This will prevent damage to any
equipment on aft side of bullhead.
Page 2 of 20
CUSTOM KIT NO. 135
d Drill two (2) 0.47´•ineh diameter holes in forward pressure bulkhead for instullntian at AW897-4D
plba~w.
e. Drill a 0.25-inch diameter hole in forward pressure bulkhead far routing of electrical wiring lif
required).
L Using pilot hales in 8(10144´•3 bracket assembly as a template, Locate and drill four (4) O 1l0-inch
diameter holes in bracket assembly and forward pressure bulkhead for installation of bracket assembly
NOTE
To prevent interference with any equipment that may be
located on nose deck, it may be necessary to locate bracket
assembly to the left or right of area shown in Figure i.
g Apply sealant, conforming to Military Specification MIL-S-88o2, between bracket assembly nanges and
forward pressure bulkhead and install 800744-3 bracket assembly using NA1738B4 blind rivets Cover
heads of rivets with sealant after rivets have been pulled
NOTE
The following sealants conform to Military SpecificationMIL-S-8802, Class A brushable sealants:
Company Part No.
Products Research Co. PR1422 81 PR1440
Chem Seal CS3240
3M Corporation EC1675
Coast Pro Seal 890
Sealing shall be accomplished in accordance with proceduresC
outlined in Section Il of Model 690 and 690A/B Maintenance
Manuals.
h. Install DRA46C´•45 mach warning switch on bracket assembly using M836206-247 screw (2 places) and
AN960D8L washer (2 places).
i. Install AN919-3D reducer and S-0309-905 a-ring on static port of mach warning switch
j. Install ANB16´•ID union and S-0309-904 o-ring on pitot port of mach warning switch,
Place an AN9601)716L washer on each of the AN831-4D elbows and insert elbows in O 47-inch dianietei
holes that were drilled in step d, in forward pressure bulkhead. Washers are to be on Eorwnl´•d side of
bulkhead.
I. Apply MIL´•S-8802 sealant around AN924-4D nuts andsecure AN837-4D elbows to forward pressure
bulkhead with nuts, Orient elbows upward towards mach warning switch,
I~auno. 1CAUTION
Routing of pitot and static lines is optional: however, ensure
that no sumps exist after hoses are installed, System shall
be installed to ensure proper drainage. Condensation will
collect in a sump area and will not drain. The water may
freeze causing aural mach overspeed warning system to
malfunction and indicate erroneous readings.
Page 4 of 20
CUSTOM KIT NO. 1S5
c;F~t
ASSEMBLY INSTRUCTIONS
To install MS27404-4D end fitilngs an MIL-H-5593-4 hose, proceedas follows:
i. Cut hose to Length required and assure both ends are square
and then insert hose into socket and ensure that hose bottoms
up against recess in socket.
WOll
lberal application of soapy water to hose end
makes insertion of hose into socket easier.
2. Install mandrelinto igl~ nut through nipple and Lubricate inside
diameter of hose, threads of both socket and nipple with oil.
nOTI!
If mandrei is not ava~lable, install a bulkhead fittinginto "B" nut.
3. Screw Ripple into secret and hose. Tighten nipple and leave a
gap (1/3i-inch manmum) between socket and "B" nut so that
nut will swivel.
4. Remove mandrel or bulkhead fitting ir~m "B" nut.
FiBY" 2.
Page 5 of 20
CUSTOM KIT NO. 135
m. Cut two (2) hoses, to route from mach warning switch to elbows on forward pressure bulkhead, Elom
~MLenll to desired isogth iOusrall length la(ui´•sd mmun ona (li in.h to allor for
n. Install MS27404-4D Flttinga on hoses (refer to Figure 2).
a. Clean hose assemblies of all contaminants.
p. Connect fabncated hose assemblies to mach warning switch and to elbows on forward side of pressurebulkhead. Tighten hose assembly connections to a torque value oi40 to 65 inoh´•pounds while holdingswitch flttings and bulkhead elbows.
q. Install MS35489-1 grommet in 025-inch diameter hole (if drilled for wire routing) in forward pressurebulkhead
NOTE
If electrical wiring is to be muted with an existing wire
bundle, one (1) of the MS35489-1 grommets, furnished withthis kit, is not required.
2 The following procedures are applicable to Model 690, serial numbers 11001 thru 11079 and Models 690A and
690B, serial numbers 11100 thru 11521 that have not installed the pitot-static modification per Service Letter
No. 323A, dated 13 November 1980 (refer to Figure 3):
a. Disconnect existing copilot interconnect pitot tube assembly (Pi~ 850430-17) from tee fitting on rightpitot tube assembly, push the tube assembly upward and install 4R6X-D tee on top of existing tee.
b. Reconnect existing copilot interconnect pitot tube assembly (PIN 850430-17) to top of 4R6X-D tee.
c. Remove existing AN929-4 cap assembly from copilot static system that is located on top of the nose wheel
well closure and install 4R6X-D tee an top of existing tee.
d. Reinstall existing AN929-4 cap assembly on tap of 4R6X-D tee installed in step c.
cnurloN
Routing of pitot and static lines is optional; however, ensure
that no sumps exist after hoses are installed. System shallbe installed to ensure proper drainage. Condensation willcollect in a sump area and will not drain. The water mayfreeze causing aural mach warning system to malfunctionand indicate erroneous readings.
e. Cut two (2) hoses, to route from pitot and static tees to elbows on aft side of forward pressure bulkhead,from MIL-H-5593-4 hose material to desired lengths (Overall length required minus one (1) inch toallow for both end Bttinps).
f install M527404-40 fittings on hoses (refer to Figure 2).
IclunoNCAUIION
Assure that pitot and static hoses are connected properly.The top elbow on the forward pressure bulkhead is thestatic connection and the bottom elbow is the pitoteonneetion. incorrect connections could result in damage to
the system
Page 6 al 20
CUSTOM KPT NO´• 195
Q LENGTH OF HOSES TO BE DETERMINED
ON INSTALLATION. ROUTING IS OPTIONAL
WITH THE ONLY REQUIREMENT BehlG
THAT HO~S ARE ROUTED SUCH THAT
NO SUMPS EXIST.
I\EXISTING P~OT TUBE
ASSY (P/N 850430-17)
4RBX.D TEE
\EXblTINGICAPEXISTING TEEASSY (REF)
~IL-H-558S-4 PIIOT HOSE 17 ~4RBX-D TEEMS27404-4D FITTING (2 REQD)
TORQUE 40 TO 85 IN~LBS I
sPr,’r Q MIL-H-559S´•4 STATIC HOSO
M82~404´•40 FITTING (2 RFQD)TORQUE 40 TO BS IN-LBS
DRA1ISC-(S SW~PCH
(REF)
NOSE WHEEL WELL
CLOSURE (REF)
FORWARD PRESSUREBULKHEAD (REF)
MODELS BgO, 880A AND 880B, S/N 11001
THRU 11521 THAT HAYE NOT COMPLIED
WITH SERYICE LETTER NO. SaSA
Figure 9.
Page? ol 20
CUSTOM KIT NO 195
ha. Ma.mblias Ch. Connect one (1) fabricated hose assembly to new tee installed on right pitot tube assembly and to Elbow
on aft aide of forward pressure bulkhead. Tighten hose assembly connections to a torque value of 40
to 65 inch-pounds.
Connect the other fabricated hose assembly to new tee installed on copilot static system tee on nose wlieei
well closure and to elbow on aft side of forward pressure bulkhead Tighten hose assembly connections
to a torque value of 40 to 66 inch-pounds.
sOTe
Use MS3367-1-9 tiedown straps to secure hose assemblies to
eliminate the possibility of sumps in pitot and static lines.
i. Proceed to step 6.
3. The following procedures are applicable to Models 690A and 690B, serial numbers 11100 thru 11451 that have
installed the pitot-static system modification per Service Letter No. 323A, dated 13 November 1980 (refer to
Figure 4):
a. Remove and discard existing AN929-4 cap assembly from tee on right pitot tube assembly.
b. Disconnect instrument static line from tee on copilot static drain tee and install 4R6X-D tee on drain
tee.
c. Reconnect instrument static line to top of(RBX-D tee.
cnurlou
Routing of pitot and static lines is optional; however, ensure
that no sumps exist after hoses are installed. System shall
be installed to ensure proper drainage. Condensation will
collect in a sump area and will not drain. The water may
freeze causing aural mach warning system to malfunction
and indicate erroneous readings.
d. Cut two (2) hoses. to route from pitot and static tees to elbows on aft side of LMiard pressure bulkhead,hem MIL-H-659S-4 hose material to desired lengths (Overall length required minus one (1) inch to
allow for bath end fittings.)
e. Install MS214o4´•4D Bttings on hoses (refer to Figure 2).
I CI\UTIONCAUTION
Assure that pitot and static hoses are connected properly.The top elbow on the forward pressure bulkhead is the
static connection end the bottom elbow is the pitotconnection. Incorrect connections could result in damage to
the system.
Page 8 of 20
CUSTOM RPI NO. 135
Q U;NDTH OF MUSES To BE DETERMINBOON INSTALLATION. BOUTWG LS OPTIONALWITH THE ONLY REQUIRE~PENT DEING THATHOSES AI1E ROUTED SUCH THAT NO SUMPS
EXIST.
EXISTMO P~OT
HOSE ASSY (PIEF)
EXWTING CAP
ASSY (REB)
4R6X-D TEE
ExeTwo TEE (REF)
MIL-H-5593´•4 PITOT HOSE QMS21404-4D FPTING (2 RE~D)
TORBUE 40 TO 65 IN-LBS I~ II II COPULOT INSTRUMENT
STATIC LINE (REF)
4R6X-D TEE
EXLSTINO COPIL(YI~
STATIC DRAW TEE
(REF)
Q MIL-H-5598-4 STATIC HOSE
M821404-40 FBTWO (2 REQD)TOR&UE 40 TO 65 W-LBB
DRA45C-45 SWITCH
(REF)
FORWARD PRESSURE
BULKHEAD (REF)
MODELS 890A AND 6908, S/N 111UO
THRU 11451 THAT HAYE COMPLIEDWITH SFRVICE LETTER NO. 323A
Pilurs i.
Page 9 of 20
CUSTOM KIT NO 135
i Clean h´•s slssmblie,~f 11I
g. Connect one (1) fabricated hose assembly to existing tee on nght pitot tube assembly and to elbow (pitatconnection) on aft side of forward pressure bulkhead. Tighten hose assembly connections to a torquevalue of 40 to 65 ineh-paunds.
h Connect the other fabricated hose assembly to new tee installed on copilot static drain tee and to elbow
(stntic connection) an aft side of forward pressure bulkhead. Tighten hose assembly connections to a
torque value of 40 to 66 inch-pounds.
NOIE
Use MS3367-1-9 tiedown straps to secure hose assemblies to
eliminate the possibility oEsumpssumps in pitot and static lines.
Proceed to step 6.
4. The following procedures are applicable to Model 690B, serial numbers 11452 thru 11521 that have installed
the pitot-static system modification per Service Letter No. 323A, dated 13 November 1980 and for Model 69011,serial numbers 11522 thru 11566 (refer to Figure 5):
a. Remove and discard existing AN929-4 cap assembly from tee on right pitot tube assembly.
b. Remove upholstery panel on copilot’s side to gain access to secondary static lines at fuselage station
1250.
c. Disconnect existing copilot rate´•of-elimb hose assembly (P~ 850503-95) from elbow on frame at
fuselage station 12.50.
d. Remove and discard existing elbow from frame at fuseiagestation 12.50 and install ANB04-4D tee at
that position using existing hardware.
a. Recannect existing copilot rate-of-climb hose assembly (PIN 850503-95) to new tee at fuselage station
12.60.
f Cut two (2) hoses, to route from pitot and static tees to elbows on aft side of forward pressure bulthead,from MIL-H´•5593-4 hose material to desired lengths (Overall length required minus one (1) inch to
allow for bath end Bttings).
s´• Install M527404-4D flttings on hoses (refer to Figure 2).
cnurlo~
Assure that pitot and static hoses are connected properlyThe top elbow on the forward pressure bulkhead is the
static connection and the bottom elbow is the pitotconnection. Incorrect connections could result in damage to
the system.
h Clean hose assemblies ofall eontaminants.
Connect on. (1) fabricated hose assembly to top of existing tee on right pitot tube assembly and to elbow
(pitot connection) on an side of forward pressure bulkhead. Tighten hose assembly connections to a
torque value of 40 to 66 inch-pounds.
j. Connect the other fabricated hose assembly to new tee that is installed an frame at fuselage station
12.50 and to elbow (static connection) on aft side of forward pressure bulkhead. Tighten hose assemblyconnections to a torque value of 40 to 65 inch-pounds.
Page 10 of 20
CUSTOM KFP NO´• 135
o LENGTH OF HOSES TO BE DETERMINED
ON INSTALLATION. ROUTING IS OPTIONAL
WITH THE ONLY REQUIREMENT BEING
THAT HOSES ARE ROUTED SUCH THAT
NO SUMPS EXIST.
COPILOT RATE-OF-CLIMB
INDICATOR (REF)
EXISTING 850503-85
HOSE ASSY (REF)
EXISTING P~OT
HOSE ASSY (REF)
EXISTING TEE
(REF)
MIL-H-5583-4 PITOT HOSE 0 ~3
MSzl4oa-4o FITTING (2 REQD)TORQUE 40 TO 85 IN-LBS (UII EXISTING STATIC
TUBE ASSY (REF)
REh(OYE
ELBOW AND INSTALL
CO Mn-H-558S-4 STATIC HOSE
MS27a04-4D FITTING (2 RE9D)TORQUE 40 TO 65 IN-LBS
STA 12. 50
DRA45C-45 SWITCH
(REF)
PRESSUREBULKHEAD (REF)
MODEL 680B, S/N 11452 THRU 11521 THAT HAVE
COMPLIED WITH SERVICE LETTER NO. 323/1 AND
MODEL 680B, S/N 11522 THRU 11588 WITH FACTORY
INSTALLED SPLIT PITOT-STATIC SYSTEM.
Figula
Page 11 ol 20
CUSTOM KIT NO. 195
N.T.
Use M53367-1-9 tiedown straps to secure hose assemblies to
eliminate the possibility olsumps in pitot and static lines
k P,´•oceed to Jteg 6.
5. The following procedures are applicable to Models 690C and 695 irefer to Figure 6):
a. Remove bar behind copilot seat (ifinstalled) and remove copilot seat.
b. Remove nose compnrtment access door to gain access to forward side of forward pressure bulkhead,
c. Remove insulation, bonded on aft side offorward pressure bulkhead, in area where hole is to be drilledLr routing oleiedrieai wiring,
NOTE
Electrical wiring required with this installation may be
routed through forward pressure bulkhead with any
existing wire bundle rather than drilling an additional hole
as outlined in step d, below,
I?au~loNcnurlow
install a stop on drill bit in order to penetrate the bulkhead
but not the insulation. This will prsvsnt to any
equipment on aft side of bulkhead.
d. Drill a 0.25´•inch diameter hole in forward pressure bullhead (if required) above existing static Rttingand install MS35489-1 grommet in hole.
NOTE
If electrical wiring is to be routed with an existing wire
bundle, one (11 of the MS35489´•1 grommets, furnished with
this kit, is not required,
e. Install AN815-6D union and S´•0309-905 o-ring an static port of mach warning switch Torque union 86
to 160 inch-pounds.
L install AN811´•4D union and 5-0309-904 o-ring on pitot port of mach warning switch. Torque union 70
to 120 inch-pounds.
g. Instaii DRA45C-45 mach warning switch on bracket assembly using MS35206-247 screw (2 places) and
AN960D8L washer (2 places),
h. If existing pitot and static fittings. located on right side of forward pressm´•e buiklichd, are unused
(capped). proceed as follows:
(11 Remove existing cap assemblies from pitot and static fittings and retain for inter
reinstallation.
(2) Install 800744-11 tube assembly an static fitting and tighten "B" nut to a torque value of 60
to 80 inch-pounds,
Page 12 of 20
CUSTOM KIT NO. 135
(3) Install 800744-7 tube assembly an pitot fitting and tighten nut to a torque value of 40 to
66 inch-pounds.
(41 install AN824-5D tee on 800744´•11 tube assembly and tighten "B" nut to a torque value of 60
to 80 inch-pounds,
(5) Install AN824-4D tee on 800144-7 tube assembly and tighten nut to a torque value of 40
to 65 inch-pounds.
(6) Install existing cap assemblies, removed in step (1), on new pitot and static tees.
17) Connect 800744-17 tube assembly to static port on mach warning switch and to static tee atForward pressure bulkhead and tighten "B" nuts an tube assembly to a torque value of 60 to80 inch-pounds while holding union an switch secure.
(8) Connect 8(10744´•15 tubs assembly to pitat port ofmach warning switch and to pitot tee at
forward pressure bulkhead and tighten "B" nuts on tube assembly to a torque value of 40 to66 inch-pounds while holding union on switch secure.
If existing pitot and static fittings, located on right side of fonvard pressure bulkhead, have tubeassemblies connected to them, proceed as follows:
(1) Disconnect existing tube assemblies from pitot and static fittings on forward pressurebulkhead.
(2) Install 800744´•11 tube assembly on static fitting and tighten "B~’ nut to a torque value of 60to 80 inch-pounds.
(3) install 800744´•7 tube assembly on pitot fitting and tighten "B" nut to a torque value of 40 to
(4) Install AN824-5D tee on 800744-11 tube assembly and tighten "B" nut to a torque value o160
65 ineh´•pounds
to Bo inch-pounda.
(5) Install AN824´•4D tee on 800144-1 tube assembly and tighten "B" nut to a torque value of 40to 65 inch-pounds.
(6) Cut existing tube assemblies, diaconneoted in step (1), to Length required to connect to new
pitot and static tees. Install existing sleeves and "B" nuts on tube assemblies and dare tubing
NOTE
If bends in existing static line prevent cutting to new lengthand prevent flaring of static line, it may be necessary to
fabricate a new static line.
(7) Connect existing tube assemblies to piMt and static tees. Tighten "B’~ nut on static tee to a
torque value of 60 to 80 inch-pounds and tighten "B’~ nut on pitot tee to a torque value of 40to 65 inch-pounds.
j. With tube assemblies connected to switch assembly and using pilot holes in 80[)744´•3 bracket assemblyas a template, locate and drill four (4) O.llO-inch diameter holes in bracket assembly and forward
pressure bulkhead for installation of bracket assembly.
k. Apply sealant, conforming to Military Speeineation MIL-S-8802, between bracket assembly nanges andforward pressure bulkhead and install 800744-9 bracket assembly using NAS1138B4 blind rivets.Cover rivet heads with sealant after rivets are pulled.
Page 14 of 20
CUSTOM KIT NO. 195
K800158-KS DECAL
M/CI(
WARN
O. 250" DIA. HOLEpa-lzs (WH~E) SWITCH
PTT
LEFT INSTRUMENT PANEL(REF) 8O0 o ´•00
NOIB
LOCATION OF PB-126 (WHITE) SWITCH ONLEFT INSTRUMENT PANEL iS OPTIONAL.
Figure 7
Page 15 oL 20
CUSTOM KIT NO. 135
UOTB
The following sealants conform to Military SpeciBcationMIL-S-8802. Class A brushable sealants:
Company Part No.
Products Research Co. PR1422 PR1440
Cilem Seal C53240
3M Corporation ECi615
Coast Pro Seal 590
Sealing shall be accomplished in accardance with
procedures outlined in Chapter 20 of the AirplaneMaintenance Manual
6. On all madels, proceed as foilaws:
a. Locate and drill a o.250-inch diameter hole in left instrument panel for installation of PB´•126 Lwhitoi
switch (refer to Figure 7)
NOTE
Location of switch an left instrument panel is optional.
b. Install K800159-K3 decai on left instrument panel (refer to Figure 7).
c. install PB-126 (white) switch on left instrument panel (reEer to Figure 7).
d. Remove copilot’s side panel.
e. Cut a 11s-inch diameter hole in capiiat side panel and install K80o7fi9-K1 aural annunciator unit on
panel. Insulation may be cut and removed in area to clear annunciator unit. Apply Y-9082 thermal
insulation tape (or equivsient) on fuselage skin behind annunciator unit (reEer to Figure 8).
f Connect aural mnch overspeed warning system to airplane electrical system as shown on Figure 9
NOTE
Use MS3361-1-9 tiedown straps to secure electrical wiringas necessary
g Reinrtiill col,ilot’s upholstery side panrl.
7. Seal around grommet, rivets and electrical wiring an both sides of forward pressm´•e bulkhead with MII.-S-RROP
sealant.
8. Rebond insulation to forward pressure bulkhead using EC1103 cement.
9. Perform a leak check of Primary ipilatl and Secondary (copilot) pitot-static system individually as follows:
a Assure that all instruments are connected to their respective pitot-rtatie systems
b. Seal static ports an each side of airplane fuselage and pitot drain hales
c. Connect a vacuum source at static drain fitting and pitot tube assembly such that same vacuum is
applied simuitaneously to each paint
d Adlust altimeter to ~ero
e. Apply vacuum slowly until altimeter indicates 12.600 feet
Page 18 of 20
CUSTOM KIT NO. 135
BCUT 1.181’ DIA. HOLE W COPILOT
4SIDE PANEL IN THIS AREA DENOTED37.00
BY CROSS-HATCHING AND INSTALL
K800758-K7 AURAL ANNUNCIATOR UNIT.
n
nlJ
IjVIEW LOOKING OUTBOARD AT COPILOT SIDE
COPILOT SIDE PANEL II h FUSELAGE SKIN
(REF)~ I I II (REF)
Y-0052 THERMAL INSULATION
K800159-K7 AURAL I nlrl TAPE OR EQUTYALENT
ANNUNCIATOR UNIT
(REF)
INSULATIONI I I VIEW A~A(REF)
Pigura 8.
Page 17 ol 20
CUSTOM KII NO. 165
ON MODEL 680, CONNECT THIS WIRE TO TBS (CONTROLLED BY
LEFT ENGINE INDICATOR BREAKER) OR CONNECT TO
TB4 (CONTROLLED BY R2GHT ENGINE INDICATOR CIRCUIT
BREAKER) FOR POWER SUPPLY.
ON MODELS B80A, 690B, 690C AND 695, CC~JNECT THL4 WIRE TO
AVIONICS TERMINAL AVB (LOCATED BELOW fHE EMERGENCY
EXITDOOR) FOR POWER SUPPLY AND VERIFY THAT ANNUNCULTOR
3 CIRCUIT BREAKER CONTROLS THIS CIRCUTT.
1815181-2 BUTT
SPLICE
POWER
SOURCE
M1Ba8/1-13 TERMINAL 1 COVER SOLDER CONNECTIONS
WITH #6 VINYL SLEEVE
(2 PLS)
(4 PLS)PB-128 (WHITE)
320555 PUICKDISCONNECT
SWITCH (REF)
Mwnsna CGN’D~Ct)-MW4A22
KB(IO?SI)-K1
AURAL C:W
M?828/1-15TERMINALA f
I
(2 PLS) IIM81044/8-22-8 WIRE
(TYP)
MSS1OBE1QG-SI
CONNECTOR
B CD AE
DRA45C-45
MACH
SWITCH
WIR ING DIAGRAM
FIIYIP 9´•
Page 18 ol 20
CUSTOM KIT NO, 135
*mL
When applying vacuum, do not exceed range of Rate-oE-
Climb indicator.
f Shut off vacuum and hold for one (1) minute.
g. Observe altimeter for indication of leakage. Altimeter drop in Indicated Altitude shall not exceed 250
feet.
NOTE
Tap altimeter lightly before taking a reading.
h. Release vacuum slowly and then remove static port sealing material.
NOTE:
releasing vacuum, do not exceed range of Rste´•of-
Climb indicator.
Connect a clean, dry air pressure source to pitot tube.
j, Apply pressure to pitot slowly until Airspeed indicator indicates 130 knots.
k. Shut off pressure and observe for ons (1) minute.
i. Observe Airspeed indicator for indication of leakage. Leakage shall not exceed an indicated drop of 8.5
NOTE
Tap Airspeed Indicator lightly before taking a reading.
m. Release pressure slowly and remove test pressure source.
10. To functionally check the completed instellatian, proceed as follows:
a. Airplane Power ON.
b Mach-Warn Test Switch PUSH TO TEST.
Aural Warn Alert should pulse approximately 8 times per second at 2900 HZ.
NOTE
If system does not operate, check all electrical connectionsand venfy power source. The Aural Mach Warning Switch
has no field udjustments and is factory set.
Airplane Power OFF.
11. To functionally ground check system operation, proceed as follows:
System SpeeiBeations:
Actuate (Increasing Speed):243 ii B, -O) KIAS Seal i.evei to 18,700 Pt. Alt.
.52 ii.01.-00)MACW Above 18,700 Ft. Alt.
Page 19 of 20
CUSTOM KIT NO 196
a. *Place a tight fitting eix (6) foot length of surgical tubing over right pitot head.
NOTE
If Service Letter No. 323A has not been complied with, the
left pitot tube must be seeled.
b Airplane Power ON.
c. Double tubing over and grip tubing until airspeed indicator reads 243 (t6,-0) KIAS.
hural Warn Alert should sound a pulsing tone.
d. Airplane Power OFF.
a. Remove tubing from right pitat heed.
f Remove seal from left pitot head.
If a Pitot-Static System leak cheeker is used, follow the manufacturers instructions.
12. Reinstsli nose equipment cempartment access door.
13. Reinstall copilot seat and bar.
ELECTRICAL LOAD: NO CHANCE.
WEIGHT AND BALANCE: The weight and balance change resulting from installation of this Custom Kit is as follows:
WEIGHT (LBS) H-ARM (INCHES) H-MOMENT (IN-LBS)
ta.88 62´•60 CKit No. 2 1.80 82.50 112.5
SPARES AFFECTED: NO.
PUBLICATIONS AFFECTED: The Airplane Maintenance Manual and illustrated Parta Catalog changes required bythis document will be incorporated at their naitt revision.
RECORD COMPLIANCE: Make an appropriate entry in airplane maintenonce records as follows: Custom Kit Na.
135, dated 29 September 1982, entitled, "Commander Aural Mach Overspeed Warning System’~, accomplished(date)
Page 2U of 20
OGulfstream
Custom Kit No. 136
15 November 1984
IMPROVED TAIL LIGHT STROBE LIGHT SYSTEM
MODELS AFFECTED: MODEL 690B, SERIAL NOS. 11541 THRU 11566.
MODEL 690C. SERIAL NOS. 11600 THRU 11999.
MODEL 690D. SERIAL NOS. 15001 THRU 15041.
MODEL 695. SERIAL NOS. 95000 THRU 95999.
MODEL 695h SEIAL NOS. 96001 THRU 96200.
REASON FOR PUBLICATION: TO PROVIDE AN IMPROVED TAIL LIGHT i STROBE LIGHT INSTALLATION
WITH LONGER RATED BULB LIFE.
COMPLIANCE: AT OWNER’S DISCRETION.
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE
INSTALLING THIS CUSTOM KIT, CONTACT YOUR
NEAREST GULFSTREAM COMMANDER AUTHORIZED
SERVICENTER.
sY WHOM WORK WILL BE ACCOMPLISHED: A d P MECHANIC OR EQUIYALENT.
C *PPWY~L: &NODUGBRWO DBiiION WPSCTS *R6 APPROVIID.
ESTIMATED MAN HOURS: FOUR AND ONE´•HALF (4.5) HOURS,
PARTS DATA: PARTS REqUIRED TO COMPLY WITH THIS CUSTOM KIT MAY BE PROCURED THROUGH
YOUR NEAREST GULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR (262.21. REFERENCE THIS
CUSTOM KIT, AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN ORDERING CUSTOM KIT NO. 136
CONSISTING OF THE FOLLOWING:
Prr´• BYbl´•O1 T~ Eh´•4´• Wim~ut
QTY PART NO. DESCRIPTION
1 se. 310062-609 Light Assy1 en. Complianee Card
1 ea. Custom Kit No, 136 Inatructioss
SPECIAL TOOLS: NONE
i_-Paee 1 of 3
’I
CUSTOM KIT NO. 136
ACCOMPLISHMENT INSTRUCTIONS:
1 RLmouP s.EBr. atldEh~nglail .ons to .mlans, diaronnot.lsUilal mnne..rs and remo*. tall mao
2. Remove screws and washers attaching tail cone lens to tail cone. Retain screws and washers for installing310062-509 light assembly.
3. Remove and discard existing tail cone lens.
4. Remove screws attaching existing tail i strobe light asaembly to tail cane.
5. Remove and discard existing tail i strobe light assembly.
6. Drill out rivets attaching existing nutplates and doubler to tail cone.
7. Remove and disca~d existing nutplates and doubler.
8. Make cutouts in tail cone for installation of new tail light i strobe light assembly (reEer to Figure i).
9 install 310052-509 tail light i strobe light assembly on tail cone using existing screws and washers removed
in step 2.
10 Connect 310052-509 tail light i strobe light assembly to existing electrical connectors.
Il. Reinstall existing tail cone on aft fuselage using existing hardware.
12. Functional check strobe light system to assure system is operating correctly.
13. Fill out and mail Compliance Card.
ELECTRICAL LOAD: NO CHANCE.
WEIGHT AND BI\II\NCE: NO CHANGE.
SPARES AFFECTED: SPARES TO STOCK BOTH CONFIGURATIONS OF TAIL LIGHT i STROBE LIGHTS. CPUBLICI\TIONS AFFECTED: The Airplane Maintenance Manual and illustrated Parts Catalog changes required by
this document will be incorporated at the next scheduled revision.
RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Custom Kit No. 136,dated 15 November 19811, entitled "lmprovsd Tail Light i Strobe Light Systsm*, accomplished (dated)
Page 2 of 3
CUSTOM KIT NO. 136
C0.375" DIA. x 0.75" LONGSLOTS (4 PLS)
NOTE
ACCEPTABLE TO USE THIS
ILLUSTRATION AS A TEM-PLATE SINCE IT IS SHOWN
ACTUAL SIZE.0.88"
1´•-" tt -t
3~rf-- I ‘1.´•13´•´•Dln. HOLE 2.98"
pkl-nBLENDSMOOTH
1.75" E
HOLE
I
EXISTING 1.37" DIA. HOLE
(REF)
EXISTINGTAIL CONE
(REF)DISCARD EXISTING
F. DOUBLER
TAILCONE
VIEW LOOKING FORWARD
AT TAIL CONE
Figure 1.
Pnge B of 3
QGulfstreamAerospace
CUSTOM KIT NO 136 15 November 1984
AN IMPROVED TAIL LIGHT STROBE LIGHT ASSEMBLY
FOR YOUR GULFSTREAM COMMANDER JETPROP....
O Provides individual strobe light and individual tail light
O More economical to maintain with longer rated bulb life
EFFECTIVITY:
MODEL 690B. SERIAL NOS. 11541 THRU 11566
MODEL 690C (EIGHT FORTY), SERIAL NOS 11600 THRU 11999
MODEL 690D (NINE HUNDRED). SERIAL NOS. 15001 THRU 15041
MODEL 695 (NINE EIGHTY). SERIAL NOS. 95000 THRU 95999
MODEL 695* (ONE THOUSAND), SERIAL NOS. 96001 THRU 56200
Order this kil irom your nearssl Oulfstieam Cammandsr
Authoriled ServiCenter
Price: (282.21. Plus installation
PII~´• Cn´•nl´• WI(IIOYI NnlT´•
OGulFstreamAerospace
CUSTOM KIT NO.137 18 JANUARY 1985
WINDSHIIELD ANTI-FOG SYSTEIVI FOR YOURGULFSTREAM COIVIMANDER JETPROP
O An electrically heated film is applied to the upperportion of the Pilot and Copilot windshields tomaintain a temperature sufficient to prevent fogformation.
O The heated film heats automatically with selectionof windshield heat.
C::: O Upon descent and landing a~roaeh, the heated filmreduces moisture accumulation which precludes water
dripping.
O The gold tinted film also acts as a sunscreen.
EFFECTIVITY:
Model 690, Serial Nos. 11001 thru 11079
Model 690A, Serial Nos. 11100 thru 11349
Model 690B, Serial Nos. 11350 thru 11566
Model 690C, Serial Nos. 11600 thru 11999Model 690D, Serial Nos. 16001 thru 15999Model 695, Serial Nos. 95000 thru 95999Model 695A, Serial Nos. 96001 thru 96200Model 6958, Serial Nos. 96201 thru 96999
Order this kit from your nearest Gulfstream Commander Authorized ServiCenter
Price: $486.00, plus installation
PRICE SUBJECT TO CHPINGE WIIHOUT NOTICE
ci~l,~m Nw, wlh wilov po~l aio~rl
PO Bor 22SWO*l´•homo CiN. 73123
CUSTOM KIT NO. 131
is January 1985
WINDSHIELD ANTI-F00 SYSTEM
MODELS AFFECTED: MODEL 690, SERIAL NOS 11O(I1THRU 11079.
MODEL 69DA, SERIAL NOS. 11100 THRU 11349.
MODEL 69DB, SERIAL NOS. 11350 THRU 11566.
MODEI. 680C, SERIAL NOS. 11600 THRU 11999.
MODEL 690L), SERIAL NOS. 16001 THRU 15999.
MODEL 685, SERIAL NOS. 95000 THRU 95999.
MODEL 695A, SERIAL NOS. 86001 THRU 98200.MODEL 695B. SERIAL NO9. 96201 THRU 96999.
REASON FOR PUBLICATION: ELIMINATES INTERNAL FOGGIND OF WINDSHIELDS AND SUBSEqUENTMOISTURE PROBLEMS.
COMPLII\NCE: AT OWNERS OPTION
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILE
INSTALLING THIS CUSTOM KIT, CONTACT YOUR
NEAREST GULFSTREAM COMMANDER AUTHORIZED
SERVICENTEB.
BY WHOM WORK WILL BE ACCOMPLISHED: A P MECHANIC OR EQUIYALENT.
APPROVAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED.
ESTIMI\TED MAN HOURS: THREE (3) HOURS.
PARTS DATA: PARTS REqUIKED TO INSTALL THIS CUSTOM KIT MAY BE PROCURED THROUGH YOURNEAREST OULFSTREAM COMMANDER AUTHORIZED SERVICENTER FOR (486.00. REFERENCE THIS CUSTOMKIT. AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN ORDERING CUSTOM KIT NO 137CONSISTING OF THE FOLLOWING.
BTY PARPNO. OESCRlmION
1 en. 511800 Left Heater AssyI ea. 511900 Right Heater Assy1 en Compliance Card1 en. Custom Kit No. 137 instructions
SPECI~LTOOLS: NONE.
Page lolS
CUSTOM KIT NO. 13?
I\CCOMPLISHMENT INSTRUCTIONS:
8CAUTION
UNDER NO CIRCUMSTANCES ARE HEATERASSEMBLIES TO BE FLEXED, TWISTED. FOLDED ORSPINDLED. CLEAN, LINT FREE, SOFT COTTONCLOVES SHOULD BE WORN WHILE HANDLING ANDINSTALLING HEATER ASSEMBLIES. AVOID HIGHWIND CONDITIONS THAT MAY ALLOW DIRT AND
GRIT TO BECOME EMBEDDED IN THE HEATERASSEMBLY ADHESIVE. DO NOT APPLY HEATERASSEMBLY TO A HOT WINDSHIELD.
I Remove left and right sunvisors from windshields.
2 Apply 511800 heater assembly to left windshield and 611900 heater assembly to right windshield as follows:
a. Prepare inside surface ofleR and right windshields by cleaning them with a solution ofleopmpyl Alcoholand water (SOC solution).
b. Remove the protective caaung from adhesive side of heater assemblies. This will elpoee the gold costingon the heater assemblies; themfore, elttreme caution should be erereised so as not to scratch surface ofheaterassemblies.
c. Position heater assemblies and tack to windshields using masking tape as shown in Figure 1. Maintainone (1) inch constant dimension between upper edge of windshield heating element and heaterassemblies. To help maintain this dimension, one (1) inch masking tape may be used.
d. Strip away release paper fmm adhesive along longest vertiesl saga Gnao~nl ´•d~i orhasUr as
C~shown in Figure 2.
a. Using a hand miler, apply even pressure across the width of the adhesive as shown in Figure 3.
f Strip away release paper along top and bottom of heater assembly as shown in Figure 4.
g. Hold adhesive away from windshield until miler can press adhesive onto glass and then use the handmiler to apply even pmssum across the width of the adhesive.
Cars should be taken so that Link. or wrinkles am not
intmduced into haster assembly,
h. Altsmstely work top and bottom adhesive strips with roller veN slowly.
Remove the release paper fmm adhesive strip along shortest edge (outboard edge) of heater assembly andsecure adhesive to windshield using hand miler very slowly.
i. Remove masking tape and clean inside surface of windshield where masking taps was applied using a
solution oflsopropyl Alcohol and water (S09b solution).
i Lower overhead switch panel.
4. Route wires above heater assembly to overhead switch panel and connect heater assembly wires to airplanewindshield eleftncal system. Secum heater assembly wires to e~isting wire bundles as rrquired (refer to Figure5)
6 Assure that electrical wiring is clear of panel and then close overhead switch panel.
Page a of 5
CUSTOM KIT NO. 131
CROSS HATCHING INDICATES
RLACKEO OUT AREA OF
WINOSHIELDLEFT WINDSHIELD RIOM WINDSHIELD
IREFI I IREFI
611866 HEATER ASSY 611860 HEATER ASSY
IREF) IREFL
t I II ´•I.o´•´• CONSTANT1.0" CONSTANT
j
UPPER EDGE WINDSHIELD UPPER ED(IE WINDSH1ELD
HEATING ELEMENT IREF1 HEATIN(I ELEMENT (REF)
VIEW LOOKING FW D
1118W HEATER ASSY rREFI
~Ti
B11BW HEATER ASBY (REF)PEEL OFF AOHESIVERELEASE PAPER
i aiWINoSHIELD IREF)
Figure i.
k---I--
MASKlNO TAPE TO HOLD
HEATER ASSY IN WSITION
LEFT W1NDSHIELD IREFI
Fig u re 2.
PageSolS
CUSTOM KIT NO. 157
Csllano HEATER 511500 HEATER
A55Y IREFI ASSY IREFI
MI\IIINO TAPE (REFI
HAND
ROLLER
PEEL OFF RELEASE
PAPER TOP ANDLEFT WINDSHIELD IREFI LEFT WINDSHIELD IREF) BOTTOM
Figure 3. Figure 4.
2 51 LEFT WINDSHIELD RI(IHT WINDSHIELD 15 5
WITCH (REFI SWITCH InEFI
Illh Ill^s I 5_14 _31 1)
HI I I; I ILO LO I I I\ I HI
OVERHEAD SWITCH PANEL
wo´•reOYo OND
CONNECT ONE HEATER ASSEMBLY LE~O
WIRE TO WINDSHIELD 6WITCH AND THE
OTHER LEAD WIRE TO (IROUND
LEFT I I RIGHTWINDSHIELD I I WINDSHIELDHEATER I\SEY I I HEATER ASSY
(P/N 51(5WI I I IP/N 611800)
Figure 5. i
Pape4ofS
CUSTOM KIT NO. 131
5 ohpc~ xlinhhlald in f~r ihori~ople, spplunbls ilrpl´•n. M8int~n.nEp Manual
NDT6
Due to characteristics of low wattage anti-fog heater
operation. a positive functional test cannot be verf~ed on the
ground. Functional vsri8cation will be absence of foglh~oetbuildup at altitude.
7 Reinstall left and right sunvisors on windshields using eristing hardware.
S. Fill out and mail Compliance Card.
ELECTRICAL LOAD: +0.22 WA1TS PER SBUARE INCH (2.2 AMPS TOTAL).
WEIGHT ARO BAUINCE: NO CHANGE.
SPARES PIFFECTED: NO.
PUQLICATIONG AFFECTED: The Airplane Maintenance Manual and Illustrated Parts Catalog change. required bythis document will be incorporated at the ne.t scheduled revision.
RECORD COMPU*NCE: Make an appropriate entry in airplane maintenance records as follows: Custom Kit No. 131,dated 18 January 1485, entitled "Windshield Anti-Fag System", accomplished: (date)
C
Page SofS
Custom Kiti Gulfstream
Aerospace
CUSTOM KIT NO. 138
Revision No. 1
14 June 198?
AUTOMATIC ENGINE IGNITION SYSTEM
APPROVAL: ENOINEERWC DESIGN ASPECTS ARE FAA APPROVED.
ACCOMPLISHMENT INSTRUCTIONS:
Pogo of 9
ADD Note to Figure 4:
NOTE
ON MODEL 690C, SN ~1BW THRU ll?ag AND MODEL690D. S~ 15001 THRU 16024, WIRE NO. 2K2?A22CONNECTED TO SOB SPEED SWPCH IS REPLACEDBY WIRE NO. (W22) 114 AWD WIRE NO. 2K13A22
C CONNBCPED TD laa spEnD SWPrCH 18 R8PL~OEDBY WIRE NO. (W22) 111 PER AIRPLANE WIRINGDIAGRAM MANUAL.
Page 8 of 9
ADD Note to Figure 5:
NOTE
ON MODEL 690C, S(N 11800 THRU 11128 AND MODEL
690D, Si~ 15001 THRU 15084 WIRE NO. iK27A22CONNECTED TO 60+ SPEED SWITCH IS REPLACEDBY WIRE NO. (W22) 14 AND WIRE NO. 1K1SA22CONNECTED TO 109b SPEED SWITCH 18 REPLACEDBY WIRE NO. (W22) 11 PER AIRPLANE WIRINGDIAGRAM MANUAL.
Wgslofl
C~IIGulfstreamAerospace
CUSTOM KIT NO. 13815 April 1987
AUTOMATIC ENGINE IGNITION SYSTEM
MODELS AFFECTED: MODEL 690C, SERIAL NOS. 11600 THRU 11135.MODEL 690D, SERIAL NOS. IbOOl THRU 15049.MODEL 695, SERIAL NOS. 95000 THRU 95084.MODEL 695A, SERIAL NOS. 86001 THRU 96061, 96064 THRU 96068, 96070 THRU 96074,96016 THRU 96071, 96019 THRU 96084 AND 66086 THRU 96100.MODEL 695B. SERIAL NOS 96062, 96065, 96069, 9607, 96018, 96085 AND 96P01 THRU96208.
REASON FOR PUBLICI\TION: To provide Automatic Ignition for bath engines in ease of engine namsout duringtakeoff and landing on wet runways and during nights in icing conditions. AutomaticIgnition is not limited to only these conditions. Automatic ignition is ovailableanytime the engine RPM is above 60 percent.
NOTE
Installation of this Automatic Ignition System meets therequirements of Part (b) of AD 86-24-12.
COMPLUNCE: AT OWNER’S DISCRETION.
NOTE
IF ANY PIIOIILEMS ARE ENCOUNTERED WHILEINSTALLING THIS CUSTOM KIT, CONTACT YOUR NEARESTGULFSTREAM COMMANDER AUTHORIZED SERYICECENTER.
BY WHOM WORK WILL BE I\CCOMPLISHEO: A B PMECHANIC OR EQUIYALENT.
I\PPROVAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROYED.
ESTIMATED MnN HOURS: TWENTY (20) HOURS.
PARTS DATA: PARTS R68UIRED TO INSTALL THIS CUSTOM glT ON TWO ENGINES MAY BE PROCUREDTHROUGH YOUR NEARESP GULPSTREAM COMMANDER AUTHORIZED SERVICENTER FOR: KIT NO. 162660.00 OR KIT NO. 2 12650.00. REFERENCE THIS CUSTOM KIT, AIRCRAET MODEL AND FACTORY SERIALNUMBER WHEN ORDERING) CUSTOM KIT NO. 138 CONSISTING OF THE FOLLOWING:
Kit No. 1 Models 690C and 695Kit No. 2 Models 690D, 69511 and 69SB
Page 1 of 9
CUSTOM KIT NO. 138
Kit Kit
No.l No.2
BTY BTY PART NO. DESCRIPIIION
1 en. 1 ea. 800814-15 ComponentAssy1 ea. 800814-11 Angle Assy1 os. 800814-19 Angle Assy
1 ea. 800814-21 Angle Assy1 ea. 800814-23 Angle Assy
2 ea 2 ea. 800814-29 Tube AssyI ea. 1 ea. 83(1516-1159 Placard
2 ea. 2 ea. AN894-43 Bushing8 as. 8 ea. AN960D8L Washer
40 ft. 40 R. M22159Rl-20-9 Wire
50 ft. 50 it. M8104419-229 Wire
4 ea. 4 as. llLS21042L08 Nut
2 ea. 2 ea. MS26036-102 Terminal
4 se. 4 ea. M525214-2 End Cap4 ea. 4 ea. MS21039-0807 Screw
4 se. 4 ea. MS210S0081S Screw
2 ea. 2 ea. MS310BE1OSlr3S Connector
1 se. 1 ea. MS35059-21 switch
4 ea. 4 ea. NAS4SDD3-21 Spacer2 ea. 2 ea. 211C119´•115 Pressure Switch
4 se. 4 ea. 53A2 Diode
2 ea. 2 ea. S-0310-804T O´•R(ng2 ea. 2 ea. 3RBX-s or 6602-3 Swivel Tee
8 ea. 8 ea. 320555 Terminal
20 es 20 ea. 820658
Z ea. 2 es. 320562 Tenninal
4 ea. 4ea. M?92811-13 Terminal
2 ea. 2 ea. M?9as/1-22 Terminal
1 ea. 1 ea. Compliance Card
1 ea. 1 ea. Custom Kit No. 138 Instructions
SPEC1AL TOOLS: NONE.
ACCOMPLISHMENT INSTRUCTIONS:
1. Remove baggage wmpartment liner, as necessary, to facilitate installation of th~s Custom Kit.
2. Disconnect airplane batteries.
3. Remove upper and lower cowling from left and right engines.
4. Remove acoes: doors from tap of engine nacellss, as neceseary, to facilitate installation of electrical wiring.
6. Disconnect existing engine torque oil pressure hose assembly from oil preaaure port on engine torque preasuretransducer (refer to Figure i).
6. Install SRGX-S or 6602-3 swivel tee on engine torque pressure transducer (refer to Figure i).
Install 800814-29 tube assembly, AN894-CS buehin[l, S-03109904T ~ing and 211C119-115 pressure switch
(refer to Figure 1).
8. Remove left and right inboard flaps as ontlined in Airplane Maintenance Manual.
g~ Remove left and right inboard wing closeout skins to gain access to electrical wire bundles.
Page 2 of g
CUGTOM KIT NO. 1SB
TYPICAL ENGINE PISSY.
dTYPICAL BOTH LEFT AND RIGHT ENG(NE
~J
THANSDVDER (REF)EXISTING TOROUE
ENGINEU FIREW*LL
IREF)
EXISTING ENGINE TOROUE011 PRESSURE HOSE ASM.
3RSXS TEE OR B(W129 TEEIREFI
SPOB14-29 TUBE AFSY
s´•031010dTO-RINO
2((C118´•(78 PRESSURE SWITCH
msJloellosL´•JsCoNNECroR
1.
Page 8 of 9
CUSTOM KIT NO. 138
0.1341~ Dll\. HOLE
MSJM168´•27SWITCHLEFTORCENTERINSTRUMENTPANEL
AUTO leN RELIOHT I I ILOCATION OPTIONI\LI
830516´•1168~-L 1 TEST
PLACARD
LEFT I I RI(IHT
Fi(uraZ.
10. Remove seats and lower right upholstery panels to gain secess to electrical wire bundles.
ii. Loeate, drill and install MS35059-21 switch on left or center instrument panel. Location of switeh is optional(refer to Figure 2).
12. Install 830515-1159 placard on instrument panel (reler to Figure 2).
13. On airplanes that have Service Buletin No. 194A accomplished, remove existing 800788-5 component assemblyand replace existing angles with 800814-11 and 800814-19 angle assemblies (Models 690C and 695) or 800814-21and 800814-23 angle assemblies (Models 69011 and 695A) using existing hardware. Rein3all existing 800188-3
component assembly using existing hardware (refer to Figure 3).
NOTE
Service Bulletin No 194A applies to Model 690C, serialnos. 11600
thru ll?a?. Model 69011, serial nos. 16001 thru 15018, Model 695,serial nos. 86000 thru 96084 and Model 69SA, serial nos. 96001
thru 96049.
14. If Service Bulletin Na. 194A is not applicable or has not been aocompliahed, locate, drill and install 800814-11and 800814-19 angle assernbliea (Models 690C and BgS) or 80081´•1´•21 and 800814-23 angle assemblies IModels690D 695A and 69511) using MS21039-0813 sorew 14 places), ANB60D8L washer (4 places), NAS43DD3´•24
spacer (4 places) and Ms21042L08 out (4 places) (reler O Figure 31
16. Install 800814-16 component assembly an angle assamblies, installed in step 14., using MSZ1039-0801 screw 14
places) and ANSBODBL washer (4 places) (refer to Figure S).
page loi9
CUSTOM KIT NO. 138
ACFT
BAGGAGE COMPPIRTMENT 14.MI..STRUCTURE IREFI
STA
THIS IS STI\. ZBO.O FORI\IRPLI\NESWITHOUT I i ‘BAO(I~OE COMP*RTMENTEXTENDED BAOOAOE
COMP~RTMENTSTRUCTURE
IREFL800814´•15VIEW LOOKING DOWN eOMPONENTnssv
IREF1
IC 2
8.67
oCOMP~RTMENT
B smucruallREFI
0.173~10´•(77´•1 Dl/i. HOLE
MSn099081JSCREWNI\S4JDDO´•24SPP1CERAN980OSLWASHER
MS21D41L08 NUT
I4PLS)
EXISTING OR
800114´•17ANGLE ASSY
EXISTING OR8W814´•18ANGLE ASSY
MOUNTING HOLE 14 PLS1/ I´•´•;i;´•´•nFOR 80078843 COMPONENT
ASSY (IF INSTALLED) PERSERVICE BULLETIN NO. (8d~
I ,II nit COMPONENTASSvANsSODSLWASHER
(4 PLS)
a c
e 7.36´•´•
VIEW LOOKING FORWARD
MODELS 8900 I\ND 885
FiSurs S. Ishwt( of 2)
PaReSafS
CUSTOM KIT NO. 1SB
RCFT
ST*
STRUCTURE
InEFIBaosl4-lsVIEW LOOKING DOWN CMPohlENTnssY
(REFI
´•BAl
BAGGAGE COMPARTMENTBnOOAOE COMPARTMENT
STRUCTURE rREF)‘I,.BO´•´•TYP
0.1731´•10.111~´• DIA. HOLEMSn038´•0813SCREW
~NBMD8LWASnER
/J MS21042LOBNUT14 PLS)
EXISTING OR Ii I i II EX(STINO OR
malc2~ --II I I I II awncaANGLE nsn II I i I I ANOLEASSY
MOUNTING HOLE (4 PLSIFOR 8m7BS4SCOMPONENT
pgSy (IF INSTALLED) PER
SERVICE BULLETIN NO. (84A
saos~l´•tsCOmwONENTAssv
Ms2lossoao7scnEwaNsmosLwnsHER
’4PLS’ CI´•CI
*orr
FOR SOME MODELS. ITWILL 88 NECESSARY TOTRIM ANGLE ASSEMBLIES.AS NECESSARY. FORPROPER FIT.
D.S5~TYP O.IO’~
WP
VIEW LOOKING FORWARD
MODELS 8800. 6851\ AND 8988
Flers 3. IShast 2 of 21
Page Bois
CUSTOM KIT NO. 138
16. Install 83A2 diode (4 places) and connect auto-ignition system to airplane electrical system as shown in Figures4 and 6. Route new wires along elisting wire bundles.
NOTE
Use M2216918´•20-9 wire fonuard of engine Brewall and use
M8L044/9-20-9 wire and M81044~-22-9 wire aR of engine flrewalland in an fuselage.
1?. Reinstall upper and lower cowling on engines.
is. Reinstall access doom On engine nacelles.
19. Reinstall left and right inboard wing closeout skins.
20. Reinetall left and right inhoard naps as outlined in the Airplane Maintenance Manual.
21. Reinstall interior upholstery panels and seats.
22. Reconnect airplane batteries.
23. Reinstall baggage compartment liner.
24. Check rigging ofinboard naps ae outlined in the Airplane Maintenance Manual.
26. Check auto-ignition system as follows:
a. Battery Switch ON.
b. press AUTO-IGN RELICIIT test swish to the lan L-ION lightshall illuminate.
c. Press AUTO-ION RELIGHT teet switch to the right RION light shall illuminate.
d. Bsuen~ Switch OFF.
26. If annunciator lights do not illuminate while performing step 25., check to assure that annunciator lights are
not burned out end recheek wiring pr Figures 4 and 6.
27. Assure that Pilot’s Operating Handbook has revision dated 9 April 198? pertaining to Automatic Ignition System.
28. Fill out and mail Compliance Card.
ELECTRICAL LOAD: NO CHANGE.
WE(GHT AND BALANCE; The weight and balance change resulting from installation of this Custom Kit is as follows:
WEIQHT (LBS) H´•ARM (INCHE8) HMOMENT(IN-LBS)
Kit Na. 1- +3.63 +284.1 +1031
Kit No. 2 +3.63 +284.1 +1031
SPARES AFFECTED: NO.
PUBLICATIONS AFFECTED: The Airplane Maintenance Manual and illus~ated Parts Catalog changes required bythis document will be incorporated at the nest scheduled change/revision.
RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Custom Kit No. 188,dated 16 April 193’1 entitled "Automatic Engine Ignition System," accomplished (data)
Page 9 of 9
~ICustom KitCulfstreamAerospace
cvSroM KIT NO. 140
Revision 1
18 May 1988
NOSE GEAR STEERIFNG MODIFICAT~ON
APPROYI\L: ENCINBERING DESIGN ASPECTS N(L? FAB APPROVED.
Page 1 of 14 MAN HOURS:
Change to reed: TWENTY (20) HOURS.
RIRa 1 of 1
Custom KitCulfstreamAerospace
CUSTOM KB NO. 140
BNovember 1881
NOSE WHEEL STEERING MODIFICATION
MODELS AFFECTED: MODEL 690C, SERIAL NOS. 11727, 11129 THRU 11755.
MODEL 690D, SERIAL NOS. 16021 THRU 15042.
MODEL 695A, SERIAL NOS. 96055 THRU 86082 AND 96084 THRU 96100.
MODEL 6988, SERIAL NOS. 96062, 96063, 96069, 96075, 96078, 98085 AND 96201 THRU98208.
NOTE
FOR AIRPLANES THAT ARE APPLICABLE, SERVICE LETTER
NO. 367, ENTITLED "PARKER HANNIFIN CORP. PRODUCTREFERENCE MEMO (PRM) NO. 56 (REV A)" SHOULD BE
ACCOMPLISHED IN CONJUNCTION WITH THIS CUSTOM KIT.
CHECK YOUR AIRPLANE LOC BOOK TO ASSURE THAT
SERVICE LETTER NO. 167 HAS BEEN ACCOMPLISHED IF IT
IS APPLICABLE.
REASON FOR PUBLICATION: TO PROVIDE FOR THE REMOVAL OF ELECTRICALLY CONTROLLEDHYDRAULIC SERVO VALVE NOSE WHEEL STEERING SYSTEM AND THE
INSTALLATION OF BRAKE PEDAL CONTROLLED HYDRAULICALLYACTUATED NOSE WHEEL STEERING SYSTEM.
COMPLIANCE: AT OWNER’S DISCRETION.
NOTE
IF ANY PROBLEMS ARE ENCOUNTERED WHILEINSTALLING THIS CUSTOM KIT, CONTACT YOUR NEAREST
GULFSTREAM COMMANDER AUTHORIZED SERVICENTER.
BY WHOM WORI( WILL BE ACCOMPLISHED: A d P MECHANIC OR E~UIYALENT.
APPROVAL: ENGINEERING DESIGN ASPECTS ARE FAA APPROVED.
EsnMnrEo Man HOURS: TWELVE (12) HOURS.
PARTS DATA: PARTS RE9UIRED TO INSTALL THIS CUSTOM KIT MAY BE PROCURED THROUGH YOURNEAREST OULFsTREAM COMMANDER AUTHORIZED 8ERVICEN*ER. REFERENCE THIS CUSTOM KIT,AIRCRAFT MODEL AND FACTORY SERIAL NUMBER WHEN ORDERING CUSTOM KIT NO. 140 CONSISTINGOF THE FOLLOWING:
Pase1of14
CU8TOM KIT NO. 140
BTY PART NO. DEBCRmTION1 ea. 310181-13 Covet
1 ea. 79032D17 Rad Assy1 ea. 19054361 Tubs Assy1 as. 190343-65 Tube Aaey1 se. 190343-69 Hose Aesy1 ea. 180343-11 Nose Assy1 se. 862089-610 Plate1 as. AN5-4A Bolt
1 ea. AN3-6A Bolt1 se. AN3-14A Bolt
4 ea. AN3-21A Bolt4 ea. ANS-24A Bolt2 ea. AN929-4 Cap Assy8 ea. ANI)GO-1OL Washer2 ea. ANSBOD1OL WasherI ea. ANO6OPD10 Washer1 ea. AN960PD10L Washer1 ea. M8a0382-2Cll Pin4 ea. M521042-5 Nut5 ea. M821044NS Nut
2 ea. MSa108SN4 Nut2 as. MS21919D04 Clamp2 se. MS21919D08 Clamp1 es. M824665-134 CotterPin1 ea. MSO?9?5-4 Clevia End1 se. NA843DD3-10 Spacer4 ea. NA845DD9-40 Spacer4 as. NA94SDD3-58 spacer1 as. NAs43HT8-9 Spacer1ea. NAS43HTS-32 Spacer2 ea. NAS484-3-1BA Bolt1 se. REBSN Bearing1 as. BSSlObl Plug Button1 se. V-102 Valve Asey1 ea. Compliance Card1 ea. Custom Kit No. 140 Instructions
SPECULTOOLS: NONE.
~CCOMPLISHMENT (NSTRUCTIONS:
i. Jack airplane as outlined in Chapter 1 of the Airplane Maintenance Manual.
2. Reduce hydraulic system pressure to aero by applying brakes or actuating wing flaps
5. Cain access to airplane battery through baggage compamnent.
4. Remove baggage compartment liner to e.pose airplane batteries.
5. Disconnect airplane batteries.
6. Remove upper nose mmpartment access dear.
7. Cain access to nose gear steering command patentiometer, located in right fuselage nose section, through lowerforward nose access doer (refer to Figure i).
8. Remove and disoard petentiorneter, clamp assembly and bracket assembly (refsr to Figure 1).
5. Cap and staw potentiometer electrical wires N3dA22 (refer to Figure a).
Paseaof1d
O
CUSTOhl KIT NO. 140
AEHoVETnl~CCES8DWRTO(IIUN*CCEIIS
TO COMMIND POTELIIIOMETER
I´• REMOVE AND DISCARDITEMS 1 TnRU B
REINSTALL ITEM ION EXIST1N(I NUTPLATE
11I1PLS)
m
"---~---I II I I II U 1
I1PLSJ
I i i’
i:´•,ij, i~LI
i NOSE LA\DDNNO
IREF)
FieYra I´•
Page S or 14
CUSTOM KIT NO. 140
r
Bi
T 1
pms
CONTROL MODULE
I I i+ I "´•I
t
J -tn I I ´•´•U´•
mllaL,*,
F~un).
Page 4 of 14
CUSTOM KIT NO. 140
10. Remove and discard followup potentiometer installation from nose Landing gear (refer to Figure 3).
11 Replace existing hardware on nose gear collar assembly with NAS464´•9-18A bolt (2 places), ANSB0D1OL washer
(2 places) and M521042-3 nut (2 places). Toque bolt heads 20 to 25 inch-pounds (refer to Figure 3).
12. Cap and staw followup potentiometer electrical wires NS6AaZ (refer to Figure 2).
13. Remove hydraulic nose wheel steering manifold cover, manifold assembly and related fittings and a-rings (refer
to Figure 4).
14. Cap and stow nose gear steering manifold assembly electncal connectors P140, P141, and P142 Cap and stow
electrical wires NS17C22 and NS28A22 (refer to Figure 2).
16 Remove and replace existing cover assembly on fuselage nose deck with 310181´•15 cover using existing
hardware irefer to Figure 4).
16. Seal cover, installed in step 15., with Pro Seal 706 or equivalent MIL-S-8184 sealant as outlined in Chapter20 of the Airplane Maintenance Manual.
17 Remove existing hose assemblies on nose gear a~ambly and tube assemblies that were attached to the existing
nose wheel steering manifold assembly. Seal tube assembly clamp support holes in nose wheel well with Pro
Seal 880112 or an equivalent MIL-8-88~2 sealant as autlinsd in Chapter 20 of the Airplane Maintenance Manual
(refer to Figures 4 and 5).
18. Install AN929-4 cap assembly (2 places i on existing tees where tube assemblies were removed from in step 1?
(refer to Figure 5).
18. Remove existing AN929-4 cap assemblies from right side of parking brake valve (refer to Figure 5).
cnurlo~
When drilling holes for V-1O2 valve assembly, in step 20., care
should be taken so as not to drill into any equipment installed on
nose deck.
20. Rack drill 0.180"10.194" diameter hole (4 places) through existing holes in channel and through nose deck.
Channel is installed on lower side of nose deck. Cain access to channel through wheel well (refer to Figure 6).
21. Install V-102 valve assembly, 190322-11 rad assembly, REBSN bearing end MS2?B75-4 clevis end (refer to
Figure 6).
22. Install 190545-69 Lan brake hose assembly, 790343-71 right brake hose asaembly, 180349-61 left brake tube
assembly and 7908(363 right brake tube assembly. Use existing clamps and attaching hardware or new
hardware furnished with this Custom Kit to suppo~ hose and tube assemblies (refer to Figures 6 and 7).
23. Remove and discard existing switch plate on pilafs control wheel.
24. Remove and discard existing ND 9TR switch from pilo~a control wheel and cap and stow electrical wires (refer
to Figure 2).
25. Install 862055-510 switch plate on pilot’s control wheel using existing hardware.
26. Remove and discard existing TAXI PARK switch cap, switch, lamp bulb and switch bezel. Cap and stow
electrical wires NS4C22. NS4A2a, NS8B2a, NsBC22,N8SB22 and N89BA1Z (reler to Figure 2).
27. Remove Dose steering circuit breaker from lett circuit breaker panel, cap and staw electrical wires and install
8861061 plug button in circuit breaker hole.
28. Remove STR INOP, TAXI and PARK lamp bulbs from annunciator panel.
29. Cain access to annunciator coupler, located on cockpit noor forward of control pedestal, and disconnect connector
plugs P189 and P170. Cap and stow wires NSa?Baa, NBSB22, NS6822, and D30C22 (refer to Figure 8).
90. Reconnect connector plugs P169 and P110 to annunciator coupler.
Page 5 of 14
CU8TOM KIT ND. 140
BEFORE CHANGE
NOblE LANDINDDEAR (REF)
1~
.j
i. REMOVE AND DISCARD ITEMS I
2. REPL~CEITEM1BATTACHINO1TRRU II
15 sHARDWAREWITH:
I\NWODIOLWASHERNasoea,lsn BOLT
rala~rauvr 1 ’71Ji I
ronoursoLTHEno2a TO ta IN´•LBS IZPLS)
~8SURE 6~ME NUMBER 1~ ,iOF SHIMS ARE REINSTI\LLEO OIN SAME LOCATION FROMWHICH THEY WERE REMOVED.
II
Figul´•5.
PageBof1d
CU6TOM KIT NO. 110
VIEW LOOKING AT
FUSELAGE NOSE DECK
1. REMOVE AND DISCARDITEMS 1 THRU 12
2. REMOVE AND REPLACE ITEM13 WITH 310181-13 COVER
3. REMOVE I\ND DISCARD ITEMS
id THRU 18 ISAME AS ITEMLII.3 AM)4 ON F1OURE 51 WHERE
SUPWRT HARDWARE WASREMOVED. SEAL HOLES
I?~81
i11
2 "ii,
Fllursd.
PaSa? of 14
CUSTOM KIT NO. 140
SEE FIGIUREI
1, I
i. REMOVE AND DISCARD ITEMSITHRUI
REMOVE EXISTING CAP ABIY12 PLSL FROM RIGHT HAND SIDEOF PARKING BRAKE VALVE()TEM 51
3. INSTALL *N828´•4 CAPASSY ONTEES IITEMS B AND II WHEREITEMS3 AND 4 WERE REMOVED
i. SEAL HOLE WHERE CLAMPSWERE INSTALLED IITEM 8)
Flgurali.
p,, 8 of 14
CUSTOM KIT NO. 140
AIRPLANE
Q nNsl4nsoLT A;nAS43HT132 SPACER i
1LnaDINo
Mp(044N3NUT
i oEnR cnEFI
I
ExlsrlNaBELLCRANK
IRE FI
~80922´•17ROD ASY
(REF)
780549´•61TUBE A88Y
IREFI
7em49a8HOSE ASSYIAEF)
IREFL Y´•IDZ YALVEAMY
EX18TIN0310527´•J
IREF) CHANNEL IMODEL BBOCII OR
o.lso´•~. lss- OIA 1111 1 It EXIBTINOS10889´•8
HOLE 14 PLS) CHANNEL IMODELS 880D.BACK DRILL THRU B86AAND8JSB)
HOLES IN EXISTINGCHANNEL
iii
I ----f-7em43´•7~ HOSE A6SYIREF)
STA
~IFWD
leasos~u TUBE AMY
InEFI
VIEW LOOKING DOWN ON NOSE DECK
Flp~O´•(SM(012)
Page 8 of 14
CUSTOM KIT NO. 1PO
REBSN BWRINO
NOSE LANDING (IEARIREF) "Y
EXISTING BELLCRANK
IREF)
Inl IMS210B3N9NUT
II
190522´•17ROO AS9Y
PUSELI\OE NOSE DECK
IREF)
0] i I ,MS27879d CLEVIS END
MS?IOBBN4NUT
EXISTING CHANNELIRE Fl
IN WWN POSITION
M~INTI\IN 109 FROM VERTICALFOR VALVE ARM
M9M382´•2el( PIN~N980´•IOLWI\SHERMS21~6(3(COTTEA PIN
AN3-21A BOLT (MODEL B90C1 i N~S4SnTSIJSPI\CER
I\NPZ4A BOLT IOTHER MODELSLANBBDlDL WASHER 12 REB’D) I i bl V´•(02
MS210MNINUT ii i VALVE A8SY
NAF4SDD3~0 SPACER (MODEL BBOC)NA~9De968sPnCER
IOTOER MODELSIUPLS1
VIEW A-A
LOOKING OVTBOARD
FIIYI. L (8h~M? 01 2)
Page 10 01 14
CUSTOM KIT NO. 1(0
MSlslBDOB CLAMP 12 REO’D)ANJBnBOLTNAUIDDJ´•IOSPACER MSZ(BIID(II CLAMP 12 REO’DIANB1IOPD1PLWI\SHER ANSI~BOITMPlOd2jNUT I\NBBOPDIOWASHERINSTALL SPACER BETWEEN MS(W2~3 NUTCLAMPS AND NOSE DECK
780343 -81 TUBE ASSV
V-102 VALVE
ASPY (REF) 1 780343´•89 TUBE ASSY
NOSE LANDINGOEAB (BEFI
EXISTING IBM0(7CLAMP
leouu;71 HOSE ASSY
NOSE GEAR /I EXISTING MS21818D08 CLAMPSSTEERINOCYLINDER IA ANS~A BOLT
MSZ1M2-S NUT
7803119´•88 ROSE ASSY
~1
r~CAUTION
CARE SHOULD BE TAKEN TO PREYENT*NY DAMI\(IE TO EOUIPMENT ON NOSEDECK WHEN DRILLING HOSE AND TUBECLAMPATTACHING HOLES IN NOSE DECK.
Fioursl.
Page 11 o~ 14
CUSI~OM KI~ NO. 1´•10
P189P111
INOP-1121CWAB1\22 E6--N97822----L
141 [z~U E---Nslsn----,
san.~lel il~--M8822---C
*NNUNCI*TORM~STERCnUT1ON
UNIT
029/\22
030822 0281\22---)
FilYns.
Page 12 of 14
CUSTOM KIT NO. 140
31. Reconnect airplane batteries.
32. Bleed nose wheel steering system as follows:
a. Fill hydraulic reselyoir with hydraulic nuid conforming to Military Specification MIL´•H-89282 as
outlined in Chapter 12 of the Airplane Maintenance Manual.
b. Loosen hydraulic line at forward side of nose wheel steering cylinder enough to allow nuid to seep out.
Apply slight presaure to left rudder brake pedal and hold pressure until fluid seepage is free of air.
Tighten forward hydraulic line before releasing pressure on rudder brake pedal.c. Loosen aft hydraulic line of nose wheel steering cylinder and apply alight pressure to right rudder brake
pedal and hold pressure until nuid seepage is free of sir, Tighten aft hydraulic line before releasingpressure on rudder brake pedal.
d Refill hydraulic reservoir with hydraulic fluid as outlined in Chapter 12 of the Airplane Maintenance
Manual.
SS. Bleed brake system as outlined in ChapterS~ of the Airplane Maintenance Manual
34. Functional check the nose wheel steering centering pin as follows:
a. With airplane an jacks, attach weighted tailstand as outlined in Chapter 7 ofthe Airplane Maintenance
Manual.
b. Ensure Bat nose gear strut is fully extended.
c. Turn nose wheel 450 to left by hand, releaee end allow nose wheel to center. Turn nose wheel 46’ to
right by hand, release and allow nose wheel to center.
NOTE
Should nose wheel fail to center, remove centering pin and check
far wear. Centering pin may be rotated 180D, providing a new
weanng surface.
I I*.RNINO IWbRWINO
If centenng pin is to be removed, nose gear strut pressure must be
reduced to zero prior to removing centering pin. Failure to do so
will result in pin becoming a projectile which may result in injuryto personnel.
d. Reduce hydraulic pressure to zero by applying brakes.
e. Using auxiliary hydraulic pump only, apply toe pressure to left and right rudder pedals. Nose wheel
should remain centered.
NOTE
If nose wheel turns to left or right, remove centering pin and check
for weer. Centering pin may be rotated 1800, providing a new
wearing surface.
I UIIRNIN. IW~RNINB
If centering pin is to be removed, nose gear strut pressure must bereduced to zero prior to removing centering pin. Failure to do so
will result in pin becoming a projsetile which may result in injuryto personnel.
page 13 of 14
CUSMM KIT NO. 140
35. Functional check nose gear retraction to assure no interference exists.
36. Reinstell baggage compartment liner.
31. Reinstall upper nose compartment access door.
38. Reinstall lower forward nose access door.
39. Remove jacks and weighted tailstand as outlined in Chapter of the Airplane Maintenance Manual.
40. Assure that the Pilot Operating Handbook has the revision addressing Custom Kit No. 140 mserted.
41. Fill out and mail Compliance Card.
ELECTRICP.L LOAD: -20 Amperes.
WEIGHT FIND BALANCE: The weight and balance change resulting fiom installation olthis Custom Kit is as follows:
WEIGHT (LBS) H-ARM (INCHES) H-MOMENT (IN-LBS)t2.64 35.52 +88.0
-6.62 28.40 -195.0
SPARES IFFECTED: NO
PUQUCATIONS AFFECTED: The Ai~lane Maintenance Manual and illustrated Parts Catalog changes required bythis document will be incorporated at the next scheduled revision.
RECORD COMPLIANCE: Make an appropriate entry in airplane maintenance records as follows: Custom Kit No. 140,dated 8 November 188?, entitled "Nose Wheel 8tesring Modlttcptlon," accomplished (date)
Page 14 of 14
Custom Kit A IR CRI FT CORPORI nON
P.O. Bm: 3889
AdnJbn. WA 88223
at: (208) 435´•978~ FsX:(208) 435-1112
CUSTOM KIT NO. i 41 JULY 17, 1992
ENVIRO AIR CONDITIONING AND PRESS~_RIZATIONSYSTEM_INSTALLATION
******’*’*TO PROVIDE AN ALTERNATIVE AIR CONDITIONING SYSTEM"’"""
Fan can be used for air circulation at any altitude
MODEL 690C(EIOBT mRm) SERTRI´• NUMBERS 11600 TBRV 11’135
MODEL 695(NINE ElcBrY) IERTRL NUMBERS 91000 TBRU 95084
obtain this kit and rull details from p~ournearest ~win Commander service Center.
Custem Kit *LRCR*FT
r0 8~´• UIII
*Ilinglsn. Wi\ IliD
n: is´•enr Fu; ilObl 131´•11(2
CUSTOM KIT NO. 141
JULY 17, 1992
ENVIRO AIR CONDITI(ININD AND PBESBURIZATION BYSTEM INSTALLATION
MODELS AFFECTED 690C Serial Numbers 11600 thru 11735
695 Serial Numbers 95000 thru 95084
that have not previously complied with earlier modification to
Gulfstream Dwg.880718 (Environmental system installation).
Reason for publication: To provide an alternative air
conditioning system.
Complianoe: At owner’s discretion.
NOTE:
IF ANY PROBLEMS ARE ENCOUNTERED WHILE INSTALLING THIS
CUSTOM KIT CONTACT TWIN COMMANDER A/C CORP.
By whom work will be accomplished: A P Mechanic or equivalent.
Approval. Engineering aspects are FAA approved
Estimated man hours: 375 hours for-I kit two evaporator at rear
pressure bulkhead; 385 hours for -2 6 -3 kits with one evaporatorat rear bulkhead and one evaporator forward.
NOTE:
TIME DOES NOT INCLUDE RECTIFICATION OF PRESSURIZATION
LEAKS, PAINTING OR WEIGHT AND BALANCE.
PARTS DATA: A PACKAGE OF DRAWINGS PERTAINING TO CK 141
INSTALLATION IS PROVIDED AS ADDENDUM A.
NOTE:
CUSTOM KIT 134, IMPROVED INLET AIR SUPPLY SYSTEM, MUST BE
ACCOMPLISHED AT THIS TIME IF NOT PREVIOUSLY INSTALLED.
SEE STEP 35. PARTS LIST DOES NOT INCLUDE FASTENERS
WHICH SHOULD BE PROCURED LOCALLY. OTHER PARTS REQUIREDTO INSTALL THIS CUSTOM KIT MAY BE PROCURED THROUGH YOUR
NEAREST TWIN COMMANDER SERVICE CENTER. REFERENCE
AIRPLANE S/N WHEN ORDERING CK141-1, CX141-2, CK141-3
CONSISTING OF THE FOLLOWING:
CX141-1 a Evaporator at rear pressure bulkhead.
CK141-2 1 Evaporator at rear pressure bulkhead and 1 Evaporatorinside sideways seat (only possible if A/C does not have
an electrical lavatory).
CX141-3 1 Evaporator at rear pressure bulkhead and
L Evaporator inside R/H bar.
Page 1
PARTS DATA (1)
All installations will require the following parts:
ITEM NO QTY PART NUMBER DESCRIPTION
1 1 1-48028)-0 PLUG
2 2 1-4803 05-0 CONNECTOR
3 2 110134-229 STATIC DECAL
4 1 110134-271 DECAL. EXT PWR
5 1 1250400-22 COMPRESSOR
6 1 1300)50 CABIN TEMP CONTR
7 1 1)00360 FLOW CONTROLLER
8 1 130 044 0-1 CABIN TEMP SENSOR
9 1 1300450 TEMP SENSOR
10 1 1300464 FLOW SENSOR
11 1 1300520-1 MUFFLER
12 1 1588-00-1 VALVE
13 30 205050-1 SOCKET
14 12 26838-5 STUD
15 1 310868-55 DOUBLER
16 Z 310868-57 COVER
17 5 5466 NIPPLE
18 7 60619-1 SOCKET
19 6 60620-1 PIN
20 1 62065-3/8X3/8X)/8 TEE
21 4 640903-1 PIN-RECEPTACLE
22 20 640905-1 TERMINAL
23 3 7277-i-2-12-507-61 CIRCUIT BREAKER
24 1 800655-501 BRACKET ASSY
25 1 800697-511 BUS BAR
26 1 800812-1 DOUBLER
27 1 800816-17 PANEL ASSY
28 1 800816-3 PLACARD
29 1 800816-5 PLACARD
)O 1 800816-7 PLACARD
31 1 800816-9000-1 AFTWIRE BUNDLE
32 1 800816-9000-2 2 EVAP WIRES BDL
33 1 8)3038-1 RELAY
34 1 862064-501 ESCUTCHEON
35 1 880647-11 DOUBLER
36 2 880697-13 DOUBLER
37 1 880647-5 GRILL ASSY
38 2 880701-11 BRACKET
39 1 880701-9 SPACER
40 1 880708-11 CHANNEL
41 1 880708-13 CHANNEL
42 1 880708-15 WEB
43 1 880708-19 SHIM
44 1 880708-21 PAN ASSY
45 1 880708-27 ANGLE46 2 880708-29 DRAIN TUBE ASSY
47 2 880708-3 CHANNEL
48 1 880708-35 HOSE
49 2 880708-37 HOSE, DRAIN
50 4 8807CS-49 ANGLE
51 1 880708-5 CHANNEL
ITEM NO. QTY PART NUMBER DESCRIPTION
52 1 880708-7 CHANNEL
53 1 880709-17 ANGLE ASSY
54 1 880709-413 SHROUD ASSY
55 1 880709-9 TAB
56 1 880718-17 TUBE ASSY
57 1 880718-19 TUBE
58 1 880718-23 POTENTIOMETER
59 1 880718-39 HOSE
60 1 880718-41 HOSE
61 1 880718-43 HOSE
62 1 880718-5 TUBE
63 1 880718-63 HT EXC/DUCT ASSY
64 1 880718-65 ANGLE ASSY
65 1 880718-69 ANGLE ASSY
66 1 880718-7 TUBE
67 1 880718-73 PANEL ASSY
68 1 880718-79 MODULATING VALVE
69 1 880718-81 FLOW/TEMP CNTR
70 1 880718-9 TUBE
71 1 880722-505 ANGLE ASSY
72 1 880722-507 ANGLE
73 1 880722-508 ANGLE
74 1 880722-509 ANGLE
75 1 880722-510 ANGLE
76 1 880723-1 COVER ASSY
77 1 880723-503 BAFFLE ASSY
78 1 880723-515 TUBE ASSY79 1 880723-529 CHANNEL ASSY
80 2 880724-19 LONGERN DOUBLER81 1 880724-3 TUBE ASSY
82 1 880725-25 DUCT ASSY
83 1 880726-1 TUBE ASSY
84 1 880727-501 BOX ASSY-LOWER
85 1 880727-j02 BOX ASSY-LOUVER
86 1 880728-3 SUPPORT ASSY
87 1 880728-5 TEE ASSY
88 1 880728-7 TEE ASSY
89 2 880730-11 MOUNTING PLATE
90 1 880730-7 COVER
91 1 880730-9 COVER
92 1 880732-19 HOSE ASSY
93 1 880732-21 HOSE ASSY
94 1 880732-25 HOSE ASSY
95 1 880732-29 HOSE ASSY
96 1 880734-3 TUBE ASSY
97 1 880734-9 PLACARD
98 1 880735-3 BRACKET AS SY
99 1 880735-7 ANGLE
100 16 900129-58 CLAMP
101 2 900129-66 CLAMP
102 4 930060-1 CLIP ASSY
103 16 AD34ABS POP RIVET
104 4 AD42ABS POP RIVET
ITEM NO. QTY PART NUMBER DESCRIPTION
105 20 AD44A8S POP RIVET
106 1 AGC-1 FUSE
107 45 AN3-3A BOLT
108 1 AN3-4A BOLT
109 13 AN3-5A BOLT
110 2 AN4-22A BOLT
111 4 AN4-5A BOLT
112 4 AN503-6-8 SCREW
113 10 AN737TWZZ CLAMP
114 2 AN737TW48 CLAMP
115 1 AN804D6 TEE
116 1 AN804D8 TEE
117 2 AN818-6D NUT
118 1 AN924-6D NUT
119 1 AN924-8D NUT
120 66 AN960D10 WASHER
121 14 AN960D10L WASHER
122 1 AN960D1216 WASHER
123 4 AN960D4 WASHER
124 6 AN960D416 WASHER
125 40 AN960D6 WASHER
126 5 AN960D6L WASHER
127 1 AN96~D916 WASHER
128 20 D100-00 SLEEVE SOLDER
129 24 D101-00 SLEEVE SOLDER
130 24 D436-36 SPLICE
131 )O D436-37 SPLICE
132 30 D436-38 SPLICE
133 1 ECARD COMPARISON CARD
134 1 FELT 1/16X1 BLK FELT (BLACK)135 20 FT FLEXGUARD 1/2" DIA. WIRE BUNDLE SLEEVING 135
136 1 ADJA FUSE HOLDER
137 4 M7928/1-22 RING TERMINAL
138 8 M7928/1-24 RING TERMINAL
139 3 M7928/1-3 RING TERMINAL
140 1 M7 9 Z 8 /1-42 RING TERMINAL
141 2 M7928/1-50 RING ERMINAL
142 2 MS21042-) NUT
143 2 MSZ1042L06 NUT
144 50 MS21042L3 NUT
145 4 MSZ1042L4 NUT
146 2 MS21071L06 NUTPLATE
147 2 MS21073-L06 NUTPLATE
148 12 MS21266-1N GROMMET
149 1 MSZ1266-3N GROMMET
150 1 MSZ1919DG10 CLAMP
151 5 MS21919DG13 CLAMP
152 B MS21919DG28 CLAMP
153 1 MS21919 DG34 CLAMP
154 1 MS24166-D1 RELAY
155 6 MS24621-15 SCREW
156 4 MS24621-18 SCREW
ITEM NO. PTY PART NUMBER DESCRIPTION
157 9 MS25036-103 TERT.INAL
158 5 MS25036-108 TER~INAL
159 5 M525036-123 TFREIINAL
160 2 3S25036-125 TER~INAL
161 1 MS25036-132 TERI~INAL
162 1 1S25036-133 TERMINAL
163 1 lS25036-154 TERMINAL
164 4 MS25171-1S NIPPLE
165 2 MS25171-3S NIPPLE
166 4 MS27039-1-08 SCREW
167 3 MS27039-1-09 SCREW
168 4 MS27039-4-04 SCREW
169 1 MS3126E10-6S CONNECTOR
170 15 MS3192A-20A CONTACT PIN
171 15 MS3193A20A CONTACT SOCKET
172 50 MS3367-1-9 TYRAP
173 50 MS3367-2-9 TY~P
174 4 MS35206-216 SCREW
175 5 M535206-229 SCREW
176 4 MS35206-230 SCREW
177 12 MS35206-231 SCREW
178 6 MS35207-265 SCREW
179 1 MS35207-267 SCREW
180 2 MS35842-15 CLAMP
181 2 NAS1564D6-4 REDUCER
182 1 NAS43DD3-32 SPACER
183 2 NAS43DD3-48 SPACER
184 2 NAS43DD4-53 SPACER
185 1 NC22S16-50-6 DUCT
186 2 412 PANEL BOX BLACK
187 1 NWZW2S-5-102-4 DUCT
188 2 PT06CE-8-4S CONNECTOR
189 1 RB-67-1-SK-7-M KNOB
190 1 RNF10O 3/4 HEAT SHRINK TUBE
191 2 RNF100-2IN-TY1 TUBE RED SHRINK
192 3 RNF100-31N-TY1 TUBE RED SHRINK
193 2 RNF100-4IN-TY1 TUBE RED SHRINK
194 2 RPC2300-W FELT INSULATION
195 4 S0333A6-20C SCREW
196 8 S0335A8-4 SCREW
197 1 50-370-501 JUMPER
198 3 S3A2 DIODE
199 1 SEC07C12 CONE SEAL
200 2 SECo7C16 CONE SEAL
201 3 SEC07C24 SEAL
202 8 ST3333-6-12 TUBE
203 1 9T3333-7-12 TUBE
204 1 TAPE 622 DUCT TAPE 2"
205 Z TIGLS1-1CWHC SWITCH
206 1 WTTY CARD WARRANTY CARD
207 1 YAEV4CL3 TERE:INAL
208 2 X6687 DUCT
PARTS DATA (2)
Please refer to airplane nodel and serial number and type of
installation for additional parts required.
CK141-1-1
Airplane Models 690C and 695 Serial Numbers 11600-11718 and
95000-95087, two evaporators at rear pressure bulkhead.
ITEM NO. BTY PART NUMBER DESCRIJTION
1 1 800816-9501 WIRE SET (2 EV)2 1 850618-501 PANEL
3 1 880697-29 GRILL ASSY
4 1 880697-31 DOUBLER
5 1 88 0701-413 WIRED SW PANEL
6 1 880718-101 ANGLE
7 2 880723-531 COVER
8 2 880728-15 EVAP ASSY
9 1 880732-23 HOSE ASSY
10 1 880732-27 HOSE ASSY
11 1 880741-1 HZO DEFLECTOR
12 1 AN821-8D ELBOW
13 4 MS24621-18 SCREW
14 6 MS27039-1-1l SCREW
15 2 M527039-1-20 SCREW
16 1 TIGLS1-1CWHC SWZTCA
CKI41-1-509
Airplane Models 690C Serial Numbers 11719-11729, two evaporatorsat rear pressure bulkhead.
ITEM NO. QTY PART NUMBER DESCRIPTION
1 1 800675-501 BRACKET ASSY
2 1 800816-9501 WIRE SET (2 EV)3 1 850618-501 PANEL
4 1 880697-5 INLET GRILL
5 1 880701-413 WIRED SF PANEL
6 2 880723-531 COVER
7 2 880728-15 EVAP ASSY
8 1 880732-23 HOSE ASSY
9 1 880732-27 HOSE ASSY
10 2 AN821-8D ELBOW
11 4 MS27039-1-11 SCREW
12 6 MS27039-1-20 SCREW
13 1 TIGLS1-1C-WHC SWITCH
CK141-1-511
Airplane Models 690C Serial Numbers 11730-11735, two evaporatorsat rear pressure bulkhead.
ITEM NO. QTY PART NUMBER DESCRIPTION
1 1 8 008 16-9 503 WIRE SET (2 EV)2 1 850665-513 PANEL
3 1 880697-5 GRILL ASSY
4 1 880701-413 WIRED SW PANEL
5 1 880718-55 PANEL
6 1 880718-57 PANEL
7 1 880718-61 PANEL
8 2 880723-531 COVER
9 Z 880728-15 EVAP ASSY
10 1 880732-23 HOSE ASSY
11 1 880732-27 HOSE ASSY
12 2 AN821-8D ELBOW
13 4 AT405B CAP SWITCH
14 3 MLW3022 SWITCH
15 1 MLW3028 SWITCH
16 4 MS27039-1-l1 SCREW
17 Z MS27039-1-20 SCREW
CKf41-2-525
Airplane Models 690C and 695 Serial Nunbers 11600-11718 and
95000-95084, one evaporator at rear pressure bulkhead and one
evaporator inside sideways facing observer seat.
ITEM NO. PTY PART NUMBER DESCRIPTION
1 11FT 1/2ID-X-3/BWALL #ZARMAFLEX INSL
2 1 1250340 SPLIT EVAP ASSY
3 1 3708 VENT
4 1 800816-9501 WIRE SET (2 EV)
5 1 850618-501 PANEL
6 1 862064-501 ESCUTCHEON
7 1 880697-29 GRILL ASSY
8 i 880697-31 DOUBLER
9 1 880700-75 TUBE ASSY
10 2 880701-11 BRRCKET
11 1 880701-17 SW PLATE ASSY
12 1 880701-9 SPACER
13 1 880718-101 ANGLE
14 Z 880723-531 COVER
15 1 880728-19 EVAP ASSY DUAL
16 1 880732-37 HOSE ASSY
17 1 880732-39 TUBE ASSY
18 1 880712-41 HOSE ASSY
19 1 880732-43 HOSE ASSY
20 1 880737-11 SCREEN
21 1 880737-13 BRACKET
22 1 880737-15 NAMEPLATE
23 1 880737-3 ANGLE
24 1 880737-7 ANGLE
25 1 880737-9 ANGLE
26 1 880741-1 HZO DEFLECTOR
27 4 AD42ABS POP RIVET
28 3 AN737TW107 CLAMP
29 1 AN737TW114 CLAMP
30 1 AN81j-8D UNION FLARE
31 2 AN821-8D ELBOW
32 4 MS24621-18 SCREW
33 3 MS27039-0812 SCREW
34 6 MS27039-1-11 SCREW
35 2 MS27039-1-20 SCREW
36 1 NW2W2S12-72-6 DUCT
37 1 NW21v’2S14- 72-6 DUCT
38 4 S0333A6-20C SCREW
39 1 VZZOOD4 SOCKET WIGGINS
40 1 VZZOjD4 NIPPLE WIGGLNS
41 1 VEC2OOD8 SOCKET WIGGINS
42 1 VEC205D8 NIPPLE WIGGINS
CKI4I-Z-535
Airplane Models 690C Serial Numbers 11719-11729, one evaporatorat rear pressure bulkhead and one evaporator inside sidewaysfacing observer seat.
ITEM NO. QTY PART NUMBER DESCRIPTION
1 11FT 1/2ID-X-3/8 WALL bZARMAFLEX INSL
2 1 1250340 SPLIT EVAP ASSY
3 1 370B VENT
4 1 800612-1 DOUBLER
5 1 800816-9501 WIRE SET (2 EV)6 1 850618-501 PANEL
7 1 862064-501 ESCUTCHEON
8 1 880697-5 INLET GRILL
9 1 880700-75 TUBE ASSY
10 1 880701-9 SPACER
11 2 880701-11 BRACKET
12 1 880701-17 PLATE
13 2 880723-531 COVER
14 1 880728-19 EVAP ASSY
15 1 880732-37 HOSE ASSY
16 1 880732-39 TUBE ASSY
17 1 880712-41 HOSE ASSY
18 1 880732-43 HOSE ASSY
19 1 880737-11 SCREEN
20 1 880737-13 BRACKET
21 1 880737-501 PLACARD
22 1 880737-7 ANGLE
23 1 880737-9 ANGLE
24 1 80737-15 NAMEPLATE
25 4 AD42ABS POP RIVET
26 3 AN737TW107 CLAMP
27 1 AN737TW114 CLAMP
28 2 AN821-8D ELBOW
29 3 MS27039-0812 SCREW
30 4 MS27039-1-l1 SCREW
31 6 M527039-1-20 SCREW
32 1 NW2W2S12-72-6 DUCT WIRE REINFORCED
33 1 NW2W2S14-72-6 DUCT WIRE REINFORCED
34 4 S0333A6-20C SCREW
35 1 TIGLS1-1CWHC SWITCH
36 1 V2200D4 SOCKET WIGGINS
37 1 V2205D4 NIPPLE WIGGINS
38 1 VEC200D8 SOCKET WIGGINS
39 1 VEC205D8 NIPPLE WIGGINS
CK141-2-537
Airplane Models 690C Serial Numbers 11730-11735, one evaporator
at rear pressure bulkhead and one evaporator inside sideways facingobserver seat.
ITEM NO QTY PART NUMBER DESCRIPTION
11FT 1/2ID-X-3/8 WALL #ZARMA FLEX
2 1 1250340 EVAP ASSY
3 1 3708 VENT
4 1 800816-9503 WIRE SET (2 EV)5 1 850665-513 PANEL
B 1 862064-501 ESCUTCHEON
7 1 880697-5 GRILL ASSY
8 1 880700-75 TUBE ASSY
9 2 880701-11 BRACKET
10 1 880701-17 SW PLATE ASSY
11 1 880701-413 WIRED SW PANEL
12 1 880701-9 SPACER
13 1 880718-55 PANEL
14 1 880718-57 PANEL
15 1 880718-61 PANEL
16 2 880723-531 COVER
17 1 880728-19 EVAP ASSY
18 1 880732-37 HOSE ASSY
19 1 880732-39 TUBE ASSY
20 1 880732-41 HOSE ASSY
21 1 880732-43 HOSE ASSY
22 1 880737-11 SCREEN
23 1 880737-13 BRACKET
24 1 880737-15 NAMEPLATE
25 1 880737-7 ANGLE
26 1 880737-9 ANGLE
27 4 AD42ABS POP RIVET
28 3 AN73 7TW107 CLAMP
29 1 AN73 7TW114 CLAMP
30 a AN821-8D ELBOW
31 4 AT4058 CAP SWITCH
32 3 MLW9022 SWITCH
33 1 MLW3028 SWIICH
34 3 MS27039-0812 SCREW
35 4 MS27039-1-11 SCREW
36 2 M527039-1-20 SCREW
37 1 NW2W2S12-72-6 REINFORCED DUCT
38 1 NW2W2S14-72-6 REINFORCED DUCT
39 4 S0333A6-20C SCREW
40 1 V2200D4 SOCKET WIGGINS
41 1 V2205D4 NIPPLE WIGGINS
42 1 VEC200D8 SOCKET WIGGINS
43 1 VEC205D8 NIPPLE WIGGINS
II
CK141-3-541
Airplane Models 690C and 695 Serial Numbers 11600-11735 and
95000-95079, one evaporator at rear pressure bulkhead and one
evaporator inside R/H bar.
ITEM NO QTY PART NUMBER DESCRIPTION
r 11FT I/2ID-X-3/8 WALL #ZARMA FLEX
2 1 125 0200-31 EVAPORATOR ASSY
3 1 3708 VENT
4 1 800816-9501 WIRE SET (2 EV)5 1 850618-501 PANEL
6 1 862064-501 ESCUTCAEON
7 1 880697-29 GRILL ASSY
8 1 880698-47 PLATE. EVAP MTNG
9 1 880700-67 HOSE ASSY
10 1 880700-69 TUBE ASSY
11 1 880700-71 TUBE ASSY
12 2 880701-11 BRACKET
13 1 880701-17 PLATE
14 1 880701-9 SPACER
15 1 880718-101 ANGLE
16 1 880723-531 COVER
17 1 880728-19 EVAP ASSY DUAL
18 1 880732-37 HOSE ASSY
19 1 880732-45 TUBE ASSY
20 1 880732-47 HOSE ASSY
21 1 880737-11 SCREEN
22 1 880737-13 BRACKET
23 1 880737-15 PLACARD
24 1 880737-3 ANGLE
25 1 880737-7 ANGLE
26 1 880737-9 ANGLE
27 1 880741-1 H2O DEFLECTOR
28 4 AD42ABS POP RIVET
29 1 AN737TW107 CLAMP
30 1 AN737TW98 CLAMP
31 1 AN815-8D UNION FLARE
32 4 AN821-8D ELBOW
33 4 MS24621-18 SCREW
34 6 MS27039-1-11 SCREW
35 2 MS27039-1-20 SCREW
36 1 NW2W2S12-72-6 REINFORCED DUCT
37 1 S0333A6-20C SCREW
38 1 TIGL51-1CWHC SWITCH
39 1 V2200D4 SOCKET WIGGINS
40 1 V2205D4 NIPPLE WIGGINS
41 1 VEC200D8 SOCKET WIGGINS
42 1 VEC205D8 NIPPLE WIGGINS
special tools: Enviro System test box (800816 test box)Freon system charging equipmentGround pressurization test cart
Micro shaver and sheet metal riveting tools
Digital Temperature meter 0-2000C
Electrical connector insertion/extraction tools
and crimping tools
P/N 32447(SANKYO) dipstick
NOTE:
PERsoNNEL uHo ARE NOT FAMILIAR WITH THE ENVIRO AIR CONDTTIONINO SYSTEM ARE
ADVISED TO REAO THE RELEVANT PAGES IN CHAPTER 21 OF THE AIRPLANE MAINTENANcE
MANUAL TO FAMlLTARIZE THEMSELVES PRIOR TO cOMMENOEMENT OP THIS MoOIEIcATIoN.
IN ADDITToN, PLEASE ENSURE THAT REFERENCZ: TS MAGE TO THE DRAWTNDS PRoVLDEO
FOR SPECTFTED TORC~UE VALUES WHEN ASSEMBLING THE NEW COMPONENTS.
Accom~lishmant InstructionsPrior to commencement of this kit it is strongly recommended that
the modification center obtains a list of existing discrepanciesfrom the flight crew. These discrepancies should be identified
by the maintenance personnel prior to flight crew departure.Airplane should be weighed prior to commencement of modification
to obtain a base line. Pressure check cabin as follows prior to
removal of cabin interior or Sundstrand unit.
(a) Remove static line from cabin pressure controller and
cap off port on controller. Attach a gauge calibrated in
inches of water to the static line to read cabin
pressure. Set rats selector knob on cabin pressurecontroller full clockwise position.
(b) Connect ground pressurization test cart to recirculationair duct in empennage.
(c) Remove sound proofing from R/H side wall of baggagecompartment to gain access to pneumatic system manifold.
(d) Connect an external air pressure source regulated to
18 +/-1 PSI to the inlet side of the cross
containing the overpressure switch.
NOTE;
THIS AIR SOURCE IS TO INFLATE THE DOOR SEAL.
WARNING:IT IS IMPRACTICAL TO SECURE THE PA88ENaERICREsr DOOR 80 THAT IT
CANNOT BE OPENED FROM THE OUTSIDE. Tr 58 RECOMMENDED THAT WHILEPERFORMINa GROUND PRESSMIZATION CHECKS THAT LIAFEOVRRDB BE TAKEN TO
PREVENT SOMEONE FROM OPENING THE MAIN CABIN DOOR. OPENINe DOOR WITH
CABIN PRESSZRRISED. TO ANY DEGREE. WILL CAUSE CONSIDERABLE BODILYHARM AND DESTRUCTION TO EOUIPMENT. PLACE SIGNS AROUND THE AIRPLANE.
PUT TAPE ACROSS DOOR HANDLE. SEAtINO HANDLE IN CLOSED POSITION.
HAVE PRESSURIZATXON CONTROL PERSONNEL INSIDE THE AIRPLANE AND ENSUREELECTRICAL POWER 18 8ELECTED ON AND THAT DOOR LOCK/UNLOCK SWITCH
LOCATED ON OVERHEAD SWITCH PANEL TS DEPRESSED TO THE DOOR LOCK
POSITION.
(e) Set cabin altitude knob full Cow.
(f) Close and secure the cabin door.
YIARNINO:
DO NOT EXCEED MAX ALLOWABLE
DIFFERENTIAL PRESSURE (5.4P9ID Model 695 9
690C) OTXERWISE STRUCTURAL DAMAGE AND
POBBIBLY INJURY 80 PERSONNEL COrrLD OCCUR
(g) slowly increase the pressure on the pressurization cart
until the flow rate reads 100-110 SCFM.
CAUTION:
DO NOT EXCEED 2000 FEET PER MIN OR DAMAGE CAN OCCO~R TO
PRESSURIBATION CONTROLLER.
(h) Record max cabin pressure.
(i) Set flow meter reading to 124 SCFM.
(j) Record max cabin pressure
(k) Record all cabin leaks. Pay particular attention to the
door seal, wing roots,windshields, pitot heads, rudder
pedal boots, control column boots, cabin floor access
panels, rear pressure bulkhead and Top mounted antennae.
CAosXON;
DO NOT EXCEED 2000 FT PER MINUTE OR DAMAGE CAN OCCOR TO
PRESSURIZATION CONTROLLER.
(1) Slowly decrease the pressure on pressurization cart.
(m) Depressurize the aircraft. Do not exceed 2000 ft perminute or damage can occur to pressurization controller.
open cabin door.
(n) Seal all cabin leaks and repeat test until maximum
differential of 5.4 PSID is achieved at 110 SCFM.
(0) Disconnect all test equipment
Alternate method if a pressurization cart is not available
perform pressurization test using bleed air from R/H enginerunning at 90-95% RPM.
(a) Disconnect the static air line at the cabin pressurecontroller and install a needle valve and a piece of
hose in series with the static air line and reconnect
to the controller. See Figure 1.
ENSURE NEEDLE VALVE IS FULLY OPEN
P(rTJ ~ReDBU*O
a,n
WAI
i~LENOID VALVE
1~3
~71
TrP~ROLLBR Ic~sl*
~ermRe
r pl~reR
NOTE: CHECK VA LVE NPT
INSTi~LLED ON MPDEL b90D I I
ANO bj;A AIRPLANEI.
NE30~E VA LVE
FIGURE 1
WARNING
PRE88rmIBA~ION SYBTEM CANNOT BE CONTROLLED ELECTRICALLY
(b) Close and secure cabin door
(c) Start R/H engine and set rpm to 90-95% using normal
starting procedures in P.O.H.
(d) Disconnect ground power unit.
(e) Turn on R/B generator h cabin bus.
(f) Trip cabin depress circuit breaker.
(g) Set cabin rate knob fully clockwise altitude select
knob fully counter clockwise.
(h) Set max flow switch to off.
(i) Select bleed air switch to L/H closed and environmentalmaster switch to on.
(j) Close needle valva slowly, pressurize cabin to max
differential.
CAUTION:
Do NOT EXCEED 2000 FT PER MTII OR ORMAOE CRN OCCUR To
CONTROLLBR´•
(k) Record differential pressure.
(1) Set max flow switch to on. Pressurize cabin to max
differential. Record max differential.
(m) Record all cabin leaks. Pay particular attention to
the following areas, door seal,emergency exit seal,wing roots, windshields, pitot heads, rudder pedalboots, control column boots, cabin floor access panels,rear pressure bulkhead, top mounted antennae.
(n) Open needle valve slowly daprassurize cabin at a
comfortable rate.
CAUTION:
Do NOT EXCEED Z000 rr PER YTNUTE OR DRMRCE CRN OCCUR TO
PRLSIURTZ~LTTON CONTROLZER´•
(O) When cabin altitude is close to field elevation reset
cabin depress circuit breaker.
(p) Verify cabin pressure is zero.
(q) shut down engine using normal procedures.
(r) At completion of pressure test seal all cabin leaks and
repeat test until cabin maximum differential is
obtained using the specified engi~e rpm of 90-95%.
(s) Remove needle valve and reconnect static line to the
cabin pressure controller.
(t) Set cabin rate and altitude knobs back to normal.
NOTE:
If you are unable to obtain max cabin differential then
check the pressure setting or the pressure regulatorshut off valve utilieing procedures found in chapter 21
of the airplane the Maintenance Manual.
In addition check calibrate the cabin differential pressureindicator.
Once cabin sealing integrity is established proceed as follows:
i. Fix weighted tailstand to empennage tie-down.
z. Disconnect remove both A/C bat_eries. Label GPU
socket "do not attach electrical power.
3. Remove all cabin cockpit seats, L/H R/Hcabinets, R/H table if fitted. Retain for re-
installation.
4. Remove cabin cockpit floor carpets. Retain for re-
installation.
5. Remove all trim from rear pressure bulkhead. Retain
for re-work and re-installation.
6. Remove both L/H and R/H cabin head linings. Retain for
re-installation.
7. Remove R/H lower cabin and cockpit side trim. Retain
for re-installation.
8. Remove baggage compartment trim from rear pressurebulkhead, from overhead from R/H sidewall if not
previously removed and retain for re-installation.
9. Remove plenum assy complete with the mixing valve.
Retain for re-work.
10. Working from belly access hatch and through baggagecompartment remove complete Sunds-,rand ECU and its
mountings. Remove baggage compar:ment trim. Supportstructure as required to facilitare easy removal.
11. Disconnect and remove main electrical junction box
assembly. Ensure that all wires are marked to facilitate
re-installation. Disconnect both generator control unit
connectors and remove pin D with its shielded wire intact
from the GCU connectors. Wires to be left in A/C for re-
installation. Utilize correct extraction tool for this
task. Retain electrical junction box for rework and re-
installation.
12. Remove air conditioning muffler and its brackets from
frame Y290; duct from muffler to rear cabin floor 8
discard.
Remove ECU "air in" metal shroud assy from R/H side of
fuselage discard. Leave P/N 880682-7 sealed to fuselageskin. (If CK 134 is already accomplished.)
14. Remove overhead duct transfer tube from beneath baggagefloor and discard.
15. Remove GCU’s, speed switches, prop de-ice timer retain
for re-installation,
16. Disconnect and remove ground power relay, ground power
connector, and over voltage relay. Retain for rework
and re-installation.
17. Remove inverters if location will interfere with L/Hskin doubler installation refer to Dwg.880697, Sheet
#2. Retain for re-installation.
18. Remove bleed air pipe P/N 880656-1 from ECU back to
junction of L/H and R/H engine bleed air pipes. Discard.
19. Place crawling boards across frames to facilitate re-
work in baggage area.
20. (Model 690C only) Remove propeller syncronizationcontrol box mounting plate from rear pressure bulkhead
structure. Do not disconnect electrical wires.
CAUTION;
DO N0T DRILL FASTENERS COBPLETELY OUT-DRILL OFF READS
AND PUNCX OUT 8HANKS.
21. Drill off fasteners in rear cabin floor duct transition
assembly for re-circulation air and cold air for cabin
overhead ducts and remove assemblies discard.
22. Disconnect and remove DC circuit breaker panelassembly(ies). Retain for rework and reinstallation.
23. Disconnect and remove air conditioning control panelassembly. Retain for re-work and reinstallation.
24. Remove L/H cockpit side trim up to side window lower
edge. Retain for re-work and reinstallation.
25. Remove lower flex cold air duct from Y piece at rear
pressure bulkhead and discard.
26. Remove Y piece cold air duct assy and discard.
NOTE i
RETATN UPPER TWO COLD AIR DUCTS IOR RE-WORR AND Re-TNSTWRTION.
27. Sand down L/A fuselage skin between F.S.Y254 F.S.Y310,#5 longeron 6 #9 longeron to reveal fasteners. Use 120 gritsand paper orbital sander. See Figure 2 for location.
28. Remove GPU socket relay bracket assy, 805008 doubler 6
hinge from L/H side of fuselage skin. Drill off heads of
fasteners and punch out shanks. Retain 3ea screws for later
use.
CAOTION:
DD NOT DRILL FASTENERS COMPLETELY GOT-DRILL OFF READS
AND POhlCR OUT 8KANK6.
29. Drill off fastener heads to release fuselage skin
between Y254 Y310, 65 longeron 6 89 longeron as
required to facilitate 880697 -11 doubler
installation. Refer to figure for typical area.
30. (a) Working from leading edge of fuselage skin carefullyinsert 880697-11 doubler between skin stringers and frames.
(b) Position 880697-11 doubler in accordance with Dwg.
880697, Sheet #2. Ensure that 20 edge distance an all
fasteners is maintained throughout.
(c) Mark grill cut out on fuselage skin using 880697-11
doubler cutout as a pattern.
(d) Mark GPU socket cut out on 880697-11 doubler to match
cut out in 800812-1 doubler and fuselage skin. Refer
to Dwg. 880718, Sheet 3, Zone 30A/B.
CAUTION:
ENBURE THAT ZD EDDE DISTMCE ON ALL FABTENERS I8
MAI~TAINED TBROUDWO~I!.
(e) Drill 880697-11 doubler fastener pattern usingfuselage skin existing fastener pattern.
(f) Drill 880697-11 doubler and fuselage skin in accordance
with Dwg.880697, sheet P2.
(g) Drill fuselage skin h 800812-1 GPU socket doubler in
accordance with Dwg. 880718, Sheet Zone 30A/B
(h) Remove 800812-1 GPU socket doubler from airframe.
(i) Remove 880697-11 doubler from airframe.
(j) Open out all holes for rivet pattern as shown on
Dwg’s.880718, Sheet 83, Zone 30A/B and 880697, Sheet
62, In 880697-11 doubler and fuselage skin De-burr all
holes and remove swarf from rear of fuselage skin,stringers and frames.
(k) cold dimple all fastener holes in 800812-1 GPU socket
doubler.
(1) Using a router bit cut fuselage skin grill cut out
where previously marked and smooth edge of cut out.
(m) Using a router bit cut 880697-11 doubler CPU socket
cut out where previously marked. Clean up cut out.
(n) Cold dimple all fastener holes in 880697-11 doubler.
to) cold dimple all new holes in fuselage skin.
(p) Position 880697-13 longeron doublers I.A.W. Dwg. 880697,Sheet B1. Drill off fasteners pattern and remove-13
doublers.
(q) Position 880697-11 doubler between fuselage skin,stringers and frames I.A.W. Dwg.880697-1l, Sheet #2.
Cold Dimple 880697-13 doublers.
(s) Position 880697-13 doublers I.A.W. Dwg.880697,Sheet 81.
(t) Postion 800812-1 doublers I.A.W. Dwg.880718, Sheet g3.Zones 30A/B, zone 29A/B and zone 28A/B.
(u) Install rivets to fuselage shin, 880697-13, 800812-1
880697-13 doublers I.A.w. Dwgs. 880697, Sheet #1 and
Sheet 62, 880718 Sheet 63 zones 28, 29 30A/B.Ensure that 0.12 die hole thru fuselage skin 880697-
11 doubler is left open for drainage purposes see
Dwg.880697, Sheet Il for location adjacent to F.S.
Y272.00.
(v) Install 880697-5 grill assy I.A.W. Dwg. 880697, Sheet bl.
(w) Build up 800675-501 bracket assy with componetsremoved from old GPU socket bracket assy. TogetherWith new bus bar 800697-511 I.A.W. Dwg. 880718, Sheet
63, Zone 32 A/B.
(X) Install GPU socket access door hinge and associated springs.
(y) Install built up 800675-501 bracket assembly I.A.W.
Dwg.B80718, Sheet I), zone 28, 29, 30 A/B. Utilize
previously removed 3ea attaching screws.
31. Install 880709-13 shroud assy to inside of L/Hfuselage skin between F.S. Y272 Y290 I.A.W. Dwg.880709, Sheet 12. Seal all edges of shroud assy to
structure using coast proseal 890 or equivalent two partsealer to obtain good water tight seal.
32. Fit 880708-35 hose to 880709-13 shroud assy utilizingAN737TW22 clamp. Install AN737TW22 clamp to other end
of hose for later installation to 880708-21 pan assy.See Dwg.880708, Sheet B1, Zone 3E.
33. (a) Make cut out in fuselage skin at F.S. Y259 2-9.65 on
R/H side of fuselage I.A.W. Dwg. 880734, Sheet 81.
(b) Install 880734-3 Tube assy I.A.W. Dwg.880734,Sheet II.
(c) Install 880734-9 Placard I.A.W. Dwg.880734, Sheet bl.
34. Gain access to R/H side of fuselage skin between
F.S. Y272.00 Y290.00 6 betveen #’s 9 10
longerons.
Turn off Ozbottle at bottle and purge system by operating02 masks in cockpit.
CAUTTON:
OXY(IEII L~NE Is LOCRTED TN IDNBERON´• DO NOT DAMAGE OXYGEN
LTNE WHTLE: DRTW.INO OR RIYETTNO.
(a) Make skin cut out using a router I.A.W. Dwg.880724,Sheet BZ.
(b) Install 880724-1 flush scoop assembly I.A.W. Dwg.880724, Sheet #2. All fastener locations to be
cold dimpled prior to installation. It is permissibleto use BB4 in lieu of LZ4 rivets.
(c) Install 880724-19 longeron doublers inside longerons#’s 9 Io I.A.W. DWg.880724, Sheet 62.
~a´•:
a-
I--´•´•,
ORIGINALAs Received By
ATp
PHOTO 1
23
35. Ascertain if Custom Kit 134, improved inlet air supplysystem, has been accomplished on aircraft model
690C Serial Numbers 11600 thru 11718 model 695
serial Numbers 95000 thru 95084. If C.K. 134
has been accomplished on your aircraft or serial
number is not affected than disregard this step and
proceed to step 36. If CK-134 is to be accomplishedproceed as follows.
(a) Follow instructions on page 2 of C.K. 134 steps 3, 4
11, 13 (but only install 880682-7 shroud assy to
fuselage skin. e~ not install 880682-3 closure or
880682-15 as these are reguired). Step 15,
16 8 17. Refer to CK-134 Figures 1 2.
NOIE:
IT IS PEIUIISSIBLI TO USE BB4 IN LIEU 01 CR22~8-4-) BLTND
RIVETS
36. Airplane model 690C Serial no’s 11600 thru 11718 model
695 serial numbers 95000 thru 95084 only, modify3)0387 Avionics lower access door as follows:
(a) Make cut out in door skin to match 880697-)1 doubler
I.A.W. Dwg.880697, Sheet t5.
C~LIITION:
ENBURE TKAF 8RORT VERTICAL PORTION OF 880741-1 WATER
REFLECTOR Is FAClEO FORI~ARDB.
(b) Attach grill and doubler assy together with 880741-1
water deflector assy to inside of 330387 access door
I.A.W. Dwg.880697, Sheet 65 and Engineering Order 880697
ADV R Sheet #2 and 880741 Dwg.
(c) Trim away portion of 330387 Avionic access door to 0.95
2.60 dimensions as shown on Dwg.880725, Sheet P1, Zone 4,5 6 A/B.
(d) Install MS21266-1N grommet using EC1403 adhesive or
equivalent 1.A.W. Dwg.880725, Sheet B1, Zone 4, 5 6
A/B. Retain door for later installation.
37. Airplane model 690C serial no’s 11719 thru 11735
modify rear avionic lower access door 310957-35 as
follows:
(a) Make cut out in 310957-35 door assy I.X.W. Dwg.880697, Sheet 83.
(b) Install 880697-5 grill assy I.A.W. Dwg.880697, Sheet
3.
~ea
o...,
IEB tYILTjI11 nacesl
mn~ue Bp I~LBS
ijjji
muraoLT~uruESiX)ROUE 5e’10 IKLBS
YODULEUOUHTINO PL4TPORU
dIFT ~O*leR CUIEL
R´•monl M ImDl~a ot Uod~
FIGCRE
25
NOTE:
4164 FUSEBLOCK SHOWN ON DWG. 880708, SHEET ~1 HAS BEEN
SUPERCEDED BY CIRCUIT BREAKER PANEL 860816-17 SHOWN ON
PHOTOGRAPH 62 AND SHOULD BE INSTALLED IN PLACE OF THE
FUSE BLOCK.
,s. (a) Build up Freon compressor shelf in accordance with
Dwg.880708, Sheet bl h photograph. See Dwg. 800816
Sheet #1 for C.B. panel build up.
NOTE:
PRY PARTICULAR ATTENTION TO VIEW CC,DD ZONE 90 OF
DWD 880708.
(b) Place built up freon compressor shelf assy into rear
of airplane. Install at L/H side of fuselage between
fuselage stations Y272 Y290 I.A.W. Dwg.880708, Sheet
#r.
(c) Install 880708-35 hose using AN737TW22 clamp to 880708-
21 drip pan I.A.w. Dwg.880708, Sheet B~1, Zone 3F.
(d) Install compressor 1250400-15 Rev H or subsequenton built up shelf assy I.A.W. Dwg.880708, Sheet
#1, Zone 22D 23C. Torque mounting bolts to 50-
70 inch ibs
NOTE i
IT WILL BE NECESSARY TO REMOVE THE BOLTS AND REFIT TBEH
TO THE LTDHTENED wee 880708-15 IN oRDER To INSTALL
COMPRESSOR CONDENSOR MODULE ASSY. TORPUE WEB BOLTS TO
20-25 IN LBs. SEE FIDURE 3.
(e) Check oil level of Compressor as follows: (See Figurea)
Dipstick P/N 32447 (SANKYO) or equivalent, will be requiredto check the oil level in the compressor. If oil leak is
noted, check compressor oil level as follows:
NOTE:
THE COMPRESSOR iS SHIPPED TO TWIN COMMANDER FULLY CHARGED WITH
THE CORRECT PUANTTTY OF SUNISO NO. 5GS OIL; THEREFORE, NO OTL
LEVEL CHECK IS REPUTRED UNLESS THERE IS A NOTICEABLE OIL LEAK FROM
THE COMPRESSOR AND/OR AIRPLANE SYSTEM.
NOTE:
STEPS F THROUGH H BELOW ARE NECESSARY IN ORDER TO CLEAR THE
DTPSTTCK OF INTERNAL PARTS ANO ALLOW TTS INSERTION To FULL DEPTH.
(f) Remove the oil filler plug. Look through the oil
filler plug hole and rotate the clutch front plateto position the internal parts as shown in figure 4.
______ ____ __ __
OIL PILLER‘Im*uw mmesoo *ora wm*n~ aumcsoR
uourmla *NOLE LEFTDUNTINO INOLE IICHT
~OD BI~LL
aoo
isnn SDCXFF OW
I’
saLL9DOxEIONnurEiPurr KINar n*ra
orraesson(TO~VIEII)
*aamm imaa atom uxlmn~i Lnrnmw r~slmi Nnal nmen rnane unal
OIL PILLERm3LE
a
c~ oil ha
FIGURE 4
17
(g) Compressor mounted to the right (facing clutch).Center the parts as they are moving to the rear of
the compressor (discharge stroke).
(h) Compressor mounted to left (facing clutch).Center the parts as they are moving to the front
of the compressor (suction stroke).
(i) Insert the dipstick (P/N )2447) to its stop position.The stop is the angle near the top of the dipstick.
NOTE:
OIL LEVEL SHALL BE BETWEEN DTPSTTCK INCREMENTS 4 AND 6.
(j) Remove dipstick and note increments of oil on
dipstick.
(k) Service compressor, as required, with SUNISO No.
5GS or Texaco Capella E Oil (500 viscosity).
(1) Install oil filler plug.
39. Place previously removed electrical main junction box
into position. Check to see if circular relay K1,clears recently installed compressor-condenser module
support. If relay X1 does clear the support remove
main electrical junction box once more. If relay K1,does not clear support then remove Main electrical
junction box and modify as follows:
(a) Remove K1 relay from relay base
NOTE:
DO NOT DISCONNECT ELECTRICAL WIRES.
(b) Remove K1 relay base from side of junction box.
(c) Install new relay angle P/N 880718-101 inside main
junction box r.n.W. Dwg.880718, Sheet #3, Zone 30E.
(d) Cut Tywraps as necessary from electrical bundle and
relocate relay base for relay K1 to -101 angle.
(e) Install relay K1.
NOTE:
1. EXISTING WIRING 15 SHOWN AND NEW WIRING WITH A
SoLrD LINE. WIRING AND TERMINAL ENDS ARE PROVIDED IN DARTS KIT.
2. AIRPLANE SERIAL NUMBERS 11616~ 11617, 95022, 95023,
95024, 95025, INSTALL K39A K40A 833038-505 RELAYS, AS
SHOWN ON DWG.800816, SHEET 14, ZONE 7, AND 8AB.
(f) Modify main electrical junction box wiring I.A.W.
Dwg.800816, Sheet #4, Zones 4D, 5D.
(g) Re-install main electrical junction box using retained
hardware. Reconnect all disconnected wires.
(h) Re-install Generator control unit panel below main
junction box. Install shielded wires into Pin 0 (usecorrect insertion tool for this task) of both L/H and
R/H control unit connectors. Ensure L/H and R/Hconnectors receive correct wires. Refer to relevant
schematic in wiring diagram manual. Re-install all
connectors and wires to panel.
40. (a) Connect wires from main electrical junction box to
External Power Control panel and to Compressor module
circuit breaker panel, I.A.W Dwg.B00816, Sheet #4,Zones 3, 4, 5, c D.
(b) Connect wires between Compressor Condenser module
and circuit breaker panel mounted on CompressorCondenser module structure.
(c) Connect ground wire from Compressor ground stud to
frame at F.S. Y290.
NOPE:
RETAIN WIRES X52R22 AND H52B22 PRoH REGULATOR SHUT OI‘B
VALVE AND ENVIRONMENTAL SWTTCW PRNEL FOR LATER USAGE.
a. cut back wires from duct tamp sensor and dead end
close to rear pressure bulkhead.
b. Remove cabin temp sensor controller from above
emergency exit. Cap and stow connector. Remove temp
sensor/controller from trim panel and discard. Refit
trim panel.
41. Remove relays KY36 and K46 located L/H side of center
line between F.S. 272 and 290 cut back wiring as close
to rear pressure bulkhead as practical and dead and.
Remove wiring from relay K46 and Temp control valva.
42. Install channel assy 880722-505 between F.S. Y290.00
and F.S. Y308 I.A.W. Dwg.880718, Sheet #2, Zones 9 10
A. Thru F views BE CE and zone 20 D, E F. Make
certain that anchor nut plates for KRA relay are
positioned towards rear of aircraft as shown in zone
20E of Dwg.B80718.
NOTE;
PORTION OF TUBE TO BE REMOVED BY CUTTING IT OFF FLUSH.
43. Modify previously removed 880653 plenum assy I.A.W.
Dwg.880726, Sheet bl.
(a) Install 880723-515 tube assy I.A.W. Dwg.880718, Sheet
#2, Zone 19, 20 C D. Use sealant RTV red high tampor equivalent between joints.
(b) Remove 5.62" of L/H side tube and drill holes I.A.W.
DWg.880726, Sheet 81.
(c) Install 880723-1 blank I.A.w. Dwg.880718, Sheet #2,Zone 19C, 11C view JJ. Use sealant RTV Red high tempor equivalent between joints.
(d) Retain modified plenum assy for later installation.
NOFE;
ENSURE 0001) ELECTRICAL BOND BETWEEN AIRCRAFT STRUCTURE AND
BRACKET ASSY BY BURNTSHTNO THE MATING SURFACES AND APPLYING A
sRrrsH COAT OF ALOOINE 600. USE BONDING BRUSH TO BURNISH
EPUIPHENT MOUNTING HOLES.
44. (a) Install 880735-3 Bracket Assy between F.S. Y29000 and
Y308 on L/H side of fuselage I.A.W. Dwg.880735, Sheet 82.
45. Models 690C s/n’s 11600-11729 695 s/n’s 95000-95084
proceed as follows:
(a) Disassemble removed circuit breaker panel to
provide access. Remove 5 amp circuit breaker
identified as TEMP AUTO and replace it with 2 ampcircuit breaker P/N 7277-5-2-12-507-61 provided.Install 800816-7 Placard marked ECS BLD AIR over
circuit breaker.
(b) Remove 5 amp circuit breaker marked TEMP OVRRD and
replace it with 2 amp circuit breaker P/N 7277-5-2-12-
507-61 provided. Install 800816-5 Placard marked TEMP
CONTROL over circuit breaker.
NOTE:
IT TS PREFERABLE TO CONNECT CTRCUTT BREAKER DIRECTLY TO blDrsTnrsvTlon BUS BAR. HOWEVER IF A SPARE LOCATION IS NOT
AVAILABLE TO ACHIEVE THIS THEN USE 80370-501 JUMPER TO CONNECT
CB TO DISTRIBUTION bl BUS ERR.
(c) Find any unused (open) circuit breaker position and
install 2 amp circuit breaker P/N 7277-5-2-12-507-61
provided. Circuit breaker must be connected to
Distribution B1 bus bar.
(d) Connect other side of circuit breaker to any unused
pin in connector P7 CB1 using 20 guage wire. Install
800816-3 placard marked FLOW CONTROL over circuit
breaker.
(e) Install cabin temp sensor 1300440-1 I.A.W.
Dwg.880718, Sheet #3, Zone 40 CB.
(f) Reassemble circuit breaker panel and place aside for
later installation.
46. Model 690C S/Ns 11730 thru 11735 find previouslyremoved L/H and R/w cB panels.
(a) Disassemble L/H circuit breaker panel as required to
gain access. Locate CB labelled temp AUTO. Remove 5
amp CB and install 2 amp circuit breaker. Install
800816-7 placard over circuit breaker.
(b) Install 7277-5-2-12-507-612 amp circuit breaker in
any spare location and connect to Distributor #1 bus
bar. Vtilize 50370-501 jumper if necessary to connect
CB to correct bus bar. wire r.A.W. Dwg.800816, Sheet
#2, Zone 6D. Install placard TEMP CONT. P/N 800816-5
over circuit breakers.
(c) Dissassemble R/H circuit breaker panel as necessaryto gain access. Locate CB labelled Temp OVRD. Remove
CB and replace with 2 amp cB P/N 7277-5-2-12-61.~nsta11
placard 800816-3 over circuit breaker.
(d) Install cabin temp sensor 1300440-1 I.A.W. Dwg.880718, Sheet g3, Zone 40 CB.
(e) Install cabin temp sensor on lower surface of R/Hcircuit breaker penal I.A.W. Dwg.880718, Sheat 83,Zone 40 DE.
(f) Reassemble circuit breaker panels and place aside for
future installation.
NOTE:
VALVE ASSY IS INSTALLED ON AFT SUPPORT CHANNEL
AT F.S. Y290.00.
47. Mount 880718-79 assy which includes 1300330
modulating Y valva to Compressor Condenser supportstructure I.A.W. Dwg.880718, Sheet #2, Zone 13 EF,and Dwg.880718, Sheet 65, Zone 61-69.
BOTE:
VALVE IS INSTALLED ON OVERHEAD FRAMES.
48. (a) Install 1300490 Flow Control valve between F.S. Y254
and F.S. Y272 I.A.W. Dwg.880718, Sheet ~5, Zones 66-
68.
(b) Connect up NW2W2S-5-102-4 duct to valve and 880734-1
tube I.A.W. Dwg.880718, Sheet 82, Zones 19, 20, 21, AB.
~I
Received ByAfP
PHOTO 2
32
NOTE:
SEE ZONE 7 6 15 FOR TYPICRL INSTAL;ATTON. USE EXISTING CLAMPS
AND HAROWRRE FOR INSTRLLRTI~ON.
49. Refer to Dwg.880726, Sheet %1. Install 880656-3 tube
assembly insulate tube assembly joints with ~PC2300-
WFELT and cover insulation with heat shrink tubing I.A.W.
Owg.880657, Sheet BL. Use existing clamps and hardware for
installation.
50. (a) Install bleed air shut off valve P/N 1588-00-1.
Connect valve to 880656-3 tube assy installed in step49.
(b) Install 880718-17 tube assy between shut off valve and
1300490 flow control valve I.A.W. Dwg.880718, Sheet 52,Zone 18, 19, AB. Insulate valve with RPC2300-W FELT.
cover insulation with heat shrink tubing T.A.W.
Dwg.880657, Sheet 63, Zone 45 and sheet 81, Zone 15 for
typical installation.
51. (a) Install tube assy 813333-6-12 between 1300490 flowcontrol valve and 880718-5 (or -25 as applicable) tubes
I.A.W. Dwg.880718, Sheet ~2, Zone 19 CD.
(b) Install ST3333-6-12 tube to other end of 880718-5 (or25 as applicable) and connect to 1300330 temp modulatingvalve T.A.W., Dwg.880718, Sheet 82, Zone 13FG.
52. Install 880722-1 angle assy at F.S. Y290.00. Use
existing hardware I.A.W. Dwg. 880718, Sheet 62, Zone
1), 14 C and 18-20 D.
53. (a) Install 813333-6-12 tubes on ends of muffler P/N1300520-1 using clamps I.A.W. Dwg.880718, Sheet #2,Zones 19, 20 D-F. Place muffler in position thru F.S.
Yzs0 from lightning hole ready for connection to heat
exchanger and temp modulating valve.
(b) Build up heat exchanger ground blower assy I.A.w.
DWg.880718, Sheet IZ and photograph 12 opposite.
(c) Install heat exchanger ground blower support structure
I.A.W. Dwg.880718, Sheet #2 Zone 11-21.
54. (a) Install ground blower/heat exchanger duct assemblybetween F.S. Y290.00 and F.S. Y308. Use mounting boltsand washers provided (4 each) I.A.W. Dwg.880718, Sheet
#2, Zones 11 thru 21 and Figure 5.
(b) Connect 880718-9 tube between temp modulator Y valve
and muffler 1300520-1 I.A.W. Dwg.880718, Sheet #2, Zone
14 19, 20 D.
’´•H) NUT ~ND ZE~L-FORaVe NUI ItPBYm
(NLLIS*NU ~FETI WIAE1NO FITTINB
CUYP
mA(IUE1Cp
CLIYP UISBROW 1 IKLBS(PPLSInose
NBE EUUPTOROUE(I-?2
INLBS(1PLS)CUUP
~e SCRCIYINOLOCKWISHEA
~YCT NBE ~s"*usenr~m
eree~*ln m YOOUL*TIHaYILVEN8E O
EXI(IYSIOVIRBO.
TORaUE 30~0 I,LIIS 12 PL~I
OUCTHase~ \Y~HOSEr2PLS,
CULIPronoUElcn~ ~nhrm r4~ V _CL)IUPIrc~escaPrs,, II ru8e ronous~a.n
IbLas(~prs)
OUCTISS’IH09E Y IY H09E
NBE
NBEIJSICLIYP
CUUP(ZPLBJ TOR~UB (622
IKL89(2PLS~UUFFLER
RIYIIRSCOOP .I ;UBE CUUP HEITEXOHINOERTOR(IUE(bl~IKLBS(ZPLS)
UBIH*(RDISTRIBMONPLEHUy
TeYPeRINAe9eN90R
FIGUIIE 5
51
(c) Connect 880718-19 tube between aft end of 1300520-1
muffler and heat exchanger cutlet T using 5T3333-6-12
tube and clamps I.A.W. Dwg.880718, Sheet 62, Zone 19F.
(d) Connect 880718-7 tube to tamp modulating valve and heat
exchanger using 513333-6-12 tubes and clamps route -7
tube thru opening in compressor/condenser module drippan l.R.w. Dwg.B80718, Sheet 82, Zone 19.
(e) Connect duct NC22S16-50-6 between 880724-1 scoop and
ground blower heat exchange assembly I.A.W. Dwg.88o718,Sheet #2, Zone 15.
(f) Install KIIA relay MS24166-D1 to 880722-505 channel withbolts and washers provided I.A.W. Dwg.880718, Sheet #2,Zones 20, 21 E.
(g) connect up red wire from ground blower to KT(A relayand black wire to ground on frame F.S. Y308 I.A.W.
Dwg.800816, Sheet #4, Zones 3, 4 8. Utilize red rubberterminal protectors.
55. (a) Install previously modified cabin air distribution
plenum assy 880653 with 4 bolts previously removed.See Figure 5 (21-60-01 202) Model 690C or695 MM.
(b) Connect up lower cabin air ducts (2 each) to plenumusing existing hardware.
(c) Install 1300450 duct sensor provided in same locationas old duct sensor on plenum assembly. Utilize sealantRTV Red nigh Temp or equivalent between plenum and ductsensor to ensure a gas tight joint.
(d) Install 880718-11 tube assembly between heat exchangeroutlet T and plenum assembly using ST5333-6-12 tube and823333-7-12 tube and clamps I.A.W. Dwg.880718, Sheet
#2, Zone 17 GH and zone 19, z0. Install mounting clampMS2~919-DG38 I.A.W. Dwg.880718, Sheet X2, Zone 11 H and
Zone 20 D. Move avionic wire bundle outboard toward
R/H side of fuselage to facilitate tube installation if
necessary.
56. Cut hole in rear pressure bulkhead I.A.W. Dwg.800816,Sheet bl, Zone 4C for new wire bundle. Cut hole in310868-57 cover to match hole in rear pressure bulkhead.cut hole in 310868-55 nut plate doubler I.A.W. Dwg.800816,Sheet #3, Zone 4C. Assemble doublers to pressure bulkheadwith MS35206-230 screws provided. Install MSZ1266-3N
grommet as shown on Dwg.800816, Sheet #1, Zone 4C.
57. (a) Cut two holes in rear pressure bulkhead for freon hose
fittings I.A.W. Dwg.880732, Sheet 84, Zone 6, 7D.
(b) Install tee fittings in rear pressure bulkhead as
called out on Dwg.880732, Sheet #4, Zone 7B. Do not
tighten tee fittings at this stage as they must be
sealed and oriented to suit later installation of
evaporators.
(c) Install 880732-19 and -zl hose assemblies between Tee
fittings on rear pressure bulkhead and freon compressorI.A.W. Dwg.880732, Sheet 64, Zone 4, 5 AB and views 8,C D. Hose assemblies between compressor and clamps at
FS Y272 frame may be marriage Ty-wrapped in place(To any convenient structure or bracketing). Hoses are
routed overhead to R/H side of fuselage and then alongfuselage side to rear pressure bulkhead.
(d) Lightly coat flares at compressor end with refrigerantoil and apply a small amount of thread sealant to
fitting and install fittings on compressor receiver
dryer assembly. (stay clear of first 2-3 threads).Torque fittings to 160-200 inch ibs.
(e) position tee fittings at rear pressure bulkhead to
facilitate easy installation of evaporator hoses on
forward side of rear pressure bulkhead. Tighten T
fitting nuts on rear side of rear pressure bulkhead and
seal around fittings to prevent cabin pressure loss.
Use coast pro-seal 890 or equivalent.
(f) Install hoses 880732-19 21 to T fittings at rear side
of rear pressure bulkhead. Lightly coat flares with
refrigerant ail and apply a small amount of thread
sealant to fitting threads (stay clear of first 2-3
threads).
NOTE:
ENSURE THAT A 0000 ELECTRTCAL BOND EXTSTS BETWEEN CONTROLLER AND
MOUNTTNO BRACKET.
58. (a) Install mass flow controller 1300360 an bracket
assembly L/LI side of fuselage between F.S. Y290.00
and Y308. NE. Mass flow controller is fitted forward
of cabin temp controller refer to Dwg.880735, Sheet #2.
Utilize MS35206-231 screws and AN960-6 washers
provided.NOTE:
TEMP CONTROLLER TS MOUNTED AFT 01 MASS FLOW CONTROLLER. ENSURE A
DOOD ELECTRICAL 8oND EXISTS BETWEEN CONTROLLER AND BRACKET
ASSEMBLY. UTTLTZE MS35206--23L SCREWS AND AN960D6 WASHER
PROVTOED. REFER TO DW0.880735~ SWEET 82.
(b) Install cabin temp controller 1300350 on left hand side
of fuselage between F.S.Y 290.00 and Y 308.00.
NOTE:
ENSURE R GOOD ELECTRICAL BOND EXISTS BETWEEN FLOW SENSOR
AND BRACKET ASSEMBLY. ORIENTATE CONNECTOR TO REAR OF A/C.
(c) Install mars flow sensor 1300464 to bracket assemblyL/H side of fuselage between F.S. Y290.00 and Y308 aft
of cabin temp controller utilize M935206-231 screws and
AN960-6 washers provided.
CAVTION:
Use EXTREME CAUTION WHenr INSTWTNO PROBE´• DO NOT BEND´•
(8) Route flow sensor wires along avoinics shelf lower
support and install flow sensor probe in 880718-11 tube
assembly I.A.W. Dwg.880718, Sheet 62, Zones 20 DE and E
and View EE, Zone 24. Ensure that red protective cover
is removed. Utilize AN503-6-8 screws and AN960-D6
washers. Seal between faces with RTV red high tempsealer RTV KD 492 or equivalent.
NOTE:
IT TS PERMISSIBLE TO UTILIZE PSEVIoUSLY RETAINED WIRES CODED
H52A22 AND H52B22 FOR ENVIRONMENTAL SHUT OFF VALVE OR TO
UTTLIZE NEW WIRING PROVTDED. ROUTE WIRING CLEAR OF CONTROL
CABLES AND BLEED ATR DUCTS. UTILIZE TYWRRP STRAPPING AS REPUIRED.
TIE WIRE BUNDLE ALONG AVIONICS SHELF WITH AVTONTCS WIRING BUNGLE
AND ROUTE ALONG R\H SIDE OP FUSELAGE WITH AVIONICS WIRING TO REAR
PRESURE BULKHEAD T.A.W. AC43.13.1A. REFER TO DWG.800816,SHEET 3 FOR MODELS 690C S/N 11600 THRU 11729 AND 695 S/N95000 THRU 95084. REFER TO OWG.800816, SHEET #2 FOR MODEL
690C S/N 11730 THRU 11735.
ENSURE THAT TEMP AND FLOW CONTROLLER RND FLOW SENSOR SHIELDING
GRouND WIRES ARE CONNECTED I.A.W. NOTE 10 ON DWG.880816,SHEET #2 OR ~3 AS APPLICABLE. CONNECT ENVTRO WIRING TO CB
PANEL AND ENVIRONMENTAL CONTROL PANEL AND ANNUNCIATOR PANEL
CoNNECToRS I.A.W.RELEVENT DWG.800816. ANY EXTSTTND WIRES
WHICH HAVE TO BE REMOVED FROM CONNECTORS SHOULD BE REMOVED
COEIPLETELY FROM THE A/P OR TERMINATED AT BOTH ENDS WITH
WIRE CAPS AND STOWED.
59. (a) Install enviro wire bundles thru rear pressure bulkhead.
Utilize hole installed in step 57. Feed wire bundle from
rear of pressure bulkhead forward with connectors for
controllers and valves aft of pressure bulkhead. Connect
up wiring to temp and flow controllers, Duct temp sensor,
temp modulating valve, mass flow sensor, mass flow valve,and environmental shut off valva.
(b) Install wire AC12C14 between KRA relay Al terminal
(ground blower relay) and 20 amp R/A circuit breaker on
800816-17 panel mounted on compressor/condensor module
structure I.A.W. Dwg.8008L6, Sheet 14.
37
(c) Install wire ACLA2O between KRA relay Terminal X2 and
Terminal strip TA4 located R/H side of baggagecompartment behind trim. Install S~A2 diode between
wire AC1A2O and TA4 I.A.W. Dwg.800816, Sheet 64.
(d) Install Diode S3A2 across terminals XI, X2 of KRA relayas shown on Dw9.800816, Sheet P4.
(e) Install wire AC2A to terminal X1 of KRA relay and placethru rear pressure bulkhead with wire bundle I.A.W.
Dwg.800816, Sheet 14.
(f) Install wire AC1OA from compressor power relay mounted
on compressor shelf and Terminal 11 of X39 inside main
junction box I.A.W. Dwg.80oQ16, Sheet 64.
(g) Install wire AC4C16 to lo-press switch on compressorcondenser module and thru rear pressure bulkhead hole
I.A.W. Dwg.800816, Sheet #4.
(h) Install wire AC9B16 to 15 amp EB circuit breaker on
800866-17 panel mounted on compressor/condensor module
support structure route wire thru hole in rear pressurebulkhead.
(i) Install bus feeder wire between main bus bar inside
main electrical junction box and lOSamp circuit breaker
mounted on 800816-17 panel I.A.W. Dwg.800816, Sheet#4.
(j) Install wire AC3A14 to K66 relay A2 terminal and 15 ampcircuit breaker mounted on 800816-17 panel I.A.W.
Dwg.800816, Sheet 64.
(k) Install wire AC1OBZO to K39 relay terminal 11 and K88
terminal nZ external PWR control relay I.A.W.
Dwg. 800816, Sheet R~4.
Seal wire bundle thru rear pressure bulkhead with Coast
Pro-seal 890 or equivalent.
60. (a) Take previously removed environmental control panel and
re-wire I.A.W. Dwg.800816, Sheet 83, for Models 690C
S/N’s 11600 thru 11729 and 695 S/N’s 95000 thru 95087.
Utilize existing switches, new switches and potentiometerprovided. For Model 690C S/N’s 11730 thru 11799 re-
wire I.A.W. Dwg.800816, Sheet #2. Refer to new facia
panel for location of switches. See sketch for
clarification.
BLgTCH IS DRRWN VTEIYED IFROM REAR WITB TOP OP PANEL
DOWMIRRDS
ENVIRO CABIN 5 MASS
MASTER DEPRESS 6 15 MANUAL TNCR FLOW
OFF OFF OFF SPRTNG OFF
LOADEO
CENTEI(
OFF
ON ON POTENTTOMETER ON ON
NORMAL AUTO OEC8 LOW
22 1 10 I 11 16 1 1 I ONL
14 1 8 17 11 I 1 12 30
Il 11 13 f 1 GND 1
x Terminal with a wire1 Terminal not used
(b) Remove switch guard from old overlay panel and install
on new overlay panel in same location.
61. Remove master annunciator panel front and remove lampbulb from position labelled ECU press. Refit panelfront.
62. Cut hole on L/H side of cockpit side wall trim for
freon control panel I.A.W. Dwg.880701, Sheat 82. -503,-507 installation. Ensure that top edge of PNL assy
aligns with AC circuit breaker panel top edge. Do not
fit panel assy at this stage. See step 75 later.
63. (a) Install 880708-29 drain assembly I.A.W. Dwg.880718,Sheet #3, Zones 38, 39, ABC to fuselage lower skin on
center line at F.S. Y175.8.
(b) Install 0.56 Dia hole thru floor at F.S. Y175.8 on
canter line.
(c) Install 850718-43 hose to drain assembly and thru 0.56
dia hole. Seal around hole with coat pro-seal 890 or
equivalent.
64. For those airplanes that are to receive 2 evaporatorsmounted at rear pressure bulkhead proceed as follows:
(a) Install 880730-7 and 880730-9 covers in place of floorduct assemblies previously removed at F.S. Y178 I.A.W.
Dwg.880730, Sheet /1, Zones 13,14, I5.A. Seal between
-7 and -9 covers with coast Pro-Seal 890 or equivalent.
39
NOTE:
CENTER OF L/H EVRPOIULTOR IS INSTALLED ON CENTER LTNE OF THE
R~RPLANE.
(b) Install 880728-5 and 880728-7 evaporator support Tee’s
I.A.W. Dwg.880728, Sheet II.
(c) Install evaporators to 880728-5 and 880728 Tee’s I.A.W.
Dwg.880728, Sheet ~1, and Dwg.880730, Sheet P1, Zone
13-15 A/B. Utilize screws MS27039-1-08 and AN 9600
blOL washers.
CAUTION;
USE REPRTOgRANT OTL ONLY ON IITT~N(IS. DO NOT USE PILRAFTN
BRSE O~L OR OIIERSE´•
(d) Connect up freon hoses to rear pressure bulkhead Tee
fitting and evaporators I.A.w. Dwg .880732, Sheet 84.
(e) Connect up drain hoses I.A.W. Dwg.880718, Sheet 13,Zones 37, 38, ABC.
(f) Install Prop sync control box to side of R/H evaporatorI.A.W. Dwg.880730, Sheet P1, Zones 15, 16, 17b.
Relocate wires on adjacent ground block as required to
facilitate installation. (Model 690C only)
(g) Connect up evaporator fan wiring to connectors 1-
480305-0 (2 each) I.A.W. Dwg.800816, Sheet #4, Zone 4
A/B. Find wires AC9A16, GND1B (2 each) AC8A16, AC7A16,AC6A16. connect these wires to plugs 1-480303-0
which mate with connectors 1-480305-0 I.A.W. Dwg.800816, Sheet 84, Zone 4 A/B.
(h) Install wire AZA20 to cabin bus bar at rear pressure bulkhead
R/H side. Utilize any spare location. Install 1 amp fuse
provided. See Dwg.800816, Sheet 4, Zone 6D.
65. Models 690C S/N’s 11600-11718 and 695 S\N’S 95000 thru
95084 proceed as follows:
(a) Make cut outs in upholstery and mirror at rear pressurebulkhead I.A.W. Dwg.880730, Sheat i, Zones 6-9 F/G and
view B Zone 4, 5, 6, C, D, E.
(b) Install 880727-501 and -502 louvre boxes I.A.W.
Dwg.880730, Sheet bl, Zone 6-9 F/G and view B Zone
5/6C, D, E.
(c) Connect ducts X6687 between evaporators and louvre
boxes installed in step b/ I.A.W. Dwg.880730, Sheet B1,Zones 13, 14.
(d) Inspect L/H and R/H overhead cabin panels for air
system integrity. Repair or replace any damaged ducts
or air transition units prior to installation. Ensure
air system is leak free.
(e) Shorten existing l/h and r/h overhead cabin panel ducts
to mate with new louvre box outlets I.A.W. Dwg.880730,Sheet P1, Zones lo, 11, F/G.
66. (a) For Model 690C S/N’s 11719 thru 11735, make cut outs in
upholstery and mirror at rear pressure bulkhead I.A.W.
Dwg.880730, Sheet bl, zones 12-15 and view ’A’ Zones 7-
10 A, B 8 C.
(b) Install 880727-501 502 louvre boxes I.A.W.Dwg.880730,Sheet 81, Zone 12-15 FG view ’A’ Zone 7-10 ABC.
(c) Connect ducts X6687 between evaporators and louvre
boxes installed in step b/ I.A.w. Dwg.880730, Sheet #1,Zone 13 &14.
(d) Inspect L/H and R/H overhead cabin panels for air
supply system integrity. Repair or replace any damagedducts or transition units prior to installation.
Ensure air system is leak free.
(e) Shorten existing L/H and R/H overhead cabin panel ducts
to mate with new louvre box outlets I.A.W. Dwg.880730,sheet Il, Zones 10/11 F G.
67. Airplanes which install a single evaporator at the
rear pressure bulkhead proceed in accordance with
Dwg.880730, Sheet R1, Zone 11 12 for difference
from a evaporators at rear pressure bulkhead. In
addition, steps 66 or 67 as applicable by model and
serial number should be embodied.
BOTE;
DTFWRENCE FOI1 2 EVAPORATOR TNSTALLATToN AND SINGLE EVAPoRRToR
INSTRLLATION
68. Modify previously removed 860988 rear pressure bulkhead
lower equipment cover I.A.W. Dwg.880730, Sheet 82: Zone
30-32 A, B C. Retain cover far later installation.
69. Airplanes which are to install an evaporator inside the
sideways facing observer seat opposite the main cabin
door proceed as follows:
(a) Modify previously removed observer seat I.A.W
Dwg.880737 Sheet #1. Follow instructions for -501
installation.
(b) Install 880694-23 drain assy I.A.W. Dwg.880694engineering order S, Sheet II, for location and
Dwg.880694, Sheet Il, Zone 7A view B. Seal around
880694-63 drain hose at floor with coast pro-seal 890
or equivalent.
CAUTION:
Do NOT UBE PRRRPIN BASED GRERSE OR OIL ON PTTTINDS´•
USE ONT~Y RBP~RTDERENT OIL. BLANK OP~r FORWRRD FTTTINDS.
(c) Route freon hose assemblies from rear pressure bulkhead
tee connections forward along R/B side of fuselage to
sideways facing seat location I.A.W. Dwg.880700, Sheet
#9. Connect up hoses at rear pressure bulkhead Tees.
70. (a) Route electrical wire bundle from inside rear pressurebulkhead forward along R/H side of fuselage to cockpitinstrument panel. Tyrap wire bundle as required to
provide support. I.A.W. AC43-13-1A Refer to
bwg.8008l6, Sheet #3 for Models 690C S/N’s 11600 thru
11729 and 695 S\N’s 95000 thru 95084. Refer to
Dwg.800816, Sheet g2 for Model 690C S/N’s 11730 thru
11735.
(b) Identify from relevant sheat of Dwg.80o816 wires to be
connected to P27 connector which is for the
environmental control panel. Route wires in 1/2’flexguard behind instrument panel. Removal of the
radar indicator will assist with routing. Route wires
to circuit breaker panel connectors I.A.W. Dwg.800816relevant sheet.
(c) For Models 690C S/N’s 11600 thru 11729 and 695 S/N’s95000 thru 95084 proceed as follows:
Find wire H62A22 from pin 22 of connector P14 of
annunciator panel. Join new wire H62A22 to this
existing wire and connect other end of wire to
pin L of P27 environmental control panel connector
I.A.W. Dwg.800816, Sheet 63.
(d) Model 690C S/N’s 11730 thru 11735 find wire H62AZZ in
P170 Pin 12 of annunciator Master caution unit. Join
new wire H62AZZ to this existing wire and connect other
end of wire to pin L of P27 environmental control panelconnector I.A.W. Dwg.800816, Sheat #2.
71. Connect fwd cabin temp sensor connector PT06CE-8-45 to
wires from digital temperature computer pins 14 and 34
and ground wire I.R.W. DWg.800816, Sheet BZ or Sheet #3
as applicable by Medal and serial number. Connect wire
H39sii from circuit breaker connector to fwd cabin
temperature connector I.A.W. Dwg.800816, Sheet 62 or #3
as applicable by Model and serial number.
72. (a) Find wires AC9A16, AC8A16, AC7A16, AC6A16 previouslyconnected to evaporator fans at rear pressure bulkhead
route wires along R/H side of fuselage behind
instrument panel to freon system control panel on L/Hside of cockpit install wires into plug 1-48 0283-0 as
shown on Dwg.800816, Sheet g4, Zone 5, ABC.
(b) Find wire AC9B16 and install into plug 1-480283-0
I.A.W. Dwg.80o816, Sheet P4, Zone 5, 6 CD.
(c) Find wire AC4C16 and install into plug 1-48028)-0
I.A.W. Dwg.8o0816, Sheet 64, Zone 48.
(d) Connect all ground wires for control panel and
evaporators I.A.W. Dwg.800816, Sheet %4.
73. (a) Airplanes with dual split evaporator system install
wires AC7A16, AC6A16 from aft evaporator fwd to ACI
plug I.A.W. Dwg.800816, Sheet 14, Zone 4A.
(b) Find wires AC9A16, AC8A16 and install into ACI plugI.A.W. Dwg.800816, Sheet 64, zone 4A. Route wires
behind instrument panel, along R/H side of fuselage to
forward evaporator location. Connect wires to 1-
480303-0 plug.
(c) Carry out steps 73.b/ and c/ for control panel and
evaporators. Connect all GND wires for control paneland evaporators as on Dwg.800816, Sheat P4.
74. Install freon control panel to L/H cockpit sidewall
I.A.W. Dwg.880701, Sheet 61 view AA 507 or -511 as
applicable and shown on Dwg.880701, Sheets B1 and
12 and Dwg.880718, Sheet 53, Zone 39, 40 GH when 3rd
evaporator is installed.
75. Install all upholstery previously removed from cabin area.
76. (a) Install drain assembly I.A.W. Dwg.88od9, Sheet B1 and
E.O. ADV’S’.
(b) Install co-pilots seat before installing bar assembly.
(c) Airplanes which are to install a fwd evaporator inthe R/H bar behind co-pilots seat proceed as follows:
Modify bar assembly I.A.W. Dwg.880698, Sheet ~6.
Install evaporator unit inside bar I.A.W. Dwg.880698,Sheet #6.
CnvTloru:
Do NO~ USE PlU(RPIN BRSeD OIL OR (IRERSe ON FITTTN(ls~ USE
ReFRT(IERRNT OTL ONLY.
(d) Install bar assembly in aircraft and connect upelectrical connector and freon hoses I.A.W. Dwg.800816,Sheet #4 or P6 as applicable and Dwg.880732, Sheet 86
515 installation. Connect up drain assy I.A.w.
Dwg.88 0694, Sheet bl.
77. Airplanes with forward evaporator inside sidewaysfacing lavatory seat proceed as follows:
CAUTION:
Do NOT USE PRRAPIN BRSeD ~RERSe OR OIL ON FITTINDSI USE
REFRToERANT OIT´• ONLY.
(a) Install lav seat assembly in A/P. Connect up
electrical connector and freon hoses I.A.W. Dwg.800816,Sheet #4 or #6 as applicable and Dw9.880732, Sheet P6
511 installation. Connect up drain assembly I.n.W.
Dwg.880694 Engineering order ADV’S’.
78. Install previously modified environmental control paneleither beneath pilots instrument panel or in center
console as applicable. Connect up electrical connector
P27.
79. Model 690C 11600 thru 11729 and 695 95000 thru 95084 proceedas follows:
(a) Install circuit breaker panel beneath cc-pilotsinstrument panel and connect up all electrical
connectors.
(b) Model 690C 11730 thru 11735 proceed as follows:
Install both L/H and R/H circuit breaker panels and
connect up all electrical connectors.
80. Re-install radar indicator if previously removed for
access.
81. Modify baggage compartment structure and ski storagearea I.A.W. Dwg.880718, Sheet #4, Zones 41 thru 49. If
A/P does not have ski-storage area modify only as
directed. Refit baggage compartment floor and carpetall sides and overhead trim.
(a) Install head liner assemblies L/H and R/H. Connect upto ducts at rear of headliner.
82. Install aircraft batteries and function test all
electrical systems. Correct any discrepancies.
83. Install ground power and function test. Correct any
discrepancies.
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auraessoa ~mn
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NOTE:
PERFoRM STEPS 85 ~ZND 86 CONCURRENTLY
84. Charging Freon Air Conditioning System. (Refer to
Figure 6). The following tools and/or equipment are
required to charge the refrigerant system:
1. small hand tools and socket set.
2. Vacuum pump (0 to 30 In. Hg.)3. R-12 refrigerant (1 Lb cans)4. Charging manifold assembly with gauges and hose.
(Robin air P/N 40153 or equivalent).5. Thermometer (O to 1500F)6. Ground Power Unit.
7. Adjustable inspection mirror.
8. Service light or flashlight.
To charge the freon air conditioning system, proceed as follows:
(a) Verify that airplane and/or external power is OFF.
(b) Remove aft panel from baggage compartment.
NOTE:
WHEN CONNECTING CHARGING MANIFOLD TO COMPRESSOR, THE RED(HIGHPRESSURE) HOSE MUST BE CONNECTED 20 THE PORT MARKED ’D’
(DTSCHARCE) AND THE BLUE (LOW PRESSURE) HOSE MUST BE CONNECTED
TO THE PORT MARKED ’S’ (SUCTION). TO CONNECT OTHERWTSE MAY
RESULT IN DAMROE TO THE LOW SIDE PRESSURE GAUGE.
(c) Connect charging manifold to compressor service ports.
(d) Connect manifold inlet service hose to suction side of
vacuum pump.
(e) Turn pump on, open manifold service valves and evacuate
system for 30 minutes. System should read 25-27 In.
Hg. after 10 minutes.
(f) Close manifold service valves and shutoff vacuum pump.Remove manifold service hose from vacuum pump and
connect to R-12 refrigerant can.
(g) open refrigerant can valve and crack hose fitting at
manifold to purge hose. Open both manifold valves and
charge system with refrigerant until internal system
pressure reaches 10-15 psig. Close manifold gauge
valves and refrigerant valve.
CAUTION:
8YSTEM MUST BE VENTED SLOWLY TO ASSURE THAT TIIE REIRIOE~ANT
OIL TS NOT VENTED OVERBORRD´• EYE AND HAND PROTECTION ~U8a
BE WORN DURING THIS PROCEDURE.
(h) Remove R-12 can from service hose and slowly open both
manifold valves and slowly vent system to zero.
(i) Close manifold valves and reconnect service hose to
vacuum pump.
(j) Start pump and open manifold valves. Run vacuum systemfor a minimum of 45 minutes. System vacuum should read
25 to 27 In. Hg. after 10 minutes operation.
(k) Close manifold valves and shut off vacuum pump. Remove
service hose and connect to a one (l) pound refrigerantcan.
(1) Observe vacuum gauge for 5 minutes to assure no leaks
or no excessive moisture is in system.
NOZ~E:
If loss of vacuum is noted, a system leak check or
re-evacuation will be required. If the systempassed the leak check, the only reason for vacuum
change would be excessive moisture in the system.Repeat steps a/ thru 1/.
(m) If there is no change in vacuum, connect the manifoldservice hose to a one (1) pound refrigerant can and
open the valve.
(n) Crack service hose fitting to purge air out of hose,turn can to position with outlet pointed to the groundand open both manifold valves. Allow liquid contents
of can to enter system and repeat this step until two
(2) cans of refrigerant have been consumed or systempressure is stabilized.
NOTE
IT TS IMPORTANT AT THIS POINT TO KNOW THE EXACT PIIANT~TY OF REFRIGERANT
FOR EACH AIRPLANE SYSTEM TO ASSURE THAT AN "OVE8 CHARGE" CONDTTION GOES
NOT OCCUR OR THE SYSTEM SHOULO BE CHARGED ON R HOT OAY (90-1050F) TO
ASSURE a PROPER PVANTTTY WITHOUT OVER CHAI(OT~NG.
(O) Close manifold valves and verify system pressure is
greater than 50 psig. Record, at this time, the number
of one (1) pound cans of refrigerant consumed.
(p) verify that system electrical controls are in the OFF
position. Connect a ground power unit capable of 28
V.D.C. and 200 Amp capacity to airplane electrical
system.
(q) Turn GPU power ON, place evaporator blower speed to
high and turn system power ON.
(r) With system operating, observe the suction and
discharge pressures and refrigerant condition in
receiver-dryer sight glass. Excessive bubbles
indicate low refrigerant level.
(s) With new refrigerant can connected to the manifold
service hose, slowly open the suction (blue) manifold
valve and allow refrigerant to enter system through
compressor
NOTE:
AS REFRIGERANT ENTERS COMPRESSOR, TRE SUCTION PRESSURE WILL
TNCREI\SE AND A SLIGHT INCREASE IN DISCHARGE WILL BE NOTED.
COMPRESSOR SPEED WILL BE REDUCED SLIGHTLY ALSO.
(t] Continue to add one (1) pound cans of R-12 refrigerantper above procedures until the required system chargeis loaded or until the receiver-dryer sight glass is
clear of excessive bubbles.
(u) Let the system operate for 5 to 10 minutes and observe
sight glass. If excessive bubbles appear, add a slightquantity of refrigerant until clear. Close suction side
manifold hose (blue) and close refrigerant can valve.
HAND RND EYE PROTECTION SHOULD Be WORN DURING Tars
OPERATION DUE TO HI(IH PRESSURE REFRIGERANT vENTTNG RT
veRY COLD TEMPERRTURBS´• BLIN RNm EYEB MUST BE
(v) Slowly vent service hose from can and remove from can.
(w) Allow system to operate for a minimum of is minutes
and observe compressor suction and discharge pressures.
Typical values at various ambient temperatures are
shown below:
SUCTION DISCHARGE
O.A.T. PRESSURE (PSIG) PRESSURE (PSIGI
Selow 800F 29 140-150
800F z8 (c/-2) 195 (c/-10)
900F 32 215
l00OF 34 230
(x) Check evaporator air inlet and outlet temperatures to
determine proper refrigerant distribution. The
evaporators must be balanced to obtain equalperformance. To balance the evaporators, refer to
balancing procedures as outlined in Step 88.
(y) cover both compressor service valves with shop rag and
quickly remove both suction and discharge hoses.
Disconnect charging manifold from compressor.
(z) Disconnect GPU from airplane.
NOTE:
IF NECESSARY PERFORM LEAK CHECK I.A.W. STEP 87.
85. Balancing Evaporator Module. The following equipmentwill he required to balance evaporator modules:
Ground power unit capable of 28 VDC and 200 Ampcapacity.
2. Service manifold with gauges and hoses.
3. Thermometer O to 1500 F.
To balance evaporator modules, proceed as follows:
(a) Connect a ground power unit capable of 28 VDC and 200
Amp capacity.
(b) Verify that system leak check and refrigerant charginghas been performed and system is operating within
typical values as outlined in System Chargingprocedures in this chapter.
(c) Remove all covers from evaporator modules. Each
evaporator module expansion valve must be accessiblefor this operation.
(d) Remove evaporator module blower outlet ducting and
expansion valve protective cap.
(e) Verify that evaporator coil inlet is free of
contamination or debris which could reduce air flow.
(f) verify blower speed switch is in "high" position.
(g) Verify service manifold gauges and hoses are connected
to compressor-condensor module and system is operatingnormally.
(h) Place air conditioner switch to AIR COND. Verify Ac
light illuminates.
(i) Close cabin door and measure each evaporator blower
outlet temperature and air inlet temperature. Normal
air temperature difference is 25 5) degrees F.
NOTE:
NORMALLY THE EVAPORATOR MODULES CLOSEST TO THE COIIPRESSOR-
CONDENSOR MODULE WILL INOTcRTE A LOWER BLOWER OUTLET TEMPERATURE
THAN OTHER MODULES. ALSO IF AN EVAPORATOR MODULE HI\S A LOWER
BLOWER OUTLET ATR FLOW, THE ATR TEMPERATURE WILL ALSO BE LOWER
THAN A HOO(ILE WTTH HIGH ATR FLOW. THEREFORE, EVERY EFFORT
SHOULD BE MADE TO OBTAIN EPUAL RIR FLOW FOR ALL EVAPORATORS.
(j) After all evaporator module outlet air temperatures are
recorded, the data must be reviewed to determine which
evaporator module expansion valve should be adjusted.
NcTE:
The variance of blower outlet temperature between
evaporator modules can be 20F with out any
adjustment required. However, 100F
difference will require some adjustment.
(k) To lower the outlet air temperature, the expansionvalve adjustment control must be turned clockwise. The
adjustment should be turned slowly and only 1/4 turn.
(1) Note outlet air temperature again and verify that the
compressor suction pressure stays within the limits of
26-34 psig during adjustment. If not, the unit with a
low outlet temperature must have its expansion valve
turned 1/4 turn counterclockwise to offset the increasein suction pressure and at the same time have the same
outlet air temperature as the other unit.
(m) The adjustment procedure is complete when all
evaporators have approximately the same outlet
temperature ZoF) and the compressor suction
pressure is well within desired limits.
(n) Operate system to stabilization or 10 minutes, then
shut systems off.
to) Connect evaporator blower outlet ducting.
(p) Install protective caps on evaporator expansion valves.
(q) Install covers on evaporator modules.
CAUTION:
IPREN PBNORMTNO TEE FOLLOWING STEPI RAND RND EYE PROmECTTON
SBOULD BE WORN DUE TO BTOB PRESSURE REFRIGERANT VENT AT VERY
COLD ~EMPERATURES´• BKIN RND EYES MIST BE PROTECTED.
(r) Cover both compressor service valves with clean shoprag and quickly remove both suction and discharge hoses
from compressor service valves.
(s) Remove all test equipment and disconnect ground powerunit.
86. Leak Check Freon Air Conditioning system (Refer to
Figure 6). The following tools and/or equipment will
he required to leak check the refrigerant plumbing:
1. Gaseous dry nitrogen-regulated source.
2. Charging manifold with gauges and hose. (Robin air
P/N 40153 or equivalent)3. Halogen leak detector (TIF5000 or equivalent)4. Refrigerant R-12 (1 Lb cans)5. Small hand tools and socket sat.
6. R-12 can service valve.
7. Leak check fluid (soapy-water).
TO leak check the refrigerant plumbing, proceed as follows:
(a) Verify that all plumbing connections are tight andelectrical power is OrF.
CAUTION:
WEEN CONNECPCTNOrHe CRRROlNC DYWIIIOLDI TEE RED (RIDBPRESSURE) 8088 MUST Be CONNECTED mo rHE PORT MARRED "o"
(DISCBRROe) RND THE BLUE (LOW PRESSURE) BOSE MUST BE
CONNECTED To TaE PORT MARRED 1’8" (SUCT~ON)´• ~O CONNECT
oTHERWISE MAY RESULT IN DRMRBE TO TEE LOW SIDE PRESSURE OAUOE.
(b) Connect charging manifold to R-12 compressor service
ports and charge inlet hose to refrigerant can servicevalve and bleed refrigerant into system until pressureis stabilized.
(c) close manifold and R-12 service valves.
(d) Remove R-12 can and connect service hose to regulatednitrogen source.
CAUTION:
Do NOT OYER CBRR(IE SYSTEM OR DAMAOe MAY ReSUL~´• RE(I1IWITE:
NTTROGEN INTO SYSTEM SLOWLY´•
(e) Open manifold valves and regulate nitrogen into systemto 250-255 psig.
(f) Apply soapy leak check fluid to all refrigerantplumbing connections and observe for major leaks.
CAUTION’
DO NOT OYER TT(IRTEN PLUMBING CONNECTIONS. STRIPPED 2´•BREADS
OR CRACKED FLARES MAY Re8ULT´•
(g) Wipe off soapy liquid and use halogen leak detector tofind small R-12 leaks. Tighten joints as required.
CAUTION:
SYSTEM MUST BE VEhPEED SLOWLY TO ASSURE TBRT COMPRESSOR OIL IJ
NOT VENTED OVERBOARD WIT8 ReFR~OERRNT´• DO NOT WOW RIR TO
ENTER SYSTEM´•
(h) with system leak tight, vent system slowly to remove
all nitrogen and/or refrigerant. Shut nitrogen systemoff.
(i) Disconnect service hose to nitrogen and reconnect to R-12 can and pressurize system until pressure is stable.
(j) close manifold valves and remove R-12 can. Slowly openboth manifold valves and vent system to 2-5 psig.
87. Perform after installation check out using groundpressurization cart if available. Cabin must reach max
differential in normal flow if it fails to do so
repair cabin leaks as required.
(a) Connect pressurization cart to aft connection of heat
exchanger so that air flow is routed forward thru flow
sensor.
(b) Connect an external air pressure source regulated to
18PSI 1PSI to the inlet side of the cross
containing the over pressure switch located behind the
R/H side baggage compartment trim. In order that the
door seal may be inflated.
(c) Using the enviro system test box connect a VOM to pinsC(+ve) and D(-VE) of the mass flow sensor.
(d) Connect an auxilary power unit to the A/P external
power receptacle 28.5 (c/-.5) VDC.
(e) Remove the static line from the cabin pressurecontroller and cap the static port on the controller.
Attach an H20 meter to the static line. Sat rate
selector knob on cabin pressure controller to full
clockwise position.
(f) Set start mode select switch to CPU/PAR position(battery switch also turned on if required).
(g) Verify that the flow cent. circuit breaker is IN.
87. (h) Close and secure cabin door.
WARNING i
IT IS IMPRACTICAL TO SECURE THE PAEIIENBERICREI DOORBO
THAT TT CANNOT BE OPENED P~ROM THE OUTSIDE. IT I8
RECOMMENDED THAT WHILE PER1"ORMINO O~OUND PRESBURIZATION
CHESKB THAT BAFEOIIRRDB BE TAREN TO PREVENT SOMEONE BROM
OPENIND THE MAIN CABIN DOOR. OPENIN(I DOOR WITH CABIN
PREQS[I~IBED, TO ANY DECREE. WILL CAUSE CONSIDERABLE
BODILY HARM AND DESTRUCTION TO EOUIPMENT. PLACE SICiN8
AROUND THE AIRPLANE. PUT TAPE ACROSS DOOR HANDLE.
HANDLE IN CLOSED POSITION. HAVE PRESSURIZATION
CONTROL PERSONNEL INSIDE THE AIRPLANE AND ENSURE THAT
DOOR LOCKIUNLOCK SWITCH, LOCATED ON OVERHEAD SWITCH
PANEL. IS DEPRESSED TO THE DOOR LOCK POSITION.
WARNING
DO NOT EXCEED MAXIMUM ALLOWABLE DIFFERENTIAL PRESSURE
OF 5.4 P91D OTHERWISE STRUCTURAL DAMAGE AND POSSIBLE
INJURY TO PERSONNEL COULD OCCUR.
PRESSURIBATION SYSTEM CANNOT BE CONTROLLED
ELECTRICALLY WREN CABIN DEPRESS CIRCUIT BREAKER 18
TRIPPED. PUSAINO CIRCUIT BREAKER IN WILL CAUSE RAPID
DECOMPRESSION, IPHICR MAY CAUSE INJURY TO PERSONNEL.
DO NOT OPEN MAIN CABIN DOOR WXILE AIRPLANE 18
PRES8URTgED. SERIOUS INJURY TO PERSONNEL AND DAMAGE
TO EOUIPMENT CAN OCCUR.
(i) Trip cabin depress circuit breaker
CAUTION;
Do NOT EXC&ED 2000 PT PER MINUTE CRBIN RATE OF DESCENT
OR DAMADE CAN OCCUR TO PRESSURIZATION CONTROWIER´•
Wtre~ CABIN PRESSURE BAS SICRBILTZPD RECORD: FLOW MITER
RERDINO ON PRESSURIZATION CART SCFM (SPECTFIC CUBTC
FEET PER MTMPPE)´•
(j) Slowly increase the pressure on pressurization cart
until flow sensor voltage reads 4.15 VDC (low flow)
Flow Sensor VDC
Cabin pressure H20 meter psid
NOTE:
H20 METER REAOINO DIVIOED BY 27.8 EPUAiS CABTN
PRESSURE IN PSID.
(k) Adjust air flow until flow sensor voltage reads 4.71
VDC (max flow). When cabin pressure has stabilizedrecord:
Flow meter SCFM
Flow sensor VDC
Cabin Pressure_
(HZO meter) PSID
Do NO~ EXCEED 2000 FT PER MIN OR DAMAGE CAN OCCUR TO
PRESSURIZATION CONTROLLER.
(1) Slowly decrease the pressure on the pressurizationcart and depressurize the A/c.
(m) When the cabin altitude is close to field elevation
and no further rate of climb is noted reset the cabin
depress circuit breaker. Verify that the vacuum pump
operates, dumping any remaining cabin pressure.
(n) Open cabin door.
(O) Switch off ground power and internal batteries.
(p) If it was not possible to obtain maximum cabin
differential in low flow repair cabin leaks.
(q) Reconnect static line to cabin pressure controller.
(r) Remove all test equipment attached to the A/C for this
test and set cabin pressure controls back to normal.
(s) If a ground pressurization test cart is not available
proceed I.A.W. Step 91.
88. Post installation pressurization test with enginesrunning.
NOTE:
STEPS 91 AND 92 IIAY BE CONOIICTED CONCURRENTLY. ENSURE LOWER
MODI~FIED AVToNIc DOORS RRE REFTTTED PRTOR TO TEST.
CAUTION:
ENSURE PHAT NEEDLE VALVE IS IN FULL OPEN POBITION.
IF NEEDLE VALVE I8 CLOSED AND TEE PREssURISATION
8Y8TEM Is ACTIVATED PRESSURIBA’PION NILL START
IMMEDIATELY AT API DhlKNOWN RATE.
(a) Disconnect the static air line at the cabin pressurecontroller and install a needle valve and a short
piece of hose in series with the static air line and
reconnect to the controller. See Dwg.880736, Sheet 9,Figure II.
(b) Using the enviro system test BOX connect a VOM to pinsC (cVE) and D (-VE) of the mass flow sensor.
(c) Close and secure cabin door.
(d) Start both engines using normal procedures in Pilots
operating Handbook.
(e) set RPM on both anginas to 85% RPM.
(f) Disconnect ground power unit if utilized.
(g) Switch on both generators and cabin bus switch.
WRNINO
PRESSURIZATION SYSTEM CANNOT BE CONTROLLED
ELECTRICALLY WHEN CABIN DEPRESS CIRCUIT BREAKER IS
TRIPPED. POSHINO CIRCUIT BREAKER IN WILL CAUSE
RAPID DECOMPRESBION. WHICB MAY CAUSE INJURY TO
PERSONNEL. DO NOT OPEN MAIN CABIN DOOR WHILE
AIRPLANE IS PRESSDRSBED. BERIOUS INJURY TO
PERSONNEL RND DAMAGE TO EOUIPMENT CAN OCCUR.
ENSURE THAT NEEDLE VALVE IS IN FULL OPEN POSTION.
IF NEEDLE VALVE I8 CLOSED AND TAE PRE8LiURI4ATION
SYSTEM IS ACTIVATED. PRE88URIaA’EION NILL
IMMEDIATELY AT AN UNKNOWN RATE.
(h) Trip cabin depress circuit breaker.
(i) Set cabin pressure rate knob fully clockwise and
altitude select knob fully counterclockwise.
(j) Set bleed air switch to both oPEN and environmental
master switch to DN.
(k) Set mass flow switch to LOW.
CAOTION:
DO NOT EXCEED 2000 FT PER MIN OR DAMAGE CAN OCCUR TO
PRE88m(IZA~ION CONTROLLER
(I) Close needle valve slowly until cabin is pressurizingat a comfortable rate.
(m) Pressurize cabin to max differential and record cabin
PSID Flow sensor VDC.
(n) select mars flow control to max verify max flow
annunciator illuminates on annunciator panel.
to) when cabin has stabilized record:
Cabin --PSID
Flow Sensor VDC
(p) Select mass flow control switch to normal
CAUTION:
DO NOT EXCEED 2000 FT FEB MIN MAXIMUM OR DAMADE CAN
OCCUR 90 PI1E98rmT4ATION CONTROLLER
(q) Open needle valve slowly and depressurize cabin (2000ft per min maximum).
(r) When cabin altitude is close to field elevation reset
cabin depress circuit breaker. Verify that vacuum
pump operates, dumping residual cabin pressure.
(5) Shut down engines utilizing normal procedure in Pilots
operating Handbook.
(t) If it was not possible to reach maximum differential
with normal flow selected, then repair any cabin
leaks. Repeat test
(u) Remove the needle valve and reconnect the static line
to the controller.
(v) Set cabin pressure rate knob and altitude selector
back to normal.
(w) Remove Enviro test box from system.
91. Post installation test with engines running.
(a) Close and secure the cabin door.
(b) Start both engines using normal starting procedures.
(c) Set RPM on both engines at 65 to 70 percent.
(d) Disconnect auxiliary power unit.
(e) Turn on bath generators, cabin bus switch, and air
conditioner switch.
i. verify that air conditioning system is operating.
(f) Turn right generator switch OFF.
I. Verify that air conditioner compressor stopsoperating.
(g) Turn right generator switch ON.
1. Verify that air conditioner compressor starts to
operate again.
(h) Turn left generator switch OFF.
I. Verify that air conditioner compressor stopsoperating.
(i) Turn left generator switch ON.
I. Verify that air conditioner compressor starts to
operate again.
(j) Monitor pilots left and right amp meters with the air
conditioner switch off and with the air conditioner
switch on.
The combination current increase on both amp
meters should be approximately 80 amps or more,
but no more than 1~5 amps.
(k) Set bleed air switch to BOTH CLOSE and select
environmental master switch to ENVIR MASTER (OFF).
i. verify that there is no air flow at floor
outlets.
(I) Set bleed air switch to BOTH OPEN.
i. verify that there is still no air flow into
cabin.
(m) Sat bleed air switch to BOTH CLOSE.
(n) Set Mass Flow Control switch to LOW.
to) Set Temperature Control to full counterclockwise
position.
(p) select environmental master switch to ON.
(q) Set bleed air switch to RIGHT CLOSE.
i. Verify that there is air flow at floor outlets.
(r) Set bleed air switch to LEFT CLOSE.
i. verify that there is air flaw at floor outlets.
(s) Set bleed air switch to BOTH OPEN.
i. verify that there is air flow at floor outlets.
(t) Set mass flow control to MAX position.
i. verify that there is an increase in air flow at
the floor outlets.
2. Verify that MAX FLOW annunciator is illuminated.
fu) Set mass flow control to LOW.
i. Verify that there is a decrease in air flow at
the floor outlets.
2. Verify that MAX FLOW annunciator is extinguished.
(v) Rotate temperature control full clockwise.
i. Verify that temperature at floor outlets increases.
(w) Rotate temperature control to full counterclockwise
position.
i. verify that temperature at floor outlets decreases.
(x) Place temperature control in MANUAL position and press
INCR and hold for 10 seconds.
I. Verify that temperature at floor outlets increases.
(y) Press DECR and hold for 10 seconds.
1. verify that temperature at floor outlets decreases.
90. Install enviro test box between temperature and flow
computer connectors. Connect ground power to the A/Cand select ground power and A/C batteries ON. Place
switch to test position. Operate toggle switch to
bypass and to exchange and verify that temp modulatingY valve operates. Operate flow toggle switch to openand close and verify that mass flow valve runs from
full open to full close and vice-versa.
If system does not operate correctly see trouble
shooting section for corrective adtions.
(a) Disconnect squat switch mechanically and ensure squatswitch controls ram air blower. If blower fails to
shut down when squat switch is extended inspect TA4 in
baggage compartment and install S3A2 diodes between
terminals and terminal stud with exception of wire to
squat switch itself and re-check.
91. Trouble shooting guide.
EOUIPMENT REOUIRED
1. DIGITAL VOLT/OHM METER
2. SYSTEM BREAK OUT TEST BOX (800816-TEST BOX)3. OSCILLOSCOPE (ANY BRAND)4. AIRPLANE ELECTRICAL WIRING DIAGRAM OR DRAWING
800816
5. DIGITAL TEMP METER OR EQUIVALENT TROUBLE SHOOTING
STEP REFERENCE
a. NO FLOW/PRESSURIZATION IN CABIN. SEE STEP 1 AND 2.
b. EXCESSIVE FLOW OR HEAT IN CABIN. SEE STEP 2.
c. NO TEMP CONTROL IN AUTO MODE. SEE STEP 3.
d. NO TEMP CONTROL IN MANUAL MODE. SEE STEP 4.
FLOW CONTROL SYSTEM
1. NO FLOW TO CABIN/NO PRESSURIZATTON.
a. VERIFY ENGINE BLEED AIR VALVES ARE OPEN (BLEEDAIR SWITCH IS IN "BOTH OPEN" POSITION). [REF.FIGURE 7]
b. VERIFY ENVIRO MASTER SWITCH IS IN "NORM" POSTION.
[REF. FIGURE 8]
c. VERIFY DUCTS AND HOSES TN AFT SECTION OF AIRCRAFT
ARE CONNECTED AND SECURE.
d. CHECK ENVIRONMENTAL DIGITAL FLOW CONTROL SYSTEM
[REF. FIGURE 9]1. WITH POWER ON IN THE ACFT (BATTERY SWITCH ON.
FLOW CONTROL CIRCUIT BREAKER PUSHED IN).2. VERIFY THE MASS FLOW VALVE ACTUATOR IS FULL OPEN.
[REF. FIGURE 7A]. THE ACTUATOR DRIVE ARM SHOULD BE
EXTENDED APPROXIMATELY THREE FOURTHS (S/4")INCHESOUT OF THE GEAR DRIVE HOUSING.
2. EXCESSIVE FLOW OR HEAT IN CABIN
a. VERIFY MASS FLOW CONT. SWITCH IS IN "LOW" POSITION.
b. CONNECT 800816-TEST BOX HARNESS TO DIGITAL FLOW
COMPUTER (TCAC SC-100025 HARNESS OR EQUIVALENT).
c. TURN POWER ON (EXTERNAL POWER CART) BATTERY SWITCH.
d. VERIFY 28 VDC AT PINS 9 AND 27 OF DIGITAL FLOW
COMPUTER. (USE PINS 8 OR 13 FOR NEG.)
e. VERIFY 15 .5 VDC AT PINS 31 AND 24 IF
NOT 15 VDC SUSPECT FLOW SENSOR IS LOADING POWER OUT
PUT REPLACE FLOW SENSOR.
i. COVER AMBIENT AIR INPUT PORT (R/H SIDE OF AIRCRAFT).[REF. FIGURE 5] MEASURE VOLTAGE AT PINS 5(1) AND 7(-)VERIFY 0.0 .05 VDC SHOULD BE STABLE IF NOT
STABLE AND DRIFTS h IN EXCESS OF 0.100 VDC
REPLACE FLOW SENSOR. REMOVE COVER FROM AMBIENT AIR
INPUT PORT.
g. WITH SHOP AIR PRESSURIZATION MACHINE, REMOVE HOSE
CLAMP FROM JUNCTION AT HEAT EXCHANGER [SEE FIGURE 5]CONNECT PRESSURE MACHINE.
SHOP AIR PRESSURIZATION MACHINE
(H1 AND H-2)DURING THIS TEST CABIN PRESSURIZATION CAN BE CHECKED. SEE
MAINTENANCE MANUAL.
H-l VERIFY/SET MASS FLOW SWITCH TO LOW WITH SHOP
PRESSURIZATION MACHINE SET AIR FLOW UNTIL YOU GET A
VOLTAGE READING OF 4.16 c/- .07 VDC AT PINS 5(c) AND
7(-) ON DIGITAL FLOW COMPUTER. MONITOR THIS VOLTAGE
FOR SEVERAL MINUTES TO VERIFY IT DOES NOT DRIFT. (IFTHE VOLTAGE DRIFTS, THE FLOW SENSOR SHOULD BE
REPLACED)
H-2 SET MASS FLOW SWITCH TO MAX INCREASE AIP\ ON
PRESSURIZAT1ON MACHINE FOR A VOLTAGE READING OF 4.71
c/- .07 VDC. VERIFY VOLTAGE DOES NOT DRIFT.
ji)
1. CDH flNOI t r I(N O POYE~ clle-.
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FIGIIRE 7
E. CONrlFIVlrY ANCIPOWEA CNECIC~
(SEE DW6.800816)
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a L (Cc~x.
r;iq conT:
(P P6 I
mhs~ FLOW URLY~
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a
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I__jO
FTGWE 9
USING AIRCRAFT ENGINES
(H-3 AND H-4)DURING THIS TEST CABIN pRESSURIZATION CAN BE CHECKED. SEE
MAINTENANCE MANUAL.
H-3 WITH THE ENGINES RUNNING AND WITH BLEED AIR VALVES
OPEN, YOU SHOULD SEE 4.16 .07 VDC AT PINS 5(~) AND
VERIFY THE VOLTAGE DOES NOT DRIFT (IF SO,
REPLACE FLOW SENSOR).
H-4 SET MASS FLOW SWITCH TO MAX. VOLTAGE AT PINS S(t)AND
7(-)SHOULD READ 4.71+/- .07 VDC. VERIFY TT DOES NOT
DRIFT.
NOTE A:
DURING STEPS H-l AND H-2 OR H-3 AND H-4, WATCH THE
FLOW CONTROL VALVE [FIGURE 7.A]. VERIFY THE FLOW-
CONTROL VALVE IS PULL OPEN BEFORE THE AIR FLOW STARTS,
THEN STARTS MOVING TOWARD THE CLOSED POSTION AS THE
VOLITAGE AT PINS 5( AND 7(-) NEARS 4.16 VDC.
NOTE B:
IF THE FLOW CONTROL ACTUATOR ARM DOES NOT MOVE DURING
TEST, CONNECT OSCILLOSCOPE TO PIN 22 (WHEN VALVE
SHOULD BE CLOSING) BLEED AIR RUNNING, OR PIN 23 (WHENVALVE SHOULD BE OPENING) BLEED AJR OFF AND VERIFY 0 TO
28V PULSES. IF NO PULSES SUSPECT DIG. FLOW
COMPUTER.
FLOW CONTROL VALVE MANUAL TEST
DURING THIS TEST LISTEN FOR ROUGH GEAR SOUNDS, BINDING OR
GRINDING. SHOULD BE SMOOTH RUNNING SOUND
NOTE C:
TO MANUALLY CHECK FLOW CONTROL VALVE FOR PROPER OPERATION
(USING 800816-TEST BOX) SET FLOW ROTARY SWITCH TO "TEST"
DEPRESS FLOW TOGGLE SWITCH TO "CLOSE". THE FLOW CONTROL
ACTUATOR ARM SHOULD RUN TOWARD THE CLOSED POSITION
DEPRESS THE FLOW TOGGLE SWITCH TO "OPEN# AND THE FLOW
CONTROL ACTUATOR ARM SHOULD RUN TOWARD THE OPEN POSITION.
(IF NOT, FLOW VALVE TS DEFECTIVE.) SET FLOW ROTARY SWITCH
BACX TO "NORM".
CABIN TEMP CONTROL AUTO MODE. IN THE AUTO MODE THE SYSTEM
WILL TRY TO MAINTAIN A CABIN TEMP OF BETWEEN 540 tO 86", DEPENDS
ON AUTO TEMP. POT SETTING. IF IN REAL COLD CLIMATE AND MORE
HEAT IS REQUIRED SUGGEST USING MANUAL MODE AND SET TO DESIRED
LEVEL. (S~E POH OPERATING PROCEDURES.)
3. NO TEMPERATURE CONTROL
CONNECT TEST HARNESS TO DIGITAL TEMP. COMPUTER. (REFFIGURE 10.)
a. VERIFY SET TEMP. CONTROL SWITCH TO AUTO, SET TEMP
SELECT POT FULL CLOCKWISE.
b. CHECK CABIN TEMP. SENSOR, VERIFY FAN IS TURNING.
c. CHECK VOLTAGE AT PINS A PIN B ON CABIN TEMP SENSOR
AND DUCT TEM SENSOR. GET AMBIENT TEMP. AT EACH SENSOR
REFER TO TABLE r FOR VOLTAGE READINGS FOR THE CABIN
AND DUCT TEMP SENSORS.
d. CHECK VOLTAGE BETWEEN PINS 31 AND as SHOULD BE
5.0 .5 VDC. CHECK VOLTAGE BETWEEN PINS 31(-) AND
5(~), MOVE AUTO-TEMP CONTROL POT CW AND CCW VERIFY VOLTAGE
AT PIN 5 GOES FROM 5.0 VDC TO 0 VDC.
e. CONNECT OSCILLOSCOPE TO PIN 23 (IF AMBIENT TEMPERATURE
IS 70oF OR BELOW) SET AUTO-TEMP CONTROL POT TO FULL CW
POSITION. SET AUTO-MANUAL SWITCH TO MANUAL, DEPRESS I~NCR-
DECR SWITCH TO DECR AND HOLD FOR APPROX 10 SECONDS.
NOTE:
SET AUTO-MANUAL SWITCH TO AUTO. MONITOR
OSCILLOSCOPE FOR 0 TO 28V PULSES (SLOW PULSING) AND
LISTEN TO TEMP MOD. VALVE TO HEAR IF IT IS SLOWLY
BEING DRIVEN (TOWARD BY-PASS POSITION).
NOTE:
WHILE IN MANUAL MODE YOU CAN VERIFY TEE TEMP.
MOD.VALVE IS OPERATING BY LISTENING TO IT RZTN (INCRAND DECR).
f. CONNECT OSCILLOSCOPE TO PIN 22 IF AMBIENT TEMP. IS 700FOR ABOVE. SET AUTO-TEMP CONTROL POT TO FULL CCW
POSITION. SET AUTO-MANUAL SWITCH TO MANUAL, DEPRESS
INCR-DECR SWITCH TO INCR AND HOLD FOR APPROX 10
SECONDS.
NOTE:
SET AUTO-MANUAL SWITCH TO AUTO. MONITOR OSCILLOSCOPE
FOR O TO 28 V PULSES (SLOW PULSING) AND LISTEN TO THE
TEMP MOD VALVE TO HEAR IF IT IS BEING DRIVEN (TOWARDTEE HEAR EXCHANGER POSITION).
61
)rr´•1
n*p ne o*r
´•e ´•i´• iiP
wx 2\ ]-V P B
r
a´• ;1I I rt
us JI 711L111L. 22 5 S’1 C 2 25
D1S. rmP TmMP
O"12 22 le I Z 21 tZ 1I´•1?
3t
DYCT
DC r, B
TEC\P kD.
YII~UF
FIGURE 10
61
TEMP. SENSOR DATA
TABLE I
AMBIENT VOLTAGE AMBIENT VOLTAGE
TEMPERATURE VDC TEMPERATURE VDC
DEG. F DEG. F
30 2.719 70 2.941
31 2.724 71 2.947
32 2.730 72 2.952
33 2.736 73 2.958
34 2.741 74 2.964
35 2.747 75 2.969
36 2.752 76 2.975
37 2.758 77 2.980
38 2.763 78 2.986
39 2.769 79 2.991
40 2.774 80 2.997
41 2.780 81 3.002
42 2.786 82 3.008
43 2.791 83 3.014
44 2.797 84 3.019
45 2.802 85 3.025
46 2.808 86 3.030
47 2.813 87 3.036
48 2.819 88 3.041
49 2.825 89 3.047
50 2.830 90 3.052
51 2.836 91 3.058
52 2.841 92 3.064
53 2.847 93 3.069
54 2.852 94 3.075
55 2.858 95 3.080
56 2.863 96 3.086
57 2.869 97 3.091
58 2.875 98 3.097
59 2.880 99 3.103
60 2.886 100 3.108
61 2.891 101 3.L14
62 2.897 102 3.119
63 2.902 103 3.125
64 2.908 104 3.130
65 2.913 105 3.136
66 2.919 106 3.141
67 2.925 107 3.147
68 2.930 108 3.153
69 2.936 109 3.158
70 2.941 110 3.164
66
4. NO CONTROL OF TEMPERATURE IN MANUAL MODE
a. WITH POWER OFF ON ACFT SET AUTO-MANUAL SWITCH TO MANUAL
1. MEASURE CONTINUITY BETWEEN PINS 35 AND 37 ON THE
DIGITAL TEMP COMMUTER (.025 OHMS MAX).2. MEASURE CONTINUITY BETWEEN PINS 25 AND 3 (ON DIGITAL
TEMP. COMPUTER) BY PRESSING INCR-DECR SWITCH TO
INCR. MEASURE CONTINUITY BETWEEN PINS 25 AND 6 BY
PRESSING INCR-DECR SWITCH TO DECR.
b. TURN POWER ON THE ACFT. VERIFY TEMP. CONT. CIRCUIT
BREAKER IS PUSHED IN.
i. WITH AUTO-MANUAL SWITCH IN MANUAL, PRESS TNCR-DECR
SWITCH TO DECR. VERIFY 15 .5 VDC BETWEEN PINS
6 (C) AND 8(-) AND VERIFY 28 c/- .5 VDC BETWEEN PINS
1(-) AND 22
2. PRESS INCR-DECR SWITCH TO INCR POSITION. VERIFY
VOLTAGE BETWEEN PINS 8(-) AND 3(~-) IS 15 f/- .5 VDC,AND PINS 2(-) AND 22(~) IS 28 .5 VDC.
NOTE:
IF UNABLE TO CONTROL THE HEAT INTO THE CABIN IT MAY BE A
FLOW PROBLEM NOT TEMP. CONTROL SYSTEM REFER TO STEP 2.
92. Remove all test equipment
93. Install royalite cover to inside of rear pressurebulkhead. Install upholstery to rear pressurebulkhead. Install all side trim previously removed and
carpets in cabin. Install seats in cabin. Install
all tables and bars in cabin.
94. Install all baggage compartment trim previously removed.
95. Repaint reworked areas of exterior paintwork as
necessary.
96. Install 880734-9 placard ambient air inlet port R/Hside of fuselage I.A.W. Dwg.880734, Sheet B1.
97. Weigh aircraft for weight and blance purposes and
insert new weight and balance data in the Pilots
Operating Handbook.
98. Check that the Pilots Operating Handbook has the
revision dated 29 January 1988 (for both 690C and 695
models) addressing the enviro system incorporated.
99. Conduct enviro system flight test as follows:
1. Prior to engine start:
a. Bleed Air Switch BOTH CLOSE
b. Mass Flow Switch LOW
c. Temp Control AUTO
d. Temp Control as requirede. Air Conditioner Switch OFF
67
2. After engine start:
a. Set RPM of both engines to 65 percenth. Envir Master Switch ON
c. Bleed Air Switch BOTH OPEN
d. Cabin Bus Switch CABIN
e. Air Cond Switch as requiredf. HI/LO Evap Switch as requiredg. Mass Flow Switch as required (LOW for takeoff)
3. Air Conditioner Checks During the flight
NOTE:
AIR COND NOT TO BE SELECTEO ABOVE L8,000 FEET. FAN CAN BE USED FOR
AIR CI~RCULATTON M ANY ALTITUDE.
a. Verify that the AC light is on whenever the Air Cond
Switch is in the AIR COND position.
b. Verify that there is air flow from the air conditioner
system overhead outlets when the Air Cond Switch is in
the AIR COND or FAN position, and that the air is cool
when the switch is in the AIR COND position.
c. verify that the air flow increases when the EvapSwitches are in the HI position.
4. Temperature Control System Checks During the flight
a. Verify that air flow increases out of the floor
outlets with mass flow switch in MAX position and that
the MAX FLOW annunciator illuminates.
b. Verify that cabin temperature is controlled byadjusting temperature control rheostat. Verifytemperature changes using thermometers to monitor the
duct temperature and the duct output temperature in
the cockpit. The temperatures will vary with altitude
and outside temperature.
c. With Auto/Manual Switch in MANUAL, verify that
temperature is controlled by using the INCR/DECRswitch. (Push switch for one second or Less
and wait at least one minute for a temperature
change.)
too. Fill out and mail compliance card.
ELECTRICAL LOAD Total increase with freon compressor an is124.63 amps in flight and 144.63 on ground. With freon
compressor off increase is 4.63 amps in flight and 24.63 amps on
ground.
PUBLICATION8 AFFECTED; The Airplane Maintenance Manual and Wiringdiagram changes required by this document were incorporated byamendments dated December 21st 1987 and July ist 1988 respectively for
the Model 690C and February 24th 1988 and March 15th 1988 respectivelyfor the Model 695.
RECORD COMPLTANCE: Make an appropriate entry in the airplanemaintenance records as follows: Custom Kit No. 141 dated July17,1992 entitled Enviro System Modification accomplished
Fill out compliance and warranty registration forms and return
to Twin Commander A/C Corp.
CUSTOM KIT NO. 141
ENVIRO AIR CONDITIONING AND PRESSURIZATION SYSTEM INSTALLATION
ADDENDUM A
Drawings provided with Custom Kit No. 141.
DRAWING NO. TITLE
800816 ENVIRO ELECT WIRING
880657 PIPING INSTL.
880694 MOD SYS FREON AIRCON
880697 MOD GRL FREON AIRCON
880698 MOD EVAP INSTL FWD
880700 MOD PP FREON AIRCON
880701 MOD ELEC FREON AIRCON
880708 MOD SYS FREON AIRCON
880709 MOD SHRD AIRCON EX
880718 MOD ENVIRO SYS INSTL
880724 MOD FLUSH SCOOP INSTL
880725 MOD EXHAUST AIR DUCT A& I
880726 MOD AFT FUSE PLUMBING
880718 MOD EVAP INSTL
880730 MOD AIRCON AT BLKHD
880732 MOD PLBG INSTL AC
880734 MOD TUBE INSTL
880735 MOD TEMP FLOW CONT
880737 MOD EVAP INSTL
880741 MOD DEFLECT ASSY WTR
Custom Kit ~L Ill/Al
(C=L1AYWAUltLI~AIRCRAFT CORPORATION
P.O. Box 3369, Arlington, WA 98223
(360) 435-9797 lax(360) 435-1112
CUSTOM KIT 158
January 8, 1996
ADDITION OF INBOARD DE-ICE BOOTS
MODELS AFFECTED: 690, 690A, 690B (CK158-501);690c, 695 (CK158-1)
OVERVIEW: These kits add de-ice boots between the nacelles and the fuselage on thoseairplanes of the above models that did not come from the factory with them.
COMPLIANCE: At owner’s discretion.
BY WHOM WORK WILL BE ACCOMPLISHED: A P mechanic
APPROVAL: This kit is approved by the FAA.
ESTIMATED MAN HOURS: For both kits, time to accomplish this conversion is about20 hours. (If the engines are out of the airplane, time to accomplish is shout 12 hours)
OTHER DOCUMENTS AND DRAWINGS REQUIRED: The drawing that is listed inthe parts list on the next page is included in both kits. In addition, the maintenancemanual for the airplane will be needed.
PARTS DATA: These kits are available from authorized Twin Commander ServiceCenters. When ordering, refer to the following kit numbers:
CK158-1 Kit for the addition ofinboard de´•ice boots, for 690C and 696 airplanes.CK158501 Kit for the addition ofinhoard de-ice boots, for 690, 690A, and 69011.
Page 1 of 3
Custom Rit 158
PARTS LIST:
guantityPart number Description -1 kit 501 kit Notes
890480-3 Doubler 2 2
890480-5 Yassy 2
8904807 Tee assy 2890356-503 Doubler 2 2
515194´•1 Boot, LH 1 1
515194-2 Boot, RH 1 1
890480 Drawing 1 1
MIL-H-5599-8 .50 ID hose AR AR (1)MS3367-2´•9 5-Rep AR AR (1)MS21226-() Grommet AR AR (1)AN737TW90 Clamp 8 8 (1)
Notes: (1) Not included in kit. Obtainlocally.
INSTRUCTIONS:
(1) Install the boots and other parts in accordance with installation 890480-1 (for the -1
kit), or 890480-501 (for the -501 kit). Note the following differences andclarifications:
(a) The parts that are called 890480-17, -19, -21, -23, and -25 on the drawing shouldbe fabricated locally of MIL-H-5593´•8 hose, and part-marked CK158-17, -19, -21,-23, and -25, respectively.
(b) Install the boots in accordance with the Maintenance Manual. It is acceptable touse 1300L cement (3M) instead of EC-1403, and to use Pro-Seal 890 instead ofEC1031 and EC801. The Aerazur boots do not require conductive paint or Icex.
(c) Caterpillar grommets installed in a double rib may need to be MS21226-5.(d) Observe the requirements of figure 1 (from TCAC specification 310) on the next
page when clamping hoses or hose couplings to tubes.
(e) Observe usual good practice when routing hoses. In particular, locate, and if
necessary clamp, hoses away from hot or moving parts.(f) Touch-up alodine and prime any bare aluminum edges.(g) It is important that the cement be allowed to cure for the amount of time that the
Maintenance Manual specifies: 24 hours at temperatures above 60"F, 72 hours at
temperatures below 60"F.
(2) Perform a check of the operation of the de-ice boot system in accordance with theMaintenance Manual.
Page 2 of 3
Custom I~t 158
WEIGHT AND BALANCE: For this change, Weight 7.8 ibs., H-hrm 301.5 inches.
ELECTRICAL LOAD: No change
RECORDS COMPLIANCE:
hlake an entry of this modification in the aircraft maintenance records:Custom Kit 158 -1 or ´•501], Addition of Inboard De-Ice Boots, was done on date i.
Figure 1
AM 37TW C~amp
.13 1i. to
Page 3 of 3
1~TI1IIYCustom Kit AIRCRAFT CORPORITION
I´•I:I~)UY1SI
CUSTOM KIT NO. 163
August 4, 1998
PPG WINDSHIELD MOISTURE SEAL INSTALLATION AND REPAIR PROCEDURE
FOR INSTALLED TWIN COMMANDER WINDSHIELDS
MODELS AFFECTED: 690AIBICID, 695/Ale
REASON FOR PUBLICATION: This procedure is applicable to installed windshields for
the addition or repair of hump seals as the primary weather seal between the glass and
fiberglass strap. It is necessary to perform the glass surface preparation/cleaningprocedure detailed below for all repairs that require replacement of a portion of the seal
that contacts the alasssurface or fiberglass surface1s).
COMPLIANCE: At owner’s discretion.
BY WHOM WORK WILL BE ACCOMPLISHED: A 6 P mechanics or equivalent.
APPROVAL: Engineering design aspects are FAA approved.
ESTIMATED MANHOURS: 12 Hours
PLANNING INFORMATION: It is recommended that all subject windshields be inspectedfor outboard moisture seal erosion or delamination every four months. Particular attention
should be taken at the areas eroded by the wiper blades. The entire hump seal area
should be inspected to determine if it is wall bonded to the glass and fiberglass strapsurfaces. If there is evidence that portions of the seal can be lifted with finger or plastic
spatula pressure, those portions should be removed and repaired per the followinginstructions.
NOTE
IT IS ESSENTIAL THAT REPAIRS BE MADE AS NEEDED TO INSURE
MAXIMWTION OF WINDSHIELD SERVICE LIFE.
PARTS DATA:The kit is available from authorized Twin Commander Service Centers.
Order kit no. CK163.
MATERlAtLS SUPPLIED WITH KIT:
1 Products Research Primer PR142 (16 oz.)6 Courtaudls PR 1425 B-1 12 Black with PR 142 Primer (Model 654 SEMKIT)
5 Pr. Rubber Gloves (Powder Free)
PAGE 1 OF 8
CUSTOM ~IT NO. 183
1 Plastic Spatula1 Roll Masking Tape (3m Scotch #232 Or Equiv. Crepe Paper Tape)1 Box Gauze Pads
5 Cotton Cloths
1 Cellulose Sponge2 Sht. Sandpaper (Norton 220 Grit Or Equivalent)2 Razor Blades (Single Edge, Safety)2 Felt Blocks (4x4x.5 in.]1 ZUa~D Cleanser With Oxalic Acid I Pumice I Cerium Oxide
1 CK163 "HUMP SEAL’ Tool
MATERIALS PROCURRED LOCALLY:
Allphatic Naphtha Or Methyl Ethyl t<etcne (MEK)lsopropyl Alcohol (100%)Water
INSTRUC710NS:A. Outboard Glass and FibelRlass S~lao Surface Preoaratlon
1. Mask off the outer glass surface of the window up to the inside edge of the existingoutboard moisture seal. This taping is to insure protection of the glass surface duringremoval of the damaged sealant and fiberglass strap.
2. Completely mask the metal window retainer from the inside edge of the retainer to the
outside edge.
3. When the masking is completed as detailed in steps 1 and 2, an open work area the
width of the existing seal should exist.
4. Carefully remove any damaged, debonded or deteriorated sealant or fiberglass with a
single edge safety razor blade;by shaving along the surface. This is made easier byslightly bending the razor blade at center to insure that the corners do not scratch or
cut into the outboard glass surface.
5. After removal of the damaged sealant, sand the exposed surface of the remainingintact fiberglass strap with 220 grit sandpaper.
CAUTION:
BE CAREFUL NOT TO ABRADE. OR SCRATCH THE OUTER GLASS PLY
SURFACE WITH THE SANDPAPER.
6. After sanding fiberglass strap(s), remove the masking tape and thoroughly clean the
exposed glass surface and remaining fiberglass strap using a clean cloth saturated
with aliphatic naphtha or methyl ethyl ketone (NIEK). Degrease the work area utilizing a
progressive cleaning procedure by cleaning a small area at a time followed by
PAGE 2 OF 8
CUSTOM KIT NO. 163
isopropyl rinse to remove solvent residue, then dry with a clean cloth. Discard soiled
cloths regularly to prevent redepositing contaminants.
7. Apply masking tape as shown in Figure i. After taping, an open work area of
approximately 1.00 inch should exist.
8. Soak a block of clean felt with water and using a slurry of either pumice, cerium oxide
or ZUO~ cleanser and water, polish the exposed glass surface by hand all around until
observing a water-break free surface. A water-break free surface completely"wets" or
"sheets" over the glass surface with no signs of drawing up into droplets showing dry
areas in between. Continue polishing until the water-break free surface is obtained.
Achieving the water-break free surface is critical to insure adhesion of the sealant to
the outer glass surface. This step is critical to achieving proper bond of the PR 1425 B-
1/2 to the glass since complete removal of the PPG surface seal in the bond area is
required.
9. After a water-break free surface is obtained, remove tape from glass and clean the
entire area with isopropyl alcohol (100%) and allow to air dry. Repeat the cleaning
operation changing cloths frequently until no residue is visible on the surface of cloth.
10. Apply 1" masking tape to the outboard glass surface as shown in Figure 2. One layer
of tape should be applied .25 inch from the edge of the fiberglass strap using the
"hump" seal forming tool as a template. Build up the thickness using multiple layers of
tape 50 inch from the edge of the fiberglass strap to form a guide for the "hump" seal
forming tool. After masking, an open area of.25 inch should exist between the inside
edge of the fiberglass strap and the outside edge of the first layer of masking tape
Mask the remaining area of glass (daylight opening) to protect glass surface during
repair operation. Figure 3 and Figure 5 show configuration of repaired "hump’ seal
Figure 4 shows configuration of OEM "hump" seal.
11. Wearing powder free rubber gloves, repeat the cleaning operation with clean cloths
saturated with isopropyl alcohol (100%). Take care not to soak the masltina tape
and contaminate the glass with adhesive from the tape. Again, wipe the surfaces
until no residue is visible on the cloth. Allow surface to air dry a minimum of five
minutes.
12 After a thorough cleaning of the area to be repaired has been accomplished, apply the
new sealant per the following detailed moisture seal application ptocedure.
B. Moisture Seal ADc~lication Procedure General Instructions
1. Follow all established safety rules and practices.
2. Read material safety data sheets for each material to be used
3. Wear powder free clean rubber gloves during all sealant applications to avoid
contamination of the bonding surfaces and to prevent chemical contact with skin.
PAGE 3 OF 8
CUSTOM KIT NO. 163
C. Moisture Seal Apolication Procedure
i. Apply 1 inch masking tape to the outboard metal retainer from the inside edge of the
outboard metal retainer as shown in Figure 2.
2. Using a gauze pad, apply a thin coat (enough to cover without running or dripping) of
the PR 142 primer/cleaner to the cleaned glass surface to be bonded. Allow PR 142 to
dry per manufacturers requirement.
3. Sealant must be applied to windshield immediately after the cleaning operation and
primer application to prevent dust particles and other airborne contaminants from
settling on the cleaned surfaces. Any contaminant on the surface can adversely effect
the adhesion of the sealant to the substrate.
Note: Apply mixed sealant after allowing primer to dry. (See manufacturers’
instructions).
4. Thoroughly mix the contents of the SEMKIT containing the appropriate sealant until no
streaks of either material are visible. Mix components for a minimum of five minutes.
COMPLETE MIXING IS ESSENTIAL
Follow the mixing instructions on the side of the SEMKIT package:
a) Wear safety glasses and gloves while mixing and dispensing
b) Hold cartridge and pull dasher rod back approximately 1/4 of the way up the
cartridgec) Insert ramrod into hollow of dasher rod. Move piston and inject about 1/3 of the
contents of the rod into the cartridge.
CAUTION:
USE FIRM BUT EVEN PRESSURE. DO NOT FORCE, TAP, POUND OR JOLT
RAMROD, IF PISTON DOES NOT MOVE READILY.
d) Repeat steps b and c until ail the contents of the rod are emptied into the cartridge.
Remove ramrod.
a) Hand mix: Mix material for the total number of strokes listed (40 strakes/ 30 strokes
per minute). A stroke is one complete in and out cycle. Hold cartridge and rotate rod
90 degrees in a spiral clockwise motion with each stroke. Each stroke should extend
from the neck end of the cartridge to the plunger end of the cartridge. Accepted
procedure is 30 strokes per minute.
5. Remove the mixed sealant from the SEMKIT tube by the following procedure:
a) Remove bottom cap.
b) Push dasher rod to plunger end of cartridge. Grasp cartridge firmly at plunger end
and detach dasher rod from mixing dasher by turning counter clockwise
PAGE 4 OF 8
CUSTOM I(IT NO. 163
Remove the dasher rod from cartridge. Using the dasher rod, pushlextrude contents of
SEMKIT tube onto the surface to be sealed.
6. Using a plastic spatula or air gun, spread the sealant on the cleaned and primedoutboard glass surface to be bonded.
7. Form the outboard "hump" seal using hump seel tool as shown in Figure 6. The width
of the formed "hump" seal should be 1 inch. The thickness of the formed seal should be
0.10 inch +.02 inch. See Figure 3 and Figure 5 for view of "hump" seal after repair.
Figure 4 shows view of OEM moisture seal.
8. After completing forming of "hump" seal immediately remove the masking tape from the
glass and metal surface while the sealant is still "wet" (uncured). Be careful not to
touch the "wet" (uncured) sealant during tape removal.
9. Smooth the surface of the "wer’ sealant by rubbing the surface of the sealant very
lightly and briskly with a cellulose sponge saturated with water or isopropyl alcohol
(100%).
Note:
Use light pressure only.
10. Allow the sealant to cure. Tackfree cure time for PR 1425 8-1/2 is accomplished at
room temperature (75 degrees F.150% relative humidity) in 8 hours. Cure time to 35
Rex hardness is 24 hours. For every 109150 F. rise in temperature (to a maximum of
140" F.) the cure times are cut in half, for every 100-150 F. decrease in temperature, the
cure time is doubled.
11. After the sealant has cured, inspect for voids and repair as necessary.
PAGE 5 OF 8
CUSTOM KIT NO. 163
MASKING TAPE
SINGLE LAYER OF r"MASKING TAPE
FIGURE 1TAPE FOR CLEANING
MASKINC´•TAPEMULTIPLE LAYERS OF I~ k--;28MASKING TAPE
FIGURE 2
TAPE FOR HUMP SEAL
1.0
.2610 REF.
f
FIGURE 3PROPDSED HUMP SEAL
FIELO REPAIR
PAGE 6 OF 8
ADs
Aircraft Technical Publishers Customer Service
South Hill Drive 6AM-5PM PST M´•F
Brisbane, CA 94005 (800)227-4610
ATP Grid Index to Manufacturer’s Publications:
Gulfstream Aerospace695, 695A, 6958
AD’S
AD Number
Effective Date Issue Description
84-19-05 TO PREVENT FAILURE OF THE
10/08/84 ENGINE MOUNT SYSTEMS
87-24-07 R1 TO PREVENT ENGINE FLAMEOUT
02/09/88 WHEN IN OR DEPARTING AN ICING
ENVIRONMENT
95-12-23 TO PREVENT WING DAMAGE CAUSED
07/30/95 BY FATIGUE CRACKING,WHICH,IF
Recurring NOT DETECTED AND CORRECTED,
COULD PROGRESS TO THE,CONTD.
95-13-02 TO PREVENT FAILURE OF THE
07/22/95 VERTICAL STABILIZER AS A
Recurring RESULT OF CRACKS, WHICH, IF
NOT DETECTED CORRECTED,CONTD
95-19-18 TO PREVENT STRUCTURAL DAMAGE
10/25/95 TO THE AIRPLANE CAUSED BY
EXCESSIVE TURBULENCE, WHICH
COULD RESULT IN LOSS,CONTD.
98-07-17 TO PREVENT FAILURE OF A FLAP
05/29/98 SYSTEM CABLE CAUSED BY
FATIGUE, WHICH COULD RESULT IN
LOSS OF CONTROL OF THE,CONTD.
04/09/2003 Copyright Aircraft Technical Publishers Page 1 of 2
GC 0853 SI AD
AD Number
Effective Date Issue Description
98-08-19 TO PREVENT CRACKS AT THE WING
05/18/98 TO FUSELAGE ATTACH POINTS,
Recurring WHICH, IF NOT DETECTED AND
CORRECTED, COULD CAUSE,CONTD.
98-08-25 R1 To prevent the nose landing01/05/99 gear (NLG) from collapsing due
to failure of a drag link
bolt, which could,contd.
98-20-34 TO MINIMIZE THE POTENTIAL
11/03/98 HAZARDS ASSOCIATED WITH
OPERATING THE AIRPLANE IN
SEVERE ICING CONDITIONS,CONTD.
2000-02-30 To activate the pneumatic wing03/24/00 and tail deicing boots at the
first signs of ice
accumulation
2003-07-03 To detect and correct fatigue05/16/03 damage in the wing and
Recurring fuselage areas without
reducing the service,contd.
End of Index
04/09/2003 Copyright Aircraft Technical Publishers Page 2 of 2
GC 0853 SI AD
Aircraft Technical Publishers Customer Service~s
101 Sduth Hill Drive 6AM-5PM PST H-F
Brisbane, CA 94005 (800)227-4610
ATP Grid Index to Manufacturer’s Publications:
Twin Commander A/C
695. 695A. 6958
AD’S
Serial# Tach.Time Total Time N Number Date Researchd
Hours
AD Number Issue Description Date of At Method of One Next Authori zed
EffectiveDate Compliance Compliance Comp Compliance Time Recurring Comp.Due Signature
84-19-05 TO PREVENT FAILURE OF THE I I I I I I I10/08/1984 ENGINE MOUNT SYSTEMS
87-24-07 R1 TO PREVENT ENGINE FLAMEOUT I I I I I I02/09/1988 WHEN IN OR DEPARTING AN ICING
ENVIRONMENT
95-12-23 TO PREVENT WING DAMAGE CAUSED I I I I I I07/30/1995 BY FATIGUE CRACKING.WHICH.IF
Recurring NOT DETECTED AND CORRECTED.
COULD PROGRESS TO THE.CONTD.
95-13-02 TO PREVENT FAILURE OF ME j I I I I I I07/22/1995 VERTICAL STABILIZER AS A
Recurring RESULT OF CRACKS. WHICH. IF
NOT DETECTED 8 CORRECTED.CONTD
95-19-18 TO PREVENT STRUCTURAL DAMAGE I I I I I I I10/25/1995 TO ME AIRPLANE CAUSED BY
EXCESSIVE TURBULENCE. WHICH
COULD RESULT IN LOSS.CONTD.
98-07-17 TO PREVENT FAILURE OF AFLAP I I I I I I I05/29/1998 SYSTEM CABLE CAUSED BY
FATIGUE. WHICH COULD RESULT IN
LOSS OF CONTROL OF THE.CONTD.
98-08-19 TO PREVENT CRACKS AT THE WING I I j I I I I05/18/1998 TO FUSELAGE ATTACH POINTS.
Recurring WHICH, IF NOT DETECTED AND
CORRECTED. COULD CAUSE.CONTD.
04/09/2003 Copyright Aircraft Technical Publishers Page 1 of 2
GC 0853 SI AD
Hours
AD Number Issue Description Date of At Method of One Next Authorized
Effective Date Compliance Compliance Comp Compliance Time Recurring Comp.Due Signature
98-08-25 R1 To prevent the nose landing I I 1 I I I I
01/05/1999 gear (NLG) from collapsing due
to failure of a drag link
bolt, which could.contd.
98-20-34 TO MINIMIZE THE POTENTIAL I I I I I I I
11/03/1998 HAZARDS ASSOCIATED WITH
OPERATING THE AIRPLANE IN
SEVERE ICING CONDITIONS,CONTD.
2000-02-30 To activate the pneumatic wing I I I I I I I
03/24/2000 and tail deicing boots at the
first signs of ice
accumulation
2003-07-03 To detect and correct fatigue I I I I I I I
05/16/2003 damage in the wing and
Recurring fuselage areas without
reducing the service.contd.
End of Index
04/09/2003 Copyright Aircraft Technical Publishers Page 2 of 2
GC 0853 SI AD
84’´•19-05 :sTREnM´•nERosPACE MRPORATION:
Amendment 39-4925. Applies to Models 690 and 690A, (S/Ns 11001 through 11284 which
have had engine isolator assemblies replaced after July 28, 1975): 690A (S/Ns 11285 through
11344): B90B (S/Ns 11350 through 11566); 690C (S/Ns 11600 through 11732); 690D (S/Ns15001 through 15033 and 15037); 695 (S/Ns 95000 through 95084); 695A (S/Ns 98001
through 960B1,96063through 96072, 96075, 96078, 96085, and 96088) airplanes certificated
In any category.
Compliance: Required as indicated, unless already accomplished.
To prevent failure of me engine mount systems accomplish the following:
(a) Within 50 hours time-in-service after the eftectlve date of this AD, inspect and
modify, if required, the engine mount systems in accordance with Guffstream Aerospace
Corporation Service Bulletin SB201 issued May 11, 1984.
(b) Airplanes may be flown in accordance with FAR 21.197 to a location where this
AD may be accomplished.
(c) An equivalent method ofcompliance with this AD may be used ifapproved bythe
Manager, Airplane Certification Branch, ASW-150, FAA, Southwest Region, Past ORlce Box
1689, Fort Worth, Texas 76101; telephone (817) 877-2070.
This amendment becomes effective on October 8, 1984.
GULFSTRUIMAMERIC4NCORWR4~/0N
87-24-07 R1CORPORATION: Amendment 395774 as amended by amendment 39-5840. Applies to
Models 690, B90A, 6908, 690C, 690D, 895, 695A, and 6958 tell serial numbers) airplanescertificated in any category.
Compliance: Required within the next 50 hours’ time-in-service after the effective date
of this AD, unless already accomplished.
(a) To prevent engine Rameout when in or departing an icing environment,
accomplish the following:
(1) Revise the airplane POHIAFM by inserting or assun’ng thatthe appropriateGulfstream published revision has been inserted as defined by the following listing:
Modal 690, Revision No. 23, dated May 20, 1987
Model 690A, Revision No. 30, dated May 20, 1987
Model 6908, Revision No. 23, dated May 20, 1987
Mode1690C, Revision No. 21, dated April 9, 1987
Model 690D, Revision No. 12, dated April 9. 1987
Model 695, Revision no. 12, dated April 9, 1987
Model 695A, Revision No. 20, dated April 9, 1987
Model 6958, Revision No, 9, dated April 9, 1987
Ifthe listed revision is not available, revise the POH/AFM by inserting Appendix 1 of this
AD in the "LIMITATIONS" section of the POM/AFM. Appendix 1 procedures supersede any
other POHIAFM procedures which may be contradictory.
NOTE 1: If the above actions have been accomplished in compliance with AD 86-
24-12, no further action is required in order to comply with paragraph (a)(l) of this AD.
(2) Forthose airplanes with ignition systems having a continuous duty cycleof less than 1 hour:
(i) Fabricate and install a placard on the instrument panel in clear view
of the pilot stating, "This airplane is prohibited from flight into known icing," and operate the
airplane in accordance with this limitation. This placard must consist of a minimum of 0.1 inch
high lenerswlth white and red contrasting letterand background colors and may be of a plasticadhesive type.
(ii) The requirements ofsection (a)(2)(i) are no longer applicable when
the aircraft ignition system having a continuous duty cycle of less than 1 hour is modified to
increase the duty cycle to 1 hour or more in accordance with Gulfstream Service information
Nos. SI-211 and/or $1-212 both dated June 30, 1986.
GULFSTRtZ(MAMERIWINCORPaR4nON
(b) The requirements of paragraph (a) of this AD are no longer applicable when the
airplane is modified in accordance with Gulfstream Custom Kit Nos. 138 dated April 15, 1987,or 1 39 dated May 28, 1987, orbythe addition ofother FAA approved automatic rellght ignition
systems for both engines.
NOTE 2: Automatic-rellght ignition is a system which automatically energizes engineignition without pilot action when engine RPM ortorque decays below a specified level and de-
energizes engine ignition when RPM or torque exceeds the specified level. It is not
synonymous with CONTINOUS IGNITION.
(c) The requirements of paragraph (a)(l) and ~a)(2)(1) of this AD may be
accomplished by the holder of a pilot certificate issued under Part 61 of the FAR on any
airplane owned or operated by the pilot, and which is not used under Part 121 or 135. The
person accomplishing these actions must make the appropriate airplane maintenance record
entry as prescribed by FAR 91.173.
(d) Airplanes may be flown in accordance with FAR 21.197 to a location where this
AD may be accomplished.
(e) An equivalent means of compliance with this AD may be used if approved bytheManager, Airplane Certification Branch, ASW-150, FAA, Fort Worth, Texas 76193-0150;
telephone (817) 624-5150.
All persons affected by this directive may obtain copies of the documents(s) referred to
herein upon request to the Gulfstream Aerospace Corporation, Wiley Post Airport, P.O. Box
22500, Oklahoma City, Oklahoma 73123; Telephone (405) 789-5000; or may be examined at
the FAA, Office of the Regional Counsel, Room 1558, 801 East 12th Street, Kansas City,Missouri 84106.
This AD revises AD 81-24-07, Amendment 39-5774, which superseded AD 86-24-12,Amendment 39-5483 (52 FR 43849: November 17, 1987.).
This amendment, 39-5840, becomes effective on Februaty 9, 1988.
APPENDIX I
Supplement to the POH/AFM
Oulfstream Aerospace CorporationModels 690, 690A, 6908, 690C, 690D,
695, 695A, and 6958 Airplanes
Continuous ignition switch shall be assured by selecting Manual IGN or ION Override or IGN
OVRD on the ignition switch as appropriate during all operations in actual or potential icingconditions described herein:
(1) During takeoff and climb out in actual or potential icing conditions.
(2) When ice is visible on, or shedding from propeller(s), splnner(s),or leading edge(s).
"(3) Before selecting ENG INLET, when ice has accumulated.
(4) Immediately, any time engine Rameout occurs as a possible result of ice
Ingestion.(5) During approach and landing while in or shortly following Right in actual or
potential icing conditions.
*Note: If icing conditions are entered in Right without the engine anti-icing system having
been selected, switch one ENGINE system to ENG INLET ON position. If the engine runs
satisfactorily, switch the second ENGINE system tq the ENG INLET ON position and checle
that the second engine continues to run satisfactorily.
CAUTION
Flight in actual or potential icing conditions will be limited by duty cycle of the ignition system.
Ignition system time limits must be observed to prevent exceeding duty cycle times. Operator
should verify these limits for his particular installation.
For the purpose of this supplement, the following definition applies:
"Potentlal icing conditions in precipitation orvlsible moisture meteorological conditions:
(1) Begin when the OAT is +5 degrees C (+41 degrees Fl or colder, and
(2) End when the OAT is +10 degrees C (+50 degrees Fl or warmer.
The procedures and conditions described in this appendix supersede any other POH/AFM
procedures and conditions which may be contradictory.
GULFSTRUIMAMERIWINCORPOR4nON
95-1 2-23TWIN COMMANDER AIRCRAFT CORPORATION:
Amendment 39-9275; Docket No. 94-CE-29-AO.
Applicability: The following airplane models and serial numbers, certificated in anycategory:
Model Serial Numbers
690C 11600 through 11735
695 95000 through 95084
NOTE 1: This AD applies to each airplane identified in the preceding applicabilityprovision, regardless of whether it has been modified, altered, or repaired in the area subjectto the requirements of this AD. For airplanes that have been modified, altered, or repaired so
that the performance of the requirements of this AD is affected, the owner/operator must use
the authority provided in paragraph (g) of this AD to request approval from the FAA. This
approval may address either no action, if the current configuration eliminates the unsafe
condition, or different actions necessary to address the unsafe condition described in this AD.Such a request should include an assessment of the effect of the changed configuration on
the unsafe condition addressed by this AD. In no case does the presence of any modification,alteration, or repair remove any airplane from the applicability of this AD.
Compliance: Required upon the accumulation of 6,000 hours time-in-service (TIS) or
within the next 50 hours TIS after the effective date of this AD, whichever occurs later, unless
already accomplished, and thereafter as indicated in the body of this AD.
To prevent wing damage caused by fatigue cracking, which, if not detected and
corrected, could progress to the point of structural failure, accomplish the following:
(a) For all affected serial number Model 695 airplanes, and any Model 690C
airplane incorporating a serial number in the 11600 through 11730 range, inspect the wingstructure for cracks in accordance with the PART I ACCOMPLISHMENT INSTRUCTIONS
(INSPECTIONS) section of Twin Commander Service Bulletin (SB) No. 213, dated July 29,1994.
(b) For any Model 690C airplane incorporating a serial number in the 11731 through11735 range, inspect the wing structure for cracks in accordance with item 10 of the PART IACCOMPLISHMENT INSTRUCTIONS (INSPECTIONS) section of Twin Commander SE No.
213, dated July 29, 1994.
TWIN COMMANDER AIRCRP~FT CORPORPITION
(c) If, during the inspections required in paragraphs (a) and (b) of this AD, cracks
are found in the areas referenced in Figures 1 through 5 and the instructions of the service
information referenced above, prior to further flight, replace the damaged structure and modifythe wing structure in accordance with the PART II ACCOMPLISHMENT INSTRUCTIONS
(MODIFICATIONS) section of Twin Commander SE No. 213, dated July 29, 1994.
(d) If no cracks are found, accomplish one of the following:
11) For all airplanes, upon the accumulation of 7,500 hours TIS or within
1,000 hours TIS after the initial inspection, whichever occurs later, reinspect the structure in
accordance with either paragraph (a) or (b) of this AD, as applicable, and reinspect thereafter
at intervals not to exceed 1,000 hours TIS, and, if applicable, replace any damaged part or
modify the wing structure as specified in paragraph (c) of this AD; or
(2) For Model 695 airplanes and any Model 690C airplane incorporating a
serial number in the 1 1600 through 1 1730 range, prior to further flight, modify the wingstructure in accordance with the PART II ACCOMPLISHMENT INSTRUCTIONS
(MCDIFICATIONS) section of Twin Commander SE No. 213, dated July 29, 1994.
(e) For all affected Model 695 airplanes and any Model 690C airplane incorporatinga serial number in the 11600 through 11730 range, the modification referenced in paragraphs(c) and (d)(2) of this AD may be accomplished any time after the initial inspection as
terminating action for the repetitive inspection requirement of this AD, except for the inspectionof the doublers at the wing attach fittings located in the Fuselage Station 144 frame (Item 10 of
PART I ACCOMPLISHMENT INSTRUCTIONS section of the Twin Commander SE No. 213,dated July 29, 1994). All affected model and serial number airplanes must inspect in this area
at every 1,000 hours TIS.
NOTE 2. For those airplanes that have not accumulated 6,000 hours TIS, the initial
and first repetitive inspection required by this AD were established to coincide with the 6,000-hour Major Inspection Guide I and 7,500-hour Major Inspection Guide II inspections,respectively, so that the operator may schedule the required action in accordance with these
major inspections.
(f) Special flight permits may be issued in accordance with sections 21.197 and
21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the
airplane to a location where the requirements of this AD can be accomplished.
(g) An alternative method of compliance or adjustment of the initial or repetitivecompliance times that provides an equivalent level of safety may be approved by the
Manager, Seattle Aircraft Certification Office (ACO), FAA, Northwest Mountain Region, 1601
Lind Avenue S.W., Renton, Washington 98055-4056. The request shall be forwarded throughan appropriate FAA Maintenance Inspector, who may add comments and then send it to the
Manager, Seattle AGO.
95-12-23
TWIH COLHIIINOER blRCRI\FT CORPORbTIOYL
NOTE 3: Information concerning the existence of approved alternative methods of
compliance with this AD, if any, may be obtained from the Seattle AGO.
(h) The inspections and modification required by this AD shall be done in
accordance with Twin Commander Service Bulletin No. 213, dated July 29, 1994. This
incorporation by reference was approved by the Director of the Federal Register in
accordance with 5 U.S,C. 552(a) and 1 CFR palt 51.Copies may be obtained from Twin
Commander Aircraft Corporation, 19003 59th Drive, NE., Arlington, Washington 98223.
Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel,Room 1558, 601 E. 121h Street, Kansas City, Missouri, or at the Office of the Federal Register,800 North Capitol Street, NW., suite 700, Washington, DC.
(i) This amendment becomes effective on July 30, 1995.
FOR FURTHER INFORMATION CONTACT:
Mr. David D. Swartz, Aerospace Engineer. FAA, Northwest Mountain Region, 1601 Lind
Avenue S.W., Renton, Washington 98055-4056: telephone (206) 227-2624; facsimile (206)227-1181.
95-12-23
TWIN COMMANDER nlRCRACT CORPORATION
3
95-~ 3_Q2TW.
Amendment 39-9283; Docket No. 94-CE-27-AD.
Applicability: The following airplane models and serial numbers, certificated in any
category, that do not have the vertical stabilizer modified in accordance with the
ACCOMPLISHMENT INSTRUCTIONS: PART II MODIFICATION section of Twin Commander
Service Bulletin (88) No. 218, dated May 19, 1994, including Revision Notices 1 and 2, dated
July 11, 1994, and September 23, 1994, respectively:
Model Serial Numbers
685 12000 through 12088
690 11000 through 11079
680A 11100 through 11344
690B 11350 through 11566
BBOC 11600through11735690D 15001 through 15042
695 95000 through 85084
695A 88001 through 86100
NOTE 1: This AD applies to each airplane identified in the preceding applicabilityprovision, regardless of whether it has been modified, altered, or repaired in the area subjectto the requirements of this AD. For airplanes that have been modified, altered, or repaired so
that the performance of the requirements of this AD is affected, the owner/operator must use
the authority provided in paragraph (O of this AD to request approval from the FAA. This
approval may address either no action, if the current configuration eliminates the unsafe
condition, or different actions necessary to address the unsafe condition described in this AD.
Such a request should include an assessment of the effect of the changed configuration on
the unsafe condition addressed by this AD. In no case does the presence of any modification,alteration, or repair remove any airplane from the applicability of this AD.
Compliance: Required upon the accumulation of 2,000 hours time-in-service (TIS) on
a vertical stabilizer or within the next 50 hours TIS after the effective date of this AD,whichever occurs later, unless already accomplished, and thereafter as indicated in the bodyof this AD.
To prevent failure of the vertical stabilizer as a result of cracks, which, if not detected
and corrected, could result in loss of control of the airplane, accomplish the following:
TWIN COMMANDER AIRCRAFT CORPORATION
(a) Inspect the vertical stabilizer for cracks in accordance with the
ACCOMPLISHMENT INSTRUCTIONS: PART I INSPECTION section of Twin Commander
SE No. 218, dated May 19, 1994, including Revision Notices 1 and 2, dated July 11, 1994,and September 23, 1994, respectively.
(b) If damage or cracks are found within the limits of Figures 1 and 2 of the service
information referenced above, prior to further flight, modify the vertical stabilizer in accordance
with the ACCOMPLISHMENT INSTRUCTIONS: PART II MODIFICATION section of Twin
Commander SE No. 218, dated May 19, 1994, including Revision Notices 1 and 2, dated July11, 1994, and September 23, 1994, respectively.
(c) If damage or cracks are found outside the limits referenced in Figures 1 and 2 of
the service information referenced above or if cracks intersect, prior to further flight, replacethe damaged pads with new parts in accordance with the applicable maintenance manual
instructions. The requirements of this AD still apply when the damaged parts are replaced,unless the stabilizer is modified as specified in paragraph (b) of this AD.
(d) If no cracks are found, accomplish one of the following:
(1) Reinspect at intervals not to exceed 500 hours TIS, and modify any
damaged or cracked vertical stabilizer as specified in paragraphs (b) and (c) of this AD: or
(2) Prior to further flight, modify the vertical stabilizer in accordance with the
ACCOMPLISHMENT INSTRUCTIONS PART II MODIFICATION section of Twin
Commander SE No. 218, dated May 19, 1994, including Revision Notices 1 and 2, dated July11, 1994, and September 23, 1994, respectively. This modification may be accomplished priorto furhter flight after any repetitive inspection as terminating action for the repetitiveinspections provided no cracks are found.
(e) Special flight permits may be issued in accordance with sections 21.197 and
21.198 of the Federal Aviation Regulations (14 CFR 21.197 and 21.198) to operate the
airplane to a location where the requirements of this AD can be accomplished.
(f) An alternative method of compliance or adjustment of the initial or repetitivecompliance times that provides an equivalent level of safety may be approved by the
Manager, Seattle Aircraft Certification Office (ACO), FAA, Northwest Mountain Region, 1601
Lind Avenue S.W., Renton, Washington 98055-4056. The request shall be forwarded throughan appropriate FAA Maintenance Inspector, who may add comments and then send it to the
Manager, Seattle AGO.
NOTE 2: Information concerning the existence of approved alternative methods of
compliance with this AD, if any, may be obtained from the Seattle AGO.
as-13-oz
TWIN COMMANDER AIRCRAFT CORPORATION
(g) The inspections and modification required by this AD shall be done in
accordance with Twin Commander Service Bulletin 218, dated May 19, 1994, includingRevision Notices 1 and 2, dated July 11, 1994, and September 23, 1994, respectively. This
incorporation by reference was approved by the Director of the Federal Register in
accordance with 5 U.S.C. 552(a) and 1 CFR palt 51. Copies may be obtained from Twin
Commander Aircraft Corporation, 18003 59th Drive, NE., Arlington, Washington 98223.
Copies may be inspected at the FAA, Central Region, Office of the Assistant Chief Counsel,Room 1558, 801 E. 12th Street, Kansas City, Missouri, or at the Office of the Federal Register,800 North Capitol Street, NW., suite 700, Washington, DC.
(h) This amendment becomes effective on July 22, 1985.
FOR FURTHER INFORMATION CONTACT:
Mr. David D. Swartz, Aerospace Engineer, FAA, Northwest Mountain Region, 1801 Lind
Avenue S.W., Renton, Washington 98055-4058; telephone (206) 227-2624; facsimile (206)227-1181.
95-13-02
TWIN COMMANDER AIRCRAFT CORPORATION
4
95-1 9-1 8TWIN rm~LMNDeR BRCRIFTCORPD~UTIOII:
Amendment 39-9379: Docket No. 95-CE-20-AD.
Applicability: The following airplane models and serial numbers, certificated in any
category.
Models Serlel Numbers
680T and 680V 1473 through 1720
680W 1721 through 1850
681 8001 through 6072
690 11001 through 11079
690A 11100 through 11344
6908 11350 through 11566
690C 11800 through 11735
890D 15001 through 15042
695 95000 through 95084
695A 96000 through 96100
6958 96201 through 86208
NOTE 1: This AD applies to each airplane identified in the preceding applicabilityrevision, regardless of whether it has been modified, altered, or repaired in the area subjectto the requirements of this AD. For airplanes that have been modified, altered, or repaired so
that the performance of the requirements of this AD is affected, the owner/operator must
request approval for an anemative method of compliance in accordance with paragraph (c) of
this AD. The request should include an assessment of the effect of the modification,
alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe
condition has not been eliminated, the request should include specific proposed actions to
address it.
Compliance: Required within the next 50 hours time-in-service after the effective date of
this AD, unless already accomplished.
To prevent structural damage to the airplane caused by excessive turbulence, which
could result in loss of the airplane, accomplish the following:
(a) Install the placard (to the windshield centerpost) and incorporate the airplaneflight manual/pilot operating handbook (AFMIPOH) revisions that are included with the kits
presented below. The placard and AFM/POH revisions provide warnings to the airplaneoperator of the impo~tance of observing the Tult~ulent Air Penetration and Maneuveringspeeds:
TWIN COMMANDER nlRCRIFT CORPORATION
Kit No. Model Affected
SB220-1 680T
58220-2 680V
58220-3 680W
58220-4 681
58220-5 690
58220-6 690A
58220-7 6908
SB220´•8 890C58220-9 690D
58~20-10 695
SB22011 6951\
58220-12 6958
NOTE 2: Twin Commander Service Bulletin No. 220, dated February 1, 1995,relates to the subject of this AD, and references the 58220 senrice kits specified above.
(b) Special flight permits may be issued in accordance with sections 21.197 and21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the
airplane to a location where the requirements of this AD can be accomplished.
(C) An altemative method of compliance or adjustment of the compliance time that
provides an equivalent level of safety may be approved by the Manager, Seattle AircraftCertification Office (ACO), FAA, Northwest Mountain Region, 1601 Lind Avenue S.W., Renton,Washington 96055-4056. The request shall be forwarded through an appropriate FAAMaintenance Inspector, who may add comments and then send it to the Manager, SeattleAGO.
NOTE 3: Information concerning the existence of approved altemative methods of
compliance with this AD, if any, may be obtained from the Seattle AGO.
(d) All persons affected by this directive may obtain copies of the kits referencedabove that include the placard and the AFM revisions upon request to the Twin CommanderAircraft Corporation, 19010 5Wh Drive, NE., Arlington, Washington 98223; or may examinethis document at the FAA, Central Region, Office of the Assistant Chief Counsel, Room 1558,601 E. 12th Street, Kansas City, Missouri 64106.
(e) This amendment becomes effective on October 25, 1995.
FOR FURTHER INFORMATION CONTACT:Mr. David D. Swartz, Aerospace Engineer, FAA, Northwest Mountain Region, 1601 LindAvenue S.W., Renton, Washington 98055-4058; telephone (206) 227-2624; facsimile (208)227-1181.
95-19-18
TWIN COMMANMR AIRCRAFT CORPORATION
98-07-17 TWIN COMMANDER AIRCRAFT
CORPORATION: Amendment 39-10437; Docket No. 97-CE-69-AD. Supersedes AD
94-04-17, Amendment 39-8837.
Applicability: The following airplane models tall serial numbers), ce~tificated in
any category:
500 500-A 500-B 500-5 500-U
520 560 560-A 580-E 560-F
seo seo-e 680-F 680FL 680FL(P)680FP 680T 680V 680W 681
885 690 690A 69013 690C
690D 695 695A 695B 720
NOTE 1: This AD applies to each airplane identified in the precedingapplicability provision, regardless of whether it has been modified, altered, or repairedin the area subject to the requirements of this AD. For airplanes that have been
modified, altered, or repaired so that the performance of the requirements of this AD is
affected, the owner/operator must request approval for an alternative method of
compliance in accordance with paragraph (e) of this AD. The request should include an
assessment of the effect of the modification, alteration, or repair on the unsafe condition
addressed by this AD; and, if the unsafe condition has not been eliminated, the requestshould include specific proposed actions to address it.
Compliance: Required as indicated in the body of this AD, unless alreadyaccomplished.
To prevent failure of a flap system cable caused by fatigue, which could result in
loss of control of the airplane, accomplish the following:
(a) Within the next 300 hours timein-selvice (TIS) after the effective date ofthis AD, unless already accomplished, perform the following in accordance with the
ACCOMPLISHMENT INSTRUCTIONS section of Twin Commander Aircraft Corporation(Twin Commander) Mandatory Service Bulletin No. 226, dated April 14, 1997 (RevisionNo. 1 Release Date: July~lB, 1997):
(1) Inspect all flap system cable grooves for the correct width;
(2) Inspect all flap system pulleys for rubbing on the support brackets;
(3) Inspect all flap pulley cable assemblies for frayed wires; and
TWIN COMMANDER AIRCRAFT CORPORATION
(4) Mark pulleys that have been inspected and have the correct grooveradius with two parallel lines as specified in the service bulletin.
NOTE 2: Revision No. 1 Release Date: July 15, 1997, of Twin Commander
Mandatory Service Bulletin No. 226, specifies changes in the workhours necessary to
accomplish this action and makes reference to a gauge that is available from the
manufacturer for use in accomplishing the inspection.
(b) If any of the above discrepancies are found, prior to further flight after the
inspections required by paragraph (a), including all subparagraphs, of this AD, rework
or replace the affected palt in accordance with Twin Commander Mandatory Service
Bulletin No. 226, dated April 14, 1997 (Revision No. 1 Release Date: July 15, 1997).
(C) As Of the effective date of this AD, no person may install a pulley that
does not have the criteria presented in either paragraph (c)(l), (c)(2), or (c)(3) of this
AD:
(1) A pulley that has been inspected, found acceptable, and marked
with two parallel lines in accordance with paragraph (a), including allsubparagraphs, of
this AD;
(2) A pulley that has been reworked in accordance with an FAA-
approved procedure and is marked "SB 226"; or
(3) A new pulley that is marked "SB 226-NEW".
(d) Special flight permits may be issued in accordance with sections 21.197
and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operatethe airplane to a location where the requirements of this AD can be accomplished.
(e) An alternative method of compliance or adjustment of the compliance time
that provides an equivalent level of safety may be approved by the Manager, Seattle
Aircraft Certification Office (ACO), Northwest Mountain Region, FAA, f 601 Lind Avenue
S.W., Renton, Washington 98055-4056.
(1) The request shall be foNvarded through an appropriate FAA
Maintenance inspector, who may add comments and then send it to the Manager,Seattle AGO.
(2) Alternative methods of compliance approved in accordance with
AD 84-04-17 (superseded by this AD) are not considered approved as alternative
methods of compliance for this AD.
NOTE 3: information concerning the existence of approved alternativemethods of compliance with this AD, if any, may be obtained from the Seattle AGO.
981)7-17
TWIN COMMANDER AIRCRAFT CORPORATION
(f) The inspections and replacements required by this AD shall be done in
accordance with Twin Commander Mandatory Service Bulletin No. 226, dated April 14,1997 (Revision No. 1 Release Date: July 15, 1997). This incorporation by reference
was approved by the Director of the Federal Register in accordance with 5 U.S.C.
552(8) and 1 CFR part 51. Copies may be obtained from the Twin Commander Aircraft
Corporation, 19003 59th Drive, NE, Arlington, Washington 98223-7832. Copies may be
inspected at the FAA, Central Region, Office of the Regional Counsel, Room 1558, 601
E. 1 2th Street, Kansas City, Missouri, or at the Office of the Federal Register, 800 North
Capitol Street, NW, suite 700, Washington, DC.
(9) This amendment supersedes AD 94-04-17, Amendment 39-8837.
(h) This amendment becomes effective on May 29, 1998.
FOR FURTHER INFORMATION CONTACT:Mr. Jeffrey Morfitt, Aerospace Engineer, FAA, Northwest Mountain Region, 1601 Lind
Avenue S.W., Renton, Washington 98055-4056; telephone: (425) 227-2595: facsimile:
(425) 227-1181.
98-07-17
TWIN COMMANDER AIRCRAFT CORPORATION
98-08-1 9iwa co..narun alncna~
CORPORA710N: Amendment 39-10468; Docket No. 95-CE-92-AD.
Applicability: Models 500, 500A, 5008, 5008, 500U, 520, 560, 560A, 560E,560F, 680, 680E, 680F, 680FL, 680FLP, 680FP, 680T, 680V, 680W, 681, 685, 690,690A, 6908, 690C, 690D, 695, 695A, 6958 and 720 airplanes, all serial numbers,certificated in any category.
NOTE 1: This AD applies to each airplane identified in the precedingapplicability provision, regardless of whether it has been modified, altered, or repairedin the area subject to the requirements of this AD. For airplanes that have been
modified, altered, or repaired so that the performance of the requirements of this AD is
affected, the owner/operator must request approval for an alternative method of
compliance in accordance with paragraph (f) of this AD. The request should include an
assessment of the effect of the modification, alteration, or repair on the unsafe conditionaddressed by this AD; and, if the unsafe condition has not been eliminated, the requestshould include specific proposed actions to address it.
Compliance: Required as indicated in the body of this AD after the effective dateof this AD, unless already accomplished.
To prevent cracks at the wing to fuselage attach points, which, if not detectedand corrected, could cause structural failure and loss of control of the airplane,accomplish the following:
(a) For all models except Models 520, 560, 690C and 695, accomplish theactions in the following table in accordance with the Compliance section and Part I, II,and III of the ACCOMPLISHMENT INSTRUCTIONS sections of Twin CommanderService Bulletin No. 223, dated October 24, 1996 as amended by Revision Notice No.1, dated May 8, 1997 and Revision Notice No. 2, dated August 18, 1997:
TWIN COMMANDER AIRCRAFT CORPORATION
A B IC
Upon the if cracked, prior to if no cracks are
accumulation of further flight, replace found, repeat6,000 hours total the brackets and inspection at 1,000time-in-service CTIS) straps or repair the hour (hr.) intervals
PART I or within the next 100 part by an approved until cracks are
hours TIS, whichever repair scheme (see found, replace theoccurs later, install paragraph (b) of this cracked part or repair byaccess holes in left AD). Then, accomplish an approved repairand right wing leading PART II of this AD. scheme (seeedges and inspect the paragraph (b) of thisforward attach (Accomplish in AD), then accomplishbrackets and straps accordance with PART II.
for cracks. PART I of ComplianceSection in Twin Commander (Accomplish in
For any airplanes that SE 223, accordance withhave wings modified dated Oct. 24, 1996 as PART I of Compliancewith titanium leading amended by Revision Notice Section in Twin
edges through an No. 1, dated Commander SE 223,STC, remove the wing May 8, 1997 and dated Oct. 24, 1996root farlngs to Revision Notice No. 2, as amended byaccomplish the required dated August 18, 1997) Revision Notice No. 1,inspections, dated May 8, 1997in lieu of installing and Revision Noticethe access holes. No. 2, dated
August 18, 1997.)(Accomplish in
accordance with
PART I of ComplianceSection in Twin
Commander SE 223,dated Oct. 24, 1996
as amended byRevision Notice No. 1,dated May 8, 1997
and Revision Notice
No. 2, dated
August 18,1997.)
ss-os-´•ca
TWIN COMMANDER AIRCRAFT CORPORATION
A B C
Inspect for cracks at if cracked, prior to After repair or
the wing leading edge further flight, replace replacement is
close-outs, upper any cracked part or accomplished,lower return flange radius, repair the part with an continue to inspect at
PART II fuselage frame where tee approved repair 6,000 hr. intervals.
bracket attaches, inboard scheme (see paragraphside (b) of this AD). If no (Accomplish in
of attach bracket and cracks are found, accordance with
frame tee bracket, continue to repetitively PART II of Complianceinspect at 1,000 hour Section in Twin
(Acoomplish in TIS intervals. Commander SE 223,accordance with dated Oct. 24, 1996
PART II of Compliance (Accomplish in as amended bySection in Twin accordance with Revision Notice No. i,Commander SE 223, PART II of Compliance dated May 8, 1997
dated Oct. 24, 1996 Section in Twin and Revision Notice
as amended by Commander SE 223, No. 2, dated
Revision Notice No. 1, dated Oct. 24, 1996 as August 18, 1997.)dated May 8, 1997, amended by Revision Notice
and Revision Notice No. I,datedNo. 2, dated May 8, 1997 and
August 18, 1997.) Revision Notice No. 2,dated August 18,1997
For pressurized airplanes, if cracked, prior to if no cracks, repeatat further flight, repair inspection at
6,000 hr. total TIS or with an approved 1,000 hr, intervals
the next repair scheme (see until cracks are
100 hours TIS paragraph (b) of this found, then
PARTIII whicheveroccurs AD), and continue to accomplish PART III B
later, inspect fuselage inspect at 1,000 hr. of this AD.
station (F.S.) 100 for intervals.
cracks. (Accomplish in
(Accomplish in accordance with
For non-pressurized accordance with PART iii of
airplanes, at 12,000 PART III of Compliance Compliance Section in
hr. total TIS or within Section in Twin Twin Commander
the next 100 hours I Commder SE 223, SE 223, dated
SIS whichever occurs dated Oct. 24, 1996 as Oct. 24, 1996 as
later, inspect F.S. 100 amended by Revision Notice amended by Revision
for cracks. No. 1, dated Notice No. i, dated
May 8, 1997 and May 8, 1997 and
(Accomplish in Revision Notice No. 2, Revision Notice No. 2,
accordance with dated August 18, dated August 18,PART III of 1997.) 1 1997
g8-OCls
TWIN COMMANDER AIRCRAFT CORPORPITION
Compliance Section in
Twin Commander
SE 223, dated
Oct. 24, 1996 as
amended by Revision
Notice No. 1 dated
May 8, f 997 and
Revision Notice No. 2,dated August 18,1997.
(b) Obtain an FAA-approved repair scheme from the manufacturer throughthe Manager of the Seattle Aircraft Certification Office at the address specified in
paragraph (f) of this AD.
(c) For Twin Commander Models 520 and 560 airplanes, upon the
accumulation of 6,000 hours total TIS or within the next 100 hours TIS, whichever
occurs later, accomplish PART II of the table in paragraph (a) of this AD. AccomplishPART III in accordance with the compliance times in the above table of paragraph (a).These models are excluded from the wing leading edge access hole installation in
PART I of the table in paragraph (a) of this AD.
(d) For Twin Commander Models 690C and 695 airplanes, accomplishPARTS I and II in accordance with the compliance times in the above table of
paragraph (a). These Models are excluded from PART III of the table in paragraph (a)of this AD.
(e) Special flight permits may be issued in accordance with sections 21.1 97and 21.189 of the FederalAviation Regulations (14 CFR 21.197 and 21.199) to operatethe airplane to a location where the requirements of this AD can be accomplished.
(f) An altemative method of compliance or adiustment of the initial or
repetitive compliance times that provides an equivalent level of safety may be approvedby the Manager, Seattle Aircraft Certification Office, 1601 Lind Ave. S.W., Renton,Washington, 98055-4056 The request shall be forwarded through an appropriate FAAMaintenance Inspector, who may add comments and then send it to the Manager,Seattle Aircraft Certification Office.
NOTE 2: Information concerning the existence of approved alternativemethods of compliance with this AD, if any, may be obtained from the Seattle AircraftCertification Office.
(g) The inspections and installations required by this AD shall be done in
accordance with the Twin Commander Service Bulletin No. 223, dated October 24,1996 as amended by Revision Notice No. 1, dated May 8, 1997 and Revision NoticeNo. 2, dated August 18, 1997. This incorporation by reference was approved by the
as-as-is
TWIN COMMANDER AIRCRAFT CORPORATION
Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 61.
Copies may be obtained from Twin Commander Aircraft Corporation, P.O. Box 3369,Arlington, Washington, 98223. Copies may be inspected at the FAA, Central Region,Office of the Regional Counsel, Room 1558, 601 E. 12th Street, Kansas City, Missouri,or at the Office of the Federal Register, 800 North Capitol Street, NW, suite 700,Washington, DC.
(h) This amendment becomes effective on May 18, 1998.
FOR FVRTHER INFORMATION CONTACT:
Jeffrey Morfitt, Aerospace Engineer, FAA, Seattle Aircraft Certification Office, 1601 LindAve. S.W., Renton, Washington, 98055-4058; telephone (425) 227-2595; facsimile
(425) 227-1181.
9B-0&ls
TWIN COMMANDER AIRCRAFT CORPORATION
Revision issued January 1999
98-08-25 R1 TMnN COMMANDER
A1RCRAFT CORPORATION: Amendment 39-10821: Docket No. 98-CE-54-AD.
Revises AD 98-08-25, Amendment 39-10474, which superseded AD 96-12-08,Amendment 39-9650.
Applicability: The following model and serial number airplanes,ce~tificated in any catego~y:Models Serial Numbers
5005 3185, 3228, 3230, 3262, and 3291
500U 1785
680F 1195
681 6027
680V 1677
690 11035, 11053, 11068, and 11074
690A 11111, 11134,11146,11153,11173,11177,11205.11215.11237, 11249, 11271, 11273, and 11282
890B 11360, 11382, 11409, 11424, 11451, 11455, 11463, 11491,11513, 11521,11535, 11536, 11539, and 11586
690C 11638, 11643, 11676, 11689, and 11719
690D 15041
695 95010, 95033, 95044, and 95066
695A 96010, 98041,96056, and 96061
NOTE 1: This AD applies to each airplane identified in the precedingapplicability provision, regardless of whether it has been modified, altered, or
repaired in the area subject to the requirements of this AD. For airplanes that
have been modified, altered, or repaired so that the performance of the
requirements of this AD is affected, the owner/operator must request approvalfor an altemative method of compliance in accordance with paragraph (g) of this
AD. The request should include an assessment of the effect of the modification,alteration, or repair on the unsafe condition addressed by this AD; and, if the
unsafe condition has not been eliminated, the request should include specificproposed actions to address it.
Compliance: Required as indicated below, unless already accomplished:
1. For all affected airplane models, except for Model 695A airplanes:Within 75 hours time-in-service (TIS) after May 18, 1998 (the effective date of
AD 98-08-25).
TWIN COMMANDER AIRCRAFT CORPORATION
2. For Model 695A airplanes: Within the next 75 hours TIS after the
effective date of this AD.
To prevent the nose landing gear (NLG) from collapsing due to failure of a
drag link bolt, which could result in loss of control of the airplane during landingoperations, accomplish the following:
(a) For all airplane models, except for Models 690D and 695A, replacethe NLG drag link bolt, part number (P/N) ED 10055, with a new bolt in
accordance with the INSTRVCTIONS section of Twin Commander ServiceBulletin (SB) 224, Revision C, dated July 25, 1996.
(b) For airplane Models 690D and 695A, replace the NLG drag link bolt
(PIN ED 10055), with a new bolt (P/N 750076-1) in accordance with Twin
Commander SE 224, Revision C, dated July 25, 1996.
(c) The new replacement bolt must be marked with the manufacturer’s
serial number, the date of manufacture, and the last three digits of the drawingnumber, 055, on the bolthead forall but Models 690D and 695A. Models 690D
and 695A bolts must be marked with the manufacturer’s serial number, the date
of manufacture, and the last three digits of the drawing number, 76-1, on the bolt
head.
NOTE 2: Although not required by this AD, FAA highly recommends
that the removed bolt (P/N ED 10055) be retumed to Twin Commander for
Rockwell Hardness testing.
(d) For all affected airplane models, except for Models 690D and 695A
airplanes, compliance with Twin Commander SE 224, Revision A, dated April 24,1996; or Twin Commander SE 224, Revision C, dated July 25, 1996, fulfills the
applicable requirements of this AD. For the affected Models 690 and 695A
airplanes, compliance must be in accordance with Twin Commander SE 224,Revision C, dated July 25, 1998.
(e) As of the effective date of this AD, no person shall install, on anyaffected airplane, a NLG drag link bolt that does not have the manufacturer’s
serial number, manufacture date, and the last three digits of the drawing number
as specified in paragraph (8) of this AD.
(f) Special flight permits may be issued in accordance with sections
21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and
21.199) to operate the airplane to a location where the requirements of this AD
can be accomplished.
~&08-25 R1
NYIN COMMANDER AIRCRAFT CORPORAnOM
(0) An alternative method of compliance or adjustment of the
compliance time that provides an equivalent level of safety may be approved bythe Manager, Seattle Aircraft Certification Office, 1601 Lind Ave. SW, Renton,
Washington, 98055-4056. The request shall be forwarded through an
appropriate FAA Maintenance Inspector. who may add comments and then send
it to the Manager, Seattle Aircraft Certification Office.
NOTE 3: information conceming the existence of approved altemative
methods of compliance with this AD, if any, may be obtained Seattle Aircraft
Certification Office.
(h) The inspection and replacement required by this AD shall be done
in accordance with Twin Commander Service Bulletin 224, Revision C, dated
July 25, 1996. This incorporation by reference was previously approved by the
Director of the Federal Register as of May 18, 1998 (63 FR 19387, April 20,
1998). Copies may be obtained from Twin Commander Aircraft Corporation,19010 59th Drive NE, Arlington. Washington 98223-7832. Copies may be
inspected at the FAA, Central Region, Office of the Regional Counsel, Room
1558, 601 E. 12th Street, Kansas City, Missouri. or at the Office of the Federal
Register, 800 North Capitol Street, NW, suite 700, Washington, DC.
(i) This amendment revises AD 98-08-25, Amendment 39-10474,which superseded AD 96-12-08, Amendment No. 39-9650.
(j) This amendment becomes effective on January 5, 1989.
FOR FURTHER INFORMATION CONTACT:
Jeffrey Morfitt, Aerospace Engineer, FAA, Seattle Aircraft Certification Office,1601 Lind Ave. S.W., Renton, Washington, 98055-4056; telephone:(206) 227-2595; facsimile: (206) 227-1181.
48´•0&25 Al
NYIN COMMANDER AIRCRAFT CORPOR~TION
98-2O -34TWIN COMMANDER AIRCRAFT
CORPORATION: Amendment 39-10801; Docltet Na. 97-CE-57-AD.
Applicability: Models 500,-500-A, -500-8, -500-8, -500-U, -520, -560,-560-A, -560-8, -560-F, -BB0, -680-8, -B8OFL(F), -680T, -680V, -680W, -681,-685, -690, -690A,-BgOB, 690C,-690D, -695, -695A, -6958, and 720 airplanestall serial numbers), certificated in any category.
NOTE 1: This AD applies to each airplane identified in the precedingapplicability provision, regardless of whether it has been modified, altered, or
repaired in the area subject to the requirements of this AD. For airplanes that
have been modified, altered, or repaired so that the performance of the
requirements of this AD is affected, the owner/operator must request approvalfor an alternative method of compliance in accordance with paragraph (d) of
this AD. The request should include an assessment of the effect of the
modification, alteration, or repair on the unsafe condition addressed by this
AD; and, if the unsafe condition has not been eliminated, the request should
include specific proposed actions to address it.
Compliance: Required as indicated, unless already accomplished.
To minimize the potential hazards associated with operating the airplanein severe icing conditions by providing more clearly defined procedures and
limitations associated with such conditions, accomplish the following:
(a) Within 30 days after the effective date of this AD, accomplish the
requirements of paragraphs (a)(l) and (a)(2) of this AD.
NOTE 2: Operators should initiate action to notify and ensure that
flight crewmembers are apprised of this change.
(1) Revise the FAA-approved Airplane Flight Manual (AFM) byincorporating the following into the Limitations Section of the AFM. This may be
accomplished by inserting a copy of this AD in the AFM.
"WARNING
Severe icing may result from environmental conditions outside of those for
which the airplane is certificated. Flight in freezing rain, freezing drizzle, or mixed
icing conditions (supercooled liquid water and ice crystals) may result in ice
build-up on protected surfaces exceeding the capability of the ice protectionsystem, or may result in ice forming aft of the protected surfaces. This ice may
TWIN COMMANDER AIRCRAFT CORPORATION
not be shed using the ice protection systems, and may seriously degrade the
performance and controllabilny of the airplane.
During flight, severe icing conditions that exceed those for which the
airplane is certificated shall be determined by the following visual cues. If
one or more of these visual cues exists, immediately request priorityhandling from Air Traffic Control to facilitate a route or an altitude changeto exit the icing conditions.
Unusually extensive ice accumulation on the airframe and windshield in
areas not normally observed to collect ice.
Accumulation of ice on the lower surface of the wing aft of the protectedarea.
Accumulation of ice on the engine nacelles and propeller spinnersfarther aft than normally observed.
Since the autopilot, when installed and operating, may mask tactile
cues that indicate adverse changes in handling characteristics, use of the
autopilot is prohibited when any of the visual cues specified above exist, or
when unusual lateral trim requirements or autopilot trim warnings are
encountered while the airplane is in icing conditions.
Allwing icing inspection lights must be operative prior to flight into
known or forecast icing conditions at night. [Note: This supersedes any relief
provided by the Master Minimum Equipment List (MMEL).]"
(2) Revise the FAA-approved AFM by incorporating the
following into the Normal Procedures Section of the AFM. This may be
accomplished by inserting a copy of this AD in the AFM.
"THE FOLLOWING WEATHER CONDITIONS MAY BE CONDUCIVE TO
SEVERE IN-FLIGHT ICING:
Visible rain at temperatures below O degrees Celsius ambient air
temperature.
Droplets that splash or splatter on impact at temperatures below O
degrees Celsius ambient air temperature.
PROCEDURES FOR EXITING THE SEVERE ICING ENVIRONMENT:
These procedures are applicable to all flight phases from takeoff to
landing. Monitor the ambient air temperature. While severe icing may form at
98-20-34
TWIN COMMANDER AIRCRAFT CORPORATION
temperatures as cold as -18 degrees Celsius, increased vigilance is warranted
at temperatures around freezing with visible moisture present. If the visual
cues specified in the Limitations Section of the AFM for identifying severe
icing conditions are observed, accomplish the following:
Immediately request priority handling from Air Traffic Control to
facilitate a route or an altitude change to exit the severe icing conditions
in order to avoid extended exposure to flight conditions more severe than
those for which the airplane has been certificated.
Avoid abrupt and excessive maneuvering that may exacerbate control
difficulties.
Do not engage the autopilot.
If the autopilot is engaged, hold the control wheel firmly and disengagethe autopilot.
If an unusual roll response or uncommanded roll control movement is
observed, reduce the angle-of-attack.
Do not extend flaps when holding in icing conditions. Operation with
flaps extended can result in a reduced wing angle-ofattack, with the
possibility of ice forming on the upper surface further aft on the wing than
normal, possibly aft of the protected area.
If the flaps are extended, do not retract them until the airframe is
clear of ice.
Report these weather conditions to Air Traffic Control."
(b) Incorporating the AFM revisions, as required by this AD, may be
performed by the owner/operator holding at least a private pilot certificate as
authorized by section 43.7 of the FederalAviation Regulations (14 CFR 43.7),and must be entered into the aircraft records showing compliance with this AD inaccordance with section 43.9 of the Federal Aviation Regulations (14 CFR 43.9).
(c) Special flight permits may be issued in accordance with sections21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and
21.199) to operate the airplane to a location where the requirements of this AD
can be accomplished.
(d) An alternative method of compliance or adjustment of the
compliance tim$ that provides an equivalent level of safety may be approved bythe Manager, Small Airplane Directorate, FAA, 1201 Walnut, suite 900, Kansas
98-20-34
TWIN COMMANDER AIRCRAFT CORPORATION
City, Missouri 64106. The request shall be forwarded through an appropriateFAA Maintenance Inspector, who may add comments and then send it to the
Manager, SmallAirplane Directorate.
NOTE 3: Information concerning the existence of approved alternativemethods of compliance with this AD, if any, may be obtained from the Small
Airplane Directorate.
(e) All persons affected by this directive may examine informationrelated to this AD at the FAA, Central Region, Office of the Regional Counsel,Room 1558, 601 E. 12th Street, Kansas City, Missouri 64106.
(f) This amendment becomes effective on November 3, 1998.
FOR FVRTHER INFORMATION CONTACT:
Mr. John P. Dow, Sr., Aerospace Engineer, SmallAirplane Directorate, AircraftCertification Service, 1201 Walnut, suite 900, Kansas City, Missouri 64106,telephone (816) 426-6932, facsimile (816) 426-2169.
98-20-34
TWIN COMMANDIR AIRCRAFT CORPORATION
2000-02-30CORPORATION: Amendment 39-11548; Docket No. 99-CE-51-AD.
(a) What airplanes are affected by this AO?: The following Model 600 series
airplanes, all serial numbers, that are:
(1) equipped with pneumatic deicing boots; and
(2) certificated in any category.
Models
680, 680E, 680F, 680FL, 680FL(P), 680T, 680V, 680W, 681, 690, 685, 690A, 690B,690C, 690D, 695, 695A, and 6958
(b) Who must comply with this AD?: Anyone who wishes to operate any of the
above airplanes on the U.S. Register. The AD does not apply to your airplane if it is not
equipped with pneumatic de-icing boots.
(c) What problem does this AD address?: The information necessary to
activate the pneumatic wing and tail deicing boots at the first signs of ice accumulation
is critical for flight in icing conditions. If we did not take action to include this information,flight crews could experience reduced controllability of the aircraft due to adverse
aerodynamic effects of ice adhering to the airplane prior to the first deicing cycle.
(d) What must I do to address this problem?: To address this problem, youmust revise the Limitations Section of the FAA-approved Airplane Flight Manual (AFM)to include the following requirements for activation of the ice protection systems. You
must accomplish this action within the next 10 calendar days after the effective date of
this AD, unless already accomplished. You may insert a copy of this AD in the AFM to
accomplish this action:
Except for certain phases of flight where the AFM specifies that deicingboots should not be used (e.g., take´•off, final approach, and landing), compliance with
the following is required.
Wing and Tail Leading Edge Pneumatic Deicing Boot System, if installed,must be activated:
At the first sign of ice formation anywhere on the aircraft, or uponannunciation from an ice detector system, whichever occurs first; and
TWIN COMMANDER AIRCRAFT CORPORPITION
The system must either be continued to be operated in the
automatic cycling mode, if available; or the system must be manually cycled as needed
to minimize the ice accretions on the airframe.
The wing and tail leading edge pneumatic deicing boot system may be
deactivated only after leaving icing conditions and after the airplane is determined to be
clear of ice."
(e) Can the pilot accomplish the action?: Yes. Anyone who holds at least a
private pilot certificate, as authorized by section 43.7 of the Federal Aviation
Regulations (14 CFR 43.7), may incorporate the AFM revisions required by this AD.
You must make an entry into the aircraft records that shows compliance with this AD, in
accordance with section 43.9 of the Federal Aviation Regulations (14 CFR 43.9).
(f) Can I comply with this AD in any other way?: Yes.
(1) You may use an alternative method of compliance or adjust the
compliance time if:
(i) Your alternative method of compliance provides an
equivalent level of safety; and
(ii) The Manager, Small Airplane Directorate, approves
your alternative. Submit your request through an FAA Principal Maintenance Inspector,who may add comments and then send it to the Manager.
(2) This AD applies to each airplane identified in the precedingapplicability provision, regardless of whether it has been modified, altered, or repaired in
the area subject to the requirements of this AD. For airplanes that have been modified,altered, or repaired so that the performance of the requirements of this AD is affected,the owner/operator must request approval for an alternative method of compliance in
accordance with paragraph (f)(l) of this AD. The request should include an assessment
of the effect of the modification, alteration, or repair on the unsafe condition addressed
by this AD: and, if you have not eliminated the unsafe condition, specific actions you
propose to address it.
(g) Where can I get information about any already-approved alternative
methods of compliance?: Contact the Small Airplane Directorate, 901 Locust, Room
301, Kansas City, Missouri 64106; telephone: (816) 329-4121;facsimile:(316)329-4091.
(h) What if I need to fly the airplane to another location to comply with this
AD?: The FAA can issue a special flight permit under sections 21.197 and 21.199 of the
Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate your airplane to a
location where you can accomplish the requirements of this AD.
2000-02-30
TWIN COMMANDER AIRCRAFT CORPORATION
(i) When does this amendment become effective?: This amendment
becomes effective on March 24, 2000.
FOR FURTHER INFORMATION CONTACT:Mr. John P. Dow, Sr., Aerospace Engineer, FAA, Small Airplane Directorate, 901
Locust, Room 506, Kansas City, Missouri 64106; telephone: (816) 329-4121: facsimile:
(816)329-4090.
Issued in Kansas City, Missouri, on January 25, 2000.
Michael Gallagher, Manager, Small Airplane Directorate, Aircraft Certification Service
2000-02-30
TWIN COMMANDER AIRCRAFT CORPORATION
2003-07-03Tlin Commander lircran
Corporation: Amendment 39-13099; Docket No. 2000-CE-56-AD.
(a) What airplanes are affected by this AD? This AD affects the following Twin
Commander Aviation Corporation (TCAC) airplane models and serial numbers that are
certificated in any category:
Model Serial Nos.
690D 15001 through 15036 and 15038 through 15040.
695A96001 through 96062, 96065 through 96068, 96070, 96071,96073, 96074, 96076, 96077,and 96079 through 96084, 96086, 96087, and 96089 through 96100.
6958 96063, 96069, 96075, 96078, 96085, and 96204 through 96208.
(b) Who must comply with this AD? Anyone who wishes to operate any of the
airplanes identified in paragraph (a) of this AD must comply with this AD.
(c) What problem does this AD address? The actions specified by this AD are
intended to detect and correct fatigue damage in the wing and fuselage areas without
reducing the service life of the airplane. Such undetected and uncorrected damagecould result in structural failure with consequent loss of control of the airplane.
(d) What must I do to address this problem? To address this problem, youmust initially inspect and modify the wing and fuselage areas (Part 1
Inspection/Modifications as identified in Twin Commander Aircraft CorporationMandatory Service Bulletin No. 214, dated January 26, 2000) and repetitively inspectwith necessary modification or replacement of damaged parts (Part 2 Recurrent
Inspections as identified in Twin Commander Aircraft Corporation Mandatory Service
Bulletin No. 214, dated January 26, 2000) in accordance with the following schedules:
(1) Part 1 Initial Inspections/Modifications: Initially (unless alreadydone) accomplish the Part 1 Inspections/Modifications at whichever compliance time in
paragraph (d)(l)(i) or (d)(l)(ii) of this AD that occurs later:
(i) the compliance times presented in Part 1 Table 1 of Twin
Commander Aircraft Corporation Mandatory Service Bulletin No. 214, dated January 26,2000; Twin Commander Aircraft Corporation Service Publications revision notice to
Service Bulletin No. 214, Revision 1, Release Date: April 19, 2000; and Twin
Commander Aircraft Corporation Service Publications revision notice to Service Bulletin
No. 214, Revision 2, Release Date: May 21, 2001; or
TWIN COMMANDER AIRCRAFT CORPORATION
(ii) the Table A compliance times presented on page 1 of the
service information and replicated below:
Current airframe hours Initial compliance time
time-in-service (TIS)
(A) 0000 through 1,700 Upon accumulating 2,700 hours TIS or within the next 36 months after May16, 2003 (the effective date of this AD), whichever occurs first.
(B) 1,701 through 2,500 Upon accumulating 3,400 hours TIS or within the next 36 months after May16, 2003 (the effective date of this AD), whichever occurs first.
(C) 2,501 through 3,000 Upon accumulating 3,800 hours TIS or within the next 36 months after May16, 2003 (the effective date of this AD), whichever occurs first.
(D) 3,001 through 5,000 Upon accumulating 5,500 hours TIS or within the next 30 months after May16, 2003 (the effective date of this AD), whichever occurs first.
(E) 5,001 through 6,000 Upon accumulating 6,400 hours TIS or within the next 24 months after May16, 2003 (the effective date of this AD), whichever occurs first.
(F) 6,001 through 7,500 Upon accumulating 7,800 hours TIS or within the next 18 months after May16, 2003 (the effective date of this AD), whichever occurs first.
(G) Over 7,500 Within the next 12 months after May 16, 2003 (the effective date of this AD).
(2) Part 2 Recurring Inspections: Repetitively inspect as referenced in
Part 2 Recurring Inspections on page 62 of Twin Commander Aircraft CorporationMandatory Service Bulletin No. 214, dated January 26, 2000; Twin Commander Aircraft
Corporation Service Publications revision notice to Service Bulletin No. 214, Revision 1,Release Date: April 19, 2000; and Twin Commander Aircraft Corporation Service
Publications revision notice to Service Bulletin No. 214, Revision 2, Release Date: May21,2001.
(3) Mandatory Replacements and Modifications: If any damage is
found during any inspection required by paragraphs (d), (d)(l), and (d)(2) of this AD,prior to further flight, replace or modify the part as specified in the following:
(i) Twin Commander Aircraft Corporation Mandatory Service
Bulletin No. 214, dated January 26, 2000;
(ii) Twin Commander Aircraft Corporation Service Publications
revision notice to Service Bulletin No. 214, Revision 1, Release Date: April 19, 2000;and
(iii) Twin Commander Aircraft Corporation Service Publications
revision notice to Service Bulletin No. 214, Revision 2, Release Date: May 21, 2001.
(e) Can I comply with this AD in any other way? You may use an alternative
method of compliance or adjust the compliance time if:
2003-07-03
TWIN COMMANDER AIRCRAFT CORPORATION
(1) Your alternative method of compliance provides an equivalent level
of safety; and
(2) The Manager, Seattle Aircraft Certification Office (ACO), approves
your alternative. Submit your request through an FAA Principal Maintenance Inspector,who may add comments and then send it to the Manager, Seattle AGO.
Note: This AD applies to each airplane identified in paragraph (a) of this
AD, regardless of whether it has been modified, altered, or repaired in the area subjectto the requirements of this AD. For airplanes that have been modified, altered, or
repaired so that the performance of the requirements of this AD is affected, the
owner/operator must request approval for an alternative method of compliance in
accordance with paragraph (e) of this AD. The request should include an assessment of
the effect of the modification, alteration, or repair on the unsafe condition addressed bythis AD; and, if you have not eliminated the unsafe condition, specific actions you
propose to address it.
(f) Where can I get information about any already-approved alternative
methods of compliance? Contact Della Swartz, Aerospace Engineer, FAA, Seattle
Aircraft Certification Office, 1601 Lind Avenue, SW, Renton, Washington 98055-4065;telephone: (425) 687-4246; facsimile: (425) 687-4248.
(g) What if I need to fly the airplane to another location to comply with this
AD? The FAA can issue a special flight permit under sections 21.197 and 21.199 of the
Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate your airplane to a
location where you can accomplish the requirements of this AD.
(h) Are any service bulletins incorporated into this AD by reference? Actions
required by this AD must be done in accordance with Twin Commander Aircraft
Corporation Mandatory Service Bulletin No. 214, dated January 26, 2000; Twin
Commander Aircraft Corporation Service Bulletin No. 214, Revision 1, Release Date:
April 19, 2000; and Twin Commander Aircraft Corporation Service Bulletin No. 214,Revision 2, Release Date: May 21, 2001. The Director of the Federal Register approvedthis incorporation by reference under 5 U.S.C. 552(a) and 1 CFR part 51. You may getcopies from Twin Commander Aircraft Corporation, 19010 59th Drive N.E., Arlington,Washington 98223-7832; telephone: (360) 435-9797; facsimile: (360) 435-1112. You
may view copies at the FAA, Central Region, Office of the Regional Counsel, 901
Locust, Room 506, Kansas City, Missouri, or at the Office of the Federal Register, 800
North Capitol Street, NW., suite 700, Washington, DC.
(i) When does this amendment become effective? This amendment becomes
effective on May 16, 2003.
2003-07-03
TWIN COMMANDER AIRCRAFT CORPORATION
FOR FURTHER INFORMATION CONTACT: Della Swartz, Aerospace Engineer, FAA,Seattle Aircraft Certification Office, 1601 Lind Avenue, SW., Renton, Washington98055-4065; telephone: (425) 687-4246; facsimile: (425) 687-4248.
Issued in Kansas City, MO, on March 25, 2003.
Michael Gallagher, Manager, Small Airplane Directorate, Aircraft Certification Service.
2003-07-03
TWIN COMMANDER AIRCRAFT CORPORATION