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CN-235 MAINTENANCE MANUAL

CHAPTER 61

LIST OF EFFECTIVE PAGES

CHAPTER

SUBJECT PAGE DATE

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List ofEffectivePage 1 May 15/15 2 May 15/15 3 May 15/15 4 May 15/15 5 May 15/15 6 May 15/15

Table ofContents 1 May 15/15 2 May 15/15 3 May 15/15 4 May 15/1561-00-00 1 Jul. 31/93 2 Jul. 31/9361-10-00CONFIG.1 1 Jul. 31/06 2 Jul. 31/06 3 Jul. 31/06

4 Jul. 31/06 5 Jul. 31/06 6 Jul. 31/06 7 Jul. 31/06 8 Jul. 31/0661-10-00 501 May 15/15 502 May 15/15 503 May 15/15 504 May 15/15 505 May 15/15 506 May 15/15 507 May 15/15 508 May 15/15 509 May 15/15 510 May 15/15 511 May 15/15 512 May 15/15 513 May 15/15 514 May 15/15

515 May 15/15 516 May 15/15 517 May 15/15 518 May 15/15 519 May 15/15 520 May 15/15 521 May 15/15 522 May 15/15 523 May 15/15

524 May 15/15 525 May 15/15 526 May 15/15 601 May 15/15 602 May 15/15 603 May 15/15 604 May 15/15 605 May 15/15 606 May 15/15 607 May 15/15 608 May 15/15 609 May 15/15 610 May 15/15

701 Mar. 31/00 702 Mar. 31/00 703 Mar. 31/00 704 Mar. 31/0061-10-10 401 May 15/13 402 May 15/13 403 May 15/13 404 May 15/13 405 May 15/13 406 May 15/13 407 May 15/13 408 May 15/13 409 May 15/13 410 May 15/13 411 May 15/13 412 May 15/13 413 May 15/13 414 May 15/13 415 May 15/13

Effectivity: OM01 61 - LEP Pag. 1

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416 May 15/13

61-20-00CONFIG.1 1 Jun. 30/02 2 Jun. 30/02 3 Jun. 30/02 4 Jun. 30/02 5 Jun. 30/02 6 Jun. 30/02 7 Jun. 30/02 8 Jun. 30/02 9 Jun. 30/02 10 Jun. 30/02 11 Jun. 30/02 12 Jun. 30/02

13 Jun. 30/02 14 Jun. 30/02 15 Jun. 30/02 16 Jun. 30/02 17 Jun. 30/02 18 Jun. 30/02 19 Jun. 30/02 20 Jun. 30/02 21 Jun. 30/02 22 Jun. 30/02 23 Jun. 30/02 24 Jun. 30/02 25 Jun. 30/02

26 Jun. 30/02 27 Jun. 30/02 28 Jun. 30/02 29 Jun. 30/02 30 Jun. 30/02 31 Jun. 30/02 32 Jun. 30/02 33 Jun. 30/02 34 Jun. 30/02 35 Jun. 30/02 36 Jun. 30/02 37 Jun. 30/02 38 Jun. 30/02 39 Jun. 30/02 40 Jun. 30/02 41 Jun. 30/02 42 Jun. 30/0261-20-00 101 Jun. 01/99 102 Jun. 01/99

103 Jun. 01/99 104 Jun. 01/99

105 Jun. 01/99 106 Jun. 01/99 301 May 15/15 302 May 15/15 303 May 15/15 304 May 15/15 305 May 15/15 306 May 15/15 307 May 15/15 308 May 15/15 309 May 15/15 310 May 15/15 501 Nov. 15/13

502 Nov. 15/13 503 Nov. 15/13 504 Nov. 15/13 505 Nov. 15/13 506 Nov. 15/1361-20-10 401 Oct. 15/00 402 Oct. 15/00 403 Oct. 15/00 404 Oct. 15/0061-20-11CONFIG.2 401 Jun. 30/02

402 Jun. 30/02 403 Jun. 30/02 404 Jun. 30/0261-20-12CONFIG.2 1 Jun. 30/02 2 Jun. 30/02 3 Jun. 30/02 4 Jun. 30/02 5 Jun. 30/02 6 Jun. 30/0261-20-12CONFIG.1 401 Oct. 15/00 402 Oct. 15/00 403 Oct. 15/00 404 Oct. 15/0061-20-13 401 Mar. 31/00 402 Mar. 31/00


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403 Mar. 31/00

404 Mar. 31/00

61-20-14 401 Mar. 31/00 402 Mar. 31/00 403 Mar. 31/00 404 Mar. 31/0061-20-15 401 Mar. 31/00 402 Mar. 31/00 403 Mar. 31/00 404 Mar. 31/0061-20-16 401 Jul. 30/08 402 Jul. 30/08

403 Jul. 30/08 404 Jul. 30/08 405 Jul. 30/08 406 Jul. 30/0861-20-17CONFIG.1 401 Jun. 30/02 402 Jun. 30/02 403 Jun. 30/02 404 Jun. 30/02 405 Jun. 30/02 406 Jun. 30/02

61-20-18 401 Mar. 31/00 402 Mar. 31/00 403 Mar. 31/00 404 Mar. 31/0061-20-19 401 Mar. 31/00 402 Mar. 31/00 403 Mar. 31/00 404 Mar. 31/0061-26-00CONFIG.1 1 Nov. 30/97 2 Nov. 30/97 3 Nov. 30/97 4 Nov. 30/97 5 Nov. 30/97 6 Nov. 30/97CONFIG.2 1 Mar. 01/99 2 Mar. 01/99

3 Mar. 01/99 4 Mar. 01/99

5 Mar. 01/99 6 Mar. 01/99 7 Mar. 01/99 8 Mar. 01/99 9 Mar. 01/99 10 Mar. 01/99 11 Mar. 01/99 12 Mar. 01/99 13 Mar. 01/99 14 Mar. 01/9961-26-00CONFIG.1 101 Nov. 30/97

102 Nov. 30/97 103 Nov. 30/97 104 Nov. 30/97CONFIG.2 101 Mar. 01/99 102 Mar. 01/99 103 Mar. 01/99 104 Mar. 01/9961-26-00CONFIG.1 501 Nov. 15/14 502 Nov. 15/14 503 Nov. 15/14

504 Nov. 15/14CONFIG.2 501 Dec. 15/10 502 Dec. 15/10 503 Dec. 15/10 504 Dec. 15/10 505 Dec. 15/10 506 Dec. 15/10 507 Dec. 15/10 508 Dec. 15/10 509 Dec. 15/10 510 Dec. 15/10 511 Dec. 15/10 512 Dec. 15/1061-26-01CONFIG.1 401 Jun. 30/02 402 Jun. 30/02 403 Jun. 30/02 404 Jun. 30/02


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61-26-02 401 Mar. 31/00

402 Mar. 31/00 403 Mar. 31/00 404 Mar. 31/0061-30-00 1 Jul. 31/93 2 Jul. 31/9361-31-00CONFIG.1 1 Jun. 01/99 2 Jun. 01/99 3 Jun. 01/99 4 Jun. 01/99 5 Jun. 01/99

6 Jun. 01/99 7 Jun. 01/99 8 Jun. 01/99 9 Jun. 01/99 10 Jun. 01/99 11 Jun. 01/99 12 Jun. 01/99 13 Jun. 01/99 14 Jun. 01/99 15 Jun. 01/99 16 Jun. 01/99CONFIG.1 101 Jul. 01/98

102 Jul. 01/98 103 Jul. 01/98 104 Jul. 01/98 105 Jul. 01/98 106 Jul. 01/9861-31-00 301 Dec. 15/08 302 Dec. 15/08 303 Dec. 15/08 304 Dec. 15/08 501 Dec. 15/08 502 Dec. 15/08 503 Dec. 15/08 504 Dec. 15/08 505 Dec. 15/08 506 Dec. 15/08 507 Dec. 15/08 508 Dec. 15/08 509 Dec. 15/08 510 Dec. 15/08

511 Dec. 15/08 512 Dec. 15/08

513 Dec. 15/08 514 Dec. 15/08 515 Dec. 15/08 516 Dec. 15/08 517 Dec. 15/08 518 Dec. 15/08 519 Dec. 15/08 520 Dec. 15/0861-31-11 401 Dec. 15/08 402 Dec. 15/08 403 Dec. 15/08 404 Dec. 15/08

405 Dec. 15/08 406 Dec. 15/0861-31-12 401 Dec. 15/08 402 Dec. 15/08 403 Dec. 15/08 404 Dec. 15/08 405 Dec. 15/08 406 Dec. 15/0861-31-13 401 Mar. 31/00 402 Mar. 31/00 403 Mar. 31/00

404 Mar. 31/0061-31-14 401 Dec. 15/08 402 Dec. 15/08 403 Dec. 15/08 404 Dec. 15/08 405 Dec. 15/08 406 Dec. 15/08 601 Dec. 15/08 602 Dec. 15/08 603 Dec. 15/08 604 Dec. 15/08 605 Dec. 15/08 606 Dec. 15/0861-40-00CONFIG.1 1 Jul. 31/06 2 Jul. 31/06 3 Jul. 31/06 4 Jul. 31/06


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5 Jul. 31/06

6 Jul. 31/06

61-40-00 101 Jul. 31/93 102 Jul. 31/93 601 Mar. 31/00 602 Mar. 31/00 603 Mar. 31/00 604 Mar. 31/00


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INTENTIONALLY LEFT BLANK


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CHAPTER 61

TABLE OF CONTENTS

CHAPTER/SUBJECT SECTION PAGE EFF.

PROPELLERS 61-00-00 All

Description/Operation 1

PROPELLER ASSEMBLY 61-10-00 SERIES 100

Description/Operation CONFIG.1 1


Adjustment/Test 501

Inspection/Check 601

Cleaning/Painting 701


Removal/Installation 401

PROPELLER CONTROLLING 61-20-00 SERIES 100


PROPELLER CONTROLLING 61-20-00 SERIES 100

Troubleshooting 101

Servicing 301

Adjustment/Test 501

SYNCHROPHASING CONTROL UNIT, KD3 61-20-10 SERIES 100

Effectivity: OM01 61 - TOC Pag. 1

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SWITCHER, KC80 61-20-11 OM01 POST.SB.235-61-04M

Removal/Installation CONFIG.2 401

FEATHER SYST CONTROL UNIT, KC50 61-20-12


FEATHER SYST CONTROL UNIT, KC50 61-20-12 SERIES 100


AUXILIARY PUMP, KC41 (KC42) 61-20-13 SERIES 100


OVERSPEED GOVERNOR, KC37 (KC38) 61-20-14 SERIES 100


PRESSURE SWITCH, KC33 (KC34) 61-20-15 SERIES 100


CONTROL ADAPTER ASSEMBLY 61-20-16 SERIES 100


TIMER, KC15 (KC16) 61-20-17 SERIES 100


AUTOFEATHER COMPUTER, KC43 61-20-18 SERIES 100



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MAGNETIC SENSOR, KD4 (KD5) 61-20-19 SERIES 100


FLIGHT IDLE SOLENOID OVERRIDECIRCUIT

61-26-00

Description/Operation CONFIG.1 1 OM01 PRE.SB.235-76-06M

Description/Operation CONFIG.2 1 OM01 POST.SB.235-76-06M


61-26-00

Troubleshooting CONFIG.1 101 OM01 PRE.SB.235-76-06MTroubleshooting CONFIG.2 101 OM01 POST.SB.235-76-06M


61-26-00

Adjustment/Test CONFIG.1 501 OM01 PRE.SB.235-76-06M

Adjustment/Test CONFIG.2 501 OM01 POST.SB.235-76-06M

REVERSE CONTROL UNIT, KB48 61-26-01 OM01 POST.SB.235-76-06M


FILTER UNIT, KB56 61-26-02 OM01 POST.SB.235-76-06M


BRAKING 61-30-00 All

Description/Operation 1

PROPELLER BRAKE SYSTEM 61-31-00 SERIES 100



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Troubleshooting CONFIG.1 101

PROPELLER BRAKE SYSTEM 61-31-00 All

Servicing 301

Adjustment/Test 501

PROPELLER BRAKE CONTROL VALVE 61-31-11 All


QUICK DISCONNECT COUPLINGS 61-31-12 All


PRESSURE SWITCH KE11, KE12 61-31-13 All


PROPELLER BRAKE HEAD ASSEMBLY 61-31-14 All



PROPELLER INDICATING 61-40-00 SERIES 100


PROPELLER INDICATING 61-40-00 SERIES 100

Troubleshooting 101



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DESCRI PTI ON/ OPERATI ON

Gener al


PROPELLERS

1.

The propel l er s i nst al l ed on t he ai r cr af t ar e Hami l t on Standar d Type14RF- 21, f our - bl aded, var i abl e pi t ch, f eat her i ng pr opel l er assembl i es( Ref . 61- 10- 00, P. Bl ock 1) .

Pi t ch and f eat her i ng cont r ol i s done t hr u a pr opel l er cont r ol uni t and anauxi l i ar y f eat her i ng pump ( Ref . 61- 20- 00, P. Bl ock 1) i nstal l ed on t hepr opel l er gear box ( Ref . 71- 00- 00, P. Bl ock 1) .

To l et t he RH engi ne be used as an auxi l i ar y power uni t dur i ng groundoper at i ons, t he RH pr opel l er can be pr event ed f r om t ur ni ng thru apr opel l er br ake uni t i nst al l ed on t he f r on of t he pr opel l er gear box

( Ref . 61- 30- 00, P. Bl ock 1) .

A phase synchr oni zat i on syst emi s used t o r educe t he l evel of noi se andvi br at i on ( Ref . 61- 20- 00, P. Bl ock 1) .

Ef f ecti vi t y: See TOC61-00-00 Pag. 1

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Ef f ecti vi t y: See TOC

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DESCRIPTION/OPERATION

General

Component Location (Fig. 1)

Description (Fig. 2)


PROPELLER ASSEMBLY

1.

The propellers are four bladed assemblies, with hydraulically controlledvariable pitch, feathering and reverse capability.

Pitch and feathering controls is done thru a propeller control unit and anauxiliary oil pump using oil from the propeller gearbox sump(Ref. 61-20-00, P. Block 1).

2.

ITEM FIN DESIGNATION ZONE ACCESSPANEL

REFERENCE

(1) Propeller LH

Assembly RH410420

411421

61-10-10

3.

The propeller assembly is made up of a propeller hub (2), four bladeassemblies (20), blade to hub retention mechanism, pitch change actuator(15), spinner, backing bulkhead (10), oil transfer tube (5) and propellerto gearbox attachment bolts.

Each blade assembly has a solid aluminum alloy spar with an externalglass-reinforced plastic (GRP) airfoil bonded to the spar. The leading andtrailing edges of the airfoil are filled with low-density, polyurethanefoam. The leading edge of each blade is protected from erosion by a nickelsheath external (1). De-icing of the blades is done thru selectable dualcycle heaters with a 10-second ON, 60-second OFF or 20-second ON,60-second OFF operating mode. Each blade is protected from lighteningstrikes by an integral tip strap.

Each blade is installed in a one-piece aluminum alloy hub by hardenedsteel bearing races and nylon ball separators (13). The bearing races areheld in position by an outer nylon retainer (21). To prevent loss of

lubrication, each blade root is sealed in the hub by a retaining joint(12), (22).

Effectivity: See TOC 61-10-00

CONFIG. 1Pag. 1

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Propellers - Component Location

CM1.61.10.00.0AO.00.01-00


Fig. 1Propellers - Component Location


CONFIG. 1Pag. 2

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Operation (Fig. 3)


Each blade is statically held in position in its bearing race by atwo-piece, molded plastic retaining ring, which is also the attachmentpoint for the blade de-icing electrical leads.

A GRP bulkhead (10) is installed on the rear of the hub to give support tothe aluminum spinner, which is fastened by twelve tri-wing screws (11). On

the rear of the bulkhead, slip rings (8) are bonded which transferelectrical power supply to the blade de-icing heaters.

A magnetic sensor (4) on the rear of the propeller bulkhead (10) is usedto sense the RPM of the propeller for the synchrophaser of the propellercontrol system.

After assembly, the propeller is balanced by installing special bolts,washer and nuts (9) in the propeller bulkhead.

The propeller hub rear face is machined with fourteen holes. Twelve holesare used for the twelve bolts which fasten the propeller to the gearbox.Two opposing holes (7) are used to engage with dowels on the gearbox drive

shaft flange. The twelve attachment bolts are held in a bolt torque plateby means of a locking flange on the inner face of the rear hub section.

To prevent loss of lubrication, seals (6), (19) are installed between thehub and gearbox drive shaft flange, and between the front face of the hub(2) and the pitch change cylinder (15).

The pitch change cylinder (15) is fastened to the front face of the hub bytwelve bolts, and holds an actuator piston (16) and integral yoke, afour-way metering valve assembly (17) and a pitchlock screw (14). An oiltransfer tube (5), installed thru the center of the cylinder, receivespitch change oil from the gearbox sump via the propeller control and agearbox driven main pump.

4.

The propeller is driven by the engine thru a propeller speed reductiongearbox. The propeller and propeller pitch control are installed on acommon centerline and are connected together by the oil transfer tube (5). The oil transfer torque tube transfers supply oil from the gearboxdriven oil pump via the propeller control unit to the four-way meteringvalve (7) in the propeller pitch change assembly.


CONFIG. 1Pag. 3

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Propellers - General Arrangement

CM1.61.10.00.0BO.00.01-00


Fig. 2Propellers - General Arrangement


CONFIG. 1Pag. 4

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Pitch change signals from the propeller control unit are supplied via theoil transfer torque tube (4) to drive the acme pitchlock screw (6) in thepitch change assembly. Turning the pitchlock screw (6) moves the meteringvalve (7) which connects the supply pressure oil to one side of theactuator piston (1) and the other side of the piston to return. Supplypressure oil can now act on the piston (1) and move it in the selected

direction. Movement of the piston (1) is transferred to the blades (9)thru the yoke (2) and blade pins (3). At the same time, the pitchlockscrew nut (5) is moved to the closed (null) position and the blades arehydraulically locked at the signalled pitch angle.

A. Increasing Propeller Pitch

Turning the pitchlock screw (6) counterclockwise (viewed from therear) advances the pitchlock screw forward in the yoke (2). Thismovement operates the metering valve (7) which opens to direct supplypressure oil to the increase pitch side of the actuator piston andconnects the decrease pitch side of the piston to return. The supplypressure oil moves the piston (1), yoke (2) and pitchlock screw nut

(5) rearward to push the yoke trunnion arms and blade pin (3) turningthe blades to increase the pitch angle.

The metering valve (7) is kept open by continued propeller controlunit output to the pitchlock screw (4) until the required blade angleis reached. When the control unit output is removed, continuedrearward movement of the yoke (2) closes the metering valve (7) tocomplete the pitch change actuation.

B. Decreasing Propeller Pitch

To move the blades towards decrease pitch, the pitchlock screw (6) isturned clockwise. This movement opens the metering valve (7) to

direct supply pressure oil to the decrease pitch side of the actuatorpiston (1) and connects the increase pitch side of the piston toreturn. The supply pressure oil moves the piston (1), yoke (2) andpitchscrew nut (5) forward pulling the yoke trunnion arms andbladepin (3) turning the blades to decrease the pitch angle.

When the propeller control unit senses that the blades are at therequired angle, control unit output is removed and the metering valve(7) is closed by the null action of the final movement of the yoke(2) to complete the pitch change actuation.


CONFIG. 1Pag. 5

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Variable Pitch Propeller Operation - Schematic

CM1.61.10.00.0CO.00.01-00


Fig. 3Variable Pitch Propeller Operation - Schematic


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Interfaces


C. Pitchlock Gap

During pitch changes, the pitchlock screw (6) is moved to maintain apitchlock gap of approximately 1 of blade angle 0,030 in (0,76mm).This pitchlock gap makes certain that blade pitch will not decrease

if supply pressure oil fails. The pitchlock screw (6) acts as a lowpitch stop since the blades cannot decrease pitch more than 1 fromthe selected pitch angle.

Normal aerodynamic and centrifugal forces acting on the propeller tryto turn the blades to low pitch. If supply pressure oil fails whenthe blades are at a positive pitch angle, the blades will try to movethe yoke (2), pitchlock screw (6) and metering valve (7) forward inthe pitch charge cylinder (8). Significant movement is prevented bythe pitchlock feature. The yoke (2) can only move thru the 1 bladeangle of the pitchlock gap.

Pitchlock occurs when the pitchlock screw (6) is touching the body of

the pitch change metering valve.

Actuation of the yoke (2) and blades (9) will be possible when supplyoil pressure is available again.

D. Blade De-icing System (Fig. 2)

The de-icing system uses face-type slip rings (8) which are bonded tothe rear of the propeller bulkhead (10).

The slip rings (8) transfer electrical power from the fixed supply tothe turning propeller blade heaters integrally molded into the bladeleading edges.

5.

The propeller assemblies interface with the following systems orsub-systems:

- Propeller De-icing System (Ref. 30-61-00, P. Block 1)

- Propeller Controlling (Ref. 61-20-00, P. Block 1).


CONFIG. 1Pag. 7

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Effectivity: See TOC

61-10-00CONFIG. 1

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ADJUSTMENT/TEST

Propeller Dynamic Balance (using the Dinamic Balancer/Analyzer Kit ITEM61-10-14)


PROPELLER ASSEMBLY

WARNING: BEFORE ELECTRICAL POWER IS SUPPLIED TO THE AIRCRAFT, MAKE SURE THATELECTRICAL CIRCUITS UPON WHICH WORK IS IN PROGRESS ARE ISOLATED.

WARNING: BEFORE STARTING ENGINES, MAKE SURE THAT WARNING NOTICES AREPOSITIONED MARKING DANGER AREAS.

WARNING: ADMIT AUTHORIZED PERSONNEL ONLY AND MAKE SURE THAT THEY AREADEQUATELY BRIEFED.

WARNING: WEAR EAR DEFENDERS WHEN WORKING ON, OR IN THE VICINITY OF, RUNNINGENGINES. DO NOT WEAR OTHER HEADGEAR OR LOOSE ARTICLES OF CLOTHING.

WARNING: MAKE SURE THAT ADEQUATE FIRE FIGHTING FACILITIES ARE READILYAVAILABLE.

WARNING: MAKE SURE THAT AREA IN VICINITY OF PROPELLERS IS CLEAR AND FREEFROM LOOSE OBJECTS.

1.

A. Reason for the Job

To measure the vibration value of the propeller assembly and do thePropeller Dynamic Balance if required.

B. Equipment and Materials

ITEM DESIGNATION

(1) ITEM 20-15-01 Circuit Breakers Safety Clips and Tags

(2) ITEM 23-00-02 Headsets

(3) ITEM 61-10-14 Dynamic Balancer/Analyzer Kit

(4) ITEM 61-10-21 Dynamic Balancer/Analyzer Harness

(5) Standard Tool Servicing Platform

(6) Standard Tool Ear Defenders

(7) Standard Tool Stopwatch(8) Standard Tool Warning Notices

(9) Z-24.301 Adhesive Tape

Effectivity: See TOC 61-10-00 Pag. 501

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Procedure


ITEM DESIGNATION

(10) AN970-3 Washer

(11) AN960-10 Washer

(12) AN960-10L Washer

(13) NAS603-18 Screw

(14) MS21083 Nut

Referenced Procedures:

- 06-41-51, P. Block 1 -Access Provision - Interior- 06-41-54, P. Block 1 -Access Provision - Nacelles- 24-40-00, P. Block 201 -External Power- 61-10-10, P. Block 401 - Propeller Assembly- 71-00-00, P. Block 501 - Powerplant- 71-20-00, P. Block 1 - Mounts

C.

(1) Job Set-Up

(a) Put the aircraft in position facing into the wind. Make surethat the dangerous area around the engine exhaust fumes isclear.

(b) Put warning notices in position around aircraft prohibitingunauthorized personnel or equipment.

(c) Make sure that all the landing gear wheels are chocked andthe Nose Landing Gear is centralized.

(d) Make sure that the fire fighting equipment is in position.

(e) Remove the engine intake covers, exhaust blanks, pitot headcovers and static vent plugs.

(f) Open, safety and tag with ITEM 20-15-01these circuitbreakers:

PANEL SERVICE FIN

BATTERY BUS 1 START KA1

L MISCELLANEOUS SYNC PROP KD1


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(g) Put the access platform in the applicable engine.

(2) Equipment Installation

(a) Velocimeters Installation on PGB (Fig. 501).

1 Remove the right forward cowling 412AR at the leftengine, and 422AR at the right engine(Ref.06-41-54, P. Block 1).

2 Locate the bracket (3) that is installed in the RightAnti-vibration Mount that attaches the right side ofthe engine PGB to the forward mount(Ref.71-20-00, P. Block 1).

3 Install the velocimeter (4) (p/n 7310 included in thekit ITEM 61-10-14)in the bracket (3). Use the AN970-3(2) washer and the 0,25-28 NYLOC Nut (1).

NOTE: Make sure that the connector of the velocimeter

points to the RH at horizontal position .

4 Connect the connector (5) to the velocimeter connector.

(b) Installation of the Velocimeters Cables (Fig. 502).

1 Open the right access doors 413AR and 423AR(Ref.06-41-54, P. Block 1).

2 Put the velocimeter cables (P/N:11212-100 included inthe kit ITEM 61-10-14)out of the engine through thestarter/generator air inlet.

CAUTION: MAKE SURE THAT THERE IS NO INTERFERENCE

BETWEEN THE SECTION OF THE VELOCIMETER CABLEINSIDE THE ENGINE COWLINGS AND THE ENGINECONTROL CABLES OR MOVING PARTS.

CAUTION: MAKE SURE THAT THE SECTION OF THE VELOCIMETERCABLE INSIDE THE ENGINE COWLINGS IS CLEARFROM HOT PARTS.

3 Close the right access doors 413AR and 423AR(Ref.06-41-54, P. Block 1).

4 Put the velocimeter cables over the wings, along therear fuselage and inside the main compartment through


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the rear door.

CAUTION: MAKE SURE NOT TO CLOSE THE REAR DOOR, THIS

CAN CAUSE DAMAGE TO THE CABLE.

NOTE: For security, use tape Z-24.301at intervals to

keep the cable held to the aircraft.

5 Put the velocimeter cables into the cockpit.

NOTE: Put marks (LH or RH) in the cable ends to

indicate the propeller which signal transmit.

(c) Disconnection of the Syncrophaser Control Unit, KD3 (Fig.503).

1 Open access pannel 222CR (Ref.

06-41-51, P. Block 1).

2 In the electrical rack locate the Syncrophaser ControlUnit, KD3 (1).

3 Disconnect the electrical connector (3) from theSyncrophaser Control Unit, KD3 (1). Put a cap on theSyncrophaser Control Unit receptacle (2).

(d) Installation of the Test Equipment in the Cockpit (Fig.504).

1 Put the Signal Selector (P/N 8520C included in the kitITEM 61-10-14)in the cockpit.

2 Put the Balancer/Analyzer (P/N 8500C included in thekit ITEM 61-10-14)in the cockpit.

3 Connect the LH velocimeter cable (p/n 11210-100included in the kit ITEM 61-10-14)to the connector ofthe n 1 Velocimeter Channel of the Signal Selector(p/n 8520C).

4 Connect the RH velocimeter cable (p/n 11210-100included in the kit ITEM 61-10-14)to the connector ofthe n 4 Velocimeter Channel of the Signal Selector(p/n 8520C).

5 Connect the test harness ITEM 61-10-21to thepreviously disconnected connector KD3a.

6 Connect the test harness branch with the "LH PICK UP"label to the Magnetic Pickup Channel A of the SignalSelector (P/N 8520C included in the kit ITEM 61-10-14).


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7 Connect the test harness branch with the "RH PICK UP"label to the Magnetic Pickup Channel B of the SignalSelector (P/N 8520C included in the kit ITEM 61-10-14).

8 Connect the test harness branch with the "DC POWER"label to the 28 VDC Power Connector of the Signal

Selector (P/N 8520C included in the kit ITEM 61-10-14).

9 Use the harness (p/n 10811-12 included in the kit ITEM61-10-14)to connect the Output/Power Connector of theSignal Selector (P/N 8520C) with the 28 VDC/SIGNALconnector of the Balancer/Analyzer (P/N 8500C).

(e) Record the amount and bulkhead location of the previouslyinstalled balance weights. Remove the propeller spinner ifrequired (Ref.61-10-10, P. Block 401).


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Velocimeters Installation

CM1.61.10.00.5AO.00.00-00


Fig. 501Velocimeters Installation


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Velocimeters Cable installation on Aircraft

CM1.61.10.00.5BO.00.00-01


Fig. 502Velocimeters Cable installation on Aircraft


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Syncrophaser Control Unit, KD3

CM1.61.10.00.5CO.00.00-01


Fig. 503Syncrophaser Control Unit, KD3


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Test Equipment Installation in the Cockpit

CM1.61.10.00.5DO.00.00-01


Fig. 504Test Equipment Installation in the Cockpit


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(3) Propeller Vibration Measurement

NOTE: Before inserting the disk, make sure that it has the

applicable software.

NOTE: During all the Vibration Measurement follow the step bystep instructions shown on the display of theBalancer/Analyzer. Use the Chadwick-Helmuth's Model8500/8500C+ Operators Manual for more data.

(a) Connect the GPU and switch on the aircraft electrical system(Ref.24-40-00, P. Block 201). Make sure that the GPU ispositioned clear of the propeller wash.

(b) Close the following circuit breakers:

PANEL SERVICE FIN



(c) Start the engines (Ref.71-00-00, P. Block 501).

NOTE: Make sure that the wind speed value is not more than10 knots and the aircraft is headed to the wind.

NOTE: To avoid cross-talk interference, set the propellerspeed only on the engine which vibration you

measure.

NOTE: If you only have to measure the unbalance value ofone engine, start only the affected engine.

(d) On the CONTROL QUADRANT, set to ON the PROP SYNC OFF, KD7propeller synchronization switch. This switch is locatedbetween the PL's and CL's.

NOTE: This action supplies 28 VDC to the

Balancer/Analyzer.

(e) Make sure that, after approximately 45 seconds, the

Balancer/Analyzer completes its autotest satisfactorily andshows the following options: BALANCE, SPECTRUM and TRACK.

NOTE: If required, adjust the knobs (1) and (2) to set the


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contrast and backlight (Fig. 504).

NOTE: In case an instrument malfunction remove the powersupply to the Balancer/Analyzer, this will reset theinstrument without erase the memory.

NOTE: In case the instrument reset does not eliminate the

malfunction, do a cold start to erase the memory. Todo a cold start remove the power supply, then keeppressed the START button while supply 28 VDC power.Wait 5 seconds after release the START button.

(f) Get into BALANCE mode and select the appropriate balancechart. If required show or print the chart info.

(g) Press the SETUP button to check the appropriate balanceparameters.

NOTE: Make sure that the magnetic pick-up and velocimeter

input channels are the appropiated for the propeller

which vibration you measure. Modify as required.

NOTE: Make sure that the balance parameters are theappropriate.

(h) Move the Condition Levers to MAX and the Power Levers to FI.

(j) Adjust the PL until TQ value is 200 lbs and the CL until NPvalue is 87 %.

NOTE: Make sure that all engine parameters are stable.

NOTE: To avoid cross-talk interference, set the propellerspeed only on the engine which vibration youmeasure.

(k) Press START to start the vibration measurement.

(l) Do the steps (j) and (k) again adjusting the PL until TQvalue is 300 lbs and the CL until NP value is 97%.

(m) After the measurement, the unbalance value and is locationis shown on the Balancer/Analyzer screen.

(n) After the Balancer/Analyzer calculates a balance solution,

it is shown on the screen. Print the balance solution ifrequired.

NOTE: If balance weights were previously installed on the


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bulkhead, enter the balance weights configuration atthis step. Print the new balance solution.

(p) Do the steps (f) thru ( n ) again for the other engine.

NOTE: Make sure that the magnetic pick-up and velocimeterinput channels are the appropiated for the propeller

which vibration you measure. Modify as required.


(q) On the CONTROL QUADRANT, set to OFF the PROP SYNC OFF, KD7propeller synchronization switch. This switch is locatedbetween the PL's and CL's.

NOTE: This action eliminates the 28 VDC power supply to

the Balancer/Analyzer.

(r) Stop the engines (Ref.71-00-00, P. Block 501).

(4) Propeller Balance(Fig. 505).

(a) If the value of the propeller unbalance is not more than0,200 IPS no balance correction is required.

(b) If the value of the propeller unbalance is more than 0,200IPS do the following procedure to correct the unbalance:

1 Remove the propeller spinner(Ref.61-10-10, P. Block 401).

2 Locate, on the bulkhead (4), the balance points wherethe balance weights are installed.

3 With the previously obtained balance solution selectthe quantity and location of balance weights.

NOTE: The weight of one AN970-3 washer is 4,5 grams

(0,1 OZ).

NOTE: The weight of one AN960-10 washer is 0,9 grams(0,03 OZ).

NOTE: The weight of one AN960-10L washer is 0,4 grams(0,01 OZ).

NOTE: The weight of one NAS603-18 screw is 4,5 grams(0,1 OZ).


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NOTE: The weight of one MS21083 nutis 1,8 grams (0,06OZ).

4 At each position, install one screw (1), one nut (3)and the required quantity of washers (2). Torquetighten to 30-40 lbs.inch (3,4-4,5 Nm) (above runningtorque).

NOTE: Do not install more than 9 washers AN970-3 for

each screw.

NOTE: Do not install more than 6 screws for eachpropeller.

NOTE: Install a minimum of one flat washer on eachside of the bulkhead.

NOTE: Install the balancing washers on the aft side ofthe bulkhead.

5 Install the propeller spinner(Ref.61-10-10, P. Block 401).


(a) Do the propeller vibration measurement again, refer toparagraph 1.C.(3).

NOTE: If after some runs you can not decrease the

unbalance to a value lower than 0,2 IPS check:

- The aircraft continues headed to the wind

- The wind speed value is lower than 10 Knots

- The test equipment is correctly installed andoperative

- The spinner is correctly installed

- Do a check of the weight of the balance screws,washers and nuts.

NOTE: If after some runs you can not decrease theunbalance to a value lower than 0,2 IPS interchangethe two blades of the unbalance position. In this

case remove the balance weights before the next run.

NOTE: When the difference between the vibration values(for High and Low Torque condition) is more than 0,4IPS it can be impossible to balance the propeller


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(Refer to Model 8500 Maintenance and OperatorManuals):

- Low Torque: CL MAX and PL GI

- High Torque: CL 90% Np and PL 300 lb.ft.

(b) If propeller can not be balanced remove the propeller

assembly from aircraft (Ref.

61-10-10, P. Block 401).

(c) Record the number and location of dynamic balance weights,if they have been reconfigured, in the logbook.

(6) Close Up

(a) Open, safety and tag with ITEM 20-15-01these circuitbreakers:

PANEL SERVICE FIN



(b) Disconnect the test connectors from the signal selector.

(c) Put the access platform in the applicable engine.

(d) Open the right access doors 413AR and 423AR(Ref.06-41-54, P. Block 1).

(e) Disconnect the connectors from the velocimeters. Remove the

velocimeter harness from the aircraft.

(f) Remove the velocimeters from the engines.

(g) Close the right access doors 413AR and 423AR(Ref.06-41-54, P. Block 1).

(h) Install the right forward cowling 412AR at the left engine,and 422AR at the right engine (Ref.06-41-54, P. Block 1).

(j) In the electrical rack locate the Syncrophaser Control Unit,KD3 (1). Remove the electrical cap from the connector of theSyncrophaser Control Unit, KD3 (Fig. 503).

(k) Disconnect the test harness ITEM 61-10-21from thepreviously connected connector.


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(l) Connect the electrical connector (3) to the SyncrophaserControl Unit, KD3 (1)(Fig. 503).

(m) Close access pannel 222CR (Ref.

06-41-51, P. Block 1).

(n) Remove the Signal Selector and the Balancer/Analyzer from

the cockpit.


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Propeller Balance Weights Installation

CM1.61.10.00.5EO.00.00-00


Fig. 505Propeller Balance Weights Installation


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Propeller Dynamic Balance (using the Aircraft Vibration Analysis andControl Equipment, Chadwick VXP ITEM 61-10-20)

Procedure


2.


To measure the vibration value of the propeller assembly and do the

Propeller Dynamic Balance if required.


ITEM DESIGNATION


(2) ITEM 23-00-02 Headsets

(3) ITEM 61-10-20 Aircraft Vibration Analysis and ControlEquipment, Chadwick VXP

(4) ITEM 61-10-21 Dynamic Balancer/Analyzer Harness

(5) Standard Tool Servicing Platform

(6) Standard Tool Ear Defenders

(7) Standard Tool Stopwatch

(8) Standard Tool Warning Notices

(9) Z-24.301 Adhesive Tape

(10) AN970-3 Washer

(11) AN960-10 Washer

(12) AN960-10L Washer

(13) NAS603-18 Screw

(14) MS21083 Nut


- 06-41-51, P. Block 1 -Access Provision - Interior- 06-41-54, P. Block 1 -Access Provision - Nacelles- 24-40-00, P. Block 201 -External Power- 61-10-10, P. Block 401 - Propeller Assembly- 71-00-00, P. Block 501 - Powerplant- 71-20-00, P. Block 1 - Mounts

C.

(1) Job Set-Up


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(a) Putthe aircraft in position facing into the wind. Make surethat the dangerous area around the engine exhaust fumes isclear.

(b) Put warning notices in position around aircraft prohibitingunauthorized personnel or equipment.

(c) Make sure that all the landing gear wheels are chocked andthe Nose Landing Gear is centralized.

(d) Make sure that the fire fighting equipment is in position.

(e) Remove the engine intake covers, exhaust blanks, pitot headcovers and static vent plugs.

(f) Open, safety and tag with ITEM 20-15-01these circuitbreakers:

PANEL SERVICE FIN



(g) Put the access platform in the applicable engine.

(2) Equipment Installation

(a) Velocimeters Installation on PGB (Fig. 501).

1 Remove the right forward cowling 412AR at the left

engine, and 422AR at the right engine(Ref.06-41-54, P. Block 1).

2 Locate the bracket (3) that is installed in the RightAnti-vibration Mount that attaches the right side ofthe engine PGB to the forward mount(Ref.

71-20-00, P. Block 1).

3 Install the velocimeter (4) (p/n 7310 included in thekit ITEM 61-10-20) in the bracket (3). Use the AN970-3(2) washer and the 0,25-28 NYLOC Nut (1).

NOTE: Make sure that the connector of the velocimeterpoints to the RH at horizontal position.

4 Connect the connector (5) to the velocimeter connector.


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(b) Installation of the Velocimeters Cables (Fig. 502).

1 Open the right access doors 413AR and 423AR(Ref.

06-41-54, P. Block 1).

2 Put the velocimeter cables (P/N:11212-100 included in

the kit ITEM 61-10-20)out of the engine through thestarter/generator air inlet.

CAUTION: MAKE SURE THAT THERE IS NO INTERFERENCE

BETWEEN THE SECTION OF THE VELOCIMETER CABLEINSIDE THE ENGINE COWLINGS AND THE ENGINECONTROL CABLES OR MOVING PARTS.

CAUTION: MAKE SURE THAT THE SECTION OF THE VELOCIMETERCABLE INSIDE THE ENGINE COWLINGS IS CLEARFROM HOT PARTS.

3 Close the right access doors 413AR and 423AR(Ref.06-41-54, P. Block 1).

4 Put the velocimeter cables over the wings, along therear fuselage and inside the main compartment throughthe rear door.

CAUTION: MAKE SURE NOT TO CLOSE THE REAR DOOR, THIS

CAN CAUSE DAMAGE TO THE CABLE.

NOTE: For security, use tape Z-24.301at intervals tokeep the cable held to the aircraft.

5 Put the velocimeter cables into the cockpit.

NOTE: Put marks (LH or RH) in the cable ends to

indicate the propeller which signal transmit.

(c) Disconnection of the Syncrophaser Control Unit, KD3 (Fig.503).

1 Open access pannel 222CR (Ref.06-41-51, P. Block 1).

2 In the electrical rack locate the Syncrophaser ControlUnit, KD3 (1).


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3 Disconnect the electrical connector (3) from theSyncrophaser Control Unit, KD3 (1). Put a cap on theSyncrophaser Control Unit receptacle (2).

(d) Installation of the Test Equipment in the Cockpit (Fig.506).

1 Put the VXP Acquisition Unit (VXP AU) (P/N 15160-2included in the kit ITEM 61-10-20)in the cockpit.

2 Put the VXP Display Unit (VXP DU) (P/N 17330-1 includedin the kit ITEM 61-10-20)in the cockpit, as well asPrinter P/N 14492.

3 Connect the LH velocimeter cable (p/n 11210-100included in the kit ITEM 61-10-20)to the connector ofthe n 1 Velocimeter Channel of the VXP AU (p/n15160-2).

4 Connect the RH velocimeter cable (p/n 11210-100included in the kit ITEM 61-10-20)to the connector ofthe n 2 Velocimeter Channel of the VXP AU (p/n15160-2).

5 Connect the test harness ITEM 61-10-21to thepreviously disconnected connector KD3a.

6 Connect the test harness branch with the "LH PICK UP"label to the Magnetic Pickup Channel A of the VXP AU(P/N 15160-2 included in the kit ITEM 61-10-20).

7 Connect the test harness branch with the "RH PICK UP"label to the Magnetic Pickup Channel B of the VXP AU(P/N 15160-2 included in the kit ITEM 61-10-20).

8 Connect the test harness branch with the "DC POWER"label to the 28 VDC Power Connector of the VXP AU (P/N15160-2 included in the kit ITEM 61-10-20).

9 Use the harness P/N 17317-12A to link the connector ofthe VXP AU (labeled COMPUTER) with the RS-232 COMport input connector of the VXP DU (Display Unit,PANASONIC TOUGHBOOK laptop Computer) using the orangebranch cable. Connect as well the associated DC power

connector to the relevant power input connector ofcomputer. Use the black branch of harness P/N 17317-12Ato connect to the printer P/N 14492, including thepower connector.


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Test Equipment Installation in the Cockpit

CM1.61.10.00.5FO.00.00-01


Fig. 506Test Equipment Installation in the Cockpit


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(e) Record the amount and bulkhead location of the previouslyinstalled balance weights. Remove the propeller spinner ifrequired (Ref.61-10-10, P. Block 401).


NOTE: During all the Vibration Measurement follow the step by

step instructions shown on the display of the VXP DU. Usethe Honeywell's model VXP manual for more data.

(a) Connect the GPU and switch on the aircraft electrical system(Ref.24-40-00, P. Block 201). Make sure that the GPU ispositioned clear of the propeller wash.

NOTE: Make sure that the battery is not completely flat.

(b) Close the following circuit breakers:

PANEL SERVICE FIN



(c) Start the engines (Ref.71-00-00, P. Block 501).

NOTE: Make sure that the wind speed value is not more than10 knots and the aircraft is headed to the wind.


NOTE: If you only have to measure the unbalance value ofone engine, start only the affected engine.

(d) On the CONTROL QUADRANT, set to ON the PROP SYNC OFF, KD7propeller synchronization switch. This switch is locatedbetween the PL's and CL's.

NOTE: This action supplies 28 VDC to the VXP DU.

(e) Switch on the Display unit (PANASONIC TOUGHBOOK COMPUTER).

NOTE: Microsoft WINDOWS will start automatically the VXPDisplay program. If not, load the CN235 APPLICATION


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(APP) software from the flash memory included withinthe kit (Refer to VXP operating instruction).

(f) Adjust the PL until TQ value is 200 lbs and the CL until NPvalue is 87 %.

NOTE: Make sure that all engine parameters are stable.


(g) Start the data acquisition by clicking the button related tothe propeller being worked.

(h) Do the steps (f) and (g) again adjusting the PL until TQvalue is 300 lbs and the CL until NP value is 97%.

(j) After the measurement, the unbalance value and is locationis shown on the VXP DU screen.

(k) After the VXP DU calculates a balance solution, it is shownon the screen. Print the balance solution if required withthe Printer (p/n 14492).

NOTE: If balance weights were previously installed on the

bulkhead, enter the balance weights configuration atthis step. Print the new balance solution.

(l) Do the steps (f) thru ( k ) again for the other engine.

NOTE: Make sure that the magnetic pick-up and velocimeterinput channels are the appropiated for the propellerwhich vibration you measure. Modify as required.


(m) On the CONTROL QUADRANT, set to OFF the PROP SYNC OFF, KD7propeller synchronization switch. This switch is locatedbetween the PL's and CL's.

NOTE: This action eliminates the 28 VDC power supply to

the VXP DU.

(n) Stop the engines (Ref.

71-00-00, P. Block 501).

(4) Propeller Balance(Fig. 505).


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(a) If the value of the propeller unbalance is not more than0,200 IPS no balance correction is required.

(b) If the value of the propeller unbalance is more than 0,200IPS do the following procedure to correct the unbalance:

1 Remove the propeller spinner(Ref.61-10-10, P. Block 401).

2 Locate, on the bulkhead (4), the balance points wherethe balance weights are installed.

3 With the previously obtained balance solution selectthe quantity and location of balance weights.

NOTE: The weight of one AN970-3 washer is 4,5 grams

(0,1 OZ).

NOTE: The weight of one AN960-10 washer is 0,9 grams(0,03 OZ).

NOTE: The weight of one AN960-10L washer is 0,4 grams(0,01 OZ).

NOTE: The weight of one NAS603-18 screw is 4,5 grams(0,1 OZ).

NOTE: The weight of one MS21083 nut is 1,8 grams (0,06OZ).

4 At each position, install one screw (1), one nut (3)and the required quantity of washers (2). Torquetighten to 30-40 lbs.inch (3,4-4,5 Nm) (above runningtorque).

NOTE: Do not install more than 9 washers AN970-3 for

each screw.

NOTE: Do not install more than 6 screws for eachpropeller.

NOTE: Install a minimum of one flat washer on each

side of the bulkhead.

NOTE: Install the balancing washers on the aft side ofthe bulkhead.


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5 Install the propeller spinner(Ref.61-10-10, P. Block 401).


(a) Do the propeller vibration measurement again, refer to

paragraph 2.C.(3).

NOTE: If after some runs you can not decrease theunbalance to a value lower than 0,2 IPS check:

- The aircraft continues headed to the wind

- The wind speed value is lower than 10 Knots

- The test equipment is correctly installed andoperative

- The spinner is correctly installed

- Do a Check of the weight of the balance screws,washers and nuts.

NOTE: If after some runs you can not decrease theunbalance to a value lower than 0,2 IPS interchangethe two blades of the unbalance position. In thiscase remove the balance weights before the next run.

NOTE: When the difference between the vibration values(for High and Low Torque condition) is more than 0,4IPS it can be impossible to balance the propeller(Refer to Model VXP Maintenance and OperatorManuals):

- Low Torque: CL MAX and PL GI

- High Torque: CL 90% Np and PL 300 lb.ft.

(b) If propeller can not be balanced remove the propellerassembly from aircraft (Ref.61-10-10, P. Block 401).

(c) Record the number and location of dynamic balance weights,if they have been reconfigured, in the logbook.

(6) Close Up

(a) Open, safety and tag with ITEM 20-15-01these circuitbreakers:


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PANEL SERVICE FIN



(b) Disconnect the test connectors from the VXP AU.

(c) Put the access platform in the applicable engine.

(d) Open the right access doors 413AR and 423AR(Ref.

06-41-54, P. Block 1).

(e) Disconnect the connectors from the velocimeters. Remove thevelocimeter harness from the aircraft.

(f) Remove the velocimeters from the engines.

(g) Close the right access doors 413AR and 423AR(Ref.

06-41-54, P. Block 1).

(h) Install the right forward cowling 412AR at the left engine,and 422AR at the right engine (Ref.06-41-54, P. Block 1).

(j) In the electrical rack locate the Syncrophaser Control Unit,KD3 (1). Remove the electrical cap from the connector of theSyncrophaser Control Unit, KD3 (Fig. 503).

(k) Disconnect the test harness ITEM 61-10-21from thepreviously connected connector.

(l) Connect the electrical connector (3) to the SyncrophaserControl Unit, KD3 (1)(Fig. 503).

(m) Close access pannel 222CR (Ref.06-41-51, P. Block 1).

(n) Remove the VXP AU and the VXP DU from the cockpit.


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INSPECTION/CHECK

General Check of the Propeller Assembly


PROPELLER ASSEMBLY

WARNING: BEFORE DOING ANY MAINTENANCE WORK, PUT WARNING NOTICES IN FLIGHT

COMPARTMENT PREVENTING STARTING OR GROUND RUNNING OF RELEVANTENGINE.

WARNING: MAKE CERTAIN THAT RELEVANT ELECTRICAL CIRCUITS ARE ISOLATED.

WARNING: THE SYNTHETIC OIL USED HAS TOXIC ADDITIVES, WEAR PROTECTIVECLOTHING. IN CASES OF CONTAMINATION OF SKIN OR EYES, WASH WITHLARGE QUANTITIES OF CLEAN WATER, AND SEEK IMMEDIATE MEDICALATTENTION.

WARNING: PETROLEUM SOLVENT, AMS 3160, IS TOXIC. USE ONLY IN WELL VENTILATEDAREA. DO NOT BREATHE FUMES. KEEP PETROLEUM SOLVENT OFF SKIN ANDWEAR GOGGLES. IN CASES OF CONTAMINATION OR INHALATION, WASH

AFFECTED AREAS WITH MILD SOAP AND WATER, AND SEEK IMMEDIATE MEDICALATTENTION.

CAUTION: SYNTHETIC OIL CAN CAUSE DAMAGE TO PAINTWORK AND CERTAIN TYPES OFRUBBER. AVOID CONTAMINATION OF AIRCRAFT STRUCTURE AND SYSTEMS. OILSPILLAGE MUST BE REMOVED IMMEDIATELY.

1.

A. Definition of Terms

(1) Depression

Impression caused by the compression or removal of material froma given surface. Usually, it is small with a small depth.

(2) Gouge

Impression usually caused by the removal and, in second instance,compression of material.

(3) Scratch

Impression caused by the removal of material. Usually, it is afibre breakage caused by the impact of sharp objects.

(4) Crack

Effectivity: See TOC61-10-00 Pag. 601

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Procedure


Irregular shaped separation of material, usually with a narrowopening at the surface and caused by impact.

(5) Debond

Separation of the nickel leading edge sheath.

(6) Delamination

Separation of the Glass-Reinforced Plastic (GRP).


ITEM DESIGNATION

(1) ITEM 20-15-01 Circuit Breaker Safety Clips and Tags

(2) Standard Tool Servicing Platform, 2 m (6.5 ft)



-61-10-00, P. Block 701 -Propeller Assembly-61-10-10, P. Block 401 -Propeller Assembly-CMM 61-13-03, P. Block 601 -Variable Pitch Aircraft Propeller

C.

(1) Job Set-Up

(a) Open, safety and tag, with ITEM 20-15-01,the circuitbreaker:

PANEL SERVICE FIN


(b) Put the warning notices in the flight compartment tellingpersonnel not to start or ground run the relevant engine.

(c) Put the servicing platform in position below the relatedengine.

(d) Remove the spinner (Ref. 61-10-10, P. Block 401).


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(e) Clean the propeller assembly (Ref. 61-10-00, P. Block 701).

(2) Examine the nickel leading edge sheath on each propeller bladefor damage and debond. Replace or repair the propellers whichshow:

(a) A sheath debond larger than 0.125 in (3,125 mm).

(b) Cracks in the sheath nearer than 0.5 in (12,7 mm) to eachother or nearer than 1.0 in (25,4 mm) to the blade tip.

(c) Sheaths with a chip area larger than 0.062 in (1,59 mm)diameter.

(d) A sheath debond adjacent to cracks.

(3) Examine the blades for erosion, damage and lightening strike.Replace or repair the propellers which show:

NOTE: Scratches and gouges which have not penetrated thru the

GRP to expose the foam filling need not be repairedproviding the damaged area does not exceed 0.75 in 2(4,8cm2). The blades with erosion must be repaired (Ref. CMMof Hamilton 61-13-03).

(a) Evidence of blade delamination related to the sheath cracks.

(b) Depressions in the blade GRP larger than 0.5 in (12,7 mm)diameter or length, or nearer than 2.0 in (50,8 mm) to otherdepression. A maximum of four depressions in a distance of

12.0 in (305 mm) is permitted.

(c) Depressions nearer than 4.0 in (101,5 mm) to the inboard endof the sheath, or nearer than 0.25 in (6,350 mm) to thesheath trailing edge.

(d) Evidence of a lighting strike, shown as dark and discoloredareas at the blade tip.

(4) Examine the blade retaining rings for cracks, scratches and

gouges. If found, replace or repair the propeller.

(5) Hub Assembly


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Inspection of the Blades Nickel Sheath


(a) Examine the hub assembly for cracks, oil leaks, corrosion,wear and security of attachment. Reject the propeller ifdamages are found.

(b) Examine the blade heater wires for safety conditions anddeterioration of the insulators. Repair or replace as

necessary.

(c) Clean the slip rings on the rear part of the hub back-plate(Ref.

61-10-00, P. Block 701). Do an inspection of the sliprings for damage and corrosion. The maximum groove depthpermitted in the ring is 0.004 in (0,102 mm). Theerosion-resistant coating must be intact. Reject thepropeller if the values are more than the maximum permitted.

(6) Spinner

(a) Examine the spinner for damage, corrosion and security oftri-wing securing screws. Repair or replace as necessary.

(7) Close-Up

(a) Make sure that the work area is clean and clear of tools,equipment and loose objects.

(b) Install the spinner (Ref. 61-10-10, P. Block 401).

(c) Remove the servicing platform.

(d) Remove the warning notices from the flight compartment.

(e) Remove the safety clip and tag, ITEM 20-15-01,and close

START circuit breaker, KA1.** On A/C: Series 3002.


To do the 61.10.00.05 MRB task (MRB Document PV02M), "Detailed visualinspection of Blades Nickel Sheath Trailing Edge for separationevidence".



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Procedure


ITEM DESIGNATION


(2) Standard Tool Servicing Platform, 2 m (6,5 ft)



-61-10-00, P. Block 701 -Propeller Assembly

C.

(1) Job Set-Up

(a) Open, safety and tag, with ITEM 20-15-01,the circuitbreaker:

PANEL SERVICE FIN




(d) Clean the blades of the propeller assembly if necessary(Ref.61-10-00, P. Block 701).

(2) Inspection

(a) Do an inspection of the nickel sheath leading edge on eachpropeller blade for damage and debond. Replace or repair theblades that show:

1 A sheath debond larger than 0.125 in (3,125 mm).

2 Cracks in the sheath nearer than 0.5 in (12,7 mm) to

each other or nearer than 1.0 in (25,4 mm) to the bladeend.

3 A sheath with a chip area larger than 0.062 in (1,59 mm)of diameter.


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General Visual Inspection of the Propeller Assembly

Procedure


4 Sheath debonds adjacent to cracks.

(3) Close Up

(a) Remove the servicing platform.

(b) Remove the safety clip and tag, ITEM 20-15-01,and close thecircuit breaker:

PANEL SERVICE FIN


(c) Remove the warning notices from the flight compartment.

(d) Remove all tools and equipment from the work area. Make sure

that the work area is clean.

3.


To do the 61.10.00.02 MRB task (MRB Document PV02M), "General visualinspection of Propeller Assembly for general condition (groundlevel)".


ITEM DESIGNATION



C.

(1) Job Set-Up

(a) Open, safety and tag, with ITEM 20-15-01,the circuit

breaker:

PANEL SERVICE FIN


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PANEL SERVICE FIN


PANEL SERVICE FIN




(d) Clean the blades of the propeller assembly if necessary(Ref.61-10-00, P. Block 701).

(2) Inspection

(a) Do a general visual inspection of the blades for:

- Surface damage on the two sides of the blade. Examine theblades for signs of dents, nicks, scratches, and corrosion.Repair if necessary.

- Evidence of erosion. Repair if necessary.

- Cracks and delamination on the surfaces and edges. Smallstone impacts can create delaminations or microcracks andlet the moisture go into the blade. When the moisturefreezes into the blade it causes delaminations.

- Examine the blade for straightness. Examine the edges tofind deformations.

- Examine the blade for looseness. Move the blades to findunusual changes in looseness and play. Blade-to-bladedifferences indicate that an internal problem can exist.

- Correct bonding between the blade de-ice heaters and thepropeller assembly.

- Cracks and debonds on the nickel sheath. Repair ifnecessary.

(b) Examine for oil and grease leakages. Examine for oil orlubricant leaks the unusual areas, such as outside surfaces

and seals. A seal failure or a crack can cause oil or greaseleakages. The source of the oil or grease leak should bedetermined before flight.

(c) Examine the Spinner and Bulkhead. Externally examine thespinner and bulkhead for security, missing fasteners,


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Mandatory Inspections of the Propeller Assembly


damage, and cracks. Cracks typically originate from theattachment screws.

(d) Examine the propeller for general condition. Examine forloose wires, grease fittings and debris.

(3) Close Up

(a) Remove the safety clip and tag, ITEM 20-15-01and close thecircuit breaker:

PANEL SERVICE FIN


(b) Remove the warning notices from the flight compartment.

(c) Remove all tools and equipment from the work area. Make surethat the work area is clean.

4.


To do the 61.10.00.04 MRB task (MRB Document PV02M), "Perform allPropeller Assembly Maintenance Tasks included in the 'AirworthinessLimitation' Section of the Hamilton Standard's Maintenance ManualP5209, latest revision".


ITEM DESIGNATION



-CMM 61-00-00 -Propeller System - AirworthinessLimitations

C. Procedure

(1) Do all the Propeller Maintenance Tasks included in the"Airworthiness Limitations" section of the Hamilton Standard'sMaintenance Manual 14RF-37 (Ref.CMM 61-00-00).


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** On A/C: All


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CLEANI NG/ PAI NTI NG

Equi pment and Mat er i al s

Procedur e


PROPELLER ASSEMBLY

WARNI NG: BEFORE DOI NG ANY MAI NTENANCE WORK, PUT WARNI NG NOTI CES I N FLI GHT

COMPARTMENT PREVENTI NG STARTI NG OR GROUND RUNNI NG OF RELEVANTENGI NE.

WARNI NG: PETROLEUM SOLVENT, AMS 3160, I S TOXI C. USE ONLY I N WELL VENTI LATEDAREA. DO NOT BREATHE FUMES. KEEP PETROLEUM SOLVENT OFF SKI N ANDWEAR GOGGLES. I N CASES OF CONTAMI NATI ON OR I NHALATI ON, WASHAFFECTED AREAS WI TH MI LD SOAP AND WATER, AND SEEK I MMEDI ATE MEDI CALATTENTI ON.

WARNI NG: MAKE CERTAI N THAT RELEVANT ELECTRI CAL CI RCUI TS ARE I SOLATED.

CAUTI ON: DO NOT LET PETROLEUM SOLVENT COME I NTO CONTACT WI TH RUBBER, PLASTI COR GRP PARTS. WI PE OFF ANY SPI LLAGE I MMEDI ATELY.

1.

I TEM DESI GNATI ON

A. Z- 23. 146 Cl eani ng Compound

B. Z- 23. 139 Pet r ol eum Sol vent ( or equi val ent )

C. Z- 24. 907 Rubber Protect i ve Gl oves

D. - Goggl es

E. Z- 24. 930 Sof t Li nt - f ree Cl ot h

F. - Nyl on Abr asi ve Pad

Ref erenced Pr ocedures:

- 61- 10- 10, P. Bl ock 401 - Pr opel l er Assembl y2.

A. J ob Set - Up

( 1) Open, saf et y and t ag t he f ol l owi ng ci r cui t br eaker : .

PANEL SERVI CE FI N



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( 2) Put not i ces i n f l i ght compar t ment war ni ng agai nst st ar t i ng orgr ound r unni ng of r el evant engi ne.

( 3) Put access pl at f or m under r el evant pr opel l er .

( 4) Remove spi nner ( Ref . 61- 10- 10, P. Bl ock 401) .

B. Cl eani ng

( 1) Wear i ng gogl es and r ubber pr ot ect i ve gl oves. Cl ean spi nner andmet al l i c exter nal sur f aces of t he pr opel l er wi t h appr oved sol ventZ- 23. 139 ( or equi val ent ) .

NOTE: Appl y sol vent spar i ngl y wi t h a sof t cl ot h or br ush.

( 2) Remove sol vent by thor oughl y ri nsi ng wi t h f r esh wat er . Wi pe dr ywi t h a sof t cl ot h.

( 3) Cl ean al l r ubber , pl ast i c and bl ade GRP sur f aces wi t h a mi l d soapand warm water sol ut i on and a sof t cl oth. Ri nse wi t h f r esh waterand dr y wi t h a sof t cl ot h.

( 4) Dampen a f our - i nch squar e pi ece of nyl on abr assi ve pad wi t hcl eani ng compound Z- 23. 146.

( 5) Scr ub sl i p- r i ngs and adj acent GRP unt i l cl ean i n accor dance wi t ht he f ol l owi ng l i mi t s:

( a) GRP usi ng a br i ght l i ght i nspect f or bl ack oi l , gr aphi t e

sl udge or r esi due r emai ns i n or ar ound r i ng. Sl i ght r esi dueonl y i s per mi ssabl e i n I D or OD r adi us of sl i p- r i ngs.

( b) Sl i p- r i ngs shoul d have a cl ean copper f i ni sh wi t h sl i ghtr esi due per mi t t ed i n pi t t i ng or gr ooves i n t he ri ngs.

( 6) Wi pe sl i p- r i ngs and GRP wi t h a cl ean, sof t l i nt - f r ee cl ot h unt i lt horoughl y dr y.

NOTE: Make cer t ai n t hat GRP i s compl et el y dr y of cl eani ng

f l ui d.

C. Cl ose- Up

( 1) Make cer t ai n t hat wor k ar ea i s cl ean and cl ear of t ool s,equi pment and l oose obj ect s.

(2) I nst al l spi nner (Ref . 61- 10- 10, P. Bl ock 401) .


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( 3) Remove access pl at f or m f r om pr opel l er area.

( 4) Remove saf et y cl i p and t ag and cl ose START ci r cui t br eaker KA1( Ref . par a. 2 A ( 1) ) .

( 5) Remove war ni ng not i ces f r om f l i ght compar t ment .


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I NTENTI ONALLY LEFT BLANK


Ef f ecti vi t y: See TOC

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REMOVAL/INSTALLATION


PROPELLER ASSEMBLY

WARNING: MAKE SURE THAT RELEVANT ELECTRICAL CIRCUITS ARE ISOLATED.

WARNING: THE SYNTHETIC OIL USED CONTAINS TOXIC ADDITIVES. WEAR PROTECTIVECLOTHING. IN CASE OF CONTAMINATION OF SKIN OR EYES, WASH WITH LARGEQUANTITIES OF CLEAN WATER, AND SEEK IMMEDIATE MEDICAL ATTENTION.

WARNING: BE CAREFUL WHEN YOU USE OILS AND GREASES.OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND THE LOCALREGULATIONS.USE PROTECTIVE CLOTHING, GOGGLES AND GLOVES.

IF YOU GET OIL AND GREASE:

- ON YOUR SKIN, REMOVE IT WITH SOAP AND CLEAN WATER

- IN YOUR EYES OR IN YOUR MOUTH, FLUSH IT AWAY WITH CLEAN WATER

- GET MEDICAL AID.

IN GENERAL, OILS AND GREASES ARE POISONOUS AND SKIN IRRITANTS.

WARNING: BE CAREFUL WHEN YOU USE SOLVENTS/CLEANING AGENTS, SEALANTS ANDOTHER MATERIALS.OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND THE LOCALREGULATIONS.MAKE SURE THAT THERE IS A GOOD FLOW OF AIR THROUGH THE WORK AREA.DO NOT BREATHE THE FUMES.DO NOT SMOKE.

DO NOT USE THESE MATERIALS NEAR A FLAME, SPARKS OR SOURCES OF HEAT.USE PROTECTIVE CLOTHING, GOGGLES AND GLOVES.

IF YOU GET ONE OF THESE MATERIALS:

- ON YOUR SKIN OR IN YOUR EYES, FLUSH IT AWAY WITH A FLOW OF CLEANWATER

- IN YOUR MOUTH, GET IMMEDIATE MEDICAL AID.

IN GENERAL, THESE MATERIALS ARE FLAMMABLE, POISONOUS AND SKINIRRITANTS.

CAUTION: SYNTHETIC OIL CAN CAUSE DAMAGE TO PAINTWORK AND CERTAIN TYPES OFRUBBER. AVOID CONTAMINATION OF AIRCRAFT STRUCTURE AND SYSTEMS. OILSPILLAGE MUST BE REMOVED IMMEDIATELY.


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Removal/Installation of the Propeller Assembly


CAUTION: TAKE STRINGENT PRECAUTIONS TO AVOID CONTAMINATION OF THE OILSYSTEM. INSTALL PROTECTIVE COVERS TO EXPOSED OIL PASSAGES ANDCOMPONENTS IMMEDIATELY AFTER REMOVAL.

CAUTION: WHENEVER ANY PART OF THE PROPELLER ASSEMBLY IS DISMANTLED,ADJUSTED, REPAIRED OR REPLACED, DETAILED INVESTIGATION MUST BE MADE

ON COMPLETION TO MAKE SURE THAT DISTORTION, TOOLS, RAGS OR ANYLOOSE ARTICLES OR FOREIGN MATTER, THAT COULD IMPEDE THE FREEMOVEMENT AND SAFE OPERATION OF THE ASSEMBLY, ARE NOT PRESENT, ANDTHAT THE SYSTEM AND INSTALLATIONS IN THE WORK AREA ARE CLEAN.

CAUTION: WHENEVER ANY PART OF THE SYSTEM IS DISMANTLED, ADJUSTED, REPAIREDOR REPLACED, THAT PART OF THE SYSTEM WILL, AFTER COMPLETION OF THEWORK, BE TESTED TO ESTABLISH THE CORRECT OPERATION.

1.


- To remove and install the propeller assembly when it isunserviceable or to get access to other components.

- To do the 61.004 MRB task (MRB Documents PV01 and PV01M),"Restoration".

- To do the 61.10.00.03 MRB task (MRB Document PV02M), "RemovePropeller Assembly for restoration".


ITEM DESIGNATION

(1) ITEM 20-00-04 Screwdriver for Torq-Set Screw


(3) ITEM 61-10-01 Tri-Wing Screwdriver

(4) ITEM 61-10-03 Propeller Transport Cart

(5) ITEM 61-10-04 Control Alignment Tool

(6) ITEM 61-10-05 Adapter Plate

(7) ITEM 61-10-08 Torque Adapter

(8) ITEM 61-10-12 Oil Transfer Tube Box

(9) ITEM 61-10-13 Turning Fixture

(10) Standard Tool Servicing Platform, 2 m (6.5 ft)



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ITEM DESIGNATION

(12) Standard Tool Drip Tray

(13) Z-21.101 Lubricating Oil

(14) Z-21.220or Z-21.209 Grease

(15) Z-23.117 Solvent

(16) Z-24.930 Lint-Free Cloth

(17) 110-318 Seal (Hamilton Sundstrand MM 61-10-00)

(18) 69272-25 Cotter Pin (Hamilton Sundstrand MM61-10-00)

(19) 779247-7 Preformed Packing (Hamilton Sundstrand MM61-10-00)

(20) 786124-1 Tee Seal (Hamilton Sundstrand MM61-10-00)

(21) 794444-1 L Seal (Hamilton Sundstrand MM 61-10-00)

(22) AS3209-043 Packing

(23) M83248-1-115 Packing

(24) MS9245-27 Cotter Pin

(25) MS20995C20 Lockwire


-07-13-10, P. Block 1 -Propeller Hoisting-12-13-10, P. Block 1 -Propeller Gearbox Lubrication-20-21-00, P. Block 1 -Standard Torques

-20-38-00, P. Block 1 -Sealing-30-61-00, P. Block 501 -Propeller De-Icing System-61-20-00, P. Block 301 -Propeller Controlling-61-20-19, P. Block 401 -Magnetic Sensor-71-00-00, P. Block 501 -Powerplant-MM 61-10-00, P. Block 701 -Propeller MM (Hamilton Sundstrand)-MM 72-00-00 -Engine MM (General Electric)

-Flight Test After Maintenance ActionsInstructions Handbook

C. Procedure

(1) Job Set-Up

(a) Feather the propeller (Ref. 71-00-00, P. Block 501), ifapplicable.


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(b) Open, safety and tags, with ITEM 20-15-01,the circuitbreaker:


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PANEL SERVICE FIN


(c) Put the warning notices in the flight compartment tellingpersonnel not to start or ground run the relevant engine, oroperate the feathering system.

(d) Put the servicing platform in position.

(e) Put the drip tray under the propeller assembly.

(2) Removal (Fig. 401)

(a) Using the tri-wing screwdriver ITEM 61-10-01for tri-wingscrews, or the screwdriver for the torq-set screws ITEM20-00-04,moved the screws (2), which attach the spinner (1)

to the back plate, from the contact surface.

(b) To prove the breakaway torque along all the thread of eachscrew, and discard those that have less than 3,5 in.lb (4cm.kg), or those that the threads are damaged.

(c) Remove the propeller spinner (1).

(d) Remove and discard the preformed packing (3) from thepropeller dome (4).

(e) Remove and discard the cotter pin (19). Remove the pin (18)and the plug (9). Remove and discard the packing (10) from

the plug (9).

(f) Remove and discard the cotter pin (12) from the end of theoil transfer tube (16) and the retainer (11).

(g) Rotate the oil transfer tube (16) and the retainer (11)clockwise until the retainer tangs (13) on the retainer (11)align with the slots in the pitch control valve (17). Theretainer (11) should spring back slightly.

(h) Remove the oil transfer tube (16) and the retainer (11),from the pitch control valve (17).

(j) Remove and discard the packings or the seals (15).


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Propeller Assembly

CM1.61.10.10.4AO.01.00-01


Fig. 401Propeller Assembly (Sheet 1 of 2)


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CM1.61.10.10.4AO.02.00-00


Fig. 401Propeller Assembly (Sheet 2 of 2)


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(k) Put the oil transfer tube (16) and the retainer (11) in theoil transfer tube box ITEM 61-10-12.

(l) Rotate the propeller until the relief valve (20) ispositioned upward.

(m) Remove the relief valve (20) and the seal (21). Discard theseal (21).

(n) Engage the turning fixture ITEM 61-10-13to the pitchcontrol valve slots (17).

(p) To prevent the blades locking, turn the pitch change valve(17) counterclockwise while turning the blades by hand tofull reverse position.

(q) Remove the turning fixture ITEM 61-10-13.

(r) Reinstall the relief valve (20) and a new seal 110-318 (21).Tighten by hand until the seal (21) is compresses.

(s) Install the propeller sling adapter and the sling(Ref. 07-13-10, P. Block 1), and attach the hoist of thelifter to the aft ring of the sling adapter.

(t) Remove the hexagon nuts (5) which attach the propeller tothe gearbox flange (6), using the torque adapter ITEM61-10-08.Discard the hexagon nuts, that have a torque lessthan 24 in.lb (27,5 cm.kg).

(u) Carefully separate the propeller assembly forward, until the

propeller hub is out of the dowels (7) on the gearbox flange(6).

CAUTION: MAKE SURE THAT THE WORK AREA IS FREE OF

OBSTRUCTIONS WHEN REMOVING THE PROPELLER FROM THEGEARCASE. USE SLOW MOVEMENTS TO KEEP THEPROPELLERS AND BLADES ON A STABLE PLANE.

(v) Carefully lower the propeller and guide hub onto the adapterplate ITEM 61-10-05,of the propeller transport cart ITEM61-10-03.

(w) Safety the propeller to the adapter plate ITEM 61-10-05

withfour hexagon nuts (5), and tighten securely to the standardtorque value (Ref.20-21-00, P. Block 1).

(x) Remove the sling adapter and the sling(Ref. 07-13-10, P. Block 1).


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(y) Remove and discard the packing (8).

(z) Reinstall the plug (9) in the pitch control valve (17) withthe pin (18), and temporarily hold them with lockwirethrough the cotter pin hole.

(aa) Put suitable protective coverings over the exposed gearboxshaft and the propeller hub openings.

(3) Preparation for Installation (Fig. 401)

NOTE: The propeller blades must be in the full reverse position

before you start the installation procedure. This willmake sure that the tail shaft of the pitch change yoke isretracted into the hub, for protection from damage.

NOTE: To see if a propeller balancing is needed, and its

procedure, refer to the Propeller Maintenance Manual(Ref. MM 61-10-00, P. Block 701), of Hamilton Sundstrand.

(a) Remove the protective covering from the gearbox shaft andthe propeller hub.

(b) Make sure that the gearbox axis and flange (6) and thepropeller mating surfaces are clear and free from burrs andcorrosion.

(c)WARNING: BE CAREFUL WHEN YOU USE MATERIAL Z-23.117.OBEY

THE MATERIAL MANUFACTURER'S INSTRUCTIONS

Clean the surfaces with a lint-free cloth Z-24.930,impregnated with solvent Z-23.117,and let air dry for aminimum of two minutes.

(d)WARNING: BE CAREFUL WHEN YOU USE MATERIAL Z-21.101.OBEY

THE MATERIAL MANUFACTURER'S INSTRUCTIONS

Apply a coat of lubrication oil Z-21.101to the new packingAS3209-043(8).


61-10-10 Pag. 409May 15/13


61-10-10 Pag. 409May 15/13
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(e) Install the new packing AS3209-043(8) into the gearboxflange (6).

CAUTION: MAKE SURE THAT THERE IS NOT LUBRICATING OIL ON

THE GEAR CASE OR HUB MOUNTING FLANGES. OTHERWISE,

RUB IT OFF WITH A CLEAN LINT-FREE CLOTH.

(f) Inspect the oil transfer tube (16) housing in the gearboxshaft for damage and corrosion. If any found, refer to theEngine Maintenance Manual (Ref. MM 72-00-00), of GeneralElectric.

(g) Make sure that the oil transfer tube (16) housing is freefrom obstruction. If necessary, clean with a lint-freeclothZ-24.930.

(4) Installation (Fig. 401)

(a) Install the propeller sling adapter and the sling(Ref. 07-13-10, P. Block 1), and attach the hoist of thelifter to the aft ring of the sling adapter.

(b) Remove the hexagon nuts that attach the propeller to theadapter plate ITEM 61-10-05,on propeller transport cartITEM 61-10-03.

(c) Carefully remove the propeller from the propeller transportcart ITEM 61-10-03,and use the hand to keep the propellerin a stable position in a vertical plane.

(d)

WARNING: BE CAREFUL WHEN YOU USE MATERIAL Z-23.117.OBEYTHE MATERIAL MANUFACTURER'S INSTRUCTIONS.

Clean the contact surfaces, the bolts and the hexagon nutsthreads with a lint-free cloth Z-24.930,impregnated withsolvent Z-23.117,and let air dry for a minimum of twominutes.

(e) Hoist the propeller carefully until the hub is in line withthe gearbox flange (6).

(f) Make sure that the packing (8) is installed.

(g) Align the dow

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