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LIST OF CHARTS::,-Peqal Split Conversion ChartEngine Fire Extinguisher Pressures

'CH-47A Cockpit Controls Posit ionEnvelope

,G H -47 B Cockpit Controls Posit ion" ' ~ ' , Env.elopeCH47C Cockpit ~ o n t r o l s Position

EnvelopePower Topping T 5 5 ' l - ~ Power Topping T55L777B " " ~ ' Power Topping 'T55-L7C (66:1)Power Topping T55L7C (64:1)Intersttlge Air Bleed Band., ...

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CH-47 AMTPCBEFORE EXTER lOR CH ECKRequired paperwork completedand log book and records checkedWeight and balance forms checked (Compute ifnecessary)Flight crew briefing on purpose and objectivesof flightBATTERY switch OFFEXTERIOR CHECKEntrance Door

1. Condition - CH ECK2. Upper section escape panel - CH ECKsecure

General Inspection1. Protective covers - REMOVED2. Blade tiedowns - REMOVED3. Wheels - CHOCKED4. Fuel leakage - CHECK5. Area - Clear of obstructions and loose

objectsRight Cabin Fuselage Section

1. AC power equip compartmenta. Equipment - CH ECKb. Door - LATCHED

. 1

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CH-47 AMTPC

2. Fwd Aux Fuel Tank - CH ECK leakage.servIcing. and cap secure

3. Static port - CHECK4. Fuel vents - CHECK clear5. Navigation l ight - CH ECK condition6. Forward landing gear support structure

open access panel - CHECK for cracks ordistortion

7. Forward landing gear - CH ECK thefollowing:a. Tires for inflation. condition. and ply

ratingb. Shock strut for inflationc. Hoses and wheel brake assembly forleakage. chafing. and securityd. Fwd Aux fuel tank electrical connections

and fuel lines - CHECK condition andsecurity

e. Close access panel8. Fuel main tank - CH ECK leakage. re

quired servicing. and cap secure9. Fuselage skin - CHECK for dents.

wrinkles. and loose or missing rivets10. Fuel vents - CHECK clear11. Aft aux fuel tank - CHECK leakage.

servicing. and cap secure12. Windows - CH ECK for cracks and

cleanliness

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CH-47 AMTPCTop of Fuselage

1. Forward rotor - CHECK lag damper lockouts removed, security of components, oillevel in all reservoirs, forward and aftblades for damage, sight cups ("A" Modelonly), Rotor - Phasing marks alignment.droop stops, pitch links, swashplate, upperboost actuators for condition security andleakage. and speed trim actuator forcondition

2. SAS Port and Lines - CHECK condition andsecurity "A" Model only

3. Forward transmission - CHECK forservicing

4. Hydraulic filter buttons and hydraulic l i nes CHECK5. First and second stage mixing un i t s -

CH ECK for condition and security6. Synch shaft adapter - CH ECK7. Forward pylon fairing - CHECK secure8. Drive shafting, lord mounts, Thomas coup

lings, and support brackets - CH ECK forcondition, security. and foreign objects

9. Push-pull tubes, bellcranks, oil lines,hydraulic lines and electrical wiring CH ECK for condition and security

10. Drive shaft fairing - CHECK secure11. Formation lights - CH ECK condition

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CH-47 AMTPC

12. Top of fuselage - CHECK for foreignobjects

13. Fuselage skin - CHECK condition14. No. 1 engine - CHECK as follows:

a. Inlet cover removedb. Inlet for foreign objectsc. Oil level and cap secured. Fairing securee. Tailpipe for cracks, hot spots, security,

and cover removedf. Power turbine section, ignitors, and fire

warning system15. Aft rotor - CHECK as follows:

a. Lag damper lockouts removedb. Oil levels in all reservoirs, sight cups

("A" Model only) for oilc. Droop stops, pitch links, swashplate, upper

boost actuators, and speed trimactuator

d. Thrust bearing - CHECK condition16. Upper boost actuator safety b l o c k s

REMOVED17. Aft transmission - CH ECK condition18. Hydraulic filters, reservoirs and l i n e s

CH ECK for condition and security19. Rotor phasing marks - CH ECK for proper

alignment

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CH-47 AMTPC20. Anti-collision and formation lights - CHECK21. Combining transmission area - CH ECK as

follows:a. Oil coolers and linesb. Servicingc. Phasing mechanismd. Engine to transmission drive shafting

22. Doors and covers - SECURE23. No.2 engine - CHECK same as No. 1

engine

Aft Pylon Section1. Aft landing gear support structure - CHECK

for cracks or distortion2. Aft landing gear - CH ECK the following:

a. Tires for inflation and conditionb. Tires for ply ratingc. Shock strut for inflation and static lock

unlockedd. Power steering actuator, wheel brakes,

and hoses for leakage, chafing, andsecurity

e. Electrical connections for condition andsecurity

3. All access doors and covers - SECURE4. Ramp control - As required and close

access door

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CH-47 AMTPC

5. Hydraulic system test panel - CH ECK allcaps secure

6. Hydraulic oi l cooler air inlet - CH ECKclear7. Fluid vent and drain lines - CHECK clear8. APU air inlet - CHECK clear9. Cargo loading ramp - CHECK condition

10. APU exhaust outlet - CHECK cover removed and outlet clear

11. Navigation light - CH ECK condition12. Fluid vent and drain lines - CHECK clear13. All access doors and covers - CH ECK

secure14. Aft landing gear support structure - CH ECKfor cracks or distortion15. Aft landing gear - CHECK the following:

a. Tires for inflation. condition. and plyrating

b. Static ground wir'e secure and contacting the ground

c. Shock strut for inflation and static lockunlocked

d. Hoses and wheel brake assembly forleakage. chafing. and security

Left Cabin Fuselage Section1. Windows - CH ECK for cracks and clean

liness

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CH-47 AMTPC

2. Fuselage skin - CHECK for dents,wrinkles, loose or missing rivets

3. Aft aux tank fuel vent - CH ECK clear4. Main and aux fuel tanks - CH ECK leakage,required servicing, and caps secure

5. Fuel vents - CH ECK clear6. Static port - CH ECK clear7. Navigation lights - CHECK condition

r-" 8. Anticollision lights - CHECK condition9. Antennas - CH ECK condition and security

10. Forward landing gear support structure CH ECK for cracks or distortion

11. Forward landing gear - CHECK thefollowing:a. Tires for inflation, condition, and ply

ratingb. Shock strut for inflationc. Hoses and wheel brake assembly for

leakage, chafing, and securityd. Fwd aux fuel tank electrical connections

and fuel lines - CH ECK condition andsecurity

12. DC power equipment - CH ECK batteryconnected, transformer rectifiers for con dition and security, and sump jar

13. Access door - SECURE14. Escape panel - SECU RE

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CH-47 AMTPC

Forward Cabin Section1. Copilot's jettisonable door - CHECK con

dition and security2. Copilot's hydraulic brake lines - CHECK for

leakage3. SAS yaw ports - CH ECK clear4. Pitot tube - CH ECK cover removed5. Windshields - CHECK for cracks and

cleanliness6. Windshield wipers - CHECK condition7. Nose access panel - CHECK secure8. Rear view mirror - CHECK condition and

cover as required9. Landing-search lights - CHECK condition

10. Pilot's hydraulic brake lines - CHECK forleakage

11. Outside air thermometer - CH ECK12. Pilot's jettisonable door - CHECK condition

and security13. Heater intake and exhaust outlet - CHECK

clearNEUTRAL RIG CHECKPerform Neutral Rig Check Controls(left stick)Pedals - Neutral (Even)

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CH-47 AMTPCLongitudinal - 11 'h 1/ Ii 1/ from

Emergency SwitchLateral - 15 'h 1/ 'h"from left side

frameThrust - 5%1/ %1/ from top of pivot

blockStick positioner should be at "0"All Upper Boost Actuators6%1/ Ye1/Ball SliderForward - 2%1/ /;61/Aft - 2%1/ X61/INTERIOR CHECKCabin Fuselage Section (right-hand side)

1. Cabin and ramp lights forward controlswitches - As required

2. Interior - CHECK for loose equipment3. Speed trim amplifier function s w i t c h

CH ECK at AC positionNOTE

During flight. if the switch is left atAFT, FWD, A/S, or MAN., longitudinal cyclic speed trim programming maybe affected

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CH-47 AMTPC

4. Heater compartment - CHECK security ofcomponents. vibrator contact position. andignition circuit fuse

5. Winch and winch accessories - CHECKsecurity

6. Emergency escape axe - CHECK conditionand security

7. Seats. litters. or cargo - CHECK security8. Heat outlets - position as required9. Cabin lights - CH ECK condition

10. Jettisonable cabin windows - CHECKsecurity

11. First aid kits - CHECK security12. Rescue hatch door - CHECK and positionas required13. Cargo hook - CHECK and position as re

quired - check air charge - 2100 PSI14. Lower rescue door - CHECK and position

as required15. Hoist control panel - CHECK switches andstow grip16. Litter straps - CH ECK stowed if not used

Aft Cabin Section1. Combining transmission area - CH ECK for

leaks2. Cabin and ramp lights switch - As required3. Ramp control sequence valve - As required

/

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CH-47 AMTPC4. Ramp control lever - As required5. ENGine NO.2 fuel valve - CHECK CLOSED

(Check Open "C" Model only)6. ENGine NO.2 FUEL VALVE caution l i g h t PRESS-TO-TEST. The BATTERY switch mustbe at ON to check the light. (Light will notilluminate on "C" Model unless Fuel Valveis closed)

7. CROSSFEED FUEL VALVE - CHECKCLOSED8. CROSSFEED FUEL VALVE caution l i g h t

PRESS-TO-TEST. The BATTERY switch mustbe ON to check the light

9. MANIFOLD VALVE - As required10. MANUAL DEFUELING VALVE - CHECKCLOSED11. Hand pump - CHECK condition and leaks12. Manual control valve - CHECK NORMAL13. Utility Filler and Pressurized Tank - CHECK

for leaks and fluid level14. Utility hydraulic accumulators - CHECK

NOTEIf pressure in the utility hydraulic accumulator is below 3.000 psi. it is necessary to pressurize the system withthe hand pu mp before attempting tostart the APU.

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CH-47 AMTPC15. Ramp area hydraulic lines - CHECK for

leaks and filter button position16. Utility bleed valve - CHECK for contamination17. Ramp - CHECK condition and position as

required18. Ramp escape panel - CHECK security19. Jettisonable cargo door - CH ECK secure20. APU - CHECK condition21. AG B area lines - CH ECK for leaks and

condition22. Flight control accumulators - CHECK 1,400

psi precharge23. Flight boost manifolds - CH ECK for leaks24. Aft transmission and AGB - CHECK for oil

level and condition (Use the OIL LEVELCH ECK light switch if necessary.)

25. Engine fire extinguisher pressures - CHECK(Refer to Table 2, Engine Fire ExtinguisherPressures)

26. Fire extinguisher circuit break.ers - IN27. Troop alarm box - CHECK condition28. APU fuel solenoid valve - CH ECK29. APU manual fuel shutoff valve - CH ECK

OPEN30. Compass flux valve - CHECK security

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CH-47 AMTPC31. Rearview mirror - CHECK stowed (If not

installed)32. APU fuel pump - CH ECK for leaks andcondition ("A" & "B" Model)33. Engine No. 1 fuel valve - CHECK CLOSED

(CHECK OPEN - "C" Model)34. ENGINE NO. 1 FUEL VALVE caution l i g h t

PRESS-TO-TEST. The BATTERY switch mustbe ON to check the light. (The light will notilluminate on "C" Model unless Fuel Valve isclosed)

35. Ramp interphone control panel - As required

36. Hand fire extinguisher - CH ECK pressureand security

Cabin Fuselage Section (left-hand side)1. First aid kits - CH ECK security2. Litter straps - CH ECK stowed if not used3. Jettisonable cabin windows - CHECK secure4. Handcrank - CHECK stowed5. Cabin heater thermostat - CH ECK

NOTEIf the left side of the A/C is exposedto the sun, the thermostat will heatup sufficiently to sig nal the heater notto light off.

6. Transformer-rectifier air intake screensCH ECK clear

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CH-47 AMTPC7. Cabin escape panel - CHECK security8. Hand fire extinguisher - CH ECK pressure

and security9. Troop alarm box - CH ECK condition10. Avionic equipment - CH ECK security of

components and connections11. CH ECK SAS Electrical connections for

condition and security12. Litter poles - CH ECK secure13. SAS amplifier selector switches - CHECK

at AC position14. First aid kit - CH ECK security15. Troop CM DR seat

Flight Control Closet1. Filters - CHECK2. Hydraulic Lines - CH ECK for leaks and

security3. SAS extensible links - CHECK condition

and security4. Electrical wiring and plugs - check con

dition and security5. Lower Boost Actuators - CHECK for con

dition, leaks, and security6. DCP Speed and Stick Trim A c t u a t o r

CHECK nominal length - 34'%/ ' /;6"condition and security

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CH-47 AMTPC7. Flight Controls - CHECK all push-pull tubes,

magnetic brakes and viscous dampers forcondition and security

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CH-47 AMTPC

COCKP IT CH ECKPilot/Copilot Seats - CH ECK

1. Axis adjustment and lock in place2. Seat belt and shoulder harness

r---. 3. "G" lock manual and automatic operationPilot/Copilot Windows and Doors

1. Open and close (50-lb maximum force)2. Slide operation (15-lb maximum force)3. Handle alignment - CH ECK4. Jettison doors using inside and outside

handles - 50-lb maximum force (optional)Fire Bottle SecuritySpare Lamp Box - CH ECKCockpit Placard

1. Takeoff and landing checklist2. Radio identification3. Magnetic compass card

Adjust Mirror (if installed)Circuit Breakers - As required

, Switches1. Lights - As required2. Battery switch - OFF

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CH-47 AMTPC3. Generator switches - OFF4. Utility System switch - As required5. Anti-icing switches - OFF6. Ignition switches - OFF7. Start fuel switches - CLOSE8. Flight control centering switch - ON9. Hydraulic boost switch - BOTH ON

10. SAS switch - BOTH ON11. Heater - OFF12. Troop jump lights switch - OFF13. Troop alarm switch - OFF14. Windshield wipers switch - OFF15. Engine fuel valve switches - CLOSE ("A"and "B" model only)16. Crossfeed fuel valve switch - CLOSE17. Fuel booster pump switches - OFF18. Hoist control and cargo hook s w i t c h e s

OFF19. Static discharger - OFF

Instrument Panel1. Magnetic compass - free of bubbles2. Fire extinguisher agent switch - NEUTRAL3. Fire control handles - CH ECK IN4. Instrument range markings

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CH-47 AMTPC

a. Rotor tach("A" Model)Red radial at 204, 233, 261Green arc from 204 to 233("8" Model)Red radial at 204, 233, 261Yellow arc from 204 to 223Green arc from 223 to 233("C" Model)Red radial at 214, 233, 261Yellow arc from 214 to 223Green arc from 223 to 233

b. Torque meter("A" & "8 " Model)Red radial at 860("C" Model)Red radial at 890 (Dual Engine)

1015 (Single Eng.)c. A/S IND

("A" Model)Red radial at 132 knots("8" & "C" Model)Red radial at 174 knots

d. N I TachRed radialPer individual eng.

e. EGT Gauge (L-7C Engine)Red radial: 740 and 816

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CH-47 AMTPCBlue radial: 700Green arc: 230 to 660Yellow arc: 752 to 816

(L-7/L-7B)Red radial: 735. 816Green arc: 230 to 635Yellow arc: 746 to 816

(L-5)Red radial: 638. 760Green arc: 230 to 602Yellow arc: 649 to 760

f. Eng. oil temp.Red radial at 138C

g. Eng. oil press.Red radial 10 and 110 psiYellow arc 40 to 50 psiGreen arc 50 to 90 psi

h. Xmsn oil press.Red radial 20 psiGreen arc 20 to 90 psi

I. Xmsn oil temp.Red radial 130. 140CGreen arc 60 to 130CYellow arc 130 to 140C

J. Flight boost press.Red radial 2500. 3200 psiGreen arc 2500 to 3200 psi

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CH-47 AMTPC

k. Utility boost press.Red radial 2500, 3400 psiGreen arc 2500 to 3400 psi

5. Transmission oil pressure selector switch AFT

6. Transmission oil temp. selector switch SCAN

7. Fuel quantity selector switch - LH Tank,("C" Model-Total)

8. Radar altimeter (i f installed) - SET9. Compass slaving switches - IN

1O. VGI switches - NORM11. Clocks - SET12. Cockpit air knobs - CLIMATIC

Console1. Navigation equip - OFF2. Stick positioner - ZERO3. Air control handles - CLIMATIC4. Marker beacon sensitivity switch - As

required5. Marker beacon switch - OFF6. Aft wheel swivel lock switch - As re

quired7. Engine condition levers - STOP8. Emergency SAS release - RELEASE

(Guard up)

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CH-47 AMTPC

9. Speed trim function switch - AUTO10. Pilot and copilot interphone panel

switches - As required11. Communications equip - OFF12. Transponder - (IFF) OFF13. Power steering switch - OFF14. Troop commander's interphone panel

switches - As required15. Personal equip - CHECK

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CH-47 AMTPCMalfunction

Battery Switch - 0 N 011, Check ICS all positions J12, Cockpit lights

a. Dome and utility lights 02-5b. Instrument flood lights 06c. Jump lights and troop alarm 07,8d. Cabin lights (jump lights go to dim 09,10

on red cabin l ight postion)3. UH F radio - ON then OFF J2

BATTERY Switch to Emergency 011Position

1. ICS - CHECK2. Caution lights - OUT3. FM radio - ON then OFF J24. Emergency beep G15. BATTERY switch to ON

Caution Lights 012, 1. Test switch (all lights illuminate) 013

2. Master caution lights - press to reset 0143. Bright dim switch - Operation 0154. Dome light switch to white position; 016

dim caution lights go to brightUtility Hydraulic Switch - ON

1. Reset parking brake E1

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2. Check parking brake caution light op- E2 eration

3. Check swivel lock operationAPU Start

1. APU switch to APU position2. Three warning lights operation - (EXH. A2

TEMP. and OVSP illuminated) (OILPRESS press to test)

3. APU to START (90% within 14 seconds A3maximum)

4. Stabilize 98 - 106% A4Generator - Rectifier Operation

1. Turn on each generator 0172. Each generator operates both T/Rs 018,19

Aft Transmission Pressure-CheckHydraulic Boost Pressure Indications

1. Pressure within 30 seconds maximum E3after APU start

2. NO.1 and NO.2 boost pressure stabilize E4-6at 2500-3200 psi

3. Utility boost press stabilize at 2500 3400 psi4. 50 psi fluctuation maximum

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Windshield Anti-Ice

~ Do not operate system above an 020,21outside air temperature of 24C.

Pitot and SAS Port Heat 0221. Observe No. 2 AIC load meter

Lights1. Search 023-25

a. Lightb. Auto retract

2. Anti-collision 026,273. Position and formation lights 028,294. Instrument 030,315. Emergency flood lights 06

a. Pilot instrument light rheostat - ONb. GENerator CONTROL and BATTERY

switches - 0 FFc. Check emergency flood lights - ON 032

Center Flight ControlsRadios - ONFire Detection Lights 033

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T-Handle Fuel Shutoff

1. Turn both fuel valves - ON H12. Operate T-Handles H13. Fuel'valve closed - CH ECK H1

Crossfeed Valve Operation H2VGI

1. 90 seconds maximum to align J32. Pitch/roll adjustment and travel3. Emergency operation

Turn and Slip Indicators1. Alignment between indicators

Altimeters1. Set field barometric press on both 81

altimeters2. Observe both alt 50 feet of fieldelevation

Fuel Gauge1. Left side:2. Right side: H3,43. Total (Full' tanks-7000 Ibs) "C" Model(Full tanks-4000 Ibs) "A" "8 " Models

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4. Left and right - total H3-5 300 Ibs. "C" Model H6,7 50 Ibs. "A" & "B" Models

Control Interference C1,21. Perform control check

a. Both boostb. Single boost

NOTEPedals adjusted full aft, will not contactfloor.

NOTEAs each boost is turned OFF, ob- E9,10serve warning light ON at 2,000 50psi. As each boost is turned on, observe boost press to normal range within two seconds. Select NO.1 boost Onand place APU/AG B switch to E7,8start, observe NO.1 boost drop to 500 50 psi and No. 2 boost returns tonormal range as No. 1 falls below2,000 psi.

Control Centering C3-51. Switch ON - holds control at full dis

placement2. Switch OFF - CHECK control force

feel

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CH-47 AMTPC

Malfunction

Control Travels C61. Check cockpit indicator position vs meas

ured neutral measurements obtainedfrom previous rig checka. Longitudinal travel 7.5" fwd

6.5" aft 0.5" (Useindicator)

b. Trim wheel full fwd. travel 8" 0.5"c. Trim wheel full aft. long. aft travel

7;!a" 0.5"2. Lateral travel from measured neutral ap

proximately equal3. Directional travel approximately equal4. Thrust travel detent to full down 1 to

1.5"5. Lateral play between cyclics ;!a" max

ImumControl Break Out Forces

1. Longitudinal fwd and aft 1.2 to 2 Ibs2. Lateral left and right 1.2 to 2 Ibs3. Directional left and right 11 to 20 Ibs4. Detent (5 Ibs max. up and 9 lb. max.

down)("A" Model detent - 4 Ibs max. up and 5Ibs max. down)

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NOTEBreak out forces should be approximately symmetrical.

Aft Transmission Pressure - SCANEngine Start and Operation

1.' Prestarta. Beep full decrease (hold for 8 sec) G2,3b. E.C.L.toGND.c. Fuel boost pumps - ONd. Fuel Valve - OPEN ("AU & "B"

Models)e. Start fuel - ONf. Ignition - ON

2. Starta. Depress Start Button and hold until

N, reaches 35%b. Start fuel off at EGT 450C or

N j = 35%c. Engine motoring speed 18% within G4,5

15 seconds3. Start to ground idle speed 45 seconds G6,7

maximum (N j 37.5 - 42.7%) EGT not toexceed 816C for L-7. 760C for L-5

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4. Oil pressure 10 psi minimum G8,95. Ignition off

a. Cross feed - OPEN ("C" Model)b. Repeat steps 1b, 1d, 1e, and 1f for

other eng.c. Repeat steps 2, 3, and 4d. After engine stabilizes at ground

idle - Ignition - OFF6. Ground idle to flight idle over 80 rotor G10

rpm. (Torque not to exceed 1200 footIbs) (On single engine "C" Model. 1300foot Ibs)a. Boost Pumps - ON

Crossfeed - CLOSED ("C" Model)7. Beep switch operation, pilot and co- G11-16

pilot No. 1 and BOTHa. Pilot and copilot rotor tachometer 82-4

readings 4 rpm split max.8. Bleed band check (optional) (Ref. Fig. 5)

a. Operate eng. at F.1. for 2 min.b. Station C.E. at eng. to determine

closurec. Slowly increase beep (rate not to ex

ceed 1% N 1 in 10 sec.)d. Check N I speed with Fig. 5 (Tol

erance +0, -2% NI)

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9. Eng. oil press flux check 5 psi max.APU OFF

NOTERotors at 230 rpm (225 "B" Model)

Fuel Boost and Crossfeed - CH ECK1. Al l boost pumps off H8,9

a. Observe both warning lights - ON2. Crossfeed - OPEN H2,H103. Turn on boost pump (one at a time)

a. Observe both warning lights - OUT4. Check all boost pumps H8,9,10

Underfrequency Check1. Both engines to minimum beep2. Both emergency beeps to full decrease3. Remain at or below 193 4 rpm for

5 seconds ("A" and "B" Model) 2044 rpm for 5 seconds ("C" Model and"B" Model w/2200 series xmsn)

4. Check generators remain on line above197 or 208 rpm

5. Beep to 230 rpm (225 "B" Model) 034No Relative Torque Change From G17Detent to Full Down Movement of Thrust

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Transmission Press Indicator Operation 85-81. Check individual readings. Maximum al

lowable flux (10% of nominal reading)2. Scan reading 3 psi of low transmis

sion3. Test position to 0 psi4. Warning lights ON at 20 2 psi

Transmission Temperature Indicator 89-14Operation

1. Check individual readings2. Scan reading 50 of high temp.

Xmsn3. Test position to -70C or below

Engine Vibration Check (optional)81ade Track (SAS "OFF")

1. 230 rpm (225 "B" Model)2. Thrust in detent3. %" spread between each blade and

master blade4. Ye" maximum total separation

Radio Operation1. Ensure all radios are operating

Anti-Collision Lights - 0 N

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TAXI AND HOVER CHECKBrakes

1. Pilots and copilots. right and left 11-13Power Steering Check

1. Left and right turnsa. Full 90 turns

2. Wheel centering - swivel locks E17,18LOCKED

3. Directional control E14-16a. Swivels unlocked - 10 deviation

per 100 ft.b. Swivels locked - 50 deviation

per 100 ft.Lift Off

1. Check ground instability2. Apply brakes and lift front gear off

ground and check rear brakes3. Check flight control response4. SAS "ON". Check for hardovers5. Check instruments for normal operating

ranges6. Lift off to hover

SAS Check F1-61. Stabilize at a hover

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2. Check pitch, roll, and yaw on Both, No.1,and NO.2 SAS

NOTENo return to trim in roll axis on "B" &"C" Model

3. Check engage error on each SASControl Positions C8,9

NOTESAS off if engage error exists

1. Longitudinala. Crosswind hoverb. Measure positionc. Note indicator positiond. Tolerance %" forward to %" aft

of neutral position2. Lateral C10

a. Hover into wind,b. Measure positionc. 0 to 1,0" right of neutral position

3. Directional C11a. Hover into windb. Measure positionc. 1,0" maximum split (Refer to

Table 1.)

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4. Trim wheel operationa. Note longitudinal cyclic position C12,13

on indicatorb. Rotate trim wheel full forward

NOTEPosition indicator should move 1.4O.5 inch

c. Repeat for aftEngine Anti-Ice - CH ECK (Do not check D35with screens installed)

1. Place Ale on ground. Thrust In detent2. Engine Anti-Ice switch - ON

a. Note EGT rise (both engines)b. Note N1 drop (both engines)

. Single Engine Operation1. Hover on individual engines G182. Note

a. N 1b. EGTc. TQ

3. Torques should be within 12%differential

Emergency Beep Operation1. Both generators - OFF G1

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2. Battery switch to emergency G193. Check each emer beep switch for In

crease then decreaseEGT - CHECK B15

1. Match NI's2. Note EGT readings

Droop Eliminator G201. Establish 230 rpm in detent (225 "B"

Model)2. Lift off to stabilized hover3. Maximum stabilized droop 3 rpm

Fuel Boost - CH ECK H111. All boost pumps OFF for 2 minutes

Heater Operation 036-391. Check heater duct controls2. Light off within 30 seconds3. Switch heater 0 FF. Check that blower

continues to run until combustion cham ber cools

4. Vent position operation

Flight Instruments1. Gyro compass 2 0 split between pilot and

copilot indicators

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2. Mag compass 5 0 of gyro compassindication

3. VGI alignment4. Turn and slip indicator5. IVSI6. ClocksInstrument Check

1. Check all instruments for normal 816,17operation

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FORWARD FLIGHT CHECI< - CH-47ASpeed Sweep Check

NOTERecord zero A/S long. cyc. positionfrom hover check.

1. Airspeed 60 knotsa. Record long. cyclic pos. from

indicatorb. Record lateral cyclic positionc. Record directional pedal splitd. Check airspeed on pilot and 818,19

copilot indicatorsNOTE

7 knot differential between indicators4 knot fluctuation all speeds

2. Airspeed 80 knotsa. Record long. cyc. positionb. Record cyc. speed trim lift off (lift

off 80 knots 10 knots)3. Airspeed 100 knots

a. Record long. cyclic positionb. Note airspeed pilot and copilot indicators (5 knots difference maximum)

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c. Record cyclic speed trim full extension F8-10100 10 knots.

4. Airspeed 120 knotsa. Record long. cyclic position

5. Airspeed 132 knots or Vnea. Record long. cyclic positionb. Record lateral cyclic positionc. Record directional pedal splitd. Check airspeed of pilot and copilot in

dicators (5 knots difference maximum)e. Evaluate 1/Rev and 3/Rev vibra- 11-3

tion at rotor rpm closest to 230 forminimum vibration level

f. Check coordinated turns6. Airspeed 100 knots

a. Record retraction of speed trim 100 10 knots

7. Airspeed 80 knotsa. Record full retraction of speed trim

(80 knots 10 knots)Manual Operation

1. Establish 90 knots A/S2. Place speed trim switch to manual. F11Fully extend and retract both actuators,

observing indicator movement. Switch toauto.

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3. Increase A/S to 70 knots. Observethat both indicators have started to movefrom retracted position. Record eye.speed trim lift off. (Lift off 60 knots 10 knots)

4. Airspeed 80 knots. Record long. cyclicposition

5. Airspeed 100 knotsa. Record long. cyclic positionb. Note airspeed. pilot and copilot indi

cators (5 knots difference maximum)6. Airspeed 120 knots

a. Record long. cyclic positionb. Observe, that both indicators are in

the upper green block (Fully extended120 knots 10 knots)

7. Airspeed 140 knotsa. Record long. cyclic positionb. Record lateral cyclic positionc. Record directional pedal splitd. Check airspeed of pilot and copilot

indicators. (6 knots difference maxi mum)

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8. Airspeed 150 knotsa. Evaluate 1/Rev and 3/Rev vibra

tionb. Check coordinated turns

9. Airspeed 120 knotsRecord retraction of speed trim 120 10 knots10. Airspeed 60 knotsRecord full retraction of speed trim(60 knots 10 knots)

Manual Operation1. Establish 90 knots A/S2. Place speed trim switch to manual. F11

Fully extend and retract both actuatorsobserving indicator movement. Switch toauto. note indicators return to midrange.

SAS evaluation 120 knots F12,131. Check both. No. 1 and No. 2 In pitch.

roll and yaw axis.2. Check coordinated turns on single SAS

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FORWARD FLIGHT CHECK - CH-47CSpeed Sweep Check

NOTERecord zero A/S long cyclic positionfrom hover check

1. Stabilize A/S at 50 knots. Observethat both speed trim indicators are inthe lower green block

2. Increase A/S to 60 knotsa. Record long. cyclic position from In

dicatorb. Record lateral cyclic positionc. Record directional pedal splitd. Check airspeed on pilot and co 818,19

pilot indicatorsNOTE

7 knot differential between indicators4 knot fluctuation all airspeeds3. Increase A/S to 70 knots. Observe

that both indicators have started tomove from retracted position

Record cyclic speed trim lift off (liftoff 60 knots 10 knots)

4. Airspeed 80 knotsRecord long. cyclic position

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5. Airspeed 100 knotsa. Record long. cyclic positionb. Note airspeed pilot and copilot indi

cators (5 knot difference maximum)6. Airspeed 120 knots

Record long. cyclic position7. Airspeed 140 knots

a. Record long. cyclic positionb. Record lateral cyclic positionc. Record directional pedal splitd. Check airspeed of pilot and copilot

indicators (6 knots difference maxi mum)8. Airspeed 150 knots

a. Record long. cyclic positionb. Evaluate 1/Rev. and 3/Rev. vibra

tionc. Check coordinated turns

. 9. Increase airspeed to 160 knots. Observethat both indicators are in the uppergreen block (fully extended 160 knots 13 knots)

NOTEIf unable to reach 160 knots. estimateindicator position

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10. Airspeed 150 knotsRecord retraction of speed trim (160knots 13 knots)

11. Airspeed 60 knotsRecord full retraction of speed trim(60 knots 10 knots)

Manual Operation1. Establish 110 knots A/S2. Place speed trim switch to manual. F11

Fully extend and retract both actuators observing indicator movement.Switch to auto, note indicators returnto mid range

SAS Evaluation 120 knots F12.131. Check both, No. and No.2 in pitch, roll

and yaw axis2. Check coordinated turns on single SAS

Engine Power1. Determine topping altitude from 621-24

Figure 1, 2, 3, or 42. Single engine at maximum beep-droop

rotor rpm to attain maximum N I reading3. Record

a. Pressure altitude (Set altimeter at29.92)

b. Outside air temp.

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c. Airspeedd. Torquee. RPMf. N 1g. EGT

NOTE"e" Model - maximum torque singleengine 1015 lb. ft. Dual engine 890 lb.ft.

Autorotation C14,151. Establish 70 knots2. Record

a. Pressure altitudeb. Outside air temp.c. Fueld. RPM in detente. RPM in flat pitchf. Pedal split (2" maximum) (Refer to

Table 1.)Navigation and Communication

1. UHF J4a. Transmit and receiveb. Preset and manual tune

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2. FMa. Transmit and receive

b. Homing J5(1) Center needle note relative course(2) OFF flags concealed

3. Gyro and magnetic compassa. Synchronize compass J6b. Magnetic compass 5% of gyro J7

compass on North, South, East, Westheadings

c. 2 0 maximum difference between pilotand copilot indicators

4. VORa. Tuning, reception, volume J8b. No.2 needle on gyro compass 3 J9

of true magnetic course to stationc. Course direction indicator J10

(1) 3 of true magnetic course(2) 10 0 off course gives full needle

displacementd. Station passagee. Total NO.2 needle fluctuation 10 0 J11

5. ADFa. Tuning, reception, volume

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b. Check ADF, ANT, LOOP, and BFOoperation

c. NO.1 needle on gyro compass 3 12,13of magnetic bearing to station

d. Total NO.1 needle fluctuation 5 J14e. Station passage

6. Marker beacona. Push-to-test lights J15b. Check audio high and lowc. Check light operation high and low J16

7. Transponder CH ECK APX-44 or IFF J17a. Master Control Switch - ST. BY. pilotlight - ONb. Warm up 3 to 5 minutesc. Audio switch - OFFd. l iP switch - OFFe. Function control switch - CIVI Lf. Mode 2 and 3 switch - As requiredg. Mode 1 and 3 code control switch

As requiredMiscellaneous

1. IVSI2. Turn and slip indicators3. Altimeters

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a. Pilot and copilot difference100 @ 0 to 500 feet150 @ 1000 - 2000 feet200 @ 2000 - 4000 feet300 @ 4000 - 8000 feet350 @ 8000 - 10,000 feet

b. No needle sticking at any altitude4. Heater operation

Record Instrument IndicationsAfter Landing Check

1. Anti-collision lights OFF2. Transponder (IFF) OFF3. SAS OFF4. Swivel locks - As required5. Power steering - As required

Engine Shutdown1. Parking brakes - SET2. Minimum beep - CH ECK

a. Both engines G25,26(1) 204 4 rpm (L-5 engines)(2) 208 4 rpm (L-7 engines)(3) 220 2 rpm ("C" Model)

b. Individual engines(1) 204 4 (L-5 engines)

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(2) 208 4 (L-7 engines)(3) 216 2 ("C" Model)c. Adjust for closest possible TO match

without excessive N I splitNOTE

1. "S" Model with -2200 series aft transmission installed, "C" Model mInImum beep applies

2. During minimum beep check, recordground idle speed for each engine.

3. Always beep up then down after each adjustmentd. No. 2 engine condition l e ve r

GROUND THEN STOPe. Fuel boost pump switches - OFFf. Fuel valve switch - CLOSE ("A" &

"S" Models only)g. Engine beep trim switch (No. 1 and2) Regain 230 ROTOR RPM 225

ROTOR RPM "S" Modelh. APU - STARTI. Engine beep trim switch (No. 1 and

2) - DECREASEj. No. 1 engine condition l eve r - GROUND THEN STOPk. Fuel boost pump switches - OFF

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I. Fuel valve switch - CLOSE ("A" &"B" Models only)m. All radios and navigation equIp

ment - OFFn. Generator switches - OFFo. APU - STOPp. Battery switch - OFF

Conclusion and De- Briefing1. Check engine topping (See figure 1, 2,

3, or 4)2. Check stick plot (See chart 1, 2, or 3)

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CH-47 AMTPC

Malfunction Probable Cause

b. Defective hydraulic pump motor is causingAPU drag

c. APU bearing wear causing excessive drag

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CH-47 AMTPC

SECTION BINSTRUMENTS


81. Altimeters in excess of 50 feet of fieldelevationa. Altimeter set wrongb. Faulty altimeter

82. Pilots and copilots rotor tachometer indicatorinoperativea. Defective rotor tachometer generatorb. Defective wiring

83. Pilots rotor tachometer indicator inoperativea. Defective rotor tachometer indicatorb. Defective wiring

84. Greater than 4 RPM split between pilots andcopilots rotor tach indicatorsa. Defective indicatorsb. Defective wiring

85. Pressure on low individual indication is moreor less than 3 psi of scan indicationa. Faulty indicatorb. Faulty selector switch

86. Fluctuation is more than 10% of nominalindicationa. Faulty transducer

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b. Defective pressure relief valve87. Transmission oil pressure indicating system in

operativea. Transmission oil pressure circuit breaker outb. Defective indicatorc. Defective selector switchd. Defective wiring

88. When scan select switch is placed to test,pointer moves to 0 psi but the transmission oillow caution l ight does not come ona. Defective indicatorb. Defective wiring

89. Temperature drops to -70C (scan or individualpositions)a. Faulty temperature bulbb. Broken wirec. Faulty indicatord. Faulty selector switch

810. Temperature goes to full high indicationa. Faulty temperature bulbb. Faulty indicatorc. Faulty selector switch

811. Temperature indication on high individual indication is more or less than 5 of scan indicationa. Fal;Jlty indicator

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b. Faulty selector switchc. Defective wiring

812. With scan selector switch In TEST position, theindicator pointer moves toward but not below-70Ca. Defective indicatorb. Defective selector switch

813. Transmission oil temperature indicating systeminoperative (all positions)a. Transmission oil temperature circuit breaker

outb. Defective se lector switchc. Defective indicatord. Defective wiring

814. One transmission does not indicate when se lecteda. Defective selector switch

815. EGT's have excessive split with matched NI'sa. Faulty EGT indicatorb. Faulty EGT harnessc. Check EGT system calibration

816. Engine oil pressure fluctuates in excess of 5psia. Defective indicatorb. Defective transmitterc. Filters clogged

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d. Sticky relief valvee. Defective oil pump

817. Unable to reduce angle box pressurea. Stiff or hung up pressure relief springb. Crossed wires between combining and en

gine transmissions818. Excessive A/S indicator fluctuations

a. Faulty indicatorb. Leak in pitot static lines

819. Greater than 7 knots difference between pilotsand copilots A/S indicatorsa. Faulty indicatorb. Leaking lines

- - - - - - - - - ~ ~58

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CH-47 AMTPC

SECTION CFLIGHT CONTROLS


C1. Binding in controlsa. Connecting bolts overtorquedb. Faulty rod endsc. Improper riggingd. Floor fasteners loosee. Defective stick boost actuators

C2. Trim wheel will not functiona. Disconnected DCP actuator motorb. AC SIT circuit breaker outc. Defective SIT amplifierd. Trim wheel inoperativee. DCP actuator inoperativef. Defective wiring

C3. Magnetic brake will not hold controls at fulltravela. Switch wired backwardsb. Magnetic brake slippingc. Magnetic brake inoperatived. Circuit breaker oute. Control centering incorrectly riggedf. Defective centering spring

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C4. Control system will not stay in displaced posi tiona. Twisted brake line (pedals)b. Improper balance spring settingc. Defective viscous dampersd. Defective artificial feel systeme. Improperly adjusted balance and detent

C5. Control centering lacks authority throughoutrangea. Magnetic brake positioning arm not proper

ly adjustedb. Wrong magnetic brake installed

CG. Control travel incorrecta. Improper rigging; stops improperly set or

upper boostactuator improperly setb. Cockpit indicator incorrectc. Binding in controls

C7. Breakout forces not symmetricala. Balance springs improperly setb. Binding in controlsc. Improper spring installed

C8. In crosswind hover longitudinal cyclic stick posi tion is greater than %" forward or %" aft ofneutrala. AIC improperly rigged

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b. Cyclic position indicator improperly positioned

c. Trim wheel not centeredd. Speed trim not properly sete. Pitch link adjustment required

C9. Excessive control displacementsa. A/C incorrectly riggedb. SAS engage error

C10. Lateral stick is out of tolerance during an intothe-wind hovera. A/C incorrectly rigged

C11. Excessive pedal split in hovera. SAS engage errorb. A/C incorrectly rigged

C12. With trim wheel rotated full forward cyclic stickmoves aft 1.4 O.5 inches as noted on stickposition indicatora. Trim wheel installed backwardsb. Wiring reversed to trim wheel electrical con

nectorC13. With trim wheel moved full aft, cyclic stick posi

tion indicator indicates less than 1.4 O. 5 inchaft cyclic stick travela. Defective servo-amplifier card in speed trim

amplifierb. Defective trim wheel

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c. Defective (DCP) stick trim actuatorC14. Autorotation rpm low

a. A/C incorrectly riggedb. Blade pitch angle too high

C15. Excessive pedal splita. A/C improperly riggedb. SAS engage error

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CH-47 AMTPC

SECTION DELECTRICAL


01. No indication of battery power supplied to thehelicoptera. Caution lights circuit breaker outb. Battery disconnectedc. Battery lowd. Faulty battery relaye. Faulty battery switchf. Defective wiring

02. Cockpit dome lights inoperativea. Circuit breaker outb. Burned out bulbc. Defective switchd. Defective wiring

03. Cockpit dome lights will not dima. Defective rheostatb. Defective wiring

04. Cockpit white dome lights only inoperativea. Defective bulbsb. Defective l ight selector switchc. Defective wiring

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05. Utility lights inoperativea. Circuit breaker outb. Defective light assemblyc. Defective wi ri ng

06. Instrument flood lights inoperativea. Defective bulbsb. Defective instrument panel flood

light switchc. Defective wiring

07. Jump lights and TROOP ALARM inoperativea. Defective jump light relayb. Defective wiring

08. Troop alarm bells inoperativea. Circuit breaker outb. Defective alarm bell switchc. Defective wiring

09. Cabin and ramp lights inoperativea. Defective cabin light relayb. Defective switchc. Defective wiring

010. Cabin and ramp lights inoperative in REDa. Defective switchb. Defective bu Ibsc. Defective relay

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d. Defective wiring011. No power to emergency bus

a. Feeder circuit breaker outb. Defective BATTERY switchc. Defective emergency bus relayd. Defective wiring

012. Caution lights inoperativea. BATTERY switch OFF or in EMERGENCYb. Caution light circuit breakers outc. Defective caution light paneld. Defective wiring

013. Caution lights do not come on when testswitch is depresseda. Defective test switchb. Defective caution light panelc. Defective wiring

014. Master caution light (MCLC) won't cancel whenreseta. Master cautio'n capsule sticking in panelb.' Defective master caution light panel

015. Caution lights do not dima. Defective dim switchb. Defective dimming relayc. Defective caution light paneld. Defective wiring

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016. When dome light switch is placed to WH ITE{caution lights dimmed} the caution lights donot go to brighta. Defective dimming lock-out relayb. Defective wiring

017. No. 1 generator won't come on linea. Defective voltage regulatorb. Defective protection control panelc. Defective frequency sensing and time delay

relay {APU and generator control box}d. Defective wiringe. Defective generator

018. No.1 or No.2 generator OFF, No.1 or 2 GENOUT CAUTION light ON {no ac cross-tie indicated on load meter} No. 2 transformer/rectifier warning light ONa. Ac bus control circuit breaker outb. Defective ac bus-tie relayc. Defective wiring

019. Both generators on line, No. 2 rectifier OFFcaution light is on, indicating dc cross tie {No.1loadmeter indication increasing}a. Secondary bus insufficiently loadedb. No. 2 transformer/rectifier 3-phase ac cir

cuit breaker outc. Defective No. 2 transformer/rectifier

/

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d. Defective wiring020. Windshield anti-ice system will not cycle at

present temperature of 45 Ca. Defective windshield temperature sensor

elementb. Defective windshield anti-ice controllerc. Defective anti -ice control relay

021. Windshield anti-ice system will not operate beIowan outside air temperature of 24Ca. Windshield anti-ice ac circuit breaker outb. DC circuit breaker outc. Defective temperature sensing elementd. Defective windshielde. Defective controllerf. Defective wIring

022. No pitot heat and SAS port heata. Pitot heat circuit breaker outb. Defective pitot heat switchc. Defective heating elementsd. Defective wiring

023. Searchlight-pilots or copilots search light willnot come ona. Searchlight circuit breaker outb. Defective searchlight filament (SLT-FIU

switch on thrust lever

Il

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c. Defective bu Ibd. Defective searchlight assemblye. Defective wiring

024. Pilot's or copilot's searchlight will not extenda. Searchlight control circuit breaker outb. Defective SEARCH L1G HT control switch on

thrust leverc. Defective SEARCH L1G HT switch (SLT

CONT)d. Defective wiringe. Defective searchlight assembly

025. Pilot's or copilot's searchlight will not rotateleft or righta. Defective SEARCHLIGHT control switchb. Defective wIringc. Defective searchlight assembly

026. Top and bottom anti-collision lights will n.otrotate or come ona. Anti-collision lights circuit breaker outb. Defective anti-collision light switchc. Defective wiringd. Defective light assembly

027. Anti-collision light rotates but will not comeona. Defective bulb

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CH-47 AMTPCMalfunction Probable Cause

b. Defective light assemblyD28. All position lights inoperative

a. Position lights circuit breaker outb. Defective position lights switchc. Defective wi ri ng

D29. Position lights will not dima. Defective position lights switchb. Defective position lights dimming resistorc. Defective wiring

D30. Instrument lights inoperativea. Circuit breaker outb. Defective rheostatc. Defective dimming rheostatd. Defective wiring

D31. Instrument lights will not brightena. Defective rheostatb. Dimming rheostat requires adjustment

D32. No emergency flood lights when GENeratorCONTROL and BATTERY switches are OFFa. SECONDARY COCKPIT LIGHTS circuit

breaker outb. Pilot's instrument light's rheostat is OFFc. Defective flood light relayd. Defective wiring

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033. Fire detection lights inopera tivea. Burned out bulbb. Defective PRESS-TO-TEST switchc. Defective wiringd. Defective eng detection elemente. Defective controller

034. At emergency minimum beep, generators dropoff the line at 198 or 209 rpma. Defective frequency and time delay relayb. Defective PMG section on generator

035. When engine anti-ice switch is placed to ON, adecrease in N I is not detected and EGT doesnot risea. Defective switchb. System blockedc. Defective valve

036. Heater blower inoperativea. Heater blower circuit breaker outb. Defective blower relayc. Defective blowerd. Defective wiring

037. Heater will not l ight off but vent worksa. Plug fouledb. Thermostat hot

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D38. Heater does not light off within 30 secondsa. Defective blowerb. Defective air pressure switchc. Defective relaysd. Defective wiring

D39. Heater inoperativea. Defective blower systemb. Defective fuel systemc. Defective ignition system

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CH-47 AMTPC

SECTION EHYDRAULIC

Malfunction Probable Cause".

E1. Parking brake won't reseta. Utility hydraulic switch inoperativeb. Brake incorrectly rigged

E2. Parking brake warning light won't stay ona. Brake incorrectly riggedb. M icroswitch incorrectly rigged

E3. No boost pressure indicationa. Defective transmitterb. Inoperative pump

E4. Fluctuating pressurea. Defective transmitterb. Low service levelc. Defective gauged. Trapped air in the systeme. Defective flight control hydraulic boost

pumpE5. No. 2 flight boost pump pressure does not

build up within 30 seconds after APU start a. AG B overloadedb. AG B hydraulic motor defectivec. Defective frequency sensing and time delay

relay

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d. Defective wiringE6. No. 1 boost pressure is below 2500 psi

a. Low reservoir levelb. Trapped air in systemc. Hoses kinkedd. Defective flight control hydraulic boost in

dicatore. Defective flight control hydraulic boost trans

mitterf. Defective flight control hydraulic boost pump

E7. Hydraulic boost switch OFF, caution light outa. Defective hydraulic boost pressure switchb. Defective wiring

E8. Hydraulic boost pressure does not indicate with-In 2 seconds after switch is turned ona. Defective hydraulic boost switchb. Defective hydraulic boost solenoid valvec. Defective hydraulic boost pump

E9. Able to turn off both flight boostsa. Interlock malfunction

E10. No.1 boost will not drop to 500 50 PSIa. AGB switch malfunctionb. Defective boost pump solenoid valvec. Defective No. 1 hydraulic boost pump

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d. Defective wiringE11. Brakes are spongy

a. Air in brake lineE12. Brakes are leaking

a. Over servicedb. Faulty seal

E13. Brakes will not holda. Defective utility hydraulic systemb. Defective wheel brake

E14. Intermittent power steeringNOTE

When power steering or swivel lockswitch is cycled. if hydraulic pressuredrops approximately 200 pounds.stays there for short duration and re turns to previous value. the problem ishydraulic; if no drop. the problem iselectrical

a. Faulty actuatorb. Faulty control box

E15. Power steering turns left or right with controlin neutrala. Struts unevenb. Aft gear misalignedc. Power steering not properly adjustedd. Defective actuator

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CH-47 AMTPCMalfunct ion Probable Cause

e. Defective hydraulic systemf.. Defective wiring

E16. Aircraft turns left or right with swivels lockeda. Struts unevenb. Aft gear misalignedc. Swivels not locking

E17. Wheels will not center with swivel locks turnedONa. Aft gear misalignedb. Swivel lock inoperative

E18. Wheel does not center after liftoffa. Defective utility hydraulic systemb. Defective centering cam assembly

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CH-47 AMTPC

SECTION FSAS/SPEED TR 1M


F1. Yaw kicksa. Water in side slip linesb. Defective SAS link

F2. No pitch or roll responsea. Failed gyro in SAS box

F3. Hardovera. Defective card in SAS box

F4. Oscillationa. Faulty linkb. Gain too high in given channel

F5. Excessive left pedal with helicopter trimmedIn hover and SAS ona. Pedals incorrectly riggedb. Yaw extensible link not adjusted for neu tral

F6. In a hover SAS is switched from BOTH ON tosingle SAS ON and a kick is felt in the yawaxis (engagement error)a. Yaw channel for given SAS requires bal

ancingb. Yaw link feedback potentiometer requires

adjustment

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c. Defective demodulator-modulator card inyaw channel

d. Defective SAS boxF7. Forward or aft cyclic trim actuator does not

start to extend at 60 or 80 knots indicatedair speeda. Forward or aft cyclic trim channels out ofadjustmentb. Failed actuatorc. Defective amplifierd. Leak in pitot static lines to the amplifier

F8. Cyclic speed trim does not fully extend or isfully extended too soona. Speed trim out of adjustment

F9. Cyclic position plot too high or lowa. DCP schedule out of adjustmentb. AIC incorrectly rigged

F10. Cyclic speed trim completely inoperative inautomatic modea. Speed trim ac circuit breaker outb. Defective amplifierc. Defective wiring

F11. Cyclic speed trim does not operate manuallya. Failed actuatorb. Faulty switchc. Defective wiring

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CH-47 AMTPC


F12. Uncoordinated turnsa. SAS roll yaw circuit faultyb. Leak in side slip lines

F13. Yaw huntinga. High gain in yaw channel In SAS boxb. Leak in side slip lines

I

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CH-47 AMTPC

SECTION GENGINES AND TRANSMISSIONS


G1. Emergency beep inoperativea. Faulty relayb. Faulty or failed actuator motorc. BATTERY switch OFF

G2. Normal N II system inoperativea. No AC power, circuit breaker not resetb. Defective remote control boxc. Defective wiring

G3. Both normal and emergency engine control sys tems inoperativea. Defective N II actuatorb. Defective emergency trim relayc. Defective wiring between remote control box

and actuatorG4. No.1 engine will not motor with START button

depresseda. Engine start circuit. breaker outb. Defective start switchc. Defective engine start solenoid valved. Defective start relaye. Defective utility hydraulic systemf. Defective wIring

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CH-47 AMTPC


G5. Engine will not accelerate to 19% within 15seconds during start cyclea. Insufficient starting fuelb. Defective utility hydraulic start solenoid

valvec. Defective utility hydraulic systemd. Defective hydraulic starter motor

G6. Engine will not accelerate to ground idlea. N I improperly riggedb. Faulty start motorc. G.!. ADJ screw requires adjustment

G7. Engine will not accelerate from ground idle toflight range within 45 secondsa. N I actuator slowb. Fuel control acceleration and start fuel re

quires adjustmentc. Bleed band defectived. Defective engine fuel control

G8. No oil pressurea. Transmitter disconnectedb. Transmitter failedc. Gauge inoperative

G9. Engine oil pressure below 10 psia. Clogged No.2 bearing filterb. Engine oil pump not adjusted properly

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CH-47 AMTPC


c. Defective indicatord. Defective engine oil pressure transmittere. Improper transmitter installed

G1O. Transient torque exceeds 1200 foot pounds(1300 foot pounds, single engine)a. Acceleration schedule set too highb. Faulty fuel controlc. Faulty torque indicating systemd. Engine beep trim switches not at minimum

beep prior to moving ECl to FIG11. Pilot and copilot beep trim switches inopera

tivea. Engine trim dc circuit breaker outb. Defective wIring

G12. Pilot's NO. 1 AND 2 ENGINE BEEP TRIMswitch inoperativea. Defective switchb. Defective wiring

G13. To match engine torques, engine beep trimswitches must be beeped in opposite direc tionsa. Excessive N II actuators speeds between

engine No. 1 and No. 2b. Beep trim actuator speeds In the No.1 and

No. 2 engine remote control box vary ex cessively

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CH-47 AMTPC


G14. Engine torques will not matcha. N II system not rigged properlyb. Defective N II actuatorc. Defective engine fuel controld. Defective engine torque transmittere. Defective torque indicatorf. Defective engine

G15. While beeping engines to match torque. No. 1engine beeps up much faster than No. 2 caus ing an excessive torque split. and No. 1 enginemust be beeped in the opposite direction tomatch torques (engines stabilized. torques remain matched)a. Excessive difference in N" actuator speeds

between the No. 1 and No.2 engineb. Defective N II actuatorc. Defective remote control box

G16. Excessive hunting with engine torquesmatcheda. Defective N" actuatorb. Defective remote control boxc. Defective wiring

G17. Excessive change in engine torque when thrustlever is moved to full downa. Flight controls (thrust system) incorrectly

rigged

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CH-47 AMTPC


b. Engine droop eliminator potentiometer outof adjustment

G18. Difference in engine torque indications duringsingle engine operation greater than 6% of aver age TO between enginesa. Faulty torque indicatorb. Faulty torque indicating system of enginec. Emergency engine trim circuit breaker outd. Defective emergency beep trim switche. Defective wIring

G19. Engine emergency beep trim switch operatesin increase but inoperative when placed to decreasea. Defective switchb. Defective actuatorc. Defective emergency trim relayd. Defective wiring

G20. Droop greater than 3 rpma. Droop potentiometers improperly adjustedb. Engine improperly riggedc. Defective droop eliminator potentiometer

G21. Excessive torque fluctuation of toppinga. ~ a u l t y transducerb. Faulty indicatorc. Excessive Ale vibration

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CH-47 AMTPCMalfunction Probable CauseG22. Excessive N1 fluctuation at topping

a. Faulty indicatorb. Faulty tachometer generatorc. Defective wiring

G23. Topping too lowa. N1 improperly riggedb. N II improperly riggedc. Topping adjustment lowd. Torque rate limiter adjustment lowe. Improper bleed band adjustment

G24. Torque low at topping (N I and EGT appearnormal)a. Defective torque indicating system

G25. At minimum beep, rotor rpm not 208 4,204 4, or 21 6 2a. Minimum beep trim resistor in RH pod re

quires adjustmentG26. Unable to adjust minimum beep

a. N II engine controls improperly riggedb. Defective minimum beep trim variable re

sistorc. Defective N II actuator (feed back pot)

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CH-47 AMTPC

SECTION HFUEL

Malfunction Probable CauseH1. Main fuel valve does not close when fire T

handle is pulled outa. Faulty T-handle micro switchb. Defective wiring

H2. Crossfeed valve does not open when switch ISplaced to ONa. Crossfeed control circuit breaker outb. Defective crossfeed valve switchc. Defective crossfeed valved. Defective wIring

H3. Indicator pointer pegged full scale for all positions of fuel selector switcha. Open shielded wiring from tank probes

H4. No fuel indication all switch positionsa. FUEL OTY system requires calibrationb. Defective indicatorc. Defective selector switchd. Defective wIring

H5. Indicated total does not equal computed totalby 50 pounds or 300 poundsa. FUEL OTY system requires calibrationb. Defective selector switchc. Defective wi ri ng

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CH-47 AMTPCMalfunct ion Probable CauseH6. Fuel quantity indicator pointer erratic

a. Open shielded wiring from tank probesb. Defective indicatorc. Defective Wiringd. Defective probes

H7. Tanks full, no single tank indication. Total indication OK.a. Defective selector switchb. Defective wiring

H8. No fuel pressure warning lights when fuel boostpumps are OFFa. Caution lights circuit breaker outb. Defective wiring

H9. Boost pump inoperativea. Fuel boost pump circuit breaker outb. Defective boost pump relayc. Defective pu mpd. Defective wIring

H10. With crossfeed switch at OPEN and single boostpump turned on, only ~ h caution light for thetested system turned on goes outa. Crossfeed circuit breaker outb. Defective crossfeed valvec. Defective caution lightd. Defective wiring

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CH-47 AMTPC


H 11. Engine flames out with boost pumps offa. Failed engine driven boost pump

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CH-47 AMTPC

SECTION IVIBRATIONS


11. Excessive 1/Rev vibrationa. Blades out of trackb. Weak lag damperc. Blades unbalanced

12. Excessive 3/Rev vibrationa. Loose aft pylon splice boltsb. Loose component support fittingc. Loose engine. fairing. or tail coned. Loose landing gear, work platforms, access

doors, ramps, escape panels. windows. ordoors

13. High frequency vibrationa. Sync shaft out of balanceb. Engine out of balance or has F.G.D.c. Excessive radial play on transmission

shaftsd. Defective lord mount on sync shafting

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CH-47 AMTPC

SECTION JCOMMUN ICATION/NAVIGATION


J1. No ICSa. Intercom switches offb. Failed intercom boxc. Broken jack cordd. Broken or improper headsete. Faulty interphone junction box

J2. Radio inoperative. a. Defective R/T unitb. Defective wiring

J3. VGI will not aligna. Faulty gyrob. Faulty indicatorc. Circuit breaker out

J4. UHF continues to channela. Faulty control head

J5. FM homing will not center, always gives fullright or left deflectiona. Faulty antennab. Faulty home sensing unitc. Shortened coaxial cabled. Weak receiver

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CH-47 AMTPCMalfunction Probable CauseJ6. Gyro compass will not hold sync

a. Faulty gyrob. Faulty flux valvec. Faulty indicator

J7. Gyro compass will not synca. Faulty indicatorb. Flux valve needs re-swinging

J8. VOR volume weaka. Faulty receiverb. Low sensitivity

J9. VOR off heading (No. 2 needle)a. Faulty receiver

J10. Course direction indicator does not give 10sweepa. Receiver requires adjustment

J11. Excessive needle fluxa. Faulty receiver

J12. ADF indicates OFF heading greater than 3 aa. Antenna loop requires compensationb. Faulty receiver

J13. No.1 needle more than 3 a off magnetic bear ing to stationa. Gyro compass not synchronizedb. Faulty antennac. Fau.lty receiver

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CH-47 AMTPCMalfunct ion Probable CauseJ14. Excessive No. 1 needle flux

a. Faulty receiverb. Faulty antenna

J15. Marker beacon audio weak or inoperativea. Low sensitivity (place adjustment to posi

tion 5)b. Faulty receiver

J16. Marker beacon light inoperative or inoperativeon low positiona. Low sensitivityb. Faulty receiverc. Antenna not peaked

J17. Transponder malfunction: pilot light not on;press the test button. If pilot light still fails tol ight either the bulb is burned out or no poweris reaching the set

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~ " CH-47 AMTPCFAILURE Of ONE ENG INEDURING TAKEOFF

Maintain Necessary Control and Power(Continued Flight)

Engine beep trim switch (No. 1 & 2) MAINTAIN 230 ROTOR RPM

Airspeed - BEST SINGLE-ENGINECLIMB

Cleanup Dead EngineEngine condition lever (affected engine)

STOPPresence of fire - CH ECKFuel valve switch (affected engine) - CLOSECrossfeed switch - AS REQUIREDFuel booster pump switches (affected

engine) - AS REQU IREDMaintain Necessary Control and Power(Discontinued Flight)

Thrust control rod - MAINTAINSETTING

Cyclic stick and directional p e d a l s ADJUST

Thrust control rod - RAI SE

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~ ~ ~ ~ , , ~ ~ ~ " " " " " ~ H-47 AMTPCFAILURE OF BOTH ENG INESOUR ING FLIGHTMaintain Necessary Control

Thrust control rod - ADJUSTAirspeed - MAINTAIN 70 OR 90

KNOTSEngine or engines - RESTART

Cleanup Dead EnginesEngine condition levers - STOPPresence of fire - CH ECKFuel valve switches - CLOSECrossfeed switch - CLOSEFuel booster pump switches - OFF

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CH-47 AMTPCFAILURE OF ONE ENGINEOUR ING FLIGHT

,--......

Maintain Necessary Control And PowerEngine beep trim switch (No. 1 & 2)

MAINTAIN 230 ROTOR RPMAirspeed - BEST SINGLE-ENGINE

CRUISECleanup Dead Engine,--......

Engine condition lever (affected engine) STOP

Presence of fire - CH ECKFuel valve switch (affected engine) CLOSECrossfeed switch - AS REQUIREDFuel booster pu mp switches (affected

engine) - AS REQU IRED

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CH-47 AMTPC

ENG INE RESTART DUR ING FLIGHTEngine condition lever - GROUNDFire control handle - CHECK INFuel booster pump switches (affected

engine) - CHECK ONCrossfeed switch - AS REQUIREDFuel valve switch - OPENIgnition switch - ONStart fuel switch - OPENStart pushbutton - DEPRESS AND

HOLDStart fuel switch - CLOSE (600C)Engine oil pressure - CHECKIgnition switch - OFFEngine instruments - RECHECKEngine condition lever - FLIGHTRotor rpm - 230Engine torque - MATCH

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. , , ~ ~ ~ CH-47 AMTPC

FUEL PRESSURE DROP - ENG INEOPERATING NORMALLY

Below 6,000 Feet - Engine OperatingNormallyMaster caution l ight - PUSH TO

RESETCrossfeed switch - OPENMaster caution panel - CHECK

Above 6,000 Feet - Engine Flames OutEngine condition lever (affected

engine) - STOPMaster caution light - PUSH TO

RESETCrossfeed switch - OPENMaster caution panel - CHECKEngine - RESTART

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~ ~ CH-47 AMTPCGO-AROUND WITH ONEENG INE INOPERATIVE

Cyclic stick - ADJUSTEngine beep trim switch (No. 1 & 2)

MAINTAIN 230 ROTOR RPMThrust control rod - ADJUST

TAKEOFF WITH ONE ENGINEINOPERATIVEPrior to Takeoff

Thrust control rod - 3-DEGREE DETENTRotor rpm - 230

TakeoffThrust control rod - RAISE AND

MAINTAIN 230 ROTOR RPMCyclic stick - ADJUSTTrim wheel - ADJUSTAirspeed - BEST SINGLE-ENGINE

CLIMB

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.:.CH-47 AMTPC

NORMAL ENG INE BEEP TR 1MSWITCH FAILURE

Both ac eng trim circuit breakersPULL IMMEDIATELY

Emergency beep trim switches - USEEMERGENCY ENGINE SHUTDOWNDuring Failure of Ac and DcElectrical Systems

Fuel valves - CLOSE (Manually)All other switches and controls - OFF

EMERGENCY ENG INE SHUTDOWNDuring Gas Producer Actuator orCondition Lever Failure

Fuel valve switch (affected e n g i n e ) CLOSE

All other switches and controls - OFFLOW OIL QUANTITY

Master caution lights - PUSH TORESET

Oil temperature and pressure indicators(affected engine) - CHECK

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CH-47 AMTPC

TRANSM ISS ION 0 I L TEMPERATURE ORPRESSURE CAUTION LIGHT ON


Thrust control rod - LOWERTransmission oil temperature and

pressure indicators - CHECKENGINE FIRE DURING STARTINGOR SHUTDOWN

Engine condition lever (affected engine) STOP

Fuel valve switch (affected engine) CLOSEEngine start pushbutton (affected engine)

PRESS AND HOLDStart fuel switch (affected engine)

CLOSEIgnition switch (affected engine) - OFFFuel booster pumps - OFF

AUXILIARY POWER UNIT FIREAPU switch - STOPEngine condition levers - STOPFuel valve switches - CLOSEPortable fire extinguisher - USE

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~ ~ CH-47 AMTPCENG INE COMPARTMENT FIREIN FLIGHT

Engine condition lever (affectedengine) - STOP

Fire control handle (affected e n g i n e ) PULL

Fire extinguisher agent switch - SELECTBOTTLE NO. 1 OR BOTTLE NO.2

Fuel valve switch (affected engine) CLOSE

Crossfeed switch - AS REQUIREDFuel booster pump switches (affected

engine) - AS REQUIREDElECTR ICAl FIRE

Personnel - ALERTEDAirspeed - 100 KNOTS OR BELOWBattery switch - EMERGENCYGenerator switches - OFFHand fire extinguisher - AS REQUIREDHelicopter - LAND AS SOON AS

PRACTICAL

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CH-47 AMTPCSMOKE AND FUME ELIM INATION

Airspeed - 80 to 100 knotsCargo loading ramp - OPENUpper half of main cabin doo r -

OPENPilot's sliding window - OPENHelicopter attitude - 20LEFT YAW

FUEL BOOSTER PUMP FAILUREMaster caution light - PUSH TO

RESETEngine condition lever (affected

engine) - STOPCrossfeed switch - OPENMaster caution panel - CH ECKFuel booster pu mp switches (affected

tank) - OFFEngine - RESTART

FUEL LOW CAUTION LIGHT ONMaster caution l ight - PUSH TO

RESETFuel quantity indicator - CHECKFuel quantity - BALANCE

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CH-47 AMTPC~ ' " " " " " " " " " " " " ' ' ' ' ~ , , ~ ' ' ' ' ~ ~ FAILURE OF ONE AC GENERATOR

Master caution lights - PU SH TORESET

All circuit breakers - CHECKGenerator switch - RESET AND

THEN ONMaster caution panel - CHECK

FAILURE OF BOTH AC GENERATORSr--- Airspeed - 100 KNOTS OR BELOW

Helicopter - LAND AS SOON ASPRACTICAL

Altitude - DESCEND BELOW 6,000 FEETGenerator switches - TEST

Ac bus cont circuit breaker - PU LLGenerator switch - RESET THEN ON

To isolateGenerator switch - OFFCircuit breakers - PU LLGenerator switch - RESET THEN ONCircuit breakers - PU SH INAc bus cont circuit breaker - PUSH IN

Battery switch - AS REQUIREDEmergency engine beep trim swi tches

AS REQUIREDHelicopter - LAND AS SOON AS

PRACTICAL

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CH-47 AMTPCFAILURE OF BOTH TRANSFORMER RECTIFIERS


Airspeed - 100 KNOTS OR BELOWBattery switch - AS REQUIREDAll dc equipment not essential to

flight - OFFEMERGENCY DESCENT

Thrust control rod - LOWERAirspeed - ESTABLISH AN AIRSPEED

WHICH WILL PRODUCE MAXIMUMRATE OF DESCENT

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CH-47 AMTPC

AUTOROTATIVE LAND INGThrust control rod - LOWER

IMMEDIATELYAirspeed - MAINTAIN 70 OR 85

KNOTSLongitudinal cyclic speed trim

CHECK RETRACTEDPersonnel - ALERTIff - EMERGENCYRadio call - COMPLETEShoulder harness - LOCKParking brake - CHECK RELEASEDFlare - 100 FEETThrust control rod - RAISEWheel brakes - AS REQUIRED

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H-47 AMTPCPRACTICE AUTOROTATIONEntry

Aft wheel swivel locks - LOCKEDRotor rpm - 230Thrust control rod - LOWERAirspeed - 70 OR 85 KNOTSLongitudinal cyclic speed trim

CHECK RETRACTEDAt Approximately 100 Feet

Cyclic - FLAREThrust control rod - AS REQUIRED

At Approximately 15 Feet(Aft Wheel Height)

Thrust control rod - RAI SECyclic stick and directional p e d a l s

AS REQUIREDAfter Touchdown

Cyclic stick - FORWARDThrust control wd - LOWERWheel brakes - USE

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CH-47 AMTPC

EMERGENCY LANDING IN HEAVILYWOODED AREAS

Engine condition levers - STOPGenerator switches - OFFBattery switch - OFF

LONG ITUD INAL CYCLIC SPEEDTRIM SYSTEM FAILURE

Airspeed - AS REQUIREDAc and dc speed trim circuit breakers

CHECK INSpeed trim function switch - SELECT

OTHER FUNCTIONSINGLE SAS FAILURE - BOTH ON

Helicopter - MAINTAIN CONTROLAirspeed - REDUCE TO 60 TO 80

KNOTS lASLongitudinal cyclic speed trim

CHECK RETRACTEDAltitude - INCREASE IF AT EXTREMELYLOW GROUND CLEARANCEMalfunctioning system - ISOLATEMalfunctioning SAS, SAS dc circuit

breaker - PU LL

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CH-47 AMTPCBAILOUT CHECKLIST

Alarm bell - RINGAirspeed - 80 KNOTSFlight controls - TRIMHelicopter - EXIT

PILOT AND COPILOTJETTISONABLE DOORExterior Ground Jettisoning

Trigger button - PUSHJettisoning handle - TURN HANDLE

UP OR DOWNIf door does not fall away - PU LL

In-Flight JettisoningJettisoning handle - ROTATEIf door is not carried away - PUSH

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) ) ) ) ) )Table 2

Engine Fire Extinguisher PressuresAmbient Minimum Maximum

Temperature Indication Indication(Fahrenheit) (Psi) {Psi}

("')_65 0 271 344 J:, _60 0 275 350 -...J_40 0 292 37 0 l>S_20 0 32 0 40 0 - l0 0 355 437 "tJ("')

20 0 396 48640 449 54060 0 518 61880 0 593 702

100 691 784->-> 125 785 9020'1

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....

.... CH-47A COCKPIT CONTROLS POSITION ENVELOPEenAIRCRAFT CONFIGURATION ROTOR RPM - 230STANDARD UN BALLASTED RATE OF CLIMB - 0 FT/MIN.STICK POSITION TRIM - "0"

2.0(' )J:,

......

....

( )'oJ

C....N'

III...

....

):>LONG -iSTICK

POSITION"'tl(' )

(INCHES)

o 10 20 30 40 50 60 70 80 90 100 110 120 130) ) ) )

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oa.(f)

.J

o0IZouIa.u ouI'IU

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) ) ) ),'.

c....

( ).,....

....

.....

.....

--.J

LATERALSTICK POSI TION(INCHES)

PEDALSEPARATION(I NCHES)

1.0 I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I II I I I I RIGHT I I I I

0 If! I I I I I I I I I I I

CLIMB AND AUTOROTATION I I I I I I I I I I I I I I I I I I I60 KNOTS .

I I I I I LEFT I I I I I I I I I I I I I I I I I I I I I I I1.0 I I I I I I I I I I I I I I I I 1 I I I I I I I I I I I I I I

1.0 I I I I I I I I I I I=---k

2.0 I I I I I I I I I I I I .. I I I I I I I I I I I I I I I I I I

0 If! I I I ! I I I !o 10 20 30 40 50 60 70 80 90 100 110 120 130

AIRSPEED (KNOTS)

(' ):::I:, --.J):>S-;(' )"

\

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....

.... CH-47B COCKPIT CONTROLS POSITION ENVELOPEto AIRCRAFT CONFIGURATION ROTOR RPM - 225STANDARD UNBALLASTED RATE OF CLIMB - 0 FT/MIN

STICK POSITION - "0"3.0

2.0

NOTE: LONGITUDINAL STICK MUSTBE FURTHER FWD AT 100KNOTS THAN 60 KNOTS aAT 155 KNOTS THAN 100KNOTS-

FWD

AFT

("'):::I:,

...... ( ) -.J- ::to III :t>.... 1.0 S N -l"'tILONG ("')STICKPOSITION 0( INCHES)

1.0

o 10 20 30 40 50 60 70 80 90 100 110 120 130 140 150 160) ) )

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Ieno0.en.Joa:IzoUIa.:cuou(l)l"VIIU

\

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) ) ) ) ) )1.0

LATERALSTICKPOSITION(INCHES)

I 1 I I 1 I 1 1 1 1 1 I I 1 1 1 1 1 1 I 1 I 1 1 1 1 lu l .,LI 1 I 1 1 RIGHT 1 I I 1

0 ' f I I I I I I I I I I I

10 20 30 40 50 60 70 80 90 100 110 120 130 140 150 160

CLIMB AND AUTOROTATION 1 I 1 I I I 1 I I 1 1 1 I 1 1 1 I I 1 I60 KNOTS

I I I I I LEFT 1 I 1 I I 1 I I I 1 1 1 I I I 1 I I 1 1 1 I 1 1 I

I I I I I I I I I I"'-d---+-

I 1 I 1 1 1 1 I 1 1 1 I I 1 1 I I 1 1 1 I I 1 1 I I 1 I 1 I 1 1 I1 I I I , I I I I I I I 1 1 I I 1 I 1 I I I 1 I 1 I 1 I I I 1 I

I 1 'I! 1 I I I

("')J:,f:.

...... ( ) 1.0I\) '" III .... 4 2.0 s= I\ ) - l("')

1.0

PEDALSEPARATION(INCHES) 0 tt' I I

o........to AIRSPEED (KNOTS)

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~

-' CH-47C COCKPIT CONTROLS POSITION ENVELOPENo AI RCRAFT CONFIGURATION ROTOR RPM - 23 0STANDARD UN BALLASTED RATE OF CLIMB - 0 FT/MINSTICK POSITION - "0 "~ .

2.0 (")

NOTE: LONGITUDINAL STICK MUSTBE FURTHER FWD AT 100KNOTS THAN 60 KNOTS aAT 155 KNOTS THAN 100KNOTS

FWD

AFT

J:,...... (' ) +:>.. . :J Q S; "l>... .. 1.0 s: (,,) - iLONG ""0(")STICKPOSITION 0( INCHES)

1.0

o 10 20 30 40 50 60 70 80 90 100 110 120 130 140 150 160, )) ) ) )'\

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0en0aen-J

\

0

\

cr

\

z

\

0u

\

\

\

a

\

\

u0

\

u

\

u

\

f-V

\

IIU

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) ) ) ) )-1.0

I I I I I RIGHT I I I ILATERALSTICKPOSITION 0(INCHES)

(")I I I I I LEFT I I I I I I I I I I I I I I I I I I I I I I I I I :r:,,f::. C') 1.0 I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I I -..J

C N

:t>... 2.0 I I I I I I I I I I I I ... I I I I I I I I I I I I I I I I I I I I s;: (. ) CLIMB AND AUTOROTATION 11 I I I I I I I I I I I I I I I I I I I I - l60 KNOTS ""C(")

1.0 IPEDALSEPARATION(INCHES) 0.,.'

-"N-"

I I I I I I I I P" .....+-+

I ' I ' I ! I I Io 10 20 30 40 50 60 70 80 90 100 110 120 130 140 150 160AI RSPEED (KNOTS)

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C H ~ 4 7 AMTPC

680

76 0

E-

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\CH-47 AMTPC

POWER T O P P I ~ G T55-L7C (66:1)

Figure 3

JOIN OAT AN D PRESSURE jALTITUDE, MARK A.JOIN lAS AND POINT A. PROJECT TO TAS.

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CHI-47 AMTPC

POWER TOPPING T55-L7C (64:1)

'\

JOIN OAT AND PRESSURJOIN lAS AND POINT A.

'J

MARK A.TAS.

Figure 4

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CH-471 AMTPC

INTERSTAGE AIR BLEED BAND CLOSURE

85HI SPEED VS AMBIEHT AIR TEMPERATURE I I I I I I I I III I I I I I I I I I I I I I I I I I I I

80I %wU'"l1.

I.%

I 75Q T55.L7 .

MAlt H, TO FULLYww

CLbsE AIR BL EED5;'"l e'"'"u 70::>Qe'" T55-L.51. I I ! I I I I I I I ~ I I I I I I I I I I I I I - L I I I : I I I I I I ~ "

QCl

65 III111 i I I i I I I 1 I I 1 1 1 1 1 1 1 1 1 II I II I I I I I I I U TTl I I I 1 I I I I I I I I I [ I I I T T l !

"

-20

H. ' 18,720 RPM

20 40 60

AMBIEHT TEMPERATURE - DEGREES F

80 10

Figure 5

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