OPERATOR’S AND CREWMEMBER’S CHECKLIST UH · PDF fileC 6 TM 1--1520--237--CL CHANGE HEADQUARTERS DEPARTMENT OF THE ARMY NO. 6 WASHINGTON,D.C.,27 November2000 Operator’s and Crewmember’s

OPERATOR’S ANDCREWMEMBER’S

CHECKLIST

UH-60A HELICOPTERUH-60L HELICOPTEREH-60A HELICOPTER

DISTRIBUTION STATEMENT A: Approved for publicrelease; distribution is unlimited.

*This manual supercedes TM 1-1520-237-CL, dated 31August 1994, including all changes.

*TM 1-1520-237-CL

TECHNICAL MANUAL

31 October 1996

C 6TM 1--1520--237--CL

CHANGE HEADQUARTERSDEPARTMENT OF THE ARMY

NO. 6 WASHINGTON, D.C., 27 November 2000

Operator’s and Crewmember ’sChecklist

ARMY MODELS

UH--60A HELICOPTERSUH--60L HELICOPTERSEH--60A HELICOPTERS

DISTRIBUTION STATEMENT A: Approved for publicrelease; distribution is unlimited.

TM 1--1520--237--CL, dated 31 October 1996, ischanged as follows:

1. Remove and insert pages as indicated below. New orchanged text material is indicated by a vertical bar inthe margin. An illustration change is indicated by avertical barnext to the figure title. Text that flows to thefollowing page is indicated by a current change num-ber.

TM 1-1520-237-CL C6 Remove Pages Insert Pages A and B A and B I and ii I and ii N-7 through N-10 N-7 through N-10 E-27 and E-28 E-27 and E-28 P-11 and P-12 P-11 and P-12 P-15 and P-16 P-15 and P-16 2. Retain this sheet in front of manual for reference purposes. By Order of the Secretary of the Army:

Official:

ERIC K. SHINSEKI General, United States Army Chief of Staff

JOEL B. HUDSON Administrative Assistant to the Secretary of the Army 0019572 DISTRIBUTION: To be distributed in accordance with Initial Distribution No. (IDN) 311310, requirements for TM 1-1520-237-CL.

TM 1-1520-237-CLC 5

CHANGE HEADQUARTERS DEPARTMENT OF THE ARMYNO. 5 WASHINGTON, D.C., 3 April 2000

Operator’s and Crewmember’sChecklist

ARMY MODELS

UH-60A HELICOPTERSUH-60L HELICOPTERSEH-60A HELICOPTERS

DISTRIBUTION STATEMENT A: Approved for public release;distribution is unlimited.

TM 1-1520-237-CL, dated 31 October 1996, ischanged as follows:

1. Remove and insert pages as indicated below. New orchanged text material is indicated by a vertical bar in themargin. An illustration change is indicated by a miniaturepointing hand.

TM 1-1520-237-CLC 5

Remove pages Insert pages

A/(B blank) A and BP-19 and P-20

2. Retain this sheet in front of manual for reference pur-poses.

By Order of the Secretary of the Army:

ERIC K. SHINSEKIGeneral, United States Army

Chief of Staff

Official:

JOEL B. HUDSONAdministrative Assistant to the

Secretary of the Army9931329

DISTRIBUTION:To be distributed in accordance with InitialDistribution Number (IDN) 311310 requirements forTM 1-1520-237-CL.

P-19 and P-20

TM 1-1520-237-CLC 4

CHANGE HEADQUARTERS DEPARTMENT OF THE ARMYNO. 4 WASHINGTON, D.C., 30 July 1999


ARMY MODELS





TM 1-1520-237-CLC 4


A/(B blank) A/(B blank)N-1 through N-4 N-1 through N-4N-4.1/(N-4.2 blank) N-4.1/(N-4.2 blank)N-5 and N-6 N-5 and N-6N-6.1/(N-6.2 blank) N-6.1/(N-6.2 blank)N-11 through N-11 through

N-15/(N-16 blank) N-15/(N-16 blank)E-11 through E-14 E-11 through E-14E-21 through E-24 E-21 through E-24P-3 and P-4 P-3 and P-4P-7 through P-16 P-7 through P-16P-16.1/(P-16.2 blank) P-16.1/(P-16.2 blank)



ERIC K. SHINSEKIGeneral, United States Army

Chief of Staff

Official:




TM 1-1520-237-CLC 3

CHANGE HEADQUARTERS DEPARTMENT OF THE ARMYNO. 3 WASHINGTON, D.C., 29 January 1999


ARMY MODELS






A/(B blank) A and Bi and ii i and iiN-3 through N-4 N-3 through N-4N-4.1/(N-4.2 blank) N-4.1/(N-4.2 blank)N-5 and N-6 N-5 and N-6N-7 and N-8 N-7 and N-8N-9 and N-10 N-9 and N-10N-11 and N-12 N-11 and N-12

TM 1-1520-237-CLC 3

N-13 and N-14 N-13 and N-14N-15/(N-16 blank) N-15/(N-16 blank)E-29 through E-32 E-29 through E-32

P-3 and P-4 P-3 and P-4P-13 through P-16 P-13 through P-16P-17 and P-18 P-17 and P-18None P-18.1/(P-18.2 blank)

P-19 through P-24 P-19 through P-24None P-24.1 and P-24.2



DENNIS J. REIMERGeneral, United States Army

Chief of Staff

Official:




TM 1-1520-237-CLC 2

CHANGE HEADQUARTERS DEPARTMENT OF THE ARMYNO. 2 WASHINGTON, D.C., 30 OCTOBER 1998


ARMY MODELS





TM 1-1520-237-CLC 2


A/(B blank) A/(B blank)i and ii i and iiN-3 and N-4 N-3 and N-4None N-4.1/(N-4.2 blank)N-5 and N-6 N-5 and N-6None N-6.1/(N-6.2 blank)N-9 and N-10 N-9 and N-10N-13 and N-14 N-13 and N-14N-15/(N-16 blank) N-15/(N-16 blank)E-23 through E-26 E-23 through E-26P-15 and P-16 P-15 and P-16None P-16.1/(P-16.2 blank)




Chief of Staff

Official:




TM 1-1520-237-CLC 1

CHANGE HEADQUARTERS DEPARTMENT OF THE ARMYNO. 1 WASHINGTON, D.C., 30 JUNE 1997


ARMY MODELS



TM 1-1520-237-MTF, dated 31 October 1996, ischanged as follows:



A/(B blank) A/(B blank)N-11 and N-12 N-11 and N-12E-7 and E-8 E-7 and E-8E-23 and E-24 E-23 and E-24E-25 and E-26 E-25 and E-26P-19 and P-20 P-19 and P-20P-23/(P-24 blank) P-23 through P-57/(P-58

blank)2. Retain this sheet in front of manual for reference pur-

poses.

TM 1-1520-237-CLC 1



Chief of Staff

Official:



DISTRIBUTION:To be distributed in accordance with DA Form 12-31E, block no. 1310, requirements for TM 1-1520-237-CL.

LIST OF EFFECTIVE PAGES

Insert latest changed pages; dispose of superseded pages inaccordance with applicable regulations.

NOTE: On a changed page, the portion of the text affectedby the latest change is indicated by a vertical line, or otherchange symbol in the outer margin of the page.

Total number of pages in this manual is 122.Original . . . . . . . . . . . . . . . . . . . . . . . . . . 31 October 1996Change 1 . . . . . . . . . . . . . . . . . . . . . . 30 June 1997Change 2 . . . . . . . . . . . . . . . . . . . . . . 30 October 1998Change 3 . . . . . . . . . . . . . . . . . . . . . . 29 January 1999Change 4 . . . . . . . . . . . . . . . . . . . . . . 30 July 1999Change 5 . . . . . . . . . . . . . . . . . . . . . . 3 April 2000Change 6 . . . . . . . . . . . . . . . . . . . . . . 27 November 2000

PageNo.

ChangeNo.

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* Zero in this column indicates an original page.

A C6

PageNo.

ChangeNo.

P-4....................... 3P-5 - P-7 ............. 0P-8....................... 4P-9....................... 0P-10..................... 4P-11..................... 6P-12 - P-14 ......... 4P-15..................... 6P-16 - P-16.1 ...... 4

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P-16.2 Blank....... 4P-17..................... 0P-18 - P-18.1 ...... 3P-18.2 Blank....... 3P-19..................... 5P-20 - P-24.2 ...... 3P-25 - P-57 ......... 1P-58 Blank.......... 1

TM 1-1520-237-CL

* Zero in this column indicates an original page.

B C6

GENERAL INFORMATION AND SCOPE

SCOPE. This checklist contains the operator’s checks to beaccomplished during normal and emergency operations.

GENERAL INFORMATION. This checklist consists ofthree parts: normal procedures, emergency procedures, andperformance data. Normal procedures consist of the proce-dures required for normal flight and those required for9BeforeLanding9. The normal procedures portion will be subdividedto include the before landing checks of Chapter 8 of the opera-tor’s manual. Emergency procedures are subdivided into 10classifications as follows: engine, propeller/rotor (insert eitherPROP or ROTOR), fire, fuel, electrical (ELECT), hydraulic(HYD), landing and ditching (LDG/DTCH), flight controls(FLT CONT), bailout or ejection (BAILOUT) (EJECT), andmission equipment (MSN/EQPT) (as applicable). Detailedprocedures consists of detailed procedural checks.

NOTE

This checklist does not replace the amplified ver-sion of the procedures in the operator’s manual(TM 1-1520-237-10), but is a condensed versionof each procedure.

NORMAL PROCEDURE PAGES. The contents of the nor-mal procedures of this manual are a condensed version of theamplified checklist appearing in the normal procedures or crewduties portion of the applicable operator’s manual.

EMERGENCY PROCEDURES PAGES. The require-ments of this section of the condensed checklist manual (CL)are identical to those for the normal procedures, except thatthe information is drawn from the amplified checks in theemergency procedures portion of the operator’s manual.

The emergency requirements are subdivided into 10 classifi-cations listed above. Immediate action items shall be under-lined.

TM 1-1520-237-CL

i C6

Symbols preceding numbered steps:

* — Indicates performance of steps is mandatory forall thru flights.

N — Indicates performance of step is mandatory fornight flights.

. — Indicates a detailed procedure for this step isincluded in the performance checks section,located at the back of the checklist.

I — Indicates mandatory check for instrument flights.

O — Indicates if installed.

④ — Pilot not on the controls duties.

Immediate action emergency items are underlined.

REPORTING ERRORS ANDRECOMMENDING IMPROVEMENTS

You can help improve this manual. If you find any mistakes,or if you know of a way to improve these procedures, pleaselet us know. Mail your letter or DA Form 2028 (Recom-mended Changes to Publications and Blank Forms), or DAForm 2028-2 located in the back of the applicable Operator’sManual (when using the 2028-2 from the Operator’s Manual,make sure the publication number and title are changed toreflect this CL) directly to: Commander, US Army Aviationand Missile Command, ATTN: AMSAM-MMC-LS-LP, Red-stone Arsenal, AL 35898-5230. A reply will be furnished toyou. You may also submit your comments electronically to ourE-mail address: [email protected] or by fax 256-842-6546/DSN 788-6546. Instructions for sending an electronic2028 may be found at the backof the applicable Operator’sManual immediately preceding the hard copy 2028.

TM 1-1520-237-CL

ii C3

BEFORE EXTERIOR CHECK

1. Publications - Check.

* 2. Helicopter covers, locking devices, tiedowns, andgrounding cables - Removed and secured.

* 3. Fuel - Check quantity as required.

4. Fuel sample - As required.

EXTERIOR CHECK

NOSE SECTION (AREA 1)

* 1. Main rotor blades - Check.

2. Fuselage - Check.

COCKPIT - LEFT SIDE (AREA 2)

1. Cockpit area - Check.

* 2. Left engine oil level - Check.

CABIN TOP (AREA 3)

1. Cabin top - Check.

2. APU - Check; oil level.

O 3. APU IPS - Check.

4. Gust lock - Check.

5. Main transmission - Check; oil level.

* 6. Main rotor system - Check.

TM 1-1520-237-CL

N-1

INTERIOR CABIN (AREA 4)

1. Cabin - Check.

2. APU accumulator pressure gage - Check.

3. Transmission oil filter impending bypass indica-tor - Check.

4. Cargo Hook - Check.

5. Survival gear and mission equipment - Check.

FUSELAGE - LEFT SIDE (AREA 5)


* 2. Intermediate gear box - Check; oil level.

TAIL PYLON (AREA 6)

1. Tail pylon - Check.

* 2. Tail rotor - Check.

* 3. Tail rotor gear box - Check; oil level.

FUSELAGE RIGHT SIDE (AREA 7)


COCKPIT - RIGHT SIDE (AREA 8)

* 1. Right engine oil level - Check.

2. Cockpit area - Check.

.* 3. Crew and passenger briefing - Complete asrequired.

TM 1-1520-237-CL

N-2 C4

BEFORE STARTING ENGINES

* 1. Copilot’s collective - Extended and locked.

2. Shoulder harness locks - Check.

3. PARKING BRAKE - Release, then set.

. 4. Circuit breakers and switches - Set.

COCKPIT EQUIPMENT CHECKS

* 1. FUEL PUMP switch - APU BOOST.

* 2. APU CONTR switch - ON.

* 3. APU generator switch -ON.

* 4. EXT PWR switch - OFF.

O. 5. ERFS AUXILIARY FUEL MANAGE-MENT control panel -TEST.

O* 6. ERFS AUXILIARY FUEL MANAGE-MENT control panel - Set fuel as required.

* 7. EH IINS SYSTEMS SELECT switches -DGandVG.

. * 8. EH IINS - Align.

9. Caution/advisory/warning panels - Check.

10. 701C DEC engine fault indicator codes - Check.

N 11. Interior/exterior lighting - Set.

O. 12. Mission equipment - Check.

TM 1-1520-237-CL

N-3 C3

. * 13. Cold weather control exercise - Check if tem-perature is below -17°C (1°F).

* 14. AFCS FAILURE ADVISORY lights - If on,POWER ON RESET.

* 15. SAS 1 off, SAS 2, TRIM , FPS, and BOOSTswitches - PushON.

. 16. Flight controls - Check first aircraft flight of day.

. 17. Stabilator - Check.

* 18. Avionics - On.

* 18.1. Doppler/GPS - Program.

* 18.2. Doppler/GPS mode select switch -OFF.

* 19. COMPASS switch - SLAVED . Set as required.

20. Barometric altimeters - Set.

* 21. Cyclic and pedals centered - Collective raise nomore than 1 inch and friction.

22. BACKUP HYD PUMP switch - OFF.

O. 23. Blade deice system - Test as required.

24. Avionics - Check as required.

.* 25. AFMS AUXILIARY FUEL MANAGEMENTcontrol panel -TEST, set as required.

STARTING ENGINES

* 1. ENG FUEL SYS selector(s) - As required(XFD) for first start of day.

TM 1-1520-237-CL

N-4 C4

* 2. Deleted.

* 3. ENGINE IGNITION switch - ON.

* 4. GUST LOCK caution light - Off.

TM 1-1520-237-CL

N-4.1/(N-4.2 Blank) C4

* 2. Fire guard - Posted if available.

* 3. Rotor blades - Check clear.

. * 7. Engine(s) - Start.

* 8. If single-engine start was made, repeat step 7 forother engine.

* 9. Systems - Check.

* 10. BACKUP HYD PUMP switch - AUTO .

. 11. Hydraulic leak test system - Check.

. 12. Tail Rotro Servo transfer - Check.

O 13. AUX CABIN HEATER switch - As desired.

* 11. Engine warmup - Check if temperature is below-17°C (1°F).

ENGINE RUNUP

* 1. Flight controls - Hold.

* 2. ENG POWER CONT lever(s) -FLY .

* 3. Droop stops - Check out 70% to 75%RPM R.

* 4. #1 and#2 GEN caution lights - Off.

* 5. EH ECS panel switches - As desired.

O. 6. DEICE EOT - Check as required.

* 7. % TRQ 1 and2 - Matched within 5%.

* 8. EH Q/F PWR switch - As desired.

TM 1-1520-237-CL

N-5

* 9. FUEL PUMP switch - OFF.

* 10. APU CONTR switch - OFF.

* 11. AIR SOURCE HEAT/START switch - Asrequired.

* 12. ENG FUEL SYS selectors - As required.

* 13. SAS 1 - ON.

13.1. Doppler/GPS mode select switch - As desired.

* 14. Collective friction - As required.

O* 15. HUD - Adjust brightness, mode, barometric alti-tude, pitch, and roll as necessary.

O* 16. EH IINS NAVRDY light flashing - CDU modeselect switch toNAV .

O* 17. EH IINS SYSTEMS SELECT switches -IINS .

18. Engine Health Indicator Test (HIT)/ Anti-IcingCheck - Accomplish.

* 19. FUEL BOOST PUMP CONTROL switches -ON (for all fuel types). Indicator lights check on.

O. 20. ERFS AFMS External extended range fueltransfer - Check.

BEFORE TAXI

O* 1. ES Ejector rack lock levers unlocked.

O* 2. VOL Volcano jettison safety pins - Removeand red arming levers to arm.

TM 1-1520-237-CL

N-6 C4

O* 3. Chaff, EH flare electronic module(s) safetypin(s) - Remove.

* 4. Chocks - Removed.

* 5. Doors - Secure.

TM 1-1520-237-CL

N-6.1/(N-6.2 Blank) C4

* 5. PARKING BRAKE - Release.

* 7. TAIL WHEEL switch - As required.

7. Wheel brakes - Check as required.

HOVER CHECK

1. Systems - Check.

2. Flight instruments - Check.

3. Power - Check.

BEFORE TAKEOFF

* 1. ENG POWER CONT levers -FLY .


* 3. Avionics - As required.

* 4. Crew, passengers, and mission equipment -Check.

AFTER TAKEOFF

O. 1. ERFS AFMS Extended range fuel systemtransfer - As required.

2. EH ASE - As required.

O. 3. VOL Mine launch, post mine launch - Asrequired.

BEFORE LANDING

1. TAIL WHEEL switch - As required.

2. PARKING BRAKE - As required.

TM 1-1520-237-CL

N-7 C3

3. Crew, passengers, and mission equipment -Check.

AFTER LANDING CHECK


2. Exterior lights - As required.

3. Avionics/mission equipment - As required.

PARKING AND SHUTDOWN


2. PARKING BRAKE - Set.

2.1. FUEL BOOST PUMP CONTROL switches -OFF.

3. Landing gear - Chocked.

O 4. AUXILIARY FUEL MANAGEMENT controlpanel ERFS FUEL XFR MODE switch -OFF. AFMS XFER MODE switch - OFF.

O 5. ERFS AFMS AUXILIARY FUEL MAN-AGEMENT control panelPRESSswitch(es) -Off.

O 6. VOL Volcano red arming levers -SAFE andjettison safety pins install.

O 7. ES Ejector rack locking levers - Locked.

O 8. Chaff, EH flare electronic module safety pin(s) -Install.

9. EH IINS SYSTEMS SELECT switches -DG/VG.

TM 1-1520-237-CL

N-8 C6

O 10. EH IINS - OFF.

O 11. EH ECS panel switches -OFF.

12. SAS 1 - Off.

13. DEICE , PITOT , ANTI-ICE , HEATER andEH Q/F PWR switches -OFF.

14. AIR SOURCE HEAT/START switch - APU.

15. FUEL PUMP switch - APU BOOST.

16. APU CONTR switch - ON.

17. Collective raise no more than 1 inch.

18. Flight controls - Hold.

19. ENG POWER CONT levers -IDLE .

20. ENGINE IGNITION switch - OFF.

21. Cyclic - As required.

22. Droop stops - Verify in, about 50%RPM R.

23. BACKUP HYD PUMP switch - OFF.

24. Stabilator - Slew to 0° after last flight of the day.

25. BACK-UP PUMP ON advisory light - Checkoff.

26. ENG POWER CONT levers -OFF after 2 min-utes atNg SPEEDof 90% or less.

27. ENG FUEL SYS selector -OFF.

28. TGT - Monitor.

TM 1-1520-237-CL

N-9 C6

O 29. AUX CABIN HEATER switch - OFF.

30. 701C DEC torque indicator fault code - Check.

31. Avionics - Off.

32. Deleted.

O 33. HUD ADJ/ON/OFF switch - OFF.

34. Overhead switches - As required.

35. APU generator switch -OFF.

36. FUEL PUMP switch - OFF.

37. APU CONTR switch - OFF.

38. BATT switch - OFF.

BEFORE LEAVING HELICOPTER

1. Walkaround - Complete.

2. Mission equipment - Secure.

3. Complete logbook forms.

4. Secure helicopter - As required.

THRU-FLIGHT CHECKLIST

BEFORE EXTERIOR CHECK

* 1. Helicopter covers, locking devices, tiedowns, andgrounding cables - Removed and secured.

* 2. Fuel - Check quantity as required.

TM 1-1520-237-CL

N-10 C6

EXTERIOR CHECK

NOSE SECTION (AREA 1)

* 1. Main rotor blades - Check.

COCKPIT - LEFT SIDE (AREA 2)

* 1. Left engine oil level - Check.

CABIN TOP (AREA 3)

* 1. Main rotor system - Check.

FUSELAGE - LEFT SIDE (AREA 5)

O* 1. VOL Armament system - Check.

* 2. Intermediate gear box - Check; oil level.

TAIL PYLON (AREA 6)

* 1. Tail rotor - Check.

* 2. Tail rotor gear box - Check; oil level.

FUSELAGE RIGHT SIDE (AREA 7)

O* 1. VOL Armament system - Check.

COCKPIT - RIGHT SIDE (AREA 8)

* 1. Right engine oil level - Check.

. * 2. Crew and passenger briefing - Complete asrequired.

BEFORE STARTING ENGINES

* 1. Copilot’s collective - Extended and locked.

TM 1-1520-237-CL

N-11 C3

* 2. Radar altimeter - Set.EH Left LO bug 200 feet.

* 3. ANTICOLLISION/POSITION LIGHTS - Asrequired.

* 4. EH Q/F PWR switch - OFF.

O* 5. EH ECS panel switches -OFF.

* 6. AIR SOURCE HEAT/START switch - APU.

* 7. BATT switch - ON.

COCKPIT EQUIPMENT CHECKS

* 1. FUEL PUMP switch - APU BOOST.

* 2. APU CONTR switch - ON.

* 3. APU generator switch -ON.

* 4. EXT PWR switch - OFF.

O* 5. ERFS AUXILIARY FUEL MANAGE-MENT control panel - Set fuel as required.

* 6. EH IINS SYSTEMS SELECT switches -DGandVG.

. * 7. EH IINS - Align.

. * 8. Cold weather control exercise - Check if tem-perature is below -17°C (1°F).

* 9. AFCS FAILURE ADVISORY lights - If on,POWER ON RESET.

* 10. SAS 1 off, SAS 2, TRIM , FPS, and BOOSTswitches - PushON.

TM 1-1520-237-CL

N-12 C4

* 11. Avionics - On.

* 11.1. Doppler/GPS - Program.

* 11.2. Doppler/GPS mode select switch -OFF.

* 12. COMPASS switch - SLAVED . Set as required.

* 13. Cyclic and pedals centered - Collective raise nomore than 1 inch and friction.

. * 14. AFMS AUXILIARY FUEL MANAGEMENTcontrol panel -TEST, set as required.

STARTING ENGINES

* 1. ENG FUEL SYS selector(s) - As required.

* 2. Deleted.

* 3. ENGINE IGNITION switch - ON.

* 4. GUST LOCK caution light - Off.

* 5. Fire guard - Posted if available.

* 6. Rotor blades - Check clear.

. * 7. Engine(s) - Start.

* 8. If single-engine start was made, repeat step 7 forother engine.


* 10. BACKUP HYD PUMP switch - AUTO .

* 11. Engine warmup - Check if temperature is below-17°C (1°F).

TM 1-1520-237-CL

N-13 C4

ENGINE RUNUP

* 1. Flight controls - Hold.

* 2. ENG POWER CONT lever(s) -FLY .

* 3. Droop stops - Check out 70% to 75%RPM R.

* 4. #1 and#2 GEN caution lights - Off.

* 5. EH ECS panel switches - As desired.

* 6. % TRQ 1 and2 - Matched within 5%.

* 7. EH Q/F PWR switch - As desired.

* 8. FUEL PUMP switch - OFF.

* 9. APU CONTR switch - OFF.

* 10. AIR SOURCE HEAT/START switch - Asrequired.

* 11. ENG FUEL SYS selectors - As required.

* 12. SAS 1 - ON.

* 12.1. Doppler/GPS mode select switch - As desired.

* 13. Collective friction - As required.

O* 14. HUD - Adjust brightness, mode, barometric alti-tude, pitch, and roll as necessary.

O* 15. EH IINS NAVRDY light flashing - CDU modeselect switch toNAV .

O* 16. EH IINS SYSTEMS SELECT switches -IINS .

TM 1-1520-237-CL

N-14 C4

* 17. FUEL BOOST PUMP CONTROL switches -ON (for all fuel types). Indicator lights check on.

BEFORE TAXI

O* 1. ES Ejector rack lock levers unlocked.

O* 2. VOL Volcano jettison safety pins - Removeand red arming levers to arm.

O* 3. Chaff, EH flare electronic module safety pin(s) -Remove.

* 4. Chocks - Remove.

* 5. Doors - Secure.

* 6. PARKING BRAKE - Release.

* 7. TAIL WHEEL switch - As required.

BEFORE TAKEOFF

* 1. ENG POWER CONT levers -FLY .


* 3. Avionics - As required.

* 4. Crew, passengers, and mission equipment -Check.

TM 1-1520-237-CL

N-15/(N-16 Blank) C4

Section I. AIRCRAFT SYSTEMS

ENGINE

SINGLE-ENGINE FAILURE

1. Collective - Adjust to maintain RPM R.

2. External cargo/stores - Jettison (if required).

If continued flight is not possible:

3. LAND AS SOON AS POSSIBLE.

If continued flight is possible:

4. Establish single-engine airspeed.

5. LAND AS SOON AS PRACTICABLE.

DUAL-ENGINE FAILURE

AUTOROTATE.

DECREASING % RPM R

1. Collective - Adjust to controlRPM R.

2. ENG POWER CONT lever - LOCKOUT lowpower/TGT engine. Maintain TRQ approxi-mately 10% below other engine.


TM 1-1520-237-CL

E-1

INCREASING % RPM R

1. ENG POWER CONT lever - Retard highpower/TGT engine, maintainTRQ approxi-mately 10% below other engine.


If the affected engine does not respond toENG POWERCONT lever movement in the range betweenFLY andIDLE , the HMU may be malfunctioning internally.

If this occurs:

3. Establish single engine airspeed.

4. Perform EMER ENG SHUTDOWN (affected en-gine).

5. Refer to single engine failure emergency proce-dure.

TM 1-1520-237-CL

E-2

% RPM INCREASING/DECREASING(OSCILLATION)

1. Slowly retard theENG POWER CONT leveron the suspected engine.

If the oscillation stops:

2. Place that engine inLOCKOUT and manuallycontrol the power.


If the oscillation continues:

4. Place theENG POWER CONT lever back toFLY and retard theENG POWER CONT leverof the other engine.

When the oscillation stops:

5. Place the engine inLOCKOUT , manually con-trol the power.


TM 1-1520-237-CL

E-3

% TRQ SPLIT BETWEEN ENGINES 1 AND 2

1. If TGT of one engine exceeds the limiter (700

849°C, 701C 872°C with low power engineabove 50%TRQ or 896°C with low power en-gine below 50%TRQ),retard ENG POWERCONT lever on that engine to reduceTGT . Re-tard theENG POWER CONT lever to maintaintorque of the manually controlled engine at ap-proximately 10% below the other engine.

2. If TGT limit on either engine is not exceeded,slowly retard ENG POWER CONT lever onhigh% TRQ engine and observe% TRQ of lowpower engine.

3. If % TRQ of low power engine increases,ENGPOWER CONT lever on high power engine -Retard to maintain% TRQ approximately 10%below other engine (The high power engine hasbeen identified as a high side failure).

4. If % TRQ of low power engine does not in-crease, or% RPM R decreases,ENG POWERCONT lever - Return high power engine toFLY(The low power engine has been identified as alow side failure).

5. If additional power is required, low powerENGPOWER CONT lever, momentarily move toLOCKOUT and adjust to set% TRQ approxi-mately 10% below the other engine.


TM 1-1520-237-CL

E-4

ENGINE COMPRESSOR STALL

1. Collective - Reduce.

If condition persists:

2. ENG POWER CONT lever (affected engine) -Retard (TGT should decrease).

3. ENG POWER CONT lever (affected engine) -FLY .

If stall condition recurs:

4. EMER ENG SHUTDOWN (affected engine).

5. Refer to single-engine failure emergency proce-dure.

ENGINE OIL FILTER BYPASS CAUTIONLIGHT ON, ENGINE CHIP CAUTION LIGHTON, ENG OIL PRESS HIGH/LOW, ENGINEOIL TEMP HIGH, ENGINE OIL TEMPCAUTION LIGHT ON, ENGINE OIL PRESSCAUTION LIGHT ON

1. ENG POWER CONT lever - Retard to reducetorque on affected engine.

If oil pressure is below minimum limits or oil temperatureremains above maximum limits:

2. EMER ENG SHUTDOWN (affected engine).


TM 1-1520-237-CL

E-5

ENGINE HIGH-SPEED SHAFT FAILURE

1. Collective - Adjust.

2. EMER ENG SHUTDOWN (affected engine). Donot attempt to restart.


LIGHTNING STRIKE

1. ENG POWER CONT levers - Adjust as re-quired to controlRPM.


TM 1-1520-237-CL

E-6

ROTORS, TRANSMISSIONS ANDDRIVE SYSTEMS

LOSS OF TAIL ROTOR THRUST

1. AUTOROTATE.

2. ENG POWER CONT levers - OFF (whenintended point of landing is assured).

LOSS OF TAIL ROTOR THRUST AT LOWAIRSPEED/HOVER

1. Collective - Reduce.

2. ENG POWER CONT levers -OFF (5 to 10 feetabove touchdown).

TAIL ROTOR QUADRANT CAUTION LIGHTON WITH NO LOSS OF TAIL ROTORCONTROL

LAND AS SOON AS PRACTICABLE.

TAIL ROTOR QUADRANT CAUTION LIGHTON WITH LOSS OF TAIL ROTOR CONTROL

1. Collective - Adjust.


TM 1-1520-237-CL

E-7 C1

PEDAL BIND/RESTRICTION OR DRIVEWITH NO ACCOMPANYING CAUTIONLIGHT

1. Apply pedal force to oppose the drive.

2. TRIM switch - Off.

If normal control forces are not restored:

3. BOOST switch - Off.

If control forces, normal for boost off flight are notrestored:

4. BOOST switch - ON.

5. TAIL SERVO switch -BACKUP if tail rotor isnot restored.


#1 TAIL RTR SERVO CAUTION LIGHT ONAND BACK-UP PUMP ON ADVISORYLIGHT OFF OR #2 TAIL RTR SERVO ONADVISORY LIGHT OFF

1. TAIL SERVO switch - BACKUP .

2. BACKUP HYD PUMP switch - ON.


TM 1-1520-237-CL

E-8

MAIN XMSN OIL PRESS CAUTION LIGHTON/XMSN OIL PRESS LOW/XMSN OILTEMP HIGH OR XMSN OIL TEMP CAUTIONLIGHT ON


If time permits:

2. Slow to 80 KIAS.

3. EMER APU START.

4. GENERATORS NO. 1 and NO. 2 switches -OFF.

CHIP INPUT MDL LH OR RH CAUTIONLIGHT ON

1. ENG POWER CONT lever on affected engine -IDLE .


CHIP MAIN MDL SUMP, CHIP ACCESS MDLLH OR RH, CHIP TAIL XMSN OR CHIP INTXMSN/TAIL XMSN OIL TEMP OR INT XMSNOIL TEMP CAUTION LIGHT ON

LAND AS SOON AS POSSIBLE.

TM 1-1520-237-CL

E-9/(E-10 Blank)

FIRE

ENGINE/FUSELAGE FIRE ON GROUND

1. ENG POWER CONT levers -OFF.

2. ENG EMER OFF handle - Pull if applicable.

3. FIRE EXTGH switch - MAIN/RESERVE asrequired.

APU COMPARTMENT FIRE

1. APU fire T-handle - Pull.


APU OIL TEMP HI CAUTION LIGHT ON

APU CONTR switch - OFF. Do not attemptrestart until oil level has been checked.

ENGINE FIRE IN FLIGHT

1. ENG POWER CONT lever (affected engine) -OFF.

2. ENG EMER OFF handle - Pull.



ELECTRICAL FIRE IN FLIGHT

1. BATT andGENERATORS switches -OFF.


TM 1-1520-237-CL

E-11 C4

SMOKE AND FUME ELIMINATION

1. Airspeed - 80 KIAS or less.

2. Cabin doors and gunner’s windows - Open.

3. Place helicopter out of trim.


TM 1-1520-237-CL

E-12

FUEL SYSTEM

#1 OR #2 FUEL FLTR BYPASS CAUTIONLIGHT ON

1. ENG FUEL SYS selector on affected engine -XFD.


#1 AND #2 FUEL FLTR BYPASS CAUTIONLIGHTS ON


#1 FUEL LOW AND #2 FUEL LOWCAUTION LIGHTS ON


TM 1-1520-237-CL

E-13

#1 OR #2 FUEL PRESS CAUTION LIGHTON

If the situation is critical:

1. FUEL BOOST PUMP CONTROL switches -NO.1 PUMP andNO.2 PUMP - ON.


If the situation is not critical:

3. ENG FUEL SYS selector on affected engine -XFD.

If light stays on:

4. FUEL BOOST PUMP CONTROL switches -NO. 1 PUMP andNO. 2 PUMP - ON.

If light stays on:

5. FUEL BOOST PUMP CONTROL switches -NO. 1 PUMP andNO. 2 PUMP - OFF.


TM 1-1520-237-CL

E-14

ELECTRICAL SYSTEM

#1 AND #2 GENERATOR FAILURE (#1 AND#2 CONV AND AC ESS BUS OFF CAUTIONLIGHTS ON)

1. SAS 1switch - Press off.

2. Airspeed - Adjust (80 KIAS or less).

3. GENERATORS NO. 1 and NO. 2 switches -RESET; thenON.

If caution lights remain on:

4. GENERATORS NO. 1 and NO. 2 switches -OFF.

5. EMER APU START.

6. SAS 1switch - ON.


#1 OR #2 GEN CAUTION LIGHT ON

1. Affected GENERATORS switch - RESET;thenON.

If caution light remains on:

2. Affected GENERATORS switch - OFF.

#1 AND #2 CONV CAUTION LIGHTS ON

1. Unnecessary dc electrical equipment - OFF.


TM 1-1520-237-CL

E-15

BATTERY FAULT CAUTION LIGHT ON

1. BATT switch - OFF; then ON. If BATTERYFAULT caution light goes on, cycleBATTswitch no more than two times.

If light remains on:

2. BATT switch - OFF.

BATT LOW CHARGE CAUTION LIGHT ON

BATT LOW CHARGE caution light on indicates chargeis at or below 40%.

If light goes on after ground APU start:

1. BATT switch - OFF; then ON to reset chargeranalyzer logic. About 30 minutes may be re-quired to recharge battery.

If light goes on in flight:

2. BATT switch -OFF, to conserve remaining bat-tery charge.

TM 1-1520-237-CL

E-16

HYDRAULIC SYSTEM

#1 HYD PUMP CAUTION LIGHT ON

1. TAIL SERVO switch - BACKUP ; then NOR-MAL .


#2 HYD PUMP CAUTION LIGHT ON

1. POWER ON RESET switches - Simultaneouslypress and release.


#1 AND #2 HYD PUMP CAUTION LIGHTSON

LAND AS SOON AS POSSIBLE. Restrict con-trol movement to moderate rates.

#1 OR #2 HYD PUMP CAUTION LIGHT ONAND BACK-UP PUMP ON ADVISORYLIGHT OFF

1. Airspeed - Adjust to a comfortable airspeed.

2. BACKUP HYD PUMP switch - ON.

If BACK-UP PUMP ON advisory light remains off:

3. FPS and BOOST switches - Off (for#2 HYDPUMP caution light).


TM 1-1520-237-CL

E-17

#1 OR #2 PRI SERVO PRESS CAUTIONLIGHT ON


#1 RSVR LOW AND #1 HYD PUMPCAUTION LIGHTS ON WITH BACK-UPPUMP ON ADVISORY LIGHT ON


If the BACK-UP RSVR LOW caution light also goes on:

2. SVO OFF switch - 1ST STG.


#2 RSVR LOW AND #2 HYD PUMPCAUTION LIGHTS ON WITH BACK-UPPUMP ON ADVISORY LIGHT ON

1. POWER ON RESET switches - Simultaneouslypress; then release.


If BACK-UP RSVR LOW caution light also goes on:

3. SVO OFF switch - 2ND STG.


#2 RSVR LOW CAUTION LIGHT ON

1. BOOST andFPS switches - Off.


TM 1-1520-237-CL

E-18

COLLECTIVE BOOST SERVO HARDOVER/POWER PISTON FAILURE



PITCH BOOST SERVO HARDOVER

1. SAS (1 and2) andFPS switches - Off.


BOOST SERVO OFF CAUTION LIGHT ON



TM 1-1520-237-CL

E-19/(E-20 Blank)

LANDING AND DITCHING

EMERGENCY LANDING IN WOODEDAREAS. POWER OFF

1. AUTOROTATE. Decelerate helicopter to stopall forward speed at treetop level.

2. Collective adjust to maximum before main rotorcontacts tree branches.

DITCHING - POWER ON

1. Approach to a hover.

2. Cockpit doors jettison and cabin doors open priorto entering water.

3. Pilot shoulder harness - Lock.

4. Survival gear - Deploy.

5. Personnel, except pilot, exit helicopter.

6. Fly helicopter downwind a safe distance andhover.

7. ENG POWER CONT levers -OFF.

8. Perform hovering autorotation, apply full collec-tive to decay rotor RPM as helicopter settles.

9. Position cyclic in direction of roll.

10. Exit when main rotor has stopped.

TM 1-1520-237-CL

E-21 C4

DITCHING - POWER OFF

1. AUTOROTATE.

2. Cockpit doors jettison and cabin doors open priorto entering water.

3. Cyclic - Position in direction of roll.

4. Exit when main rotor has stopped.

TM 1-1520-237-CL

E-22

FLIGHT CONTROL/MAIN-ROTORSYSTEM MALFUNCTIONS

If the main rotor system malfunctions:


2. EMER ENG(S) SHUTDOWN after landing.

SAS FAILURE WITH NO FAILURE/ADVISORY INDICATION

1. SAS 1switch - Off.

If condition persists:

2. SAS 1switch - ON.

3. SAS 2switch - Off.

If malfunction still persists:

4. SAS 1andFPS switches - Off.

SAS 2 FAILURE ADVISORY LIGHT ON

POWER ON RESET switches - Simulta-neously press and then release.

SAS OFF CAUTION LIGHT ON

FPS switch - Off.

TM 1-1520-237-CL

E-23 C4

FLT PATH STAB CAUTION LIGHT ON

1. EH SYSTEMS SELECT - DG/VG.

2. POWER ON RESET switches - Simultaneouslypress and then release.

If failure returns, control affected axis manually.

If airspeed fault light remains illuminated on the AFCSpanel:

3. Manually slew stabilator - Adjust to 0° if above40 KIAS. The preferred method of manuallyslewing the stabilator up is to use the cyclicmounted stabilator slew-up switch.


PITCH, ROLL OR YAW/TRIM HARDOVER

POWER ON RESET switches - Simultaneously pressand then release.

If failure returns, control affected axis manually.

TRIM ACTUATOR JAMMED


TM 1-1520-237-CL

E-24 C2

STABILATOR MALFUNCTION - AUTOMODE FAILURE

1. Cyclic mounted stabilator slew-up switch -Adjust if necessary to arrest nose down pitchrate.

2. AUTO CONTROL switch - PressON once.

If automatic control is not regained:

3. Manually slew stabilator - Adjust to 0° if above40 KIAS or full down when airspeed is below 40KIAS. The preferred method of manually slew-ing the stabilator up is to use the cyclic mountedstabilator slew-up switch.


If manual control is not possible:

5. STAB POS indicator - Check and fly at or belowKIAS LIMITS shown on placard.


TM 1-1520-237-CL

E-25 C2

UNCOMMANDED NOSE DOWN/UP PITCHATTITUDE CHANGE

If an uncommanded nose down pitch attitude occurs:

1. Cyclic - Adjust as required.

2. Collective - Maintain or increase.

3. Cyclic mounted stabilator slew-up switch -Adjust as required to arrest nose down pitch rate.

4. MAN SLEW switch - Adjust to 0° at airspeedsabove 40 KIAS and full down at airspeeds below40 KIAS.


If an uncommanded nose up pitch attitude occurs:

1. Cyclic - Adjust as required.

2. Collective - Reduce as required.

3. MAN SLEW switch - Adjust to 0° at airspeedsabove 40 KIAS and full down at airspeeds below40 KIAS.


TM 1-1520-237-CL

E-26 C2

Section II. MISSION EQUIPMENT

EMERGENCY JETTISONING

CARGO REL or HOOK EMER REL button- Press.

EMERGENCY RELEASE OF RESCUEHOIST LOAD

If the rescue hoist becomes jammed, inoperative, or if thecable is entangled and emergency release is required:

To cut cable from cockpit:

1. CABLE SHEAR switch - FIRE .

To cut cable from hoist operator’s position:

1. CABLE CUT switch - FIRE .

MR DE-ICE FAULT OR MR DE-ICE FAIL, ORTR DE-ICE FAIL CAUTION LIGHT ON

1. Icing conditions - Exit.

2. BLADE DEICE POWER switch - OFF, whenout of icing conditions.

If vibrations increase:


TM 1-1520-237-CL

E-27 C6

PWR MAIN RTR AND/OR TAIL RTRMONITOR LIGHT ON

If a PWR monitor light is on with BLADE DEICEPOWER switch ON to stop power from being applied toblades:

1. Icing conditions - Exit.

2. BLADE DEICE POWER switch - OFF.

If a PWR monitor light is still on withBLADE DEICEPOWER switch OFF:

3. GENERATORS NO. 1 or NO. 2 switch -OFF.

4. APU generator switch -OFF (if in use).


ICE RATE METER FAIL OR INACCURATE

1. BLADE DEICE MODE switch -MANUAL asrequired.

If vibration levels increase or % TRQ required increases:

2. Higher icingMODE - Select as required.

If ice buildup continues:


LOSS OF NO. 1 OR NO. 2 GENERATORDURING BLADE DEICE OPERATION

Pilot not on the controls:

EMER APU START.

TM 1-1520-237-CL

E-28

EXTERNAL EXTENDED RANGE FUELSYSTEM FAILURE TO TRANSFERSYMMETRICALLY IN MANUAL MODE

ERFS

If asymmetric fuel transfer is suspected:

1. Stop transfer on tank set.

2. Select other tank set and initiate transfer.


Should controlled flight with one heavy external tankbecome necessary, proceed as follows:

1. Make all turns shallow (up to standard rate), andin the direction away from heavy side (particu-larly when a right tank remains full).

2. Avoid abrupt control motions, especially lateralcyclic.

3. If possible, shift personnel to the light side of thehelicopter.

4. Select a suitable roll-on landing area, and make aroll-on landing with touchdown speed in excessof 30 KIAS. To increase control margin, executethe approach into the wind or with a front quar-tering wind from the heavy side and align thelongitudinal axis of the aircraft with the groundtrack upon commencing the approach. If a suit-able roll-on landing area is not available, makean approach to a hover into the wind, or with afront quartering wind from the heavy side.

TM 1-1520-237-CL

E-29 C3

EXTERNAL AUXILIARY FUELMANAGEMENT SYSTEM FAILURE TOTRANSFER SYMMETRICALLY IN MANUALMODE AFMS

When an asymmetric fuel condition (greater than 400pound difference between external tank pairs) is identified:

1. XFER MODE switch - MAN .

2. MAN XFER switch - Select heavy tankLEFTor RIGHT until imbalance condition is cor-rected. If the imbalance condition cannot be cor-rected:

3. XFER MODE switch - OFF.


Should controlled flight with one heavy external tankbecome necessary, proceed as follows:

1. Make all turns shallow (up to standard rate), andin the direction away from heavy side (particu-larly when a right tank remains full).

2. Avoid abrupt control motions, especially lateralcyclic.

3. If possible, shift personnel to the light side of thehelicopter.

4. Select a suitable roll-on landing area, and make aroll-on landing with touchdown speed in excessof 30 KIAS. To increase control margin, executethe approach into the wind or with a front quar-tering wind from the heavy side and align thelongitudinal axis of the aircraft with the groundtrack upon commencing the approach. If a suit-

TM 1-1520-237-CL

E-30 C3

able roll-on landing area is not available, makean approach to a hover into the wind, or with afront quartering wind from the heavy side.

EXTERNAL STORES JETTISON ES

If jettisoning of tanks is required:

1. STORES JETTISON switch - Select INBDBOTH , OUTBD BOTH or ALL as applicable.

2. JETT switch - Actuate.

If primary jettison system does not operate:

3. EMER JETT ALL switch - Actuate.

FUEL FUMES IN COCKPIT/CABIN WITHEXTERNAL EXTENDED RANGE FUELSYSTEM PRESSURIZED ERFS

If heater is on:

1. HEATER switch - OFF.

If heater is off or fumes persist:

2. PRESS OUTBDand INBD switches -OFF.

3. MODE switch - OFF.

4. FUEL BOOST PUMP CONTROL switches -As required.

TM 1-1520-237-CL

E-31 C3

FUEL FUMES IN COCKPIT/CABIN WITHEXTERNAL EXTENDED RANGE FUELSYSTEM PRESSURIZED AFMS

If heater is on:

1. HEATER switch - OFF.

If heater is off or fumes persist:

2. PRESSswitch - OFF.

3. XFER MODE switch -OFF.

4. FUEL BOOST PUMP CONTROL switches -As required.

LAUNCHER RACKS JETTISON VOL

If jettisoning of launch rack is required:

1. JETTISON switch - JETTISON .

If jettison procedure above fails, do the following imme-diately:

2. EMER JETTISON switch - JETTISON .

TM 1-1520-237-CL

E-32 C3

DETAILED PROCEDURES

CREW BRIEFING

A crew briefing shall be conducted to ensure a thorough un-derstanding of individual and team responsibilities. The brief-ing should include, but not be limited to, pilots, crew chief,mission equipment operator, ground crew responsibilities, andthe coordination necessary to complete the mission in the mostefficient manner. A review of visual signals is desirable whenground guides do not have direct voice communications linkwith the crew.

PASSENGER BRIEFING

The following guide may be used in accomplishing requiredpassenger briefings. Items that do not pertain to a specific mis-sion may be omitted.

a. Crew introduction.

b. Equipment.

(1) Personal.

(2) Professional.

(3) Survival.

c. Flight data.

(1) Route.

(2) Altitude.

(3) Time en route.

(4) Weather.

d. Normal procedures.

TM 1-1520-237-CL

P-1

(1) Entry and exit the helicopter.

(2) Seating.

(3) Seat belts.

(4) Movement in helicopter.

(5) Internal communications.

(6) Security of equipment.

(7) Smoking.

(8) Oxygen.

(9) Refueling.

(10) Weapons.

(11) Protective masks.

(12) Parachutes.

(13) Hearing protection.

(14) Aviation life support equipment.

e. Emergency procedures.

(1) Emergency exits.

(2) Emergency equipment.

(3) Emergency landing/ditching procedures.

CIRCUIT BREAKERS AND SWITCHES

a. Circuit breakers - In.

TM 1-1520-237-CL

P-2

b. Avionics - Off, frequencies set.

c. BLADE DEICE POWER switch - OFF.

* d. Radar altimeter - Set.EH Left LO bug 200 feet.

e. Clocks - Set and running.

f. BACKUP HYD PUMP - AUTO .

* g. ANTICOLLISION/POSITION LIGHTS - Asrequired.

* h. EH Q/F PWR switch - OFF.

O* i. EH ECS panel switches -OFF.

j. CARGO HOOK EMERG REL switch -OPEN, ARMING switch - SAFE.

k. APU CONTR switch - OFF; APU T-handle -In.

l. GENERATORS NO. 1 and NO. 2 switches -CheckON.

m. Ground power unit - Connected if required.

* n. AIR SOURCE HEAT/START switch - APU(OFF for external air source).

o. EMER OFF T-handles - Full forward.

* p. BATT switch - ON.

TM 1-1520-237-CL

P-3 C4

AUXILIARY FUEL MANAGEMENTCONTROL PANEL - TEST ERFS

a. TEST button - Press. Digits should display 8’sandDEGRADED andVENT SENSOR, (FAILandOVFL ) lights should illuminate.

b. TEST button - Release. Digits should display 8’sin sequence from left to right three times; 5 sec-onds later, display GOOD or EO failure code; 3seconds later, display type fuel density; then fuelTOTAL .

c. Deleted.

d. Auxiliary fuel quantity switch -CAL .

e. INCR/DECR switch - Set calibration.

f. Auxiliary fuel quantity switch -INBD .

g. INCR/DECR switch - Set inboard fuel quantity.

h. Auxiliary fuel quantity switch -OUTBD.

i. INCR/DECR switch - Set outboard fuel quan-tity.

j. Auxiliary fuel quantity switch move toTOTAL- Check.

k. PRESS OUTBD and INBD switches - Asdesired.

IINS ALIGN EH

a. Ensure that the circuit breakers are in.

b. IINS mode select switch -NORM .

TM 1-1520-237-CL

P-4 C3

c. Page select switch -POS.

d. Line select key 7 right - Select UTM or L/L.

(1) Enter GRID ZONE/SPHEROID or LATI-TUDE in scratch pad.

(2) Press line select key 5 left.

(3) Enter AREA, EASTINGS, NORTHINGS,or LONGITUDE in scratch pad.


e. Verify line 3 on left side display indicates correctmagnetic variation, MV.

(1) If incorrect, enter MV in scratch pad.

(2) Verify scratch pad entry is correct.


(4) Verify line 3 left displays: - >MV = XNN.N. (The 9=9 sign indicates that a manualMV was entered and automatic MV updat-ing will not occur.)

f. Rotate page select switch toINS.

(1) Enter barometric pressure of present posi-tion in scratch pad.


(3) Enter altitude of present position in scratchpad (e.g., 156 ft is entered as 0.156 and dis-played as 0.2).


TM 1-1520-237-CL

P-5

g. Rotate page select switch toDEST.

(1) PressDEST toggle switch to selectDESTdesired page.

(2) Press line select key 7 right to display de-sired coordinate system (UTM or L/L).

(3) Enter grid zone and spheroid or latitude inscratch pad.


(5) Enter Area/Eastings/Northings or longitudein scratch pad.


(7) PressDEST toggle switch to increment tothe next page.

h. Rotate page select switch toTCN.

(1) Turn ON TACAN by pressing line selectkey 1 left.

(2) Press line 3 left until REC is displayed onthe CRT.

(3) Press Page Slew toggle switch to displayTACAN station zero page.

(a) Enter magnetic variation in scratchpad.

(b) Press line select key 3 left.

(c) Enter latitude in scratch pad.

(d) Press line select key 5 left.

TM 1-1520-237-CL

P-6

(e) Enter longitude in scratch pad.

(f) Press line select key 7 left.

(g) Press line select key 1 right to displayACT.

(h) Enter channel number in scratch pad.

(i) Press line select key 3 right.

(j) Enter elevation of TACAN station onscratch pad.

(k) Press line select key 5 right.

(l) Press page slew toggle switch to dis-play next TACAN page.

(m) Enter data as described in steps (a)through (l).

i. Select an appropriate destination number andtoggle the STR toggle switch to indicate thenumber, i.e., S1. (It is not necessary that the DXand SX numbers agree, only that SX is the de-sired destination.)

j. Set mode select switch toNAV . (Pull switch up;then rotate.)

k. Set page select switch to TACAN.

(1) Press line select key 3 left to display T/R.

(2) Press line select key 5 left to display UPDT.

TM 1-1520-237-CL

P-7

l. On HSI/VSI MODE SEL panel, pressIINSswitch. Note that bearing to destination (No. 1needle), range to destination, course deviationandTO/FROM flag are displayed on the HSI.

m. OnSYSTEMS SELECT panel, set switches andobserve indications as follows:

(1) PressHDG switch, INS illuminates andinertial derived heading is displayed on theHSI.

(2) PressATT switch, IINS illuminates andinertial derived pitch and roll is displayedon the VSI.

MISSION EQUIPMENT CHECK

RADAR SIGNAL DETECTOR

a. DSCRM switch - OFF.

b. PWR switch - ON.

c. SELF TEST control - Press and hold. Forwardand aft strobes appear and 2.5 kHz PRF audiopresent, alarm audio present andMA lamp startsflashing.

d. BRIL , Filter andAUDIO controls - As desired.

e. SELF TEST control - Release.

f. DSCRM switch - ON.

g. SELF TEST control - Press and hold. Forwardand aft strobes appear and 1.2 kHz PRF audiopresent, then other strobes will appear, PRFaudio will double, alarm audio present andMAlamp starts flashing.

TM 1-1520-237-CL

P-8 C4

h. SELF TEST control - Release.

i. PWR switch - As required.

CARGO HOOK EMERGENCY RELEASECIRCUIT CHECK

a. EMERG REL TEST light - Press. Light shouldbe on.

b. Pilot’s release - Check.

(1) Short test.

(a) CARGO HOOK EMERG RELswitch - SHORT.

(b) Pilot’s HOOK EMER REL button -Press and hold.

(c) CARGO HOOK TEST light - On.

(d) HOOK EMER REL button - Re-lease.TEST light off.

(e) Repeat steps (b) through (d) for copi-lot’s HOOK EMER REL button, andcrewmember’s cargo hook controlpendantEMER RLSE button.

(2) Open test.

(a) CARGO HOOK EMERG RELswitch - OPEN.

(b) Pilot’s HOOK EMER REL button -Press and hold.

(c) CARGO HOOK TEST light - On.

TM 1-1520-237-CL

P-9

(d) HOOK EMER REL button -Release.TEST light off.

(e) Repeat steps (b) through (d) for copi-lot’s HOOK EMER REL button, andcrewmember’s cargo hook controlpendantEMER RLSE button.

c. CARGO HOOK EMERG REL switch -NORM .

If the cargo hook is not to be used immediately after com-pleting the circuit test check, theEMERG REL switchshall remain atOPEN until ready for load pickup.

NORMAL RELEASE MODE CHECK

a. CARGO HOOK CONTR switch - As required.CKPT for pilot and copilot check, orALL forcrewmember check.

b. CARGO HOOK ARMING switch - ARMED .

c. HOOK ARMED advisory light - Check on.

d. Place about 20 pounds downward pressure onload beam.

e. CARGO REL switch (pilot and copilot);NOR-MAL RLSE (crewmember) - Press and release.

f. CARGO HOOK OPEN advisory light - Checkon.

g. CARGO HOOK OPEN advisory light - Checkoff when hook closes.

h. Repeat steps d. through g. for copilot and crew-member position.

TM 1-1520-237-CL

P-10 C4

MANUAL RELEASE CHECK

a. Manual release lever spring - Installed. Checkthat the spring is straight and provides positivepressure on the lever.

b. Place about 20 pounds downward pressure onload beam.

c. Manual release lever - Pull up/turn fully clock-wise and release.

d. Load beam - Check open.

e. CARGO HOOK OPEN advisory light - On.

f. When downward pressure is released, load beamwill close and latch.

g. CARGO HOOK OPEN advisory light - Offwhen hook closes.

RESCUE HOIST CHECK

SQUIB CIRCUIT TEST

a. SQUIB switch - Hold atTEST.

b. SQUIB IND light - Check On.

c. SQUIB switch - Release toNORM . SQUIBIND light off.

BOOM POSITION AND HOIST CABLECONTROL OPERATIONAL CHECK

a. MASTER power switch -ON.

TM 1-1520-237-CL

P-11 C6

b. Hoist operator - Check power on indicator (bluelight), check yellow caution light on control pen-dant is on, and cooling fan operating.

c. Check ICS switch on pendant.

d. Hoist operator -BOOM switch - OUT and thenIN .

e. RESCUE HOIST CONTROL panel - Rotateboom OUT; then IN , then OUT to test boomoperation.

f. Speed mode switch -HIGH .

g. RESCUE HOIST CONTROL panel -DOWN,reel cable out until caution light is off.

h. RESCUE HOIST CONTROL panel - Reel incable and observe that cable speed slows whencaution light goes on (8 to 10 feet of cable out).

i. Boom up limit actuator arm - Push up on armduring reeling in to check that hoist stops runningwhen up limit switches are activated. Observethat cable slows when hook is 12 to 18 inchesfrom full up position.

j. Speed mode switch -LOW and repeat steps g.through i.

k. Repeat steps g. through i., using control pendantassembly. Check that cable speed can be regu-lated by control pendant from 0 to 250 fpm whencable is reeled out beyond 10 feet.

l. BOOM switch - Rotate boom in to stowed posi-tion.

TM 1-1520-237-CL

P-12 C4

COLD WEATHER CONTROL EXERCISECHECK

After starting the APU, the controls must be exercisedwhen operating in a temperature range of -17°C (1°F) andbelow. The control exercise is required

a. At temperatures between -17°C (1°F) and -31°C(-24°F), cycle collective control slowly for 1minute.

(1) Move collective stick grip up about 3inches from lower stop, and down again 30times during 1 minute of control cycling instep a.

(2) Move each tail rotor pedal alternatelythrough 3/4-inch of travel from neutralposition 30 times during 1 minute of con-trol cycling in step a.

b. At temperatures between -31°C (-24°F) and-43°C (-45°F), cycle collective control slowly for2 minutes.

(1) Move collective stick grip up about 1-1/2inches from lower stop and down again dur-ing first minute, and 3 inches of travel dur-ing second minute of control cycling in stepb.

(2) Move each tail rotor pedal alternatelythrough 3/8-inch of travel from neutralposition during first minute, and 3/4-inch oftravel during second minute of controlcycling in step b.

c. At temperatures between -43°C (-45°F) and-54°C (-65°F), cycle collective stick grip slowlyfor 5 minutes.

TM 1-1520-237-CL

P-13 C4

Move collective and pedals through travel for times shownbelow:

Collective Travel(Approximately)

Pedals Travel(Approximately) Time Duration

3/4-inch 1/8-inch First minute1-1/2 inches 1/4-inch Second minute1-3/4 inches 1/2-inch Third minute2-1/2 inches 5/8-inch Fourth minute3 inches 3/4-inch Fifth minute

FLIGHT CONTROL CHECK

First aircraft flight of the day.

a. Collective - Midposition, pedals centered, fric-tion off.

b. BOOST switch - Press off. There will be a slightincrease in collective and pedal forces.BOOSTSERVO OFF caution light on.MASTER CAU-TION light should be on.

c. Right SVO OFF switch - 1ST STG. No allow-able cyclic stick jump.#1 PRI SERVO PRESSandMASTER CAUTION lights should be on.

d. Move cyclic and pedals slowly through fullrange. There should be no binds or restrictions.Move collective full up to full down in about 1 to2 seconds. Check#2 PRI SERVO PRESScau-tion light does not illuminate during movementof collective.

e. RightSVO OFF switch - 2ND STG. No allow-able cyclic stick jump.#2 PRI SERVO PRESSandMASTER CAUTION lights should be on.

TM 1-1520-237-CL

P-14 C4

f. Repeat step d. above. Check#1 PRI SERVOPRESScaution light does not illuminate duringmovement of collective.

g. SVO OFF switch - Center.

h. Collective - Move through full range in no lessthan 5 seconds. There should be no binding.

i. Pedals - Move both pedals through the full rangein no less than 5 seconds. There should be nobinding.

j. TAIL SERVO switch - BACKUP . #1 TAILRTR SERVO caution light, both MASTERCAUTION lights illuminate, #2 TAIL RTRSERVO ON advisory light illuminates. Movepedals through full range in no less than 5 sec-onds. There should be no binding.

k. TAIL SERVO switch -NORMAL . Caution andadvisory lights out.

l. BOOST switch - ON. BOOST SERVO OFFcaution light should be off.

STABILATOR CHECK

a. STAB POS indicator should be between 34° and42° DN.

b. TEST button - Press and hold. CheckSTABPOS indicator moves up 5° to 12°.MASTERCAUTION and STABILATOR caution lightson; stabilator audio heard.

c. AUTO CONTROL RESET switch - PressON.Note that theSTABILATOR caution light andaudio are off andSTAB POS indicator moves to34° to 42° down.

TM 1-1520-237-CL

P-15 C6

d. Either cyclic mounted stabilator slew-up switch -Press and hold untilSTAB POS indicator movesapproximately 15° trailing edge up, release, sta-bilator should stop.STABILATOR and MAS-TER CAUTION lights on and beeping audiblewarning in pilot’s and copilot’s headsets.MAS-TER CAUTION - Press to reset audio tone.

e. Other cyclic mounted stabilator slew-up switch -Press and hold untilSTAB POS indicator movesapproximately 15° trailing edge up, release, sta-bilator should stop.

f. MAN SLEW switch - UP and hold until stabi-lator stops.STAB POS indicator should be 6° to10° up.

g. MAN SLEW switch - DN and hold untilSTABPOS indicator reads 0°.

h. AUTO CONTROL RESET switch - PressON.STAB POS indicator should move 34° to 42°DN. STABILATOR caution light off.

BLADE DEICE SYSTEM TEST

a. Ice rate meterPRESS TO TESTbutton - Pressand release.

b. Ice rate meter indicator - Moves to half scale(1.0) holds for about 50 seconds; then falls to 0or below. ICE DETECTED and MASTERCAUTION lights on after 15 to 20 seconds intothe test, and FAIL flag should not be visible inflag window. Ice rate meter should move to zerowithin 75 seconds after pressingPRESS TOTEST button.

c. BLADE DE-ICE TEST panel select switch -NORM .

TM 1-1520-237-CL

P-16 C4

d. BLADE DEICE POWER switch - TEST.

e. PWR MAIN RTR and TAIL RTR monitorlights - Check.MAIN RTR monitor light maygo on for 2 to 4 seconds. If either light remainson for 10 seconds or more:

(1) BLADE DEICE POWER switch - OFF.If either light is still on:

(2) APU generator switch and/orEXT PWRswitch - OFF.

f. TEST IN PROGRESS light - Check. Lightshould be on for 105 to 135 seconds. No otherblade deice system lights should be on.PWRMAIN RTR and TAIL RTR monitor lightsshould go on momentarily near end of test.TEST IN PROGRESS light should then go off.

TM 1-1520-237-CL

P-16.1/(P-16.2 Blank) C4

g. Crewman touch each droop stop cam - Camsshould be warm to touch.

h. BLADE DEICE POWER switch - OFF.

i. BLADE DE-ICE TEST panel select switch -SYNC 1.

j. BLADE DEICE POWER switch - TEST. MRDE-ICE FAIL andMASTER CAUTION lightson.

k. BLADE DEICE POWER switch - OFF. MRDE-ICE FAIL andMASTER CAUTION lightsoff.

l. BLADE DE-ICE TEST panel select switch -SYNC 2.

m. BLADE DEICE POWER switch - TEST. MRDE-ICE FAIL andMASTER CAUTION lightson.

n. BLADE DEICE POWER switch - OFF. MRDE-ICE FAIL andMASTER CAUTION lightsoff.

o. BLADE DE-ICE TEST panel select switch -OAT .

p. BLADE DEICE POWER switch - TEST. MRDE-ICE FAIL , TR DE-ICE FAIL , andMAS-TER CAUTION lights on.

q. BLADE DEICE POWER switch - OFF. MRDE-ICE FAIL , TR DE-ICE FAIL , andMAS-TER CAUTION lights off.

TM 1-1520-237-CL

P-17

AUXILIARY FUEL MANAGEMENTCONTROL PANEL - TEST AFMS

a. AUX FUEL QTY LBS digital readout - Notecurrent reading.

b. TEST/RESET - Press. All annunciators willlight andE07 will be displayed if test is initiatedwithin approximately one minute of applying acpower. If E07 appears, pressTEST/RESETagain. E07 should not appear until test is fin-ished.

c. BIT indications - Check. Insure theAUX FUELcaution light on the Caution Advisory panel isoff. Press and releaseTEST/RESET button onAFMP to reset theAUX FUEL caution light.

d. PRESSswitch - As desired for tanks installed.

ENGINE(S) START

a. If any of these indications occur, perform EMERENG SHUTDOWN as required.

(1) No TGT increase (light off) within 45 sec-onds.

(2) No ENG OIL PRESS within 45 seconds.

(3) No % RPM 1 or 2 within 45 seconds.

(4) ENGINE STARTER caution light goesoff before reaching 52%Ng SPEED.

(5) TGT reaches 700 850°C or 701C 851°Cbefore idle is attained (Ng 63%).

b. Starter button(s) - Press untilNg SPEEDincreases; release.

TM 1-1520-237-CL

P-18 C3

c. TGT - Check below 700 150°C or 701C 80°Cbefore advancingENG POWER CONT levers.

d. ENG POWER CONT lever(s) - IDLE . Startclock.

e. System indications - Check.

f. ENGINE STARTER caution light(s). Check,off at 52% to 65%Ng SPEED. If ENGINESTARTER caution light remains on after 65%Ng:

(1) ENG POWER CONT lever - Pull out.

If caution light remains on:

(2) APU - OFF or engine air source remove asrequired.

TM 1-1520-237-CL

P-18.1/(P-18.2 Blank) C3

HYDRAULIC LEAK TEST SYSTEM CHECK

a. HYD LEAK TEST switch - TEST. #1 TAILRTR SERVO, BOOST SERVO OFF, SASOFF, #1 and #2 RSVR LOW, BACK-UPRSVR LOW , andMASTER CAUTION lightsand#2 TAIL RTR SERVO ON andBACK-UPPUMP ON advisory lights on. During this check,it is normal for the collective and pedals to moveslightly.

b. HYD LEAK TEST switch -RESET. The lightsin a. should go off.

TAIL ROTOR SERVO TRANSFER CHECK

a. BACKUP HYD PUMP switch - AUTO withbackup pump not running.

b. TAIL SERVO switch - BACKUP . #1 TAILRTR SERVO caution light on and#2 TAILRTR SERVO ON and BACK-UP PUMP ONadvisory lights on within 3 to 5 seconds.

c. TAIL SERVO switch - NORMAL . #1 TAILRTR SERVO caution light and#2 TAIL RTRSERVO ON advisory light off. BACK-UPPUMP ON advisory light remains on forapproximately 90 seconds.

DEICE EOT CHECK

a. BLADE DE-ICE TEST select switch -EOT.

b. BLADE DEICE MODE select switch -MANUAL M .

c. BLADE DEICE POWER switch - ON.

TM 1-1520-237-CL

P-19 C5

d. TR DE-ICE FAIL and MASTER CAUTIONlights go on after 15 to 30 seconds andMRDE-ICE FAIL caution light on after 50 to 70seconds.

e. BLADE DEICE POWER switch - OFF. TRDE-ICE FAIL , MR DE-ICE FAIL , andMAS-TER CAUTION lights off.

f. BLADE DE-ICE TEST select switch -NORM .

g. GENERATORS NO. 1 or NO. 2 switch -OFF.Applicable GEN and MASTER CAUTIONlights on.

h. BLADE DEICE POWER switch -ON. Wait 30seconds, no deice lights on.

i. GENERATORS switch(es) - ON. ApplicableGEN caution light(s) off.

j. BLADE DEICE POWER switch - OFF.

k. BLADE DEICE MODE select switch -AUTO .

EXTERNAL EXTENDED RANGE FUELTRANSFER CHECK ERFS

a. AIR SOURCE HEAT/START switch - ENG.

b. FUEL BOOST PUMP CONTROL switches -CheckON.

c. PRESS OUTBD and INBD switches -ON fortanks installed.

d. Fuel quantity switch -TOTAL .

e. TANKS switch - As desired.

TM 1-1520-237-CL

P-20 C3

f. MODE switch - MANUAL .

g. MANUAL XFR RIGHT switch - ON.

h. Main FUEL QTY TOTAL FUEL readout -Check for increase of about 20 pounds.

i. TANKS switch - Repeat for other position.

j. MANUAL XFR RIGHT switch - OFF.

k. MANUAL XFR LEFT switch - ON.

l. Repeat steps h. and i. forMANUAL XFRLEFT .

m. MANUAL XFR switches -OFF.

n. External extended range fuel transfer system -Set as desired.

EXTERNAL AUXILIARY FUELMANAGEMENT SYSTEM TRANSFERCHECK AFMS



c. PRESSswitch - As required for tanks installed.

d. XFER FROM switch - OUTBD.

e. MAN XFER switch - BOTH .

f. XFER MODE switch - MAN .

TM 1-1520-237-CL

P-21 C3

g. Main FUEL QTY TOTAL FUEL readout -Check for increase of about 40 pounds, andAUXFUEL QTY LBS decrease of 20 pounds pertank.

h. XFER FROM switch - INBD if installed.

i. Main FUEL QTY TOTAL FUEL readout -Check for increase of about 40 pounds, andAUXFUEL QTY LBS decrease of 20 pounds pertank.

j. XFER MODE switch - OFF.

k. External extended range fuel transfer system -Set as desired.

FUEL TRANSFER IN AUTO MODE ERFS



c. PRESS OUTBD and INBD switches - Asrequired for tanks installed.

d. MODE switch - AUTO .

e. TANKS switch - OUTBD, thenINBD .

FUEL TRANSFER IN AUTO MODE AFMS



c. PRESSswitch - As required for tanks installed.

TM 1-1520-237-CL

P-22 C3

d. XFER FROM switch - OUTBD, thenINBD .

e. XFER MODE switch - AUTO .

FUEL TRANSFER IN MANUAL MODE ERFS

If AUTO mode is inoperative, transfer inMANUALmode as follows:



c. PRESS OUTBD and INBD switches -ON fortank sets installed.

d. MODE switch - MANUAL .

e. TANKS switch - OUTBD then INBD .

f. MANUAL XFR switchesRIGHT andLEFT -ON.

FUEL TRANSFER IN MANUALMODE AFMS

If AUTO mode is inoperative or a lateral imbalancegreater than 400 pounds between tank pairs is identified,transfer inMANUAL mode as follows:



c. PRESSswitch - As required for tank installed.

d. XFER FROM switch - OUTBD then INBD .

TM 1-1520-237-CL

P-23 C3

e. MAN XFR switch BOTH or select heavy tankto correct imbalance.

FUEL FLOW VERIFICATION IN MANUALMODE ERFS

NOTE

Ensure main fuel tanks are not completely full.



c. PRESS OUTBD and INBD switches -ON fortank sets installed.

d. MODE switch - MANUAL .

e. TANKS switch - OUTBD then INBD .

f. MANUAL XFR RIGHT switch -ON. Note therate of decrease of theAUX FUEL QTYPOUNDS indicator. The normal transfer fuelflow rate per tank should be between 20 to 38pounds per minute.

g. MANUAL XFR RIGHT switch - OFF.

h. Repeat steps f. and g. for left tank.

MINE LAUNCH VOL

a. DCU FIRE CIRCUIT switch safety pin andstreamer - Remove.

b. DCU FIRE CIRCUIT switch - ENABLE .

TM 1-1520-237-CL

P-24 C3

c. VOLCANO ARM switch - ARM . Verify P/F/ARMED indicatesARMED .

d. Verify that the HELICOPTER DELIVERYSPEEDsetting agrees with the helicopter groundspeed.

e. GA (go around) button - Press to start launchingmines. PressGA button a second time to stopmine launching.

POST MINE LAUNCH CHECK VOL

a. VOLCANO ARM switch - Off.

b. DCU FIRE CIRCUIT switch - OFF. Installsafety pin and streamer.

c. DCU POWER switch - Toggle toOFF.

TM 1-1520-237-CL

P-24.1 C3

SAFAA9971_1_CL

0~FT −50 −45 −40 −25−30−35HP FREE AIR TEMPERATURE ~ 0C

−20

ATF = 1.0 OR 0.9

* MAXIMUM TORQUE AVAILABLE IS LIMITED TO 100%

MAXIMUM TORQUE AVAILABLE* − 30 MINUTE LIMITANTI−ICE OFF T700−GE−700 ENGINE

100100100100100100100100

999795939290888785848280797776747372706967666563

100100100100100100100100

999795949290888785848280797776757372706967666563

100100100100100100100100

999795949290898785848280797776757372706967666563

100100100100100100100100

999796949290898785848281797876757372706967666563

100100100100100100100100

999896949291898786848381807876757372706968666564

100100100100100100100100100

9997959392908887858382807977767473717068676664

100100100100100100100100100100

98969492918987868483817978767574727169686765

1000

2000

3000

4000

5000

6000

7000

8000

9000

10,000

11,000

12,000

13,000

14,000

15,000

500

1500

2500

3500

4500

5500

6500

7500

8500

9500

10,500

11,500

12,500

13,500

14,500

15,500

Figure 1. Maximum Torque Available (Sheet 1 of 5)700

TM 1-1520-237-CL

P-24.2 C3

SAFAA9971_2_CL

1.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.9

1.00.91.00.91.00.91.00.9

0

500

1000

1500

2000

2500

3000

3500

4000

4500

5000

5500

6000

6500

7000

7500

~FT ATF −15 −10 −5 1050HP FREE AIR TEMPERATURE ~ 0C

15

MAXIMUM TORQUE AVAILABLE* − 30 MINUTE LIMITANTI−ICE OFF T700−GE−700 ENGINE (CONTINUED)


100100100100100100100100100100100100100100100100100100100100

999997979696949492929090

100100100100100100100100100100100100100100100100100100100100100

9899979795959394919290

100100100100100100100100100100100100100100100100100100100

981009699949793959193899288

100100100100100100100100100100100100100100100100100100100

981009699949792959093889187

100100100100100100100100100100100100100100100

99100

97100

95999397919590938891868984

100100100100100100100100100100100100100

98100

97100

959993979195899387918689848782

100100100100100100100100100

98100

97100

95100

9399929790958893869184898387818579


TM 1-1520-237-CL

P-25 C1

SAFAA9971_3_CL

1.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.9

1.00.91.00.91.00.91.00.9

8000

8500

9000

9500

10,000

10,500

11,000

11,500

12,000

12,500

13,000

13,500

14,000

14,500

15,000

15,500


15



8989878786868484828281817979787876767575737372727070696968686666

9088898787858583848282808078797777757674747373717170706869676766

9086888486838581837981788076787577737572737072697067696668656663

9085888386828480837881777975787476727470736971677066686466636562

8883868184798278817679757773767174707268716769666864666365616360

8581847982778076797477737571747072687167696568646662656163606258

8478827680757973777275707469726771666964676366616460635962576056


TM 1-1520-237-CL

P-26 C1

SAFAA9971_4_CL

1.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.9

1.00.91.00.91.00.91.00.9

0

500

1000

1500

2000

2500

3000

3500

4000

4500

5000

5500

6000

6500

7000

7500

~FT ATF 20 25 30 454035HP FREE AIR TEMPERATURE ~ 0C

50


* MAXIMUM TORQUE AVAILABLE IS LIMITED TO 100%AREA IS ABOVE ENGINE AMBIENT TEMPERATURE LIMIT

100100100100100

98100

97100

95100

93100

92989096889487928590838881878085788376

10098

10096

10095

10093

1009199909788958793859283908188808678847682758173

10094

10093

100919990978896869485928391828980877885778375817380727870

10090988897879585938491829081887986788576837481737971777076687467

9586948492839181898087798677847682748172797177697568746672657063

9182898087798677847683748173807278707669756773657164706368616660

8677847683748173807278707769756874667265706369626760665964586356


TM 1-1520-237-CL

P-27 C1

SAFAA9971_5_CL

1.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.9

1.00.91.00.91.00.91.00.9

8000

8500

9000

9500

10,000

10,500

11,000

11,500

12,000

12,500

13,000

13,500

14,000

14,500

15,000

15,500


50


* MAXIMUM TORQUE AVAILABLE IS LIMITED TO 100%AREA IS ABOVE ENGINE AMBIENT TEMPERATURE LIMIT

827580737872777075697468726670656963

6762666064596358615660555854

797277707669746772667164696368626660

6559635762566055595357525651

766975677366716470636861676065596357

6256605559535752565155495348

736571646962686166606558635762556054

5953575156505449534852465045

696267616659645863566155605458525751

5550544953475146504549444743

655863576256615459535852565155495348

524751464945

615560545852575156505449534851465045

4944484346424541444043394237

4843474246414540


TM 1-1520-237-CL

P-28 C1

SAFAA9977_1_CL

1000

2500

3500

4500

~FT −45 −40 −25−30−35HP FREE AIR TEMPERATURE ~ 0C

−20

ATF = 1.0 OR 0.9

* GW ~ 100 LB = GW DIVIDED BY 100 LB

0

2000

3000

4000

5000

GW ~ 100 LB

MAXIMUM OGE HOVER WEIGHT AND TORQUE REQUIREDANTI−ICE OFF T700−GE−700 ENGINE

Q ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

−15

Q = TORQUE %OGE = 100 FT WHEEL HEIGHT

MAXIMUM HOVER WEIGHT IS LIMITED TO 22,000 LB100% Q TRANSMISSION LIMIT OR30 MINUTE ENGINE Q LIMIT.

*

~IGE = 10 FT WHEEL HEIGHT

5500GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

2209885

2209986

21910086

21810086

21610086

21510086

2129984

2089783

2049581

2009480

2209986

21910086

21710086

21510086

21410086

213100

85210

9984

2069783

2029581

1989480

22010086

21810086

21510086

21410086

21310086

211100

852099984

2059783

2019581

1989480

21910086

21710086

21410086

21310086

21210086

210100

85208

9984

2049783

2019682

1979480

21810086

21610086

21310086

21210086

211100

85209100

85208100

852059984

2019782

1979581

21710086

21510086

21210086

21110086

210100

85208100

85207100

852059984

2019883

1989682

21610086

21410086

21110086

21010086

209100

85207100

85206100

85205100

852029984

1999783

Figure 2. Hover Torque Required (Sheet 1 of 12)700

TM 1-1520-237-CL

P-29 C1

SAFAA9977_2_CL

6500

7500

8500

9500


−20

ATF = 1.0 OR 0.9


6000

7000

8000

9000

10,000

GW ~ 100 LB

MAXIMUM OGE HOVER WEIGHT AND TORQUE REQUIREDANTI−ICE OFF T700−GE−700 ENGINE (CONTINUED)

Q ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

−15



*


10,500GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

1969278

1939077

1898876

1868774

1828573

1798471

1758270

1728069

1697967

1667766

1959278

1919077

1878976

1848774

1808573

1778471

1748270

1708069

1677967

1647866

1949278

1909077

1878976

1838774

1808673

1778472

1738270

1708169

1677967

1637866

1939279

1909177

1868976

1838774

1798673

1768472

1738370

1698169

1667967

1637866

1949379

1909278

1869076

1838875

1798674

1768572

1738371

1708270

1668068

1637967

1949480

1909279

1879177

1838976

1808774

1768673

1738472

1708370

1678169

1637968

1959681

1919480

1889278

1849077

1818975

1778774

1748673

1718471

1678270

1648169


TM 1-1520-237-CL

P-30 C1

SAFAA9977_3_CL

11,500

12,500

13,500

14,500


−20

ATF = 1.0 OR 0.9


11,000

12,000

13,000

14,000

15,000

GW ~ 100 LB


Q ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

−15



*


15,500GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

1627665

1597564

1567362

1537261

1507060

1476959

1446858

1416656

1396555

1366454

1617665

1587564

1557362

1527261

1487060

1456959

1426757

1406656

1376555

1346354

1607665

1577564

1547362

1517261

1487060

1456959

1426757

1396656

1366555

1346354

1607665

1577564

1537362

1507261

1477060

1446959

1416857

1396656

1366555

1336454

1607766

1577664

1547463

1517362

1487161

1457059

1426858

1396757

1366656

1346555

1607866

1577665

1547564

1517462

1487261

1457160

1426959

1406858

1376757

1346556

1617967

1587866

1557665

1527563

1497362

1467261

1437060

1406959

1386857

1356656


TM 1-1520-237-CL

P-31 C1

SAFAA9978_1_CL

1000

3000

4500

5500

~FT−10 0−5HP

FREE AIR TEMPERATURE ~ 0C


0

2000

4000

5000

6000

GW ~ 100 LB


Q ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

5



*


1.0 0.9 1.0 0.9 1.0 0.9 1.0 0.9

ATF

6500GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

21510086

21310086

21010086

208100

85205100

85204100

85202100

85200

9984

1969782

1929581

21510086

21310086

21010086

208100

85205100

85204100

85200

9884

1979782

1939581

1909379

21410086

21210086

21010086

207100

85204100

85203100

85202100

851999984

1959782

1919581

21410086

21210086

21010086

207100

85204100

85200

9883

1979682

1939480

1899379

1869177

21410086

21110086

20910086

206100

85203100

85202100

85201100

85198

9984

1949782

1909581

21410086

21110086

20910086

206100

85203100

851999883

1959682

1919480

1889278

1849077

21310086

21010086

20810086

205100

85203100

85201100

85198

9984

1949782

1909580

1879379

21310086

21010086

20810086

205100

85199

9783

1959581

1919380

1879178

1849076

1808875


TM 1-1520-237-CL

P-32 C1

SAFAA9978_2_CL

7500

8500

9500

10,500

~FT−10 0−5HP



7000

8000

9000

10,000

11,000

GW ~ 100 LB


Q ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

5



*


1.0 0.9 1.0 0.9 1.0 0.9 1.0 0.9

ATF

11,500GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

1899479

1859278

1829076

1788875

1758774

1728572

1688471

1658269

1628068

1597967

1869278

1839076

1798875

1768773

1738572

1698371

1668269

1638068

1607867

1567765

1889479

1849278

1819076

1778875

1748673

1708572

1678370

1648169

1618068

1577866

1828976

1798875

1758673

1728472

1698370

1658169

1627968

1597866

1567665

1537564

1879379

1839278

1809076

1768875

1738673

1698472

1668370

1628169

1597967

1567866

1818875

1778774

1748572

1708371

1678270

1648068

1607867

1577765

1547564

1517463

1839177

1808976

1768774

1738673

1698471

1668270

1638169

1597967

1567766

1537664

1778673

1738472

1708371

1668169

1637968

1607866

1577665

1537564

1507362

1477261


TM 1-1520-237-CL

P-33 C1

SAFAA9978_3_CL

12,500

13,500

14,500

15,000

~FT−10 0−5HP



12,000

13,000

14,000

15,500

GW ~ 100 LB


Q ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

5



*


1.0 0.9 1.0 0.9 1.0 0.9 1.0 0.9

ATF

1567765

1537664

1507463

1477362

1447160

1417059

1386958

1366757

1537564

1507463

1477362

1457160

1427059

1396858

1366757

1346656

1547665

1517564

1487362

1457261

1427060

1396958

1366857

1336656

1507362

1477261

1447060

1416959

1386757

1356656

1326455

1306354

1537664

1497463

1467362

1437160

1407059

1376858

1346656

1316555

1477261

1447060

1416959

1386758

1356656

1336555

1306354

1276253

1507463

1477362

1437160

1406959

1376858

1346656

1326555

1296354

1447060

1416959

1386757

1356656

1326455

1306354

1276152

1246051


TM 1-1520-237-CL

P-34 C1

SAFAA9979_1_CL

1000

2500

3500

4500

~FT10 2015HP



0

2000

3000

4000

5000

GW ~ 100 LB


Q ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

25



*


1.0 0.9 1.0 0.9 1.0 0.9 1.0 0.9

ATF

5500GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

21210086

20910086

20710086

205100

85204100

85203100

85201100

85198

9984

1959782

1919580

21210086

20910086

20710086

205100

852029884

1989782

1949580

1919379

1879177

1848976

21110086

20810086

2049884

2009783

1969581

1939380

1899278

1869077

1828875

1798674

21010086

20710086

205100

85203100

85202100

851989884

1959682

1919480

1879279

1849077

21010086

2059884

1989581

1949380

1919279

1879077

1848876

1808774

1778572

1738371

20910086

20610086

204100

852019984

1979783

1949581

1909380

1869178

1839076

1798875

2069884

1999581

1929179

1889077

1858876

1828774

1788573

1758372

1718170

1688069

21110086

208100

85206100

85204100

85203100

85201100

951989884

1959682

1919480

1879279


TM 1-1520-237-CL

P-35 C1

SAFAA9979_2_CL

6500

7500

8500

9500

~FT10 2015HP



6000

7000

8000

9000

10,000

GW ~ 100 LB


Q ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

25



*


1.0 0.9 1.0 0.9 1.0 0.9 1.0 0.9

ATF

10,500

GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

1879379

1839177

1818976

1768774

1738573

1698471

1668270

1628068

1597967

1557766

1808775

1778673

1738471

1698270

1668169

1637967

1607766

1567665

1537463

1507362

1849177

1808976

1768774

1738573

1698471

1668270

1628068

1597967

1557766

1527564

1758472

1728371

1688169

1657968

1627867

1587665

1557564

1527363

1497261

1467060

1808875

1778774

1738573

1708371

1668270

1638068

1597867

1567765

1527564

1497463

1708170

1678068

1637867

1607766

1577564

1547363

1517262

1487060

1456959

1426758

1768673

1728472

1698270

1658169

1627967

1587766

1547664

1517463

1487262

1447161

1657867

1617666

1587564

1557363

1527262

1487061

1456959

1426758

1396657

1366456


TM 1-1520-237-CL

P-36 C1

SAFAA9979_3_CL

11,500

12,500

13,500

14,500

~FT10 2015HP



11,000

12,000

13,000

14,000

15,000

GW ~ 100 LB


Q ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

25



*


1.0 0.9 1.0 0.9 1.0 0.9 1.0 0.9

ATF

15,500GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

1527564

1497463

1467262

1437160

6959

6858

6656

6555

6354

6253

1477161

1447060

1416858

1386757

6556

6455

6253

6152

6051

5850

1497463

1467262

1437160

1406959

6758

6656

6455

6354

6253

6051

1436959

1406758

1376656

1346455

6354

6153

6052

5950

5749

5648

1467261

1437060

1406959

1376758

6656

6455

6354

6152

1236051

1205850

1396657

1366556

1336354

1306253

6052

5951

5850

5648

1165547

1135446

1416959

1386858

1356657

1336555

1306354

1276253

1256052

1225950

1346354

1316253

1286052

1255951

1225750

1195648

1175547

1145346

140

137

132

129

135

132

127

124

137

135

129

126

131

128

123

120

134

131

126

127

124

119

135 129 132 126 129 121

126 121 123 117

ABOVEENGINE

AMBIENTTEMPLIMIT


TM 1-1520-237-CL

P-37 C1

SAFAA9980_1_CL

500

1500

2500

3500

~FT30 4035HP


0

1000

2000

3000

4000

GW ~ 100 LB


Q ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

45* 1.0 0.9 1.0 0.9 1.0 0.9 1.0 0.9

ATF

4500 Q ~ OGE ~ %

Q ~ IGE ~ %

GW ~ 100 LB

* GW ~ 100 LB = GW DIVIDED BY 100 LBQ = TORQUE %OGE = 100 FT WHEEL HEIGHT



5000 Q ~ OGE ~ %

Q ~ IGE ~ %

GW ~ 100 LB

5500 Q ~ OGE ~ %

Q ~ IGE ~ %

GW ~ 100 LB ABOVEENGINE

AMBIENTTEMPLIMIT

20810086

20710086

20610086

2039985

2009783

1969682

1939480

1899279

1859077

1828976

1788774

1748573

2009481

1969380

1939178

1899077

1868876

1838674

1798573

1768372

1738270

1698069

1667867

1627766

20710086

2049884

2009783

1969581

1939380

1899178

1869077

1828876

1798674

1758573

1728371

1688169

1929078

1898876

1868775

1828574

1798472

1768271

1738170

1697968

1667867

1637666

1597464

1567363

2009582

1969481

1939279

1899178

1868976

1828775

1798674

1758472

1728271

1698169

1657968

1627766

1858674

1828473

1798372

1768271

1728069

1697968

1667767

1637565

1607464

1567262

1537161

1506960

1929178

1888977

1858775

1828674

1788473

1758371

1728170

1688069

1657867

1627666

1587564

1788271

1758070

1717968

1687767

1657666

1627565

1597363

1567262

1537061

1506960

1466758


TM 1-1520-237-CL

P-38 C1

SAFAA9980_2_CL

6500

7500

8500

9500

~FT30 4035HP


6000

7000

8000

9000

10,000

GW ~ 100 LB


Q ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

Q ~ OGE ~ %

Q ~ IGE ~ %

Q ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

45ATF

10,500 Q ~ OGE ~ %

Q ~ IGE ~ %




11,000 Q ~ OGE ~ %

Q ~ IGE ~ %

GW ~ 100 LB

11,500 Q ~ OGE ~ %

Q ~ IGE ~ %

GW ~ 100 LB

Q ~ IGE ~ %

GW ~ 100 LB

GW ~ 100 LB

GW ~ 100 LB

* 1.0 0.9 1.0 0.9 1.0 0.9 1.0 0.9

8371

8170

8068

7867

7665

7564

7363

7161

7060

6858

6757

6556

7564

7363

7262

7061

6959

6758

6657

6456

6354

6253

6052

5951

7968

7766

7665

7464

7362

7161

1456960

1426858

1396657

1366556

7161

7060

6859

6758

6556

6455

1346254

1326153

1296052

1265850

7565

7463

1527262

1487061

1466959

1426758

6859

6657

1416556

1386355

1356254

1326153

1517161

1487060

1406456

1376354

138

135

129

126

154

151

148

144

141

146

143

140

137

134

131

151

148

140

137

171

167

164

161

157

159

156

153

149

164

161

158

155

153

150

146

143

158

155

147

144

ABOVE ENGINEAMBIENT

TEMP LIMIT


TM 1-1520-237-CL

P-39 C1

SAFAA9981CL

500

1500

2500

~FT50 55HP



0

1000

2000

GW ~ 100 LB


Q ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %



*


1.0 0.9 1.0 0.9

ATF

8674

8473

8372

8170

8069

7868

184

180

177

174

171

167 ABOVE ENGINEAMBIENT

TEMP LIMIT

1707767

1677666

1647565

1617364

1587262

1557061

1768271

1738069

1707968

1677767

1637665

1637364

1607263

1577162

1546961

1516859


TM 1-1520-237-CL

P-40 C1

SAFAA9970_1_CL

0

1000

2000

3000

4000

5000

6000

7000

8000

9000

10,000

11,000

12,000

13,000

14,000

15,000

~FT −50 −45 −40 −25−30−35HP FREE AIR TEMPERATURE ~ 0C

−20

ATF = 1.0 OR 0.9

* MAXIMUM TORQUE AVAILABLE IS LIMITED TO 120%BELOW 80 KIAS AND 100% TORQUE ABOVE 80 KIAS

500

1500

2500

3500

4500

5500

6500

7500

8500

9500

10,500

11,500

12,500

13,500

14,500

15,500

120120120120120118116114112110108106104102100

9896949391898886848381807876757372

1201201201201201191171141121101081061041031019997959392908887858382807877757472

120120120120120120117115113111109107105103101100

98969492918987868482817977767473

120120120120120120118116114112110108106104102100

99979593919088868583818078767573

12012012012012012012011711511311110910710510310199989694929089878583828079777574

120120120120120120120118116114112110108106104102100

989694939189878684828179777674

120120120120120120120119117115112110108106104102101999795939190888685838180787675

MAXIMUM TORQUE AVAILABLE* − 10 MINUTE LIMITANTI−ICE OFF T700−GE−701C ENGINE

Figure 3. Maximum Torque Available (Sheet 1 of 5)701C

TM 1-1520-237-CL

P-41 C1

SAFAA9970_2_CL

1.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.9

1.00.91.00.91.00.91.00.9

0

500

1000

1500

2000

2500

3000

3500

4000

4500

5000

5500

6000

6500

7000

7500


15

MAXIMUM TORQUE AVAILABLE* − 10 MINUTE LIMITANTI−ICE OFF T700−GE−701C ENGINE (CONTINUED)


120120120120120120120120120120120120120120120120118118116116114114112112110110108108106106104104

120120120120120120120120120120120120120120120118119116117114115112113110111108109106107104105102

120120120120120120120120120120120120120119120117119115116113114111112109110107108105106103104101

120120120120120120120120120120120120120118120116118114115112113110111108109105107103105102103100

12012012012012012012012012012012011812011611811311611111410911210711010510810310510110399

10197

120120120120120120120119120117120115119113116111114109112107110105108103106101104

9910297

10095

120120120120120119120117120115119113117110115108113106111104109102106100104

9810297

100959893


TM 1-1520-237-CL

P-42 C1

SAFAA9970_3_CL

1.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.9

1.00.91.00.91.00.91.00.9

8000

8500

9000

9500

10,000

10,500

11,000

11,500

12,000

12,500

13,000

13,500

14,000

14,500

15,000

15,500


15



102102100100

98989696949492929191898987878686848482828181797977777676

1031001019899969794959394919289908888868784858383818279807878767674

10299

1009798959693949192909188898687858583848182808078797677757573

10198999697949592939091888986888586838481828081787976777576737472

9995979395929390928890868884868384818379817879767875767375727370

9893969194899288908688848782858183798177807678747673757173707268

9691948992879185898487828580837982778075787477727571736972687166


TM 1-1520-237-CL

P-43 C1

SAFAA9970_4_CL

10998

10796

10594

10393

101919989978795859384918289808778

8577837582738072

11310211110010998

10796

10594

10392

1019199899787958593839182

8980877885778375

11710611510411310211110010998

10796

10594

10292

10090988896879485

9283908189808778

120109119107117105114103112101110

99108

97106

95104

9310292

100909888

9686948492839081

12011312011112010911810711610511410311210110999

10797

10596

10394

10192

9990978895869384

12011712011512011312011111810911610711410511110310910110799

10597

10395

10193999197899587

12012012011812011612011412011211811011610811310611110410910210710010598

10396

1019499929790

1.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.9

1.00.91.00.91.00.91.00.9

0

500

1000

1500

2000

2500

3000

3500

4000

4500

5000

5500

6000

6500

7000

7500


50



AREA IS ABOVE ENGINE AMBIENT TEMPERATURE LIMIT


TM 1-1520-237-CL

P-44 C1

SAFAA9970_5_CL

1.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.91.00.9

1.00.91.00.91.00.91.00.9

8000

8500

9000

9500

10,000

10,500

11,000

11,500

12,000

12,500

13,000

13,500

14,000

14,500

15,000

15,500


50



958893879185898387818580847882768075787377727570746972677166

938691848982878085798477827580747872777175697368

91838981877985788376827480737871

8879867784768274

6964

7266706569636762

76697568736671657063686267616559

807279717769756874667265706369626760665964586356

8576837581737971787076687467726571646962686166596558635762556054

8173807278707668746773657164696268616659655863576255605459535752

7870766974677365716469626861665964586357615560545953575156505449

AREA IS ABOVE ENGINE AMBIENT TEMPERATURE LIMIT


TM 1-1520-237-CL

P-45 C1

SAFAA9972_1_CL

1000

3000

5000

6000


−20

ATF = 1.0 OR 0.9


0

2000

4000

5500

6500

GW ~ 100 LB

MAXIMUM OGE HOVER WEIGHT AND TORQUE REQUIREDANTI−ICE OFF T700−GE−701C ENGINE

Q ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

−15

9785

9886

10087

10187

10489

10690

10690

10488

10287

9886

9986

10187

10389

10690

10892

10791

10589

10388

9886

10087

10288

10489

10691

10993

10892

10690

10489

9986

10187

10389

10590

10792

11093

10993

10791

10589

10087

10188

10389

10691

10892

11194

11093

10892

10690

10187

10289

10490

10691

10993

11195

11094

10892

10690

10188

10389

10590

10792

11094

11296

11295

11093

10892



*


220

220

220

220

220

217

213

209

220

220

220

220

220

217

213

209

220

220

220

220

220

217

213

209

220

220

220

220

220

217

213

209

220

220

220

220

220

217

213

209

220

220

220

220

220

217

213

209

220

220

220

220

220

217

213

209

220 220 220 220 220 220 220

Figure 4. Hover Torque Required (Sheet 1 of 12)701C

TM 1-1520-237-CL

P-46 C1

SAFAA9972_2_CL

7500

8500

9500

10,500


−20

ATF = 1.0 OR 0.9


7000

8000

9000

10,000

11,000

GW ~ 100 LB

MAXIMUM OGE HOVER WEIGHT AND TORQUE REQUIREDANTI−ICE OFF T700−GE−701C ENGINE (CONTINUED)

Q ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

−15



*


205100

852019883

1989682

1949480

1909379

1879179

1838977

1808876

1768675

20510186

201100

851979883

1949682

1909480

1879279

1839177

1808976

1768775

20510287

201100

851979884

1949782

1909581

1879379

1839178

1809076

1768875

20510388

20110186

1979984

1949883

1909681

1879480

1839278

1809177

1768875

205104

8820110287

197100

85194

9883

1909682

1869580

1839379

1809177

1768976

205104

8920110287

19710186

1949984

1909782

1869581

1839379

1799178

1769076

205106

90202104

8819810287

194100

85190

9883

1879682

1839480

1809279

1769177


TM 1-1520-237-CL

P-47 C1

SAFAA9972_3_CL

12,000

13,000

14,000

15,000


−20

ATF = 1.0 OR 0.9


11,500

12,500

13,500

14,500

15,500

GW ~ 100 LB


Q ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

−15



*


1738473

1698372

1668171

1638069

1607868

1577667

1547564

1507362

1738673

1698472

1668270

1638169

1597967

1567766

1537664

1507463

1477362

1738673

1698572

1668370

1638169

1598068

1567866

1537665

1507564

1477362

1738774

1698572

1668471

1638270

1598068

1567967

1537766

1507564

1477463

1728774

1698673

1668471

1638270

1598169

1567967

1537866

1507665

1477463

1728875

1698673

1668572

1628371

1598169

1568068

1537866

1507765

1477564

1738976

1708774

1668673

1638471

1608270

1578169

1537967

1507766

1477664

1477261


TM 1-1520-237-CL

P-48 C1

SAFAA9973_1_CL

2000

4000

5500

6500

~FT−10 0−5HP



0

3000

5000

6000

7000

GW ~ 100 LB


Q ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

5



*


1.0 0.9 1.0 0.9 1.0 0.9 1.0 0.9

ATF

22010288

220106

91220108

93220110

9422011396

21811396

21411194

210109

93206107

91

22010288

220106

91220108

93220110

9422011396

21611295

212110

93208108

92205106

90

22010389

220106

92220109

9322011195

220114

9721611296

212110

94208108

92204106

90

22010389

220106

92220109

9322011195

21611195

212109

93208107

9120510590

20110388

22010389

220107

9222010994

22011296

218113

9721411195

210109

93206107

9120210589

22010389

220107

9222010994

22011296

214110

94210108

92206106

90202104

8919810287

22010490

220108

93220110

9522011396

21511295

211110

93207108

92203106

9019910388

22010490

220108

93220110

9521811195

210107

9220610590

20210388

19810187

1959985


TM 1-1520-237-CL

P-49 C1

SAFAA9973_2_CL

8000

9000

10,000

11,000

~FT−10 0−5HP



7500

8500

9500

10,500

11,500

GW ~ 100 LB


Q ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

5



*


1.0 0.9 1.0 0.9 1.0 0.9 1.0 0.9

ATF

20210589

19910388

19510186

1919984

1879783

1849581

1809480

1779278

1739077

201104

8819710287

193100

85190

9883

1869682

1829480

1799279

1759177

1728976

200104

8919610287

193100

851899883

1859682

1829480

1789279

1759177

1718976

19710186

1939985

1899785

1869581

1829380

1789178

1759077

1728875

1688674

19810388

19410186

1919984

1879783

1839581

1799379

1769178

1738976

1698775

194100

851919883

1879684

1839480

1809279

1769077

1728875

1698674

1668572

19510186

1929985

1889783

1849581

1819480

1779278

1739077

1708875

1678674

1919783

1879582

1830380

1809278

1769077

17388

1698674

1668472

1638371

75


TM 1-1520-237-CL

P-50 C1

SAFAA9973_3_CL

12,500

13,500

14,500

15,000

~FT−10 0−5HP



12,000

13,000

14,000

15,500

GW ~ 100 LB


Q ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

5



*


1.0 0.9 1.0 0.9 1.0 0.9 1.0 0.9

ATF

1708875

1678774

1648572

1608371

1578270

1548068

1517866

1477665

1698774

1658673

1628471

1598270

1568169

1537967

1507765

1467564

1688774

1658573

1618471

1588270

1558068

1527967

1497766

1658572

1628371

1598169

1558068

1527867

1497665

1467564

1437363

1668673

1628472

1598270

1568169

1537967

1507766

1477665

1447463

1628371

1598170

1568068

1537867

1507665

1477564

1447363

1417261

1638472

1608371

1578169

1547968

1517866

1477665

1447564

1417362

1598169

1567968

1537867

1507665

1477564

1447363

1417262

1387062

1467564


TM 1-1520-237-CL

P-51 C1

SAFAA9974_1_CL

1000

3000

4000

5000

~FT10 2015HP



0

2000

3500

4500

5500

GW ~ 100 LB


Q ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

25



*


1.0 0.9 1.0 0.9 1.0 0.9 1.0 0.9

ATF

6000GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

22010590

220106

92220109

9322011195

22011296

220114

9721611296

212110

94208108

92

10690

22010590

220106

92220109

9322011195

21811195

214109

93210107

9220610590

20210388

10187

220105

91220107

9222010994

22011196

220113

9721711396

21311194

209109

93205106

91

10489

220105

91220107

9222010994

21811195

214109

93210106

9120610490

20210288

19910086

9885

220106

92220108

93220110

9522011396

219113

9721411195

210109

93206107

9120210589

10388

220106

92220108

93220110

95214108

93210106

91206104

8920210288

19810086

1959884

9683

220107

9222010994

22011195

219114

9721511195

211109

93207107

9120310590

19910388

10186

220107

9222010994

21710994

20910590

20510388

20110187

1979985

1949783

1909582

9380

204 198 201 195 199 191 195 186


TM 1-1520-237-CL

P-52 C1

SAFAA9974_2_CL

7000

8000

9000

10,000

~FT10 2015HP



6500

7500

8500

9500

10,500

GW ~ 100 LB


Q ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

25



*


1.0 0.9 1.0 0.9 1.0 0.9 1.0 0.9

ATF

11,000GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

200104

8919610289

193100

851899883

185

1959985

1919783

1879582

1839380

180

19810287

19410086

1909884

1869682

183

1919783

1879581

1849380

1809178

176

19510186

1939984

1879783

1839581

180

1879481

1839279

1809078

1768976

173

1919984

1889783

1849581

1809379

177

1829179

1798979

1758777

1728674

1689682

1829480

1789279

1749077

1718875

8774

9178

1768977

1738875

1698674

1668472

8271

9481

1799279

1759177

1728976

1759177

8573

8977

1738775

1698573

1668472

1638270

8069

9379

1769178

1738976

1698775

1668573

8472

8775

1698573

1668372

1628170

1598069

7867

9178

1738976

1708775

1668573

1638472

8270

8472

1658271

1618069

1587868

1557766

7565

168 163 165 159 163 156 160 152


TM 1-1520-237-CL

P-53 C1

SAFAA9974_3_CL

12,000

13,000

14,000

15,000

~FT10 2015HP



11,500

12,500

13,500

14,500

15,500

GW ~ 100 LB


Q ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

25



*


1.0 0.9 1.0 0.9 1.0 0.9 1.0 0.9

ATF

16,000 Q ~ OGE ~ %

Q ~ IGE ~ %

GW ~ 100 LB

1648572

1618371

1588170

1558068

1517867

1487665

1457564

7363

7263

7062

1598169

1567968

1537766

1507665

1477464

1447362

1417161

7060

6859

6759

1628371

1588270

1558068

1527867

1497766

1467564

1437363

7262

7060

6959

1567968

1537766

1507565

1477464

1447262

1417161

1386960

6858

6657

6556

1598272

1568070

1537967

1507766

1477565

1447463

1417262

7160

6959

6858

1537666

1507566

1477363

1447262

1417061

1386961

1356758

6657

6455

6354

1568069

1537867

1507766

1477564

1447363

1417262

1387060

1497464

1457262

1427061

1376858

1376858

1346659

1316556

142

139

136

138

135

132

140

137

134

135

132

129

138

135

132

132

129

126

ABOVEENGINE

AMBIENTTEMPLIMIT


TM 1-1520-237-CL

P-54 C1

SAFAA9975_1_CL

500

1500

2500

3500

~FT30 4035HP


0

1000

2000

3000

4000

GW ~ 100 LB


Q ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

45* 1.0 0.9 1.0 0.9 1.0 0.9 1.0 0.9

ATF

4500 Q ~ OGE ~ %

Q ~ IGE ~ %

GW ~ 100 LB




5000 Q ~ OGE ~ %

Q ~ IGE ~ %

GW ~ 100 LB

5500 Q ~ OGE ~ %

Q ~ IGE ~ %

GW ~ 100 LB

22010793

220108

9322010994

220110

9522011296

220113

9721611295

212109

93208107

9220410590

10388

10186

22010793

220108

9322010994

21610793

212105

9120810389

20410187

20010086

1969884

1929682

9481

9279

220108

9322010994

220110

9522011196

21911296

215110

94211108

93207106

91203104

8919910287

10085

9884

220108

93217107

92213105

9120910389

20510187

2019986

1979784

1949582

1909381

1869279

9078

8876

22010994

220110

9522011195

21811195

214109

93210107

9220610590

20210288

19810086

1949885

9683

9481

22010994

21110490

20810288

20410086

2009885

1969683

1929481

1889280

1859078

1818977

8775

8574

220110

9522011195

216106

94212107

9220810590

20410388

20010187

1969985

1929683

1889582

9380

20910288

206100

872029885

1989683

1949482

1909280

1879178

1838977

1798775

1768574

8372

200 189 195 183 190 178 185 172

196 185 191 179 186 174 ABOVEENGINE

AMBIENTTEMPLIMIT


TM 1-1520-237-CL

P-55 C1

SAFAA9975_2_CL

6500

7500

8500

9500

~FT30 4035HP


6000

7000

8000

9000

10,000

GW ~ 100 LB


Q ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

Q ~ OGE ~ %

Q ~ IGE ~ %

Q ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %

45ATF

10,500 Q ~ OGE ~ %

Q ~ IGE ~ %




11,000 Q ~ OGE ~ %

Q ~ IGE ~ %

GW ~ 100 LB

11,500 Q ~ OGE ~ %

Q ~ IGE ~ %

GW ~ 100 LB

Q ~ IGE ~ %

GW ~ 100 LB

GW ~ 100 LB

GW ~ 100 LB

* 1.0 0.9 1.0 0.9 1.0 0.9 1.0 0.9

1929985

1889783

9581

9380

9178

8976

8775

8573

8372

8270

8068

7867

1819078

1788876

8674

8573

8371

8170

7968

7867

7665

7464

7363

7161

1879682

1849480

9279

9077

8875

8674

8472

8271

8169

7968

7766

7565

1758674

1728473

8371

8170

7968

7767

7666

7464

7264

7161

6958

6859

1839280

1799178

8976

8776

8573

8371

1708372

1678170

8069

7867

7666

7565

1778977

1748775

1658071

1627868

185

181

177

174

171

167

164

180

176

173

169

168

165

162

158

175

172

168

165

164

160

157

154174

170

167

163

160

156

153

160

157

154

151

147

144

166

162

159

156

152

149

155

152

148

145

142

139

ABOVE ENGINEAMBIENT

TEMP LIMIT


TM 1-1520-237-CL

P-56 C1

SAFAA9976CL

500

1500

2500

~FT50 55HP



0

1000

2000

GW ~ 100 LB


Q ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %GW ~ 100 LBQ ~ OGE ~ %

Q ~ IGE ~ %



*


1.0 0.9 1.0 0.9

ATF

10994

10792

10591

10389

10187

9985

9885

9684

9482

9380

9179

8977

10591

10389

10187

9985

9784

9582

9380

9179

8977

8776

218

214

210

206

202

203

199

196

192

188

212

208

204

200

196

197

193

190

186

182

198 184 ABOVE ENGINEAMBIENT

TEMP LIMIT


TM 1-1520-237-CL

P-57/(P-58 Blank) C1

The Metric System and Equivalents

Linear Measure

1 centimeter = 10 millimeters = .39 inch1 decimeter = 10 centimeters = 3.94 inches1 meter = 10 decimeters = 39.37 inches1 dekameter = 10 meters = 32.8 feet1 hectometer = 10 dekameters = 328.08 feet1 kilometer = 10 hectometers = 3,280.8 feet

Weights

1 centigram = 10 milligrams = .15 grain1 decigram = 10 centigrams = 1.54 grains1 gram = 10 decigrams = .035 ounce1 dekagram = 10 grams = .35 ounce1 hectogram = 10 dekagrams = 3.52 ounces1 kilogram = 10 hectograms = 2.2 pounds1 quintal = 100 kilograms = 220.46 pounds1 metric ton = 10 quintals = 1.1 short tons

Liquid Measure

1 centiliter = 10 milliters = .34 fl. ounce1 deciliter = 10 centiliters = 3.38 fl. ounces1 liter = 10 deciliters = 33.81 fl. ounces1 dekaliter = 10 liters = 2.64 gallons1 hectoliter = 10 dekaliters = 26.42 gallons1 kiloliter = 10 hectoliters = 264.18 gallons

Temperature Conversion

°C to °F = (9/5 x°C) + 32°F to °C = (°F - 32) x 5/9

TM 1-1520-237-CL

TM 1-1520-237-CL



Chief of Staff

Official:



DISTRIBUTION:To be distributed in accordance with DA Form 12-31-E,block no. 1310, requirements for TM 1-1520-237-CL.

Documents

OPERATOR’S AND CREWMEMBER’S CHECKLIST UH · PDF fileC 6 TM 1--1520--237--CL CHANGE HEADQUARTERS DEPARTMENT OF THE ARMY NO. 6 WASHINGTON,D.C.,27 November2000 Operator’s and Crewmember’s