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TRANSCRIPT
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
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 4
Remove pages Insert pages
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)
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 Army9917306
DISTRIBUTION:To be distributed in accordance with InitialDistribution Number (IDN) 311310 requirements forTM 1-1520-237-CL.
TM 1-1520-237-CLC 3
CHANGE HEADQUARTERS DEPARTMENT OF THE ARMYNO. 3 WASHINGTON, D.C., 29 January 1999
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.
Remove pages Insert pages
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
2. Retain this sheet in front of manual for reference pur-poses.
By Order of the Secretary of the Army:
DENNIS J. REIMERGeneral, United States Army
Chief of Staff
Official:
JOEL B. HUDSONAdministrative Assistant to the
Secretary of the Army05404
DISTRIBUTION:To be distributed in accordance with InitialDistribution Number (IDN) 311310 requirements forTM 1-1520-237-CL.
TM 1-1520-237-CLC 2
CHANGE HEADQUARTERS DEPARTMENT OF THE ARMYNO. 2 WASHINGTON, D.C., 30 OCTOBER 1998
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 2
Remove pages Insert pages
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)
2. Retain this sheet in front of manual for reference pur-poses.
By Order of the Secretary of the Army:
DENNIS J. REIMERGeneral, United States Army
Chief of Staff
Official:
JOEL B. HUDSONAdministrative Assistant to the
Secretary of the Army05471
DISTRIBUTION:To be distributed in accordance with InitialDistribution Number (IDN) 311310 requirements forTM 1-1520-237-CL.
TM 1-1520-237-CLC 1
CHANGE HEADQUARTERS DEPARTMENT OF THE ARMYNO. 1 WASHINGTON, D.C., 30 JUNE 1997
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-MTF, 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.
Remove pages Insert pages
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
By Order of the Secretary of the Army:
DENNIS J. REIMERGeneral, United States Army
Chief of Staff
Official:
JOEL B. HUDSONAdministrative Assistant to the
Secretary of the Army03948
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.
Title..................... 0Blank................... 0A-B ..................... 6i ........................... 6ii .......................... 3N-1 ...................... 0N-2 ...................... 4N-3 ...................... 3N-4 - N-4.1......... 4N-4.2 Blank ........ 4N-5 ...................... 0N-6 - N-6.1......... 4N-6.2 Blank ........ 4N-7 ...................... 3N-8 - N-10.......... 6N-11 .................... 3N-12 - N-15........ 4N-16 Blank ......... 4
PageNo.
ChangeNo.
E-1 - E-6............. 0E-7....................... 1E-8 - E-9............. 0E-10 Blank.......... 0E-11..................... 4E-12 - E-13......... 0E-14..................... 4E-15 - E-19......... 0E-20 Blank.......... 0E-21..................... 4E-22..................... 0E-23..................... 4E-24 - E-26......... 2E-27..................... 6E-28..................... 0E-29 - E-32......... 3P-1 - P-2 ............. 0P-3....................... 4
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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
PageNo.
ChangeNo.
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)
1. Fuselage - Check.
* 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)
1. Fuselage - Check.
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 .
* 2. Systems - Check.
* 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
1. TAIL WHEEL switch - As required.
2. Exterior lights - As required.
3. Avionics/mission equipment - As required.
PARKING AND SHUTDOWN
1. TAIL WHEEL switch - As required.
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.
* 9. Systems - Check.
* 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 .
* 2. Systems - Check.
* 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.
3. LAND AS SOON AS PRACTICABLE.
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.
2. LAND AS SOON AS PRACTICABLE.
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.
3. LAND AS SOON AS PRACTICABLE.
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.
6. LAND AS SOON AS PRACTICABLE.
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.
6. LAND AS SOON AS PRACTICABLE.
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).
3. Refer to single-engine failure emergency proce-dure.
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.
3. Refer to single-engine failure emergency proce-dure.
LIGHTNING STRIKE
1. ENG POWER CONT levers - Adjust as re-quired to controlRPM.
2. LAND AS SOON AS POSSIBLE.
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.
2. LAND AS SOON AS PRACTICABLE.
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.
6. LAND AS SOON AS PRACTICABLE.
#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.
3. LAND AS SOON AS PRACTICABLE.
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
1. LAND AS SOON AS POSSIBLE.
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 .
2. LAND AS SOON AS POSSIBLE.
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.
2. FIRE EXTGH switch - MAIN/RESERVE asrequired.
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.
3. FIRE EXTGH switch - MAIN/RESERVE asrequired.
4. LAND AS SOON AS POSSIBLE.
ELECTRICAL FIRE IN FLIGHT
1. BATT andGENERATORS switches -OFF.
2. LAND AS SOON AS POSSIBLE.
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.
4. LAND AS SOON AS PRACTICABLE.
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.
2. LAND AS SOON AS PRACTICABLE.
#1 AND #2 FUEL FLTR BYPASS CAUTIONLIGHTS ON
LAND AS SOON AS POSSIBLE.
#1 FUEL LOW AND #2 FUEL LOWCAUTION LIGHTS ON
LAND AS SOON AS PRACTICABLE.
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.
2. LAND AS SOON AS PRACTICABLE.
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.
6. LAND AS SOON AS PRACTICABLE.
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.
7. LAND AS SOON AS PRACTICABLE.
#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.
2. LAND AS SOON AS PRACTICABLE.
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. LAND AS SOON AS PRACTICABLE.
#2 HYD PUMP CAUTION LIGHT ON
1. POWER ON RESET switches - Simultaneouslypress and release.
2. LAND AS SOON AS PRACTICABLE.
#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).
4. LAND AS SOON AS POSSIBLE.
TM 1-1520-237-CL
E-17
#1 OR #2 PRI SERVO PRESS CAUTIONLIGHT ON
LAND AS SOON AS POSSIBLE.
#1 RSVR LOW AND #1 HYD PUMPCAUTION LIGHTS ON WITH BACK-UPPUMP ON ADVISORY LIGHT ON
1. LAND AS SOON AS PRACTICABLE.
If the BACK-UP RSVR LOW caution light also goes on:
2. SVO OFF switch - 1ST STG.
3. LAND AS SOON AS POSSIBLE.
#2 RSVR LOW AND #2 HYD PUMPCAUTION LIGHTS ON WITH BACK-UPPUMP ON ADVISORY LIGHT ON
1. POWER ON RESET switches - Simultaneouslypress; then release.
2. LAND AS SOON AS PRACTICABLE.
If BACK-UP RSVR LOW caution light also goes on:
3. SVO OFF switch - 2ND STG.
4. LAND AS SOON AS POSSIBLE.
#2 RSVR LOW CAUTION LIGHT ON
1. BOOST andFPS switches - Off.
2. LAND AS SOON AS PRACTICABLE.
TM 1-1520-237-CL
E-18
COLLECTIVE BOOST SERVO HARDOVER/POWER PISTON FAILURE
1. BOOST switch - Off.
2. LAND AS SOON AS PRACTICABLE.
PITCH BOOST SERVO HARDOVER
1. SAS (1 and2) andFPS switches - Off.
2. LAND AS SOON AS PRACTICABLE.
BOOST SERVO OFF CAUTION LIGHT ON
1. BOOST switch - Off.
2. LAND AS SOON AS PRACTICABLE.
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:
5. LAND AS SOON AS POSSIBLE.
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.
4. LAND AS SOON AS PRACTICABLE.
PITCH, ROLL OR YAW/TRIM HARDOVER
POWER ON RESET switches - Simultaneously pressand then release.
If failure returns, control affected axis manually.
TRIM ACTUATOR JAMMED
LAND AS SOON AS PRACTICABLE.
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.
4. LAND AS SOON AS PRACTICABLE.
If manual control is not possible:
5. STAB POS indicator - Check and fly at or belowKIAS LIMITS shown on placard.
6. LAND AS SOON AS PRACTICABLE.
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.
5. LAND AS SOON AS PRACTICABLE.
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.
4. LAND AS SOON AS PRACTICABLE.
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:
3. LAND AS SOON AS POSSIBLE.
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).
5. LAND AS SOON AS PRACTICABLE.
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:
3. LAND AS SOON AS PRACTICABLE.
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.
3. LAND AS SOON AS PRACTICABLE.
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.
4. LAND AS SOON AS PRACTICABLE.
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.
(4) Press line select key 7 left.
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.
(3) Press line select key 3 left.
(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.
(2) Press line select key 5 left.
(3) Enter altitude of present position in scratchpad (e.g., 156 ft is entered as 0.156 and dis-played as 0.2).
(4) Press line select key 3 left.
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.
(4) Press line select key 5 left.
(5) Enter Area/Eastings/Northings or longitudein scratch pad.
(6) Press line select key 7 left.
(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
a. AIR SOURCE HEAT/START switch - ENG.
b. FUEL BOOST PUMP CONTROL switches -CheckON.
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
a. AIR SOURCE HEAT/START switch - ENG.
b. FUEL BOOST PUMP CONTROL switches -CheckON.
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
a. AIR SOURCE HEAT/START switch - ENG.
b. FUEL BOOST PUMP CONTROL switches -CheckON.
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:
a. AIR SOURCE HEAT/START switch - ENG.
b. FUEL BOOST PUMP CONTROL switches -CheckON.
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:
a. AIR SOURCE HEAT/START switch - ENG.
b. FUEL BOOST PUMP CONTROL switches -CheckON.
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.
a. AIR SOURCE HEAT/START switch - ENG.
b. FUEL BOOST PUMP CONTROL switches -CheckON.
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)
* MAXIMUM TORQUE AVAILABLE IS LIMITED TO 100%
100100100100100100100100100100100100100100100100100100100100
999997979696949492929090
100100100100100100100100100100100100100100100100100100100100100
9899979795959394919290
100100100100100100100100100100100100100100100100100100100
981009699949793959193899288
100100100100100100100100100100100100100100100100100100100
981009699949792959093889187
100100100100100100100100100100100100100100100
99100
97100
95999397919590938891868984
100100100100100100100100100100100100100
98100
97100
959993979195899387918689848782
100100100100100100100100100
98100
97100
95100
9399929790958893869184898387818579
Figure 1. Maximum Torque Available (Sheet 2 of 5)700
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
~FT ATF −15 −10 −5 1050HP FREE AIR TEMPERATURE ~ 0C
15
MAXIMUM TORQUE AVAILABLE* − 30 MINUTE LIMITANTI−ICE OFF T700−GE−700 ENGINE (CONTINUED)
* MAXIMUM TORQUE AVAILABLE IS LIMITED TO 100%
8989878786868484828281817979787876767575737372727070696968686666
9088898787858583848282808078797777757674747373717170706869676766
9086888486838581837981788076787577737572737072697067696668656663
9085888386828480837881777975787476727470736971677066686466636562
8883868184798278817679757773767174707268716769666864666365616360
8581847982778076797477737571747072687167696568646662656163606258
8478827680757973777275707469726771666964676366616460635962576056
Figure 1. Maximum Torque Available (Sheet 3 of 5)700
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* − 30 MINUTE LIMITANTI−ICE OFF T700−GE−700 ENGINE (CONTINUED)
* 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
Figure 1. Maximum Torque Available (Sheet 4 of 5)700
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
~FT ATF 20 25 30 454035HP FREE AIR TEMPERATURE ~ 0C
50
MAXIMUM TORQUE AVAILABLE* − 30 MINUTE LIMITANTI−ICE OFF T700−GE−700 ENGINE (CONTINUED)
* 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
Figure 1. Maximum Torque Available (Sheet 5 of 5)700
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
~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
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
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
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
Figure 2. Hover Torque Required (Sheet 2 of 12)700
TM 1-1520-237-CL
P-30 C1
SAFAA9977_3_CL
11,500
12,500
13,500
14,500
~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
11,000
12,000
13,000
14,000
15,000
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
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
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
Figure 2. Hover Torque Required (Sheet 3 of 12)700
TM 1-1520-237-CL
P-31 C1
SAFAA9978_1_CL
1000
3000
4500
5500
~FT−10 0−5HP
FREE AIR TEMPERATURE ~ 0C
* GW ~ 100 LB = GW DIVIDED BY 100 LB
0
2000
4000
5000
6000
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 ~ %
5
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
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
Figure 2. Hover Torque Required (Sheet 4 of 12)700
TM 1-1520-237-CL
P-32 C1
SAFAA9978_2_CL
7500
8500
9500
10,500
~FT−10 0−5HP
FREE AIR TEMPERATURE ~ 0C
* GW ~ 100 LB = GW DIVIDED BY 100 LB
7000
8000
9000
10,000
11,000
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 ~ %
5
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
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
Figure 2. Hover Torque Required (Sheet 5 of 12)700
TM 1-1520-237-CL
P-33 C1
SAFAA9978_3_CL
12,500
13,500
14,500
15,000
~FT−10 0−5HP
FREE AIR TEMPERATURE ~ 0C
* GW ~ 100 LB = GW DIVIDED BY 100 LB
12,000
13,000
14,000
15,500
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 ~ %
5
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
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
Figure 2. Hover Torque Required (Sheet 6 of 12)700
TM 1-1520-237-CL
P-34 C1
SAFAA9979_1_CL
1000
2500
3500
4500
~FT10 2015HP
FREE AIR TEMPERATURE ~ 0C
* 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 (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 ~ %
25
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
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
Figure 2. Hover Torque Required (Sheet 7 of 12)700
TM 1-1520-237-CL
P-35 C1
SAFAA9979_2_CL
6500
7500
8500
9500
~FT10 2015HP
FREE AIR TEMPERATURE ~ 0C
* GW ~ 100 LB = GW DIVIDED BY 100 LB
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 ~ %
25
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
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
Figure 2. Hover Torque Required (Sheet 8 of 12)700
TM 1-1520-237-CL
P-36 C1
SAFAA9979_3_CL
11,500
12,500
13,500
14,500
~FT10 2015HP
FREE AIR TEMPERATURE ~ 0C
* GW ~ 100 LB = GW DIVIDED BY 100 LB
11,000
12,000
13,000
14,000
15,000
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 ~ %
25
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
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
Figure 2. Hover Torque Required (Sheet 9 of 12)700
TM 1-1520-237-CL
P-37 C1
SAFAA9980_1_CL
500
1500
2500
3500
~FT30 4035HP
FREE AIR TEMPERATURE ~ 0C
0
1000
2000
3000
4000
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 ~ %
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
MAXIMUM HOVER WEIGHT IS LIMITED TO 22,000 LB100% Q TRANSMISSION LIMIT OR30 MINUTE ENGINE Q LIMIT.
~IGE = 10 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
Figure 2. Hover Torque Required (Sheet 10 of 12)700
TM 1-1520-237-CL
P-38 C1
SAFAA9980_2_CL
6500
7500
8500
9500
~FT30 4035HP
FREE AIR TEMPERATURE ~ 0C
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 ~ %
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 ~ %
* GW ~ 100 LB = GW DIVIDED BY 100 LBQ = 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
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
Figure 2. Hover Torque Required (Sheet 11 of 12)700
TM 1-1520-237-CL
P-39 C1
SAFAA9981CL
500
1500
2500
~FT50 55HP
FREE AIR TEMPERATURE ~ 0C
* GW ~ 100 LB = GW DIVIDED BY 100 LB
0
1000
2000
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 ~ %
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
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
Figure 2. Hover Torque Required (Sheet 12 of 12)700
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
~FT ATF −15 −10 −5 1050HP FREE AIR TEMPERATURE ~ 0C
15
MAXIMUM TORQUE AVAILABLE* − 10 MINUTE LIMITANTI−ICE OFF T700−GE−701C ENGINE (CONTINUED)
* MAXIMUM TORQUE AVAILABLE IS LIMITED TO 120%BELOW 80 KIAS AND 100% TORQUE ABOVE 80 KIAS
120120120120120120120120120120120120120120120120118118116116114114112112110110108108106106104104
120120120120120120120120120120120120120120120118119116117114115112113110111108109106107104105102
120120120120120120120120120120120120120119120117119115116113114111112109110107108105106103104101
120120120120120120120120120120120120120118120116118114115112113110111108109105107103105102103100
12012012012012012012012012012012011812011611811311611111410911210711010510810310510110399
10197
120120120120120120120119120117120115119113116111114109112107110105108103106101104
9910297
10095
120120120120120119120117120115119113117110115108113106111104109102106100104
9810297
100959893
Figure 3. Maximum Torque Available (Sheet 2 of 5)701C
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
~FT ATF −15 −10 −5 1050HP FREE AIR TEMPERATURE ~ 0C
15
MAXIMUM TORQUE AVAILABLE* − 10 MINUTE LIMITANTI−ICE OFF T700−GE−701C ENGINE (CONTINUED)
* MAXIMUM TORQUE AVAILABLE IS LIMITED TO 120%BELOW 80 KIAS AND 100% TORQUE ABOVE 80 KIAS
102102100100
98989696949492929191898987878686848482828181797977777676
1031001019899969794959394919289908888868784858383818279807878767674
10299
1009798959693949192909188898687858583848182808078797677757573
10198999697949592939091888986888586838481828081787976777576737472
9995979395929390928890868884868384818379817879767875767375727370
9893969194899288908688848782858183798177807678747673757173707268
9691948992879185898487828580837982778075787477727571736972687166
Figure 3. Maximum Torque Available (Sheet 3 of 5)701C
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
~FT ATF 20 25 30 454035HP FREE AIR TEMPERATURE ~ 0C
50
MAXIMUM TORQUE AVAILABLE* − 10 MINUTE LIMITANTI−ICE OFF T700−GE−701C ENGINE (CONTINUED)
* MAXIMUM TORQUE AVAILABLE IS LIMITED TO 120%BELOW 80 KIAS AND 100% TORQUE ABOVE 80 KIAS
AREA IS ABOVE ENGINE AMBIENT TEMPERATURE LIMIT
Figure 3. Maximum Torque Available (Sheet 4 of 5)701C
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
~FT ATF 20 25 30 454035HP FREE AIR TEMPERATURE ~ 0C
50
MAXIMUM TORQUE AVAILABLE* − 10 MINUTE LIMITANTI−ICE OFF T700−GE−701C ENGINE (CONTINUED)
* MAXIMUM TORQUE AVAILABLE IS LIMITED TO 120%BELOW 80 KIAS AND 100% TORQUE ABOVE 80 KIAS
958893879185898387818580847882768075787377727570746972677166
938691848982878085798477827580747872777175697368
91838981877985788376827480737871
8879867784768274
6964
7266706569636762
76697568736671657063686267616559
807279717769756874667265706369626760665964586356
8576837581737971787076687467726571646962686166596558635762556054
8173807278707668746773657164696268616659655863576255605459535752
7870766974677365716469626861665964586357615560545953575156505449
AREA IS ABOVE ENGINE AMBIENT TEMPERATURE LIMIT
Figure 3. Maximum Torque Available (Sheet 5 of 5)701C
TM 1-1520-237-CL
P-45 C1
SAFAA9972_1_CL
1000
3000
5000
6000
~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
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
Q = TORQUE %OGE = 100 FT WHEEL HEIGHT
MAXIMUM HOVER WEIGHT IS LIMITED TO 22,000 LB120% Q TRANSMISSION LIMIT OR10 MINUTE ENGINE Q LIMIT.
*
~IGE = 10 FT WHEEL HEIGHT
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
~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
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
Q = TORQUE %OGE = 100 FT WHEEL HEIGHT
MAXIMUM HOVER WEIGHT IS LIMITED TO 22,000 LB120% Q TRANSMISSION LIMIT OR10 MINUTE ENGINE Q LIMIT.
*
~IGE = 10 FT WHEEL HEIGHT
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
Figure 4. Hover Torque Required (Sheet 2 of 12)701C
TM 1-1520-237-CL
P-47 C1
SAFAA9972_3_CL
12,000
13,000
14,000
15,000
~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
11,500
12,500
13,500
14,500
15,500
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
Q = TORQUE %OGE = 100 FT WHEEL HEIGHT
MAXIMUM HOVER WEIGHT IS LIMITED TO 22,000 LB120% Q TRANSMISSION LIMIT OR10 MINUTE ENGINE Q LIMIT.
*
~IGE = 10 FT WHEEL HEIGHT
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
Figure 4. Hover Torque Required (Sheet 3 of 12)701C
TM 1-1520-237-CL
P-48 C1
SAFAA9973_1_CL
2000
4000
5500
6500
~FT−10 0−5HP
FREE AIR TEMPERATURE ~ 0C
* GW ~ 100 LB = GW DIVIDED BY 100 LB
0
3000
5000
6000
7000
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 ~ %
5
Q = TORQUE %OGE = 100 FT WHEEL HEIGHT
MAXIMUM HOVER WEIGHT IS LIMITED TO 22,000 LB120% Q TRANSMISSION LIMIT OR10 MINUTE ENGINE Q LIMIT.
*
~IGE = 10 FT WHEEL HEIGHT
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
Figure 4. Hover Torque Required (Sheet 4 of 12)701C
TM 1-1520-237-CL
P-49 C1
SAFAA9973_2_CL
8000
9000
10,000
11,000
~FT−10 0−5HP
FREE AIR TEMPERATURE ~ 0C
* GW ~ 100 LB = GW DIVIDED BY 100 LB
7500
8500
9500
10,500
11,500
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 ~ %
5
Q = TORQUE %OGE = 100 FT WHEEL HEIGHT
MAXIMUM HOVER WEIGHT IS LIMITED TO 22,000 LB120% Q TRANSMISSION LIMIT OR10 MINUTE ENGINE Q LIMIT.
*
~IGE = 10 FT WHEEL HEIGHT
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
Figure 4. Hover Torque Required (Sheet 5 of 12)701C
TM 1-1520-237-CL
P-50 C1
SAFAA9973_3_CL
12,500
13,500
14,500
15,000
~FT−10 0−5HP
FREE AIR TEMPERATURE ~ 0C
* GW ~ 100 LB = GW DIVIDED BY 100 LB
12,000
13,000
14,000
15,500
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 ~ %
5
Q = TORQUE %OGE = 100 FT WHEEL HEIGHT
MAXIMUM HOVER WEIGHT IS LIMITED TO 22,000 LB120% Q TRANSMISSION LIMIT OR10 MINUTE ENGINE Q LIMIT.
*
~IGE = 10 FT WHEEL HEIGHT
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
Figure 4. Hover Torque Required (Sheet 6 of 12)701C
TM 1-1520-237-CL
P-51 C1
SAFAA9974_1_CL
1000
3000
4000
5000
~FT10 2015HP
FREE AIR TEMPERATURE ~ 0C
* GW ~ 100 LB = GW DIVIDED BY 100 LB
0
2000
3500
4500
5500
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 ~ %
25
Q = TORQUE %OGE = 100 FT WHEEL HEIGHT
MAXIMUM HOVER WEIGHT IS LIMITED TO 22,000 LB120% Q TRANSMISSION LIMIT OR10 MINUTE ENGINE Q LIMIT.
*
~IGE = 10 FT WHEEL HEIGHT
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
Figure 4. Hover Torque Required (Sheet 7 of 12)701C
TM 1-1520-237-CL
P-52 C1
SAFAA9974_2_CL
7000
8000
9000
10,000
~FT10 2015HP
FREE AIR TEMPERATURE ~ 0C
* GW ~ 100 LB = GW DIVIDED BY 100 LB
6500
7500
8500
9500
10,500
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 ~ %
25
Q = TORQUE %OGE = 100 FT WHEEL HEIGHT
MAXIMUM HOVER WEIGHT IS LIMITED TO 22,000 LB120% Q TRANSMISSION LIMIT OR10 MINUTE ENGINE Q LIMIT.
*
~IGE = 10 FT WHEEL HEIGHT
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
Figure 4. Hover Torque Required (Sheet 8 of 12)701C
TM 1-1520-237-CL
P-53 C1
SAFAA9974_3_CL
12,000
13,000
14,000
15,000
~FT10 2015HP
FREE AIR TEMPERATURE ~ 0C
* GW ~ 100 LB = GW DIVIDED BY 100 LB
11,500
12,500
13,500
14,500
15,500
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 ~ %
25
Q = TORQUE %OGE = 100 FT WHEEL HEIGHT
MAXIMUM HOVER WEIGHT IS LIMITED TO 22,000 LB120% Q TRANSMISSION LIMIT OR10 MINUTE ENGINE Q LIMIT.
*
~IGE = 10 FT WHEEL HEIGHT
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
Figure 4. Hover Torque Required (Sheet 9 of 12)701C
TM 1-1520-237-CL
P-54 C1
SAFAA9975_1_CL
500
1500
2500
3500
~FT30 4035HP
FREE AIR TEMPERATURE ~ 0C
0
1000
2000
3000
4000
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 ~ %
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
MAXIMUM HOVER WEIGHT IS LIMITED TO 22,000 LB120% Q TRANSMISSION LIMIT OR10 MINUTE ENGINE Q LIMIT.
~IGE = 10 FT WHEEL HEIGHT
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
Figure 4. Hover Torque Required (Sheet 10 of 12)701C
TM 1-1520-237-CL
P-55 C1
SAFAA9975_2_CL
6500
7500
8500
9500
~FT30 4035HP
FREE AIR TEMPERATURE ~ 0C
6000
7000
8000
9000
10,000
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 ~ %
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 ~ %
* GW ~ 100 LB = GW DIVIDED BY 100 LBQ = TORQUE %OGE = 100 FT WHEEL HEIGHT
MAXIMUM HOVER WEIGHT IS LIMITED TO 22,000 LB120% Q TRANSMISSION LIMIT OR10 MINUTE ENGINE Q LIMIT.
~IGE = 10 FT WHEEL HEIGHT
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
Figure 4. Hover Torque Required (Sheet 11 of 12)701C
TM 1-1520-237-CL
P-56 C1
SAFAA9976CL
500
1500
2500
~FT50 55HP
FREE AIR TEMPERATURE ~ 0C
* GW ~ 100 LB = GW DIVIDED BY 100 LB
0
1000
2000
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 ~ %
Q = TORQUE %OGE = 100 FT WHEEL HEIGHT
MAXIMUM HOVER WEIGHT IS LIMITED TO 22,000 LB120% Q TRANSMISSION LIMIT OR10 MINUTE ENGINE Q LIMIT.
*
~IGE = 10 FT WHEEL HEIGHT
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
Figure 4. Hover Torque Required (Sheet 12 of 12)701C
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
By Order of the Secretary of the Army:
DENNIS J. REIMERGeneral, United States Army
Chief of Staff
Official:
JOEL B. HUDSONAdministrative Assistant to the
Secretary of the Army03463
DISTRIBUTION:To be distributed in accordance with DA Form 12-31-E,block no. 1310, requirements for TM 1-1520-237-CL.