TM_1-1520-237-10.pdf

TECHNICAL MANUAL

OPERATOR’S MANUAL

FOR

HELICOPTER, UTILITY TACTICAL TRANSPORT

UH-60A NSN 1520-01-035-0266 (EIC RSA)

UH-60L NSN 1520-01-298-4532 (EIC: RSM)

EH-60A NSN 1520-01-082-0686 (EIC: RSB)

*This manual supersedes TM 1-1520-237-10, dated 17 April 2006, including all changes.

*TM 1-1520-237-10

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WARNING

Personnel performing operations, procedures, and practices which are included or implied in this technical manual shall observe the following warnings. Disregard of these warnings and precautionary information can cause serious injury or loss of life.

SEALED LEAD ACID BATTERIES (SLAB)

Lead-acid cells and batteries produce hydrogen-sulfide gas during charging. Normally, gases produced are recombined within the cells. Venting can occur if the cells are defective, damaged, or charged excessively. If venting occurs, it is evident by a sulfur (rotten eggs) odor in the cockpit/cabin. Although the possibility of toxic levels is extremely remote, the crew should immediately ventilate the cockpit.

CARBON MONOXIDE

When smoke, suspected carbon monoxide fumes, or symptoms of anoxia exist, the crew should immediately ventilate the cockpit.

ELECTROMAGNETIC INTERFERENCE (EMI)

No electrical/electronic devices of any sort, other than those described in this manual or appropriate airworthiness release and approved by USAAMCOM AMSRD-AMR-AE-U, are to be operated by crewmembers or passengers during operation of this helicopter.

FIRE EXTINGUISHER

Exposure to high concentrations of extinguishing agent or decomposition products should be avoided. The liquid should not be allowed to come into contact with the skin, as it may cause frost bite or low temperature burns.

HANDLING FUEL AND OIL

Turbine fuels and lubricating oils contain additives which are poisonous and readily absorbed through the skin. Do not al-low them to remain on skin longer than necessary.

HIGH VOLTAGE

All ground handling personnel shall be informed of high voltage hazards when making external cargo hookups.

NOISE

Sound pressure levels in this helicopter during some operating conditions exceed the Surgeon General’s hearing conserva-tion criteria, as defined in DA PAM 40-501. Hearing protection devices, such as the aviator helmet or ear plugs are required to be worn by all personnel in and around the helicopter during its operation. When window guns are firing, when flights exceed 100 minutes during any 24 hour period, or when speeds are above 120 knots, helmet and ear plugs shall be worn by all crewmembers.

WEAPONS AND AMMUNITION

Observe all standard safety precautions governing the handling of weapons and live ammunition. When not in use, point all weapons in a direction offering the least exposure to personnel and property in case of accidental firing. Do not walk in front of weapons. Ensure that rounds are not chambered while weapons are stowed in the mounts. SAFE the machine gun before servicing. To avoid potentially dangerous situations, follow all procedural warnings in text.

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LITHIUM BATTERIES

Lithium batteries, including but not limited to lithium-ion batteries, utilized in computers and carry-on/worn equipment, may experience thermal runaway, spontaneous ignition or explosion if disassembled, physically damaged, short circuited, overcharged, or exposed to fire or high temperatures. Avoid solar heating of lithium batteries, devices with lithium batteries installed, and do not place near sources of heat. Thermal runaway may be indicated by rapid heating, odor, smoke, and may quickly produce jets of flame. Battery thermal runaway may produce both flammable vapor and oxygen. In the event of thermal runaway, the carry on/worn equipment containing the battery should be jettisoned from the aircraft immediately.

Use of fire extinguisher agent or water may temporarily slow thermal reaction while the equipment is removed from personnel/aircraft. Do not cover or enclose the device in an attempt to smother the fire, as this will insulate the battery pack and encourage further thermal runaway. A lithium battery fire may be difficult to extinguish and reignition is highly likely.

Thermal runaway of batteries in rack-mounted equipment should be treated as an aircraft fire.

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- 0A - 0 - 0A C T

T A C MM M M T

You can improve this manual. If you find any mistakes, or if you know of a way to improve these procedures, please let us know. Mail your letter or DA Form 2028 (Recommended Changes to Publications and Blank Forms), located in the back of this manual, directly to: Commander, US Army Aviation and Missile Command, ATTN: AMSAM-MSS-LP, Redstone Arsenal, AL 35898- 5000. A reply will be furnished to you. You may also send in your comments electronically to our E-mail address: 2028@redstone.army.mil or by fax 256-842-6546/DSN 788-6546. For the World Wide Web use: https://amcom2028.redstone.army.mil. Instructions for sending an electronic 2028 may be found at the back of this manual immediately preceding the hard copy 2028.

AZA MAT A MAT

This document has been reviewed for the presence of HAZARDOUS CHEMICALS AND TOXIC SUBSTANCES as defined by the EPCRA 302 and 313 lists by the AMCOM G-4 (Logistics) Environmental Division. As of the base document through Change 04, dated 17 April 2013, all references to Hazardous Chemicals and Toxic Substances have been removed from this docu-ment by substitution with non-hazardous or less hazardous materials where possible.

TA C T T

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CHAPTER 1 INTRODUCTION ......................................................................................... 1-1

CHAPTER 2 AIRCRAFT AND SYSTEMS DESCRIPTION AND OPERATION .......... 2-1

Section I Aircraft........................................................................................................... 2-1

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T C CA MA A A A T

A TM T T A M

. 1-1520-237-10 A T .C. 25 eptem er 200

*This manual supersedes TM 1-1520-237-10, dated 17 April 2006, including all changes.

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UH-60A

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TABLE OF CONTENTS

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TA C T T Cont

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Section II Emergency Equipment................................................................................... 2-27

Section III Engines and Related Systems........................................................................ 2-29

Section IV Fuel System ................................................................................................... 2-41

Section V Flight Controls ............................................................................................... 2-43

Section VI Hydraulic and Pneumatic System.................................................................. 2-51

Section VII Powertrain System ......................................................................................... 2-56.1

Section VIII Main and Tail Rotor Groups ......................................................................... 2-59

Section IX Utility Systems............................................................................................... 2-61

Section X Heating, Ventilating, Cooling, and Environmental Control Unit ................. 2-66.6

Section XI Electrical Power Supply and Distribution Systems....................................... 2-69

Section XII Auxiliary Power Unit..................................................................................... 2-78

Section XIII Lighting.......................................................................................................... 2-81

Section XIV Flight Instruments .......................................................................................... 2-84

Section XV Servicing, Parking, and Mooring................................................................... 2-104.1

CHAPTER 3 AVIONICS .................................................................................................... 3-1

Section I General........................................................................................................... 3-1

Section II Communications ............................................................................................ 3-8.1

Section III Navigation...................................................................................................... 3-43

Section IV Transponder and Radar.................................................................................. 3-137

CHAPTER 4 MISSION EQUIPMENT............................................................................... 4-1

Section I Mission Avionics ........................................................................................... 4-1

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Section II Armament ...................................................................................................... 4-25

Section III Cargo Handling Systems ............................................................................... 4-40

Section IV Mission Flexible Systems.............................................................................. 4-45

Section V Air Warrior .................................................................................................... 4-83

Section VI Blue Force Tracking System ......................................................................... 4-93

CHAPTER 5 OPERATING LIMITS AND RESTRICTIONS ........................................... 5-1

Section I General........................................................................................................... 5-1

Section II System Limits ................................................................................................ 5-2

Section III Power Limits.................................................................................................. 5-8.1

Section IV Loading Limits............................................................................................... 5-11

Section V Airspeed Limits ............................................................................................. 5-12

Section VI Maneuvering Limits....................................................................................... 5-18

Section VII Environmental Restrictions ........................................................................... 5-21

Section VIII Other Limitations........................................................................................... 5-23

CHAPTER 6 WEIGHT/BALANCE AND LOADING....................................................... 6-1

Section I General........................................................................................................... 6-1

Section II Weight and Balance....................................................................................... 6-3

Section III Fuel/Oil .......................................................................................................... 6-5

Section IV Personnel........................................................................................................ 6-7

Section V Mission Equipment ........................................................................................ 6-16.7

Section VI Cargo Loading ............................................................................................... 6-19

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TABLE OF CONTENTS

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Section VII Center of Gravity ........................................................................................... 6-25

CHAPTER 7 PERFORMANCE DATA 700 ................................................................. 7-1

Section I Introduction.................................................................................................... 7-1

Section II Maximum Torque Available ......................................................................... 7-6

Section III Hover.............................................................................................................. 7-9

Section IV Cruise ............................................................................................................. 7-13

Section V Optimum Cruise............................................................................................. 7-144

Section VI Drag................................................................................................................ 7-147

Section VII Climb - Descent ............................................................................................. 7-150

Section VIII Fuel Flow ....................................................................................................... 7-153

Section IX Airspeed System Description ........................................................................ 7-156

Section X Special Mission Performance ........................................................................ 7-163

CHAPTER 7A PERFORMANCE DATA 701C 701 CC ............................................ 7A-1

Section I Introduction.................................................................................................... 7A-1

Section II Maximum Torque Available ......................................................................... 7A-6

Section III Hover.............................................................................................................. 7A-14

Section IV Cruise ............................................................................................................. 7A-18

Section V Optimum Cruise............................................................................................. 7A-172

Section VI Drag................................................................................................................ 7A-175

Section VII Climb - Descent ............................................................................................. 7A-178

Section VIII Fuel Flow ....................................................................................................... 7A-181

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Section IX Airspeed System Characteristics ................................................................... 7A-184

Section X Special Mission Performance ........................................................................ 7A-187

CHAPTER 8 NORMAL PROCEDURES ........................................................................... 8-1

Section I Mission Planning ........................................................................................... 8-1

Section II Operating Procedures and Maneuvers........................................................... 8-3

Section III Instrument Flight ........................................................................................... 8-20.1

Section IV Flight Characteristics ..................................................................................... 8-21

Section V Adverse Environmental Conditions............................................................... 8-23

CHAPTER 9 EMERGENCY PROCEDURES ................................................................... 9-1

Section I Aircraft Systems ............................................................................................ 9-1

Section II Mission Equipment ........................................................................................ 9-25

APPENDIX A REFERENCES .............................................................................................. A-1

APPENDIX B ABBREVIATIONS AND TERMS............................................................... B-1

INDEX INDEX ........................................................................................................... INDEX-1

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TABLE OF CONTENTS

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1.1 General

These instructions are for use by the operator. They ap-ply to UH-60A, UH-60L, and EH-60A helicopters.

1.2 WARNINGS, CAUTIONS AND NOTES.

Warnings, cautions, and notes are used to emphasize important and critical instructions and are used for the fol-lowing conditions

W

An operating procedure, practice, etc., which, if not correctly followed, could result in personal injury or loss of life.

C

An operating procedure, practice, etc., which, if not strictly observed, could result in damage to or destruction of equipment.

T

An operating procedure, condition, etc., which is essential to highlight.

1.3 C T .

This manual contains the complete operating instruc-tions and procedures for UH-60A, UH-60L, and EH-60A helicopters. The primary mission of this helicopter is that of tactical transport of troops, medical evacuation, cargo, and reconnaissance within the capabil i t ies of the helicopter. The observance of limitations, performance, and weight and balance data provided is mandatory. The observance of procedures is mandatory except when modification is required because of multiple emergencies, adverse weather, terrain, etc. Your flying experience is recognized and therefore, basic flight principles are not included. IT IS REQUIRED THAT THIS MANUAL BE

CARRIED IN THE HELICOPTER AT ALL TIMES.

1. A A C .

Appendix A is a listing of official publications cited within the manual applicable to and available for flight crews and fault isolation/trouble references.

1.5 A A AT A T M .

Abbreviations listed are to be used to clarify the text in this manual only. Do not use them as standard abbrevia-tions.

1. .

The index lists, in alphabetical order, paragraphs, figures, and tables contained in this manual. Chapter 7 and Chapter 7A performance data have additional indexes within the chapters.

1.7 A M A AT A T AM.

Reports necessary to comply with the safety program are prescribed in AR 385-10.

1.8 T CT A M MAT T

T M .

For information concerning destruction of Army materiel to prevent enemy use, refer to TM 750-244-1-5.

1. M A C .

Army aviators flight record and aircraft inspection and maintenance records, which are to be used by crewmem-bers, are prescribed in PAM 738-751 and TM 55-1500- 342-23.

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WARNING

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CAUTION

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DESCRIPTION.

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APPENDIX A, REFERENCES

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APPENDIX B, ABBREVIATIONS AND TERMS

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6 INDEX

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1.10 A AT C A M .

Changes (except as noted below) to the text and tables, including new material on added pages, are indicated by a vertical line in the outer margin extending close to the entire area of the material affected. A miniature pointing hand symbol denotes changes on an illustration. A MA OR CHANGE symbol on the illustration indicates extensive changes have been made. Change symbols are not used to indicate changes in the following

a. Introductory material.

b. Indexes and tabular data where the change cannot be identified.

c. Blank space resulting from the deletion of text, an illustration, or a table.

d. Correction of minor inaccuracies, such as spelling, punctuation, relocation of material, etc., unless such cor-rection changes the meaning of instructive information and procedures.

1.11 A CT T C .

Designator symbols listed below, are used to show limited effectivity of airframe information material in conjunction with text content, paragraph titles, and il-lustrations. Designators may be used to indicate proper ef-fectivity, unless the material applies to all models and configurations within the manual. Designator symbols precede procedural steps in Chapters 8 and 9. If the mate-rial applies to all series and configurations, no designator symbol will be used.

DESIGNATOR

SYMBOL

APPLICATION

U H - 6 0 A a n d U H - 6 0 L peculiar information.

0A UH-60A peculiar informa-tion.

0A H-60A equipped with T700- GE-701D/CC engines (701D core with 701C hydrome-chanical unit and digital electronic unit) and H-60L

CDU.

0 UH-60L peculiar informa-tion.

DESIGNATOR

SYMBOL

APPLICATION

EH-60A peculiar informa-tion.

700 Helicopters equipped with T700-GE-700 engines.

701C 701 CC Helicopters equipped with T700-GE-701C engines or T700-GE-701D/CC engines (701D core with 701C hy-d romechan ica l un i t and digital electronic unit).

C Enhanced Digital Engine C o n t r o l U n i t s p e c i fi c information.

A Helicopters equipped with Attitude Heading Reference Set.

128 Helicopters equipped with Doppler/GPS Navigation Set

(DGNS) AN/ASN-128D.

A2C2 Helicopters with AN/ASC-38 i n s t a l l e d . A n A W R i s required for A2C2S opera-tion.

A C2 Helicopters with AN/ASC-15 i n s t a l l e d . A n A W R i s required for ABC2 operation.

CM Helicopters equipped with

AN/AAR-57.

C A Helicopters equipped with AN/AAR-57 cha ff on l y capability.

M Helicopters equipped with Integrated Vehicle Health Management System.

1.12 A M .

This symbol will be used throughout this manual to designate information applicable to the high drag configuration described in Chapters 7 and 7A.

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EXPLANATION OF CHANGE SYMBOLS.

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WERIES AND EFFECTIVITY CODES

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UH

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UH-60A

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UH-60L

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EDECU

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AHRS

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HIGH DRAG SYMBOL

1.13 PLACARDED AIRCRAFT SYMBOL.

This symbol will be used throughout this manual to designate applicability to helicopters which have torque placard limitations.

1.14 USE OF WORDS SHALL, SHOULD, AND

MAY.

Within this technical manual the word shall is used to indicate a mandatory requirement. The word should is used to indicate a nonmandatory but preferred method of accomplishment. The word may is used to indicate an ac-ceptable method of accomplishment.

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CHAPTER 2

AIRCRAFT AND SYSTEMS DESCRIPTION AND OPERATION

Section I AIRCRAFT

2.1 GENERAL.

This chapter describes the UH-60A, UH-60L, and EH- 60A helicopters’ systems and flight controls. The functioning of electrical and mechanical components is simplified where more detailed knowledge is not neces-sary.

2.2 UH-60A.

The UH-60A (BLACK HAWK) (Figure 2-1) is a twin-turbine engine, single rotor, semimonocoque fuselage helicopter. Primary mission capability of the helicopter is tactical transport of troops, supplies and equipment.

Secondary missions include training, mobilization, development of new and improved concepts, and support of disaster relief. The main rotor system has four blades made of titanium/fiberglass. The drive train consists of a main transmission, intermediate gear box, and tail rotor gear box with interconnecting shafts. The propulsion system has two T700-GE-700 engines operating in paral-lel. The nonretractable landing gear consists of the main landing gear and a tailwheel. The armament consists of two 7.62 mm machineguns, one on each side of the helicopter in the forward cabin. Kit installations for the helicopter consist of range extension tanks, rescue hoist, medical evacuation, infrared suppression, blade anti-icing/ deicing, blackout devices, snow skis, winterization, and static/rappelling kit. Refer to this chapter and Chapter 4 for kit descriptions.

2.3 UH-60A WITH T700-GE-701D/CC ENGINES.

H−60A+ Some UH-60A helicopters have been modi-fied by replacing the T700-GE-700 with T700-GE-701D/ CC engines. This modification also added upgraded Inlet Anti-Ice valves, cross bleed shutoff valves and couplings that withstand the higher bleed air temperatures of the new engine. An additional Nr sensor mounted on the accessory gearbox and a third potentiometer installed on the mixing unit provide transient droop improvement. Automatic relight is provided by the addition of relays in the cabin overhead. The Central Display Unit (CDU) has been re-placed with a UH-60L CDU to provide T700-GE-701D/ CC engine parameters.

2.4 UH-60L.

The UH-60L helicopter is the same as the UH-60A helicopter except engines T700-GE-701C or T700-GE- 701D/CC replace T700-GE-700. Also the main transmis-sion has been modified to increase its durability. Differ-ences between the two transmissions are annotated with UH-60A or UH-60L.

2.5 EH-60A.

The EH-60A helicopter is a modified UH-60A (Figure 2-1) with a crew of four. The mission equipment consists of electronic systems with modifications that will ensure that the mission requirements are met. The EH-60A system includes air conditioning, helicopter survivability equipment, and avionics equipment. An electronics compartment within the transition section is used for avionics equipment. The compartment can be entered from the right side of the helicopter. The mission systems employ two operators: The direction finder/electronics surveillance measure (DF ESM) operator controlling the electronics surveillance functions, and the electronics countermeasure (ECM) operator controlling the active countermeasure functions. The EH-60A can operate independently or in conjunction with up to two additional, similarly equipped, helicopter. When operating in the mul-tisystem mode, secured air-to-air communications are provided for automatic tasking between helicopter.

Secured air-to-ground communications are also provided for voice reporting purposes.

2.6 DIMENSIONS.

Principle dimensions of the helicopter are based on the cyclic stick and tail rotor pedals being centered and the collective stick being in its lowest position. All dimensions are approximate and they are as shown on Figure 2-2.

2-1

2.7 TURNING RADIUS AND GROUND

CLEARANCE.

WARNING

Main rotor clearance in Figure 2-3 is shown with cyclic centered and level ground. Cyclic displacement or sloping terrain may cause rotor blade clearance to be significantly less.

For information on turning radius and ground clearance refer to Figure 2-3.

2.8 COMPARTMENT DIAGRAM.

2.8.1 Compartment Diagram. UH The fuselage is

divided into two main compartments, the cockpit and cabin. The cockpit (Figure 2-4) is at the front of the helicopter with the pilots sitting in parallel, each with a set of flight controls and instruments. Operation of electrical controls is shared by both. The cabin compartment contains space for crew chief seating, troop seating, litter installation, and cargo. Restraint of cargo is by tiedown rings installed in the floor. Two stowage compartments (Figure 6-12), at the rear of the cabin over the main fuel tanks, are for flyaway equipment. The equipment storage compartments are reached from inside the cabin. A gust lock control, APU accumulator handpump and pressure gage, and APU ESU (Figure 2-5) are also installed.

2.8.2 Compartment Diagram. EH A fixed observer

seat is installed to allow observation of either operator position (Figure 2-6). Floor attachments are provided for securing rack mounts and seats. Blackout curtains may be used to eliminate any light intrusion into the cockpit dur-ing night operations, or any glare on the operator’s console during day operations. Blackout curtains may be used between cockpit and cabin during NVG operations.

2.9 UPPER AND LOWER CONSOLES.

All cockpit electrical controls are on the upper and lower consoles and instrument panel. The upper console (Figure 2-7), overhead between pilot and copilot, contains engine controls, fire emergency controls, heater and windshield wiper controls, internal and external light controls, electrical systems, and miscellaneous helicopter system controls. The rear portion of the upper panel contains the dc essential bus circuit breaker panels. The lower console (Figure 2-8) next to the base of the instru-ment panel and extending through the cockpit between the pilot and copilot is easily reached by either pilot. The console is arranged with communicat ion panels , navigational panels, and flight attitude/stability controls.

The rear part of the console houses the battery bus and battery utility bus circuit breaker panel and parking brake handle.

2.10 LANDING GEAR SYSTEM.

The helicopter has a nonretractable landing gear consisting of two main gear assemblies and a tailwheel assembly. The landing gear permits helicopter takeoffs and landings on slopes in any direct ion. The system incorporates a jack and kneel feature that permits manual raising or lowering of the fuselage for air transportability.

A landing gear weight-on-wheels (WOW) switch is in-stalled on the left landing gear to control operation of selected systems (Table 2-1). The switch is deactivated when the weight of the helicopter is on the landing gear.

On helicopters equipped with ESSS fixed provisions, a WOW switch is also installed on the right landing gear drag beam to provide ac underfrequency cutout and external stores jettison. The left WOW switch provides all other WOW functions as without ESSS provisions and the EMER JETT ALL capabilities. The left WOW switch allows the A2C2S Interface Panel (AIP) isolate switch to isolate the aircraft’s AC Essential Bus power from the cockpit, while on the ground. See Table 2-1 for reference.

2.10.1 Main Landing Gear. The main landing gear is

mounted on each side of the helicopter forward of center of gravity. Each individual landing gear has a single wheel, a drag beam, and a two-stage oleo shock strut. The lower stage will absorb energy from landings up to 10 feet-per-second (fps). Above 10 fps the upper stage and lower stage combine to absorb loads up to 39 fps (about

11.25 Gs).

2.10.2 Wheel Brake System. Main landing gear

wheels have disc hydraulic brakes. The self-contained, self-adjusting system is operated by the pilot’s and copilot’s tail rotor pedals. The brakes have a visual brake puck wear indicator. Each wheel brake consists of two steel rotating discs, brake pucks, and a housing that contains the hydraulic pistons. The parking brake handle, marked PARKING BRAKE, is on the right side of the lower console. A hand-operated parking brake handle al-lows brakes to be locked by either pilot or copilot after brake pressure is applied. The parking brakes are applied by pressing the toe brake pedals, pulling the parking brake handle to its fully extended position, and then releasing the toe brakes while holding the handle out. An advisory will appear indicating PARKING BRAKE ON. Pressing either pilot or copilot left brake pedal will release the parking brakes, the handle will return to the off position

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2289232425

1. PITOT CUTTER

2. BACK HYDRAULIC PUMP

3. NO. 1 HYDRAULIC PUMP AND NO.1 GENERATOR

4. UPPER (ROTOR PYLON) CUTTER

5.

6. AFT MAINTENANCE LIGHT RECEPTACLE

7. TAIL LANDING GEAR DEFLECTOR

8.

9.

10. APU EXHAUST PORT

11. COOLING AIR INLET PORT

12. PNEUMATIC PORT

13. PRESSURE AND CLOSED CIRCUIT REFUELING PORTS

14. NO. 1 ENGINE

15. MAIN LANDING GEAR DEFLECTOR / CUTTER

16. LANDING GEAR JOINT DEFLECTOR

17. STEP AND EXTENSION DEFLECTOR

18. DOOR HINGE DEFLECTOR

19. RIGHT POSITION LIGHT (GREEN)

20. FIRE EXTINGUISHER BOTTLES

21. FORMATION LIGHTS

22. TAIL POSITION LIGHT (WHITE)

23. APU

24. LEFT POSITION LIGHT (RED)

25. PITOT TUBES

1 2 3 4

18 17 16 15 14 13 12 10 9 7

11 8

AA0403_1E

SA

Figure 2-1. General Arrangement (Sheet 1 of 4)

TM 1-1520-237-10

Change 5 2-3 troy.mercier Cross-Out troy.mercier Text Box troy.mercier Text Box troy.mercier Text Box troy.mercier Text Box troy.mercier Text Box troy.mercier Text Box troy.mercier Text Box troy.mercier Text Box troy.mercier Text Box troy.mercier Text Box

27 28 29 30

3233343536373839

26.

27.

28.

29.

30.

31.

32.

33.

34.

35.

36.

37.

UPPER ANTICOLLISION LIGHT

TAIL DRIVE SHAFT

NO. 2 HYDRAULIC PUMP AND NO. 2 GENERATOR

PYLON CUTTER

HEATER AIR INTAKE PORT

EXTERNAL ELECTRICAL POWER RECEPTACLE

NO. 2. ENGINE

ICE DETECTOR

AMBIENT SENSE PORT

ENGINE FAIRING / WORK PLATFORM (SAME BOTH SIDES)

CONDENSER EXHAUST / STEP

GRAVITY REFUELING PORT (SAME BOTH SIDES)

39.

40.

41.

42.

43.

44.

45.

46.

47.

48.

49.

AFT AVIONICS COMPARTMENT DOORS

IINS BLOWER INLET FILTER

TAIL PYLON FOLD HINGES

TAIL PYLON SERVICE LADDER (SAME BOTH SIDES)

STABILATOR

ENGINE BAY AREA COOLING AIR INTAKE (SAME BOTH SIDES)

WINDSHIELD POST DEFLECTOR

WINDSHIELD WIPER DEFLECTOR

AVIONICS COMPARTMENT

OAT SENSOR

ICE DETECTOR

PYLON COOLING AIR INTAKE

EH

EH

EH

38.

AA0403_2F

SA

Figure 2-1. General Arrangement (Sheet 2 of 4)

TM 1-1520-237-10

2-4 Change 5 troy.mercier Text Box

52655150

67 57 56 55 54

SA

AB5171_1

6252605958

64 63 54 52

51. CURRENT LIMITER

55. TERMINAL JUNCTION BOX ASSY

56. CREW SAFETY SWITCH

57. DIODE BLACK RAILS

59. SAFE/ARM SWITCH PANEL

60. TROOP COMMANDER ANTENNA

62. AN/ALE 47 SEQUENC

63. CONTROL INDICATOR (CI)

64. RELAY BOX

65. ELECTRONIC CONTROL UNIT (ECU)

CMWS

50. AUXILIARY CB PANEL

51. CURRENT LIMITER

52. ICMD FLARE DISPENSER

53. QUICK DISCONNECT BRACKET

55. TERMINAL JUNCTION BOX ASSY

56. CREW SAFETY SWITCH

57. DIODE BLACK RAILS

58. CAUTION ADVISORY PANEL LIGHT

59. SAFE/ARM SWITCH PANEL

60. TROOP COMMANDER ANTENNA

62. AN/ALE 47

63. CONTROL INDICATOR (CI)

64. RELAY BOX

65. ELECTRONIC CONTROL UNIT (ECU)

CMWS

Figure 2-1. General Arrangement (Sheet 3 of 4)

TM 1-1520-237-10

Change 5 2-4.1 troy.mercier Text Box troy.mercier Text Box troy.mercier Text Box troy.mercier Text Box troy.mercier Text Box troy.mercier Text Box troy.mercier Text Box troy.mercier Text Box troy.mercier Text Box troy.mercier Text Box troy.mercier Text Box troy.mercier Text Box troy.mercier Text Box troy.mercier Text Box troy.mercier Typewritten Text troy.mercier Typewritten Text troy.mercier Typewritten Text

BLANK

troy.mercier Typewritten Text

SA

AA0514B

TAIL ROTOR

DIAMETER

11 FEET12 FEET−

4 INCHES

9 FEET −

5 INCHES

MAIN ROTOR DIAMETER

53 FEET − 8 INCHES

7 FEET −

7 INCHES

1 FOOT −

7 INCHES

WHEEL BASE 29 FEET

LENGTH − ROTORS AND PYLON FOLDED 41 FEET − 4 INCHES

FUSELAGE LENGTH 50 FEET − 7.5 INCHES

OVERALL LENGTH 64 FEET − 10 INCHES

6 FEET −

6 INCHES

2.8 INCHES

FUSELAGE WIDTH

7 FEET − 9 INCHES

TREAD

8 FEET

10.6 INCHES

MAIN LANDING GEAR

9 FEET − 8.6 INCHES

STABILATOR WIDTH

14 FEET − 4 INCHES

8 FEET−

9 INCHES

20O

5 FEET

1 INCH

3 FEET

9.5 INCHES

WIDTH WITH ESSS AND EXTERNAL

EXTENDED RANGE TANKS INSTALLED

21 FEET

FUSELAGE WIDTH WITH

HOVER IR SUPPRESSORS

INSTALLED

9 FEET − 8 INCHES

Figure 2-2. Principle Dimensions

2-5

TURNING

RADIUS

41 FEET

7.7 INCHES

12 FEET

4 INCHES

9 FEET

5 INCHES

ROTOR

TURNING

7 FEET

7 INCHES

ROTOR

STATIONARY

12 FEET

1 INCH

11 FEET

4 INCHES WHEELBASE 29 FEET 12 FEET

5 INCHES

6 FEET

6 INCHES

16 FEET

10 INCHES

TAIL ROTOR IS CANTED 20O. UPPER

TIP PATH PLANE IS 16 FEET 10 INCHES

ABOVE GROUND LEVEL

SA

AA0402

Figure 2-3. Turning Radius and Clearance

2-6

AB0821_1

CHECK LIST

STOWAGE

DATA & M

AP

CHECK LIST

DATA & MAP

STOWAGE

1. UPPER CONSOLE

2. PILOT’S COCKPIT UTILITY LIGHT

3. FREE−AIR TEMPERATURE GAGE (ON

HELICOPTERS WITH HEATED CENTER

WINDSHIELD)

4. NO. 2 ENGINE FUEL SELECTOR LEVER

5. NO. 2 ENGINE OFF / FIRE T−HANDLE

6. NO. 2 ENGINE POWER CONTROL LEVER

7. WINDSHIELD WIPER

8. INSTRUMENT PANEL GLARE SHIELD

9. INSTRUMENT PANEL

10. VENT / DEFOGGER

11. ASHTRAY

12. PEDAL ADJUST LEVER

13. MAP / DATA CASE

15. CHAFF RELEASE SWITCH

16. PARKING BRAKE LEVER

17. FUEL BOOST PUMP PANEL

18. LOWER CONSOLE UTILITY LIGHT

20. NO. 1 ENGINE POWER CONTROL LEVER

21. NO. 1 ENGINE OFF / FIRE T−HANDLE

22. NO. 1 ENGINE FUEL SELECTOR LEVER

23. AC ESNTL BUS CIRCUIT BREAKER

PANEL

24. COPILOT’S COCKPIT UTILITY LIGHT

25. FREE−AIR TEMPERATURE GAGE (ON

HELICOPTERS WITHOUT HEATED

CENTER WINDSHIELD)

EH

EH

111618 14

19. STANDBY (MAGNETIC COMPASS)

14. CABIN DOME LIGHTS DIMMER

Figure 2-4. Cockpit Diagram (Sheet 1 of 2)

TM 1-1520-237-10

2-7

26 27

CHECK LIST

STOWAGE

DATA & M

AP

CHECK LIST

DATA & MAP

STOWAGE

26.

27.

28.

29.

30.

31.

32.

33.

34.

37384041424344

COCKPIT FLOODLIGHT CONTROL

UPPER CONSOLE

MASTER WARNING PANEL

SLIDING WINDOW

COCKPIT DOOR EMERGENCY RELEASE

CYCLIC STICK

DIRECTIONAL CONTROL PEDALS

PILOT’S SEAT

35.

36.

37.

38.

39.

40.

CREW CHIEF / GUNNER ICS CONTROL

PANEL

CREW CHIEF AMMUNITION / GRENADE

STOWAGE COMPARTMENT

STOWAGE BAG

COLLECTIVE STICK FRICTION CONTROL

COLLECTIVE STICK GRIP

ENGINE IGNITION KEYLOCK

LOWER CONSOLE

41.

42.

43.

44.

45.

46.

BATTERY / BATTERY UTILITY BUS

CIRCUIT BREAKER PANEL

FIRE EXTINGUISHER

GUNNER’S ICS CONTROL PANEL

FIRST AID KIT

GUNNER’S AMMUNITION / GRENADE

COPILOT’S SIDE LOWER CONSOLE

47. AUXILIARY FUEL MANAGEMENT PANEL

48. FORWARD COCKPIT AIRBAG

AB0821_2A

SA

Figure 2-4. Cockpit Diagram (Sheet 2 of 2)

2-8 Change 6

AA0323_1E

ON HELICOPTERS EQUIPPED WITH

AUXILIARY ELECTRICAL CABIN HEATER

GUST LOCK CONTROL

APU ACCUMULATOR

(LOOKING UP)

(LOCATED BELOW LEFT GUNNER’S WINDOW)

GUST LOCK

RELEASE

BUTTON

GUST LOCK

HANDLE

HEATER AIR

INLET PORT

50 85

CABIN DOME

LIGHTS (THREE)

TROOP COMMANDER’S

ANTENNA COAX

D E

B

ACCUMULATOR

PRESSURE GAGE

ACCUMULATOR

HAND PUMP

ACCUMULATOR

PISTON POSITION

INDICATOR

MANUAL

START

VALVE

ACCUMULATORB

HEATER TEMPERATURE

CONTROL

STA

349.50

STA

378.50

STA

332.50

A

REAR

TROOP COMMANDER’S ICS CONTROL

TROOP COMMANDER’S HANDSET

PUSH−TO−TALK

SWITCH

AUX NAV1 2 3 4 5

OFF

HOT MIKE

ON

OFF

ON

OFF

VOL

ICS

2 3

C O N T

C O M M

E

D

C

A

F

C

ON HELICOPTERS

EQUIPPED WITH

AUXILIARY ELECTRICAL

CABIN HEATER

G

G

Figure 2-5. Cabin Interior (Sheet 1 of 3)

2-9

APU DIGITAL ELECTRONIC SEQUENCE

RESET

START FUEL VALVE & EXCITER SIGNAL OUT (5%)

MAIN FUEL VALVE SIGNAL OUT (14%)

START FUEL VALVE & EXCITER SIGNAL OFF (70%)

90% RPM SWITCH ON

READY FOR SERVICE (90% + 1.5 SEC)

PROCESSOR BOARD FAILURE

SENSOR/DATA BOARD FAILURE

OVERTEMPERATURE

OVERSPEED

UNDERSPEED

FAIL TO START

LOW OIL PRESSURE

HIGH OIL TEMPERATURE (WARNING)

FAIL TO LIGHT (NO DATA)

SHORTED THERMOCOUPLE PROBE (WARNING)

OPEN THERMOCOUPLE

PROCESSOR SEQUENCE FAIL

NO DATA

OPERATION

START

SEQUENCE

1 2 3 4

BITE #

T−62T−40−1

DECODED BITE INFORMATION

FAULT INDICATION FAULTS

APU ELECTRONIC SEQUENCE UNIT FAULT INDICATION

RESET (START INITIATED)

FUEL VALVE AND IGNITION SIGNAL ON (5%)

START VALVE SIGNAL OFF (70%)

IGNITION SIGNAL OFF (95%)

READY FOR SERVICE (LOSS OF DC POWER)

A/C START SYSTEM FAILURE

OVERTEMPERATURE

OVERSPEED

UNDERSPEED

FAIL TO START

LOW OIL PRESSURE

HOT SENSOR FAILED

1 2 3 4

BITE # DECODED BITE INFORMATION

FAULT INDICATION FAULTS

GTC−P36−150

ESU FAILURE

OIL PRESSURE SWITCH FAILED

THERMOCOUPLE FAILED

MONOPOLE FAILED

FUEL SOLENOID FAILED

FUEL TORQUE MOTOR FAILED

IGNITION UNIT FAILED

NO DATA

OPERATION

START

SEQUENCE

(ON HELICOPTERS EQUIPPED WITH GTC−P36−150 APU)

1 2 3 4

BITE # DECODED BITE INFORMATION

OPERATION

POWER ON RESET

START COMMAND RECEIVED

START FUEL AND EXCITER ON

MAIN FUEL ON

START FUEL AND EXCITER OFF

90% RPM

READY TO LOAD

NORMAL OPERATION

DESU FAILURE

−SPARE−

OVERTEMPERATURE RUN

OVERSPEED

UNDERSPEED

FAIL TO ROTATE

LOW OIL PRESSURE

HIGH OIL TEMPERATURE

SHORTED OIL PRESSURE SW

T/C SHORTED

EICAS LINES FAULT

T/C OPEN CIRCUIT FAULT

LOSS OF SPEED DATA

−SPARE−

POWER INTERRUPT

RTL INDICATOR FAILURE

MALF INDICATOR FAILURE

MAX FUEL VALVE FAILURE

HOT INDICATOR FAILURE

MAIN FUEL VALVE FAILURE

ANTI−SURGE VALVE FAILURE

START CIRCUIT FAILURE

START FUEL/EXCITER FAILURE

ILLOGICAL SWITCH INPUTS

FAIL TO LIGHT

FAIL TO ACCEL (START FUEL)

FAIL TO ACCEL (START & MAIN)

FAIL TO ACCEL (MAIN FUEL)

SLOW ACCEL (TIME OUT)

OVERTEMPERATURE (START)

APU START SWITCH FAILURE

T−62T−40−1

SA

AA0323_2D

START

SEQUENCE

FAULTSFAULT INDICATION

APU ELECTRONIC SEQUENCE UNIT FAULT INDICATION

(ON HELICOPTERS EQUIPPED WITH T−62T−40−1 APU)

F

UNIT FAULT INDICATION

(ON HELICOPTERS EQUIPPED WITH T−62T−40−1 APU)

Figure 2-5. Cabin Interior (Sheet 2 of 3)

2-10 and the advisory will disappear. Power for the advisory comes from the No. 1 dc primary bus through a circuit breaker marked LIGHTS ADVSY.

2.10.3 Tail Landing Gear. The tail landing gear is

below the rear section of the tail cone. It has a two-stage oleo shock strut, tailwheel lock system fork assembly, yoke assembly, and a wheel and tire. The fork assembly is the attachment point for the tailwheel and allows the wheel to swivel 360°. The tailwheel can be locked in a trail position by a TAILWHEEL switch in the cockpit indicating LOCK or UNLK. The fork is locked by an electrical actuator through a bellcrank and locking pin.

When the pin is extended, the switch will indicate LOCK.

When the pin is retracted, the switch will indicate UNLK.

Power to operate the locking system is by the dc essential bus through a circuit breaker marked TAIL WHEEL

LOCK.

2.11 INSTRUMENT PANEL.

2.11.1 Instrument Panel. UH Engine and dual flight

instruments are on the one-piece instrument panel (Figure 2-9). The panel is tilted back 30°. The master warning panels are mounted on the upper instrument panel below the glare shield, to inform the pilot of conditions that require immediate action.

2.11.2 Instrument Panel. EH The instrument panel of

the EH-60A is as shown on Figure 2-9. Refer to Chapter 3 for description and operation of systems switch panels and Chapter 4 for BDHI, CREW CALL switch, FLARE switch an

2.11.3 Vertical Instrument Display System (VIDS).

The VIDS consists of a vertical strip central display unit (CDU), two vertical strip pilot display units (PDU), and two signal data converters (SDC). Those readings are shown by ascending and descending columns of multicolored lights (red, yellow, and green) measured against vertical scales which operate in this manner: the segments will light in normal progression and remain on as the received signal level increases. Those scales will go off in normal progression as the received signal level decreases. Scales with red-coded and/or amber-coded seg-ments below green-coded segments operate in this manner:

when the received signal level is zero or bottom scale, the segments will light in normal progression and will remain

on. When the first segment above the red or amber range

FLOW CONTROL

ROTATE

G

MEDIUMLOW HIGH

OPTION II CABIN HEATER EJECTOR

SA

AA0323_3

Figure 2-5. Cabin Interior (Sheet 3 of 3)

TM 1-1520-237-10

Change 4 2-11 goes on, all red-coded or amber-coded segments will go off. These segments will remain off until the received signal level indicates a reading at or within the red or amber range. At that time all red-coded or amber-coded segments will go on and the scale display will either go on or go off in normal progression, depending upon the received signal level. The CDU and PDUs contain photocells that automatically adjust lighting of the indica-tors with respect to ambient light. If any one of the three photocells should fail, the lights on the vertical scales of the PDUs or CDU may not be at the optimum brightness for the ambient conditions. The DIM knob on the CDU contains an override capability which allows the pilot to manually set the display light level. The SDCs receive parameter data from the No. 1 and No. 2 engines, trans-mission, and fuel system; provide processing and transmit the resulting signal data to the instrument display. The No.

1 engine instruments on the CDU and copilot’s PDU, receive signal data from the No. 1 SDC (CHAN 1). The No. 2 engine and main transmission instruments on the CDU and pilot’s PDU receive signal data from the No. 2 SDC (CHAN 2). If either SDC fails, the corresponding CHAN 1 or 2 light will go on, and it is likely the pilot’s or copilot’s PDU and the corresponding instruments will fail.

Failure of a lamp power supply within an SDC will cause every second display light on the CDU to go off. When a lamp power supply has failed with the improved CDU, the pilot’s PDU will not light, but the

SA

AA0401

PILOT ECM CONSOLE ECM OPERATOR SEAT ECM EQUIPMENT RACK MISSION INTERFACE PANEL

COPILOT DF CONSOLE DF OPERATOR SEAT OBSERVER SEAT DF EQUIPMENT RACK

Figure 2-6. Cabin Mission Equipment Arrangement EH

TM 1-1520-237-10

2-12 Change 5 improved CDU will continue to function; the alternate vertical scale lamps will not be off. Both SDCs receive %

RPM R; and % RPM 1 and 2 and % TRQ information from both engines.

WOW SWITCH FUNCTION ON GROUND IN FLIGHT

Backup Pump Automatic Operation Disabled (Except when APU accumulator is low)

Enabled

Hydraulic Leak Test System Enabled Disabled

Backup Pump Thermal Switch Enabled Disabled

Low % RPM R Audio Warning Disabled Enabled

SAS/FPS Computer Degraded Enabled

Generator Underfrequency Protection Enabled Disabled

IFF Mode 4 Operation Disabled Automatic Zeroize Enabled Automatic Zeroize

External Stores Jettison Disabled Enabled

CMWS CMWS Ground Safe Enabled Disabled

A2C2S AIP AC Essential Bus Isolate Enabled Disabled

Table 2-1. Weight-On-Wheels (WOW) Functions

TM 1-1520-237-10

Change 6 2-12.1/(2-12.2 Blank) troy.mercier Text Box

BLANK

troy.mercier Typewritten Text troy.mercier Typewritten Text troy.mercier Typewritten Text troy.mercier Typewritten Text troy.mercier Typewritten Text

Therefore if one SDC fails only one PDU will provide % RPM 1 and 2 and % TRQ for both engines.

2.11.4 Central Display Unit. The CDU contains

instruments that display fuel quantity, transmission oil temperature and pressure, engine oil temperature and pres-sure, turbine gas temperature (TGT), and gas generator speed (Ng) readings. Those readings are shown by ascending and descending columns of multicolored lights (red, yellow, and green) measured against vertical scales.

If the instrument contains low range turnoff (red or yellow lights below green lights) they will go off when the system is operating within the normal range (green). If the instru-ment contains yellow or red lights above the green range, the green as well as the yellow or red will stay on when operating above the green range. The operating ranges for the different instruments are shown in Figures 5-1 and 5-2.

Digital readouts are also installed on the TOTAL FUEL quantity, TGT, and Ng gages.

2.11.4.1 Lamp Test System. The lamp test provides a

means of electrically checking all CDU scale lamps, digital readouts, and % RPM RTR OVERSPEED lights on the PDUs. When the PUSH TO TEST switch on the CDU is pressed, all CDU scale lamps should light, digital readouts should display 888, and three RTR OVER- SPEED lights on the PDUs should be on.

2.11.4.2 Dim Control. The DIM control allows the

pilot to set a desired display light level of the CDU and PDUs in accordance with the ambient light, or override the auto-dim sensors. If the auto-dim circuitry should fail or malfunction, turn the DIM control fully clockwise to regain illumination of the CDU and PDUs.

2.11.4.3 CDU and PDU Digital Control. An ON, OFF DIGITS control switch is on the CDU to turn on or off the digital readout displays on the CDU and PDUs. If a digital processor fails, all digital displays will go off.

2.11.5 Pilot’s Display Unit. The PDU displays to the

pilot engine power turbine speed (% RPM 1 and 2), rotor speed (% RPM R), and torque (% TRQ). Readings are shown by ascending and descending columns of multicolored lights (red, yellow, and green) measured against vertical scales.