TM 1-1520-237-10

the illustration or a MAJOR CHANGE symbol. Dates of issue for original and change pages are: Original . . . . . . . . . . . . . . . . . . . . . . . . . . 25 September 2009 Total number of pages in this manual is 892 consisting of the following: Page No. *Change No. Title....................... 0 Blank..................... 0 a - b...................... 0 A .......................... 0 B Blank.................. 0 i - v ....................... 0 vi Blank ................. 0 1-1 - 1-2 ............... 0 Page No. *Change No. 2-1 - 2-117 ........... 0 2-118 Blank .......... 0 3-1 - 3-151 ........... 0 3-152 Blank .......... 0 4-1 - 4-88 ............. 0 5-1 - 5-24 ............. 0 6-1 - 6-30 ............. 0 7-1 - 7-166 ........... 0 Page No. *Change No. 7A-1 - 7A-194 ...... 0 8-1 - 8-27 ............. 0 8-28 Blank ............ 0 9-1 - 9-28 ............. 0 A-1 - A-2 .............. 0 B-1 - B-5 ............... 0 B-6 Blank............... 0 Index-1 - Index-42 . 0 TM 1-1520-237-10 LIST OF EFFECTIVE PAGES * Zero in this column indicates an original page. A/(B Blank) Operator’s Manual for UH-60A, UH-60L, EH-60A HELICOPTERS REPORTING ERRORS AND RECOMMENDING IMPROVEMENTS 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-MMC-MA-NP, 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. WARNING - This document contains technical data whose export is restricted by the Arms Export Control Act (Title 22, U.S.C. Sec. 2751 et seq.) or the Export Administration Act of 1979, as amended, Title 50, U.S.C., App. 2401 et seq. Violation of these export laws are subject to severe criminal penalties. Disseminate in accordance with provisions of DoD Directive 5230.25. DISTRIBUTION STATEMENT D. Distribution authorized to the DOD and DOD contractors only due to Critical Technology effective as of 15 June 2003. Other requests must be referred to Commander, US Army Aviation and Missile Command, ATTN: SFAE-AV-UH/L, Redstone Arsenal, AL 35898-5000. DESTRUCTION NOTICE - Destroy by any method that will prevent disclosure of contents or reconstruction of the document. TABLE OF CONTENTS Chapter & Section Page CHAPTER 1 INTRODUCTION ......................................................................................... 1-1 CHAPTER 2 AIRCRAFT AND SYSTEMS DESCRIPTION AND OPERATION .......... 2-1 Section I Aircraft........................................................................................................... 2-1 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 TM 1-1520-237-10 TECHNICAL MANUAL HEADQUARTERS DEPARTMENT OF THE ARMY NO. 1-1520-237-10 WASHINGTON, D.C. 25 SEPTEMBER 2009 *This manual supersedes TM 1-1520-237-10, dated 17 April 2006, including all changes. i TABLE OF CONTENTS (Cont) Chapter & Section Page CHAPTER 2 AIRCRAFT AND SYSTEMS DESCRIPTION AND OPERATION .......... 2-1 Section I Aircraft........................................................................................................... 2-1 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 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 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 CHAPTER 3 AVIONICS .................................................................................................... 3-1 Section I General........................................................................................................... 3-1 Section II Communications ............................................................................................ 3-8 Section III Navigation...................................................................................................... 3-43 Section IV Transponder and Radar.................................................................................. 3-137 TM 1-1520-237-10 ii TABLE OF CONTENTS (Cont) Chapter & Section Page CHAPTER 4 MISSION EQUIPMENT............................................................................... 4-1 Section I Mission Avionics ........................................................................................... 4-1 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 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 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 ........................................................................................ 6-13 TM 1-1520-237-10 iii TABLE OF CONTENTS (Cont) Chapter & Section Page Section VI Cargo Loading ............................................................................................... 6-19 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 ........................................................................ 7-159 CHAPTER 7A PERFORMANCE DATA 701C 701D/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 TM 1-1520-237-10 iv TABLE OF CONTENTS (Cont) Chapter & Section Page Section VIII Fuel Flow ....................................................................................................... 7A-181 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 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 ........................................................................................ 9-24 APPENDIX A REFERENCES .............................................................................................. A-1 APPENDIX B ABBREVIATIONS AND TERMS ............................................................... B-1 INDEX INDEX ........................................................................................................... INDEX-1 TM 1-1520-237-10 v/(vi Blank) CHAPTER 1 INTRODUCTION 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: WARNING An operating procedure, practice, etc., which, if not correctly followed, could result in personal injury or loss of life. CAUTION An operating procedure, practice, etc., which, if not strictly observed, could result in damage to or destruction of equipment. NOTE An operating procedure, condition, etc., which is essential to highlight. 1.3 DESCRIPTION. 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 capabilities 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. 1.4 APPENDIX A, REFERENCES. 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 APPENDIX B, ABBREVIATIONS AND TERMS. Abbreviations listed are to be used to clarify the text in this manual only. Do not use them as standard abbrevia- tions. 1.6 INDEX. 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 ARMY AVIATION SAFETY PROGRAM. Reports necessary to comply with the safety program are prescribed in AR 385-10. 1.8 DESTRUCTION OF ARMY MATERIEL TO PREVENT ENEMY USE. For information concerning destruction of Army materiel to prevent enemy use, refer to TM 750-244-1-5. 1.9 FORMS AND RECORDS. 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. TM 1-1520-237-10 1-1 1.10 EXPLANATION OF CHANGE SYMBOLS. 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 MAJOR 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 SERIES AND EFFECTIVITY CODES. 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 configuration 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 UH UH-60A and UH-60L peculiar information. UH−60A UH-60A peculiar informa- tion. H−60A+ UH-60A equipped with T700-GE-701D/CC engines (701D core with 701C hy- dromechanical unit and digital electronic unit) and UH-60L CDU. UH−60L UH-60L peculiar informa- tion. DESIGNATOR SYMBOL APPLICATION EH EH-60A peculiar informa- tion. 700 Helicopters equipped with T700-GE-700 engines. 701C 701D/CC Helicopters equipped with T700-GE-701C engines or T700-GE-701D/CC engines (701D core with 701C hy- dromechanical unit and digital electronic unit). ERFS Helicopters with Extended Range Fuel System. AFMS Helicopters with Auxiliary Fuel Management System. CEFS Helicopters with Crashwor- thy External Fuel System. AHRS Helicopters equipped with Attitude Heading Reference Set. 128D Helicopters equipped with Doppler/GPS Navigation Set (DGNS) AN/ASN-128D. 1.12 HIGH DRAG SYMBOL. This symbol will be used throughout this manual to designate information applicable to the high drag configuration described in Chapters 7 and 7A. 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. TM 1-1520-237-10 1-2 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. TM 1-1520-237-10 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 communication 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 l a n d i n g s o n s l o p e s i n a n y d i r e c t i o n . T h e s y s t e m 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. See Table 2-1 for refer- ence. 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 TM 1-1520-237-10 2-2 SA AA0403_1B 19 5 20 21 21 22 8 9 23 24 25 1. PITOT CUTTER 2. BACK HYDRAULIC PUMP 3. NO. 1 HYDRAULIC PUMP AND NO.1 GENERATOR 4. UPPER (ROTOR PYLON) CUTTER 5. INFRARED COUNTERMEASURE TRANSMITTER 6. AFT MAINTENANCE LIGHT RECEPTACLE 7. TAIL LANDING GEAR DEFLECTOR 8. FLARE DISPENSER 9. CHAFF DIPENSER 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 ON HELICOPTERS EQUIPPED WITH WIRE STRIKE PROTECTION SYSTEM EH EH 1 2 3 4 5 18 17 16 15 14 13 12 10 9 8 7 6 11 Figure 2-1. General Arrangement (Sheet 1 of 2) TM 1-1520-237-10 2-3 SA AA0403_2C 27 28 29 30 31 32 33 34 35 36 37 38 39 40 41 42 26 43 44 45 46 47 45 44 48 49 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 ON HELICOPTERS EQUIPPED WITH WIRE STRIKE PROTECTION SYSTEM EH EH EH 26 38. Figure 2-1. General Arrangement (Sheet 2 of 2) TM 1-1520-237-10 2-4 SA AA0514B TAIL ROTOR DIAMETER 11 FEET 12 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 20 O 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 TM 1-1520-237-10 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 20 O . UPPER TIP PATH PLANE IS 16 FEET 10 INCHES ABOVE GROUND LEVEL * SA AA0402 Figure 2-3. Turning Radius and Clearance TM 1-1520-237-10 2-6 SA AB0821_1 25 24 CHECK LIST STOWAGE DATA & MAP 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 23 3 22 21 20 7 19 12 10 11 13 1 2 3 6 4 5 7 8 9 10 11 12 13 17 15 11 16 18 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 28 30 33 34 35 36 29 32 31 26 27 CHECK LIST STOWAGE DATA & MAP CHECK LIST DATA & MAP STOWAGE 26. 27. 28. 29. 30. 31. 32. 33. 34. 28 29 30 31 32 46 38 45 37 38 40 41 42 43 44 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 SA AB0821_2 39 47 47. AUXILIARY FUEL MANAGEMENT PANEL AFMS 48 48 48. FORWARD COCKPIT AIRBAG Figure 2-4. Cockpit Diagram (Sheet 2 of 2) TM 1-1520-237-10 2-8 SA 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 67 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 ACCUMULATOR B 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 NAV 1 2 3 4 5 OFF HOT MIKE ON OFF ON OFF VOL ICS 1 2 3 4 5 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) TM 1-1520-237-10 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 5 T−62T−40−1 SA AA0323_2D START SEQUENCE FAULTS FAULT 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) TM 1-1520-237-10 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 and ECM ANTENNA switch and countermeasure set ALQ-156. 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 s h o w n b y a s c e n d i n g a n d d e s c e n d i n g c o l u m n s o f 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 MEDIUM LOW HIGH OPTION II CABIN HEATER EJECTOR SA AA0323_3 Figure 2-5. Cabin Interior (Sheet 3 of 3) TM 1-1520-237-10 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; provides processing and transmits the resulting signal data to the instrument dis- play. 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, receives 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. Both SDCs receive % RPM R; and % RPM 1 and 2 and % TRQ information from both engines. 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 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 s h o w n b y a s c e n d i n g a n d d e s c e n d i n g c o l u m n s o f multicolored lights (red, yellow, and green) measured against vertical scales. A TEST switch provides a means of electrically checking all PDU scale lamps and digital readouts. When the TEST switch is pressed, all PDU scale lamps should light and digital readouts should display 188. The % RPM indicators contain low range turnoff below the normal operating range. Three overspeed lights at the top will go on from left to right when a corresponding ro- tor speed of 127%, 137%, and 142% is reached. Once a light is turned on, a latch prevents it from going off until reset by maintenance. Power for the PDUs is from No. 1 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 ERFS AUX FUEL INCR/DECR Switch Enabled Disabled AFMS 5 minute delay before continuous BIT (CBIT) monitors attitude sensor after AFMP power up Enabled Disabled AFMS AFMP Power up BIT (PBIT) and Initiated BIT (IBIT) Enabled Disabled Table 2-1. Weight-On-Wheels (WOW) Functions TM 1-1520-237-10 2-13 NO.2 ENG SENSE SPLY 5 5 10 ESNTL DC BATT BUS FIRE DET CONTR SRCH 20 5 5 DC ESNTL BUS LIGHTS SEC PNL PWR CONTR CONSOLE LT LOWER PILOT FLT INSTR LT WINDSHIELD ANTI−ICE COPILOT PITOT HEAT BLOWER BRT OFF BRT OFF ON ON ON CTR O F F O O F F SA AA0364_1C A MAIN TEST SHORT SAFE ARMED CKPT NORM EMERG REL CONTR ARMING RESET TEST TEST TEST ON EXT PWR BATT APU NO. 1 NO. 2 GENERATORS TEST A TEST B OPER TEST A TEST B NO. 1 ENG OVSP NO. 2 ENG OVSP FIRE DETR TEST 1 2 AIR SOURCE HEAT / START FUEL PUMP APU BOOST FUEL PRIME APU ENGINE APU ON ON ON ON CARGO HOOK ALL APU CONTR FIRE EXTGH ON FIRE EXTGH RESERVE O F F O F F O F F O F F O F F O F F R E S E T O F F R E S E T O F F R E S E T O P E N OFF PNL CONTR FUEL DUMP NO. 1 VOR / ILS CHIP DC ESNTL BUS 2 5 2 5 2 5 5 2 2 5 7.5 5 ICS ESSS JTSN PILOT COPILOT VHF FM DET CONTR OUTBD COMM SCTY SET NO. 1 FM UHF AM UHF AM CAUT / ADVSY BACKUP HYD HOIST CABLE * ESSS JTSN SHEAR INBD * NO.1 ENG 5 5 5 5 5 7.5 STAB CARGO HOOK PWR EMER SAS NO. 1 ENG TAIL WHEEL BOOST START LOCK PARK OFF LOW HI UPPER NON FLT NO. 1 NO. 2 ENG ANTI−ICE ON WINDSHIELD WIPER VENT BRT OFF BRT OFF ON ON O F F O F F O F F F F 28V #387 SPARE LAMPS OPEN 7.5 7.5 FORMATION LT POSITION LIGHTS STEADY ANTICOLLISION LIGHTS LOWER NIGHT DAY DIM BRT FLASH UPPER CABIN DOME LT WHITE BLUE HYD LEAK TEST BACKUP HYD PUMP RESET TEST ON OFF CARGO HOOK LT ON NAV LTS IR LIGHTED SWITCHES BRT OFF GLARESHIELD LIGHTS BRT OFF CPLT FLT INST LTS BRT OFF 5 4 3 2 1 OFF O F F O F F O F F O F F N O R M N O R M B O T H A U T O BLUE WHITE O F F TYPICAL O F F MED OFF HI ON HEATER B C ON O F F PILOT W AHRS Figure 2-7. Upper Console (Sheet 1 of 3) TM 1-1520-237-10 2-14 SA AA0364_2C (ON HELICOPTERS EQUIPPED WITHOUT HEATED CENTER WINDSHIELD) B MED OFF HI FWD HEATER O F F FWD/AFT A (ON HELICOPTERS EQUIPPED WITH OPTION II CABIN HEATER SYSTEM) NO.1 NO.2 DETR ENG ENG SENSE SPLY 5 2 5 5 5 10 ESNTL BUS BATT BUS FIRE DET CONTR SRCH 5 5 20 5 5 5 DC ESNTL BUS LIGHTS 7.5 STAB CARGO HOOK PILOT TURN PWR EMER SAS NO. 1 ENG TAIL WHEEL SEC BOOST START LOCK PNL PWR CONTR C ANTI−ICE COPILOT PITOT HEAT ON ON O F F O F F ON O F F PILOT WINDSHIELD W/O AHRS Figure 2-7. Upper Console (Sheet 2 of 3) TM 1-1520-237-10 2-15 SA AA0364_3 MAIN RESET TEST TEST TEST ON EXT PWR BATT APU NO. 1 NO. 2 GENERATORS TEST A TEST B OPER TEST A TEST B NO. 1 ENG OVSP NO. 2 ENG OVSP FIRE DETR TEST 1 2 AIR SOURCE HEAT / START FUEL PUMP APU BOOST FUEL PRIME APU ENGINE APU ON ON ON ON APU CONTR FIRE EXTGH ON FIRE EXTGH RESERVE O F F O F F O F F O F F O F F O F F R E S E T O F F R E S E T O F F R E S E T OFF 28V #387 SPARE LAMPS OPEN FORMATION LT POSITION LIGHTS STEADY ANTICOLLISION LIGHTS LOWER NIGHT DAY DIM BRT FLASH UPPER CABIN DOME LT WHITE BLUE HYD LEAK TEST BACKUP HYD PUMP RESET TEST ON OFF CARGO HOOK LT ON NAV LTS IR LIGHTED SWITCHES BRT OFF GLARESHIELD LIGHTS BRT OFF CPLT FLT INST LTS BRT OFF 5 4 3 2 1 OFF O F F O F F O F F O F F N O R M N O R M B O T H A U T O BLUE WHITE O F F PNL CONTR NO. 1 VOR / ILS CHIP DC ESNTL BUS 2 5 2 5 2 5 2 2 5 ICS ESSS JTSN PILOT COPILOT VHF FM DET OUTBD COMM SCTY SET NO. 1 FM UHF AM UHF AM CAUT / ADVSY BACKUP HYD ESSS JTSN INBD 7.5 7.5 7.5 DC ESNTL BUS NO.1 NO.2 RATE ENG ENG SENSE SPLY 2 5 5 5 10 ESNTL DC BATT BUS FIRE DET CONTR SRCH 5 5 20 5 5 5 LIGHTS STAB PILOT TURN PWR SAS NO. 1 ENG TAIL WHEEL SEC BOOST START LOCK PNL PWR CONTR 7.5 MED PARK OFF LOW HI CONSOLE LT UPPER LOWER OFF HI NON FLT PILOT FLT INST LT NO. 1 NO. 2 ENG ANTI−ICE WINDSHIELD COPILOT ANTI−ICE CTR ON WINDSHIELD WIPER PITOT HEAT VENT BLOWER BRT OFF BRT OFF BRT OFF BRT OFF ON ON ON ON ON ON ON PILOT HEATER O F F O F F O F F O F F O F F O F F O F F O F F FAN PWR ON HTR COOL TEMP CONT Q / F ECS ON AIR COND COOL WARM O F F O F F O F F EH Figure 2-7. Upper Console (Sheet 3 of 3) TM 1-1520-237-10 2-16 STORES JETTISON EMER JETT ALL JETT INBD OUTBD BOTH BOTH R R L L OFF ALL ON OFF ON OFF VOL ICS 1 2 4 3 5 HOT MIKE OFF C O M M 1 2 3 4 5 AUX NAV C O N T MB VOL OFF TEST HI LO TAIL WHEEL GYRO ERECT TAIL SERVO NORMAL BACKUP M I S C S W FUEL BOOST PUMP CONTROL ON OFF NO. 1 PUMP NO. 2 PUMP ON OFF TEST CHAN 1 3 0 0 0 00 MAIN VOL PRESET GUARD MANUAL BOTH OFF ADF TONE SQUELCH OFF ON U H F ON OFF ON OFF VOL ICS 1 2 4 3 5 HOT MIKE OFF C O M M 1 2 3 4 5 AUX NAV C O N T PLAIN C / RAD MODE DELAY ON POWER OP LD RV 1 2 3 4 5 6 Z E R O I Z E KY 58 R C U FILL 1 2 3 5 4 6 P R E S S T O T E S T D I M P R E S S T O T E S T D I M TEST TEST/MON TOP BOT MASTER TEST OUT STATUS IDENT MIC TEST AUDIO P R E S S T O T E S T D I M REPLY CODE M−1 M−2 M−3 / A M−C A N T D I V O N O N L I G H T O U T MODE 1 MODE 3 / A N O G O E M E R N O R M S T B Y OF F ALT KIT ANT 0 0 1 2 0 0 A B MODE 4 O N G O FM 1 / FM 2 FM 2 / UHF FM 2 / VHF FM 1 / VHF FM 1 / UHF VHF / UHF OFF OUT MAN SLEW UP DN TEST AUTO CONTROL ON ON ON ON ON ON STABILATOR CONTROL SAS 1 SAS 2 TRIM FPS AUTO FLIGHT CONTROL BOOST R E S E T O F F R E S E T R E S E T POWER ON RESET CPTR TRIM SAS 2 RGYR ACCL A / S CLTV GYRO FAILURE ADVISORY Z ER O H O L D RAD TEST FUEL IND F I F RADIO RETRANSMISSION PLAIN C / RAD MODE DELAY ON POWER OP LD RV 1 2 3 4 5 6 Z E R O I Z E KY 58 R C U FILL 1 2 3 5 4 6 1 2 3 FREQ 4 5 6 7 8 9 TIME CLR Sto ENT H−Ld 0 L L E ERF OFST MAN 1 2 3 4 5 6 CUE PRESET TEST SQ ON SQ OFF LD LD−V Z−A STOW FUNCTION RXMT OFF OFF LO NORM HI IFM RF PWR MODE HOM SC FH FH−M VOL 9 14 1 0 50 FM AM MAN PRE DF TR OFF V O L S Q D I S T O N E EMER LOAD PRESET C O M M PLAIN C / RAD MODE DELAY ON POWER OP LD RV 1 2 3 4 5 6 Z E R O I Z E KY 58 R C U FILL 1 2 3 5 4 6 1 2 3 FREQ 4 5 6 7 8 9 TIME CLR Sto ENT H−Ld 0 L L E ERF OFST MAN 1 2 3 4 5 6 CUE PRESET TEST SQ ON SQ OFF LD LD−V Z−A STOW FUNCTION RXMT OFF OFF LO NORM HI IFM RF PWR MODE HOM SC FH FH−M VOL CURSOR VALUE T / R SILENT STBY OFF ZERO (PULL) VOL SQL PRE MAN ALE ECCM EMER 1 2 3 4 5 6 KEY DATA DSPL OFF BRT PNL OFF INIT FILL CIK AUDIO KY− 100 OFL EB RK CT PT MODE PRESET Z ALL (PULL) 1 2 3 4 6 REM MAN PWR OFF BAT 1 2 3 4 6 5 U PARKING BRAKE BATT & ESNTL DC WARN DC AC & ESNTL BUS FUEL PRIME BATT BUS FIRE SPLY CONV WARN EXT PWR CONTR BOOST CONTR EXTGH APU UTIL LTS APU CONTR INST CONTR INST FIRE DET GEN CONTR CKPT B A T T U T I L B U S B A T T B U S 50 5 5 5 5 5 5 5 5 5 5 0 0 0 0 FLARE CHAFF DISP CONT ARM MAN PGRM R I P P L E F I R E SAFE OFF ARM P R E S S T O T E S T D IM LTR LEFT LTR MID LTR RIGHT ABC 1 DEF 2 GHI 3 JKL 4 MNO 5 PQR 6 GPS LDG LAT / LONG MGRS TEST LAMP TEST OFF XTK/TKC KEY GS/TK NAV M PP DIST / BRG TIME WIND−UTC DATA WP TGT DATUM ROUTE DISPLAY N A V MODE P / P R STU 7 VWX 8 YZ* 9 CLR # 0 ENT (PAGE) KYBD F1 TGT STR INC (+) DEC (−) MAL BRT DIM 1 7 : B ANDO 0 3 0MG 9 1 GP S : M N A V : C GS : 1 1 7KM / HR TK : 0 2 5 " FLY TO EPE SYS STAT TGT STR G S D L B SA AA0385_1J CABS 2 ALT/P/R PGM INC SEL DEC NXT ADJ OFF ON BIT ACK DCLT 1−4 P−PGM CP−PGM OP BRT D / U DIM L / R CPLT DSPL POS MODE + MODE FAIL ON D / U L / R BRT DIM DSPL POS PLT 1−4 DCLT CHAFF DISPENSE GPS ZEROIZE + PWR SELF DSCRM ON OFF ON OFF AUDIO TEST 2 MAN 2182 500 A D F TEST TONE VOL TAKE CMD ADF ANT OFF 0 0 0 .0 DTM OR 12 PT BLANK OR TACAN OR 12 PT A H R S ALN FAIL SLAVE CCAL FUNC MODE ENT DG NAV VOL MB ON N V A C A Figure 2-8. Lower Console (Sheet 1 of 3) UH TM 1-1520-237-10 2-17 SA AA0385_2E NAV VOL MB VOL OFF VOR / MB TEST OFF MB SENS HI LO 108.00 C AUDIO KILOCYCLES CW TEST VOICE LOOP T U N E A D F R C V R OFF LOOP COMP ANT 2 9 80 90 L R B A COMPASS SLAVED FREE PUSH TO SET + + W/O AHRS Figure 2-8. Lower Console (Sheet 2 of 3) UH TM 1-1520-237-10 2-18 SA AA1304_2C AUDIO KILOCYCLES CW TEST VOICE LOOP T U N E A D F R C V R OFF LOOP COMP ANT 2 9 80 90 L R ON OFF ON OFF VOL ICS 1 2 4 3 5 HOT MIKE OFF C O M M NAV VOL MB VOL OFF 108 00 VOR / MB TEST OFF MB SENS HI LO TAIL WHEEL GYRO ERECT TAIL SERVO NORMAL BACKUP M I S C S W 9 14 1 0 50 FM AM MAN PRE DF TR OFF V O L S Q D I S T O N E EMER LOAD PRESET C O M M P R E S S T O T E S T D I M P R E S S T O T E S T D I M TEST TEST/MON TOP BOT MASTER TEST OUT STATUS IDENT MIC TEST AUDIO OUT P R E S S T O T E S T D I M REPLY CODE M−1 M−2 M−3/A M−C RAD TEST A N T D I V I F F O N O N L I G H T O U T MODE 1 MODE 3 / A N O G O E M E R N O R M S T B Y O F F ALT KIT ANT 0 0 1 2 0 0 MODE 4 O N G O 1 2 3 4 5 AUX NAV C O N T FM 1 / FM 2 FM 2 / UHF FM 2 / VHF FM 1 / VHF FM 1 / UHF VHF / UHF OFF COMPASS SLAVED FREE PUSH TO SET + 0 0 + CHAN 1 3 0 0 0 00 MAIN VOL PRESET GUARD MANUAL BOTH OFF ADF TONE SQUELCH OFF ON U H F ON OFF ON OFF VOL ICS 1 2 4 3 5 HOT MIKE OFF C O M M 1 2 3 4 5 AUX NAV C O N T 3 0 6 0 FLARE ARM CHAFF DISP CONT ARM MAN PGRM R I P P L E F I R E + PWR SELF DSCRM ON OFF ON OFF AUDIO TEST CHAFF DISPENSE SAFE FUEL IND OUT FUEL BOOST PUMP CONTROL ON OFF NO. 1 PUMP NO. 2 PUMP ON OFF MAN SLEW UP DN TEST AUTO CONTROL ON ON ON ON ON ON STABILATOR CONTROL SAS 1 SAS 2 TRIM FPS AUTO FLIGHT CONTROL BOOST R E S E T O F F R E S E T R E S E T POWER ON RESET CPTR TRIM SAS 2 RGYR ACCL A / S CLTV GYRO DEF ABC GHJ KLM NPQ RST UVW XYZ LTR W4 1 5 E6 3 M2 USE 0 CLR FACK BRT MRK STR BIT DEST 7 S8 9 I I N S DEST INS POS STR TCN UPDT NAV NORM FAST OFF TEST CAL ATTD _ PARKING BRAKE AN/ARC−201 AN/ALQ−162 COVER FAILURE ADVISORY P R E S S T O T E S T D IM A B Z ER O H O L D RADIO RETRANSMISSION TEST ALQ 162 NO GO CW THRT CW JAM ALQ−156 CM JAM ALQ−144 IRCM INOP CM INOP PLAIN C / RAD MODE DELAY ON POWER OP LD RV 1 2 3 4 5 6 Z E R O I Z E KY 58 R C U FILL 1 2 3 5 4 6 PLAIN C / RAD MODE DELAY ON POWER OP LD RV 1 2 3 4 5 6 Z E R O I Z E KY 58 R C U FILL 1 2 3 5 4 6 VHF−FM NO. 1 IFM CONTROL AN/ARC−201 PLAIN C / RAD MODE DELAY ON POWER OP LD RV 1 2 3 4 5 6 Z E R O I Z E KY 58 R C U FILL 1 2 3 5 4 6 VHF−FM NO. 2 BATT & ESNTL DC WARN DC AC & ESNTL BUS FUEL PRIME BATT BUS FIRE SPLY CONV WARN EXT PWR CONTR BOOST CONTR EXTGH APU UTIL LTS APU CONTR INST CONTR INST FIRE DET GEN CONTR CKPT B A T T U T I L B U S B A T T B U S 50 5 5 5 5 5 5 5 5 5 5 CABS 2 COVER Figure 2-8. Lower Console (Sheet 3 of 3) EH TM 1-1520-237-10 2-19 and No. 2 ac and dc primary buses through circuit breakers marked NO. 1 AC INST/NO. 1 DC INST and NO. 2 AC INST/NO. 2 DC INST, respectively. Refer to Figures 5-1 and 5-2 for instrument markings. 2.12 DOORS AND WINDOWS. 2.12.1 Cockpit Doors. The crew compartment is reached through two doors, one on each side of the cockpit. The doors swing outward and are hinged on the forward side. Each door has a window for ventilation. In- stalled on the back of each door is a latch handle to allow unlatching the door from either inside or outside the cockpit. Emergency release handles are on the inside frame of each door (Figure 9-1). They allow the cockpit doors to be jettisoned in case of an emergency. There is an emergency release pull tab on the inside forward portion of each cockpit door window for pilot egress. Data compart- ments are on each cockpit door. 2.12.2 Troop/Cargo (Cabin) Doors. Aft sliding doors are on each side of the troop/cargo compartment. Single- action door latches allow the doors to be latched in the fully open or fully closed positions. Each of the two doors incorporate two jettisonable windows, for emergency exit (Figure 9-1). 2.12.3 Crew Chief/Gunner Windows. The Crew Chief/Gunner Stations have forward sliding hatch windows, split vertically into two panels. A spring-loaded security latch is installed on each gunner’s aft window, to prevent the window opening from the outside. The dead bolt lock requires activation of the security latch lever from inside the helicopter. Another window latch bar is actuated to allow the forward window to be moved to a stowed position. The windows may be opened to move a machine gun into position for firing. 2.12.4 Door Locks. Key door locks are installed on each of the cabin, cockpit and avionics compartment doors. A common key is used to lock and unlock the doors from the outside to secure the helicopter. Each crew chief/ gunner sliding window is locked from the inside only. 2.13 CREW SEATS. 2.13.1 Pilots’ Seats. WARNING Do not store any items below seats. Seats stroke downward during a crash and any obstruction will increase the probability and severity of injury. The pilots’ seats provide ballistic protection and can be adjusted for the pilots’ leg length and height. The pilot’s seat is on the right side, and the copilot’s is on the left. Each seat has a one-piece ceramic composite bucket at- tached to energy absorption tubes. Each seat is positioned on a track with the bucket directly above a recess in the cockpit floor. Crash loads are reduced by allowing the seat and occupant to move vertically as a single unit. Occupant restraint is provided by a shoulder harness, lap belts, and a crotch belt. 2.13.1.1 Seat Height Adjustment. WARNING To prevent injury to personnel, do not release either the normal or emergency vertical adjust levers unless someone is sitting in the seat. The extension springs are under load at all times. With seat at lowest position, the vertical preload on the seat could be as high as 150 pounds. If no one is in the seat and vertical adjust lever(s) is released, the seat will be snapped to the highest stop. Anyone leaning over the seat or with hands on guide tubes above linear bearings will be seriously injured. Vertical seat adjustment is controlled by a lever on the right front of the seat bucket. Springs are installed to counterbalance the weight of the seat. The lever returns to the locked position when released. 2.13.1.2 Forward and Rear Adjustment. The seat is adjusted for leg length by a locking lever on the left front of the seat bucket. The lever is spring-loaded and returns to the locked position when released. 2.13.1.3 Emergency Tilt Release Levers. The emergency tilt release levers are on each side of the seat support frame. The seat may be tilted back into the cabin for removal or treatment of a wounded pilot. Seat tilting can be done from the cabin only when the seat is in the full down and aft position. On RA-30525 seats, tilting is achieved by pushing the tilt levers in toward center, and then pulling the seat top rearward. On D3801 and D3802 seats, tilting is achieved by pushing the tilt levers outboard, and then pulling the seat top rearward. TM 1-1520-237-10 2-20 SA AB0823_1B 0 2 4 6 8 10 12 14 1 2 TOTAL FUEL PUSH TO TEST OFF DIGITS DIM ON QTY LB X 100 TEMP C X 10 PRESS PSI X 10 TEMP C X 10 −4 0 4 6 8 10 12 16 0 3 4 5 6 7 11 19 −4 0 4 8 10 12 14 18 1 2 TEST RTR OVERSPEED 1 R 2 1 2 0 70 30 90 95 100 105 110 120 130 0 70 30 90 95 100 105 110 120 130 1 R 2 1 2 0 20 40 60 80 100 120 140 140 120 100 80 60 40 20 0 100 150 200 250 20 50 KNOTS VERTICAL SPEED 1000 FT PER MIN DOWN UP 5 5 0 0 1 2 3 4 5 6 7 8 9 1 2 4 6 4 2 1 10 0 10 20 30 40 DN O F F STAB POS DEG 0O 10 O 20 O 30O 40 O KIAS LIMIT 150 100 80 60 45 S T A B D E G 1 2 3 4 30 0 HDG CRS N W E S 3 6 12 15 21 24 30 33 KM COURSE H D G NAV 2 1 2 1 MODE SEL DPLR VOR ILS VOR ILS BACK CRS BACK CRS FM HOME FM HOME NORM ALTR PLT CPLT NORM ALTR ADF VOR TURN RATE CRS HDG VERT GYRO BRG 2 L H 5 10 15 FT X 100 LO ABS ALT FEET HI LO OFF PUSH 0 1 2 SET SET #1 FUEL LOW #1 GEN #2 GEN #2 FUEL LOW #2 GEN BRG #1 GEN BRG #1 ENGINE OIL PRESS #1 CONV #2 CONV #2 ENGINE OIL PRESS #2 ENGINE OIL TEMP DC ESS BUS OFF AC ESS BUS OFF #1 ENGINE OIL TEMP CHIP #1 ENGINE BATT LOW CHARGE BATTERY FAULT CHIP #2 ENGINE #2 FUEL FLTR BYPASS GUST #1 FUEL FLTR BYPASS #1 OIL FLTR BYPASS #2 OIL FLTR BYPASS #1 PRI SERVO PRESS IRCM INOP #2 HYD PUMP #2 PRI SERVO PRESS #1 TAIL RTR SERVO TAIL ROTOR QUADRANT MAIN XMSN OIL TEMP INT XMSN OIL TEMP TAIL XMSN OIL TEMP APU OIL TEMP HI TRIM FAIL SAS OFF STABILATOR BOOST SERVO OFF LFT PITOT HEAT IFF RT PITOT HEAT CHIP INPUT MDL−LH CHIP INT XMSN CHIP TAIL XMSN CHIP INPUT MDL−RH CHIP ACCESS MDL−RH APU FAIL CHIP MAIN MDL SUMP CHIP ACCESS MDL−LH MR DE−ICE FAIL MR DE−ICE FAULT TR DE−ICE FAIL ICE DETECTED BACK−UP RSVR LOW #2 RSVR LOW #1 RSVR LOW MAIN XMSN OIL PRESS #2 ENG ANTI−ICE ON BACK−UP PUMP ON #2 TAIL RTR SERVO ON #2 ENG INLET ANTI−ICE ON PRIME BOOST PUMP ON LDG LT ON HOOK ARMED EXT PWR CONNECTED #1 ENG INLET ANTI−ICE ON APU GEN ON CARGO HOOK OPEN PARKING BRAKE ON APU ACCUM LOW APU ON #1 ENG ANTI−ICE ON BRT / TEST #2 ENGINE STARTER FLT PATH STAB OFF ON ENGINE IGNITION NON SECURE RADIOS WILL NOT BE KEYED WHEN USING ANY SECURE RADIO OR THE INTERCOM FOR CLASSIFIED COMMUNICATIONS RADIO FM 1 SW NO. 1 UHF 2 VHF 3 FM2 4 5 VOR LOC AUX MB ADF NAV ICS IDENT RAD ALT DIMMING NVG DIMMING MA WRN CAUT/ADVSY TO TEST ALT 1000 FT 100 FT IN. HG 1 2 2 9 9 0 #1 ENGINE #2 ENGINE PRESS PRESS LOCK PITCH BIAS FAIL #1 ENGINE STARTER RADIO CALL 00 0 00 22 23 25 7 9 8 11 5 4 6 12 1 2 3 13 14 24 21 19 20 15 16 17 18 13 14 7 9 8 10 11 4 5 6 1 2 3 27 26 12 27 #1 ENG OUT #2 ENG OUT LOW ROTOR RPM MASTER CAUTION PRESS TO RESET FIRE CMD ATT 30 30 30 30 NAV ROLL PITCH CLI M B DI VE G S GA DH MB DIM #1 HYD PUMP * AUX FUEL SEARCH LT * * ON CODE OFF % RPM % TRQ FUEL XMSN ENG B DPLR NO FLOW VENT FAIL IMBAL EMPTY EMPTY INBD OUTBD L NO FLOW VENT OVFL EMPTY EMPTY OUTBD INBD R AUX FUEL QTY LBS TEST / RESET XFER MODE AUTO MAN O F F LEFT RIGHT O T H INBD OUTBD B MAN XFER XFER FROM PRESS OUTBD INBD OFF ALL 28 28 RST MODE ST/SP 12:34 SET LC−6 ADV CHRONOMETER 55 12 1 2 3 4 567 8 9 10 11 60 5 10 15 20 25 30 35 40 45 50 55 C B C DPLR GPS 29 29 MSG WPT NO GPS HOLD RAIM APR Figure 2-9. Instrument Panel (Sheet 1 of 4) UH TM 1-1520-237-10 2-21 OFF DIGITS 1 − CHAN − 2 PRESS PSI 5 10 TEMP \ X 100 SPEED \ X 10 OIL TGT Ng TGT Ng 1 4 5 6 7 8 13 17 1 2 1 2 0 2 4 5 6 7 8 9 0 4 7 8 9 10 11 HDG NAV ALT HDG ON NAV ON ALT ON CIS MODE SEL MODE SEL DPLR VOR ILS VOR ILS BACK CRS BACK CRS FM HOME FM HOME NORM ALTR PLT CPLT NORM ALTR ADF VOR TURN RATE CRS HDG VERT GYRO BRG 2 POWER ON TEST TEST IN PROGRESS MODE AUTO T L M BLADE DE−ICE TEST NORM SYNC 1 SYNC 2 OAT EOT PWR MAIN TAIL RTR RTR ON OFF PRESS TO TEST B L A D E D E I C E I R C M M AN U A L L W G 9 / m 3 T L M H 0 2 5 5 10 1 5 2 0 F A IL RADIO CALL 00 0 00 MA DAY NIGHT BRIL #1 ENG OUT #2 ENG OUT LOW ROTOR RPM MASTER CAUTION PRESS TO RESET FIRE CMD ATT 30 30 30 30 NAV ROLL PITCH CLI M B DI VE G S 1 2 3 4 30 0 HDG CRS N W E S 3 6 12 15 21 24 30 33 KM COURSE H D G NAV 2 1 2 1 10 0 10 20 30 40 DN O F F STAB POS DEG 0 O 10 O 20 O 30 O 40 O KIAS LIMIT 150 100 80 60 45 S T A B D E G RAD ALT DIMMING TEST RTR OVERSPEED 1 R 2 1 2 0 70 30 90 95 100 105 110 120 130 0 70 30 90 95 100 105 110 120 130 1 R 2 1 2 0 20 40 60 80 100 120 140 140 120 100 80 60 40 20 0 % RPM % TRQ 100 150 200 250 20 50 KNOTS VERTICAL SPEED 1000 FT PER MIN DOWN UP .5 .5 1000 FT 100 FT IN. HG 1 2 0 2 9 0 1 2 3 4 5 6 7 8 9 1 2 4 6 4 2 1 9 0 L 5 10 15 FT X 100 LO ABS ALT FEET HI LO OFF PUSH 0 1 2 SET SET TO TEST ALT POWER ON TEST TEST IN PROGRESS MODE AUTO T L M BLADE DE−ICE TEST NORM SYNC 1 SYNC 2 OAT EOT PWR MAIN TAIL RTR RTR ON OFF PRESS TO TEST B L A D E D E I C E I R C M M AN U A L L W G g / m 3 T L M H 0 2 5. 5 10 1 5 2 0 F A IL O F F 1. RADAR ALTIMETER 2. BAROMETRIC ALTIMETER 3. VERTICAL SPEED INDICATOR 4. MASTER WARNING PANEL 5. VERTICAL SITUATION INDICATOR 6. HORIZONTAL SITUATION INDICATOR 7. AIRSPEED INDICATOR 8. STABILATOR POSITION PLACARD 9. STABILATOR INDICATOR 10. CIS MODE SELECTOR 11. VSI / HSI MODE SELECTOR 12. RADIO CALL PLACARD 13. PILOT’S DISPLAY UNIT 14. CLOCK 15. ICE RATE METER 16. BLADE DEICE CONTROL PANEL 17. BLADE DEICE TEST PANEL 18. INFRARED COUNTERMEASURE CONTROL PANEL 19. CENTRAL DISPLAY UNIT 20. RADAR WARNING INDICATOR 21. AUXILIARY FUEL MANAGEMENT PANEL 22. ENGINE IGNITION SWITCH 23. RADIO SELECT PLACARD 24. CAUTION / ADVISORY PANEL 25. SECURE WARNING PLACARD 26. NVG DIMMING CONTROL PANEL 27. RAD ALT DIMMING A SA DM MA (ON HELICOPTERS WITH REARRANGED BLADE DEICE PANELS) AFMS A 28. FORWARD COCKPIT AIRBAG C B 29. GPS ANNUNCIATORS 128D DPLR GPS SASA AB0823_2B MSG WPT NO GPS HOLD RAIM APR RST MODE ST/SP 12:34 SET LC−6 ADV CHRONOMETER 55 Figure 2-9. Instrument Panel (Sheet 2 of 4) UH TM 1-1520-237-10 2-22 SA AA0516_3C 0 2 4 6 8 10 12 14 1 2 TOTAL FUEL TO TEST OFF DIGITS DIM ON QTY LB X 100 TEMP PRESS PSI X 10 TEMP O C X 10 −4 0 4 6 8 10 12 16 0 3 4 5 6 7 11 19 −4 0 4 8 10 12 14 18 1 2 TEST RTR OVERSPEED 1 R 2 1 2 0 70 30 90 95 100 105 110 120 130 0 70 30 90 95 100 105 110 120 130 1 R 2 1 2 0 20 40 60 80 100 120 140 140 120 100 80 60 40 20 0 #1 ENG OUT #2 ENG OUT LOW ROTOR RPM MASTER CAUTION PRESS TO RESET FIRE VERTICAL SPEED 1000 FT PER MIN DOWN UP 5 5 0 0 1 2 3 4 5 6 7 8 9 1 2 4 6 4 2 1 10 0 10 20 30 40 DN O F F STAB POS DEG CMD ATT 30 30 30 30 NAV ROLL PITCH CLI M B DI VE G S 0O 10O 20O 30O 40O KIAS LIMIT 150 100 80 60 45 S T A B D E G 1 2 3 4 30 0 HDG CRS N W E S 3 6 12 15 21 24 30 33 KM COURSE H D G NAV 2 1 2 1 MODE SEL IINS IINS VOR ILS VOR ILS BACK CRS BACK CRS FM HOME FM HOME NORM ALTR PLT CPLT NORM ALTR ADF VOR TURN RATE CRS HDG VERT GYRO BRG 2 L H 5 10 15 FT X 100 LO ABS ALT FEET HI LO OFF PUSH 0 1 2 SET SET #1 FUEL LOW #1 GEN #2 GEN #2 FUEL LOW #2 GEN BRG #1 GEN BRG #1 ENGINE OIL PRESS #1 CONV #2 CONV #2 ENGINE OIL PRESS #2 ENGINE OIL TEMP DC ESS BUS OFF AC ESS BUS OFF #1 ENGINE OIL TEMP CHIP #1 ENGINE BATT LOW CHARGE BATTERY FAULT CHIP #2 ENGINE #2 FUEL FLTR BYPASS GUST #1 FUEL FLTR BYPASS #1 OIL FLTR BYPASS #2 OIL FLTR BYPASS #1 PRI SERVO PRESS #1 HYD PUMP #2 HYD PUMP #2 PRI SERVO PRESS #1 TAIL RTR SERVO TAIL ROTOR QUADRANT MAIN XMSN OIL TEMP INT XMSN OIL TEMP TAIL XMSN OIL TEMP APU OIL TEMP HI TRIM FAIL SAS OFF STABILATOR BOOST SERVO OFF LFT PITOT HEAT IFF RT PITOT HEAT CHIP INPUT MDL−LH CHIP INT XMSN CHIP TAIL XMSN CHIP INPUT MDL−RH CHIP ACCESS MDL−RH APU FAIL CHIP MAIN MDL SUMP CHIP ACCESS MDL−LH MR DE−ICE FAIL MR DE−ICE FAULT TR DE−ICE FAIL ICE DETECTED BACK−UP RSVR LOW #2 RSVR LOW #1 RSVR LOW MAIN XMSN OIL PRESS #2 ENG ANTI−ICE ON BACK−UP PUMP ON #2 TAIL RTR SERVO ON #2 ENG INLET ANTI−ICE ON PRIME BOOST PUMP ON LDG LT ON EXT PWR CONNECTED #1 ENG INLET ANTI−ICE ON APU GEN ON AIR COND ON PARKING BRAKE ON APU ACCUM LOW APU ON #1 ENG ANTI−ICE ON BRT / TEST #2 ENGINE STARTER FLT PATH STAB OFF ON ENGINE IGNITION NON SECURE RADIOS WILL NOT BE KEYED SYSTEMS SELECT INTERCOM FOR CLASSIFIED COMMUNICATIONS RADIO FM 1 SW NO. 1 UHF 2 VHF 3 FM2 4 5 VOR LOC AUX MB ADF NAV ICS IDENT RAD ALT DIMMING NVG DIMMING MA WRN CAUT / ADVSY TO TEST ALT 1000 FT 100 FT IN. HG 1 2 2 9 9 0 #1 ENGINE #2 ENGINE PRESS PRESS LOCK ANTENNA EXTENDED #1 ENGINE STARTER RADIO CALL 00 0 00 IRCM INDP AUX FUEL SEARCH LT ON CABIN HEAT ON ANTENNA RETRACTED DIM FLARE 3 6 9 12 15 18 0 21 24 27 30 33 0 0 0 0 K N CREW CALL WHEN USING ANY SECURE RADIO OR THE DG IINS HDG VG IINS ATT 27 31 7 9 8 11 5 4 6 12 1 2 3 13 14 28 25 21 22 15 16 17 18 13 14 7 9 8 10 11 6 1 2 3 33 32 12 33 30 29 26 24 23 20 5 4 PUSH GA DH MB 100 150 200 250 20 50 KNOTS CODE OFF O C X 10 % TRQ % RPM FUEL XMSN ENG 19 34 34 12 1 2 3 4 567 8 9 10 11 60 5 10 15 20 25 30 35 40 45 50 55 C Figure 2-9. Instrument Panel (Sheet 3 of 4) EH TM 1-1520-237-10 2-23 SA AA0516_4E HDG NAV ALT HDG ON NAV ON ALT ON CIS MODE SEL MODE SEL DPLR DPLR VOR ILS VOR ILS BACK CRS BACK CRS FM HOME FM HOME NORM ALTR PLT CPLT NORM ALTR ADF VOR TURN RATE CRS HDG VERT GYRO BRG 2 RADIO CALL 00 0 00 MA DAY NIGHT BRIL #1 ENG OUT #2 ENG OUT LOW ROTOR RPM MASTER CAUTION PRESS TO RESET FIRE CMD ATT 30 30 30 30 NAV ROLL PITCH CLI M B DI VE G S 1 2 3 4 30 0 HDG CRS N W E S 3 6 12 15 21 24 30 33 KM COURSE H D G NAV 2 1 2 1 10 0 10 20 30 40 DN O F F STAB POS DEG 0 O 10 O 20 O 30 O 40 O KIAS LIMIT 150 100 80 60 45 S T A B D E G RAD ALT DIMMING TEST RTR OVERSPEED 1 R 2 1 2 0 70 30 90 95 100 105 110 120 130 0 70 30 90 95 100 105 110 120 130 1 R 2 1 2 0 20 40 60 80 100 120 140 140 120 100 80 60 40 20 0 % RPM % TRQ 100 150 200 250 20 50 KNOTS VERTICAL SPEED 1000 FT PER MIN DOWN UP .5 .5 1000 FT 100 FT IN. HG 1 2 0 2 9 0 1 2 3 4 5 6 7 8 9 1 2 4 6 4 2 1 9 0 L 5 10 15 FT X 100 LO ABS ALT FEET HI LO OFF PUSH 0 1 2 SET SET TO TEST ALT POWER ON TEST TEST IN PROGRESS MODE AUTO T L M BLADE DE−ICE TEST NORM SYNC 1 SYNC 2 OAT EOT PWR MAIN TAIL RTR RTR ON OFF PRESS TO TEST B L A D E D E I C E I R C M M AN U A L L W G 9 / m 3 T L M H 0 2 5 5 10 1 5 2 0 F A IL O F F 1. RADAR ALTIMETER 2. BAROMETRIC ALTIMETER 3. VERTICAL SPEED INDICATOR 4. MASTER WARNING PANEL 5. VERTICAL SITUATION INDICATOR 6. HORIZONTAL SITUATION INDICATOR 7. AIRSPEED INDICATOR 8. STABILATOR POSITION PLACARD 9. STABILATOR POSITION INDICATOR 10. CIS MODE SELECTOR 11. VSI / HSI MODE SELECTOR 12. RADIO CALL PLACARD 13. PILOT’S DISPLAY UNIT 14. CLOCK GA DM MB RETRACT OFF EXTEND OFF ON POWER PUSH FOR STANDBY STATUS TEST FLARE 15. BLADE DEICE CONTROL PANEL 16. BLADE DEICE TEST PANEL 17. ICE RATE METER 18. ALQ−144 INFRARED COUNTERMEASURE 19. ASE STATUS PANEL 21. CENTRAL DISPLAY UNIT 22. RADAR WARNING INDICATOR 23. ECM ANTENNA SWITCH 24. ENGINE IGNITION SWITCH 25. BEARING DISTANCE HEADING INDICATOR 26. CREW CALL SWITCH / INDICATOR 27. SYSTEM SELECT PANEL 28. CAUTION / ADVISORY PANEL 29. FLARE DISPENSE SWITCH 30. RADIO SELECT PLACARD 31. SECURE RADIO WARNING PLACARD 32. NVG DIMMING CONTROL PANEL 33. RADAR ALTIMETER DIMMING 1 − CHAN − 2 PRESS PSI 5 10 TEMP SPEED OIL TGT Ng TGT Ng 1 4 5 6 7 8 13 17 1 2 1 2 0 2 4 5 6 7 8 9 0 4 7 8 9 10 11 9 C X 100 % X 10 CONTROL PANEL ALQ 162 CW THRT NO G0 CW JAM ALQ 156 CM JAM CM INOP ALQ 144 IRCM INOP ALQ 135 OVER TEMP RDR INOP 20. ALQ−156 COUNTERMEASURE PANEL A S E 34. FORWARD COCKPIT AIRBAG 12 1 2 3 4 567 8 9 10 11 60 5 10 15 20 25 30 35 40 45 50 55 C Figure 2-9. Instrument Panel (Sheet 4 of 4) EH TM 1-1520-237-10 2-24 2.13.1.4 Emergency Vertical Release Lever. The emergency vertical release lever permits the seat to drop to the lowest adjustment point for tilting. The emergency vertical release lever is on the upper center back of RA- 30525 seats, and is actuated by pulling right on the lever. The emergency vertical release pedal is on the lower back of the D3801 and D3802 seats, and is actuated by pushing down on the foot operated pedal. 2.13.1.5 Seatbelts. The pilot’s and copilot’s seats each contain a shoulder harness, seatbelt, and a crotch strap connected to a common buckle assembly. All belts and straps have adjustment fittings. The attachment buckle has a single-point release that will be common in configuration on the pilot’s and copilot’s seats; they may be of the lift lever or rotary release configuration. When the lanyard is pulled or the release is turned, all belts and straps will release simultaneously. 2.13.2 Protective Armor. Armor protection is provided for the body of the pilot and copilot against 7.62 mm rounds from the side and from the back and below. Armored wings, attached to the cockpit interior, consist of a sliding panel at the outboard side of each seat. A release lever at the front of each panel permits sliding the panel aft to allow rapid entrance and exit, as well as freedom of movement for the seat occupant. The CABS side air bag modules are mounted on the inboard panel. 2.13.3 Crew Chief/Gunner Seats. WARNING Do not store any items below seats. Dur- ing a crash any obstruction will increase the probability and severity of injury. Two outward facing seats (Figure 2-10), one on each side of the helicopter at the front of the cabin, are for the crew chief/gunners. Each seat faces a window. Each seat is a cable-supported steel tube assembly with a fire-resistant, high strength fabric seat and backrest containing two lower energy attenuators designed to reduce personal injury in a crash. Each seat has a complete lap belt and dual torso- restraint shoulder harness attached to a dual action rotary release buckle. The shoulder harness is connected to inertia reels on the seat back and bottom. This gives the wearer freedom to move about his station. On helicopters equipped with improved crewchief/gunner’s restraint system, the restraint system is equipped with a single ac- tion rotary release buckle with a guard. A release plate must be pressed to allow rotation of release, preventing inadvertent handle rotation from contact with equipment, etc. The inertia reel lock control is replaced by a shorter push/pull manual locking control. Push in and the inertia reel is manually locked in place. When the control is pulled out, the reel will lock on sudden pull. 2.14 TROOP PROVISIONS. WARNING Do not store any items below seats. Dur- ing a crash any obstruction will increase the probability and severity of injury. UH In addition to crew chief and gunner seats, troop seats may be installed for up to 12 persons. Each troop seat has a belt and shoulder harness for body restraint. The backs and seat pans are attached through cables to the cabin ceiling and through cables and rods to seat fittings installed in the floor. The seats may be installed in any quantity from 1 to 12. Each seat contains two lower energy attenuators designed to reduce personnel injury in a crash. In Row 1, do not install a passenger/troop seat in the most forward center position directly behind the cockpit center console. When seats are removed from the cabin and stowed in the stowage compartment, adjustments must be made for weight and balance using data in Figures 6-3 and 6-12. 2.14.1 Troop Seatbelt Operation. UH 1. Extend shoulder strap and attach shoulder strap fittings to buckle. 2. Extend lap belt and place across body. 3. Place lap belt fitting into buckle and make certain of positive lock. 4. Adjust lap belt tension and shoulder straps for a comfortable fit. 2.14.2 DF and ECM Operator’s Seats. EH The seats are similar to the pilot’s and copilot’s seats except that armored wing protection is not provided. 2.14.3 Observer’s Seat. EH The observer’s seat (Figure 2-6) is identical to a troop seat. It is installed behind, and to the right, of the DF operator’s seat. TM 1-1520-237-10 2-25 TROOP COMMANDER’S SEAT CREW CHIEF / GUNNER’S SEAT TROOP SEAT (TYPICAL) LEFT GUNNER’S SEAT SA AA0407 Figure 2-10. Troop Seats UH TM 1-1520-237-10 2-26