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TECHNICAL MANUAL
OPERATORS MANUALFOR
UH-60A HELICOPTER
UH-60L HELICOPTER
EH-60A HELICOPTER
WARNING - This document contains technical data whose export is restricted by the Arms ExportControl Act (Title 22, U.S.C. Sec. 2751 et seq.) or the Export Administration Act of 1979, asamended, Title 50, U.S.C., App. 2401 et seq. Violation of these export laws are subject to severecriminal penalties. Disseminate in accordance with provisions of DoD Directive 5230.25.
DISTRIBUTION STATEMENT D. Distribution authorized to the DOD and DOD contractors only due toCritical 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 orreconstruction of the document.
*This manual supersedes TM 1-1520-237-10, dated 17 April 2006, including all changes.
*TM 1-1520-237-10
HEADQUARTERS, DEPARTMENT OF THE ARMY
25 SEPTEMBER 2009
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WARNING
Personnel performing operations, procedures, and practices which are included or implied in this technical manual shallobserve the following warnings. Disregard of these warnings and precautionary information can cause serious injury or loss
of life.BATTERY ELECTROLYTE
Battery electrolyte is harmful to the skin and clothing. If potassium hydroxide is spilled on clothing or other material, washimmediately with clean water. If spilled on personnel, immediately ush the affected area with clean water. Continuewashing until medical assistance arrives. Neutralize any spilled electrolyte by thoroughly ushing contacted area with water.
CARBON MONOXIDE
When smoke, suspected carbon monoxide fumes, or symptoms of anoxia exist, the crew should immediately ventilate thecockpit.
ELECTROMAGNETIC INTERFERENCE (EMI)
No electrical/electronic devices of any sort, other than those described in this manual or appropriate airworthiness releaseand approved by USAAMCOM AMSRD-AMR-AE-U, are to be operated by crewmembers or passengers during operationof this helicopter.
FIRE EXTINGUISHER
Exposure to high concentrations of extinguishing agent or decomposition products should be avoided. The liquid should notbe 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 Generals hearing conserva-tion criteria, as dened in DA PAM 40-501. Hearing protection devices, such as the aviator helmet or ear plugs are requiredto be worn by all personnel in and around the helicopter during its operation. When window guns are ring, when ightsexceed 100 minutes during any 24 hour period, or when speeds are above 120 knots, helmet and ear plugs shall be worn byall 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 ring. Do not walk infront of weapons. SAFE the machinegun before servicing. To avoid potentially dangerous situations, follow all proceduralwarnings in text.
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ELECTROMAGNETIC RADIATION
Do not stand within six feet of Aircraft Survivability Equipment (ASE), ALQ-156, ALQ-162, and ALQ-144 transmitantennas when the ASE equipment is on. High frequency electromagnetic radiation can cause internal burns without causingany sensation of heat. The HF radio transmits high power electromagnetic radiation. Serious injury or death can occur if you touch the HF antenna while it is transmitting. Do not grasp, or lean against the antenna when power is applied to thehelicopter.
ALQ-144
Do not continuously look at the ALQ-144 infrared countermeasure transmitter during operation, or for a period of over 1minute from a distance of less than 3 feet. Skin exposure to countermeasure radiation for longer than 10 seconds at adistance less than 4 inches shall be avoided.
IR COUNTERMEASURES MUNITIONS
Advanced IR countermeasures munitions (AIRCMM) M-211 and M-212 ares should not be loaded in the M-130 generalpurpose dispenser as countermeasures against IR missile threat environment. Advanced IR countermeasures munitions(AIRCMM) M-211 and M-212 ares will provide inadequate IR countermeasures capability and will signicantly increaseaircrew vulnerability.
AIR WARRIOR
If performing a combat mission with an Air Warrior ballistic upgrade plate (BUP), the seat belt buckle must be positionedbelow the BUP to prevent potential aft cyclic restriction.
When performing a combat mission or overwater mission, aviator worn gear can restrict head and torso movement. Usersshould conduct ground familiarity drills (blind switch/control identication) and crew coordination exercises before ightsince eld of regard can be restricted by aviator worn mission equipment. The user must strictly adhere to proper crewcoordination procedures during switch identication.
Prior to ight, the user must perform control sweeps to ensure there are no ight control interference problems with aviatorworn gear. If a restriction is found, the interfering gear must be adjusted/moved to eliminate the restriction.
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Insert latest change pages; dispose of superseded pages in accordance with applicable policies.
NOTE: On a changed page, the portion of the text affected by the latest change is indicated by a vertical line inthe outer margin of the page. Changes to illustrations are indicated by a hand pointing to the changed area onthe 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:
PageNo.
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Title....................... 0Blank..................... 0a - b...................... 0 A .......................... 0B Blank.................. 0i - v ....................... 0 vi Blank ................. 01-1 - 1-2 ............... 0
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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
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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
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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 emphasizeimportant and critical instructions and are used for the fol-lowing conditions:
WARNING
An operating procedure, practice, etc.,which, if not correctly followed, couldresult in personal injury or loss of life.
CAUTION
An operating procedure, practice, etc.,
which, if not strictly observed, couldresult 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 thatof tactical transport of troops, medical evacuation, cargo,and reconnaissance wi th in the capabi l i t i es o f thehelicopter. The observance of limitations, performance,and weight and balance data provided is mandatory. Theobservance of procedures is mandatory except when
modication is required because of multiple emergencies,adverse weather, terrain, etc. Your ying experience isrecognized and therefore, basic ight principles are notincluded. IT IS REQUIRED THAT THIS MANUAL BECARRIED IN THE HELICOPTER AT ALL TIMES.
1.4 APPENDIX A, REFERENCES.
Appendix A is a listing of official publications citedwithin the manual applicable to and available for ightcrews and fault isolation/trouble references.
1.5 APPENDIX B, ABBREVIATIONS AND TERMS.
Abbreviations listed are to be used to clarify the text inthis manual only. Do not use them as standard abbrevia-tions.
1.6 INDEX.
The index lists, in alphabetical order, paragraphs,gures, and tables contained in this manual. Chapter 7 andChapter 7A performance data have additional indexeswithin the chapters.
1.7 ARMY AVIATION SAFETY PROGRAM.
Reports necessary to comply with the safety programare prescribed in AR 385-10.
1.8 DESTRUCTION OF ARMY MATERIEL TOPREVENT ENEMY USE.
For information concerning destruction of Armymateriel to prevent enemy use, refer to TM 750-244-1-5.
1.9 FORMS AND RECORDS.
Army aviators ight record and aircraft inspection andmaintenance 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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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 avertical line in the outer margin extending close to theentire area of the material affected. A miniature pointinghand symbol denotes changes on an i l lustrat ion. AMAJOR CHANGE symbol on the illustration indicatesextensive changes have been made. Change symbols arenot used to indicate changes in the following:
a. Introductory material.
b. Indexes and tabular data where the change cannot beidentied.
c. Blank space resulting from the deletion of text, anillustration, 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 andprocedures.
1.11 SERIES AND EFFECTIVITY CODES.
Designator symbols listed below, are used to showlimited effectivity of airframe information material inconjunction with text content, paragraph titles, and il-lustrations. Designators may be used to indicate proper ef-fectivity, unless the material applies to all models andconguration within the manual. Designator symbolsprecede procedural steps in Chapters 8 and 9. If the mate-
rial applies to all series and congurations, no designatorsymbol will be used.
DESIGNATORSYMBOL
APPLICATION
UH UH-60A and UH-60Lpeculiar information.
UH60A UH-60A peculiar informa-tion.
H60A+ UH-60A equipped withT700-GE-701D/CC engines(701D core with 701C hy-dromechanical unit anddigital electronic unit) andUH-60L CDU.
UH60L UH-60L peculiar informa-tion.
DESIGNATORSYMBOL
APPLICATION
EH EH-60A peculiar informa-tion.
700 Helicopters equipped withT700-GE-700 engines.
701C 701D/CC Helicopters equipped withT700-GE-701C engines orT700-GE-701D/CC engines(701D core with 701C hy-dromechanical unit anddigital electronic unit).
ERFS Helicopters with ExtendedRange Fuel System.
AFMS Helicopters with AuxiliaryFuel Management System.
CEFS Helicopters with Crashwor-thy External Fuel System.
AHRS Helicopters equipped withAttitude Heading ReferenceSet.
128D Helicopters equipped withDoppler/GPS Navigation Set(DGNS) AN/ASN-128D.
1.12 HIGH DRAG SYMBOL.
This symbol will be used throughout this manual todesignate information applicable to the high dragconguration described in Chapters 7 and 7A.
1.13 PLACARDED AIRCRAFT SYMBOL.
This symbol will be used throughout this manualto designate applicability to helicopters which have torqueplacard limitations.
1.14 USE OF WORDS SHALL, SHOULD, ANDMAY.
Within this technical manual the word shall is used toindicate a mandatory requirement. The word should isused 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 hel icopters sys tems and igh t cont ro ls. Thefunctioning of electrical and mechanical components issimplied 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 fuselagehelicopter. Primary mission capability of the helicopter istactical transport of troops, supplies and equipment.Secondary missions include training, mobilization,development of new and improved concepts, and supportof disaster relief. The main rotor system has four bladesmade of titanium/berglass. The drive train consists of amain transmission, intermediate gear box, and tail rotorgear box with interconnecting shafts. The propulsionsystem has two T700-GE-700 engines operating in paral-
lel. The nonretractable landing gear consists of the mainlanding gear and a tailwheel. The armament consists of two 7.62 mm machineguns, one on each side of thehelicopter in the forward cabin. Kit installations for thehelicopter consist of range extension tanks, rescue hoist,medical evacuation, infrared suppression, blade anti-icing/ deicing, blackout devices, snow skis, winterization, andstatic/rappelling kit. Refer to this chapter and Chapter 4 forkit descriptions.
2.3 UH-60A WITH T700-GE-701D/CC ENGINES.
H60A+ Some UH-60A helicopters have been modi-
ed by replacing the T700-GE-700 with T700-GE-701D/ CC engines. This modication also added upgraded InletAnti-Ice valves, cross bleed shutoff valves and couplingsthat withstand the higher bleed air temperatures of the newengine. An additional Nr sensor mounted on the accessorygearbox and a third potentiometer installed on the mixingunit provide transient droop improvement. Automaticrelight 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-60Ahelicopter except engines T700-GE-701C or T700-GE-
701D/CC replace T700-GE-700. Also the main transmis-sion has been modied to increase its durability. Differ-ences between the two transmissions are annotated withUH-60A or UH-60L.
2.5 EH-60A.
The EH-60A helicopter is a modied UH-60A (Figure2-1 ) with a crew of four. The mission equipment consistsof electronic systems with modications that will ensurethat the mission requirements are met. The EH-60Asystem includes air conditioning, helicopter survivabilityequipment, and avionics equipment. An electronics
compartment within the transition section is used foravionics equipment. The compartment can be entered fromthe right side of the helicopter. The mission systemsemploy two operators: The direction nder/electronicssurveillance measure (DF ESM) operator controlling theelectronics surveillance functions, and the electronicscountermeasure (ECM) operator controlling the activecountermeasure functions. The EH-60A can operateindependently or in conjunction with up to two additional,similarly equipped, helicopter. When operating in the mul-tisystem mode, secured air-to-air communications areprovided for automatic tasking between helicopter.Secured air-to-ground communications are also providedfor voice reporting purposes.
2.6 DIMENSIONS.
Principle dimensions of the helicopter are based on thecyclic stick and tail rotor pedals being centered and thecollective stick being in its lowest position. All dimensionsare approximate and they are as shown on Figure 2-2.
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2.7 TURNING RADIUS AND GROUNDCLEARANCE.
WARNING
Main rotor clearance in Figure 2-3 isshown with cyclic centered and levelground. Cyclic displacement or slopingterrain may cause rotor blade clearanceto be signicantly less.
For information on turning radius and ground clearancerefer to Figure 2-3.
2.8 COMPARTMENT DIAGRAM.
2.8.1 Compartment Diagram. UH The fuselage isdivided into two main compartments, the cockpit and
cabin. The cockpit (Figure 2-4 ) is at the front of thehelicopter with the pilots sitting in parallel, each with a setof ight controls and instruments. Operation of electricalcontrols is shared by both. The cabin compartmentcontains space for crew chief seating, troop seating, litterinstallation, and cargo. Restraint of cargo is by tiedownrings installed in the oor. Two stowage compartments(Figure 6-12 ), at the rear of the cabin over the main fueltanks, are for yaway equipment. The equipment storagecompartments are reached from inside the cabin. A gustlock control, APU accumulator handpump and pressuregage, and APU ESU (Figure 2-5) are also installed.
2.8.2 Compartment Diagram. EH A xed observerseat is installed to allow observation of either operatorposition (Figure 2-6) . Floor attachments are provided forsecuring rack mounts and seats. Blackout curtains may beused to eliminate any light intrusion into the cockpit dur-ing night operations, or any glare on the operators consoleduring day operations. Blackout curtains may be usedbetween cockpit and cabin during NVG operations.
2.9 UPPER AND LOWER CONSOLES.
All cockpit electrical controls are on the upper andlower consoles and instrument panel. The upper console(Figure 2-7) , overhead between pilot and copilot, containsengine controls, re emergency controls, heater andwindshield wiper controls, internal and external lightcontrols, electrical systems, and miscellaneous helicoptersystem controls. The rear portion of the upper panelcontains the dc essential bus circuit breaker panels. Thelower 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. Theco n so l e i s a r ran g ed wi t h co mmu n i ca t io n p an e l s ,navigational panels, and ight attitude/stability controls.The rear part of the console houses the battery bus andbattery utility bus circuit breaker panel and parking brakehandle.
2.10 LANDING GEAR SYSTEM.The helicopter has a nonretractable landing gear
consisting of two main gear assemblies and a tailwheelassembly. The landing gear permits helicopter takeoffs andl an d i n g s o n s l o p es i n an y d i rec t i o n . Th e sy s t emincorporates a jack and kneel feature that permits manualraising 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 deactivatedwhen the weight of the helicopter is on the landing gear.On helicopters equipped with ESSS xed provisions, a
WOW switch is also installed on the right landing geardrag beam to provide ac underfrequency cutout andexternal stores jettison. The left WOW switch provides allother WOW functions as without ESSS provisions and theEMER JETT ALL capabilities. See Table 2-1 for refer-ence.
2.10.1 Main Landing Gear. The main landing gear ismounted on each side of the helicopter forward of centerof gravity. Each individual landing gear has a singlewheel, a drag beam, and a two-stage oleo shock strut. Thelower stage will absorb energy from landings up to 10feet-per-second (fps). Above 10 fps the upper stage and
lower stage combine to absorb loads up to 39 fps (about11.25 Gs).
2 .1 0. 2 W he el Bra ke Sy st em. Main landing gearwheels have disc hydraulic brakes. The self-contained,self-adjusting system is operated by the pilots andcopilots tail rotor pedals. The brakes have a visual brakepuck wear indicator. Each wheel brake consists of twosteel rotating discs, brake pucks, and a housing thatcontains the hydraulic pistons. The parking brake handle,marked PARKING BRAKE , is on the right side of thelower console. A hand-operated parking brake handle al-lows brakes to be locked by either pilot or copilot afterbrake pressure is applied. The parking brakes are appliedby pressing the toe brake pedals, pulling the parking brakehandle to its fully extended position, and then releasing thetoe brakes while holding the handle out. An advisory willappear indicating PARKING BRAKE ON . Pressingeither pilot or copilot left brake pedal will release theparking brakes, the handle will return to the off position
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SAAA0403_1B
19 5 20 21 21
2289232425
1. PITOT CUTTER2. BACK HYDRAULIC PUMP3. NO. 1 HYDRAULIC PUMP AND NO.1 GENERATOR4. UPPER (ROTOR PYLON) CUTTER5. INFRARED COUNTERMEASURE TRANSMITTER6. AFT MAINTENANCE LIGHT RECEPTACLE7. TAIL LANDING GEAR DEFLECTOR
8. FLARE DISPENSER9. CHAFF DIPENSER10. APU EXHAUST PORT11. COOLING AIR INLET PORT12. PNEUMATIC PORT13. PRESSURE AND CLOSED CIRCUIT REFUELING PORTS
14. NO. 1 ENGINE15. MAIN LANDING GEAR DEFLECTOR / CUTTER16. LANDING GEAR JOINT DEFLECTOR17. STEP AND EXTENSION DEFLECTOR18. DOOR HINGE DEFLECTOR19. RIGHT POSITION LIGHT (GREEN)20. FIRE EXTINGUISHER BOTTLES
21. FORMATION LIGHTS22. TAIL POSITION LIGHT (WHITE)23. APU24. 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)
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SAAA0403_2C
27 28 29 30
313233343536373839
404142
26
43
44
45
46
47
45
44
48
49
26.27.28.29.30.31.32.33.34.35.36.37.
UPPER ANTICOLLISION LIGHTTAIL DRIVE SHAFTNO. 2 HYDRAULIC PUMP AND NO. 2 GENERATORPYLON CUTTERHEATER AIR INTAKE PORTEXTERNAL ELECTRICAL POWER RECEPTACLENO. 2. ENGINEICE DETECTORAMBIENT SENSE PORTENGINE FAIRING / WORK PLATFORM (SAME BOTH SIDES)CONDENSER EXHAUST / STEPGRAVITY REFUELING PORT (SAME BOTH SIDES)
39.40.41.42.43.44.45.46.47.48.49.
AFT AVIONICS COMPARTMENT DOORSIINS BLOWER INLET FILTERTAIL PYLON FOLD HINGESTAIL PYLON SERVICE LADDER (SAME BOTH SIDES)STABILATORENGINE BAY AREA COOLING AIR INTAKE (SAME BOTH SIDES)WINDSHIELD POST DEFLECTORWINDSHIELD WIPER DEFLECTORAVIONICS COMPARTMENTOAT SENSORICE DETECTORPYLON COOLING AIR INTAKE
ON HELICOPTERS EQUIPPED WITH WIRE STRIKE PROTECTION SYSTEM
EH
EHEH
26
38.
Figure 2-1. General Arrangement (Sheet 2 of 2)
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SAAA0514B
TAIL ROTORDIAMETER11 FEET12 FEET
4 INCHES
9 FEET 5 INCHES
MAIN ROTOR DIAMETER53 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 WIDTH7 FEET 9 INCHES
TREAD8 FEET
10.6 INCHES
MAIN LANDING GEAR9 FEET 8.6 INCHES
STABILATOR WIDTH14 FEET 4 INCHES
8 FEET9 INCHES
20 O
5 FEET1 INCH
3 FEET9.5 INCHES
WIDTH WITH ESSS AND EXTERNALEXTENDED RANGE TANKS INSTALLED
21 FEET
FUSELAGE WIDTH WITHHOVER IR SUPPRESSORS
INSTALLED9 FEET 8 INCHES
Figure 2-2. Principle Dimensions
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TURNING
RADIUS41 FEET7.7 INCHES
12 FEET4 INCHES
9 FEET5 INCHESROTORTURNING
7 FEET7 INCHESROTORSTATIONARY
12 FEET1 INCH
11 FEET4 INCHES WHEELBASE 29 FEET
12 FEET5 INCHES
6 FEET6 INCHES
16 FEET10 INCHES*
TAIL ROTOR IS CANTED 20 O. UPPERTIP PATH PLANE IS 16 FEET 10 INCHESABOVE GROUND LEVEL
*
SAAA0402
Figure 2-3. Turning Radius and Clearance
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SAAB0821_1
2524
C HECK
L I S T
S TO WA
GEDA
TA & M
APCHECK LISTDATA & MAPSTOWAGE
1. UPPER CONSOLE
2. PILOTS COCKPIT UTILITY LIGHT 3. FREEAIR TEMPERATURE GAGE (ONHELICOPTERS WITH HEATED CENTERWINDSHIELD)
4. NO. 2 ENGINE FUEL SELECTOR LEVER 5. NO. 2 ENGINE OFF / FIRE THANDLE 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 THANDLE 22. NO. 1 ENGINE FUEL SELECTOR LEVER 23. AC ESNTL BUS CIRCUIT BREAKER
PANEL 24. COPILOTS COCKPIT UTILITY LIGHT 25. FREEAIR TEMPERATURE GAGE (ON
HELICOPTERS WITHOUT HEATEDCENTER 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
1715
111618 14
19. STANDBY (MAGNETIC COMPASS)
14. CABIN DOME LIGHTS DIMMER
Figure 2-4. Cockpit Diagram (Sheet 1 of 2)
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28
30
33
34
35
36
29
32
31
26 27
C HECK
L I S T
S TO WA
GEDA
TA & M
APCHECK LISTDATA & MAPSTOWAGE
26. 27. 28. 29. 30. 31. 32. 33.
34.
28
29
30
31
32
46
38
45
37384041424344
COCKPIT FLOODLIGHT CONTROLUPPER CONSOLEMASTER WARNING PANELSLIDING WINDOWCOCKPIT DOOR EMERGENCY RELEASECYCLIC STICKDIRECTIONAL CONTROL PEDALSPILOTS SEAT
35.
36. 37. 38. 39. 40.
CREW CHIEF / GUNNER ICS CONTROL
PANELCREW CHIEF AMMUNITION / GRENADESTOWAGE COMPARTMENTSTOWAGE BAGCOLLECTIVE STICK FRICTION CONTROLCOLLECTIVE STICK GRIPENGINE IGNITION KEYLOCKLOWER CONSOLE
41.
42. 43. 44. 45. 46.
BATTERY / BATTERY UTILITY BUSCIRCUIT BREAKER PANELFIRE EXTINGUISHERGUNNERS ICS CONTROL PANELFIRST AID KITGUNNERS AMMUNITION / GRENADECOPILOTS SIDE LOWER CONSOLE
SAAB0821_2
39
47
47. AUXILIARY FUEL MANAGEMENT PANELAFMS
48
48
48. FORWARD COCKPIT AIRBAG
Figure 2-4. Cockpit Diagram (Sheet 2 of 2)
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SAAA0323_1E
ON HELICOPTERS EQUIPPED WITHAUXILIARY ELECTRICAL CABIN HEATER
GUST LOCK CONTROL
APU ACCUMULATOR(LOOKING UP)
(LOCATED BELOW LEFT GUNNERS WINDOW)
GUST LOCKRELEASEBUTTON
GUST LOCKHANDLE
HEATER AIRINLET PORT
67
50 85
CABIN DOMELIGHTS (THREE)
TROOP COMMANDERSANTENNA COAX
D E
B
ACCUMULATORPRESSURE GAGE
ACCUMULATORHAND PUMP
ACCUMULATORPISTON POSITIONINDICATOR
MANUALSTARTVALVE
ACCUMULATORB
HEATER TEMPERATURECONTROL
STA349.50
STA378.50
STA332.50
A
REAR
TROOP COMMANDERS ICS CONTROL
TROOP COMMANDERS HANDSET
PUSHTOTALKSWITCH
AUX NAV1 2 3 4 5
OFF
HOT MIKE
ON
OFF
ON
OFF
VOLICS
1
2 3
4
5
CONT
COMM
E
D
C
A
F
CON HELICOPTERSEQUIPPED WITHAUXILIARY ELECTRICALCABIN HEATER
G
G
Figure 2-5. Cabin Interior (Sheet 1 of 3)
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APU DIGITAL ELECTRONIC SEQUENCE
RESETSTART FUEL VALVE & EXCITER SIGNAL OUT (5%)MAIN FUEL VALVE SIGNAL OUT (14%)START FUEL VALVE & EXCITER SIGNAL OFF (70%)90% RPM SWITCH ONREADY FOR SERVICE (90% + 1.5 SEC)PROCESSOR BOARD FAILURESENSOR/DATA BOARD FAILUREOVERTEMPERATUREOVERSPEEDUNDERSPEEDFAIL TO STARTLOW OIL PRESSUREHIGH OIL TEMPERATURE (WARNING)FAIL TO LIGHT (NO DATA)SHORTED THERMOCOUPLE PROBE (WARNING)OPEN THERMOCOUPLEPROCESSOR SEQUENCE FAILNO DATA
OPERATION
STARTSEQUENCE
1 2 3 4BITE #
T62T401DECODED 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 FAILUREOVERTEMPERATUREOVERSPEEDUNDERSPEEDFAIL TO STARTLOW OIL PRESSURE
HOT SENSOR FAILED
1 2 3 4BITE # DECODED BITE INFORMATION
FAULT INDICATION FAULTS
GTCP36150
ESU FAILURE
OIL PRESSURE SWITCH FAILEDTHERMOCOUPLE FAILEDMONOPOLE FAILEDFUEL SOLENOID FAILEDFUEL TORQUE MOTOR FAILEDIGNITION UNIT FAILED
NO DATA
OPERATION
STARTSEQUENCE
(ON HELICOPTERS EQUIPPED WITH GTCP36150 APU)
1 2 3 4BITE # DECODED BITE INFORMATION
OPERATION
POWER ON RESETSTART COMMAND RECEIVEDSTART FUEL AND EXCITER ONMAIN FUEL ONSTART FUEL AND EXCITER OFF90% RPMREADY TO LOADNORMAL OPERATIONDESU FAILURESPAREOVERTEMPERATURE RUNOVERSPEEDUNDERSPEEDFAIL TO ROTATELOW OIL PRESSURE
HIGH OIL TEMPERATURESHORTED OIL PRESSURE SWT/C SHORTEDEICAS LINES FAULTT/C OPEN CIRCUIT FAULTLOSS OF SPEED DATASPAREPOWER INTERRUPTRTL INDICATOR FAILUREMALF INDICATOR FAILUREMAX FUEL VALVE FAILUREHOT INDICATOR FAILUREMAIN FUEL VALVE FAILUREANTISURGE VALVE FAILURESTART CIRCUIT FAILURESTART FUEL/EXCITER FAILUREILLOGICAL SWITCH INPUTSFAIL TO LIGHTFAIL 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
T62T401
SAAA0323_2D
STARTSEQUENCE
FAULTSFAULT INDICATION
APU ELECTRONIC SEQUENCE UNIT FAULT INDICATION(ON HELICOPTERS EQUIPPED WITH T62T401 APU)
F
UNIT FAULT INDICATION(ON HELICOPTERS EQUIPPED WITH T62T401 APU)
Figure 2-5. Cabin Interior (Sheet 2 of 3)
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and the advisory will disappear. Power for the advisorycomes from the No. 1 dc primary bus through a circuitbreaker marked LIGHTS ADVSY .
2.10.3 Tai l Landing Gear. The tail landing gear is
below the rear section of the tail cone. It has a two-stageoleo shock strut, tailwheel lock system fork assembly,yoke assembly, and a wheel and tire. The fork assembly isthe attachment point for the tailwheel and allows the wheelto swivel 360. The tailwheel can be locked in a trailposi t ion by a TAILWHEEL switch in the cockpitindicating LOCK or UNLK . The fork is locked by anelectrical 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 essentialbus through a circuit breaker marked TAIL WHEELLOCK .
2.11 INSTRUMENT PANEL.
2.11.1 Instrument Panel. UH Engine and dual ightinstruments are on the one-piece instrument panel (Figure2-9 ). The panel is tilted back 30. The master warningpanels are mounted on the upper instrument panel below
the glare shield, to inform the pilot of conditions thatrequire 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 andChapter 4 f or BDHI , CREW CALL switch, FLAREswitch and ECM ANTENNA switch and countermeasureset 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), andtwo signal data converters (SDC). Those readings aresh o wn b y a scen d i n g an d d escen d i n g co l u mn s o f multicolored lights (red, yellow, and green) measuredagainst vertical scales which operate in this manner: thesegments 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 leveldecreases. 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, thesegments will light in normal progression and will remainon. When the rst segment above the red or amber range
FLOW CONTROL
ROTATE
G
MEDIUMLOW HIGH
OPTION II CABIN HEATER EJECTOR
SAAA0323_3
Figure 2-5. Cabin Interior (Sheet 3 of 3)
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goes on, all red-coded or amber-coded segments will gooff. These segments will remain off until the receivedsignal level indicates a reading at or within the red oramber range. At that time all red-coded or amber-codedsegments will go on and the scale display will either go onor go off in normal progression, depending upon the
received signal level . The CDU and PDUs containphotocells that automatically adjust lighting of the indica-tors with respect to ambient light. If any one of the threephotocells should fail, the lights on the vertical scales of the PDUs or CDU may not be at the optimum brightnessfor the ambient conditions. The DIM knob on the CDUcontains an override capability which allows the pilot tomanually 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 andtransmits the resulting signal data to the instrument dis-play. The No. 1 engine instruments on the CDU andcopilots PDU, receive signal data from the No. 1 SDC(CHAN 1). The No. 2 engine and main transmission
instruments on the CDU and pilots PDU, receives signaldata from the No. 2 SDC (CHAN 2). If either SDC fails,the corresponding CHAN 1 or 2 light will go on, and it islikely the pilots or copilots PDU and the correspondinginstruments will fail. Failure of a lamp power supplywithin an SDC will cause every second display light on theCDU to go off. Both SDCs receive % RPM R ; and %RPM 1 and 2 and % TRQ information from both engines.
SAAA0401
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
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Therefore if one SDC fails only one PDU will provide %RPM 1 and 2 and % TRQ for both engines.
2 .11.4 Cen tral Display Uni t. The CDU containsinstruments that display fuel quantity, transmission oiltemperature and pressure, engine oil temperature and pres-sure, turbine gas temperature (TGT), and gas generatorspeed (Ng) readings. Those readings are shown byascending and descending columns of multicolored lights(red, yellow, and green) measured against vertical scales.If the instrument contains low range turnoff (red or yellowlights below green lights) they will go off when the systemis 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 whenoperating above the green range. The operating ranges forthe different instruments are shown in Figures 5-1 and 5-2.Digital readouts are also installed on the TOTAL FUELquantity, TGT , and Ng gages.
2.11.4.1 Lamp Test System. The lamp test provides ameans of electrically checking all CDU scale lamps,digital readouts, and % RPM RTR OVERSPEED lightson the PDUs. When the PUSH TO TEST switch on theCDU is pressed, all CDU scale lamps should light, digitalreadouts should display 88 8 , and three RTR OVER-SPEED lights on the PDUs should be on.
2.11.4.2 Dim Control. The DIM control allows thepilot to set a desired display light level of the CDU andPDUs in accordance with the ambient light, or override theauto-dim sensors. If the auto-dim circuitry should fail ormalfunction, turn the DIM control fully clockwise toregain illumination of the CDU and PDUs.
2 .11.4.3 CDU and PDU Digi ta l Cont ro l. An ON ,OFF DIGITS control switch is on the CDU to turn on oroff the digital readout displays on the CDU and PDUs. If adigital processor fails, all digital displays will go off.
2.11.5 Pilots Display Unit. The PDU displays to thepilot engine power turbine speed ( % RPM 1 and 2), rotorspeed ( % RPM R ), and torque ( % TRQ ). Readings aresh o wn b y a scen d i n g an d d escen d i n g co l u mn s o f multicolored lights (red, yellow, and green) measuredagainst vertical scales. A TEST switch provides a meansof electrically checking all PDU scale lamps and digitalreadouts. When the TEST switch is pressed, all PDU scalelamps should light and digital readouts should display 188 .The % RPM indicators contain low range turnoff belowthe normal operating range. Three overspeed lights at thetop will go on from left to right when a corresponding ro-tor speed of 127%, 137%, and 142% is reached. Once alight is turned on, a latch prevents it from going off untilreset by maintenance. Power for the PDUs is from No. 1
WOW SWITCH FUNCTION ON GROUND IN FLIGHT
Backup Pump Automatic Operation Disabled (Except when APUaccumulator 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 continuousBIT (CBIT) monitors attitude sensor afterAFMP power up
Enabled Disabled
AFMS AFMP Power up BIT (PBIT) andInitiated BIT (IBIT)
Enabled Disabled
Table 2-1. Weight-On-Wheels (WOW) Functions
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NO.2
ENG SENSE SPLY
5 5 10
ESNTLDC
BATTBUS
FIRE DET
CONTR SRCH
20 55
DC ESNTL BUS
LIGHTS
SEC
PNL PWR CONTR
CONSOLE LT
LOWER
PILOT FLT
INSTR LT
WINDSHIELD ANTIICECOPILOT
PITOTHEAT
BLOWER
BRTOFF
BRTOFF
ON
ON ON
CTR
OFF
O OFF
SAAA0364_1C
A
MAIN
TEST
SHORT
SAFE
ARMED
CKPTNORMEMERG 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 BNO. 1 ENG OVSP NO. 2 ENG OVSPFIRE DETR TEST
1
2
AIR SOURCEHEAT / STARTFUEL PUMP
APU BOOST
FUEL PRIME APU
ENGINE
APU
ON ON ON ON
CARGO HOOK
ALL
APUCONTR FIRE EXTGH
ON
FIRE EXTGHRESERVE
OFF
OFF
OFF
OFF
OFF
OFF
RESET
OFF
RESET
OFF
RESET
OPEN
OFFPNL CONTR
FUELDUMPNO. 1 VOR / ILS CHIP
DC ESNTL BUS
2 5
2 5
2 5 5
2
2
57.5 5
ICSESSSJTSN
PILOT COPILOT VHF FM DET CONTR OUTBD
COMM SCTY SETNO. 1 FM UHF AM
UHFAM
CAUT / ADVSY
BACKUPHYD
HOISTCABLE
*ESSSJTSN
S HE AR I NB D
*NO.1
ENG
5 5
5 55
7.5
STABCARGOHOOK
PWR EMER
SASNO. 1ENG
TAILWHEEL
B OO ST S TA RT L OC K
PARKOFF
LOW
HI
UPPER
NON FLT
NO. 1 NO. 2ENG ANTIICE
ON
WINDSHIELDWIPER
VENT
BRTOFF
BRTOFF
ON ON
OFF
OFF
OFF
FF
28V #387
SPARELAMPS
OPEN
7.5
7.5
FORMATION LT
POSITIONLIGHTS
STEADY
ANTICOLLISIONLIGHTS
LOWER NIGHT
DAYDIM
BRT FLASH
UPPER
CABINDOME LT
WHITE
BLUE
HYDLEAK TEST
BACKUPHYD PUMP
RESET
TESTON
OFF
CARGOHOOK LT
ON
NAV LTS
IR
LIGHTEDSWITCHES
BRTOFF
GLARESHIELDLIGHTS
BRTOFF
CPLT FLTINST LTS
BRTOFF
543
2
1OFF
OFF
OFF
OFF
OFF
NORM
NORM
BOTH
AUTO
B L U E
W H I T E
O F F
TYPICAL
OFF
MED
OFF HION
HEATER
B
C
ON
OFF
PILOT
W AHRS
Figure 2-7. Upper Console (Sheet 1 of 3)
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SAAA0364_2C
(ON HELICOPTERS EQUIPPED WITHOUTHEATED CENTER WINDSHIELD)
B
MED
OFF HIFWD
HEATER
OFF
FWD/AFT
A
(ON HELICOPTERS EQUIPPED WITHOPTION 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 55 5
DC ESNTL BUS
LIGHTS
7.5
STAB
CARGO
HOOK
PILOT
TURN
PWR EMER
SASNO. 1ENG
TAILWHEEL SEC
BOOST START LOCK PNL PWR CONTR
C
ANTIICECOPILOT
PITOTHEAT
ON
ON
OFF
OFF
ON
OFF
PILOTWINDSHIELD
W/O AHRS
Figure 2-7. Upper Console (Sheet 2 of 3)
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SAAA0364_3
MAIN
RESET TEST TEST TEST
ON
EXT PWR BATT APU NO. 1 NO. 2
GENERATORS
TEST A TEST B OPER TEST A TEST BNO. 1 ENG OVSP NO. 2 ENG OVSPFIRE DETR TEST
1
2
AIR SOURCEHEAT / STARTFUEL PUMP
APU BOOST
FUEL PRIME APU
ENGINE
APU
ON ON ON ON
APUCONTR FIRE EXTGH
ON
FIRE EXTGHRESERVE
OFF
OFF
OFF
OFF
OFF
OFF
RESET
OFF
RESET
OFF
RESET
OFF
28V #387
SPARELAMPS
OPEN
FORMATION LT
POSITIONLIGHTS
STEADY
ANTICOLLISIONLIGHTS
LOWER NIGHT
DAYDIM
BRT FLASH
UPPER
CABINDOME LT
WHITE
BLUE
HYDLEAK TEST
BACKUPHYD PUMP
RESET
TESTON
OFF
CARGOHOOK LT
ON
NAV LTS
IR
LIGHTEDSWITCHES
BRTOFF
GLARESHIELDLIGHTS
BRTOFF
CPLT FLTINST LTS
BRTOFF
543
2
1
OFF
OFF
OFF
OFF
OFF
NORM
NORM
BOTH
AUTO
B L U E
W H I T E
O F F
PNL CONTR
NO. 1 VOR / ILS CHIP
DC ESNTL BUS
2 5
2 5
2 5
2
2
5
ICSESSSJTSN
PILOT COPILOT VHF FM DET OUTBD
COMM SCTY SETNO. 1 FM UHF AM
UHFAM
CAUT / ADVSY
BACKUPHYD
ESSSJTSN
INBD
7.5
7.57.5
DC ESNTL BUS
NO.1 NO.2
RATE ENG ENG SENSE SPLY
2 5 5 5 10
ESNTLDC
BATTBUS
FIRE DET
CONTR SRCH
5 5 20 55 5
LIGHTS
STABPILOTTURN
PWR
SASNO. 1ENG
TAILW HE EL SE C
BOOST START LOCK PNL PWR CONTR
7.5
MEDPARK
OFFLOW
HI
CONSOLE LT
UPPER LOWER
OFF HI
NON FLT PILOT FLT
INST LT
NO. 1 NO. 2ENG ANTIICE
WINDSHIELDCOPILOT
ANTIICECTR
ON
WINDSHIELDWIPER
PITOTHEAT
VENTBLOWER
BRTOFF BRTOFF
BRTOFF BRTOFF
ON
ONON ON
ON ON ON
PILOT
HEATER
OFF
OFF
OFF
OFF
OFF
OFF
OFF
OFF
FAN
PWR
ON
HTRCOOL TEMP CONT Q / F
ECS
ON
AIR COND
COOL WARM
OFF
OFF
OFF
EH
Figure 2-7. Upper Console (Sheet 3 of 3)
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STORES JETTISONEMERJETTALL JETT
INBD OUTBDBOTH BOTH
R R
L L
OFF ALL
ON
OFF
ON
OFF
VOL ICS
12
43
5HOT MIKE
OFF
COMM
1 2 3 4 5 AUX NAV
CONT
MBVOL
OFF
TESTHILO
TAILWHEEL
GYROERECT
TAIL SERVONORMAL
BACKUP
MISC
SW
FUEL BOOST PUMP CONTROL
ON
OFF
NO. 1PUMP
NO. 2PUMP
ON
OFF
TEST
CHAN
1
3 0 0 0 00
MAIN VOL PRESETGUARDMANUALBOTHOFF
ADF
TONESQUELCH
OFF ON
UHF
ON
OFF
ON
OFF
VOL ICS
12
43
5HOT MIKE
OFF
COMM
1 2 3 4 5 AUX NAV
CONT
PLAINC / RAD
MODE
DELAY
ON
POWER
OPLD
RV
1
23 4
5
6
ZEROI
ZE
KY58RCU
FILL12 3 54 6
P R E S S T O T
E S T
D IM P R E S S T O T
E S T
D IM TEST TEST/MON TOP
BOT
MASTER
TEST
OUTSTATUS
IDENT
MIC
T ES T A UD IO
P R E S S T O T
E S T
D IM
REPLY
CODE
M1 M2 M 3 / A MC
ANT
DIV
ON
ON
LIGHT
OUT
MODE 1 MODE 3 / A
NOGO
E M E R
N O
R M S T
B Y OFF
ALT KIT ANT
0 0 1 2 0 0
A B
MODE 4
ON
GO
F M 1 / F M 2 F M 2 / U H F
F M 2 / V H F F M 1 / V H F
F M 1 / U H F V H F / U H F
O F F
OUT
MAN SLEWUP
DN
TESTAUTO
CONTROL
ON
ON ON ON ON
ON
STABILATOR CONTROL
SAS 1 SAS 2 TRIM FPS
AUTO FLIGHT CONTROL
BOOST
RESET
OFF
RESET
RESET
POWER ON RESET
CPTR
TRIM
SAS 2
RGYR
ACCL
A / S
CLTV
GYRO
FAIL URE ADVIS ORY
Z E R O
H O L
D
RADTEST
FUELIND
FI
F
R A D I O R E T R A N S M I S S I O N
PLAINC / RAD
MODE
DELAY
ON
POWER
OPLD
RV
1
23 4
5
6
ZE
ROIZE
KY58RC
U
FILL12
3 54 6
1 2 3 FREQ
4 5 6
7 8 9 TIME
CLR StoENTHLd
0
L
L E
ERFOFST
MAN
12 3 4
56
CUE
PRESET
TEST
SQ ONSQ OF F L D
LDVZA
STOW
FUNCTIONRXMT
OFF
OFFLO
NORM HIIFM RF PWR
MODEHOM
SCFH
FHM
VOL
9
14 1 0 50
FM AM
MAN
PRE
DF
TR
OFF
VOL
SQDIS
TONE
EMER
LOAD
PRESET
CO
MM
PLAINC / RAD
MODE
DELAY
ON
POWER
OPLD
RV
1
23 4
5
6
ZER
OIZE
KY58RCU
FILL12
3 54 6
1 2 3 FREQ
4 5 6
7 8 9 TIME
CLR StoENTHLd
0
L
L E
ERFOFST
MAN
12 3 4
56
CUE
PRESET
TEST
SQ ONSQ OFF LD
LDVZA
STOW
FUNCTIONRXMT
OFF
OFFLO
NORM HIIFM RF PWR
MODEHOMSC
FHFHM
VOL
CURSOR
VALUE
T / RSILENT
STBY
OFF
ZERO(PULL)
VOLSQL
PREMAN
ALEECCM
EMER
1
2
34 5
6
KEY DATA
D S P L O F F
B R T
P N L O F F
I N I T
F I L L
C I K
A U D I O
K Y 1 0 0
O F L E B
R K
C T
P T M O D E P R E S E T
Z A L L ( P U L L )
1 2 3 4
6 R E M
M A N P W R
O F F
B A T
1 2 3
4 6 5
U
P ARKI N
G BRAKE
BATT &ESNTL DC
WARNDC AC &ESNTL BUS FUEL
PRIMEBATTBUS FIRE
SPLY CONVWARN
EXT PWRCONTR
BOOST CONTR EXTGH
APUUTILLTS APU
CONTRINST
CONTRINST
FIREDET
GENCONTR
CKPT
BATT
UTIL
BUS
BATT
BUS
50 5 5 5 5 5
5 5 5 5 5
0 0 0 0
FLARE CHAFF
DISPCONT
ARM MANPGRM
RIPPLE
FIRE
SAFE
OFF
ARM
P R E S
S T O
T E S T
D I M
LTRLEFT
LTRMID
LTRRIGHT
ABC1
DEF2
GHI3
JKL4
MNO5
PQR6
GPSLDG
LAT/ LONG
MGRSTEST
LAMPTEST
OFF
XTK/TKCKEY
GS/TKNAVM
PPDIST/BRG
TIME
WINDUTCDATA
WPTGT
DATUM
ROUTE
DISPLAY
NAV
MODE
P
/
P
R
STU7
VWX8
YZ*9
CLR #0
ENT(PAGE)
KYBD
F1
TGTSTR
INC(+)
DEC()
MALBRT
DIM
1 7 : B A ND O 0 3 0 MG 9 1GP S : M N AV : CG S : 1 1 7 KM / HRT K : 0 2 5 "
FLY TO EPESYS
STATTGTSTR
G
S
D
L
B
SAAA0385_1J
CABS
2
ALT/P/R
PGM
INCSEL
DECNXT
ADJ
OFF
ON
BIT
ACKDCLT
14PPGM
CPPGM
OP
BRT D / U
D IM L / R
CPLTDSPL POS
MODE+
MODE
FAIL
ON
D / U
L / R
BRT
DIMDSPL POS
PLT
14
DCLT
CHAFFDISPENSE GPSZEROIZE
+PWR SELF DSCRM
ONOFF
ONOFF AUDIOTEST
2
MAN
2182
500
ADF
TEST
TONE
VOLTAKECMD ADF
ANT
OFF
0 0 0 .0
DTM OR 12 PT
BLANK OR TACANOR 12 PT
AHRS
ALN
FAILSLAVE CCAL
FUNCMODE ENT
DG
NAVVOL
MB
ON
N
VA
C
A
Figure 2-8. Lower Console (Sheet 1 of 3) UH
TM 1-1520-237-10
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SAAA0385_2E
NAV VOL MB VOL
OFF
VOR / MBTEST
OFF
MB SENS
HI
LO
108.00
C
AUDIO
KILOCYCLESCW
TEST
VOICE
LOOP
TUNE
ADF
RCVR OFF LOOP
COMP ANT
2 9
80
90
L R
B
A
COMPASS
SLAVED
FREEPUSH TO
SET
+ +
W/O AHRS
Figure 2-8. Lower Console (Sheet 2 of 3) UH
TM 1-1520-237-10
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SAAA1304_2C
AUDIO
KILOCYCLESCW
TEST
VOICE
LOOP
TUNE
ADF
RCVR OFF LOOP
C OMP A NT
2 9
80
90
L R
ON
OFF
ON
OFF
VOL ICS
12
43
5HOT MIKE
OFF
COMM
NAV VOL MB VOL
OFF
108 00
VOR / MBTEST
OFF
MB SENS
HI
LO
TAILWHEEL
GYROERECT
TAIL SERVONORMAL
BACKUP
MISC
SW
9
14 1 0 50
FM AM
MAN
PRE
DF
TR
OFF
VOL
SQDIS
TONE
EMER
LOAD
PRESET
CO
MM
P R E S S T O T
E S T
D IM P R E S S T O T
E S T
D IM TEST TEST/MON TOP
BOT
MASTER
TEST
OUTSTATUS
IDENT
MIC
TEST AUDIO
OUT
P R E S S T O T
E S T
D IM
REPLY
CODE
M1 M2 M3/A MC RADTEST
ANT
DIV
IFF
ON
ON
LI
GHT
OUT
MODE 1 MODE 3 / A
NOGO
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
ON
GO
1 2 3 4 5 AUX NAV
CONT
FM 1 / FM 2 FM 2 / UHF
FM 2 / VHFFM 1 / VHF
FM 1 / UHF VHF / UHF
OFF
COMPASS
SLAVED
FREEPUSH TO
SET
+ 0 0 +
CHAN
1
3 0 0 0 00
MAIN VOL PRESETGUARDMANUALBOTHOFF
ADF
TONE
SQUELCH
OFF ON
UHF
ON
OFF
ON
OFF
VOL ICS
12
43
5HOT MIKE
OFF
COMM
1 2 3 4 5 AUX NAV
CONT
3 0 6 0
FLARE ARM CHAFF
DISPCONT
ARM
MAN PGRMRIPPLE
FIRE
+PWR SELF DSCRM
ONOFF
ONOFF AUDIOTEST
CHAFFDISPENSE
SAFE
FUELIND
OUT
FUEL BOOST PUMP CONTROL
ON
OFF
NO. 1PUMP
NO. 2PUMP
ON
OFF
MAN SLEW
UP
DN
TEST
AUTOCONTROL
ON
ON ON ON ON
ON
STABILATOR CONTROL
SAS 1 SAS 2 TRIM FPS
AUTO FLIGHT CONTROL
BOOST
RESET
OFF
RESET
RESET
POWER ON RESET
CPTR
TRIM
SAS2
RGYR
ACCL
A/ S
CLTV
GYRO
DEFABC
GHJ KLM NPQ
RST UVW XYZ
LTR
W4
1
5 E6
3M2
USE 0 CLR
FACK
BRT
MRK
STR
BIT
DEST
7 S 8 9
IINS
DESTINS
POS
STR
TCN
UPDTNAV
NORM
FAST
OFF
TEST
CALATTD
_
P ARKI N
G BRAKE
AN/ARC201
AN/ALQ162
COVER
FAILURE ADVISORY
P R E S S T O
T E S T
D I M
A B
Z E R
O
H O L D
RADIO RETRANSMISSION
TEST
ALQ162
NOGO
CWTHRT
CWJAM
ALQ156
CMJAM
ALQ144
IRCMINOP
CMINOP
PLAINC / RAD
MODE
DELAY
ON
POWER
OPLD
RV
1
23 4
5
6
ZEROIZE
KY58RCU
FILL12
3 54 6
PLAINC / RAD
MODE
DELAY
ON
POWER
OPLD
RV
1
23 4
5
6
ZEROIZE
KY58RCU
FILL12
3 54 6
VHFFM NO. 1
IFM CONTROL
AN/ARC201
PLAINC / RAD
MODE
DELAY
ON
POWER
OPLD
RV
1
23 4
5
6
ZEROIZE
KY58RCU
FILL12
3 54 6
VHFFM NO. 2
BATT &ESNTL DCWARNDC AC &
ESNTL BUS FUELPRIME
BATTBUS FIRE
SPLY CONVWARN
EXT PWRCONTR
BOOST CONTR EXTGH
APUUTILLTS APU
CONTRINST
CONTRINST
FIREDET
GENCONTR
CKPT
BATT
UTIL
BUS
BATT
BUS
50 5 5 5 5 5
5 5 5 5 5
CABS
2
COVER
Figure 2-8. Lower Console (Sheet 3 of 3) EH
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SAAB0823_1B
0
2
4
6
8
10
12
14
1 2
TOTAL FUEL
PUSH
TO TESTOFF
DIGITSDIM
ON
QTYLB X 100
TEMPC X 10
PRESSPSI X 10
TEMPC 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 20
20
40
60
80
100
120
140 140
120
100
80
60
40
20
0
100150
200
25020
50
KNOTS
VERTICAL SPEED
1000 FT PERMIN
DOWN
UP
5
5
0
0 123
4567
89
12 4
6
421
10
0
10
20
3040
DN
O F
F
STABPOS
DEG
0O
10O
20 O
30 O
40 O
KIASLIMIT150100806045
STAB
DEG
1 2 3 4 30 0
HDG CRS
N
W
E
S
3
6
1 2 1 5
2 1
2 4
3 0 33
KM COURSE
HDG
N A V
2
1
2
1
MODE SEL
DPLRVORILS
VORILS
BACKCRS
BACKCRS
FMHOME
FMHOME
NORMALTR
PLTCPLT
NORMALTR
ADFVOR
TURNRATE CRSHDG VERTGYRO BRG2
L
H
5
10
15
FT X 100
LO
ABS ALT
FEET HILO
OFFPUSH
0
1
2
SET SET
#1 FUEL LOW #1 GEN #2 GEN #2 FUEL LOW
#2 GEN BRG#1 GEN BRG
#1 ENGINEOIL PRESS
#1 CONV #2 CONV #2 ENGINEOIL PRESS
#2 ENGINEOIL TEMP
DC ESSBUS OFF
AC ESSBUS OFF
#1 ENGINEOIL TEMP
CHIP#1 ENGINE
BATT LOWCHARGE
BATTERYFAULT
CHIP#2 ENGINE
#2 FUELFLTR BYPASS
GUST#1 FUELFLTR BYPASS
#1 OILFLTR BYPASS
#2 OILFLTR BYPASS
#1 PRISERVO PRESS
IRCMINOP
#2 HYDPUMP
#2 PRISERVO PRESS
#1 TAILRTR SERVO
TAIL ROTORQUADRANT
MAIN XMSNOIL TEMP
INT XMSNOIL TEMP
TAIL XMSNOIL TEMP
APU OILTEMP HI
TRIM FAILSAS OFFSTABILATORBOOST SERVOOFF
LFT PITOTHEAT IFF
RT PITOTHEAT
CHIP INPUTMDLLH
CHIPINT XMSN
CHIPTAIL XMSN
CHIP INPUTMDLRH
CHIP ACCESSMDLRH
APUFAIL
CHIP MAINMDL SUMP
CHIP ACCESSMDLLH
MR DEICEFAIL
MR DEICEFAULT
TR DEICEFAIL
ICEDETECTED
BACKUPRSVR LOW
#2 RSVRLOW
#1 RSVRLOW
MAIN XMSNOIL PRESS
#2 ENGANTIICE ON
BACKUPPUMP ON
#2 TAIL RTRSERVO ON
#2 ENG INLETANTIICE ON
PRIME BOOSTPUMP ON
LDG LT ON
HOOK ARMED
EXT PWRCONNECTED
#1 ENG INLETANTIICE ON
APU GEN ON
CARGOHOOK OPEN
PARKINGBRAKE ON
APU ACCUMLOW
APU ON
#1 ENGANTIICE ON
BRT /
TEST
#2 ENGINESTARTER
FLT PATHSTAB
OFF
ON
ENGINEIGNITION
NONSECURERADIOSWILLNOTBEKEYEDWHENUSINGANYSECURERADIOORTHEINTERCOMFOR CLASSIFIEDCOMMUNICATIONS
RADIOFM1SWNO.1
UHF2
VHF3
FM24 5
VORLOCAUX
MBADFNAV
ICS IDENT
RAD ALT
DIMMING NVG DIMMING
MAWRN CAUT/ADVSY
TO TEST
ALT
1000 FT100 FT
IN. HG
1
2
2 9 9 0
#1 ENGINE #2 ENGINEPRESS PRESS
LOCKPITCH BIAS
FAIL
#1 ENGINESTARTER
RADIO CALL00 0 00
22
2325
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 ENGOUT
#2 ENGOUT
LOW ROTORRPM
MASTER CAUTIONPRESS TO RESET
FIRE
CMD ATT
30 30
30 30
NAV
ROLL PITCH
C LI MB
D I VE
G S
GA DH MB
DIM
#1 HYDPUMP
* AUX FUEL
SEARCH LT* * ON
CODEOFF
% RPM % TRQ
FUEL XMSN ENG
B
DPLR
NOFLOW
VENTFAIL IMBAL
EMPTYEMPTYINBDOUTBD
L
NOFLOW
VENTOVFL
EMPTYEMPTYOUTBDINBD
R
A UX FU EL Q TY LB STEST/ RESET
XFERMODEAUTO
MAN
OFF
LEFT
RIGHT
OTH
INBD
OUTBD
B
MA N X FE R X F ER F R O M P R ES S
OUTBD
INBD
OFF
ALL
28 28
RST
MODE
ST/SP
12:34
SET
LC6
ADV
CHRONOMETER
55
12 123
4567
8910
11
605
10
15
20
2530
35
40
45
50
55
CB
C
DPLRGPS
29 29
MSGWPT
NOGPSHOLD
RAIMAPR
Figure 2-9. Instrument Panel (Sheet 1 of 4) UH
TM 1-1520-237-10
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SAAA0516_3C
0
2
4
6
8
10
12
14
1 2
TOTAL FUEL TO TEST OFFDIGITS
DIM ON
QTYLB X 100
TE MP P RE SSPSI X 10
TEMPOC 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 RTROVERSPEED
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 20
20
40
60
80
100
120
140 140
120
100
80
60
40
20
0
#1 ENGOUT
#2 ENGOUT
LOW ROTOR
RPM
MASTER CAUTION
PRESS TO RESETFIRE
VERTICAL SPEED
1000 FT PERMIN
DOWN
UP
5
5
0
0 123
4567
89
12 4
6
42
1
10
0
10
20
3040
DN
O F
F
STABPOS
DEG
CMD ATT
30 30
30 30
NAV
ROLL PITCH
C LI MB
D I VE
G S
0O
10O
20 O
30 O
40 O
KIASLIMIT150100806045
STAB
DEG
1 2 3 4 30 0
HDG CRS
N
W
E
S
3
6
1 2 1 5
2 1
2 4
3 0 3 3
KM COURSE
HDG
N A V
2
1
2
1
MODE SEL
IINS
IINS
VORILS
VORILS
BACKCRS
BACKCRS
FMHOME
FMHOME
NORMALTR
PLTCPLT
NORMALTR
ADFVOR
TURNRATE
CRSHDG
VERTGYRO
BRG2
L
H
5
10
15
FT X 100
LO
ABS ALT
FEET HILO
OFFPUSH
0
1
2
SET SET
#1 FUEL LOW #1 GEN #2 GEN #2 FUEL LOW
#2 GEN BRG#1 GEN BRG
#1 ENGINEOIL PRESS #1 CONV #2 CONV
#2 ENGINEOIL PRESS
#2 ENGINEOIL TEMP
DC ESSBUS OFF
AC ESSBUS OFF
#1 ENGINEOIL TEMP
CHIP#1 ENGINE
BATT LOWCHARGE
BATTERYFAULT
CHIP#2 ENGINE
#2 FUELFLTR BYPASS
GUST#1 FUELFLTR BYPASS
#1 OILFLTR BYPASS
#2 OILFLTR BYPASS
#1 PRISERVO PRESS
#1 HYDPUMP
#2 HYDPUMP
#2 PRISERVO PRESS
#1 TAILRTR SERVO
TAIL ROTORQUADRANT
MAIN XMSNOIL TEMP
INT XMSNOIL TEMP
TAIL XMSNOIL TEMP
APU OILTEMP HI
TRIM FAILSAS OFFSTABILATORBOOST SERVOOFF
LFT PITOTHEAT IFF
RT PITOTHEAT
CHIP INPUTMDLLH
CHIPINT XMSN
CHIPTAIL XMSN
CHIP INPUTMDLRH
CHIP ACCESSMDLRH
APUFAIL
CHIP MAINMDL SUMP
CHIP ACCESSMDLLH
MR DEICEFAIL
MR DEICEFAULT
TR DEICEFAIL
ICEDETECTED
BACKUPRSVR LOW
#2 RSVRLOW
#1 RSVRLOW
MAIN XMSNOIL PRESS
#2 ENGANTIICE ON
BACKUPPUMP ON
#2 TAIL RTRSERVO ON
#2 ENG INLETANTIICE ON
PRIME BOOSTPUMP ON
LDG LT ON
EXT PWRCONNECTED
#1 ENG INLETANTIICE ON
APU GEN ON
AIR CONDON
PARKINGBRAKE ON
APU ACCUMLOW
APU ON
#1 ENGANTIICE ON
BRT /
TEST
#2 ENGINESTARTER
FLT PATHSTAB
OFF
ON
ENGINEIGNITION
NONSECURERADIOSWILLNOTBEKEYED
SYSTEMSSELECT
INTERCOMFOR CLASSIFIEDCOMMUNICATIONS
RADIOFM1SWNO.1
UHF2
VHF3
FM24 5
VORLOCAUX
MBADFNAV
ICS IDENT
RAD ALT
DIMMING NVG DIMMING
MAWRN CAUT / ADVSY
TO TEST
ALT
1000 FT100 FT
IN. HG
1
2
2 9 9 0
#1 ENGINE #2 ENGINEPRESS PRESS
LOCKANTENNA
EXTENDED
#1 ENGINESTARTER
RADIO CALL
00 0 00
IRCMINDP AUX FUEL
SEARCH LTON
CABIN HEATON
ANTENNARETRACTEDDIM
FLARE
3 6
9
1 2
1 5 1 8
0
2 1 2 4
2 7 3 0
3 3
0 0 0 0K N
CREWCALL
WHENUSINGANYSECURERADIOORTHE
DG
IINS
HDG
VG
IINS
ATT
2731
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
116
1
2
3
33 32 12 33
30 29 26 2423 20
5
4
PUSH
GA DH MB
100150
200
25020
50
KNOTS
CODEOFF
OC X 10
% TRQ% RPM
FUEL XMSN ENG
19
34 34
12 123
4567
8910
11
605
10
15
20
2530
35
40
45
50
55
C
Figure 2-9. Instrument Panel (Sheet 3 of 4) EH
TM 1-1520-237-10
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SAAA0516_4E
HDG NAV ALT
HDG
ON
NAV
ON
ALT
ON
CIS MODE SEL
MODE SEL
DPLR
DPLR
VORILS
VORILS
BACKCRS
BACKCRS
FMHOME
FMHOME
NORMALTR
PLTCPLT
NORMALTR
ADFVOR
TURNRATE
CRSHDG
VERTGYRO
BRG2
RADIO CALL00 0 00
M A
D A YN I G H T
B R I L
#1 ENGOUT
#2 ENGOUT
LOW ROTORRPM
MASTER CAUTIONPRESS TO RESET
FIRE
CMD ATT
30 30
30 30
NAV
ROLL PITCH
C LI MB
D I VE
G S
1 2 3 4 30 0
HDG CRS
N
W
E
S
3
6
1 2 1 5
2 1
2 4
3 0 3 3
KM COURSE
HDG
N A V
2
1
2
1
100
10
20
3040
DN
O F
F
STABPOS
DEG
0O
10O
20O
30 O
40O
KIASLIMIT150100806045
STAB
DEG
RAD ALT
DIMMING
TEST RTROVERSPEED
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 20
20
40
60
80
100
120
140 140
120
100
80
60
40
20
0
% RPM % TRQ
100150
200
25020
50
KNOTS
VERTICAL SPEED
1000 FT PERMIN
DOWN
UP
.5
.5
1000 FT100 FT
IN. HG
1
20
2 9
0 123
4567
89
12 4
6
421
9 0
L 5
10
15
FT X 100
LO
ABS ALT
FEET HILO
OFFPUSH
0
1
2
SET SET
TO TEST
ALT
POWERON
TEST
TESTIN
PROGRESS
MODE
AUTOT
L
M
BLADE DEICE TEST
NORM
SYNC 1SYNC 2
OATEOT
PWRMAIN TAIL
RTR RTR
ON
OFF
PRESSTO
TEST
BLADE
DEICE
IRCM
M A N
U A L
L WG 9 / m 3
T L
M H
0 2 5 5 10 1 5
2 0 F A I L
OFF
1. RADAR ALTIMETER2. BAROMETRIC ALTIMETER3. VERTICAL SPEED INDICATOR4. MASTER WARNING PANEL5. VERTICAL SITUATION INDICATOR6. HORIZONTAL SITUATION INDICATOR7. AIRSPEED INDICATOR8. STABILATOR POSITION PLACARD9. STABILATOR POSITION INDICATOR
10. CIS MODE SELECTOR11. VSI / HSI MODE SELECTOR12. RADIO CALL PLACARD13. PILOTS DISPLAY UNIT14. CLOCK
GA DM MB
RETRACT
OFF
EXTEND OFF
ON
P OW ER P US H FO RSTANDBY
STATUS
TEST
FLARE
15. BLADE DEICE CONTROL PANEL16. BLADE DEICE TEST PANEL17. ICE RATE METER
18. ALQ144 INFRARED COUNTERMEASURE
19. ASE STATUS PANEL
21. CENTRAL DISPLAY UNIT22. RADAR WARNING INDICATOR23. ECM ANTENNA SWITCH24. ENGINE IGNITION SWITCH25. BEARING DISTANCE HEADING INDICATOR26. CREW CALL SWITCH / INDICATOR27. SYSTEM SELECT PANEL28. CAUTION / ADVISORY PANEL29. FLARE DISPENSE SWITCH30. RADIO SELECT PLACARD31. SECURE RADIO WARNING PLACARD32. NVG DIMMING CONTROL PANEL33. RADAR ALTIMETER DIMMING
1 CHAN 2
PRESSPSI 5 10
TEMP SPEEDOIL 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
ALQ162
CWTHRT
NOG0
CWJAM
ALQ156
CMJAM
CMINOP
ALQ144
IRCMINOP
ALQ135
OVERTEMP
RDRINOP
20. ALQ156 COUNTERMEASURE PANEL
ASE
34. FORWARD COCKPIT AIRBAG
12 123
4567
8910
11
60
5
10
15
20
2530
35
40
45
50
55
C
Figure 2-9. Instrument Panel (Sheet 4 of 4) EH
TM 1-1520-237-10
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2.13.1.4 Emergency Vertical Release Lever. Theemergency vertical release lever permits the seat to drop tothe lowest adjustment point for tilting. The emergencyvertical 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 pushingdown on the foot operated pedal.
2.13.1.5 Seatbelts. The pilots and copilots seats eachcontain a shoulder harness, seatbelt, and a crotch strapconnected to a common buckle assembly. All belts andstraps have adjustment ttings. The attachment buckle hasa single-point release that will be common in congurationon the pilots and copilots seats; they may be of the liftlever or rotary release conguration. When the lanyard ispulled or the release is turned, all belts and straps willrelease simultaneously.
2 .1 3. 2 P ro te ct iv e A rm or. Armor pro tec t ion i s
provided for the body of the pilot and copilot against 7.62mm 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 releaselever at the front of each panel permits sliding the panel aftto allow rapid entrance and exit, as well as freedom of movement for the seat occupant. The CABS side air bagmodules 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 increasethe probability and severity of injury.
Two outward facing seats (Figure 2-10 ), one on eachside of the helicopter at the front of the cabin, are for thecrew chief/gunners. Each seat faces a window. Each seat isa cable-supported steel tube assembly with a re-resistant,high strength fabric seat and backrest containing two lowerenergy 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 rotaryrelease buckle. The shoulder harness is connected toinertia reels on the seat back and bottom. This gives thewearer freedom to move about his station. On helicoptersequipped with improved crewchief/gunners restraintsystem, the restraint system is equipped with a single ac-
tion rotary release buckle with a guard. A release platemust be pressed to allow rotation of release, preventinginadvertent handle rotation from contact with equipment,etc. The inertia reel lock control is replaced by a shorterpush/pull manual locking control. Push in and the inertiareel is manually locked in place. When the control ispulled 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 increasethe probability and severity of injury.
UH In addition to crew chief and gunner seats, troopseats may be installed for up to 12 persons. Each troop
seat has a belt and shoulder harness for body restraint. Thebacks and seat pans are attached through cables to thecabin ceiling and through cables and rods to seat ttingsinstalled in the oor. The seats may be installed in anyquantity from 1 to 12. Each seat contains two lower energyattenuators designed to reduce personnel injury in a crash.In Row 1, do not install a passenger/troop seat in the mostforward center position directly behind the cockpit centerconsole. When seats are removed from the cabin andstowed in the stowage compartment, adjustments must bemade for weight and balance using data in Figures 6-3 and6-12.
2.14.1 Troop Seatbelt Operation. UH
1. Extend shoulder strap and attach shoulder strapttings to buckle.
2. Extend lap belt and place across body.
3. Place lap belt tting into buckle and makecertain of positive lock.
4. Adjust lap belt tension and shoulder straps fora comfortable t.
2 .14.2 DF and ECM Opera to rs Seat s. EH Theseats are similar to the pilots and copilots seats exceptthat armored wing protection is not provided.
2.14.3 Observers Seat. EH The observers seat(Figure 2-6) is identical to a troop seat. It is installedbehind, and to the right, of the DF operators seat.
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TROOPCOMMANDERSSEAT
CREW CHIEF / GUNNERSSEAT
TROOPSEAT(TYPICAL)
LEFTGUNNERSSEAT
SAAA0407
Figure 2-10. Troop Seats UH
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container are discharged into the corresponding compart-ment. When the FIRE EXTGH switch is placed toRESERVE after an ENG EMER OFF lever has beenpulled, the contents of the opposite re extinguishercontainer are discharged into the selected compartment.The contents of the re extinguisher container dischargeinto the compartment of the last lever pulled.
2.15.6 Crash-Actuated System. A crash-actuatedsystem is part of the re extinguisher system. An omnidi-rectional inertia switch is hard-mounted to the airframe tosense crash forces. Upon impact of a crash of 10 Gs ormore , the swi tch wi l l au tomat ica l ly re bo th reextinguishing containers into both engine compartments.Electrical power is supplied from the battery utility busthrough a circuit breaker on the lower console, markedFIRE EXTGH .
2.15.7 Hand-Operated Fire Extinguishers.
WARNING
Exposure to h igh concent ra t ions of extinguishing agent or decompositionproducts should be avoided. The liquidshould not be allowed to contact the skin;i t c o u l d c a u s e f r o s t b i t e o r l o wtemperature burns.
a. UH One hand-operated re extinguisher (Figure9-1 ) is mounted on the cabin wall left of the gunners seat.A second re extinguisher is on the copilots seat.
b. EH Four hand-operated portable re extinguishersare installed. One mounted on the right gunner window,
one on the left pilot seat, one on the DF operator seat, andone on the ECM operator seat.The extinguishers are heldin place by a quick-release spring.
2.16 CRASH AXE.
UH One axe is installed between the pilots seats in thecabin.
2.17 FIRST AID KITS.
a. UH Three rst aid kits are installed, two on the back of the left pilot seat and one on the back of the right pilotseat.
b. EH Five rst aid kits are installed. One on the back of the right pilot seat, two on the back of the left pilot seat,one on the back of the DF operator seat, and one on theback of the ECM operator seat.
2.18 COCKPIT AIR BAG SYSTEM.
Four Cockpit Air Bag System (CABS) units are in-stalled in the helicopter. Two forward air bag modules areinstalled on the glare shield. Two lateral air bag modulesare installed on the stationary wing panels (one on theright side and one on the left side). An Electronic CrashSensor Unit (ECSU) is attached to the mounting traylocated under the copilots seat. The CABS providesenhanced supplemental crewmember protection andreduces the likelihood of head strike injuries duringsurvivable crash events. The ECSU detects a crash event
and initiates deployment of the air bags. Power to operatethe ECSU is provided by the battery bus through a circuitbreaker marked CABS .
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Section III ENGINES AND RELATED SYSTEMS
2.19 ENGINE.
CAUTION
Use of the T700-GE-701D hydromechani-cal unit and digital electronic control unitare prohibited on the UH-60L. Use of the701D controls on the UH-60L can causesignicant damage to the powertrain.
NOTE
Th e T7 0 0 -GE-7 0 1 D/ CC i s a d ro p - i nreplacement for the T700-GE-701C engineon the UH-60L helicopter. The 701D/CCconsists of a T700-GE-701D core controlledby a T700-GE-701C hydromechanical unitand digital electronic control unit. Engineperformance is the same between the 701D/ CC and the 701C. Therefore, performancecharts used with the 701C are also validwith the 701D/CC.
The T700 engine (Figure 2-11) , is a front drive, tur-boshaft engine of modular construction. One is mountedon the airframe at either side of the main transmission. Theengine is divided into four modules: cold section, hot sec-
tion, power turbine section, and accessory section.
2.19.1 Cold Section Module. The cold section moduleincludes the inlet particle separator (IPS), the compressor,the output shaft assembly, and line replaceable units(LRUs). The IPS removes sand, dust, and other foreignmaterial from the engine inlet air. Engine inlet air passesthrough the swirl vanes, spinning the air and throwing dirtout by inertial action into the collector scroll, after which itis sucked through by the engine-driven blower anddischarged overboard around the engine exhaust duct. Thecompressor has ve axial stages and one centrifugal stage.There are variable inlet guide vanes and variable stage 1
and stage 2 vanes. LRUs mounted on the cold sectionmodule are the 700 electrical control unit (ECU) or
701C 701D/CC digital electronic control (DEC), anti-icing and start bleed valve, 700 history recorder or
701C 701D/CC history counter, ignition system, andelectrical cables.
2.19.2 Hot Section Module. The hot section moduleconsists of three subassemblies; the gas generator turbine,stage 1 nozzle assembly, and combustion liner. LRUs onthe hot section module are 701C 701D/CC ignitors and
700 primer nozzles and ignitors. The gas generatorturbine consists of a gas generator stator assembly and atwo-stage air cooled turbine rotor assembly which drivesthe compressor and the accessory gear box. Stage 1 nozzleassembly contains air cooled nozzle segments. The nozzleassemblies direct gas ow to the gas generator turbine.The combustion liner is a ring-type combustor cooled byair ow from the diffuser case.
2.19.3 Power Turbine Section Module. The powerturbine section module includes a two-stage power turbine,exhaust frame, and the shaft and C-sump assembly. TheLRUs mounted on the power turbine section module arethe thermocouple harness, torque and overspeed sensor,and Np ( % RPM 1 or 2) sensor.
2.19.4 Accessory Section Module. The accessorysection module includes the top mounted accessory gearbox and a number of LRUs. The LRUs mounted on themodule are the hydromechanical unit (HMU), enginedriven boost pump, oil lter, oil cooler, alternator, oil andscavenge pump, IPS blower, fuel lter assembly, chipdetector, oil lter bypass sensor, radial drive shaft, fuelpressure sensor, and oil pressure sensor.
2.20 ENGINE FUEL SUPPLY SYSTEM.
The engine fuel supply system consists primarily of thelow-pressure engine driven boost pump, fuel lter, fuellter bypass valve, fuel pressure sensor, hydromechanicalunit (HMU), 700 pressurizing and overspeed unit(POU), or 701C 701D/CC overspeed and drain valve(ODV).
2.20.1 Engine Driven Boost Pump. A low pressuresuction engine driven boost pump is installed on the frontface of the engine accessory gear box. It assures that theairframe fuel supply system is under negative pressure,lessening the potential of re i