-
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
-
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 lossof 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 flush the affected area with clean water.
Continuewashing until medical assistance arrives. Neutralize any
spilled electrolyte by thoroughly flushing 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 defined 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 firing, when flightsexceed 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 allweapons
in a direction offering the least exposure to personnel and
property in case of accidental firing. Do not walk infront of
weapons. SAFE the machinegun before servicing. To avoid potentially
dangerous situations, follow all proceduralwarnings in text.
TM 1-1520-237-10
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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 ifyou 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
flares 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 flares will
provide inadequate IR countermeasures capability and will
significantly 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 identification) and
crew coordination exercises before flightsince field of regard can
be restricted by aviator worn mission equipment. The user must
strictly adhere to proper crewcoordination procedures during switch
identification.
Prior to flight, the user must perform control sweeps to ensure
there are no flight control interference problems with aviatorworn
gear. If a restriction is found, the interfering gear must be
adjusted/moved to eliminate the restriction.
TM 1-1520-237-10
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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:
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Operators Manualfor
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 theseprocedures, please let us know. Mail
your letter or DA Form 2028 (Recommended Changes toPublications and
Blank Forms), located in the back of this manual, directly to:
Commander, USArmy Aviation and Missile Command, ATTN:
AMSAM-MMC-MA-NP, Redstone Arsenal, AL35898-5000. A reply will be
furnished to you. You may also send in your comments
electronicallyto our E-mail address: [email protected] or by
fax 256-842-6546/DSN 788-6546. For theWorld Wide Web use:
https://amcom2028.redstone.army.mil. Instructions for sending
anelectronic 2028 may be found at the back of this manual
immediately preceding the hard copy2028.
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, as
amended,Title 50, U.S.C., App. 2401 et seq. Violation of these
export laws are subject to severe criminalpenalties. 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, USArmy
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.
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 HEADQUARTERSDEPARTMENT 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
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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
TM 1-1520-237-10
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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
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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
TM 1-1520-237-10
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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 ofequipment.
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-60Ahelicopters. The primary
mission of this helicopter is thatof tactical transport of troops,
medical evacuation, cargo,and reconnaissance within the capabil i t
ies of thehelicopter. The observance of limitations,
performance,and weight and balance data provided is mandatory.
Theobservance of procedures is mandatory except when
modification is required because of multiple emergencies,adverse
weather, terrain, etc. Your flying experience isrecognized and
therefore, basic flight 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 flightcrews 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,figures, 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 flight 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.
TM 1-1520-237-10
1-1
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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
illustration. 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
beidentified.
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 andconfiguration within the manual.
Designator symbolsprecede procedural steps in Chapters 8 and 9. If
the mate-rial applies to all series and configurations, 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 dragconfiguration 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 ofaccomplishment. The word may is
used to indicate an ac-ceptable method of accomplishment.
TM 1-1520-237-10
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CHAPTER 2
AIRCRAFT AND SYSTEMS DESCRIPTION AND OPERATION
Section I AIRCRAFT
2.1 GENERAL.
This chapter describes the UH-60A, UH-60L, and EH-60A
helicopters systems and flight controls. Thefunctioning of
electrical and mechanical components issimplified 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/fiberglass. 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 oftwo 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-fied by replacing
the T700-GE-700 with T700-GE-701D/CC engines. This modification
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 modified 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 modified UH-60A (Figure2-1) with a
crew of four. The mission equipment consistsof electronic systems
with modifications that will ensurethat the mission requirements
are met. The EH-60Asystem includes air conditioning, helicopter
survivabilityequipment, and avionics equipment. An
electronicscompartment 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 finder/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.
TM 1-1520-237-10
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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 significantly 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 andcabin. The cockpit (Figure 2-4)
is at the front of thehelicopter with the pilots sitting in
parallel, each with a setof flight 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 floor. Two stowage
compartments(Figure 6-12), at the rear of the cabin over the main
fueltanks, are for flyaway 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 fixed 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, fire
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. Theconsole
is arranged with communicat ion panels ,navigational panels, and
flight 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 gearconsisting of
two main gear assemblies and a tailwheelassembly. The landing gear
permits helicopter takeoffs andlandings on slopes in any direct
ion. The systemincorporates 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 ofselected
systems (Table 2-1). The switch is deactivatedwhen the weight of
the helicopter is on the landing gear.On helicopters equipped with
ESSS fixed provisions, aWOW 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 andlower stage combine to absorb loads up to 39 fps
(about11.25 Gs).
2.10.2 Wheel Brake System. 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
TM 1-1520-237-10
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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 DEFLECTOR8. FLARE DISPENSER9. CHAFF DIPENSER
10. 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 BOTTLES21. 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)
TM 1-1520-237-10
2-3
-
SAAA0403_2C
27 28 29 30
313233343536373839
40
4142
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)
TM 1-1520-237-10
2-4
-
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
20O
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
TM 1-1520-237-10
2-5
-
TURNINGRADIUS41 FEET
7.7 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 20O. UPPERTIP PATH PLANE IS 16 FEET 10
INCHESABOVE GROUND LEVEL
*
SAAA0402
Figure 2-3. Turning Radius and Clearance
TM 1-1520-237-10
2-6
-
SAAB0821_1
2524
CHEC
K LIST
STOW
AGE
DATA
& MA
PCHECK LIST
DATA & MAPSTOWAGE
1. UPPER CONSOLE 2. PILOTS COCKPIT UTILITY LIGHT 3. FREEAIR
TEMPERATURE GAGE (ON
HELICOPTERS 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)
TM 1-1520-237-10
2-7
-
28
30
33
34
35
36
29
32
31
26 27
CHEC
K LIST
STOW
AGE
DATA
& MA
PCHECK LIST
DATA & 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 CONTROLPANELCREW 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)
TM 1-1520-237-10
2-8
-
SAAA0323_1E
ON HELICOPTERS EQUIPPED WITHAUXILIARY ELECTRICAL CABIN
HEATER
GUST LOCK CONTROL
APU ACCUMULATOR(LOOKING UP)
(LOCATED BELOW LEFT GUNNERS WINDOW)
GUST LOCKRELEASE BUTTON
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)
TM 1-1520-237-10
2-9
-
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 PRESSUREHIGH 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)
TM 1-1520-237-10
2-10
-
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 Tail Landing Gear. The tail landing gear isbelow 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
trailposition 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 flightinstruments
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 ofthe EH-60A is
as shown on Figure 2-9. Refer to Chapter 3for description and
operation of systems switch panels andChapter 4 for 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 areshown by ascending and
descending columns ofmulticolored lights (red, yellow, and green)
measuredagainst vertical scales which operate in this manner:
thesegments will light in normal progression and remain on asthe
received signal level increases. Those scales will go offin 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 first 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)
TM 1-1520-237-10
2-11
-
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
thereceived 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 ofthe 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
transmissioninstruments 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
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 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 888, 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 Digital Control. 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 areshown by ascending and descending
columns ofmulticolored 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
TM 1-1520-237-10
2-13
-
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 ANTIICE
COPILOT
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
SHEAR INBD
*NO.1
ENG
5 5
5 55
7.5
STABCARGOHOOK
PWR EMER
SASNO. 1ENG
TAILWHEEL
BOOST START LOCK
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
1
OFF
OFF
OFF
OFF
OFF
NORM
NORM
BOTH
AUTO
BLUE
WHITE
OFF
TYPICAL
OFF
MED
OFF HION
HEATER
B
C
ON
OFF
PILOT
W AHRS
Figure 2-7. Upper Console (Sheet 1 of 3)
TM 1-1520-237-10
2-14
-
SAAA0364_2C
(ON HELICOPTERS EQUIPPED WITHOUTHEATED CENTER WINDSHIELD)
B
MED
OFF HI
FWD
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
ESNTLBUS
BATTBUS
FIRE DET
CONTR SRCH
5 5 20 55 5
DC ESNTL BUS
LIGHTS
7.5
STABCARGOHOOK
PILOTTURN
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)
TM 1-1520-237-10
2-15
-
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
BLUE
WHITE
OFF
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
TAILWHEEL SEC
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)
TM 1-1520-237-10
2-16
-
STORES JETTISONEMERJETTALL JETT
INBD OUTBD
BOTH 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
Z
E
R
O
I
Z
E
KY58R
C
U
FILL12
3 54 6
PR
ESS TO T
ES
T
D IM
PR
ESS TO T
ES
T
D IM
TEST TEST/MON TOP
BOT
MASTER
TEST
OUTSTATUS
IDENT
MIC
TEST AUDIO
PR
ESS TO T
ES
T
D IM
REPLY
CODE
M1 M2 M3 / A MC
ANT
DIV
ON
ON
LIGHT
OUT
MODE 1 MODE 3 / A
NO
GO
EMER
NO
RM
STB Y
OFF
ALT KIT ANT
0 0 1 2 0 0
A
B
MODE 4
ON
GO
FM 1 / FM 2FM 2 / UHF
FM 2 / VHF FM 1 / VHF
FM 1 / UHFVHF / UHF
OFF
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
FAILURE ADVISORY
ZER
O
HOLD
RADTEST
FUELIND
FI
F
RADIO RETRANSMISSION
PLAINC / RAD
MODE
DELAY
ON
POWER
OPLD
RV
1
23 4
5
6
Z
E
R
O
I
Z
E
KY58R
C
U
FILL12
3 54 6
1 2 3 FREQ
4 5 6
7 8 9 TIME
CLR StoENT
HLd0
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
MODEHOM
SCFHFHM
VOL
9
14 1 0 50
FM AM
MAN
PRE
DF
TR
OFF
VOL
SQDIS
TONE
EMER
LOAD
PRESET
COMM
PLAINC / RAD
MODE
DELAY
ON
POWER
OPLD
RV
1
23 4
5
6
Z
E
R
O
I
Z
E
KY58R
C
U
FILL12
3 54 6
1 2 3 FREQ
4 5 6
7 8 9 TIME
CLR StoENT
HLd0
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
MODEHOM
SCFHFHM
VOL
CURSOR
VALUE
T / RSILENT
STBY
OFF
ZERO(PULL)
VOLSQL
PREMAN
ALEECCM
EMER
1
2
34 5
6
KEY DATA
DSPLOFF
BRT
PNLOFF
INIT
FILL
CIK
AUDIO
KY100
OFLEB
RK
CT
PTMODEPRESET
ZALL(PULL)
1234
6
REM
MANPWROFF
BAT
123
46 5
U
PA
RK
ING
BR
AK
E
BATT &ESNTL DC
WARNDC AC &
ESNTL BUS FUELPRIME
BATTBUS FIRE
SPLY CONVWARN
EXT PWRCONTR
BOOST CONTR EXTGH
APUUTILLTS APU
CONTRINST
CONTRINST
FIREDET
GENCONTR
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
DISPCONT
ARM MANPGRM
RIPPLE
FIRE
SAFE
OFF
ARM
PR
ES
STO
TE
ST
DIM
LTRLEFT
LTRMID
LTRRIGHT
ABC1
DEF2
GHI3
JKL4
MNO5
PQR6
GPSLDG
LAT /LONG
MGRSTEST
LAMP
TEST
OFF
XTK/TKCKEY
GS/TKNAV M
PPDIST / BRG
TIME
WINDUTCDATA
WP
TGT
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 ANDO 0 3 0MG9 1GP S : M N A V : CGS : 1 1 7KM /HRTK : 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
DIM L / R
CPLTDSPL POS
MODE+
MODE
FAIL
ON
D / U
L / R
BRT
DIMDSPL POS
PLT
14
DCLT
CHAFFDISPENSE GPSZEROIZE
+PWR SELF DSCRM
ON
OFF
ON
OFF 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
2-17
-
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
2-18
-
SAAA1304_2C
AUDIO
KILOCYCLESCW
TEST
VOICE
LOOP
TUNE
ADF
RCVR OFF LOOP
COMP ANT
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
COMM
PR
ESS TO T
ES
T
D IM
PR
ESS TO T
ES
T
D IM
TEST TEST/MON TOP
BOT
MASTER
TEST
OUTSTATUS
IDENT
MIC
TEST AUDIO
OUT
PR
ESS TO T
ES
T
D IM
REPLY
CODE
M1 M2 M3/A MC RADTEST
ANT
DIV
IFF
ON
ON
LIGHT
OUT
MODE 1 MODE 3 / A
NO
GO
EMER
NO
RM
ST
BYOFF
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
TONESQUELCH
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
ON
OFF
ON
OFF AUDIOTEST
CHAFFDISPENSE
SAFE
FUELIND
OUT
FUEL BOOST PUMP CONTROL
ON
OFF
NO. 1PUMP
NO. 2PUMP
ON
OFF
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
DEFABC
GHJ KLM NPQ
RST UVW XYZ
LTR
W4
1
5 E6
3M2
USE 0 CLR
FACK
BRT
MRK
STR
BIT
DEST
7 S8 9
I
I
N
S
DESTINS
POS
STR
TCN
UPDTNAV
NORM
FAST
OFF
TEST
CALATTD
_
PA
RK
ING
BR
AK
E
AN/ARC201
AN/ALQ162
COVER
FAILURE ADVISORY
PR
ESS
TO
TE
ST
DIM
A
BZE
RO
HOLD
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
Z
E
R
O
I
Z
E
KY58R
C
U
FILL12
3 54 6
PLAINC / RAD
MODE
DELAY
ON
POWER
OPLD
RV
1
23 4
5
6
Z
E
R
O
I
Z
E
KY58R
C
U
FILL12
3 54 6
VHFFM NO. 1
IFM CONTROL
AN/ARC201
PLAINC / RAD
MODE
DELAY
ON
POWER
OPLD
RV
1
23 4
5
6
Z
E
R
O
I
Z
E
KY58R
C
U
FILL12
3 54 6
VHFFM NO. 2
BATT &ESNTL DC
WARNDC AC &
ESNTL BUS FUELPRIME
BATTBUS FIRE
SPLY CONVWARN
EXT PWRCONTR
BOOST CONTR EXTGH
APUUTILLTS APU
CONTRINST
CONTRINST
FIREDET
GENCONTR
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 breakersmarked
NO. 1 AC INST/NO. 1 DC INST and NO. 2 ACINST/NO. 2 DC INST,
respectively. Refer to Figures 5-1and 5-2 for instrument
markings.
2.12 DOORS AND WINDOWS.
2.12.1 Cockpit Doors. The crew compartment isreached through two
doors, one on each side of thecockpit. The doors swing outward and
are hinged on theforward side. Each door has a window for
ventilation. In-stalled on the back of each door is a latch handle
to allowunlatching the door from either inside or outside
thecockpit. Emergency release handles are on the insideframe of
each door (Figure 9-1). They allow the cockpitdoors to be
jettisoned in case of an emergency. There is anemergency release
pull tab on the inside forward portion ofeach cockpit door window
for pilot egress. Data compart-ments are on each cockpit door.
2.12.2 Troop/Cargo (Cabin) Doors. Aft sliding doorsare on each
side of the troop/cargo compartment. Single-action door latches
allow the doors to be latched in thefully open or fully closed
positions. Each of the two doorsincorporate two jettisonable
windows, for emergency exit(Figure 9-1).
2.12.3 Crew Chief/Gunner Windows. The CrewChief/Gunner Stations
have forward sliding hatchwindows, split vertically into two
panels. A spring-loadedsecurity latch is installed on each gunners
aft window, toprevent the window opening from the outside. The
deadbolt lock requires activation of the security latch leverfrom
inside the helicopter. Another window latch bar isactuated to allow
the forward window to be moved to astowed position. The windows may
be opened to move amachine gun into position for firing.
2.12.4 Door Locks. Key door locks are installed oneach of the
cabin, cockpit and avionics compartmentdoors. A common key is used
to lock and unlock the doorsfrom 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. Seatsstroke downward during
a crash and any
obstruction will increase the probabilityand severity of
injury.
The pilots seats provide ballistic protection and can beadjusted
for the pilots leg length and height. The pilotsseat is on the
right side, and the copilots is on the left.Each seat has a
one-piece ceramic composite bucket at-tached to energy absorption
tubes. Each seat is positionedon a track with the bucket directly
above a recess in thecockpit floor. Crash loads are reduced by
allowing the seatand occupant to move vertically as a single unit.
Occupantrestraint is provided by a shoulder harness, lap belts, and
acrotch belt.
2.13.1.1 Seat Height Adjustment.
WARNING
To prevent injury to personnel, do notrelease either the normal
or emergencyvertical adjust levers unless someone issitting in the
seat. The extension springsare under load at all times. With seat
atlowest position, the vertical preload onthe seat could be as high
as 150 pounds.If no one is in the seat and vertical adjustlever(s)
is released, the seat will besnapped to the highest stop.
Anyoneleaning over the seat or with hands onguide tubes above
linear bearings will beseriously injured.
Vertical seat adjustment is controlled by a lever on theright
front of the seat bucket. Springs are installed tocounterbalance
the weight of the seat. The lever returns tothe locked position
when released.
2.13.1.2 Forward and Rear Adjustment. The seat isadjusted for
leg length by a locking lever on the left frontof the seat bucket.
The lever is spring-loaded and returnsto the locked position when
released.
2.13.1.3 Emergency Tilt Release Levers. Theemergency tilt
release levers are on each side of the seatsupport frame. The seat
may be tilted back into the cabinfor removal or treatment of a
wounded pilot. Seat tiltingcan be done from the cabin only when the
seat is in thefull down and aft position. On RA-30525 seats,
tilting isachieved by pushing the tilt levers in toward center,
andthen pulling the seat top rearward. On D3801 and D3802seats,
tilting is achieved by pushing the tilt leversoutboard, and then
pulling the seat top rearward.
TM 1-1520-237-10
2-20
-
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
OF
F
STABPOS
DEG
0O
10O
20O
30O
40O
KIASLIMIT150100806045
STAB
DEG
1 2 3 4 30 0
HDG CRS
N
W
E
S
36
1215
2124
3033
KM COURSE
HDG
NAV
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
FEETHILO
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
NON SECURE RADIOS WILL NOT BE KEYED
WHEN USING ANY SECURE RADIO OR THE
INTERCOM FOR CLASSIFIED COMMUNICATIONS
RADIO FM 1
SW NO. 1UHF
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 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
CLI MB
DI VE
GS
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
AUX FUEL QTY LBSTEST /RESET
XFER MODEAUTO
MAN
OFF
LEFT
RIGHT
OTH
INBD
OUTBD
B
MAN XFER XFER FROM PRESS
OUTBD
INBD
OFF
ALL
28 28
RST
MODE
ST/SP
12:34
SET
LC6
ADV
CHRONOMETER
55
12 123
4567
8910
11
60
5
10
15
20
2530
35
40
45
50
55
CB
C
DPLRGPS
29 29
MSGWPT
NO GPSHOLD
RAIMAPR
Figure 2-9. Instrument Panel (Sheet 1 of 4) UH
TM 1-1520-237-10
2-21
-
OFFDIGITS
1 CHAN 2
PRESSPSI 5 10
TEMP\ X 100
SPEED\ X 10
OIL TGT Ng
TGT Ng
1
4
5
6
7
8
13
17
1 2 1 20
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
DPLRVORILS
VORILS
BACKCRS
BACKCRS
FMHOME
FMHOME
NORMALTR
PLTCPLT
NORMALTR
ADFVOR
TURNRATE
CRSHDG
VERTGYRO
BRG2
POWERON
TEST
TESTIN
PROGRESS
MODE
AUTOT
L
M
BLADE DEICE TEST
NORMSYNC 1
SYNC 2
OAT
EOT
PWRMAIN TAIL
RTR RTR
ON
OFF
PRESSTO
TEST
BLADE
DEICE
IRCM
MANU
AL
LWG 9 /m3
TL
M H
025 5
10 1520FAIL
RADIO CALL00 0 00
MA
DAY
NIGHT
BRIL
#1 ENGOUT
#2 ENGOUT
LOW ROTORRPM
MASTER CAUTIONPRESS TO RESET
FIRE
CMD ATT
30 30
30 30
NAV
ROLL PITCH
CLI MB
DI VE
GS
1 2 3 4 30 0
HDG CRS
N
W
E
S
36
1215
2124
3033
KM COURSE
HDG
NAV
2
1
2
1
10
0
10
20
3040
DN
OF
F
STABPOS
DEG
0O
10O
20O
30O
40O
KIASLIMIT150100806045
STAB
DEG
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 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
L5
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
NORMSYNC 1
SYNC 2
OAT
EOT
PWRMAIN TAIL
RTR RTR
ON
OFF
PRESSTO
TEST
BLADE
DEICE
IRCM
MANU
AL
LWG g /m3
TL
M H
025.5
10 1520FAIL
O
F
F
1. RADAR ALTIMETER2. BAROMETRIC ALTIMETER3. VERTICAL SPEED
INDICATOR4. MASTER WARNING PANEL5. VERTICAL SITUATION INDICATOR6.
HORIZONTAL SITUATION INDICATOR7. AIRSPEED INDICATOR8. STABILATOR
POSITION PLACARD9. STABILATOR INDICATOR
10. CIS MODE SELECTOR11. VSI / HSI MODE SELECTOR12. RADIO CALL
PLACARD13. PILOTS DISPLAY UNIT14. CLOCK15. ICE RATE METER16. BLADE
DEICE CONTROL PANEL17. BLADE DEICE TEST PANEL18. INFRARED
COUNTERMEASURE CONTROL PANEL19. CENTRAL DISPLAY UNIT20. RADAR
WARNING INDICATOR21. AUXILIARY FUEL MANAGEMENT PANEL22. ENGINE
IGNITION SWITCH23. RADIO SELECT PLACARD24. CAUTION / ADVISORY
PANEL25. SECURE WARNING PLACARD26. NVG DIMMING CONTROL PANEL27. RAD
ALT DIMMING
A
SA DM MA
(ON HELICOPTERS WITH REARRANGEDBLADE DEICE PANELS)
AFMS
A
28. FORWARD COCKPIT AIRBAG
CB
29. GPS ANNUNCIATORS 128D
DPLRGPS
SASAAB0823_2B
MSGWPT
NO GPSHOLD
RAIMAPR
RST
MODE
ST/SP
12:34
SET
LC6
ADV
CHRONOMETER
55
Figure 2-9. Instrument Panel (Sheet 2 of 4) UH
TM 1-1520-237-10
2-22
-
SAAA0516_3C
0
2
4
6
8
10
12
14
1 2
TOTAL FUEL TO TEST OFFDIGITS
DIM ON
QTYLB X 100
TEMP PRESSPSI 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 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
#1 ENGOUT
#2 ENGOUT
LOW ROTORRPM
MASTER CAUTIONPRESS TO RESET
FIRE
VERTICAL SPEED
1000 FT PERMIN
DOWN
UP
5
5
0
0 123
4567
89
12 4
6
421
10
0
10
20
3040
DN
OF
F
STABPOS
DEG
CMD ATT
30 30
30 30
NAV
ROLL PITCH
CLI MB
DI VE
GS
0O
10O
20O
30O
40O
KIASLIMIT150100806045
STAB
DEG
1 2 3 4 30 0
HDG CRS
N
W
E
S
36
1215
2124
3033
KM COURSE
HDG
NAV
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
FEETHILO
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
NON SECURE RADIOS WILL NOT BE KEYED
SYSTEMS SELECT
INTERCOM FOR CLASSIFIED COMMUNICATIONS
RADIO FM 1
SW NO. 1UHF
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 FT100 FT
IN. HG
1
2
2 9 9 0
#1 ENGINE #2 ENGINEPRESS PRESS
LOCKANTENNA
EXTENDED
#1 ENGINESTARTER
RADIO CALL00 0 00
IRCMINDP
AUX FUEL
SEARCH LTON
CABIN HEATON
ANTENNARETRACTEDDIM
FLARE
3
69
12
1518
0
21
2427
30
33
0 0 0 0K N
CREWCALL
WHEN USING ANY SECURE RADIO OR THE
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
60
5
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
2-23
-
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
MA
DAY
NIGHT
BRIL
#1 ENGOUT
#2 ENGOUT
LOW ROTORRPM
MASTER CAUTIONPRESS TO RESET
FIRE
CMD ATT
30 30
30 30
NAV
ROLL PITCH
CLI MB
DI VE
GS
1 2 3 4 30 0
HDG CRS
N
W
E
S
36
1215
2124
3033
KM COURSE
HDG
NAV
2
1
2
1
10
0
10
20
3040
DN
OF
F
STABPOS
DEG
0O
10O
20O
30O
40O
KIASLIMIT150100806045
STAB
DEG
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 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
L5
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
NORMSYNC 1
SYNC 2
OAT
EOT
PWRMAIN TAIL
RTR RTR
ON
OFF
PRESSTO
TEST
BLADE
DEICE
IRCM
MANUA
L
LWG 9 /m3
TL
M H
0 25 5
10 1520FAIL
O
F
F
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
POWER PUSH FORSTANDBY
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 DIMMI
