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TM 55-1520-228-10

or in straight and level

ight. The warning

ag, atti-

tude (ATT) and rate of turn pointer provide indication of

system malfunctions. When the gyro is being caged or

when 28 Vdc power is interrupted, the ATT

ag will be

in full view. The rate of turn pointer will be biased out

of view when 28 Vdc is interrupted. The circuit is pow-

ered by 28 Vdc essential bus and protected by ATTD

HRZN and ATTN TURN circuit breakers. The rate-of-

turn pointer is driven by 115 VAC internal circuitry that

derives rate-of-turn from the output synchro transmitter

of the directional gyro magnetic compass.

2-65. TURN AND SLIP INDICATOR.

The turn and slip indicator (

gure 2-13) is controlled

by a direct current electrically actuated gyro. This in-

strument has a needle (turn indicator) and a ball (slip

indicator). Although needle and ball are combined in

one instrument and are normally read and interpreted

together, each has its own speci

c function and oper-

ates independently of the other. The ball indicates when

the helicopter is in directional balance either in a turn or

in straight and level

ight. If the helicopter is yawing or

slipping, the ball will be off center. The needle indicates

in which direction and at what rate the helicopter is turn-

ing.

2-66. FREE AIR TEMPERATURE INDICATOR.

The bi-metal free air temperature indicator (

gure 2-13

and

gure 2-14) is in the windshield, and provides a di-

rect reading of the outside air temperature.

2-67. MAGNETIC COMPASS.

The magnetic compass (

gure 2-13 and

gure 2-14)

is a standard, non-stabilized, magnetic type instrument

mounted on a support which is attached to the right side

of the cabin structure forward of the pilot. The compass

is used in conjunction with a compass correction card

that is located near the compass. In aircraft with low re-

ective painted interior, the compass correction card will

be located in the front of the logbook.

2-68. VERTICAL SPEED INDICATOR.

The vertical speed indicator (

gure 2-13 and

gure 2-14)

displays the helicopter ascent and descent speed in feet

per minute. the indicator is actuated by the rate of atmo-

spheric pressure change.

2-69.

CONUS NAVIGATION SYSTEM

(AN/ARN-123).

Refer to Chapter 3.

2-70. RADAR ALTIMETER (AN/APN-209).

Refer to Chapter 3.

2-71. RADAR WARNING SYSTEM.

Refer to Chapter 3.

2-72. MISCELLANEOUS INDICATORS.

Instruments and indicators that are independent or are

linked with more than one system are the clock and mas-

ter caution and warning system (

gure 2-12).

a. Clock.

The clock (

gure 2-13 and

gure 2-14)

has a sweep-second pointer and a minute totalizer hand

to indicate elapsed time. The control knob in the upper

right corner of the case starts, stops, and returns the

pointers to the 12 o’clock position when actuated.

b. Caution System.

The caution system (

gure

2-13 and

gure 2-14) is a segment wording type, con-

sisting of a segment word warning CAUTION panel

(

gure 2-19) on the lower console and a remote MAS-

TER CAUTION segment on the instrument panel. The

purpose of the CAUTION system is to provide visual

indication suitable for day or night operation, that a fault

condition has occurred. In addition, a positive signal is

provided to illuminate the remote MASTER CAUTION

indicator. Each fault condition, as it occurs, is indicated

ashing of the lettering on the segment involved

and by a

ashing of the MASTER CAUTION indicator.

, steady illumination of the lettering on the segment

involved and by a steady illumination of the MASTER

CAUTION indicator. A momentary positioning of RE-

SET-TEST switch to RESET extinguishes the MASTER

CAUTION light so that it will illuminate for the next fault

indication; also, the fault segment will be steadily ON.

Segments will remain lighted as long as the fault con-

dition(s) exist. Momentarily pressing the RESET-TEST

switch to TEST will check if all caution lights

are operational. Testing of the system will not change

the existing fault conditions. The BRIGHT-DIM

2-46.2 Change 14

Содержание OH-58A

Страница 1: ...0 TECHNICAL MANUAL OPERATOR S MANUAL ARMY MODEL OH 58A C HELICOPTER This manual supersedes TM 55 1520 228 10 and TM 55 1520 236 10 7 April 1978 including all changes HEADQUARTERS DEPARTMENT OF THE ARMY 17 JANUARY 1989 ...

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Страница 3: ...on can cause serious injury or loss of life WARNING STARTING ENGINE Coordinate all cockpit actions with ground observer Ensure that rotors and blast areas are clear and fire guard is posted if available WARNING FIRE EXTINGUISHER Exposure to high concentrations of monobromotribluoromethane CF Br extinguishing agent or toxic fumes pro duced by the agent should be avoided The liquid should not be all...

Страница 4: ...water If liquid is swallowed do not induce vomiting get immediate medical attention Wear rubber gloves when handling liquid If prolonged contact with mist is likely wear an appropri ate respirator When fluid is decomposed by heating toxic gases are released HAZARDOUS CARGO Items of cargo possessing dangerous physical properties such as explosives acids fl ammable etc must be handled with extreme c...

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Страница 7: ...e pointing hand Remove Pages Insert Pages a and b a and b A and B A and B 2 1 through 2 4 2 1 through 2 4 2 7 through 2 10 2 7 through 2 10 2 13 and 2 14 2 13 and 2 14 2 23 and 2 24 2 23 and 2 24 2 29 and 2 30 2 29 and 2 30 2 35 through 2 38 2 35 through 2 38 2 46 1 and 2 46 2 2 46 1 and 2 46 2 2 49 through 2 52 2 49 through 2 52 2 57 and 2 58 2 57 and 2 58 3 3 and 3 4 3 3 and 3 4 5 1 and 5 2 5 1 ...

Страница 8: ...ce with Initial Distribution Number IDN 310230 requirements for TM 55 1520 228 10 By Order of the Secretary of the Army PETER J SCHOOMAKER General United States Army Chief of Staff Official JOYCE E MORROW Administrative Assistant to the Secretary of the Army 0528701 ...

Страница 9: ...s indicated by a vertical bar in the margin An illustration change is indicated by a miniature pointing hand Remove Pages Insert Pages A and B A and B 2 11 and 2 12 2 11 and 2 12 5 3 blank and 5 4 5 3 blank and 5 4 2 Retain this sheet in front of manual for reference purposes DISTRIBUTION To be distributed in accordance with Initial Distribution Number IDN 310230 requirements for TM 55 1520 228 10...

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Страница 11: ...b a and b A and B A and B 2 1 through 2 12 2 1 through 2 12 2 27 and 2 28 2 27 and 2 28 2 37 and 2 38 2 37 and 2 38 2 43 and 2 44 2 43 and 2 44 2 49 through 2 52 2 49 through 2 52 2 55 through 2 60 2 55 through 2 60 2 63 and 2 64 2 63 and 2 64 5 3 blank 5 4 5 3 blank 5 4 7 79 and 7 80 7 79 and 7 80 8 7 and 8 8 8 7 and 8 8 9 7 and 9 8 9 7 and 9 8 2 Retain this sheet in front of manual for reference...

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Страница 13: ...through 2 14 2 11 through 2 14 2 17 through 2 20 2 17 through 2 20 2 23 through 26 2 23 through 2 26 2 33 and 2 34 2 33 and 2 34 2 43 and 2 44 2 43 and 2 44 2 46 1 through 2 54 2 46 1 through 2 54 2 57 and 2 58 2 57 and 2 58 2 61 through 2 67 2 68 blank 2 61 through 2 67 2 68 blank 3 1 through 3 8 1 3 8 2 blank 3 1 through 3 8 2 3 8 3 and 3 8 4 3 11 through 3 14 3 11 through 3 14 3 17 through 3 20...

Страница 14: ...4 A 1 A 2 blank A 1 and A 2 Index 1 through Index 9 Index 10 blank Index 1 through Index 9 Index 10 blank 2 Retain this sheet in front of manual for reference purposes DISTRIBUTION To be distributed in accordance with Initial Distribution Number IDN 310230 requirements for TM 55 1520 228 10 ERIC K SHINSEKI General United States Army Chief of Staff Official JOEL B HUDSON Administrative Assistant to...

Страница 15: ...ages a and b a and b A B blank A and B i through iv i through iv 1 1 and 1 2 1 1 and 1 2 2 3 through 2 12 2 3 through 2 12 2 17 and 2 18 2 17 and 2 18 2 21 and 2 22 2 21 and 2 22 2 22 1 2 22 2 blank 2 23 and 2 24 2 23 and 2 24 2 26 1 and 2 26 2 2 27 through 2 36 2 27 through 2 36 2 39 through 2 44 2 39 through 2 44 2 49 and 2 50 2 49 and 2 50 2 55 and 2 56 2 55 and 2 56 2 63 and 2 64 2 63 and 2 64...

Страница 16: ...ugh 8 16 8 9 through 8 16 8 17 8 18 blank 8 17 8 18 blank 9 1 and 9 2 9 1 and 9 2 9 7 through 9 10 9 7 through 9 10 9 13 and 9 14 9 13 9 14 blank 9 15 9 16 blank 9 15 9 16 blank A 1 A 2 blank A 1 A 2 blank Index 1 through Index 8 Index 1 through Index 8 Index 9 Index 10 blank Index 9 Index 10 blank 2 Retain this sheet in front of manual for reference purposes By Order of the Secretary of the Army ...

Страница 17: ... bar in the margin An illustration change is indicated by a miniature pointing hand Remove pages Insert pages 2 33 and 2 34 3 23 and 3 24 3 31 and 3 32 8 5 and 8 6 2 33 and 2 34 3 23 and 3 24 3 24 1 3 24 2 blank 3 31 and 3 32 3 32 1 and 3 32 2 8 5 and 8 6 2 Retain this sheet in front of manual for reference purposes By Order of the Secretary of the Army Administrative Assistant to the Secretary of...

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Страница 25: ...ration change is indicated by a miniature pointing hand Remove pages Insert pages 3 27 and 3 28 3 27 and 3 28 5 11 and 5 12 5 11 and 5 12 8 17 8 18 8 17 8 18 2 Retain this sheet in front of manual for reference purposes By Order of the Secretary of the Army GORDON R SULLIVAN General United States Army Official Chief of Staff PATRICIA P HICKERSON Colonel United States Army The Adjutant General DIST...

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Страница 27: ...iniature pointing hand Remove pages Insert pages 2 21 and 2 22 2 21 and 2 22 2 45 and 2 46 2 45 and 2 46 2 46 1 and 2 46 2 3 23 and 3 24 3 23 and 3 24 3 25 and 3 26 3 25 and 3 26 2 Retain this sheet in front of manual for reference purposes By Order of the Secretary of the Army CARL E VUONO General United States Army Official Chief of Staff WILLIAM J MEEHAN II Brigadier General United States Army ...

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Страница 29: ... the margin An illustration change is indicated by a miniature pointing hand Remove pages Insert pages 6 7 and 6 8 6 7 and 6 8 2 Retain this sheet in front of manual for reference purposes By Order of the Secretary of the Army CARL E VUONO General United Stages Army Official Chief of Staff WILLIAM J MEEHAN II Brigadier General United States Army The Adjutant General DISTRIBUTION To be distributed ...

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Страница 31: ...ove and insert pages as indicated below New or changed text material is indicated by a vertical bar in the margin An illustration change is indicated by a miniature pointing hand Remove pages Insert pages 5 11 and 5 12 5 11 and 5 12 8 13 and 8 14 8 13 and 8 14 2 Retain this sheet in front of manual for reference purposes By Order of the Secretary of the Army CARL E VUONO General United States Army...

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Страница 33: ...30 2 29 and 2 30 2 41 and 2 42 2 41 and 2 42 2 51 and 2 52 2 51 and 2 52 2 57 and 2 58 2 57 and 2 58 3 3 through 3 8 3 3 through 3 8 4 1 and 4 2 4 1 and 4 2 4 5 through 4 20 4 5 through 4 20 5 7 and 5 8 5 7 and 5 8 6 1 and 6 2 6 1 and 6 2 6 7 and 6 8 6 7 and 6 8 6 8 1 6 8 2 8 1 through 8 8 8 1 through 8 8 9 1 and 9 2 9 1 and 9 2 9 9 through 9 15 9 16 9 9 through 9 15 9 16 A 1 A 2 A 1 A 2 Index 1 t...

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Страница 35: ...Change 11 1 April 2003 Change 12 10 June 2005 Change 13 30 August 2005 Change 14 31 March 2006 TOTAL NUMBER OF PAGES IN THIS PUBLICATION IS 265 CONSISTING OF THE FOLLOWING Page Change Page Change No No No No Cover 0 blank 0 a 12 b 14 c 1 d blank 0 A and B 14 i through iv 11 1 1 and 1 2 11 2 1 14 2 2 12 2 3 10 2 4 14 2 5 12 2 6 0 2 7 14 2 8 14 2 9 10 2 10 14 2 11 13 2 12 12 2 13 14 2 14 through 2 1...

Страница 36: ... and 5 7 14 5 8 10 5 9 11 5 10 14 5 11 2 5 12 14 6 1 11 6 2 14 6 3 11 6 4 10 6 5 11 6 6 0 6 7 11 6 8 blank 10 6 8 1 1 Page Change No No 6 8 2 blank 1 6 9 10 6 10 blank 0 7 1 through 7 3 11 7 4 0 7 5 11 7 6 and 7 7 0 7 8 10 7 9 through 7 46 deleted 10 7 47 through 7 54 0 7 55 and 7 56 10 7 57 and 7 58 0 7 59 10 7 60 11 7 61 blank 11 7 62 11 7 63 through 7 76 0 7 77 and 7 78 10 7 79 0 7 80 12 7 81 0...

Страница 37: ...546 or Commercial 256 842 6546 Our e mail address is 2028 redstone army mil Instructions for sending an electronic 2028 may be found at the back of this manual immediately preceding the hard copy 2028 For the World Wide Web use https amcom2028 redstone army mil TABLE OF CONTENTS Chapter Section Page CHAPTER 1 INTRODUCTION 1 1 CHAPTER 2 HELICOPTER AND SYSTEMS DESCRIPTION AND OPERATION Section I Hel...

Страница 38: ... 7 1 II Temperature Conversion 7 6 III Torque Available A Deleted IV Hover A Deleted V Takeoff A Deleted VI Cruise A Deleted VII Drag A Deleted VIII Climb Descent A Deleted IX Idle Fuel Flow A Deleted X Torque Available C 7 47 XI Hover 7 56 XII Takeoff Not Applicable 7 60 XIII Cruise 7 62 XIV Drag C 7 76 XV Climb Descent 7 78 XVI Idle Fuel Flow 7 84 CHAPTER 8 NORMAL PROCEDURES Section I Mission Pl...

Страница 39: ... 164 V and RT 1167C ARC 164 V 3 11 3 7 AN ARC 51BX Control Panel A DELETED 3 8 Voice Security Equipment TSEC KY 58 3 15 Figure Title Page 3 9 AN ARN 89 ADF Control Panel 3 18 3 10 Radio Bearing Heading Indicator 3 20 3 11 CONUS Navigation Receiver Control Panel C 3 22 3 12 Course Deviation Indicator CDI C 3 23 3 13 Transponder APX 72 Control Panel A 3 25 3 14 Transponder Set Control Panel C 3 28 3...

Страница 40: ...rt C 7 48 7 12 Torque Available Continuous Operation Chart 7 52 7 13 Hover Chart 7 57 7 14 Takeoff Chart DELETED 7 15 Cruise Chart 7 63 7 16 Drag Chart 7 77 7 17 Climb Descent Chart C 7 79 7 18 Climb Performance C DELETED 7 19 Idle Fuel Flow Chart C 7 85 8 1 Exterior Check Diagram 8 4 8 2 Effects of Wind Azimuth on Aircraft 8 13 9 1 Emergency Exits and Equipment 9 3 9 2 Autorotational Glide Charac...

Страница 41: ...The observance of procedures is mandatory except when modification is required because of multiple emergencies adverse weather terrain etc Your flying experience is recog nized and therefore basic flight principles are not in cluded It is required that THIS MANUAL BE CARRIED IN THE HELICOPTER AT ALL TIMES 1 4 APPENDIX A REFERENCES Appendix A is a listing of official publications cited within the m...

Страница 42: ...terial One or more designator symbols may follow a text heading or illustration title to indicate proper effectiv ity unless the material applies to all series and configu rations within the manual If the material applies to all series and configurations no designator symbols will be used Where practical descriptive information is con densed and combined for all models to avoid duplica tion NOTE A...

Страница 43: ...integrated structure The most forward and aft bulkheads act as carry through structure for the skid landing gear crosstubes The tail boom is a monocoque structure with aluminum skin and aluminum substructure a Dimensions Principal dimensions of the heli copter areas are shown in figure 2 5 b Turning Radius and Ground Clearance Refer to figure 2 6 c Weights The helicopter weight empty and gross ope...

Страница 44: ...on Light Green 4 Tail Rotor Hub and Blade 14 Horizontal Stabilizer 5 Position Light White 15 Vertical Fin 6 Tail Skid 16 Battery and Avionics Compartment Door 7 Position Light Red 17 Passenger Door Left 8 Forward Transmission Fairing 18 Copilot Door 9 Pitot Tube 19 Left Static Port 10 Landing Gear Figure 2 1 General Arrangement Sheet 1 of 2 2 2 Change 12 ...

Страница 45: ...ming Antenna Right Side 24 Engine Exhaust 35 Battery Vent 25 Engine Air Inlet 36 External Power Receptacle 26 Forward Transmission Fairing Inspection Door 37 Ground Receptacle 27 Upper Cutter Assembly 38 FM Homing Antenna Left Side 28 Free Air Temperature FAT Gage 39 Landing Light 29 Windshield Deflector Cutter Assembly 30 Right Static Port Figure 2 1 General Arrangement Sheet 2 of 2 Change 10 2 3...

Страница 46: ...ssion Fairing 23 Radar Warning Blade Antenna 8 Pilot Tube 24 Radar Altimeter Antenna 9 Right Forward Radar Warning Antenna 25 Marker Beacon Antenna 10 Door Lock 26 Transponder Antenna 11 Fuel Filler Cap 27 UHF Antenna 12 Left Forward Radar Warning Antenna 28 Landing Light 13 Left Aft Radar Warning Antenna 29 Upper Cutter Assembly 14 Position Light Red 30 Windshield Deflector Cutter Assembly 15 Pos...

Страница 47: ...ionics Compartment Door 37 Passenger Door 50 Step 38 Battery Vent 51 FM Homing Antenna 39 External Power Receptacle 52 Passenger Door 40 Main Rotor Blades and Hub 53 Copilot Door 41 Free Air Temperature FAT Gage 54 Left Static Port 42 Forward Transmission Fairing Inspection Door 55 NVG Position Lights 43 Engine Air Inlet 56 Tail Cone 44 Engine Oil Tank Drain Access Door F igure 2 2 General Arrange...

Страница 48: ...rature FAT Gage 5 Pilot Door Emergency Jettison Handle 6 Instrument Panel 7 Magnetic Compass 8 Anti Torque Pedals 9 Pilot Cyclic Stick 10 Pilot Seat 11 Inertia Reel Control Handle 12 Pilot Collective Stick 13 Collective Friction Control Adjustment 14 Pedestal 15 Copilot Seat 16 Ignition Key Lock Switch 206061 90 1 Figure 2 3 Compartment Diagram A Sheet 1 of 2 2 6 ...

Страница 49: ...Not Used 19 Starter Switch 27 Not Used 20 Engine Idle Release Control 28 Not Used 21 Inertia Reel 29 Not Used 22 Inertia Reel Control Handle 30 Force Trim Switch 23 Not Used 31 Throttle 24 ICS Switch 32 Controllable Landing Light Switch Figure 2 3 Compartment Diagram A Sheet 2 of 2 Change 14 2 7 ...

Страница 50: ...ure FAT Gage 15 Collective Friction Control Adjustment 5 Pilot Door Emergency Jettison Handle 16 Console 6 Instrument Panel 17 Copilot Seat 7 Magnetic Compass 18 Copilot Collective Stick 8 Pilot Cyclic Stick 19 Copilot Anti Torque Pedals 9 Pilot Anti Torque Pedals 20 Copilot Cyclic Stick 10 Cyclic Friction Control Adjustment 21 Glareshield 11 Pilot Seat Figure 2 4 Pilot and Copilot Observer Statio...

Страница 51: ...0 22 Not Used 26 ICS Switch 23 Not Used 27 Radio Transmit Switch 24 Not Used 28 Not Used 25 Force Trim Switch 28 1 Not Used 25 1 Not Used Figure 2 4 Pilot and Copilot Observer Station Diagram Sheet 2 of 3 Change 10 2 9 ...

Страница 52: ...d 30 Starter Switch 31 Governor RPM Switch 32 Search Landing Lights 33 Engine Idle Release Control 34 Controllable Landing Light Switch 35 Deleted Figure 2 4 Pilot and Copilot Observer Station Diagram Sheet 3 of 3 2 10 Change 14 ...

Страница 53: ...TM 55 1520 228 10 Change 13 2 11 Figure 2 5 Principal Dimensions Sheet 1 of 2 ...

Страница 54: ... 9 ft 9 5 in 9 ft 10 5 in WIDTH 10 Skid Gear 6 ft 5 4 in 7 ft 3 0 in 11 ft 6 1 in 11 Horizontal Stabilizer 6 ft 5 2 in No Change No Change DIAMETERS 12 Main Rotor 35 ft 4 0 in No Change No Change 13 Tail Rotor 5 ft 5 0 in No Change No Change LENGTH 14 Overall Main Rotor Fore and Aft to Aft End of Tail Skid 40 ft 11 8 in No Change No Change 15 Nose of Cabin to Aft End of Tail Skid 32 ft 2 0 in No C...

Страница 55: ... d Tail Skid A tubular steel tail skid is attached to the lower section of the vertical fin and provides protec tion for the tail rotor in landings by indicating a tail low condition 2 4 COCKPIT AND CABIN DOORS WARNING Inadvertent jettisoning of cockpit doors is pos sible if jettison handle is utilized as a handhold or hand rest during flight Four entrance doors are provided for access to the air ...

Страница 56: ...TM 55 1520 228 10 Figure 2 7 Float Gear Equipped Helicopter 2 14 ...

Страница 57: ...TM 55 1520 228 10 Figure 2 8 Locking Devices for Doors 2 15 ...

Страница 58: ...r cutter assembly and a lower cutter assembly figure 2 1 and figure 2 2 The windshield deflector cutter assembly consisting of a sawtooth equipped aluminum extrusion provides deflection mechanism into the upper cutter while simultaneously abrading thus weakening wire and provides additional structural support for the upper cutter mounting The mechanical cutter assembly upper and lower figure 2 9 c...

Страница 59: ...TM 55 1520 228 10 2 17 Figure 2 9 WSPS Configuration ...

Страница 60: ...pe diffuser into two external ducts which convey the air to the combustion section b Combustion Section The combustion section consists of the outer combustion case and combustion liner A spark igniter and fuel nozzle are mounted in the aft end of the outer combustion case c Turbine The turbine consists of a gas producer turbine support a power turbine support a turbine and exhaust collector suppo...

Страница 61: ...TM 55 1520 228 10 Change 11 2 19 FIGURE 2 10 HAS BEEN DELETED ...

Страница 62: ...TM 55 1520 228 10 2 20 Change 11 Figure 2 11 Engine ...

Страница 63: ...nlet fittings Air enters the inlet tube and is spun by the swirl tube Clean air then enters the engine inlet plenum chamber through the outlet tube while foreign material is centrifuged into the scavenge system The foreign material is ejected overboard by the vacuum cleaner effect created by engine bleed air as it is discharged through venturies in the eductor tubes Reverse flow inlet fairings may...

Страница 64: ...TM 55 1520 228 10 Figure 2 12 Overhead Console 2 22 Change 10 ...

Страница 65: ...TM 55 1520 228 10 Figure 2 12 1 Overhead Console with AN ARC 201 Typical Change 10 2 22 1 2 22 2 blank ...

Страница 66: ......

Страница 67: ...ed Regulated power turbine speed may be adjusted in flight through the op erating range by movement of the switch as required f Gas Producer Fuel Control The gas producer fuel control has a bypass valve metering valve ac celeration bellows governing and enrichment bellows manually operated cutoff valve maximum pressure relief valve and a torque tube seal and lever assembly A maximum pressure relie...

Страница 68: ...etween the housing and the filter unit Probe type magnetic chip detectors are installed at the bottom of the power accessory gearbox and the engine oil outlet connection All engine oil system lines and connections are internal with the exception of pres sure and scavenge lines to the front compressor sup port the gas producer turbine support and the power turbine support The oil cooler blower is a...

Страница 69: ...TM 55 1520 228 10 2 25 Figure 2 13 Instrument Panel and Console Typical A ...

Страница 70: ...TM 55 1520 228 10 2 26 Change 11 Figure 2 14 Instrument Panel and Console Typical C ...

Страница 71: ...TM 55 1520 228 10 Figure 2 14 1 Instrument Panel and Console with AN ARC 201 A Typical Change 10 2 26 1 ...

Страница 72: ...er Vertical Speed Indicator Altitude Indicator RBHI Course Deviation Indicator Airspeed Indicator Dual Tachometer Torque Indicator Flip filter provided for following Rotor RPM Master Caution Caution Advisory APR 39 MA Light Figure 2 14 2 Instrument Panel and Console with AN ARC 201 C Typical 2 26 2 Change 10 ...

Страница 73: ...nstrument panel e C Turbine Outlet Temperature Indicator The turbine outlet temperature TOT indicator figure 2 14 located in the instrument panel displays temperature in degrees Celsius of the exhaust gases in the N1 turbine outlet area The indicator is powered by 28 Vdc and protected by TURB OUTLET TEMP circuit breaker f Gas Producer Tachometer The gas producer tachometer generator located on the...

Страница 74: ... transmitter one low fuel transmitter and one fuel sump drain Installed in top of the cell is one fuel quantity transmitter a vent line and a boost pump pressure switch A fuel filler cap is located on the right side just aft of the passenger door The fuel shut off valve is mounted on the right side of the aircraft above the fuel cell cavity and is manually operated by the fuel valve handle on the ...

Страница 75: ...TM 55 1520 228 10 Figure 2 15 Auxiliary Fuel System 2 29 ...

Страница 76: ...ost caution light may indicate impending fuel starvation The system is powered by 28 VDC and projected by Caution PNL LTS circuit breaker e Fuel Filter Caution Light The FUEL FILTER caution light figure 2 13 and figure 2 14 located in the caution panel will illuminate when the filter in the fuel supply line becomes partially obstructed The system is powered by 28 Vdc and protected by CAUTION PNL L...

Страница 77: ...ective lever located on the left of the copilot position contains only a twist type throttle at the forward end of the control a Copilot Collective Pitch Control Stowage 1 Remove the boot around copilot stick shaft 2 Loosen knurled nut at base of copilot stick Remove stick 3 Stow stick in clips located on forward side of copilot seat b Copilot Collective Pitch Control Installation 1 Remove stick f...

Страница 78: ... variable delivery pump and reservoir servo actuators with irreversible valve circuits for cyclic and collective controls a pressure line filter a return line filter and a solenoid shutoff valve The pump is located on the transmission The hydraulic system provides for fully powered flight controls during authoritative flight 2 33 CONTROL A hydraulic system switch HYD BOOST is located on the lower ...

Страница 79: ...the elastomeric isolation mount b The drag pin has a metal pin which is commonly referred to as the spike The drag pin or spike physically is mounted so that it rides inside the square metal opening of the transmission mount support c The isolation mount is used to dampen pylon to fuselage vibration and limit pylon rock Movement of the transmission and isolation mount is limited by means of the dr...

Страница 80: ... aluminum honey comb filler The main rotor is driven by the mast which is connected to the transmission The rotor RPM is gov erned by the engine RPM during powered flight The rotor tip path plane is controlled by the cyclic stick The rotor pitch is controlled by the collective lever 2 43 MAIN ROTOR RPM INDICATOR CAUTION The same audio tone is used for both the rotor rpm warning and engine out warn...

Страница 81: ...ver the windshield Lower nose window defog is continuous and automatic when HTR switch is turned on Outside fresh air from an intake on the top of the fuselage nose is directed through the windshield defog nozzles mounted on the lower windshield frame A VENT PULL control on the right side of the instrument panel figure 2 16 opens and closes the fresh air intake b Operation A circuit breaker switch...

Страница 82: ... 2 Heater Control Knob 9 Post Plenum 16 Air Distribution Vents 3 Heat Control Cable 10 Air Distribution Valves Cargo Passenger Area 4 Bleed Air Tube 11 Windshield Defog Nozzle 17 Pilot Seat Back REF 5 Mixing Valve 12 Plenum Drain 18 Copilot Seat Back REF 6 Plenum 13 Plenum Valve Assembly Figure 2 16 Heating and Ventilation A Sheet 1 of 2 2 36 Change 14 ...

Страница 83: ...utoff Valve 27 Igniter Plug 21 Fuel Pump 28 Duct 22 Fuel Pressure Relief Valve 29 Firewall Shutoff Control 23 Fuel Filter 30 Heat Control Knob 24 Heater 31 Pilot Seat Back 25 Combustion Blower 32 Copilot Seat Back Figure 2 16 Heating and Ventilation Sheet 2 of 2 Change 14 2 37 ...

Страница 84: ...TM 55 1520 228 10 Figure 2 17 Heater Control and Vent Pull Knobs 2 38 Change 12 ...

Страница 85: ...de control is for temperature and the right side control operates the heater shutoff valve in the event of fumes fire or heater malfunction A heater fail light is mounted on the console and will indicate heater malfunction Consumption of fuel is 3 5 gallons per hour for 30 000 BTU heater and 4 5 gallons per hour for the 50 000 BTU heater Refer to figure 2 16 b Combustion Heater Pre Start Check 1 F...

Страница 86: ...er is delivered from the battery to the essential bus 4 Generator Switch The generator switch is located on the overhead console and is a three position switch This switch is labeled GEN in the forward position OFF in the center position and RESET in the aft position The RESET position is spring loaded to return to the OFF position when released Therefore to reset the generator the switch must be ...

Страница 87: ...FIELD GENERATOR BUS RESET GEN BUS RESET CAUTION PANEL CAUTION PNL LTS SIGNAL LIGHT SIGNAL LT INSTRUMENT LIGHTS INST LTS ANTI COLLISION LIGHTS ANTI COLL LTS SRCH LANDING LT POWER SRCH LT PWR C ENGINE OIL BYPASS ENG OIL BYPASS GOVERNOR CONTROL GOV CONT FUEL BOOST PUMP FUEL PUMP STARTER START ENG IGNITER AND AUTO RELIGHT IGN ENG ENGINE ANTI ICE ENG DEICE ATTITUDE SYSTEM ATTD TURN C ATTITUDE SYSTEM AT...

Страница 88: ...d AC circuit breakers The inverter switch is located in the overhead console and is a two position toggle switch labeled INV and OFF AC electrical power is provided to the electrical system when the switch is in the forward position DC power to the inverter is supplied by the non essential bus therefore to have AC power electrical power must be available at the non essential bus When the switch is...

Страница 89: ...OLLISION LIGHTS The anti collision lights are located one on top of the en gine cowling and one centered at the lower section of the fuselage aft of the avionics compartment Electri cal power for the anti collision lights is provided by the 28 volt DC electrical system essential bus The anti collision light switch is located on the overhead con sole figure 2 12 The switch is a two position toggle ...

Страница 90: ... over the ROTOR RPM warning light of the warning panel figure 2 13 items 8 and 9 for flights using NVG and adjusted away from the ROTOR RPM warning light for flights not using NVG A hinged light filter is also at tached to the instrument panel for the other warning lights and master caution lights for use in the same manner b NVG compatible panel lights provide lighting of the ICS boxes KY28 and t...

Страница 91: ...Below an altitude of 10 000 feet a diagonal warning symbol will appear on the 10 000 foot counter A barometric pressure setting knob is provided to insert the desired altimeter setting in inches of Hg A DC pow ered vibrator operates inside the altimeter whenever air craft power is on 2 Operation a Normal Operation The ALT VIB or ALT AAU 31 32A circuit breaker must be in The altimeter indicates pne...

Страница 92: ...TM 55 1520 228 10 Figure 2 18 1 AAU 32 A Altitude Encode Pneumatic Altimeter 2 46 Change 4 ...

Страница 93: ...tion to the IFF trans ponder the CODE OFF flag must not be visible A vibra tor powered by the DC essential bus is contained in the altimeter and requires a minimum of one minute war mup prior to checking or setting the altimeter 2 Abnormal Operation a If the altimeters internal vibrator be comes in operative due to internal failure of DC power failure the pointer and drum may momentarily hang up w...

Страница 94: ...d in the front of the logbook 2 68 VERTICAL SPEED INDICATOR The vertical speed indicator figure 2 13 and figure 2 14 displays the helicopter ascent and descent speed in feet per minute the indicator is actuated by the rate of atmo spheric pressure change 2 69 C CONUS NAVIGATION SYSTEM AN ARN 123 Refer to Chapter 3 2 70 RADAR ALTIMETER AN APN 209 Refer to Chapter 3 2 71 RADAR WARNING SYSTEM Refer t...

Страница 95: ...TM 55 1520 228 10 Change 11 2 47 Figure 2 19 Warning and Caution Panels ...

Страница 96: ...d figure 2 14 is pressed to check for illumination of all the warn ing lights SECTION XIV SERVICING PARKING AND MOORING 2 73 SERVICING a Servicing Diagram Refer to figure 2 20 and fig ure 2 21 b Fuels Oils Fluids Specifications and Ca pacities Refer to table 2 1 2 74 APPROVED FUELS OILS AND FLUIDS a Fuels Refer to table 2 2 b Oils Refer to table 2 3 c Fluids Refer to table 2 4 2 75 FUEL TYPES See ...

Страница 97: ...r 16 Hydraulic Filler Cap 6 Fuel Tank Filler 17 External Power Receptacle 7 Auxiliary Fuel Cell 18 Fuel Cell Sump Drain Valve 8 Static Ground Receptacle 19 Relief Valve 9 Pillow Block Reservoirs 20 Fitting Lubrication Grease Lubrication 10 Transmission Oil Filler Cap 21 Fitting Lubrication Grease Lubrication 11 Transmission Oil Filter Figure2 20 Servicing Diagram Sheet 1of 2 Change 14 2 49 ...

Страница 98: ...TM 55 1520 228 10 Figure 2 20 Servicing Diagram Sheet 2of 2 2 50 Change 11 ...

Страница 99: ... Receiver 12 Hydraulic Sight Glass 5 Transmission Sight Glass 13 Static Ground Receptacle 6 Transmission Filler Cap 14 Fitting Lubrication Grease Lubricated Hub 7 Tail Rotor Gearbox Filler Cap 15 Relief Valve Grease Lubricated Hub 8 Tail Rotor Gearbox Sight Glass 16 Fitting Lubrication Grease Lubricated Hub 9 Engine Oil Filler Cap 17 Hydraulic Reservoir Figure 2 21 Servicing Diagram Change 14 2 51...

Страница 100: ...ber 7D 1 shall not be used in OH 58A C engine or helicopter systems It contains additives which are harmful to seals in the systems Engine Oil Note 2 MIL L 7808 NATO Code is 0 148 For use in ambient temperatures below minus 32 C 25 F MIL L 23699 NATO Code is 0 156 For use in ambient temperatures above minus 32 C 25 F 11 2 U S Pt Lubrication oil made to MIL L 7808 by Shell Oil Company un der their ...

Страница 101: ... water If liquid contacts eyes flush immediately with clear water If liquid is swallowed do not induce vomiting get immediate medical attention Wear rubber gloves when handling liquid If prolonged contact with mist is likely wear an appropriate respirator When fluid is decomposed by heating toxic gases are released Hydraulic Fluid MIL H 5606 Note 3 Fill to overfill lip in reservoir Reservoir MIL H...

Страница 102: ...50 Jet A 1 Texaco Texaco Avjet B Avjet A Avjet A 1 Union OIl Union JP 4 76 Turbine Fuel FOREIGN FUEL NATO F 40 NATO F 44 Belgium BA PF 2B Canada 3GP 22F 3 6P 24e Denmark JP 4 MIL T 5624 France Air 3407A Germany West VTL 9130 006 UTL 9130 007 UTL 9130 010 Greece JP 4 MIL T 5624 Italy AA M C 1421 AMC 143 Netherlands JP 4 MIL T 5624 D Eng Rd 2493 Norway JP 4 MIL T 5624 Portugal JP 4 MIL T 5624 Turkey...

Страница 103: ...et Engine Oil 5 Crew Chemical Corp STO 21919 STO 21919A STD 6530 W R Grace and Co Hatco Chemical Div HATCOL 3211 3611 Exxon Turbo Oil 2380 WS 6000 2395 WS 6459 2392 2393 Mobile Oil Corp RM 139A RM 147A Avrex S Turbo 260 Avrex S Turbo 265 Royal Lubricants Co Royco 899 C 915 899SC Stauffer Jet II Shell Oil Co Inc Aeroshell Turbine Oil 500 Shell International Petroleum Co Ltd Aeroshell Turbine Oil 55...

Страница 104: ...4607 Royal Lubricants Co Royco 756C D DS 437 Shell Oil Co XSL 7828 Standard Oil Co of California PED 3565 PED 3337 Texaco Inc TL 5874 Stauffer Chemical Co Aero Hydroil 500 Union Carbide Chemical Co YT 283 Union Carbide Corp FP 221 NOTE Mixing of hydraulic fluids is authorized only in emergency situations An entry in the remarks section of DA Form 2408 13 is required APPROVED COMMERCIAL MIL H 83282...

Страница 105: ...th liquid or mist can irritate eyes and skin After any prolonged contact with skin immediately wash contacted area with soap and water If liquid contacts eyes flush immediately with clear water If liquid is swallowed do not induce vomiting get immediate medical attention Wear rubber gloves when handling liquid If prolonged contact with mist is likely wear an appropriate respirator When fluid is de...

Страница 106: ...cified fuel Refer to table 2 1 In the event of major spillage of fuel all powered equipment will be shut down All personnel will leave the vicinity and be positioned to prevent any sources of possible ignition from entering area The fire department will be summoned to the area to render safety NOTE Settling time for AVGAS is 15 minutes per foot of tank depth and one hour per foot depth for jet JP ...

Страница 107: ...TM 55 1520 228 10 Figure 2 22 Gravity Refueling With Closed Circuit Receiver 2 59 ...

Страница 108: ...of receiver until slot is lined up with fuel port in bottom of receiver Position nozzle into port in order to bypass closed cir cuit refueling system if caution is not used to prevent damage to inner sleeve of receiver at fuel port through improper use of nozzle d Gravity Refueling 1 Ground the helicopter at the receptacle lo cated adjacent to the filler cap on the helicopter to the filler nozzle ...

Страница 109: ...TM 55 1520 228 10 Change 11 2 61 Figure 2 23 Refueling Receptacle ...

Страница 110: ...port is closed and flange of sleeve is in contact with rivet at base of receiver cylinder Refer to figure 2 23 CAUTION Ensure that servicing unit pressure is not above 125 PSI while refueling c Insert fueling nozzle into receiver and actuate automatic nozzle lever to ON or FLOW position Pin at base of nozzle will momentarily indicate when fuel flow stops d Fuel flow will automatically shut off whe...

Страница 111: ...tion indicates a possible failure of engine gearbox seal s which is allow ing oil to transfer from the transmission through the freewheeling unit Engine oil tank is located aft of engine and oil cooler fan Oil level is checked by a trapped ball sight gage on tank figure 2 20 and figure 2 21 Ball must be seen floating in oil for safe oil level Refer to table 2 1 for authorized oil 2 80 TRANSMISSION...

Страница 112: ... Structural damage can occur from flying objects during high wind conditions Helicopter should be hangared or evacuated to a safe weather area when wind conditions above 50 knots are expected CAUTION The mooring hardware is to be carried in the flyaway kit Flying the OH 58 with mooring hardware installed may result in damage to aircraft s honeycomb surface Retain all installation hardware together...

Страница 113: ... covers will aid in preventing marring and scratching of windshields and is accomplished as fol lows 1 Route strap from pitot tube through lower front edge of pilot door near lower hinge and then out the top edge of door to engine air inlets 2 Cut strap connecting pitot cover to engine shields strap at both ends Pitot tube cover may be held in place with the nylon cord and or a scrapped packing of...

Страница 114: ...king and Tiedown Fitting 3 Exhaust Covers 4 Aft Jacking and Tiedown Fitting 5 Main Rotor Blade Tiedown 6 Tail Rotor Tiedown 7 Engine Air Inlet Shield 8 Ground Handling Gear 9 Towing Ring Figure 2 24 Ground Handling Equipment Covers Rotor Tiedowns and Mooring Diagram ...

Страница 115: ...TM 55 1520 228 10 Change 11 2 67 2 68 blank Figure 2 25 Paved Surface Mooring Configuration OH 58A C ...

Страница 116: ......

Страница 117: ...mmunication System Control C 6533 ARC Communication Control Interphone for pilot and crew Integrates all communication equipment Stations within helicopter Radio Set AN ARC 114FM FM Radio Set Two way Voice Communications in frequency range of 30 00 to 75 95 MHz Line of sight Radio Set AN ARC 114A VHF FM FM Radio Two way Voice Communications in frequency range of 30 00 to 75 95 MHz Line of sight Ra...

Страница 118: ...et Transmit a special coded reply to ground based IFF radar interrogator system Radio Set AN ARN 123 V 1 Conus Navigation Receiver With appropriate instrumentation provides VHF omni directional range VOR localizer LOC glideslope GS and marker beacon MB position information Line of sight Radar Altimeter AN APN 209 Radar Altimeter Provides altitude indication above terrain Permits selected altitude ...

Страница 119: ...slope signal information Command Radio Set Control C 6287 Control Indicator C 6287 Secure Voice Control Indicator Control Indicator C 8157 ARC Computer Kit 1A TSEC IFF Computer Radar Warning AN APR 39 Radar Warning Set Visual and Audible Warning when a high radar threat environment is encountered Line of sight SINCGARS Radio Set AN ARC 201 FM Radio Set Two way Voice Communications in frequency ran...

Страница 120: ...p Transponder 15 Antenna Radar Warning Blade 6 Antenna VOR Right Side 16 Antenna Radar Altimeter 7 Antenna VHF FM 17 Antenna Radar Altimeter C 8 Antenna VOR Left Side 18 Antenna Bottom Transponder A 9 Antenna Radar Warning Aft Side Shown 19 Antenna UHF Aft Right Side Opposite 20 Antenna Bottom Transponder 10 Antenna FM Homing Left Side Shown Right Side Opposite Figure 3 1 Antenna Locations 3 4 Cha...

Страница 121: ... frequency range of 30 00 to 75 95 MHz on 920 channels for a 50 mile distance as limited by line of sight A guard receiver incorporated in the set is fixed tuned to 40 50 MHz Retransmission of voice CW or X mode communications is possible when a second set is installed in the helicopter The radio sets are marked VHF FM COMM and are installed in the center console Antenna location is located as sho...

Страница 122: ...E Switch Permits hand free intercommunications regardless of the position of the transmit interphone selector Permits hand free intercommunications with transmit inter phone selector in the ICS position C 5 VOL Control Adjust volume from receivers Adjust intercommunications volume 6 Transmit Interphone Selector Selects transmitter to be keyed and connects microphone to transmitter 1 FM 2 UHF 3 VHF...

Страница 123: ... in the aircraft May be used also for normal voice communications 2 Frequency Selectors Left Selector Selects first two digits of desired frequency Right Selector Selects third and fourth digits of desired frequency 3 RCVR TEST When pressed audible signal indicates proper receiver performance 4 AUDIO Adjusts receiver volume 5 SQUELCH Squelch control adjusted by maintenance personnel only 6 SQUELCH...

Страница 124: ...tions within the frequency range of 225 00 to 399 95 MHz on 3500 channels for a distance of approximately 50 miles as limited by conditions A guard receiver is incorpo rated in the set and is fixed tuned to 243 00 MHz Both receivers are disabled during transmitter operation The radio set is marked UHF AM COMM and is mounted in the bottom center section of the instrument panel The UHF radio transmi...

Страница 125: ... is ADF Power to operate the ARC 164 V radio is from the 28 vdc emergency bus through a circuit breaker marked UHF AM on the pilot overhead circuit breaker panel UHF AM Antenna location is shown in figure 3 1 b RT 1167C ARC 164 V The Receiver Trans mitter Radio RT 1167C ARC 164 V figure 3 6 has the same functions and capabilities as the RT 1167 ARC 164 V plus a HAVE QUICK mode of operation HAVE QU...

Страница 126: ...io set can be used for these modes of operation 1 Control Mode Settings a MAN mode two way voice commu nications b BOTH mode utilizing the transceiver constant monitoring of guard receiver without losing the use of the transceiver c Transmission of 1 020 Hz TONE signal 2 Transmit Receive MAIN mode a Set OFF MAIN BOTH ADF selector switch to MAIN b Set MANUAL PRESET GUARD selec tor switch to MANUAL ...

Страница 127: ...o The HAVE QUICK modified radios retain the standard single frequency UHF voice mode of operations This is referred to as the normal mode while frequency hopping operation is called the anti jam AJ mode Several ingredients are necessary for suc cessful system operations These are 1 Common frequency 2 Time synchronization 3 Common hopping pattern and rate 4 Common net number The common frequencies ...

Страница 128: ...te arrives within 60 seconds of the time the T posi tion has been selected To receive time in the normal mode rotate the A 3 2 T knob to the T position and return to a normal channel in either the manual or preset mode To receive a time update in AJ mode rotate the A 3 2 T knob to the T position and then back to the A position A TOD update time tick can be received on the selected AJ net 8 Net Num...

Страница 129: ...cted for normal communications D F Not used RETRAN Not used 2 Frequency Selectors Left Selector Selects first three digits of desired frequency Right Selector Selects fourth fifth and sixth digits of desired frequency 3 RCVR TEST When pressed audible signal indicates proper receiver performance 4 AUDIO Adjusts receiver volume 5 SQUELCH Squelch control adjusted by maintenance personnel only 206075 ...

Страница 130: ...ons D F Not used RETRAN Not used 2 Frequency Selectors Left Selector Selects first two digits of desired frequency Center Selector Selects third digit 1 MHz steps of desired frequency Right Selector Selects last two digits of desired frequency 3 RCVR TEST When pressed audible signal indicates proper receiver performance 4 AUDIO Adjusts receiver volume 5 SQUELCH Squelch control adjusted by maintena...

Страница 131: ...lector MANUAL Frequency selected with frequency selector knobs PRESET Selects preset channel as desired by CHAN selector GUARD Frequency is automatically positioned to guard channel 243 00 MHz 4 SQUELCH OFF Received unsquelched ON Received squelch operating 5 VOL Control Adjust receiver audio volume 6 TONE When pressed audible tone indicates proper receiver transmitter performance transmits on sel...

Страница 132: ...ch Both c Manual preset guard switch Preset d Manual frequency display Set WOD 15 e Preset channel select Set to 15 f Preset button under frequency cover Press g Manual frequency display Set WOD 16 h Preset channel select Set to 16 i Preset button Press j Repeat steps g thru i to store WOD 17 18 19 k Manual frequency display Set 300 050 l Preset channel select Set to 20 m Preset button Press n Rot...

Страница 133: ...TM 55 1520 228 10 Change 11 3 13 FIGURE 3 7 HAS BEEN DELETED ...

Страница 134: ...ins the crypto net variable CNV you desire c Set the POWER switch to ON d Set the PLAIN C RAD switch to C RAD e If the signal is to be retransmitted set the DELAY switch to ON f At this time a crypto alarm and background noise in the aircraft audio intercom system should be heard To clear this alarm press and release PTT in the aircraft audio intercom system Secure voice commu nication is now poss...

Страница 135: ...ssociated radio set 4 C RAD2 Location of stop for C RAD2 on front panel Switch stop 5 FILL switch Permits pilot to select one of 6 storage registers for six position filling rotary switch 6 MODE Switch In the OP position KY 58 normal operating three position In the LD position for filling rotary In the RV position KY 58 in Receive Variable Filled from another external source 7 POWER ON switch Conn...

Страница 136: ...in the variable which is being replaced d Upon instructions from the Net Controller 1 Listen for a beep on your headset 2 Wait two seconds 3 Set the RCU MODE switch to OP 4 Confirm e If the MK operation was successful the Net Controller will now contact you via the new CNV f If the MK operation was not successful the Net Controller will contact you via clear voice plain trans mission with instruct...

Страница 137: ... 3 36 DESCRIPTION DIRECTION FINDER SET AN ARN 89 The direction finder set ADF AN ARN 89 figure 3 9 is used in conjunction with gyromagnetic compass and intercommunications systems ADF bearing information is indicated on the heading radio bearing indicator fig ure 3 10 The bearing pointer displays either the ADF bearing or the VOR bearing depending on the position selected on the RMI BRG PNTR switc...

Страница 138: ...most accurate tuning of the receiver when function selector is in the COMP position 5 CW VOICE TEST Switch CW Provides tone that may be used for identification tuning or for loop operation VOICE Permits normal aural reception TEST Rotates ADF needle 180_ from original bearing to provide a check of needle accuracy with function selector in the COMP position Inoperative in LOOP and ANT position The ...

Страница 139: ...o or slaved to the earth s magnetic field when oper ated in the MAG mode magnetically slaved It provides heading information in the form of a synchro output to the radio bearing heading indicator and by presenting the magnetic heading as a reference signal to the VOR C 3 41 CONTROLS AND FUNCTIONS GYRO MAGNETIC COMPASS SET Refer to paragraph 3 42 3 42 OPERATING PROCEDURES GYRO MAGNETIC COMPASS SET ...

Страница 140: ...e immedi ate and accurate synchronization 4 ADF Pointer Indicates bearing of radio station from helicopter 5 Synchronizing Knob Determines the heading synchronization 6 Signal Strength Indicator Indicates the presence or absence of FM radio signal 7 Steering Indicator Indicates helicopter deviation from a direct approach to the FM radio transmitter 8 Station Approach Indicator Indicates aircraft s...

Страница 141: ...ter is to the left of the helicopter 2 An FM signal strength indicator shows red whenever the FM radio receiver signal is absent or is too weak for a reliable indication When the signal strength is acceptable the FM signal strength indicator shows black 3 The station approach indicator indicates helicopter approach to the FM radio transmitter The pointer moves down as the transmitter is approached...

Страница 142: ...on volume OFF Turns set OFF 3 MB SENS Switch HI Selects high receiver sensitivity LO Selects low receiver sensitivity 4 Frequency Selectors Right Selects the fractional megahertz portion of the desired frequency Left Selects the whole megahertz portion of the desired frequency 5 VOR MB TEST Switch Provides on and off capability for the VOR MB self test circuit within the receiver 206075265 Figure ...

Страница 143: ...iably weak or malfunction in receiver 5 To From Flag Indicates whether flying selected radial would direct helicop ter toward TO or from FR VOR station 6 Omnibearing Selector OBS Drives course deviation card for course selection 7 Reciprocal Course Index Indicates radial 180 degrees from selected radial 8 Glide Slope Warning Flag Red GS flag indicates GS signal is unreliably weak or mal function i...

Страница 144: ... BRG PTA switch located on instrument panel VOR 7 Interphone control panel AUX switch ON 8 Interphone control panel VOL control Ad just b Stopping Procedure NAV VOL and MB VOL switch controls OFF 3 51 COURSE DEVIATION INDICATOR CDI 3 52 DESCRIPTION COURSE DEVI ATION INDICATOR The CDI ID 1347C ARN figure 3 12 is mounted on the right side of the instrument panel and displays VOR LOC and GS bearing i...

Страница 145: ...e programmed prior to flight to display any one of many classified opera tional codes for security identification The effective range depends on the capability of interrogating radar and line of sight The code setting can be mechanically retained On the instrument Panel and Console place the IFF CODE HOLD OFF switch to the HOLD position On the Transponder Set Control Panel turn CODE switch to HOLD...

Страница 146: ......

Страница 147: ...nable set to reply to TEST mode interrogations Other functions of this switch position are classified MON Enables the monitor test circuits OUT Disables the RAD TEST and MON features 3 IDENT MIC Switch IDENT Initiates identification reply for approximately 25 seconds OUT Prevents triggering of Identification reply Spring loaded to OUT MIC Not used 4 MODE 3 A Code Select Switches Selects and Indica...

Страница 148: ... light 10 REPLY Indicator Lights when valid MODE 4 replies are present or when pressed NOTE Computer must be installed before set will reply to a MODE 4 interrogation 11 M 2 Switch ON Enables the set to reply to MODE 2 interrogations OUT Disables the reply to MODE 2 interrogations TEST Provides test of MODE 2 interrogation by indication on TEST light 12 TEST Indicator Lights when the set responds ...

Страница 149: ...ter is lim ited to line of site transmission since its frequency of operation is in the UHF band making range dependent on altitude The Mode 4 codes can be mechanically retained On the instrument Panel and Console place the HOLD OFF switch to the HOLD position On the Transponder Set Control Panel turn the CODE switch to HOLD only momentary action is required Turn the master switch or helicopter po...

Страница 150: ...DIV Selects both top and bottom antenna 4 RAD TEST Switch RAD TEST Enables set to reply to TEST mode interrogations OUT Disables to RAD TEST features 5 MASTER Control OFF Turns set OFF STBY Places in warmup standby condition NORM Set operates at normal receiver sensitivity EMER Transmits emergency replay signal to MODE 1 2 or 3 A interrogations regardless of mode control settings 206075 268 1 Figu...

Страница 151: ...Selects and indicates the MODE 2 four digit reply code number 10 MODE 1 Code Select Switches Selects and indicates the MODE 1 two digit reply code number 11 CODE CONTROL Holds zeroizes or changes MODE 4 code 12 MODE 4 TEST Switch TEST Selects MODE 4 BIT operation ON Selects MODE 4 ON operation OUT Disables MODE 4 operation 13 MODE 4 AUDIO LIGHT Control AUDIO MODE 4 is monitored by audio LIGHT MODE...

Страница 152: ...TM 55 1520 228 10 FIGURE 3 15 HAS BEEN DELETED 3 30 Change 10 ...

Страница 153: ...tude limit index Actuates LO level warning flag when limit reached 4 HI Level Warning Flag Indicates HI when altitude reaches respective limit index 5 High Limit Index Manually sets high altitude limit index Actuates HI level warning flag when limit reached 6 Altitude Pointer Indicates actual clearance in feet from helicopter to terrain zero to 1500 feet 7 HI SET Control Knob Sets high altitude li...

Страница 154: ...t the aircraft probably could not be maneuvered to avoid the object a Altimeter Operation 1 LO SET control knob Rotate clockwise from OFF Set low limit index as desired 2 HI SET control knob Set high limit index as desired b Self Test Operation 1 High limit index Set to 800 feet 2 Low limit index Set to 80 feet 3 HI SET control knob Push and hold Verify pointer indicates 1000 100 feet digital disp...

Страница 155: ... the knob clockwise until the LO bug is positioned above the pointer again The ALTITUDE LOW TOO LOW audio warning should be again heard at its initial FULL volume level 5 Lower knob Adjust counterclockwise until the LO bug is below the pointer but not quite to the OFF position The warning audio should cease The LO indicator should be extinguished 6 Lower right knob Depress and hold to put the Rada...

Страница 156: ... test should be initiated after approximately one minute Self test can be performed in MODE ONE or MODE TWO In MODE ONE the synthetic voice will announce SELF TEST SET VOLUME 1 2 3 4 5 6 7 8 9 10 11 12 In MODE TWO the synthetic voice will an nounce SELF TEST SET VOLUME 5 4 3 2 1 2 The CRT will display specific software ver sion numbers i e operational flight program OFP at the 12 o clock position ...

Страница 157: ...TM 55 1520 228 10 3 32 3 ...

Страница 158: ...lf test Self test described in paragraph 3 70 a 3 MODE Switch MODE 1 up Selects normal message format MODE 2 down Selects test abbreviated message format Mode 2 reduces audio distractions when operating in dense signal environments 4 AUDIO Control Sets synthetic voice audio level volume to the aircraft ICS Turn AUDIO control clockwise to increase volume Turn AUDIO control counterclockwise to decre...

Страница 159: ...s are not used in AN APR 39A V 1 2 MA Lamp Switch MA lamps are not used in AN APR 39A V 1 3 BRIL Control Varies Indicator display brightness Turn clockwise to increase brightness Turn counterclockwise to decrease brightness Adjust BRIL control for best readable display 4 Lethality Ring The most lethal threats are within this ring 5 Tick Marks At 30 degree increments provide relative bearing refere...

Страница 160: ...ROIZE SWITCH a Transmit Receive 1 FUNCTION selector switch SQ ON 2 MODE selector switch SC 3 PRESET selector switch MAN 4 IFM RF PWR selector switch Set as re quired 5 Frequency Select frequency using key pad as follows a FREQ key Press b CLR key Press c Key in desired frequency d STO ENT key Press 6 VOL Adjust 7 Transmit Transmit Interphone selector position No 1 No 5 for FM 2 b Frequency Hopping...

Страница 161: ...preset at any time just by pressing the push to talk on the headset 1 Starting Scanning a Set RT switches FUNCTION SQ ON MODE FH PRESET CUE Set other switches as needed b Press STO Sto ENT button on RT The display reads SCAN c Press a number 0 8 This tells the RT which preset has priority 0 is MAN 7 is CUE 8 is no priority 2 Transmitting on a Locked in Preset Press push to talk and speak into head...

Страница 162: ... OFF Receiver On Transmitter Standby Squelch Disabled RXMT Activates retransmission mode when second FM set is installed LD In this position preset frequencies time ECCM net parame ters and lockout channels may be entered LD V In this position TRANSEC variable is loaded into the RT Z A When activated all ECCM TRANSEC variables are zeroed STOW Completely disables all radio circuits during an extend...

Страница 163: ...FH M mode frequency hopping nets are selected CUE Allows a non ECCM radio to signal an ECCM radio that is in FH mode 4 IFM RF PWR Selector OFF Off Bypass LO Low Power NORM Normal Power HI High Power 5 VOL Adjusts receiver volume 6 Display Indicates active frequency Hopset numbers Failure codes and Key board inputs 7 Keyboard The keyboard is a 15 button array of pressure switches used to insert or ...

Страница 164: ......

Страница 165: ...4 MISSION EQUIPMENT SECTION I MISSION AVIONICS NOT APPLICABLE SECTION II ARMAMENT NOT APPLICABLE PAGES 4 2 THROUGH 4 20 INCLUDING PARAGRAPHS 4 1 THROUGH 4 29 AND FIGURES 4 1 THROUGH 4 10 HAVE BEEN DELETED Change 10 4 1 4 2 blank ...

Страница 166: ......

Страница 167: ...s and ranges are illustrated by the colored markings which appear on the dial faces of engine flight and utility system instruments Red markings on the dial faces of these instruments indicate the limit above or below which continued operation is likely to cause damage or shorten life The green markings on instrument indicate the safe or normal range of operation The yellow markings on instruments...

Страница 168: ...TM 55 1520 228 10 Figure 5 1 Instrument Markings A 5 2 Change 11 ...

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Страница 170: ...TM 55 1520 228 10 Figure 5 2 Instrument Markings Sheet 1 of 3 5 3 blank 5 4 Change 14 ...

Страница 171: ...TM 55 1520 228 10 Change 11 5 5 Figure 5 2 Instrument Markings Sheet 2 of 3 ...

Страница 172: ...TIONS a The helicopter can be started in a maximum wind velocity to 45 knots and a maximum gust spread of 15 knots NOTE Gust spreads are not normally reported To ob tain spread compare minimum and maximum wind velocities b Maximum wind for hovering is 35 knots cross wind and 30 knots tailwind c Maximum wind for mooring is 65 knots parallel to the ground in any direction 5 9 DELETED 5 10 TOWING LIM...

Страница 173: ... section of DA Form 2408 13 1 is required for each time emergency fuel is used 2 Practice autorotation is prohibited using emergency fuel 5 13 DELETED 5 14 ENGINE STARTING LIMITATIONS During starting if N1 does not reach 58 percent in a total time of 45 seconds or 60 seconds below 10_C FAT close throttle and press starter switch until TOT is below 200_C If engine fails to start on third attempt ab...

Страница 174: ...own with only one cockpit door or one cabin door re moved b Whenever any OH 58A C helicopter is operated without its cabin doors 1 All soundproof blankets must be in service able condition and firmly attached Pilot must verify 2 If the rear cushions bottom and back are modified per MWO 55 1520 228 30 30 they may re main installed provided seat belts and shoulder har nessses are installed properly ...

Страница 175: ...TM 55 1520 228 10 Change 11 5 9 T63 A 720 Figure 5 3 Airspeed Operating Limits Chart ...

Страница 176: ...LOW G S Flight at less than 0 5g is prohibited 5 26 FLIGHT RESTRICTIONS FOR PRAC TICE AUTOROTATION LANDINGS Figure 5 4 Practice autorotation landings may be accomplished subject to the following limitations a A qualified OH 58A C IP must be in position to take control of the aircraft b Reported surface winds must not exceed 20 knots c Surface crosswind component must not exceed 10 knots Wind gust ...

Страница 177: ...NDING TAKE OFF LIMITATIONS Slope Operations shall be limited to slopes of 8 degrees or less CAUTION Caution is to be exercised for slopes greater than 5 degrees since rigging loading terrain and wind conditions may alter the slope landing capability See Rollover characteristics in FM 1 203 Change 2 5 11 ...

Страница 178: ...sults in spray ingestion indicated by spray on the windshield should be avoided Salt spray ingestion in turbine engines may result in a deterioration in performance as well as a loss in com pressor stall margin When operating within 10 miles of salt water or within 200 miles of volcanic activity appro priate entries should be made on DA Form 2408 13 1 to alert maintenance 5 32 FLIGHT IN SAND AND D...

Страница 179: ...CATION OF HELICOPTER Army Model OH 58A C is in Class 2 Additional direc tives governing weight and balance of Class 2 aircraft forms and records are contained in AR 95 1 TM 55 1500 342 23 and DA PAM 738 751 6 3 HELICOPTER STATION DIAGRAM Figure 6 1 shows the helicopter reference datum lines fuselage stations buttlines and waterlines The primary purpose of the figure is to aid personnel in the comp...

Страница 180: ...e made for mounting to existing fuselage hardware The strength of the cargo tiedowns on the cargo platform is 2100 pounds 6 7 1 CARGO RESTRAINT CRITERIA The amount of restraint that must be used to keep the cargo from moving in any direction is called the restraint criteria and is usually expressed in units of force of gravity of G s Following are the units of the force of gravity of G s needed to...

Страница 181: ...TM 55 1520 228 10 Change 11 6 3 MS019072 FWD FWD 3000 Figure 6 2 Center of Gravity Limit Chart ...

Страница 182: ...TM 55 1520 228 10 6 4 Change 10 Figure 6 3 Cargo Space ...

Страница 183: ...TM 55 1520 228 10 Change 11 6 5 Figure 6 4 Fuel Loading Chart ...

Страница 184: ...TM 55 1520 228 10 6 6 Figure 6 5 Personnel Loading ...

Страница 185: ...plus equipment should be used If weighing facilities are not available or if the tactical situation dictates otherwise loads shall be com puted as follows a Combat equipped soldiers 240 lbs per individual b Combat equipped paratroopers 260 lbs per in dividual c Crew and passengers with no equipment com pute weight according to each individual s estimate 6 11 DELETED 6 12 DELETED 6 12 1 DELETED 6 1...

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Страница 189: ...GHT AND BALANCE RECORD The form is a continuous history of the basic weight and moment resulting from structural and equipment changes At all times the last entry is considered current weight and balance status of the basic helicopter 6 16 DD FORM 365 4 WEIGHT AND BALANCE CLEARANCE FORM F The form is a summary of actual disposition of the load in the helicopter It records the balance status of the...

Страница 190: ......

Страница 191: ...ns requiring maximum performance will be readily recognized c Familiarity with the data will allow performance to be computed more easily and quickly d Experience will be gained in accurately estimat ing the effects of variables for which data are not pre sented NOTE The information provided in this chapter is primarily intended for mission plan ning and is most useful when planning operations in ...

Страница 192: ... Inlet Installed 7 55 XI Hover 7 56 Figure 7 13 Hover Chart C Sheet 1 of 3 Hover Chart 7 57 Sheet 2 of 3 Hover Chart 7 58 Sheet 3 of 3 Hover Chart 7 59 XII Takeoff not applicable 7 60 Figure NO TAG Takeoff Chart DELETED XIII Cruise 7 62 Figure 7 15 Cruise Chart C Sheet 1 of 13 Pressure Altitude Sea Level to 2000 Ft FAT 30_C 7 63 Sheet 2 of 13 Pressure Altitude 4000 Ft to 6000 Ft FAT 30_C 7 64 Shee...

Страница 193: ...FAT 30_C 7 73 Sheet 12 of 13 Pressure Altitude Sea Level 6000 Ft FAT 45_C 7 74 Sheet 13 of 13 Pressure Altitude 8000 Ft to 14 000 Ft FAT 45_C 7 75 XIV Drag C 7 76 Figure 7 16 Drag Chart 7 77 XV Climb Descent 7 78 Figure 7 17 Climb Descent Chart C 7 79 Figure 7 18 Climb Performance C DELETED XVI Idle Fuel Flow 7 84 Figure 7 19 Idle Fuel Flow Chart C 7 85 ...

Страница 194: ... right angles to the third variable reflect left at right angles to the fourth variable reflect down etc until the final variable is read out at the final scale In addition to the primary use other uses of each chart are explained in the text accompanying each set of performance charts Colored registration blocks located at the bottom and top of each chart are used to determine if slippage has occ...

Страница 195: ...ce Knowledge will also be gained concerning the effects of variables for which data are not provided thereby increasing the accuracy of performance predic tions 7 10 DEFINITIONS OF ABBREVIATIONS a Unless otherwise indicated in the following list of abbreviations abbreviations and symbols used in this manual conform to those established in Military Stan dard MIL STD 12 which is periodically revised...

Страница 196: ...Out of ground effect SQ FT Square feet LB Pound TAS True airspeed LB HR Pounds per hour TOT Turbine outlet temperature LIM Limit TRQ Torque MAX Maximum USAASTA United States Army Aviation Systems Test Activity MIN Minute Systems Test Activity MIN Minimum VDC Volts direct current MM Millimeter V NE Velocity never exceed airspeed limitation N1 Gas producer speed airspeed limitation N2 Power turbine ...

Страница 197: ...M 55 1520 228 10 TEMPERATURE CONVERSION EXAMPLE WANTED FREE AIR TEMPERATURE IN DEGREES CELSIUS KNOWN FREE AIR TEMPERATURE 32qF Figure 7 1 Temperature Conversion Chart 7 7 TEMPERATURE CONVERSION OH 58A C ...

Страница 198: ...TM 55 1520 228 10 PAGES 7 8 THROUGH 7 46 INCLUDING PARAGRAPHS 7 12 THROUGH 7 36 AND FIGURES 7 2 THROUGH 7 10 HAVE BEEN DELETED 7 8 Change 10 ...

Страница 199: ...for maximum continuous power for the above mentioned conditions f Prolonged IGE hover may increase engine inlet temperature as much as 10ºC therefore a higher FAT must be used to correct for the increase under this condition 7 39 USE OF CHARTS The primary use of the charts is illustrated by the examples In general to determine the maximum power available it is necessary to know the pressure altitu...

Страница 200: ...TM 55 1520 228 10 Figure 7 11 Maximum Torque Available 30 Minute Operation Chart Sheet 1 of 4 7 48 ...

Страница 201: ...TM 55 1520 228 10 Figure 7 11 Maximum Torque Available 30 Minute Operation Chart Sheet 2 of 4 7 49 ...

Страница 202: ...TM 55 1520 228 10 Figure 7 11 Maximum Torque Available 30 Minute Operation Chart Sheet 3 of 4 7 50 ...

Страница 203: ...TM 55 1520 228 10 Figure 7 11 Maximum Torque Available 30 Minute Operation Chart Sheet 4 of 4 7 51 ...

Страница 204: ...TM 55 1520 228 10 Figure 7 12 Torque Available Continuous Operation Chart Sheet 1 of 4 7 52 ...

Страница 205: ...TM 55 1520 228 10 Figure 7 12 Torque Available Continuous Operation Chart Sheet 2 of 4 7 53 ...

Страница 206: ...TM 55 1520 228 10 Figure 7 12 Torque Available Continuous Operation Chart Sheet 3 of 4 7 54 ...

Страница 207: ...W INLET INSTALLED 100 RPM JP 4 CALIBRATED TORQUE Q DATA BASIS CALCULATED FROM MODEL SPEC 876 25 JULY 1975 CORRECTED FOR INSTALLATION LOSSES BASED ON FLIGHT TEST OF SIMILAR TYPE AIRCRAFT Figure 7 12 Torque Available Continuous Operation Chart Sheet 4 of 4 Change 10 7 55 TORQUE AVAILABLE OH 58A C T63 A 720 ...

Страница 208: ...rresponding to a 10 directional control margin To determine maximum right crosswind and hover height proceed as follows 1 Enter chart at appropriate pressure altitude 2 Move right to FAT 3 Move down to gross weight read the maximum right crosswind corresponding to a 10 directional control margin 4 Move left to intersection with maximum power available obtained from figure 7 11 5 Read the predicted...

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Страница 211: ...TM 55 1520 228 10 Change 10 7 59 Figure 7 13 Hover Chart Sheet 3 of 3 ...

Страница 212: ...TM 55 1520 228 10 7 60 Change 11 SECTION XII TAKEOFF NOT APPLICABLE 7 44 DELETED 7 45 DELETED 7 46 DELETED FIGURE 7 14 ON PAGE 7 61 HAS BEEN DELETED ...

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Страница 214: ...de creasing fuel weights reduced gross weight The following parameters contained in each chart are further explained as follows a Airspeed True and indicated airspeeds are pre sented at opposite sides of each chart On any chart indicated airspeed can be directly converted to true air speed or vice versa by reading directly across the chart without regard for other chart information Maxi mum permis...

Страница 215: ...TM 55 1520 228 10 Figure 7 15 Cruise Chart Sheet 1 of 13 7 63 ...

Страница 216: ...TM 55 1520 228 10 Figure 7 15 Cruise Chart Sheet 2 of 13 7 64 ...

Страница 217: ...TM 55 1520 228 10 Figure 7 15 Cruise Chart Sheet 3 of 13 7 65 ...

Страница 218: ...TM 55 1520 228 10 Figure 7 15 Cruise Chart Sheet 4 of 13 7 66 ...

Страница 219: ...TM 55 1520 228 10 Figure 7 15 Cruise Chart Sheet 5 of 13 7 67 ...

Страница 220: ...TM 55 1520 228 10 Figure 7 15 Cruise Chart Sheet 6 of 13 7 68 ...

Страница 221: ...TM 55 1520 228 10 Figure 7 15 Cruise Chart Sheet 7 of 13 7 69 ...

Страница 222: ...TM 55 1520 228 10 Figure 7 15 Cruise Chart Sheet 8 of 13 7 70 ...

Страница 223: ...TM 55 1520 228 10 Figure 7 15 Cruise Chart Sheet 9 of 13 7 71 ...

Страница 224: ...TM 55 1520 228 10 Figure 7 15 Cruise Chart Sheet 10 of 13 7 72 ...

Страница 225: ...TM 55 1520 228 10 Figure 7 15 Cruise Chart Sheet 11 of 13 7 73 ...

Страница 226: ...TM 55 1520 228 10 Figure 7 15 Cruise Chart Sheet 12 of 13 7 74 ...

Страница 227: ...TM 55 1520 228 10 Figure 7 15 Cruise Chart Sheet 13 of 13 7 75 ...

Страница 228: ...necessary to know the drag area change the true airspeed the pressure altitude and the free air temperature Enter at the known drag area change move right to TAS move down to pressure altitude move left to FAT then move down and read change in torque In addition by entering the chart in the opposite direction drag area change may be found from a known torque change This chart is used to adjust cru...

Страница 229: ...TM 55 1520 228 10 DRAG CALIBRATED TORQUE Q Figure 7 16 Drag Chart Change 10 7 77 DRAG OH 58A C T63 A 720 ...

Страница 230: ...weight and left to the corresponding rate of climb or descent may also be obtained 7 55 CONDITIONS The climb descent chart is based on the use of 100 rpm EXAMPLE WANTED SEE FIGURE 7 15 EXCESS TORQUE AVAILABLE FOR CLIMB AT MAXIMUM CONTINUOUS POWER KNOWN CLEAN CONFIGURATION GROSS WEIGHT 3200 LB PRESSURE ALTITUDE 14000 FEET FAT 30qC METHOD LOCATE CHART FIGURE 7 15 SHEET 3 FIND INTERSECTION OF 3200 LB...

Страница 231: ...TM 55 1520 228 10 7 79 Figure 7 17 Climb Descent Chart C ...

Страница 232: ...TM 55 1520 228 10 7 56 DELETED 7 57 DELETED 7 58 DELETED PAGES 7 82 FIGURE 7 18 SHEET 2 OF 2 AND 7 83 HAVE BEEN DELETED 7 80 Change 12 ...

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Страница 236: ...art is illustrated by the exam ple To determine the idle flow it is necessary to know the idle condition pressure altitude and free air temper ature Enter at the pressure altitude move right to FAT in appropriate grid then move down and read fuel flow on the scale corresponding to the condition Refer to the cruise charts to obtain fuel flow for cruise power condi tion 7 61 CONDITIONS This chart is...

Страница 237: ...TM 55 1520 228 10 Figure 7 19 Idle Fuel Flow Chart 7 85 7 86 blank ...

Страница 238: ......

Страница 239: ...w member performs his duties is the responsibility of the pilot in command a Crew Briefing A crew briefing shall be con ducted to ensure a thorough understanding of individual and team responsibilities The briefing should include but not be limited to copilot crew chief mission equip ment operator ground crew responsibilities and the coordination necessary to complete the mission in the most effic...

Страница 240: ...ocedures De scriptions of functions operations and effects of controls are covered in Section IV FLIGHT CHAR ACTERISTICS and are repeated in this section only when required for emphasis Checks that must be per formed under adverse environmental conditions such as desert and cold weather operations supplement normal procedures checks in this section and are cov ered in Section V ADVERSE ENVIRONMENT...

Страница 241: ...D PRESS and INST INVERTER caution lights should remain illuminated Do not fly if any of these lights fail to illuminate f BAT switch OFF g Pilot seat seat belt shoulder harness and armor side panels Check condition O h Crew Door Check condition 8 9 EXTERIOR CHECK 8 10 AREA 1 figure 8 1 FUSELAGE CABIN RIGHT SIDE 1 Cabin interior Check as follows O a Cargo loose equipment Check for proper loading an...

Страница 242: ...TM 55 1520 228 10 8 4 Change 10 Figure 8 1 Exterior Check Diagram ...

Страница 243: ...haft cover Check secure b Tail rotor drive Check shaft collars bear ings and hangers for condition slippage marks if cover not installed c Horizontal stabilizer Check condition d Vertical fin Check condition antenna con nections secure e Tail skid Check condition 2 Main rotor blade Check condition rotate 90 degrees to fuselage tiedown removed 8 12 AREA 3 figure 8 1 TAILBOOM LEFT SIDE 1 Tail rotor ...

Страница 244: ...uipment Check O b Cabin door Check condition c Landing gear Check condition cross tubes skid skid shoe s Wheels removed 4 Cockpit Check as follows a Copilot seat seat belts shoulder harness and armor side panels if installed Check condition Secure seat belts and shoulder harness if seat is not used b Cyclic Check secure or stow as required cannon plug connected c Collective Check secure or stow as...

Страница 245: ...an window c DIR GYRO MAG switch As required d FORCE TRIM switch FORCE TRIM e HYD BOOST switch HYD BOOST 7 Flight controls Check and set as follows a Control frictions OFF b Flight controls Check for full travel check engine out low rotor audio 8 Throttle Check Move to open then to idle stop press idle release and close 8 17 STARTING ENGINE 1 Fireguard Post if available 2 Rotor blades Check clear a...

Страница 246: ... OFF DC amps should decrease d HTR Check by moving the switch to HTR Check for increase in TOT then OFF TOT should de crease 4 Avionics Check as required 5 Deleted 6 Flight Instruments Check and set as follows a Attitude indicator Horizon A Set 5 de grees above horizon to indicate level attitude at cruise flight C b Altimeter Set and check 1 Barometric Altimeter Set to current al timeter setting a...

Страница 247: ...4 Avionics As required 8 20 HOVER CHECK Perform the following checks at a hover 1 Flight controls Check 2 Engine and Transmission instruments Check 3 Flight instruments Check as required 4 Power Check The power check is performed by comparing the torque required to hover with the predicted values from performance charts 8 21 TAKEOFF CAUTION During takeoff with the helicopter skids close to the gro...

Страница 248: ... ENG DEICE switch OFF f INV switch OFF 8 Battery change Check as follows a BAT switch OFF b Ammeter Check change indication If the change in indication is less than 5 0 am peres the battery is fully charged c BAT switch BAT 9 Throttle Close TOT stabilize below 400_ C 10 Overhead switches OFF as required a GEN b ANTI COLLISION LTS c POS LTS d CONSOLE LTS INST LTS and NVG POS LTS e BAT 11 Ignition s...

Страница 249: ...sloping ground If bumping oc curs during startup or shutdown move cyclic to mini mize or eliminate bumping If the flight envelope is inadvertently exceeded causing a low G condition and right roll move cyclic aft to return rotor to a positive thrust condition then roll level continuing flight if mast bumping has not occurred As collective pitch is reduced after engine failure or loss of tail rotor...

Страница 250: ... encounter ing the second mode is remote and is avoidable If oper ating limitations of the helicopter are observed 8 32 LOSS OF TAIL ROTOR EFFECTIVENESS a Loss of tail rotor effectiveness LTE is the occur rence of an uncommanded and rapid right yaw rate which does not subside of its own accord and which if not quickly reacted to can result in loss of aircraft con trol However the term loss of tail...

Страница 251: ...density altitude An in crease in either of these factors will decrease the power margin between the maximum available and power re quired to hover The pilot should conduct a low level low airspeed mission with only minimum essential per sonnel and equipment on board 2 Low indicated airspeed At airspeeds below ETL the tail rotor is required to produce nearly 100 per cent of the directional control ...

Страница 252: ...prior to the pre cipitation Since it is not practicable to completely cover an unsheltered helicopter those parts not protected by covers and those adjacent to cover overlap and joints require closer attention especially after blowing snow or freezing rain Remove accumulation of snow and ice prior to flight Failure to do so can result in hazardous flight due to aerodynamic and center of gravity di...

Страница 253: ...ow ambient temperatures of 12_C 10_F or below and high relative humid ity of 45 or greater If auto acceleration occurs close the throttle and shut down the engine Sub sequently restart the engine and re sume the warm up NOTE Due to the variation in types of jet fuel in cold weather the engine may experi ence a short delay before lightoff after the throttle is advanced to idle position This delay s...

Страница 254: ...original heading turning only when necessary 3 The altimeter is unreliable due to differential barometric pressures within the storm An indicated gain or loss of several hundred feet is not uncommon and should be allowed for in determining minimum safe altitude 8 39 LIGHTNING STRIKE a Although the possibility of a lightning strike is remote the helicopter could inadvertently be exposed to lightnin...

Страница 255: ...t be depended upon to re move ice from the main rotor system Vigorous control movements should not be made in an attempt to reduce low frequency vibrations caused by asymmetrical shed ding of ice from main rotor blades These movements may induce more asymmetrical shedding of ice further aggravating helicopter vibration levels WARNING Ice shed from rotor blades and or other rotating components pres...

Страница 256: ......

Страница 257: ...sary to establish an autoro tational descent and landing d The term EMER SHUTDOWN is defined as en gine shutdown without delay 1 Throttle Close 2 Fuel Shutoff Valve Handle OFF 3 BAT switch OFF Before turning the battery switch off during in flight emergencies requiring EMER SHUTDOWN the pilot should consider a MAYDAY call setting the transponder to EMER and the possible adverse effects of total el...

Страница 258: ...pared for a complete power loss In the event a partial power condition is accompanied by erratic engine operation or power surging and flight is to be continued the throttle may be adjusted in an attempt to correct the surging condition If flight is not possible close the throttle completely and complete an autorotational landing d Complete Power Loss Under a complete power loss condition delay in...

Страница 259: ...Figure 9 1 Emergency Exits and Equipment Sheet 1 of 2 Change 14 9 3 TM 55 1520 228 10 ...

Страница 260: ...Figure 9 1 Emergency Exits and Equipment Sheet 2 of 2 9 4 Change 14 TM 55 1520 228 10 ...

Страница 261: ...Figure 9 2 Autorotational Glide Characteristics Chart Change 14 9 5 TM 55 1520 228 10 ...

Страница 262: ...Figure 9 3 Minimum Height for Safe Landing After Engine Failure Chart 9 6 Change 14 TM 55 1520 228 10 ...

Страница 263: ... an increase in engine and rotor noise If an engine overspeed is experienced 1 Collective Increase to load the rotor and sustain engine rotor RPM below the maximum operating limit 2 Throttle Adjust until normal N 2 operating RPM is attained 3 LAND AS SOON AS POSSIBLE Perform a power on approach and landing by controlling the RPM manually with throttle e If RPM cannot be controlled manually 1 AUTOR...

Страница 264: ...nt upon the amount of pedal applied at the time of the malfunction Regardless of pedal setting at the time of malfunction a varying amount of tail rotor thrust will be delivered at all times during flight a Reduced power low torque 1 Indications The nose of the helicopter will turn right when power is applied 2 Procedure a If helicopter control can be maintained in powered flight the best solution...

Страница 265: ...urse of action Maintain full left pedal until the spin stops then adjust to maintain heading 9 23 MAIN DRIVESHAFT FAILURE A failure of the main driveshaft will be indicated by a sudden increase in engine RPM decrease in rotor RPM left yaw and activation of the low RPM audio and illumination of the ROTOR RPM warning light A transient overspeed of N1 and N2 may occur but will stabilize In the event ...

Страница 266: ...ETED 9 31 SMOKE AND FUME ELIMINATION Smoke and or toxic fumes entering the cockpit and cabin can be exhausted as follows Do not jettison doors in flight above effective translational lift 1 Vents Open 2 DEFOG VENT switch ON 9 32 ELECTRICAL SYSTEM MALFUNCTIONS 9 33 GENERATOR FAILURE NO OUTPUT A no output malfunction of the generator will be indicated by a zero indication on the DC AMMETER and a DC ...

Страница 267: ...and descend into the trees vertically Apply all the remaining collective prior to the main rotor blades entering the trees 9 39 DITCHING POWER ON If ditching be comes necessary with power available accomplish an approach to a hover above the water and 1 Doors Jettison at a hover 2 Crew except pilot and passengers Exit 3 Hover a safe distance away from personnel 4 AUTOROTATE Apply all remaining col...

Страница 268: ...SECTION II MISSION EQUIPMENT NOT APPLICABLE 9 12 Change 14 TM 55 1520 228 10 ...

Страница 269: ...ESS Refer to emergency procedures IFF Information system status SPARE LAND AS SOON AS POSSIBLE WARNING LIGHT CORRECTIVE ACTION ROTOR RPM Red Verify condition Adjust collective MASTER CAUTION Check for Caution Panel segment light illumination If none land as soon as possible ENGINE OUT Red Verify condition Autorotate XMSN OIL PRESS Red LAND AS SOON AS POSSIBLE XMSN OIL HOT Red LAND AS SOON AS POSSI...

Страница 270: ......

Страница 271: ... Engineering Change Proposal Short Form DD Form 1896 Jet Fuel Identaplate DOD L 85734 Lubricating Oil HelicopterTransmission System Synthetic Base MIL G 5572 Gasoline Aviation Grades 80 87 100 130 115 145 MIL H 5606 Hydraulic Fluid Petroleum Base Aircraft Missile and Or dance MIL H 83282 Hydraulic Fluid Fire Resistant Synthetic Hydrocarbon Base Metric NATO Code Number H 537 MIL I 27686 Inhibitor I...

Страница 272: ...DR TB MED 501 Noise and Conservation of Hearing TM 1 1500 250 23 General Tie Down and Mooring on all Series Army Model Helicopters TM 11 5841 284 23 P Altimeter Set Electronic AN APN 209 V 1 TM 11 5841 294 12 Radar Signal Detecting Set AN APR 39A V 1 TM 11 5841 294 30 2 Radar Signal Detecting Set AN APR 39 V 1 TM 38 250 Preparation of Hazardous Materials for Military Air Ship ment TM 55 1500 342 2...

Страница 273: ...Radio Set 3 71 F3 18 AN ARC 201 Control Panel Zeroize Switch F3 18 AN ARC 51BX Control Panel A DELETED AN ARC 51BX UHF AM Command Radio Set A DELETED AN ARN 89 ADF Control Panel F3 9 Antenna Locations F3 1 Appendix A References 1 4 Approved Fluids T2 4 Approved Fuels T2 2 Approved Fuels Oils and Fluids 2 74 T2 2 T2 3 T2 4 Approved Gas DELETED Approved Oils T2 3 Area 1 Fuselage Cabin Right Side 8 1...

Страница 274: ...ARC 201 Typical F2 12 1 Control Anti Torque Direction 2 28 Control Hydraulic System 2 33 Control Movements 5 23 Control System Engine Fuel 2 13 Controls and Functions Communications System Control 3 8 CONUS Navigation Receiver 3 49 F3 11 Course Deviation Indicator 3 53 F3 12 Direction Finder Set AN ARN 89 3 37 F3 9 Gyro Magnetic compass Set 3 41 Radar Altimeter with MWO 1 1520 228 50 52 3 67 3 F3 ...

Страница 275: ...LETED Takeoff DELETED Torque Available A DELETED Torque Available C 7 37 Transponder Set A 3 56 Transponder Set C 3 59 UHF AM Command Radio Set AN ARC 51BX A DELETED UHF AM Radio Set AN ARC 116 and AN ARC 164 3 19 UHF AM Radio Set RT 1167 ARC 164 V or RT 1167C ARC 164 V 3 23 F3 6 UHF AM Radio Set RT 1167 ARC 164 V or RT 1167C ARC 164 V 3 24 VHF AM Radio Set AN ARC 115 3 15 VHF FM Radio Set AN ARC ...

Страница 276: ... Restrictions at Low G s 5 25 Flight Restrictions for Practice Autorotation Landings 5 26 Flight Restrictions in Falling or Blowing Snow 5 30 Flight Restrictions with Float Landing Gear Installed A 5 21 Flight Under Instrument Meteorological Conditions IMC 5 29 Float Gear Equipped Helicopter A F2 7 FM Radio Set AN ARC 201 and Zeroize Switch Controls and Functions 3 73 F3 18 Firing Limitations A DE...

Страница 277: ...unctions 3 45 F3 10 Indicator Radio Bearing Heading Description 3 44 Indicator Radio Bearing Heading Operating Procedures 3 46 Indicator RPM Main Rotor 2 43 Indicator Turn and Slip 2 65 Indicator Vertical Speed 2 68 Indicators Miscellaneous Flight Instruments 2 72 Indicators Power Train System 2 41 Induction System 2 11 In Flight Wire Strike 9 43 Infrared Suppression System 2 14 Instrument Flight ...

Страница 278: ...mes 3 3 NVG Compatible Filters 2 60 NVG Position Lights 2 52 O Oil Data 6 9 Operating Characteristics 8 27 Operating Limits and Restrictions 5 1 5 2 Operation Sand and Dust 8 41 Operational Limits Exceeding 5 3 Operating Procedures AN ARC 164 3 22 F3 6 AN ARC 164 V 3 23 F3 6 Communications System Control 3 9 CONUS Navigation Receiver 3 50 Course Deviation Indicator 3 54 F3 12 Direction Finder Set ...

Страница 279: ...e Autorotation Landing Limits Crosswind Components F5 4 Preflight Check 8 7 Pressure Altimeter 2 63 Principal Dimensions F2 5 Pylon Support Structure 2 36 Pylon Suspension System 2 37 Pylon Whirl 8 30 Q R Radar Altimeter C F3 16 Radar Altimeter AN APN 209 2 70 Radar Altimeter with MWO 1 1520 228 50 52 3 67 1 F3 16 Radar Altimeter without MWO 1 1520 228 50 52 3 64 F3 16 Radar Warning System 2 71 Ra...

Страница 280: ...F3 13 Transponder Set AN APX 72 A 3 55 Transponder Set Control Panel C F3 14 Transponder Set Controls and Functions A 3 57 F3 13 Transponder Set Description A 3 56 Transponder Set Operating Procedures A 3 58 Transmission 2 35 Transmission and Gearbox Oil System Servicing 2 80 Transmission Oil Pressure Limits 5 7 Transmission Oil Temperature Limits 5 6 Trim Force Force Gradient 2 29 Turbulence 8 37...

Страница 281: ...io Set AN ARC 201 3 71 VHF FM Radio Set AN ARC 201 Zeroize Switch Controls and Functions 3 73 F3 18 VHF FM Radio Set AN ARC 201 Zeroize Switch Description 3 72 VHF FM Radio Set AN ARC 201 Zeroize Switch Operating Procedures 3 74 Voice Security Equipment TSEC KY 58 3 27 F3 8 Voice Security Equipment TSEC KY 58 Controls and Functions 3 27 F3 8 Voice Security Equipment TSEC KY 58 Description 3 27 Voi...

Страница 282: ......

Страница 283: ...Staff WILLIAM J MEEHAN II Brigadier General United States Army The Adjutant General DISTRIBUTION To be distributed in accordance with DA Form 12 31 10 and CL requirements for OH 58A and OH 58C Helicopter Observation U S GOVERNMENT PRINTING OFFICE 1994 300 421 82053 U S GOVERNMENT PRINTING OFFICE 1994 300 421 82053 ...

Страница 284: ......

Страница 285: ...28 redstone army mil Subject DA Form 2028 1 From Joe Smith 2 Unit home 3 Address 4300 Park 4 City Hometown 5 St MO 6 Zip 77777 7 Date Sent 19 OCT 93 8 Pub no 55 2840 229 23 9 Pub Title TM 10 Publication Date 04 JUL 85 11 Change Number 7 12 Submitter Rank MSG 13 Submitter FName Joe 14 Submitter MName T 15 Submitter LName Smith 16 Submitter Phone 123 123 1234 17 Problem 1 18 Page 2 19 Paragraph 3 20...

Страница 286: ......

Страница 287: ...TIONS EXCEPT RPSTL AND SC SM AND BLANK FORMS PUBLICATION FORM NUMBER TM 9 1005 433 24 DATE 16 Sep 2002 TITLE Organizational Direct Support And General Support Maintenance Manual for Machine Gun 50 Caliber M3P and M3P Machine Gun Electrical Test Set Used On Avenger Air Defense Weapon System ITEM NO PAGE NO PARA GRAPH LINE NO FIGURE NO TABLE NO RECOMMENDED CHANGES AND REASON 1 WP0005 PG 3 2 Test or ...

Страница 288: ...LISTS AND SUPPLY CATALOGS SUPPLY MANUALS PUBLICATION NUMBER DATE TITLE PAGE NO COLM NO LINE NO NATIONAL STOCK NUMBER REFERENCE NO FIGURE NO ITEM NO TOTAL NO OF MAJOR ITEMS SUPPORTED RECOMMENDED ACTION PART III REMARKS Any general remarks or recommendations or suggestions for improvement of publications and blank forms Additional blank sheets may be used if more space is needed TYPED NAME GRADE OR ...

Страница 289: ...ONS EXCEPT RPSTL AND SC SM AND BLANK FORMS PUBLICATION FORM NUMBER TM 55 1520 228 10 DATE 17 JAN 1989 TITLE Operator s Manual Army Model OH 58A C ITEM NO PAGE NO PARA GRAPH LINE NO FIGURE NO TABLE NO RECOMMENDED CHANGES AND REASON Reference to line numbers within the paragraph or subparagraph TYPED NAME GRADE OR TITLE TELEPHONE EXCHANGE AUTOVON PLUS EXTEN SION SIGNATURE DA FORM 2028 FEB 74 REPLACE...

Страница 290: ... NO LINE NO NATIONAL STOCK NUMBER REFERENCE NO FIGURE NO ITEM NO TOTAL NO OF MAJOR ITEMS SUPPORTED RECOMMENDED ACTION PART III REMARKS Any general remarks or recommendations or suggestions for improvement of publications and blank forms Additional blank sheets may be used if more space is needed TYPED NAME GRADE OR TITLE TELEPHONE EXCHANGE AUTOVON PLUS EXTENSION SIGNATURE USAPA V3 01 Commander U S...

Страница 291: ... cu centimeter 1000 cu millimeters 06 cu inch 1 cu decimeter 1000 cu centimeters 61 02 cu inches 1 cu meter 1000 cu decimeters 35 31 cu feet Approximate Conversion Factors To change To Multiply by To change To Multiply by inches centimeters 2 540 ounce inches Newton meters 007062 feet meters 305 centimeters inches 394 yards meters 914 meters feet 3 280 miles kilometers 1 609 meters yards 1 094 squ...

Страница 292: ...PIN 014142 000 ...

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