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HEADQUARTERS OH-58A Technical Manual

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TM 55-1520-228-10
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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Summary of Contents for HEADQUARTERS OH-58A

  • Page 1 TM 55-1520-228-10 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...
  • Page 3 TM 55-1520-228-10 WARNING An operating procedure, practice, etc., which, if not correctly followed, could result in personnel injury or loss of life. An operating procedure, practice, etc., which, if not strictly observed, could result in damage to or destruction of equipment. NOTE An operating procedure, condition, etc., which it is essential to highlight.
  • Page 4 TM 55-1520-228-10 CARBON MONOXIDE When smoke, suspected carbon monoxide fumes, or symptoms of anoxia exist, the crew should immediately ventilate cabin and shut off heater. HANDLING FUEL AND OILS Turbine fuels and lubricating oil contain additives which are poisonous and readily absorbed through the skin.
  • Page 7 TM 55-1520-228-10 C 14 CHANGE HEADQUARTERS No. 14 DEPARTMENT OF THE ARMY WASHINGTON, D.C., 31 March 2006 TECHNICAL MANUAL OPERATOR’S MANUAL ARMY MODEL OH-58/AC HELICOPTER DISTRIBUTION STATEMENT A: Approved for public release; distribution is unlimited. TM 55-1520-228-10, 17 January 1989, is changed as follows: 1.
  • Page 8 TM 55-1520-228-10 By Order of the Secretary of the Army: PETER J. SCHOOMAKER General, United States Army Official: Chief of Staff JOYCE E. MORROW Administrative Assistant to the Secretary of the Army 0528701 DISTRIBUTION: To be distributed in accordance with Initial Distribution Number (IDN) 310230 requirements for TM 55-1520-228-10.
  • Page 9 DEPARTMENT OF THE ARMY WASHINGTON, D.C., 30 August 2005 TECHNICAL MANUAL OPERATOR’S MANUALS ARMY MODEL OH-58A/C HELICOPTER DISTRIBUTION STATEMENT A: Approved for public release; distribution is unlimited. TM 55-1520-228-10, dated 17 January 1989, is changed as follows: 1. Remove and insert pages as indicated below. New or changed text material is indicated by a vertical bar in the margin.

  • Page 11: Through

    TM 55-1520-228-10 C 12 CHANGE HEADQUARTERS DEPARTMENT OF THE ARMY WASHINGTON, D.C., 10 June 2005 TECHNICAL MANUAL OPERATOR’S MANUAL ARMY MODEL OH-58/AC HELICOPTER DISTRIBUTION STATEMENT A: Approved for public release; distribution is unlimited. TM 55-1520-228-10, 17 January 1989, is changed as follows: 1.

  • Page 13: Through

    DEPARTMENT OF THE ARMY WASHINGTON, D.C. 1 April 2003 TECHNICAL MANUAL OPERATOR’S MANUAL ARMY MODEL OH-58A/C HELICOPTER DISTRIBUTION STATEMENT A: Approved for public release; distribution is unlimited. TM 55-1520-228-10, 17 January 1989, is changed as follows: 1. Remove and insert pages as indicated below. New or changed text material is indicated by a vertical bar in the margin.

  • Page 14: Through

    TM 55-1520-228-10 Remove pages Insert pages 7-81/(7-82 blank) – – – – – – (7-83 blank)/7-84 (7-83 blank)/7-84 8-1 through 8-12 8-1 through 8-12 8-15 through 8-17/(8-18 blank) 8-15 through 8-17/(8-18 blank) 9-1 and 9-2 9-1 and 9-2 9-7 and 9-8 9-7 and 9-8 9-11 through 9-14 9-11 through 9-14...
  • Page 15 NO. 10 WASHINGTON, D.C., 28 July 2000 TECHNICAL MANUAL OPERATOR'S MANUAL ARMY MODEL OH-58A/C HELICOPTER DISTRIBUTION STATEMENT A: Approved for public release; distribution is unlimited. TM 55-1520-228-10, 17 January 1989, is changed as follows: 1. Remove and insert pages as indicated below. New or changed text material is indicated by vertical bar in the margin.
  • Page 16 TM 55-1520-228-10 Remove Pages Insert Pages 5-1 and 5-2 5-1 and 5-2 5-3 and 5-4 (5-3 blank) /5-4 5-5 through 5-12 5-5 through 5-12 6-1 through 6-6 6-1 through 6-6 6-7 and 6-8 6-7/(6-8 blank) 6-9/(6-10 blank) 6-9/(6-10 blank) 7-1 through 7-4 7-1 through 7-4 7-7 through 7-14 7-7 and 7-8...
  • Page 17 DEPARTMENT OF THE ARMY WASHINGTON, D.C., 18 July 1997 NO. 9 Operator"s Manual ARMY MODEL OH-58A/C HELICOPTER Approved for public release; distribution is unlimited DISTRIBUTION STATEMENT A: TM 55-1520-228-10, 17 January 1989, is changed as follows: 1. Remove and insert pages as indicated below. New or changed text material is indicated by vertical bar in the margin.
  • Page 25 WASHINGTON, D.C., 22 July 1991 Operator’s Manual ARMY MODEL OH-58A/C HELICOPTER TM 55-1520-228-10, 17 January 1989, is changed as follows: Remove and insert pages as indicated below. New or changed text material is indicated by a vertical bar in the margin.
  • Page 27 General, United States Army Official: Chief of 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 Maintenance requirements for OH-58A and OH-58C Helicopter, Observation. URGENT...
  • Page 29 General, United Stages Army Official: Chief of 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 Maintenance requirements for OH-58A and OH-58C Helicopter, Observation. URGENT...
  • Page 31 General, United States Army Chief of Staff Official: 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 Maintenance requirements for OH-58A and OH-58C Helicopter, Observation. URGENT...
  • Page 33 General, United States Army Official: Chief of 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 Maintenance requirements for OH-58A and OH-58C Helicopter, Observation.
  • Page 35 TM 55-1520-228-10 LIST OF EFFECTIVE PAGES Insert latest changed pages. Dispose of superseded pages in accordance with regulations. NOTE: On a changed page, the portion of the text affected by the latest change is indicated by a vertical line, or other change symbol, in the outer margin of the page. Changes to illustrations are indicated by miniature pointing hands.
  • Page 36 TM 55-1520-228-10 LIST OF EFFECTIVE PAGES (CON’T) Page *Change Page *Change 3-7 ............10 6-8.2 blank ..........1 3-8 ............11 6-9 ............10 3-8.1 through 3-8.4 ........ 11 6-10 blank ..........0 3-9 and 3-10 ..........0 7-1 through 7-3 ........11 3-11 through 3-14 ........
  • Page 37 DEPARTMENT OF THE ARMY WASHINGTON, D.C., 17 JANUARY 1989 OPERATORS MANUAL ARMY MODEL OH-58A/C HELICOPTER REPORTING ERRORS AND RECOMMENDING IMPROVEMENTS You can improve this manual. If you find any mistakes or if you know of a way to improve these procedures, please let us know.

  • Page 38: Table Of Contents

    TM 55-1520-228-10 TABLE OF CONTENTS (Cont) Chapter/Section Page CHAPTER 4 MISSION EQUIPMENT Section I Mission Avionics (Not Applicable) ......... Armament (Not Applicable) .
  • Page 39 ......Configuration (OH-58A/C) ... .
  • Page 40 TM 55-1520-228-10 Figure Title Page Takeoff Chart ....DELETED Cruise Chart ....DELETED Drag Chart .
  • Page 41 1-3. DESCRIPTION – MANUAL. 1-9. FORMS AND RECORDS. This manual contains the complete operating instruc- tions and procedures for the Army OH-58A/C helicopter. The primary mission of this helicopter is that of observa- Army aviators flight record and helicopter maintenance...
  • Page 42 1-10. HELICOPTER DESIGNATION SYS- 1-11. DESIGNATOR SYMBOLS. TEM. NOTE The designation system prescribed by AR 70-50 is used All OH-58A and OH-58C model aircraft in helicopter designations as follows: are now equipped with the T63-A-720 Engine. Designator symbols OH-58A and...

  • Page 43: Through

    SECTION I. HELICOPTER 2-1. GENERAL. b. Turning Radius and Ground Clearance. (Refer to figure 2-6.) The OH-58A/C helicopter (figure 2-1 and figure 2-2 c. Weights. The helicopter weight empty and gross .) is a single engine, observation type helicopter de- operating weight will change according to the configu-...
  • Page 44 TM 55-1520-228-10 Anti-Collision Light Fuel Filler Cap Main Rotor Hub and Blades Aft Engine Cowling Engine Oil Tank Drain Access Door Position Light (Green) Tail Rotor Hub and Blade Horizontal Stabilizer Position Light (White) Vertical Fin Tail Skid Battery and Avionics Compartment Door Position Light (Red) Passenger Door (Left) Forward Transmission Fairing...
  • Page 45 TM 55-1520-228-10 Windshield Lower Cutter Assembly Tail Rotor Driveshaft Pilot Door Tail Rotor Gearbox Passenger Door (Right) Tail Rotor Driveshaft and Cover (if installed) FM Homing Antenna (Right Side) Engine Exhaust Battery Vent Engine Air Inlet External Power Receptacle Forward Transmission Fairing Inspection Door Ground Receptacle Upper Cutter Assembly FM Homing Antenna (Left Side)
  • Page 46 TM 55-1520-228-10 Position Light (Green) Vertical Fin Horizontal Stabilizer Lower Anti-Collision Light Aft Engine Cowling Aft Proximity Warning Antenna Infrared Suppression Shield ADF Sensor Antenna Aft Engine Cowling ADF Loop Antenna Upper Anti-Collision Light Landing Gear Forward Transmission Fairing Radar Warning Blade Antenna Pilot Tube Radar Altimeter Antenna Right Forward Radar Warning Antenna...
  • Page 47 TM 55-1520-228-10 Infrared Engine Exhaust Tail Rotor Driveshaft Cover FM No. 2 Antenna Tail Rotor Blade and Hub Windshield (Flat Glass) Tail Rotor Gearbox Right Static Port VOR Antenna Pilot Door Battery and Avionics Compartment Door Passenger Door Step Battery Vent FM Homing Antenna External Power Receptacle Passenger Door...
  • Page 48 TM 55-1520-228-10 (Figure 2-3 Sheet 1 of 2) (Figure 2-3 Sheet 2 of 2) 1. Copilot Door Emergency Jettison Handle 9. Pilot Cyclic Stick 2. Overhead Console 10. Pilot Seat 3. Fuel Shutoff Valve 11. Inertia Reel Control Handle 4. Free Air Temperature (FAT) Gage 12.
  • Page 49 TM 55-1520-228-10 Governor RPM Switch Radio Transmit Switch Not Used Search/Landing Lights Starter Switch Not Used Engine Idle Release Control Not Used Inertia Reel Not Used Inertia Reel Control Handle Force Trim Switch Not Used Throttle ICS Switch Controllable Landing Light Switch Figure 2-3.
  • Page 50 TM 55-1520-228-10 NOTE Round glass model shown Copilot Door Emergency Jettison Handle Anti-Torque Pedal Adjuster Overhead Console Inertia Reel Control Handle Fuel Shutoff Valve Pilot Collective Stick Free Air Temperature (FAT) Gage Collective Friction Control Adjustment Pilot Door Emergency Jettison Handle Console Instrument Panel Copilot Seat...
  • Page 51 TM 55-1520-228-10 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...
  • Page 52 TM 55-1520-228-10 29. Deleted 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...
  • Page 53 TM 55-1520-228-10 Figure 2-5. Principal Dimensions (Sheet 1 of 2) Change 13 2-11...
  • Page 54 TM 55-1520-228-10 HEIGHT STANDARD HIGH SKID FLOAT SKID GEAR GEAR GEAR 1. Forward Tip of Main Rotor (Static Position to Ground 9 ft. 6.0 in. 10 ft. 0.0 in. 9 ft. 7.9 in. with Droop) ........2.
  • Page 55 TM 55-1520-228-10 Figure 2-6. Turning Radius and Ground Clearance Float Gear. The float landing gear (figure 2-7) 2-4. COCKPIT AND CABIN DOORS. consists of two streamlined multi-cell inflatable floats, float support tubes, crosstubes, and necessary fittings WARNING required to equip the helicopter for water landings. A triangular plate is attached to the tail skid for added con- trollability and protection of the tail rotor in the event of a Inadvertent jettisoning of cockpit doors is pos-...
  • Page 56 TM 55-1520-228-10 Figure 2-7. Float Gear Equipped Helicopter 2-14...
  • Page 57 TM 55-1520-228-10 Figure 2-8. Locking Devices for Doors 2-15...
  • Page 58 TM 55-1520-228-10 power transmission wires. The basic system consists of 2-5. SEATS. an upper cutter assembly, a windshield deflector/cutter assembly, and a lower cutter assembly (figure 2-1 and a. Pilot and Copilot/Observer Seats. The pilot figure 2-2). The windshield deflector/cutter assembly, and copilot/ observer seats are constructed of tubing and consisting of a sawtooth equipped aluminum extrusion, stretched nylon material.
  • Page 59 TM 55-1520-228-10 Figure 2-9. WSPS Configuration 2-17...
  • Page 60 A spark igniter and fuel nozzle are mounted in the aft end of the outer combustion case. The OH-58A/C helicopter is equipped with a T63-A-720 c. Turbine. The turbine consists of a gas producer turbine engine (figure 2-11). The engine is designed for...
  • Page 61 TM 55-1520-228-10 FIGURE 2-10. HAS BEEN DELETED. Change 11 2-19...
  • Page 62 TM 55-1520-228-10 Figure 2-11. Engine 2-20 Change 11...
  • Page 63 TM 55-1520-228-10 2-10. ENGINE COMPARTMENT COOLING. scavenge system. The foreign material is ejected overboard by the vacuum-cleaner effect created by Openings are provided on both sides of the engine and engine bleed air as it is discharged through venturies in top cowling for compartment cooling.
  • Page 64 TM 55-1520-228-10 Figure 2-12. Overhead Console 2-22 Change 10...
  • Page 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)
  • Page 67 TM 55-1520-228-10 c. Droop Compensator. A droop compensator manually operated cutoff valve, maximum pressure maintains engine rpm (N2) as power demand is in- relief valve, and a torque tube seal and lever assembly. creased. The compensator is a direct mechanical A maximum pressure relief valve is incorporated to linkage between the collective stick and the speed protect the system from excessive fuel pressure.
  • Page 68 TM 55-1520-228-10 2-14. INFRARED SUPPRESSION SYS- unit. Probe type magnetic chip detectors are installed at the bottom of the power accessory gearbox and the TEM. engine oil outlet connection. All engine oil system lines and connections are internal with the exception of pres- The infrared suppression system is specially formulated sure and scavenge lines to the front compressor sup- to reduce detection of IR-seeking missiles.
  • Page 69 TM 55-1520-228-10 Figure 2-13. Instrument Panel and Console (Typical) 2-25...
  • Page 70 TM 55-1520-228-10 Figure 2-14. Instrument Panel and Console (Typical) 2-26 Change 11...
  • Page 71 TM 55-1520-228-10 Figure 2-14.1. Instrument Panel and Console with AN/ARC-201 (Typical) Change 10 2-26.1...
  • Page 72 TM 55-1520-228-10 NVG-Compatible bezel lights installed on the following instruments. Radar Altimeter Altimeter 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.
  • Page 73 Engine and the inner scale is marked light (figure 2-13 and figure 2-14), and to a tone genera- Rotor. The OH-58A indicators are direct reading instru- tor which produces a tone in the pilot headset. The warn- ing system is activated when N1 is below 55 $ 3% and ments which are not dependent on the electrical system.
  • Page 74 The switch in AUTO SECTION IV. FUEL SYSTEM 2-22. FUEL SUPPLY SYSTEM. The OH-58A/C helicopters have been equipped with an airframe mounted fuel filter. The fuel filter is a cylindrical unit mounted on the engine deck on the left side of the engine compartment.
  • Page 75 TM 55-1520-228-10 Figure 2-15. Auxiliary Fuel System 2-29...
  • Page 76 TM 55-1520-228-10 2-24. CONTROLS AND INDICATORS. remaining and actual time aircraft engine may operate. Differences in fuel consumption rates, a. Fuel Quantity Indicator. The FUEL QTY indi- aircraft altitude and operational condition of the cator (figure 2-13 and 2-14) is located in the instrument fuel subsystem will also affect actual time air- panel and displays the quantity of fuel in the fuel cell in craft engine may operate.
  • Page 77 TM 55-1520-228-10 NOTE copilot collective lever, located on the left of the copilot position, contains only a twist type throttle at the forward Removal of copilot cyclic stick can end of the control. cause pilot cyclic stick to creep slightly aft. a.
  • Page 78 TM 55-1520-228-10 2-30. HORIZONTAL STABILIZER. 2-31. VERTICAL FIN. The horizontal stabilizer (figure 2-1 and figure 2-2) is The vertical fin is located to the right of the tail rotor and located near the center of the tail boom an is installed in is installed in a predetermined fixed position.
  • Page 79 During autorotation the freewheeling unit provides en- 2-36. PYLON SUPPORT STRUCTURE. gine disconnect and transmission drives the tail rotor. a. The OH-58A/C has a design feature called a 2-39. TAIL ROTOR GEARBOX. focused pylon mounting system for its pylon. This sup-...
  • Page 80 TM 55-1520-228-10 b. Tail Rotor Gearbox Chip Detector. The chip 2 psi on decreasing pressure. The transmission oil pres- detector is located in the lower section of the tail rotor sure switch is located on the left side of the cabin roof gearbox.
  • Page 81 TM 55-1520-228-10 SECTION IX. UTILITY SYSTEM 2-46. PITOT HEATING SYSTEM. cuit breaker switch on the overhead console. The pitot heater is controlled by a switch located on the overhead a. Description. The pitot heater is installed on console (figure 2-12) labeled PITOT HTR. the pitot head and functions to prevent ice forming in the pitot tube.
  • Page 82 TM 55-1520-228-10 Vent and Defog Control Remote Sensor Ventilation and Defogging Blower (Instrument Panel) Fresh Air Inlet Ram Air Intake Grill Heater Control Knob Post Plenum Air Distribution Vents Heat Control Cable Air Distribution Valves Cargo / Passenger Area Bleed Air Tube Windshield Defog Nozzle Pilot Seat Back (REF) Mixing Valve...
  • Page 83 TM 55-1520-228-10 Combustion Heater Plenum Fresh Air Inlet Fuel Shutoff Valve Igniter Plug Fuel Pump Duct Fuel Pressure Relief Valve Firewall Shutoff Control Heat Control Knob Fuel Filter Heater Pilot Seat Back Combustion Blower Copilot Seat Back Figure 2-16. Heating and Ventilation (Sheet 2 of 2) Change 14 2-37...
  • Page 84 TM 55-1520-228-10 Figure 2-17. Heater Control and Vent Pull Knobs 2-38 Change 12...
  • Page 85 TM 55-1520-228-10 2-48. COMBUSTION HEATER. (5) BAT switch - BAT. a. Description. A combustion heater is installed on (6) FUEL VALVE - ON the electrical shelf behind the passenger seat, on helicopter serial Nos. 70-15263 thru 70-15278, in the aft (7) HEAT-OFF-VENT switch - OFF.
  • Page 86 This switch is labeled GEN in the forward position, OFF in the center position, and RESET in the The OH-58A/C helicopter is equipped with a 28-volt aft position. The RESET position is spring-loaded to direct current dual bus (essential and non-essential) return to the OFF position when released.
  • Page 87 TM 55-1520-228-10 NAV POSITION LIGHTS (NVG POS LTS) SRCH/LANDING LT CONTROL (SRCH LT CONT) AMMETER(AMM) FUEL QUANTITY INDICATOR (FUEL QTY) DUAL TACHOMETER (DUAL TACH) GAS PRODUCER TACHOMETER (GAS PROD TACH) TURBINE OUTLET TEMPERATURE INDICATOR (TURB OUTLET TEMP) ENGINE OIL TEMPERATURE INDICATOR (ENG OIL TEMP) PRIMARY DIRECTIONAL CONTROL (PRI DRI CONTR)
  • Page 88 SUPPLY. toggle switch labeled INV and OFF. AC electrical power is provided to the electrical system when the switch is in The OH-58A/C helicopter is equipped with a solid state the forward position. DC power to the inverter is inverter powered from the non-essential 28 volt DC bus supplied by the non-essential bus;...
  • Page 89 TM 55-1520-228-10 SECTION XII. LIGHTING 2-51. POSITION LIGHTS. Float equipped helicopters have lower light relocated from boom station 88.0 to boom station 103.0. The position lights consist of three lights (figure 2-1 and figure 2-2). A green light is located on the right horizon- 2-54.
  • Page 90 TM 55-1520-228-10 2-55. DELETED. (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- 2-56. INSTRUMENT LIGHTS. tached to the instrument panel for the other warning lights, and master caution lights for use in the same The instrument lights are all on one circuit and are con- manner.
  • Page 91 TM 55-1520-228-10 2-60. N VG-COMPATIBLE FILTE RS. u tility lig h t is a tta ch e d to a fle xib le g oo se n ec k ex te ns ion mounted on the centerpost between the pilot and copi- WARNING lot seats (figure 2-4).
  • Page 92 TM 55-1520-228-10 Figure 2-18.1. AAU-32/A Altitude Encode/ Pneumatic Altimeter 2-46 Change 4...
  • Page 93 TM 55-1520-228-10 side the altimeter whenever the aircraft power is on. The when passing from 9 through 0 (climbing) or from 0 vibrator is powered through the ALT AAV31/32A[A] or through 9 (descending). This hang-up will cause lag, the ALT VIB[C] circuit breaker. The encoder is DC powered magnitude of which will depend on the vertical velocity with the vibrator through the ALT AAU31/32A circuit of the aircraft and the friction in the altimeter.
  • Page 94 TM 55-1520-228-10 or in straight and level flight. The warning flag, atti- per minute. the indicator is actuated by the rate of atmo- tude (ATT) and rate of turn pointer provide indication of spheric pressure change. system malfunctions. When the gyro is being caged or when 28 Vdc power is interrupted, the ATT flag will be 2-69.
  • Page 95 TM 55-1520-228-10 Figure 2-19. Warning and Caution Panels Change 11 2-47...
  • Page 96 TM 55-1520-228-10 switch (figure 2-19) controls the brightness of the cau- remains illuminated until the fault condition is corrected. tion panel lights and the MASTER CAUTION light. The INST LTS switch must be moved from the DIM position ENGINE OUT Engine N1 speed below before the caution panel lights can be dimmed.
  • Page 97 TM 55-1520-228-10 Tail Rotor Gearbox Deleted Engine Oil Tank Deleted Tail Rotor Gearbox Filler Cap Grip Reservoirs Engine Oil Filler Cap Transmission Hydraulic Filler Cap Hydraulic Reservoir Fuel Tank Filler External Power Receptacle Auxiliary Fuel Cell Fuel Cell Sump Drain Valve Static Ground Receptacle Relief Valve Pillow Block Reservoirs...
  • Page 98 TM 55-1520-228-10 Figure 2-20. Servicing Diagram (Sheet 2of 2) 2-50 Change 11...
  • Page 99 TM 55-1520-228-10 10. Engine Oil Tank Sight Glass 1. Pillow Block Reservoir Grease Fittings 10.1. Deleted 2. Grip Reservoir 11. Hydraulic Filler Cap 3. Auxiliary Fuel Filler Cap 12. Hydraulic Sight Glass 4. Closed Circuit Refueling Receiver 13. Static Ground Receptacle 5.
  • Page 100 *Lubrication oil made to MIL-L-7808 by Shell Oil Company un- der their part number 307, qualification number 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 *MIL-L-7808 NATO Code is 0-148 11.2 U.S.
  • Page 101 CAUTION *Lubrication oil made to MIL-L-7808 by Shell Oil Company under their part number 307, qualification number 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. Tail Rotor...
  • Page 102 TM 55-1520-228-10 Table 2-2. Approved Fuels SOURCE US MILITARY JP-4 (MIL-T-5624) JP-5 (MIL-T-5624) OR JP-8 (MIL-T-83133) NATO CODE NO. F40 (WIDE CUT TYPE) F-44 OR F-34 (HIGH FLASH TYPE) COMMERCIAL FUEL JET B JET A JET A-1 ASTM-D-1655 NATO F-34 American Oil Co.
  • Page 103 TM 55-1520-228-10 Table 2-3. Approved Oils APPROVED COMMERCIAL MIL-L-7808 TYPE OILS MANUFACTURER’S NAME MANUFACTURER’S DESIGNATION American Oil and Supply Co. PQ Turbine Oil 8365 Humble Oil and Refining Co. ESSO/ENCO Turbo Oil 2389 Mobil Oil Corp. RM-184A/RM-201A Do not use Shell Oil Co., Part No 307, Qualification No. 7D-1 oil (MIL-L-7808). It can be harmful to seals made of silicone.
  • Page 104 TM 55-1520-228-10 Table 2-4. Approved Fluids APPROVED COMMERCIAL MIL-H-5606 TYPE FLUIDS MANUFACTURER'S NAME MANUFACTURER'S DESIGNATION American Oil and Supply Co "PO" 4226 Bray Oil Co Brayco 757B Brayco 756C Brayco 756D Castrol Oils, Inc. Hyspin A Humble Oil and Refining Co. Univis J41 Mobile Oil Corp Aero HFB...
  • Page 105 TM 55-1520-228-10 Table 2-4. Approved Fluids — Continued APPROVED COMMERCIAL MIL-H-83282 TYPE FLUIDS (cont) MANUFACTURER’S NAME MANUFACTURER’S DESIGNATION Gulf Oil Chemicals Co. TS 741 Penreco Petrofluid 822 Shell International Petroleum Co. Aeroshell Fluid 31 American Oil and Supply Co. PQ3883 PQ4219 PQ4268 PQ4362C...
  • Page 106 TM 55-1520-228-10 2-77. FUEL SYSTEM SERVICING. (POWER OFF) a. Precaution. In the event of major spillage of fuel, all powered equipment will be shut down. All personnel will NOTE leave the vicinity and be positioned to prevent any sources of possible ignition from entering Servicing personnel shall comply with all safety area.
  • Page 107 TM 55-1520-228-10 Figure 2-22. Gravity Refueling With Closed Circuit Receiver 2-59...
  • Page 108 TM 55-1520-228-10 Ensure that gravity refueling port is d. Gravity Refueling. closed. If not, rotate inner sleeve counterclockwise until gravity refueling port is closed and flange of sleeve is in Ground the helicopter at the receptacle lo- contact with rivet at base or receiving cylinder. Refer to cated adjacent to the filler cap on the helicopter to the figure 2-23.
  • Page 109 TM 55-1520-228-10 Figure 2-23. Refueling Receptacle Change 11 2-61...
  • Page 110 TM 55-1520-228-10 (2) Servicing unit shall be grounded (servicing CAUTION unit to ground and servicing unit to helicopter). The heli- copter should be grounded to the same ground point as is the servicing unit. Ensure that servicing unit pressure is not above 125 PSI while refueling. (3) After completion of servicing, remove nozzle, reinstall cap, and disconnect all grounds from helicopter.
  • Page 111 TM 55-1520-228-10 (2) Gravity Refueling. 2-79. ENGINE OIL SYSTEM SERVICING. Ground helicopter at receptacle located adjacent to filler cap on helicopter to filler-nozzle and remove filler cap. Rotate inner sleeve clockwise until An engine high oil level coupled with a transmis- sleeve clears port in bottom of fuel receiver.
  • Page 112 Install main rotor blade tie-down (figure 2-24). aircraft’s honeycomb surface. Retain all installation hardware together for c. Install engine air inlet shield assemblies in en- each separate OH-58A/C helicopters; gine inlets and covers on engine exhausts. due to wear, the bushings may not be interchangeable.
  • Page 113 TM 55-1520-228-10 (1) Route strap from pitot tube through lower 2-86.1 ROTOR BLADE TIE-DOWN. 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 CAUTION shields strap at both ends.
  • Page 114 TM 55-1520-228-10 Pitot Tube Cover Tail Rotor Tiedown Forward Jacking and Tiedown Fitting Engine Air Inlet Shield Exhaust Covers Ground Handling Gear Aft Jacking and Tiedown Fitting Towing Ring Main Rotor Blade Tiedown Figure 2-24. Ground Handling Equipment, Covers, Rotor Tiedowns, and Mooring Diagram 2-66 Change 11...
  • Page 115 TM 55-1520-228-10 Figure 2-25. Paved Surface Mooring Configuration (OH-58A/C) Change 11 2-67/(2-68 blank)
  • Page 117 Avionics equipment installed in the helicopter, with com- avionics equipment installed in the Army Model mon names, use, and operational range, is presented in OH-58A/C helicopter. Included information consists of Table 3-1. Antenna locations are shown in figure 3-1. description, technical characteristics, capability, loca- tion of each major component and operation instruc- 3-4.
  • Page 118 TM 55-1520-228-10 Table 3-1. Communications and Associated Electronics Equipment (Cont) NOMENCLATURE COMMON NAME RANGE Communication Secure-Voice In conjunction with FM Security Set encoder-decoder radio set to provide secure TSEC/KY-58 two-way voice commu- nication Gyromagnetic Gyromagnetic Navigational Aid Compass Set Compass provides accurate AN/ASN-43 heading information...
  • Page 119 TM 55-1520-228-10 Table 3-1. Communications and Associated Electronics Equipment (Cont) NOMENCLATURE COMMON NAME RANGE Indicator, RHBI Provides magnetic Heading-Radio heading, VOR or Bearing ADF bearing, and ID-1351C/A homing information. Indicator, Provides VOR Course course deviation, Deviation localizer and ID-1347C/ARN glideslope signal information.
  • Page 120 TM 55-1520-228-10 Antenna, Radar Warning – Fwd Right Side Antenna, Radar Warning – Fwd Left Side Deleted Deleted Antenna, FM Antenna, ADF Sense Antenna, ADF Loop Antenna, Glideslope Antenna, Top Transponder Antenna, Radar Warning – Blade Antenna, VOR – Right Side Antenna, Radar Altimeter Antenna, VHF/FM Antenna, Radar Altimeter...
  • Page 121 TM 55-1520-228-10 SECTION I. COMMUNICATIONS 3-6. COMMUNICATIONS SYSTEM CON- VHF/FM COMM and are installed in the center console. Antenna location is located as shown in figure 3-1. TROL, C-6533/ARC. 3-12. CONTROLS AND FUNCTIONS – VHF/ 3-7. DESCRIPTION – COMMUNICATIONS FM RADIO SET. SYSTEM CONTROL.
  • Page 122 TM 55-1520-228-10 CONTROL/INDICATOR FUNCTION Receiver Switches ......Connect (ON) or disconnect (OFF) communications receiv- ers from the headsets.
  • Page 123 TM 55-1520-228-10 CONTROL/INDICATOR FUNCTION 1. Function Selector Power off. Receiver-On; Transmitter-Standby. T/R GUARD Receiver-On; Transmitter-Standby; Guard Receiver-On. NOTE: Reception on guard frequency is unaffected by frequencies selected for nor- mal communications. HOMING Activates the homing mode and display on the radio bearing heading indicator. May be used also for normal voice communications.
  • Page 124 TM 55-1520-228-10 (3) Function selectors - RETRAN (Both FM within the frequency range of 225.00 to 399.95 MHz on sets). 3500 channels for a distance of approximately 50 miles as limited by conditions. A guard receiver is incorpo- (4) Receiver switches - Number 1 and number rated in the set and is fixed tuned to 243.00 MHz.
  • Page 125 TM 55-1520-228-10 a. Transmit/Receive. The radio set primarily is used for voice communication. An additional radio set capability, although not functional (1) Function selector - As desired. is ADF. Power to operate the ARC-164(V) radio is from the 28 vdc emergency bus through a circuit breaker (2) Frequency - Select.
  • Page 126 TM 55-1520-228-10 3-26. OPERATING PROCEDURE – UHF/AM PRESET A frequency is selected RADIO (RT-1167/ARC-164(V) using the preset channel RT-1167C/ARC-164(V)). selector switch for select- ing any one of 20 preset a. Modes of Operation. Depending on the settings channels as indicated on of the operating controls, the radio set can be used for the CHAN indicator.
  • Page 127 TM 55-1520-228-10 (4) 1020 Hz TONE Signal Transmission (MAIN) used. In order to defeat this communications system, mode. the jammer must find the frequency being used, jam it and then predict or find the next frequency. The HAVE (a) Set OFF-MAIN-BOTH-ADF selector QUICK modification adds the frequency hopping capa- switch to MAIN.
  • Page 128 TM 55-1520-228-10 mode, a complete TOD message is transmitted, while in return to a normal channel in either the manual or preset the AJ mode, only an abbreviated time update is trans- mode. To receive a time update in AJ mode, rotate the mitted.
  • Page 129 TM 55-1520-228-10 CONTROL/INDICATOR FUNCTION Function Selector OFF .............. Power off. T/R..............Receiver - On; Transmitter - Standby. T/R GUARD..........Receiver - On; Transmitter - Standby; Guard Receiver - On. NOTE: Reception on guard frequency is unaffected by frequencies selected for normal communications. D/F..............
  • Page 130 TM 55-1520-228-10 CONTROL/INDICATOR FUNCTION Function Selector OFF ................Power off. TIR ................Receiver - On; Transmitter - Standby. T/R GUARD..............Receiver - On; Transmitter - Standby; Guard Receiver - On. NOTE: Reception on guard frequency is unaffected by frequencies selected for normal communications. D/F ................
  • Page 131 TM 55-1520-228-10 DETAIL B DETAIL C (FREQUENCY (HAVE QUICK II SELECTOR 1 ONLY) ON HAVE QUICK) CONTROL/INDICATOR FUNCTION Frequency Selectors Hundreds ......Selects first digit of desired frequency.
  • Page 132 TM 55-1520-228-10 c. Radio Set ARC-164(V) Operation. g. Manual frequency display – Set WOD 16. h. Preset channel select – Set to 16. (1) TOD Transfer. i. Preset button – Press. a. Transfer paragraph 3-26.NO TAG.(5). j. Repeat steps g thru i to store WOD 17, 18, b.
  • Page 133 TM 55-1520-228-10 FIGURE 3-7. HAS BEEN DELETED. Change 11 3-13...
  • Page 134 TM 55-1520-228-10 3-27. VOICE SECURITY EQUIPMENT f. At this time a crypto alarm, and background noise, in the aircraft audio intercom system should be (TSEC/KY-58). heard. To clear this alarm, press and release PTT in the aircraft audio/intercom system. Secure voice commu- a.
  • Page 135 TM 55-1520-228-10 CONTROL/INDICATOR FUNCTION ZEROIZE switch ............Zeroizes the KY-58; clears any encoding in the system. (two-position momentary toggle under spring loaded cover). DELAY switch.............. Used when signal is to be retransmitted. two-position toggle PLAIN-C/RAD In the PLAIN position, permits normal (unciphered) communications Switch rotary on the associated FM radio set.
  • Page 136 TM 55-1520-228-10 3-32. AUTOMATIC REMOTE KEYING Upon instructions from the Net Controller: PROCEDURE. Listen for a beep on your headset. NOTE Wait two seconds. Automatic Remote Keying (AK) causes an “old” crypto-net variable (CNV) to be replaced by a Set the RCU MODE switch to OP. “new”...
  • Page 137 TM 55-1520-228-10 d. Continuous tone could also indicate a cryptoa- (3) When you begin to receive a ciphered mes- larm. If this tone occurs at any time other than as indi- sage, this tone indicates that the cryptovariable has cated in paragraph 3-34.c above, equipment failure passed the “parity”...
  • Page 138 TM 55-1520-228-10 CONTROL/INDICATOR FUNCTION AUDIO ........Adjusts receiver volume.
  • Page 139 TM 55-1520-228-10 c. Preliminary. 3-40. DESCRIPTION – GYRO MAGNETIC COMPASS SET. (1) Interphone control panel receiving NAV The gyro magnetic compass set provides accurate switch – ON. heading information, referenced to a free directional gyro heading when operated in the DIR gyro mode (free gyro), or slaved to the earth’s magnetic field when oper- (2) RMI BRG PTR switch –...
  • Page 140 TM 55-1520-228-10 CONTROL/INDICATOR FUNCTION Power Warning Indicator ....Indicates when AC power is not being supplied to the gyro- magnetic compass or when the AN/ASN-43 AC power sup- ply is inoperative.
  • Page 141 TM 55-1520-228-10 3-45. CONTROLS FUNCTIONS RADIO (2) An FM signal strength indicator shows red whenever the FM radio receiver signal is absent or is too BEARING HEADING INDICATOR. weak for a reliable indication. When the signal strength is acceptable, the FM signal strength indicator shows Refer to figure 3-10.
  • Page 142 TM 55-1520-228-10 CONTROL/INDICATOR FUNCTION NAV VOL Power Switch and Volume Control NAV VOL............Turns set on and controls VOR/LOC receiver volume. OFF .............. Turns set OFF. MB VOL Power Switch and Volume Control MB VOL............Turns set on and controls marker beacon volume. OFF ..............
  • Page 143 TM 55-1520-228-10 CONTROL/INDICATOR FUNCTION Course Pointer ......Indicates deviation from selected VOR radial or LOC path. Course Index .
  • Page 144 TM 55-1520-228-10 3-49. CONTROLS AND FUNCTIONS – (6) RMI BRG PTA switch (located on instrument panel) – VOR. CONUS NAVIGATION RECEIVER. (7) Interphone control panel AUX switch – ON. Refer to figure 3-11. (8) Interphone control panel VOL control – Ad- just.
  • Page 145 TM 55-1520-228-10 SECTION III. TRANSPONDER AND RADAR the IFF CODE HOLD-OFF switch to the HOLD position. 3-55. TRANSPONDER SET – AN/ On the Transponder Set Control Panel – turn CODE APX-72. switch to HOLD (only momentary action is required). The transponder set is mounted on the upper left side of the instrument panel.
  • Page 147 TM 55-1520-228-10 CONTROL/INDICATOR FUNCTION 1. MASTER Control OFF ................. Turns set OFF. STBY ............... Places in warm-up (standby) condition. LOW ................ Set operates at reduced receiver sensitivity. NORM ..............Set operates at normal receiver sensitivity. EMER ..............Transmits emergency replay signals to MODE 1, 2. or 3/A interrogations regardless of mode control settings.
  • Page 148 TM 55-1520-228-10 CONTROL/INDICATOR FUNCTION 6. MODE 4 Switch ON..............Enables the set to reply to MODE 4 interrogations. OUT..............Disables the reply to MODE 4 interrogations. 7. AUDIO-LIGHT Switch AUDIO ..............Enables aural and REPLY light monitoring of valid MODE 4 interrogations and replies. LIGHT ...............
  • Page 149 TM 55-1520-228-10 (2) Mode and code – Select as required. (f) IDENT – As required. (3) Test as required. (2) Emergency Operation. MASTER control – EMER. (4) MASTER control – LOW, NORM, EMER as required. (3) Stopping Procedure. MASTER control – (5) IDENT –...
  • Page 150 TM 55-1520-228-10 CONTROL/INDICATOR FUNCTION TEST GO ........Indicates successful built in test (BIT).
  • Page 151 TM 55-1520-228-10 CONTROL/INDICATOR FUNCTION 6. STATUS Indicators. ANT ................. Indicates that built in test (BIT) or monitor (MON) failure is due to high voltage standing wave ratio (VSWR) in antenna. KIT ................Indicates that built in test (BIT) or monitor (MON) failure is due to external computer.
  • Page 152 TM 55-1520-228-10 FIGURE 3-15 HAS BEEN DELETED. 3-30 Change 10...
  • Page 153 TM 55-1520-228-10 CONTROL/INDICATOR FUNCTION LO SET Control Knob ......Turns facility on and off, and sets low altitude limit index. LO Level Warning Flag .
  • Page 154 TM 55-1520-228-10 3-64. RADAR ALTIMETER a. Altimeter Operation. (without MWO 1-1520-228-50-52 (1) LO SET control knob – Rotate clockwise from OFF. Set low limit index as desired. NOTE (2) HI SET control knob – Set high limit index as Simultaneous operation of the AN/ desired.
  • Page 155 TM 55-1520-228-10 . OPERATING PROCEDURES – the pointer again. The “ALTITUDE LOW - TOO LOW” 3-67.4 audio warning should be again heard at its initial “FULL” RADAR ALTIMETER. volume level. (5) Lower knob – Adjust counterclockwise until NOTE the LO bug is “below” the pointer, (but not quite to the Refer to TM 11-5841-284-23&P for OFF position).
  • Page 156 TM 55-1520-228-10 occurs the processor generates the appropriate threat test should be initiated after approximately one minute. symbology and synthetic audio. It is important therefore Self test can be performed in MODE ONE or MODE that the correct theaterized EID and UDM are installed TWO.
  • Page 157 TM 55-1520-228-10 3-32.3...
  • Page 158 TM 55-1520-228-10 ZPCONTROL PANEL (AN/APR-39A(V)1) CONTROL/INDICATOR FUNCTION PWR Switch ....... . Two-position locking toggle switch.
  • Page 159 TM 55-1520-228-10 CAUTION Excessive indicator display brightness may damage CRT. NOTE Plus (+) symbol will be centered on indicator dis- play during operation and self-test. MISSILE ALERT INDICATOR / DISPLAY (AN/APR-39A(V)1) CONTROL/INDICATOR FUNCTION MA Lamps ........Missile Alert (MA) lamps are not used in AN/APR-39A(V)1.
  • Page 160 TM 55-1520-228-10 SECTION IV. AN/ARC-201 SINCGARS RADIO SET 3-71. VHF/FM RADIO SET AN/ARC-201. (a) FREQ key – Press. (b) CLR key – Press. 3-72. DESCRIPTION – VHF/FM RADIO (c) Key in desired frequency. SET. (d) STO/ENT key – Press. The AN/ARC-201 VHF FM facility, consisting of a 2300 (6) VOL –...
  • Page 161 TM 55-1520-228-10 (13) CLR key – Press. that channel is locked in. The RT display will show the channel number, and you can listen and talk on that (a) Enter day. channel. When the channel has been inactive for 2.5 seconds, scanning will begin again.
  • Page 162 TM 55-1520-228-10 CONTROL/INDICATOR FUNCTION FUNCTION Selector OFF ........Power off.
  • Page 163 TM 55-1520-228-10 CONTROL INDICATOR FUNCTION 2. MODE Selector HOM ................ Activates homing mode and display on radio bearing heading indicator. Voice communications can be conducted in this mode. SC ................Activates Single Channel mode of operation. FH ................Activates Frequency Hopping mode of operation. FH-M.................
  • Page 165 TM 55-1520-228-10 CHAPTER 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)

  • Page 167: Chapter 5 Operating Limits And Restrictions

    NOTE consist of strips of semi-transparent color tape which adhere to the glass outside of an indicator dial. All round For OH-58A aircraft, reference figure 5-2 instruments that have range markings on glass face for power turbine tachometer, gas producer...
  • Page 168 TM 55-1520-228-10 Figure 5-1. Instrument Markings 5-2 Change 11...
  • Page 170 TM 55-1520-228-10 Figure 5-2. Instrument Markings (Sheet 1 of 3) (5-3 blank)/5-4 Change 14...
  • Page 171 TM 55-1520-228-10 Figure 5-2. Instrument Markings (Sheet 2 of 3) Change 11...
  • Page 172 TM 55-1520-228-10 Figure 5-2. Instrument Markings (Sheet 3 of 3) 5-6. TRANSMISSION OIL TEMPERATURE LIMITS. NOTE 110°C - Warning Light On. Gust spreads are not normally reported. To ob- tain spread, compare minimum and maximum 5-7. TRANSMISSION OIL PRESSURE LIMITS. wind velocities.

  • Page 173: Power Limits

    TM 55-1520-228-10 SECTION III. POWER LIMITS 5-11. ENGINE LIMITATIONS. (2) Practice autorotation is prohibited using emergency fuel. Refer to Figure 5-1 , Figure 5-2. If N2 limit is exceed- 5-13. DELETED. ed, entry on DA Form 2408-13-1 must include duration and torque indicated.

  • Page 174: Load Limits

    Chapter 6. SECTION V. AIRSPEED LIMITS 5-19. AIRSPEED LIMITS. b. Whenever any OH-58A/C helicopter is operated without its cabin doors: (1) All soundproof blankets must be in service- a. Refer to airspeed operating limits chart (figure able condition and firmly attached.
  • Page 175 TM 55-1520-228-10 T63-A-720 Figure 5-3. Airspeed Operating Limits Chart Change 11...

  • Page 176: Maneuvering

    TM 55-1520-228-10 SECTION VI. MANEUVERING 5-22. AEROBATIC MANEUVERS. a. A qualified OH-58A/C IP must be in position to take control of the aircraft. Aerobatic maneuvers are prohibited. Aerobatic flight is b. Reported surface winds must not exceed 20 defined to be any intentional maneuver involving an knots.
  • Page 177 TM 55-1520-228-10 Figure 5-4. Practice Autorotation Landing Limits Crosswind Components 5-28.1. SLOPE LANDING/TAKE-OFF LIMITATIONS. CAUTION Slope Operations shall be limited to slopes of 8 degrees Caution is to be exercised for slopes or less. greater than 5 degrees since rigging, loading, terrain and wind conditions may alter the slope landing capability.

  • Page 178: Environmental Restrictions

    TM 55-1520-228-10 SECTION VII. ENVIRONMENTAL RESTRICTIONS 5-29. FLIGHT UNDER INSTRUMENT METEORO- Salt spray ingestion in turbine engines may result in a deterioration in performance as well as a loss in com- LOGICAL CONDITIONS (IMC). pressor stall margin. When operating within 10 miles of salt water or within 200 miles of volcanic activity appro- This aircraft is restricted to visual flight conditions.

  • Page 179: Chapter 6 Weight/Balance And Loading

    6-2. CLASSIFICATION OF HELICOPTER. fuselage stations, buttlines and waterlines. The primary purpose of the figure is to aid personnel in the computa- Army Model OH-58A/C is in Class 2. Additional direc- tion of helicopter weight/balance and loading. Figure 6-1. Helicopter Station Diagram...
  • Page 180 TM 55-1520-228-10 6-4. LOADING CHARTS. existing fuselage hardware. The strength of the cargo tiedowns on the cargo platform is 2100 pounds. a. Information. The loading data contained in this 6-7.1 CARGO RESTRAINT CRITERIA chapter is intended to provide information necessary to work a loading problem for the helicopters to which this The amount of restraint that must be used to keep the manual is applicable.
  • Page 181 TM 55-1520-228-10 3000 MS019072 Figure 6-2. Center of Gravity Limit Chart Change 11...
  • Page 182 TM 55-1520-228-10 Figure 6-3. Cargo Space Change 10...
  • Page 183 TM 55-1520-228-10 Figure 6-4. Fuel Loading Chart Change 11...
  • Page 184 TM 55-1520-228-10 Figure 6-5. Personnel Loading...
  • Page 185 TM 55-1520-228-10 6-9. OIL DATA. b. Combat equipped paratroopers: 260 lbs. per in- dividual. For weight and balance purposes, engine oil is part of aircraft basic weight. c. Crew and passengers with no equipment: com- pute weight according to each individual’s estimate. 6-10.

  • Page 189: Dd Form

    TM 55-1520-228-10 SECTION II. DD FORM 365 6-14. DD FORM 365-1 - BASIC WEIGHT The form is a continuous history of the basic weight and CHECK LIST. moment resulting from structural equipment changes. At all times the last entry is considered current The form is a tabulation of equipment that is, or may be, weight and balance status of the basic helicopter.

  • Page 191: Introduction

    The purpose of this chapter is to provide the best avail- NOTE able performance data for the OH-58A/C helicopter. Regular use of this information will enable you to receive The information provided in this chapter maximum safe utilization from the aircraft. Although...
  • Page 192 TM 55-1520-228-10 Torque Available ..............7-47 Figure 7-11.
  • Page 193 TM 55-1520-228-10 Sheet 10 of 13, Pressure Altitude Sea Level to 6000 Ft, FAT = +30_C ... . . 7-72 Sheet 11 of 13, Pressure Altitude 8000 Ft to 14,000 Ft, FAT = +30_C .
  • Page 194 TM 55-1520-228-10 7-3. GENERAL. 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 The data presented covers the maximum range of con- and top of each chart are used to determine if slippage ditions and performance that can reasonably be ex-...
  • Page 195 TM 55-1520-228-10 7-7. SPECIFIC CONDITIONS. 7-9. PERFORMANCE DISCREPANCIES. The data presented are accurate only for specific condi- Regular use of this chapter will allow you to monitor tions listed under the title of each chart. Variables for instruments and other aircraft systems for malfunction, which data are not presented, but which may affect that by comparing actual performance with planned perfor- phase of performance, are discussed in the text.

  • Page 196: Temperature Conversion

    TM 55-1520-228-10 LIST OF ABBREVIATIONS (Cont) Abbreviation Definition Abbreviation Definition Hour Nautical Mile Indicated airspeed Percent torque In ground effect PRESS Pressure Inch Per square inch IN HG Inches of mercury Rate of climb Infrared Rate of descent KIAS Knots indicated airspeed Revolutions per minute Knot SPEC...
  • Page 197 TM 55-1520-228-10 TEMPERATURE CONVERSION TEMPERATURE EXAMPLE CONVERSION WANTED OH-58A/C -FREE AIR TEMPERATURE IN DEGREES CELSIUS KNOWN FREE AIR TEMPERATURE = +32 F Figure 7-1. Temperature Conversion Chart...
  • Page 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. Change 10...

  • Page 199: Torque Available

    TM 55-1520-228-10 SECTION X. TORQUE AVAILABLE 7-37. DESCRIPTION. Prolonged IGE hover may increase engine inlet temperature as much as 10ºC, therefore, a higher The torque available charts show the effects of altitude FAT must be used to correct for the increase under this and temperature on engine torque.
  • Page 200 TM 55-1520-228-10 Figure 7-11. Maximum Torque Available (30 Minute Operation) Chart (Sheet 1 of 4) 7-48...
  • Page 201 TM 55-1520-228-10 Figure 7-11. Maximum Torque Available (30 Minute Operation) Chart (Sheet 2 of 4) 7-49...
  • Page 202 TM 55-1520-228-10 Figure 7-11. Maximum Torque Available (30 Minute Operation) Chart (Sheet 3 of 4) 7-50...
  • Page 203 TM 55-1520-228-10 Figure 7-11. Maximum Torque Available (30 Minute Operation) Chart (Sheet 4 of 4) 7-51...
  • Page 204 TM 55-1520-228-10 Figure 7-12. Torque Available (Continuous Operation) Chart (Sheet 1 of 4) 7-52...
  • Page 205 TM 55-1520-228-10 Figure 7-12. Torque Available (Continuous Operation) Chart (Sheet 2 of 4) 7-53...
  • Page 206 TM 55-1520-228-10 Figure 7-12. Torque Available (Continuous Operation) Chart (Sheet 3 of 4) 7-54...
  • Page 207 BLEED AIR ON PARTICLE SEPARATOR AND TORQUE REVERSE FLOW INLET INSTALLED AVAILABLE 100% RPM JP-4 OH-58A/C T63-A-720 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.
  • Page 208 TM 55-1520-228-10 SECTION XI. HOVER 7-41. DESCRIPTION. (2) Move right to FAT. The hover charts (figure 7-13, sheets 1 and 2) show the (3) Move down to gross weight, read the hover ceiling torque required hover maximum right crosswind corresponding to a 10% respectively at various pressure altitudes, ambient directional control margin.
  • Page 211 TM 55-1520-228-10 Figure 7-13. Hover Chart (Sheet 3 of 3) Change 10 7-59...
  • Page 212 TM 55-1520-228-10 SECTION XII. TAKEOFF (NOT APPLICABLE) 7-44. DELETED. 7-45. DELETED. 7-46. DELETED. FIGURE 7-14. ON PAGE 7-61 HAS BEEN DELETED. 7-60 Change 11...
  • Page 214 TM 55-1520-228-10 SECTION XIII. CRUISE 7-47. DESCRIPTION. 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 permissible airspeed (V ) limits appear as red The cruise charts (figure 7-15, sheets 1 through 13) show the torque pressure and engine rpm required for lines on some charts.
  • Page 215 TM 55-1520-228-10 Figure 7-15. Cruise Chart (Sheet 1 of 13) 7-63...
  • Page 216 TM 55-1520-228-10 Figure 7-15. Cruise Chart (Sheet 2 of 13) 7-64...
  • Page 217 TM 55-1520-228-10 Figure 7-15. Cruise Chart (Sheet 3 of 13) 7-65...
  • Page 218 TM 55-1520-228-10 Figure 7-15. Cruise Chart (Sheet 4 of 13) 7-66...
  • Page 219 TM 55-1520-228-10 Figure 7-15. Cruise Chart (Sheet 5 of 13) 7-67...
  • Page 220 TM 55-1520-228-10 Figure 7-15. Cruise Chart (Sheet 6 of 13) 7-68...
  • Page 221 TM 55-1520-228-10 Figure 7-15. Cruise Chart (Sheet 7 of 13) 7-69...
  • Page 222 TM 55-1520-228-10 Figure 7-15. Cruise Chart (Sheet 8 of 13) 7-70...
  • Page 223 TM 55-1520-228-10 Figure 7-15. Cruise Chart (Sheet 9 of 13) 7-71...
  • Page 224 TM 55-1520-228-10 Figure 7-15. Cruise Chart (Sheet 10 of 13) 7-72...
  • Page 225 TM 55-1520-228-10 Figure 7-15. Cruise Chart (Sheet 11 of 13) 7-73...
  • Page 226 TM 55-1520-228-10 Figure 7-15. Cruise Chart (Sheet 12 of 13) 7-74...
  • Page 227 TM 55-1520-228-10 Figure 7-15. Cruise Chart (Sheet 13 of 13) 7-75...
  • Page 228 TM 55-1520-228-10 SECTION XIV. DRAG 7-50. DESCRIPTION. 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 The drag chart (figure 7-16) shows the torque change direction, drag area change may be found from a known required for flight due to drag area change as a result of torque change.
  • Page 229 TM 55-1520-228-10 DRAG DRAG OH-58A/C T63-A-720 CALIBRATED TORQUE-%Q Figure 7-16. Drag Chart Change 10 7-77...

  • Page 230: Torque Available

    TM 55-1520-228-10 SECTION XV. CLIMB - DESCENT 7-53. DESCRIPTION - CLIMB - EXAMPLE DESCENT CHART. WANTED (SEE FIGURE 7-15) The grid of the climb descent chart (figure 7-17) shows EXCESS TORQUE AVAILABLE CLIMB the change in torque (above or below torque required for MAXIMUM CONTINUOUS POWER level flight...
  • Page 231 TM 55-1520-228-10 Figure 7-17. Climb – Descent Chart 7-79...
  • Page 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...
  • Page 236 TM 55-1520-228-10 SECTION XVI. IDLE FUEL FLOW 7-59. DESCRIPTION. 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 The idle fuel flow chart (figure 7-19) shows the fuel flow cruise charts to obtain fuel flow for cruise power condi- at flight idle and at flat pitch with 100% rpm.
  • Page 237 TM 55-1520-228-10 Figure 7-19. Idle Fuel Flow Chart 7-85/(7-86 blank)

  • Page 239: Chapter 8 Normal Procedures

    TM 55-1520-228-10 CHAPTER 8 NORMAL PROCEDURES SECTION I. MISSION PLANNING 8-1. MISSION PLANNING. b. Passenger Briefing The following guide may be used in accomplishing required passenger briefings; items that do not pertain to a specific mission may be Mission planning begins when the mission is assigned omitted.

  • Page 240: Operating Procedures And Maneuvers

    TM 55-1520-228-10 (e) Internal communication. (n) Aviation life support equipment (ALSE). (f) Security of equipment. Emergency procedures (g) Smoking. (a) Emergency exits. (h) Oxygen. (b) Emergency equipment. (i) Refueling. (c) Emergency landing/ditching proce- dures. (j) Weapons. (d) Bail out. (k) Protective masks. (e) Survival.
  • Page 241 TM 55-1520-228-10 8-8. BEFORE EXTERIOR CHECKS. Pilot seat, seat belt, shoulder harness, and armor side panels – Check condition. Crew Door – Check condition. Deleted. Publications – Check DA Forms 2408-12 8-9. EXTERIOR CHECK. and -18 DD Form 1896 if required; DD Form 365-4 Compass Cards;...
  • Page 242 TM 55-1520-228-10 Figure 8-1. Exterior Check Diagram Change 10...
  • Page 243 TM 55-1520-228-10 Fire extinguisher – Check. Vertical fin – Check condition; antenna con- nections secure. Cabin door – Check condition. Tail skid – Check condition. Fuselage – Check as following items are * 2. Main rotor blade – Check condition, rotate 90 checked: degrees to fuselage, tiedown removed.
  • Page 244 TM 55-1520-228-10 8-14. AREA 5 (figure 8-1) FUSELAGE – Cyclic – Check secure or stow as required, cannon plug connected. CABIN LEFT SIDE. Collective – Check secure or stow as re- Fuselage top – Check as following items are quired. checked: Cabin door –...
  • Page 245 TM 55-1520-228-10 c. INST LTS, CONSOLE LTS, and NVG POS e. HYD BOOST switch — HYD BOOST. LTS — As required. *7. Flight controls — Check and set as follows: *d. ANTI-COLLISION LTS switch — As re- a. Control frictions — OFF. quired.
  • Page 246 TM 55-1520-228-10 k. N1 — 62–64 percent. 5. Deleted. *6. Flight Instruments — Check and set as follows: a. Attitude indicator — Horizon ; Set 5 de- Do not have battery switch on and APU system grees above horizon to indicate level attitude at cruise charging simultaneously for more than 2 min- flight utes.
  • Page 247 TM 55-1520-228-10 If deceleration time is less than 2 seconds, 8-21. TAKEOFF. aircraft will not be flown. Enter conditions in the “Remarks” section of DA Form 2408-13-1. CAUTION GEN switch – GEN. During takeoff with the helicopter Throttle – Slowly increase to open. skids close to the ground, nose-low attitudes of 10 degrees or more can 8-19.
  • Page 248 TM 55-1520-228-10 8-23. BEFORE LANDING. Battery change – Check as follows: BAT switch – OFF. Prior to landing, the following checks shall be accom- plished: Ammeter – Check change indication. If the change in indication is less than 5.0 am- Crew, passenger and mission equipment –...

  • Page 249: Instrument Flight

    TM 55-1520-228-10 SECTION III. INSTRUMENT FLIGHT ducted on an emergency basis only. Flight handling, 8-26. INSTRUMENT FLIGHT – GENERAL. stability characteristics, and range are the same during instrument flight as for visual flight. Navigation and com- This aircraft is restricted to visual flight conditions. Flight munication equipment are adequate for instrument into instrument meteorological conditions will be con- flight.
  • Page 250 TM 55-1520-228-10 d. During landing, starting, and rotor coastdown, 8-32. LOSS TAIL ROTOR spike knock could also occur, especially if there are high EFFECTIVENESS. winds and/or the elastomeric damper is deteriorated. This type of spike knock is not considered damaging to the aircraft.
  • Page 251 TM 55-1520-228-10 Figure 8-2. Effects of wind Azimuth On Aircraft. (3) Disc vortex (280-330 degrees). Winds low airspeed mission with only minimum essential per- within this region will cause the main rotor tip vortices sonnel and equipment on board. to be directed onto the tail rotor. The effect of this main rotor vortex is to cause the tail rotor to operate in an (2) Low indicated airspeed.

  • Page 252: Adverse Environmental Conditions

    TM 55-1520-228-10 d. The OH-58A/C, in its typical mission configura- tained to minimize the yaw excursions that could lead tion, is closer to its maximum gross weight than most to LTE. Additionally, it has been determined that there is other aircraft in the Army inventory; thus, the pilot is...
  • Page 253 TM 55-1520-228-10 4 If exhaust covers are missing or improperly NOTE installed, rain or snow may enter the engine through the exhaust stacks and subsequently freeze, causing the Due to the variation in types of jet fuel, and N turbine blades to be imbedded in ice. If the in cold weather the engine may experi- starter is activated under these circumstances, serious ence a short delay before lightoff after...
  • Page 254 TM 55-1520-228-10 8-35. SNOW OPERATIONS. b. In the storm: (1) Maintain level attitude and constant power There are no unusual flight operational characteristics setting. Airspeed fluctuations should be expected and in snow operations. Refer to FM 1-202, Environmental disregarded. Flight, for snow takeoff and landing technique. (2) Maintain original heading, turning only when necessary.
  • Page 255 TM 55-1520-228-10 8-40. ICING CONDITIONS. may induce more asymmetrical shedding of ice, further aggravating helicopter vibration levels. a. Intentional flight in any icing condition is prohib- ited. If icing conditions are encountered during flight, WARNING effort should be made to vacate the icing conditions. Ice shed from rotor blades and/or other rotating components...

  • Page 257: Chapter 9 Emergency Procedures

    TM 55-1520-228-10 CHAPTER 9 EMERGENCY PROCEDURES SECTION I. AIRCRAFT SYSTEMS 9-1. HELICOPTER SYSTEMS. This section de- 2. Fuel Shutoff Valve Handle — OFF. scribes the helicopter systems emergencies that may 3. BAT switch — OFF. Before turning reasonably be expected to occur and presents the the battery switch off during in-flight procedures to be followed.
  • Page 258 TM 55-1520-228-10 helicopter may be flown at reduced power to a suitable landing area. Under this condition, the pilot should always be prepared for a complete power loss. the event a partial power condition is accompanied by Do not respond to the RPM audio and/or warn- erratic engine operation or power surging, and flight ing light illumination without first confirming en- is to be continued, the throttle may be adjusted in an...
  • Page 259 TM 55-1520-228-10 Figure 9-1. Emergency Exits and Equipment (Sheet 1 of 2) Change 14 9-3...
  • Page 260 TM 55-1520-228-10 Figure 9-1. Emergency Exits and Equipment (Sheet 2 of 2) 9-4 Change 14...
  • Page 261 TM 55-1520-228-10 Figure 9-2. Autorotational Glide Characteristics Chart Change 14 9-5...
  • Page 262 TM 55-1520-228-10 Figure 9-3. Minimum Height for Safe Landing After Engine Failure Chart 9-6 Change 14...
  • Page 263 TM 55-1520-228-10 9-8. MINIMUM RATE OF DESCENT – POWER 2. Throttle — Adjust until normal N-2 OFF. The power-off minimum rate of descent is at- operating RPM is attained. tained at an indicated airspeed of 43 knots and 100% 3. LAND AS SOON AS POSSIBLE. Perform rotor RPM.
  • Page 264 TM 55-1520-228-10 system, such as a severed driveshaft, causing the tail a. Reduced power (low torque). rotor to lose power. Indications: The nose of the helicopter will a. Powered Flight. turn right when power is applied. (1) Indications: (2) Procedure: Abnormal vibrations.
  • Page 265 TM 55-1520-228-10 Varying degrees of right yaw depending on If spin cannot be stopped and crash is imminent, an au- power applied and airspeed at time of failure. torotation may be the best course of action. Maintain full left pedal until the spin stops, then adjust to maintain heading.
  • Page 266 TM 55-1520-228-10 9-30.1. DELETED. 9-31. SMOKE AND FUME ELIMINATION. Smoke and/or toxic fumes entering the cockpit and cabin can If aircraft fire occurs on ground while using be exhausted as follows: Ground Power Unit (GPU) ; the GPU should be shutdown immediately.
  • Page 267 TM 55-1520-228-10 2. LAND AS SOON AS POSSIBLE. 1. Doors – Jettison at a hover. 3. EMER SHUTDOWN after landing. 2. Crew (except pilot) and passengers – Exit. 3. Hover a safe distance away from If high DC amperage indication does not dissipate, pilot personnel.

  • Page 268: Mission Equipment (Not Applicable)

    TM 55-1520-228-10 SECTION II. MISSION EQUIPMENT NOT APPLICABLE 9-12 Change 14...
  • Page 269 TM 55-1520-228-10 Table 9-2. Warning/Caution Panel Lights 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.

  • Page 271: Appendix Areferences

    TM 55-1520-228-10 APPENDIX A REFERENCES AMSAT-I-M 1379 R-E ......Request for Depot Engineering Support AR 95-1 .
  • Page 272 TM 55-1520-228-10 MWO 1-1520-228-50-53 ......Installation of Global Positioning System Special Mission Kits MWO 55-1520-228-30-30 .
  • Page 273 TM 55-1520-228-10 ALPHABETICAL INDEX Subject Paragraph, Figure, Subject Paragraph, Figure, Table Number Table Number Approved Fluids ......T2-4 Approved Fuels .
  • Page 274 TM 55-1520-228-10 Subject Paragraph, Figure, Subject Paragraph, Figure, Table Number Table Number Checklist, Operating Procedures and Control, Anti-Torque (Direction) ... . . 2-28 Maneuvers ......Control (Hydraulic System) .
  • Page 275 TM 55-1520-228-10 Subject Paragraph, Figure, Subject Paragraph, Figure, Table Number Table Number Crew Requirements, Minimum ... Torque Available ....7-37 Critical Tailboom Dynamic Modes .
  • Page 276 TM 55-1520-228-10 Subject Paragraph, Figure, Subject Paragraph, Figure, Table Number Table Number Engine, Before Starting ....8-16 Flight Restrictions with Float Landing Gear Installed .
  • Page 277 TM 55-1520-228-10 Subject Paragraph, Figure, Subject Paragraph, Figure, Table Number Table Number HAVE QUICK System, Indicators (Power Train System) ... . 2-41 UHF/AM Radio Set ....3-23, F3-6 Induction System .

  • Page 278: Maximum Torque Available Chart (30 Minute Operation)

    TM 55-1520-228-10 Subject Paragraph, Figure, Subject Paragraph, Figure, Table Number Table Number Limits, Starter ......DELETED Operation, Sand and Dust .

  • Page 279: Operating Procedures

    ... 3-45, F3-10 (OH-58A/C) ......

  • Page 280: Deleted

    TM 55-1520-228-10 Subject Paragraph, Figure, Subject Paragraph, Figure, Table Number Table Number Shutdown, Engine ......8-24 Transponder Set, Operating Procedures .

  • Page 281: Vhf/Am Radio Set (An/Arc-115)

    TM 55-1520-228-10 Subject Paragraph, Figure, Subject Paragraph, Figure, Table Number Table Number Voice Security Equipment Takeoff ..... . . DELETED TSEC/KY-58 .
  • Page 283 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...
  • Page 285 These are the instructions for sending an electronic 2028 The following format must be used if submitting an electronic 2028. The subject line must be exactly the same and all fields must be included; however only the following fields are mandatory: 1, 3, 4, 5, 6, 7, 8, 9, 10, 13, 15, 16, 17, and 27.
  • Page 287 Use Part II (reverse) for Repair Parts and Spe- DATE RECOMMENDED CHANGES TO PUBLICATIONS AND cial Tool Lists (RPSTL) and Supply Catalogs/ Supply Manuals (SC/SM) BLANK FORMS 8/30/02 For use of this form, see AR 25--30; the proponent agency is ODISC4. TO: (Forward to proponent of publication or form)(Include ZIP Code) FROM: (Activity and location)(Include ZIP Code) Commander, U.S.
  • Page 288 TO: (Forward direct to addressee listed in publication) FROM: (Activity and location) (Include ZIP Code) DATE Commander, U.S. Army Aviation and Missile Command MSG, Jane Q. Doe 8/30/02 ATTN: AMSAM--MMC--MA--NP 1234 Any Street Redstone Arsenal, AL 35898 Nowhere Town, AL 34565 PART II -- REPAIR PARTS AND SPECIAL TOOL LISTS AND SUPPLY CATALOGS/SUPPLY MANUALS PUBLICATION NUMBER DATE...
  • Page 289 Commander, U.S. Army Aviation and Missile Command ATTN: AMSAM-MMC-MA-NP Redstone Arsenal, AL 35898 PART 1 -- ALL PUBLICATIONS (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 Helicopter ITEM PAGE PARA--...
  • Page 290 Commander, U.S. Army Aviation and Missile Command ATTN: AMSAM-MMC-MA-NP Redstone Arsenal, AL 35898 PART II -- REPAIR PARTS AND SPECIAL TOOL LISTS AND SUPPLY CATALOGS/SUPPLY MANUALS PUBLICATION NUMBER TM 55-1520-228-10 DAT 17 JAN 1989 TITLE Operator's Manual Army Model OH-58A/C Helicopter TOTAL NO. PAGE COLM LINE...

  • Page 291: (30 Minute Operation) C

    The Metric System and Equivalents Linear Measure Liquid Measure 1 centiliter = 10 milliters = .34 fl. ounce 1 centimeter = 10 millimeters = .39 inch 1 deciliter = 10 centiliters = 3.38 fl. ounces 1 decimeter = 10 centimeters = 3.94 inches 1 liter = 10 deciliters = 33.81 fl.
  • Page 292 PIN: 014142-000...

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