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4-2-1. Armament Subsystems The armament subsystems, (fig. 4-2-1) are the M24, and M41 machine guns installed in the cabin door, cabin escape hatch, (M24) and on the ramp (M41). The two flexible 7.62 mm machine guns (M60D) (fig. 4-2-2) are free pointing but limited in traverse, elevation, and depression by cam surfaces, stops on the pintles, and pintle posts of the left and right mount assemblies (fig. 4-2-3). Spent cartridges are collected by an ejection control bag on the right side of the machine gun, and an ammunition can is on the left side (fig. 4-2-4). 4-2-2. Machine Gun. The 7.62 machine gun (M60D) is a link-belt-fed gas-operated air-cooled automatic weapon. Refer to TM 9-1005-224-10. 4-2-3. Mount Assemblies (M24). The mount assemblies (fig. 4-2-5) are installed on mounting brackets fastened inside the helicopter and secured with mounting pins. 4-2-4. Machine Gun Controls. For information on the operation and maintenance of the M24 and M42 machine gun systems, refer to TM 9-1005-224-10 and 9-1005-262-13. WARNING To prevent injury to personnel, the cocking handle must be returned to the forward or locked position before firing. WARNING Pressing the trigger to release the bolt accomplishes feeding and releasing of the firing mechanism. Unless firing is intended, make sure the machine gun is cleared of cartridges before pressing the trigger. CAUTION To prevent damage to the cartridge tray when no ammunition is in the machine gun, retard the forward force of the released bolt by manually restraining forward movement of the cocking handle. SECTION II. ARMAMENT TM 1-1520-240-10 4-2-5. Mount Assembly Stops, Cams, Quick-Release Pin, and Shock Cord (M24). The mount stops, cams, quick-release pin, and shock cord have the following functions: a. Maximum traverse (table 4-2-1) of the machine gun are controlled by stops on both sides of the cam on the pintle post. b. Maximum elevation and depression are controlled by cam surfaces on the pintle. c. The quick-release pin (fig. 4-2-5 is attached by cable to the mount bracket of the mount and fastens the mount bracket to the rear bracket at the helicopter opening. d. The shock cord (fig. 4-2-6) is fastened to the mount bracket and to the machine gun when stowed. 4-2-6. Operation — Armament Subsystem M24. Operate the ARMAMENT SUBSYSTEM M24 as described in the following paragraphs. 4-2-7. Preflight Checks. The preflight check consists of the following: 1. Machine Gun M60D — Check to make sure that gun is thoroughly cleaned and lubricated, operable, and secured on the pintle with the quick-release pin (fig. 4-2-9). 2. Ejection control bag (fig. 4-2-7) — Installed and securely latched. 3. Ammunition can (fig. 4-2-8) — Installed on machine gun and loaded. 4. Safety — Push button to safe (S) position, aim at clear area, and try to fire the unloaded machine gun. 5. Mount — Secured and checked for free pintle movement. 6. Extra ammunition boxes — Properly stowed. 4-2-8. Before Takeoff Check. 1. Check the weapon safety is on — (S) position. 2. Inspect the chamber to be sure it is clear. 3. Close the cover and secure the machine gun in stowed position. 4-2-1
TM 1-1520-240-10 Effective range 1100 meters (max) Rate of fire 550-650 rnds per min Length, overall 44.875 in Sighting Aircraft ring and post type Total traversing capability - left 122 side Total traversing capability - 127 right side 4-2-2 Table 4-2-1. Armament Subsystem M24 Data Depression and elevation limits: Left side maximum depression Left side maximum elevation Right side maximum depression Right side maximum elevation 6730 730 73 7
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TECHNICAL MANUAL OPERATOR’S MANUA
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TM 1-1520-240-10 b Change 1 WARNING
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URGENT TM 1-1520-240-10 CHANGE HEAD
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*Zero in this column indicates an o
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TM 1-1520-240-10 TECHNICAL MANUAL H
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TM 1-1520-240-10 Chapter/Section Pa
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TM 1-1520-240-10 1-1-13. Aircraft D
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TM 1-1520-240-10 2-1-2 Figure 2-1-1
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TM 1-1520-240-10 2-1-4 Figure 2-1-3
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TM 1-1520-240-10 2-1-10. Brakes and
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TM 1-1520-240-10 2-1-8 Figure 2-1-5
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TM 1-1520-240-10 2-1-10 Figure 2-1-
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TM 1-1520-240-10 2-1-12 Figure 2-1-
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TM 1-1520-240-10 2-1-14 Figure 2-1-
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TM 1-1520-240-10 2-1-16 Figure 2-1-
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TM 1-1520-240-10 2-1-18 Figure 2-1-
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TM 1-1520-240-10 2-2-2 Fwd Valve Fw
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TM 1-1520-240-10 2-2-8. TROOP WARN
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TM 1-1520-240-10 The power turbine
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TM 1-1520-240-10 Figure 2-3-2. Emer
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TM 1-1520-240-10 and NO. 2 OIL TEMP
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TM 1-1520-240-10 d. RRPM droop comp
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TM 1-1520-240-10 2-3-10 Figure 2-3-
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TM 1-1520-240-10 Table 2-3-1. T55-G
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TM 1-1520-240-10 2-3-14 Table 2-3-1
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TM 1-1520-240-10 Table 2-3-1. T55-G
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TM 1-1520-240-10 2-3-18 Figure 2-3-
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2-4-1. Fuel Supply System. The fuel
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2-4-6. Manual Defueling Valve. A ma
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2-4-6). The switches are used to te
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2-5-1. Flight Control System. The h
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Figure 2-5-2. Cyclic Stick Grip 2-5
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(1) HDG Switch. The HDG (heading) s
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2-6-1. Hydraulic Power Supply Syste
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us through the RAMP PWR switch and
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TM 1-1520-240-10 No. 2 engine trans
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TM 1-1520-240-10 2-7-12. Transmissi
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2-9-1. Anti Icing Systems. Anti ici
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through the HYDRAULICS MAINT PNL LT
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TM 1-1520-240-10 SECTION X. HEATING
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TM 1-1520-240-10 SECTION XI. ELECTR
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2-11-7. BATT Switch. NOTE The follo
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TM 1-1520-240-10 2-12-2 Figure 2-12
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TM 1-1520-240-10 a. Electroluminesc
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TM 1-1520-240-10 2-13-4 Figure 2-13
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TM 1-1520-240-10 bulkhead. The six
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TM 1-1520-240-10 2-13-8 Figure 2-13
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2-14-1. General. The following para
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When the helicopter descends below
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2-14-13. Controls and Function, Rad
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2-14-21. CHRONOMETER. Two digital c
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Table 2-14-1. Master Caution Panel
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2-14-30. CAUTION LT Panel. The CAUT
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SECTION XV. SERVICING, PARKING, AND
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k. Remove ground cables from the he
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Figure 2-15-2. Servicing Diagram (S
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Figure 2-15-2. Servicing Diagram (S
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TM 1-1520-240-10 Table 2-15-1. Serv
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Table 2-15-3. JP-4 Equivalent Fuel
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2-15-7. Gravity Refueling. Perform
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2-15-15. Transmission Oil System. S
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FLIGHT CONTROL, UTILITY, POWER STEE
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Figure 2-15-4. Protective Covers TM
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Figure 2-15-6. Installation of Heli
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TM 1-1520-240-10 3-1-2 Table 3-1-1.
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TM 1-1520-240-10 3-2-2 Figure 3-2-1
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TM 1-1520-240-10 3-2-6. Word-of-Day
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TM 1-1520-240-10 3-2-9. Conferencin
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TM 1-1520-240-10 SET. 3-2-8 (2) Cha
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TM 1-1520-240-10 3-2-10 NOTE The an
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TM 1-1520-240-10 c. Frequency Range
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TM 1-1520-240-10 3-2-19. Controls a
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TM 1-1520-240-10 3-2-21. HF Radio S
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TM 1-1520-240-10 3-2-24. Operating
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TM 1-1520-240-10 CONTROLS/ FUNCTION
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TM 1-1520-240-10 CONTROLS/ INDICATO
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TM 1-1520-240-10 (6) Push the INIT
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TM 1-1520-240-10 NOTE To exit and s
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TM 1-1520-240-10 3-3-8. Gyromagneti
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TM 1-1520-240-10 3-3-6 Figure 3-3-5
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TM 1-1520-240-10 CONTROLS/ INDICATO
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TM 1-1520-240-10 LEFT DISPLAY RIGHT
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TM 1-1520-240-10 e. FLY-TO DEST thu
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TM 1-1520-240-10 from the No. 2 (No
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Page 204 and 205: 3-4-1. Transponder System (AN/APX-1
Page 206 and 207: 3-4-3. Normal Operation — Transpo
Page 208 and 209: 4-1-1. Radar Signal Detecting, AN/A
Page 210 and 211: 4-1-2. CONTROLS AND FUNCTION, RADAR
Page 212 and 213: 4-1-3). Check OFP and EID numbers a
Page 214 and 215: 4-1-6. Controls and Indicators, Mis
Page 216 and 217: CONTROLS/ FUNCTION INDICATOR ARM In
Page 218 and 219: Figure 4-1-6. Flare Dispenser Syste
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Page 226 and 227: Figure 4-1-8. Heads Up Display AN/A
Page 228 and 229: No. Symbol Source Range/Description
Page 230 and 231: CAUTION Keep the protective caps on
Page 232 and 233: 8. MODE 1-4/DCLT switch — DCLT (1
Page 236 and 237: Figure 4-2-1. Armament Subsystem TM
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Page 240 and 241: Figure 4-2-5. Right Machine Gun Mou
Page 242 and 243: Figure 4-2-8. Ammunition Can — In
Page 244: Figure 4-2-10. M41 Mount — Instal
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Page 249 and 250: TM 1-1520-240-10 4-3-4 Figure 4-3-2
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Page 272 and 273: TM 1-1520-240-10 SECTION IV. EXTEND
Page 274 and 275: Figure 4-4-1. ERFS II Fuel Tank TM
Page 276 and 277: Figure 4-4-2. ERFS II Fuel Control
Page 278: 4-4-9. FARE Transfer. CAUTION Some
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400 810 890 781 940 890 O C C C C C
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Figure 5-2-1 Instrument Markings (S
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5-3-1. Engine Rating and Power Leve
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5-5-1. Airspeed Operating Limits. A
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Figure 5-5-2. Airspeed Limitations
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5-7-1. Engine Inlet Screen Limitati
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Figure 5-7-1. Rotor Blade Start-Up
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TM 1-1520-240-10 5-7-5/(5-7-6 blank
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TM 1-1520-240-10 SEA STATE 5-8-2 Ta
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6-1-1. Purpose. This chapter contai
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6-2-1. DD Form 365-3 Chart C — Ba
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TM 1-1520-240-10 6-3-2 Figure 6-3-1
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TM 1-1520-240-10 6-4-11. Litter Sup
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TM 1-1520-240-10 6-4-4 Figure 6-4-2
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TM 1-1520-240-10 6-4-6 Figure 6-4-4
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TM 1-1520-240-10 6-4-8 Figure 6-4-5
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TM 1-1520-240-10 6-4-10 Figure 6-4-
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6-5-1. Mission Equipment. CH-47D mi
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Figure 6-5-1. Mission Equipment Wei
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TM 1-1520-240-10 6-6-8. Uniformly D
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TM 1-1520-240-10 6-6-10. Concentrat
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TM 1-1520-240-10 face of the floor.
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TM 1-1520-240-10 6-6-8 Figure 6-6-3
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TM 1-1520-240-10 6-6-10 Figure 6-6-
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TM 1-1520-240-10 6-6-12 Figure 6-6-
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TM 1-1520-240-10 6-6-21. Winch. Ref
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TM 1-1520-240-10 6-6-16 CAUTION Do
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TM 1-1520-240-10 6-6-35. Cargo Weig
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TM 1-1520-240-10 Figure 6-6-11. Car
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TM 1-1520-240-10 6-6-22 Figure 6-6-
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TM 1-1520-240-10 6-6-24 CAUTION Exc
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TM 1-1520-240-10 6-6-26 Table 6-6-2
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TM 1-1520-240-10 6-6-28 Table 6-6-3
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TM 1-1520-240-10 6-6-30 Figure 6-6-
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TM 1-1520-240-10 6-6-32 Figure 6-6-
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TM 1-1520-240-10 6-7-2 Figure 6-7-1
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TM 1-1520-240-10 b. Calculated Data
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7-2-1. Emergency Torque Available.
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SECTION III. MAXIMUM TORQUE AVAILAB
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Figure 7-3-2. Maximum Torque Availa
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TM 1-1520-240-10 7-4-2 Figure 7-4-1
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TM 1-1520-240-10 7-5-2 Figure 7-5-1
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7-6-1. Description. The takeoff cha
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7-7-1. Description. The cruise char
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Pressure OAT Altitude (ft) (C) Tabl
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Figure 7-7-1 Example Cruise Chart (
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Figure 7-7-3. 98 and 100% Rotor RPM
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Figure 7-7-5. 98 and 100% Rotor RPM
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Figure 7-7-7. 100% Rotor RPM, 10 an
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Figure 7-7-9. 100% Rotor RPM, 50C,
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Figure 7-7-11. 98 and 100% Rotor RP
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Figure 7-7-15. 100% Rotor RPM, 10 a
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Figure 7-7-83. 100% Rotor RPM, -10
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7-8-1. Description. The drag chart
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7-9-1. Description. a. Climb and de
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Figure 7-9-2. Climb Performance (Sh
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7-10-1. Description. The idle fuel
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Figure 7-10-2. Idle Fuel Flow Chart
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TM 1-1520-240-10 7-11-2 Figure 7-11
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TM 1-1520-240-10 c. Estimated Data.
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SECTION II. CONTINGENCY TORQUE AVAI
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SECTION III. MAXIMUM TORQUE AVAILAB
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Figure 7A-3-2. Intermediate Torque
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TM 1-1520-240-10 7A-4-2 Figure 7A-4
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TM 1-1520-240-10 7A-5-2 Figure 7A-5
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7A-6-1. Description. The takeoff ch
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7A-7-1. Description. The cruise cha
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Figure 7A-7-1. Example Cruise Chart
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Figure 7A-7-3. 98 and 100% Rotor RP
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Figure 7A-7-5. 98 and 100% Rotor RP
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Figure 7A-7-7. 100% Rotor RPM, 10 a
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Figure 7A-7-9. 100% Rotor RPM, 50C,
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Figure 7A-7-11. 98 and 100% Rotor R
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Figure 7A-7-15. 100% Rotor RPM, 10
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Figure 7A-25. Figure 7A-7-17. 100%
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Figure 7A-7-25. 100% Rotor RPM, 50C
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Figure 7A-36. Figure 7A-7-27. 98 an
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Figure 7A-46. Figure 7A-7-37. 98 an
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Figure 7A-7-77. 100% Rotor RPM, -10
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Figure 7A-7-83. 100% Rotor RPM, -10
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7A-8-1. Description. The drag chart
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7A-9-1. Description. a. Climb and d
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Figure 7A-9-2. Climb Performance (S
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7A-10-1. Description. The idle fuel
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Figure 7A-10-2. Single Engine Fuel
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TM 1-1520-240-10 7A-11-2 Figure 7A-
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TM 1-1520-240-10 d. Normal Procedur
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TM 1-1520-240-10 8-2-2 * 6. Forward
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TM 1-1520-240-10 8-2-4 18. 714A P3
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TM 1-1520-240-10 8-2-6 15. Upper bo
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TM 1-1520-240-10 8-2-8 * 20. Cyclic
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TM 1-1520-240-10 8-2-10 * 38. GEN 1
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TM 1-1520-240-10 8-2-12 Figure 8-2-
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TM 1-1520-240-10 Takeoff over water
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TM 1-1520-240-10 8-2-16 14. PWR XFE
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8-3-1. General. The flight characte
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SECTION IV. ADVERSE ENVIRONMENTAL C
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8-4-17. Before Leaving Helicopter.
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operating in these conditions, shou
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TM 1-1520-240-10 nals will be used
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TM 1-1520-240-10 9-1-4 EMERGENCY EX
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TM 1-1520-240-10 9-1-10. Dual Engin
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TM 1-1520-240-10 Figure 9-1-4. 712
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TM 1-1520-240-10 Figure 9-1-4. 712
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TM 1-1520-240-10 Figure 9-1-6. 714A
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TM 1-1520-240-10 Figure 9-1-6. 714A
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TM 1-1520-240-10 9-1-16 Figure 9-1-
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TM 1-1520-240-10 2. ENG COND lever
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TM 1-1520-240-10 9-1-28. Engine Shu
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TM 1-1520-240-10 9-1-40. 714A Torqu
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TM 1-1520-240-10 9-1-54. FUEL LOW a
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TM 1-1520-240-10 9-1-65. Emergency
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TM 1-1520-240-10 9-1-73. Flight Con
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9-2-1. ARMAMENT 9-2-2. Armament Sub
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Figure FO-1. General Arrangement (S
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DC ALE 47 DCDU 5 10 NO.1 SEQ NO.2 S
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Figure FO-4. DC Power Supply (Typic
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EAPS 1 FAN EAPS 2 FAN Figure FO-6.
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APPENDIX A REFERENCES TM 1-1520-240
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TM 1-1520-240-10 ABBREVIATION TERM
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TM 1-1520-240-10 ABBREVIATION TERM
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TM 1-1520-240-10 APPENDIX C CONDITI
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CONDITION 2408-13-1 ENTRY REQUIRED
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TM 1-1520-240-10 Subject Paragraph,
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By Order of the Secretary of the Ar
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RECOMMENDED CHANGES TO PUBLICATIONS
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The Metric System and Equivalents L
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