By Military Manuals and Survival Ebooks Branch, U.S. Army, Delene Kvasnicka of Survivalebooks, U.S. Military, U.S. Department of Defense, U.S. Government
TECHNICAL handbook TM 1-1520-240-10, OPERATOR’S guide FOR military CH-47D HELICOPTER (Chinook),
These directions are to be used by means of the operator. They practice to CH-47D helicopters.
The CH-47D (fig. FO-1, 2-1-1 and 2-1-2) is a twin-turbine
engine, tandem rotor helicopter designed for transportation
of shipment, troops, and guns in the course of day, evening, visible, and
instrument stipulations. (Unless another way famous, numbers
refer to fig. FO-1.) The helicopter is powered through two
T55-L-712 or T55-GA-714A shaft-turbine engines (18) on
the aft fuselage. The engines at the same time force tandem
three-bladed counterrotating rotors (13 and 19) through
engine transmissions (25), a combining transmission (16),
drive shafting (14), and relief transmissions (12 and 23).
The ahead transmission is at the ahead pylon above the
cockpit (1). The aft transmission, the combining transmission,
and force shafting are within the aft cabin part and aft
pylon sections (3 and 4). force shafting from the combining
transmission to the ahead transmission is housed in a
tunnel alongside best of the fuselage. whilst rotors are stationary,
a gas-turbine auxiliary energy unit (22) drives a generator
and hydraulic pump to provide hydraulic and electric power.
Fuel is carried in pods on either side of the fuselage. The
helicopter is provided with 4 non-retractable touchdown gear.
An front door (15) is on the ahead correct part of the cargo
compartment (2). on the rear of the shipment compartment is a
hydraulically powered loading ramp (26). The pilots seat (9)
and controls are on the correct part of the cockpit; the copilot’s
seat (40) and controls are at the left aspect. See determine 2-1-3
for usual cockpit and controls.
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Additional info for Technical, Operator's Manual - CH-47D Chinook Helicopter [TM 1-1520-240-10]
2-1-9). Each torquemeter has two pointers, one for each engine, labeled 1 and 2. Each torquemeter has a range of 0 to 150 percent. The system consists of a power output shaft, torquemeter head assembly, power supply unit, 714A ratio detector power supply unit (RDPS), and a torquemeter junction box. Power to operate the torquemeter is provided by No. 1 and No. 2 AC buses through the ENGINE NO. 1 and NO. 2 TORQUE circuit breakers on the No. 1 and No. 2 PDP. Power for the power supply unit 714A and RDPS is provided by the No.
Selection of the compartment is made by pulling the appropriate FIRE PULL handle. In figure 2-2-1 the ENG 1 FIRE PULL handle has been pulled. Selection of the container is made by placing the AGENT DISCH switch in the appropriate position. In figure 2-2-1, BTL 1 has been selected. 2-2-3. FIRE PULL Handles. WARNING Before flying the aircraft ensure that each FIRE PULL handle NVG filter holder can be rotated from the closed to the open position without causing the FIRE PULL handle to be pulled. Improper handling of the NVG filter holder may cause the FIRE PULL handle to be pulled unintentionally, thus fuel to the affected engine will be shut off and the engine will shut down.
Refer to Chapter 5 for information on use of bypass panels. Helicopters with engine air particle separator (EAPS) installed, refer to TM 1-1520-240-10 EAPS SUPPLEMENT. 2-3-4. Engine Anti–Icing. The engine air inlet fairing and engine drive shaft fairing receive anti-icing protection from the thermal radiation produced by the oil tank in the engine inlet housing. The hot oil in the oil cavity of the inlet housing warms the air as it passes into the engine inlet. 2-3-5. Engine Power Control System.