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18 Cards in this Set
- Front
- Back
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202.1.1 State the purpose of the following T700 engine component: Cold section module
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Ingests outside air, separates foreign objects from the air and exhausts them, compresses the resulting clean air and directs it to the combustion liner.
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202.1.1 State the purpose of the following T700 engine component: Hot section module
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Contains 12 fuel injectors installed into swirlers in the liner dome. Swirlers break up and atomize the fuel from injectors into the liner. Hot gasses from stage 1 nozzle assembly are directed from the combuster to stage 1 and 2 rotors of the gas generator turbine. As exhaust gasses turn the gas generator turbine rotor, the compressor also turns. This makes the engine self sustaining.
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202.1.1 State the purpose of the following T700 engine component: Power turbine module
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Directs hot exhaust gasses leaving the gas generator section into a three stage turbine nozzle. Contains two sensors mounted on exhaust frame to monitor engine Np (Speed of power turbine) and engine torque.
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202.1.1 State the purpose of the following T700 engine component: Accessory section module
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Driven by the compressor rotor through a power take-off bevel gear and radial drive shaft assembly. Contains accessories necessary to engine operation.
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202.1.1 State the purpose of the following T700 engine component: Engine control quadrant
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Contains power levers. Permits starting, start aborting, and power control. Each lever has four positions; off, idle, fly, and ECU lock-out. Also contains fuel selector levers, two emergency-off fire extinguisher control ;levers (“T” handles), and a rotor brake interlock with override tab.
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202.1.2 State the purpose of the Auxiliary Power Unit (APU).
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Provides pneumatic power for starting engines and operating environmental control systems, and electrical power for ground and emergency in flight emergency operations.
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202.1.3 State the purpose of the tail drive shaft.
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Transmits power to the tail rotor blades through IGB and TGB. Tail gearbox converts drive shaft rotation from the pylon shaft to turn the tail rotor blades. The tail drive shaft is made up of six sections.
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202.1.4 State the purpose of the following Transmission system component: Main transmission module
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Drives and supports the main rotor. Made of modular design and has a built-in three degrees forward tilt. On SH-60F, a utility hydraulic pump is installed for sonar reeling machine and rescue hoist.
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202.1.4 State the purpose of the following Transmission system component: Input module
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Provides first gear reduction between engine and main module. Left and right side of main module and supports the front of the engines.
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202.1.4 State the purpose of the following Transmission system component: Accessory module
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Mounted on the forward section of each input module. Provides mounting for and drive for an aircraft electrical generator and a hydraulic pump. A rotor speed sensor (Nr) is mounted on the right module only. A main transmission low oil pressure sensor and heels Nr sensor are on the left module.
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202.1.4 State the purpose of the following Transmission system component: Intermediate gearbox
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Splash lubricated, transmits torque to the main gearbox. Changes the angle of drive and provides shaft speed reduction.
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202.1.4 State the purpose of the following Transmission system component: Tail gearbox
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Located on top of pylon. Transmit torque to tail rotor head. Mounts tail rotor, changes angle of drive, and provides gear reduction. Has a built-in 20° left tilt.
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202.1.5 State the purpose of the following Fuel system component: Main fuel cell
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Two cell connected by an interconnect breakaway valve. Each cell provides 2,040 lb. (300 gals) of fuel space plus expansion space for 184 lb. (27 gals). The lower 1/3 of each cell is self sealing for 7.62mm holes.
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202.1.5 State the purpose of the following Fuel system component: Auxiliary fuel tanks
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Holds 816 lb. (120 gals) of fuel. Each tank includes a fin on the aft end of the tank for aerodynamic stability. M Can be pressure/gravity fueled or defueled but fuel can only be transferred out of auxiliary tanks.
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202.1.5 State the purpose of the following Fuel system component: Helicopter In-Flight Refueling (HIFR) system
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Operation is same as pressure refueling except fuel is applied to the aircraft through the HIFR nipple and check valve located in top aft right section of cabin. Allows helicopter to hover over ships with no landing platform and pulls fuel hose up using rescue hoist.
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202.1.5 State the purpose of the following Fuel system component: Internal auxiliary fuel cell
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Holds 721.5 lb. (106.1 gals) of fuel and expansion space for 50.3 lb. (7.4 gals) of fuel. Has no provisions for gravity refueling or defueling. Includes a sampling pump on side for removing limited quantities of fuel.
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202.5.1 What safety precautions must be observed when the Engines are operating?
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Intake suction and exhaust temperatures are hazardous. Possible post shut-down fires may result from unburned fuel in engine. Never climb on aircraft when engines are turning.
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202.5.1 What safety precautions must be observed when the APU is operating?
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Keep clear of APU and ECS exhaust areas, as severe burns may result.
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