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100 Cards in this Set
- Front
- Back
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An aircraft taxiing at a steady speed can be used to demonstrate
a. Bernoulli’s principle. b. Newton’s first law of motion. c. Newton’s second law of motion. d. Newton’s third law of motion. |
b. Newton’s first law of motion.
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Which law may you sum up with two words: action and reaction?
a. Bernoulli’s principle. b. Newton’s first law of motion. c. Newton’s second law of motion. d. Newton’s third law of motion. |
d. Newton’s third law of motion.
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Which type of duct would decrease the velocity and increase the pressure of a gas as it passes
through? a. Elbow. b. Straight. c. Divergent. d. Convergent. |
c. Divergent.
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The ability to do work is the definition of
a. energy. b. inertia. c. friction. d. velocity. |
a. energy
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What does fuel for an engine represent?
a. Thrust produced. b. Efficiency ratio. c. Potential energy. d. Available horsepower. |
c. Potential energy
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The temperature of compressed air in a jet engine must be raised to
a. increase energy. b. decrease energy. c. increase volume. d. decrease volume. |
a. increase energy
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Which section of a jet engine introduces and burns fuel?
a. Turbine. b. Diffuser. c. Compressor. d. Combustion. |
d. combustion
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Which method of producing thrust does a turboprop engine use?
a. Using only the energy expended through the exhaust nozzle to propel the aircraft forward. b. Using the same working fluid for propulsive force as that used within the engine. c. Accelerating a large mass of air through a small velocity change. d. Moving a small quantity of air through a large velocity change. |
c. Accelerating a large mass of air through a small velocity change.
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Which type of horsepower is delivered to the propeller for useful work?
a. Brake. b. Indicated. c. Frictional. d. Equivalent shaft. |
a. Brake
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Which type of horsepower determines the performance of the engine-propeller
combination? a. Brake. b. Indicated. c. Frictional. d. Equivalent shaft. |
d. Equivalent shaft
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The two fluids combined to make up common jet fuel are
a. gasoline and oil. b. kerosene and oil. c. gasoline and water. d. kerosene and gasoline. |
d. kerosene and gasoline.
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Which is not a method of heat transfer?
a. Radiation. b. Convection. c. Penetration. d. Conduction. |
c. Penetration.
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The air temperature of a jet engine gradually rises across the compressor to the diffuser
outlet as a result of a. compression. b. fuel expansion. c. turbine discharge. d. ambient temperature increase. |
a. compression.
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Where is the highest point of temperature reached in an engine?
a. Tailpipe. b. Exhaust cone. c. Turbine section. d. Combustion section. |
d. Combustion section.
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Which engine component meters fuel for combustion?
a. P&D valve. b. Fuel pump. c. Fuel control. d. Fuel nozzles. |
c. Fuel control.
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What happens to the energy that is absorbed by the turbine wheel?
a. 50 percent is used for accessories. b. 60 percent is used for accessories. c. The energy operates the anti-ice system. d. The energy is returned to the compressor. |
d. The energy is returned to the compressor.
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On an average, what percent of all the energy produced by the fuel is required to maintain
the engine operating cycle? a. 50. b. 60. c. 70. d. 80. |
b. 60
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What directs the gases onto the first-stage turbine wheel blades in a jet engine?
a. Turbine wheel blades. b. Combustion chamber. c. Turbine stator. d. Flameholder. |
c. Turbine stator.
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A jet engine derives its name from its design in that it uses
a. turbo-superchargers within the engine. b. a turbine-type compressor to maintain power. c. nozzles which are called jet within the engine. d. a gas-driven turbine wheel to drive its compressor. |
d. a gas-driven turbine wheel to drive its compressor.
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Vane-type fuel pumps used in jet engines are similar to
a. sliding-vane air compressors. b. piston pump air compressors. c. roots air compressors. d. turbo-superchargers. |
a. sliding-vane air compressors.
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Which condition reduces the efficiency of a centrifugal compressor?
a. Resultant velocity. b. Tangential velocity. c. Pressure pulsations. d. Air mass leaving the impeller at great velocities. |
c. Pressure pulsations.
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Stationary vanes positioned between rotor discs in a compressor are used to
a. direct air and increase pressure. b. direct hot gases rearward. c. increase backup pressure. d. prolong compressor life. |
a. direct air and increase pressure.
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The jet engine compressor that is cheaper to manufacture is the
a. axial-flow type, because of its size. b. centrifugal type, because of its size. c. axial-flow type, because of its fewer parts. d. centrifugal type, because of its fewer parts. |
d. centrifugal type, because of its fewer parts.
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The percentage of combustion efficiency of a gas turbine is usually between
a. 60 and 70. b. 65 and 75. c. 75 and 95. d. 95 and 100. |
d. 95 and 100.
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What is the most probable cause of a flameout of a jet engine flying at 40,000 feet with a
constant engine revolutions per minute (rpm) of 50 percent? a. The rpm is too low. b. A decrease in barometric pressure. c. The failure of the breather pressurizing valve. d. Excessive ducting of air from the compressor into the combustion chamber. |
a. The rpm is too low.
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Carbon monoxide gas is poisonous and odorless, and has
a. a reddish color. b. a greenish color. c. a yellowish color. d. no color. |
d. no color.
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What is the most chemically correct ratio for burning fuel in a combustion chamber?
a. 10:1. b. 10:4. c. 15:1. d. 15:4. |
c. 15:1.
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The inner and outer surfaces of an annular-type combustion chamber are formed by
a. interlocking stainless-steel bands. b. the inner and outer diffuser case. c. a forged steel casing. d. solid sheet metal. |
a. interlocking stainless-steel bands.
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Fuel that accumulates after a failed start is
a. returned to the fuel control by tubes. b. drained overboard by a drain system. c. burned on the next start attempt. d. allowed to evaporate. |
b. drained overboard by a drain system.
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The parts on a can-annular combustion section must be removed in a specific order because
of the a. fuel nozzle. b. transition liner. c. combustion chamber outer case. d. combustion chamber crossover tubes. |
d. combustion chamber crossover tubes.
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What is the most common type of fuel nozzle system?
a. Pressure-atomizing. b. Fuel-blasting. c. Fuel ejector. d. Fuel tube. |
a. Pressure-atomizing.
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What type of flame speed are swirl-type fuel nozzles normally used to provide?
a. Low. b. High. c. Medium. d. Medium-high. |
b. High.
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What is placed in front of the rotating blades in a multiple-stage turbine engine?
a. Rotating vanes. b. Inlet guide vanes. c. Turbine rotating nozzles. d. Turbine nozzle vane assembly. |
d. Turbine nozzle vane assembly.
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The “fir tree” method of attaching turbine blades (buckets) to the turbine rotor disc is
preferred because a. of the temperature differential between the turbine rotor disc and the blades. b. it aids in preventing horizontal movement of the blades. c. there is more blade tip shake during engine operation. d. it aids in preventing axial movement of the bucket. |
a. of the temperature differential between the turbine rotor disc and the blades.
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Which method of attaching the turbine blades (buckets) to the turbine rotor disc is used
most frequently? a. Turbine blades fitted solidly into the rim of the rotor disc. b. Rivet placed in a hole through the base of the turbine blade. c. Close-fitting shroud ring around the outer perimeter of the disc. d. Series of grooves or notches broached in the rim of the turbine rotor disc. |
d. Series of grooves or notches broached in the rim of the turbine rotor disc.
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The exhaust duct connects the turbine outlet and the
a. fan duct. b. jet nozzle. c. fuel nozzle. d. bifurcated duct. |
b. jet nozzle.
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The purpose of the exhaust duct is to
a. swirl exhaust gas-flow. b. equalize exhaust gas-flow. c. straighten exhaust gas-flow. d. modulate exhaust gas-flow. |
c. straighten exhaust gas-flow.
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Which component in the augmentor creates local turbulence and reduces gas velocity?
a. Spraybars. b. Flameholder. c. Screech liner. d. Fuel manifold. |
b. Flameholder.
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How many different types of loads can be imposed on a jet engine bearing?
a. Two. b. Three. c. Four. d. Five. |
b. Three.
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Before inspecting new jet engine bearings, you should
a. separate the halves. b. perform a spin check. c. apply a preservative coating. d. remove the preservative coating. |
d. remove the preservative coating.
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The most commonly used bearing removal tools include
a. drift pipes and hammers. b. bearing pullers and hammers. c. drift pipes and arbor presses. d. arbor presses and bearing pullers. |
d. arbor presses and bearing pullers.
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Which type of defect appears on bearings as a result of bearing parts striking together?
a. Nicks. b. Galling. c. Grooves. d. Scratches. |
a. Nicks.
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Which type of defect appears on bearings as a result of small particles of foreign material
becoming lodged between the rollers? a. Pits. b. Bands. c. Grooves. d. Brinelling. |
c. Grooves.
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Which type of bearing defect results from inadequate lubrication?
a. Bands. b. Galling. c. Grooves. d. Brinelling. |
b. Galling.
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Before you install separable bearings, you must ensure the
a. rollers are serviceable. b. bearings are a matched set. c. rollers are properly positioned. d. parts are positioned and serviceable. |
b. bearings are a matched set.
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Of the following, the recommended method of expanding a bearing race before installation
is to use a a. hot-oil bath. b. coal furnace. c. hydraulic-oil bath. d. oscillating heater. |
a. hot-oil bath.
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Which component reduces the engine rotor speed to the revolutions per minute (rpm)
required for accessories? a. Step motors. b. Reduction motor. c. Reduction geartrain. d. Gear case drive assembly. |
c. Reduction geartrain.
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The reduction gearbox on an F100–PW–220 engine reduces speed between the main fuel
gear pump and the engine-driven main gearbox by a. 45 percent. b. 33 percent. c. 46 percent. d. 52 percent. |
d. 52 percent.
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To cause an accessory in a jet engine to operate at its most optimum speed, design engineers
must a. change the gear ratio. b. change the governor setting. c. install an additional set of drive gears. d. adjust the operating speed of the engine. |
a. change the gear ratio.
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On a F108 engine, which component serves as the mechanical coupling between the
compressor rotor and the transfer gearbox (TGB)? a. Power take-off (PTO) drive shaft. b. Accessory gearbox (AGB). c. Inlet gearbox (IGB). d. Radial drive shaft. |
c. Inlet gearbox (IGB).
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On the T56 turboprop engine, there are mounting pads on the aft side of the accessory drive
for the fuel control, fuel pump, and a. speed-sensitive valve. b. engine main oil pump. c. speed-sensitive control. d. external scavenge oil pump. |
d. external scavenge oil pump.
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On the T56 turboprop engine, which compressor section assembly disperses compressor
discharge air and directs it to the combustion chambers? a. Rotor. b. Diffuser. c. Housing. d. Air inlet housing. |
b. Diffuser.
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On the T56 turboprop engine, at the aft ends, what holds the combustion chambers (liners)
in place? a. Turbine inlet vane assemblies. b. Crossover tubes. c. Spark igniters. d. Fuel nozzles. |
a. Turbine inlet vane assemblies.
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When the engine is running above 23 percent revolutions per minute (rpm), the propeller
brake is held in the released position by a. release springs. b. the starter gear and helical splines. c. the outer member and accessory drive gear. d. reduction gearbox (RGB) system oil pressure. |
d. reduction gearbox (RGB) system oil pressure.
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Torque is transferred from the power unit to the safety coupling on the reduction gearbox
(RGB) by the a. torque shaft. b. reference shaft. c. torquemeter housing. d. compressor extension shaft. |
a. torque shaft.
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The purpose of the T56 safety coupling is to
a. prevent overspeed of the propeller. b. increase propeller pitch as negative torque occurs. c. maintain constant engine speed by decreasing propeller blade angle. d. disconnect the power section from the reduction gearbox (RGB) assembly. |
d. disconnect the power section from the reduction gearbox (RGB) assembly.
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For the safety coupling to disconnect the power unit from the reduction gearbox (RGB),
torque must reach between a. 4,200 and 7,200 inch pounds. b. 1,200 and 4,200 inch-pounds. c. –1,200 and –4,200 inch-pounds. d. –4,200 and –7,200 inch-pounds. |
d. –4,200 and –7,200 inch-pounds.
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The torque shaft can recouple to the reduction gearbox (RGB), if torque decreases below
approximately a. 9,000 inch pounds. b. 6,000 inch pounds. c. –6,000 inch pounds. d. –9,000 inch-pounds. |
c. –6,000 inch pounds.
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The type of bearings used to support the T56 compressor rotor at the front and rear include
the a. roller bearing on the front and ball bearing on the rear. b. ball bearing on the front and roller bearing on the rear. c. roller bearing on the front and rear. d. ball bearing on the front and rear. |
a. roller bearing on the front and ball bearing on the rear.
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The entire weight of the T56 turbine section is supported by the
a. diffuser inner casing. b. diffuser outer casing. c. combustion section outer case. d. combustion section inner casing. |
c. combustion section outer case.
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After engine shutdown, fuel that accumulates in the T56 engine combustion section is
a. allowed to evaporate. b. burned on the next start attempt. c. vented overboard by drain valves. d. returned to the fuel control by tubes. |
c. vented overboard by drain valves.
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The purpose of the turbine section is to convert
a. energy into torque. b. kinetic energy into airflow. c. airflow into potential energy. d. torque into mechanical energy. |
a. energy into torque.
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What are used to retain the turbine buckets in the first-stage wheel of the T56–A–15
engine? a. Cotter pins. b. Curvic splines. c. Cover plate seals. d. Anti-rotation pins. |
c. Cover plate seals.
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The AE2100D3 engine’s torquemeter assembly consists of the torquemeter shaft, the
reference shaft, the torquemeter housing and the a. anti-icing valve. b. magnetic pickup. c. anti-icing shroud. d. full authority electronic control (FADEC). |
c. anti-icing shroud.
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The bottom surface of the AE2100D3 air inlet housing provides the mounting pad for the
a. propeller gearbox (PGB). b. power unit accessory drive (PUAD). c. gearbox mounted accessory drive (GMAD). d. full authority digital electronic control (FADEC). |
b. power unit accessory drive (PUAD).
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The AE2100D3 power unit accessory drive (PUAD) is mounted on the bottom of the
a. forward end of gearbox mounted accessory drive (GMAD). b. forward end of the compressor air inlet housing. c. aft end of the compressor air inlet housing. d. aft end of the GMAD. |
b. forward end of the compressor air inlet housing.
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The AE2100D3 engine mount is divided into how many major structures?
a. Two. b. Three. c. Four. d. Five. |
a. Two.
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The T700 engine has a modular concept that allows for the replacement of entire
a. motors. b. systems. c. subsystems. d. components. |
c. subsystems.
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What routes oil and fuel through the T700 engine accessory gearbox (AGB)?
a. Internal lines. b. External lines. c. Internal passages. d. External passages. |
c. Internal passages.
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Which T700 engine section module receives the air for engine operation and separates
foreign particles from the air by using an inlet particle separator (IPS)? a. Hot. b. Cold. c. Accessory. d. Power turbine. |
b. Cold.
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The T700 A-sump output shaft assembly provides a mounting surface for the
a. No. 1 bearing. b. No. 3 bearing. c. No 1 and No. 2 bearings. d. No. 3 and No. 4 bearings. |
c. No 1 and No. 2 bearings.
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Which T700 engine module extracts most of the energy from the exhaust gases for output
power? a. Hot. b. Cold. c. Accessory. d. Power turbine. |
d. Power turbine.
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The T700 power turbine drive shaft assembly is made up of a
a. overspeed and Np sensor. b. drive shaft and overspeed sensor. c. torque sensor tube and Np sensor. d. drive shaft and torque sensor tube. |
d. drive shaft and torque sensor tube.
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Power to drive the accessory gearbox (AGB) on the F108 engine is transmitted from the
a. fan major module. b. accessory major module. c. core engine major module. d. low-pressure turbine (LPT) major module. |
b. accessory major module.
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F108 structural rigidity is obtained with a short length and by having only two main
structures that are called a. mainframes. b. primary frames. c. secondary frames. d. intermediate frames. |
a. mainframes.
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What percentage of the total engine thrust does the secondary airflow on the F108 engine
produce? a. 20. b. 50. c. 80. d. 100. |
c. 80
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On the F108 engine, the inlet gearbox (IGB) contains a horizontal bevel gear, a radial bevel
gear, and core engine thrust bearing a. No. 1 (ball). b. No. 2 (roller). c. No. 3 (ball). d. No. 4 (roller). |
c. No. 3 (ball).
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On the F108 engine, the purpose of the high-pressure turbine (HPT) nozzle assembly is to
accelerate the energy from the combustion gases to drive the a. fan rotor. b. HPT rotor. c. booster rotor. d. low-pressure turbine (LPT) rotor. |
b. HPT rotor.
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On the F108 engine, the low-pressure turbine (LPT) shaft assembly connects the fan shaft
with the a. high-pressure turbine (HPT) rotor. b. HPT stator. c. LPT rotor. d. LPT stator. |
c. LPT rotor.
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Which accessory is not found on the F108 accessory gearbox (AGB)?
a. Integrated drive generator. b. Augmentor pump. c. Hydraulic pump. d. Fuel pump. |
b. Augmentor pump.
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Which turbine stages on an F100–PW–220 engine drive the front compressor?
a. First and third. b. First and second. c. Second and third. d. Third and fourth. |
d. Third and fourth.
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What is one advantage of a modular engine?
a. Manpower can be increased. b. Modules can be repaired on the flight line. c. Entire engines are not withheld from service. d. There is no requirement to return modules to depot for overhaul. |
c. Entire engines are not withheld from service.
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External flanges on the F100 engine are referred to by
a. letter designations. b. number designations. c. directional references. d. accessories references. |
a. letter designations.
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On an F100–PW–220 engine, the leading edge vanes are hollow
a. to save weight. b. for better aerodynamics. c. to allow for variable movement. d. so that anti-icing air can flow through them. |
d. so that anti-icing air can flow through them.
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The F100–PW–220 core module remote splitter, which divides airflow from the front
compressor into fan airflow and primary airflow, is contained in the a. diffuser case. b. fan drive turbine. c. rear turbine case. d. compressor intermediate case. |
d. compressor intermediate case.
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On an F100–PW–220 engine, the No. 2 bearing package is housed in the
a. compressor intermediate case. b. combustion case. c. fan inlet case. d. diffuser case. |
a. compressor intermediate case.
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On an F100–PW–220 engine, which stages of compressor stator vanes are variable?
a. Second and third. b. Fourth and fifth. c. Sixth and seventh. d. Eighth and ninth. |
b. Fourth and fifth.
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On an F100–PW–220 engine, the front compressor drive turbine shaft is connected to the
front compressor rotor by a. the compressor drive shaft coupling. b. the turbine drive shaft coupling. c. eight connecting tie-rod bolts. d. six connecting tie-rod bolts. |
b. the turbine drive shaft coupling.
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Which component on an F100–PW–220 engine sends a signal to drive the primary actuator
flexible shaft? a. Stator generator. b. Unified control (UC). c. Electronic engine control (EEC). d. Convergent exhaust nozzle control (CENC). |
d. Convergent exhaust nozzle control (CENC).
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On an F100–PW–220 engine, the gearbox module is driven by the rear compressor through
a. a radial drive shaft. b. an axial drive shaft. c. a gearbox drive shaft. d. a transfer drive shaft. |
c. a gearbox drive shaft.
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How many stages are in the inlet fan module of the F119–PW–100 engine?
a. Two. b. Three. c. Four. d. Five. |
b. Three.
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Where is the No. 2 bearing located in the F119–PW–100 engine?
a. Inlet case. b. Diffuser case. c. Combustion case. d. Intermediate case. |
d. Intermediate case.
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What stage of compressor air provides anti-icing to the inlet guide vanes of the F119–PW–
100 engine? a. 5th. b. 7th. c. 9th. d. 11th. |
c. 9th.
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Where is the total temperature sensor (Tt2) located on a F119–PW–100 engine?
a. Inside the inlet nose cone at the 2:00 position. b. Inside the fan inlet guide vane case at the 5:30 position. c. In between the 1st and 2nd stages of the low pressure compressor at 6:00 position. d. In between the 2nd and 3rd stages of the low pressure compressor at 6:00 position. |
b. Inside the fan inlet guide vane case at the 5:30 position.
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Which is not a part of the core module of a F119–PW–100 engine?
a. Diffuser case. b. Intermediate case. c. Low pressure compressor. d. High pressure compressor. |
c. Low pressure compressor.
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How many stages are in the high pressure compressor of a F119–PW–100 engine?
a. 4. b. 5. c. 6. d. 7. |
c. 6
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How many fuel nozzles are mounted on the diffuser case of the F119–PW–100 engine?
a. 16. b. 20. c. 24. d. 28. |
c. 24.
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What drives the inlet fan module (IFM) in the F119–PW–100 engine?
a. Gearbox assembly. b. Core engine module. c. High-pressure turbine (HPT) assembly. d. Low-pressure turbine (LPT) module. |
d. Low-pressure turbine (LPT) module.
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On the F119–PW–100 engine, which of the following is not attached to the gearbox
assembly? a. Main fuel pump. b. Engine generator. c. Actuator fuel pump. d. Augmentor fuel control. |
d. Augmentor fuel control.
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How many fuel nozzles are in the augmentor assembly of the F119–PW–100 engine?
a. 14. b. 16. c. 18. d. 20. |
b. 16.
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