2a651 Cdc 2

1. 10. (206) To measure barometric pressure, you would use a

Potentiometer.

Psychrometer.

Pyrometer.

Barometer.

2. 3. (201) "The combination of decreased pressure above an airfoil, and the increased pressure below the airfoil produces lift" is best described by

Bernoulli’s principle.

Newton’s first law of motion

Newton’s second law of motion.

Newton’s third law of motion.

3. 6. (203) Which section of a jet engine keeps the compressor rotating?

Turbine.

Exhaust.

Diffuser.

Combustion.

4. 5. (203) Which section of a jet engine introduces and burns fuel?

Turbine.

Diffuser.

Compressor.

Combustion.

5. 25. (213) Fuel that accumulates after a failed start is

Returned to the fuel control by tubes.

Drained overboard by a drain system.

Burned on the next start attempt.

Allowed to evaporate.

6. 27. (213) What is the most common type of fuel nozzle system?

Pressure-atomizing.

Fuel-blasting.

Fuel ejector.

Fuel tube.

7. 38. (219) The bearing removal tools that are most commonly used include

Drift pipes and hammers.

Bearing pullers and hammers.

Drift pipes and arbor presses.

Arbor presses and bearing pullers.

8. 4. (202) The tendency of an object at rest to remain at rest and the tendency of an object in motion to continue its motion in a straight line at the same speed is called

Energy.

Inertia.

Friction.

Potential.

9. 11. (206) What is the sea-level atmospheric pressure at "standard day" conditions?

13.5 psi.

14.7 psi.

49.94 psi.

40.55 psi.

10. 33. (216) The purpose of the exhaust duct is to

Swirl exhaust gas-flow.

Equalize exhaust gas-flow.

Straighten exhaust gas-flow.

Modulate exhaust gas-flow.

11. 37. (218) Before inspecting new jet engine bearings, you should

Separate the halves.

Apply a preservative.

Perform a spin check.

Remove the preservative coating.

12. 42. (221) The recommended method of heating inner races of bearings before installing them is

Hot-oil bath.

Portable heater.

Bearing furnace.

Hydraulic oil bath.

13. 43. (222) Which component reduces the engine rotor speed to the rpm required for accessories?

Step motors.

Reduction motor.

Reduction geartrain.

Gear case drive assembly.

14. 15. (208) When two or more turbine wheels are used in a jet engine, which component is placed directly in front of each turbine wheel

Diffuser.

Jet nozzle.

Combustion chamber.

Turbine stator (nozzle diaphragm).

15. 21. (211) Stationary vanes positioned between rotor discs in a compressor are used to

Direct air and increase pressure.

Direct hot gases rearward.

Increase backup pressure.

Prolong compressor life.

16. 34. (217) The purpose of an augmentor (afterburner) in a jet engine is to

Increase engine rpm.

Reduce pressure drop.

Augment basic engine thrust.

Increase EGT.

17. 44. (223) On an F108 engine, the radial drive shaft connects the core engine to the

Hydraulic actuator motor.

Accessory drive assembly.

Variable bleed valves.

Fan booster rotor.

18. 47. (224) On the T56 turboprop engine, what is the overall reduction ratio of the RGB's main reduction gear train?

.3125 to 1.

4.333 to 1.

13.54 to 1.

13,820 to 1.

19. 2. (201) Which type of duct would decrease the velocity and increase the pressure of a gas as it passes through?

Elbow.

Straight.

Divergent.

Convergent.

20. 13. (207) Which engine component meters fuel for combustion?

P&D valve.

Fuel pump.

Fuel control.

Fuel nozzles.

21. 14. (208) What directs the gases onto the first-stage turbine wheel blades in a jet engine?

Flameholder.

Combustion chamber.

Turbine wheel blades.

Turbine stator.

22. 26. (213) The parts on a can-annular combustion section must be removed in a specific order because of the

Fuel nozzle.

Transition liner.

Combustion chamber outer case.

Combustion chamber crossover tubes.

23. 28. (213) Swirl-type fuel nozzles usually are used to provide what type of flame speed?

Low.

High.

Medium.

Medium-high.

24. 51. (225) What is the total gear reduction ratio of the RGB?

3.125:1.

4.333:1.

12.85:1.

13.54:1.

25. 16. (209) The three major sections of all jet engines are compressor, combustion, and

Turbo.

Turbine.

Exhaust.

Diffuser.

26. 24. (213) The excess airflow that is not burned in the combustion section is used to

Cool the burner surfaces.

Operate pneumatic accessories.

Decrease the mass of exhaust gases.

Increase air in the compressor section.

27. 36. (218) When you handle jet engine bearings, you must change cotton gloves frequently because they

Wear faster.

Attract dirt.

Cause oxidation.

Get soaked with sweat.

28. 7. (204) Which method of producing thrust does a turboprop engine use?

Accelerating a large mass of air by a small amount.

Moving a small quantity of air through a large velocity change.

Using the same working fluid for propulsive force as that used within the engine.

Using only the energy expended through the exhaust nozzle to propel the aircraft forward.

29. 8. (204) Which type of horsepower is delivered to the propeller for useful work?

Brake.

Indicated.

Frictional.

Equivalent shaft.

30. 12. (206) What effect does the divergent design of a diffuser have on air pressure?

Increases pressure.

Decreases pressure.

Has no effect on pressure.

Results in pressure fluctuations.

31. 17. (209) Vane-type fuel pumps used in jet engines are similar to

Sliding-vane air compressors.

Piston pump air compressors.

Roots air compressors.

Turbo-superchargers.

32. 18. (210) The two forces that air is subjected to after it is drawn into the guide vanes of a centrifugal compressor are

Rotational and centrifugal.

Rotational and tangential.

Tangential and centrifugal.

Tangential and radial.

33. 40. (220) Which type of defect appears on bearings as a result of small particles of foreign material becoming lodged between the rollers?

Pits.

Bands.

Grooves.

Brinelling.

34. 9. (205) The heat content per pound of kerosene is how many Btu's?

10,500.

15,000.

18,500.

40,000.

35. 39. (220) Which type of defect appears on bearings as a result of bearing parts striking together?

Nicks.

Galling.

Grooves.

Scratches.

36. 29. (214) Three types of turbine and vane assemblies used in jet engines are impulse, reaction, and

Fir tree.

Shrouded.

Reaction-impulse.

37. 31. (215) Why is the "fir tree" method of attaching turbine blades (buckets) to the turbine rotor disc preferred?

There is a significant temperature differential between the turbine rotor disc and the blades.

This method aids in preventing horizontal movement of the blades.

This method aids in preventing axial movement of the bucket.

There is more blade tip shake during engine operation.

38. 81. (238) On the F108 engine, the LPT shaft assembly connects the fan shaft with the

LPT rotor.

HPT rotor.

LPT stator.

HPT stator.

39. 19. (210) A constructional feature of the centrifugal compressor is that the impeller

Has two matching plates.

Has a lightweight design.

Is forged as a single unit.

Is constructed in rows of blades and stators.

40. 23. (212) Which facet of engine design helps prevent igniter plug fouling?

Gold plating on the plug.

Split electrode on the plug.

Ceramic coating on the plug.

Directing air around the plug.

41. 60. (230) The stationary (stator) vane blades on the T56 compressor are used to

Increase velocity.

Increase pressure.

Decrease pressure.

Prolong compressor life.

42. 72. (234) What routes oil and fuel through the T700 engine AGB?

Internal lines.

External lines.

Internal passages.

External passages.

43. 77. (235) Primary airflow in the F108 engine is through all of the following components except the

Booster.

Core engine.

Accessory gearbox.

Low-pressure turbine.

44. 45. (224) The major sections of a turboprop engine are the power unit, torquemeter assembly, and 45. (224) The major sections of a turboprop engine are the power unit, torquemeter assembly, and

Turbine assembly.

Compressor assembly.

Combustion assembly.

RGB assembly.

45. 41. (220) Excessive bearing wear can usually be detected by

Pits.

Bands.

Misalignment.

Roughness of the metal.

46. 49. (224) On the T56 turboprop engine, which compressor section assembly disperses compressor discharge air and directs it to the combustion chambers?

Diffuser.

Compressor rotor.

Compressor housing.

Compressor air inlet housing.

47. 1. (201) "An unbalanced force on a body produces or tends to produce an acceleration in the direction of the force and that the acceleration, if any, is directly proportional to the force and inversely proportional to the mass of the body." This statement is

Bernoulli’s principle.

Newton’s first law of motion.

Newton’s second law of motion.

Newton’s third law of motion.

48. 35. (218) How many different types of loads can be imposed on a jet engine bearing?

Two.

Three.

Four.

Five.

49. 59. (229) For the safety coupling to disconnect the power unit from the RGB, torque must reach between

4,200 and 7,200 inch pounds.

1,200 and 4,200 inch-pounds.

–1,200 and –4,200 inch-pounds.

–4,200 and –7,200 inch-pounds.

50. 54. (227) Which valve in the propeller control assembly is actuated by the NTS actuator rod to increase propeller blade angle?

Pilot.

Feather.

Beta backup.

Alpha backup.

51. 79. (236) What percentage of the total engine thrust does the secondary airflow on the F108 engine produce?

20.

50.

80.

100.

52. 57. (228) The torquemeter exciter wheels are in phase when

The shaft power output is transmitted from the power unit.

Negative or positive torque is transmitted to the torque indicator.

The rectangular teeth on the exciter wheels are aligned at zero torque.

There is a change in the torque transmitted to the torque shaft exciter wheel.

53. 66. (233) The AE2100D3 power plant major assemblies are the PGB, torquemeter assembly, power section, accessory drives, and the

Nacelle structure.

Hydraulic pump.

Electrical generator.

Tailpipe assembly.

54. 30. (214) What is placed in front of the rotating blades in an engine turbine section?

Rotating vanes.

Inlet guide vanes.

Turbine rotating nozzles.

Turbine nozzle vane assembly.

55. 53. (226) The propeller brake is in which position when the aircraft is on the ground and the engine is stopped?

Locked.

Applied.

Engaged.

Released.

56. 61. (230) What type of bearings support the T56 compressor rotor at the front and rear?

Front, roller; rear, roller.

Front, roller; rear, ball.

Front, ball; rear, roller.

Front, ball; rear, ball.

57. 74. (234) The T700 gas generator turbine rotor drives the

Compressor and turbine stators.

Compressor and AGB.

AGB and combustion.

AGB and turbine stators.

58. 86. (242) When blending fourth stage compressor blades on an F100–PW–220 engine, a maximum of how many blends are allowed on any single edge?

Two.

Three.

Four.

None.

59. 93. (247) Where is the Tt2 located on a F119–PW–100 engine?

Inside the inlet nose cone at the 2:00 position.

In the fan inlet guide vane case at the 5:30 position.

In between the 1st and 2nd stages of the low pressure compressor at 6:00 position.

In between the 2nd and 3rd stages of the low pressure compressor at 6:00 position.

60. 20. (210) The forward end of the shaft on a centrifugal compressor is hollow in order to

Act as a vibration damper.

Allow cooling air to the turbine.

Provide a passage for lubricating oil.

Provide a passage for the main fuel supply.

61. 46. (224) On the T56 turboprop engine, how many stages of reduction are in the RGB's main reduction gear train?

1.

2.

3.

4.

62. 48. (224) On the T56 turboprop engine, there are mounting pads on the aft side of the accessory drive for the fuel control, fuel pump, and

Speed-sensitive valve.

Engine main oil pump.

Speed-sensitive control.

External scavenge oil pump.

63. 56. (228) The amount of twisting deflection is determined by the

Torque shaft.

Reference shaft.

Safety coupling.

Pinion input gear.

64. 65. (232) What are used to retain the turbine buckets in the first-stage wheel of the T56–A–15 engine?

Cotter pins.

Curvic splines.

Cover plate seals.

Anti-rotation pins.

65. 83. (240) On which module of an F100–PW–220 engine is the stator generator mounted?

Core.

Inlet fan.

Gearbox.

Augmenter

66. 99. (249) On the F119–PW–100 engine, which of the following is not attached to the gearbox assembly?

Actuator fuel pump.

Main fuel pump.

Augmentor fuel control.

Engine generator.

67. 58. (229) The purpose of the T56 safety coupling is to

Prevent overspeed of the propeller.

Increase propeller pitch as negative torque occurs.

Maintain constant engine speed by decreasing propeller blade angle.

Disconnect the power section from the RGB assembly.

68. 71. (234) The T700 engine consists of what four modules?

Combustion, compressor, hot, and accessory sections.

Power turbine, accessory, compressor, and hot sections.

Compressor, combustion, cold, and power turbine section.

Accessory, compressor, combustion, and power turbine section.

69. 80. (237) On the F108 engine, the purpose of the HPT nozzle assembly is to accelerate the energy from the combustion gases to drive the

HPT rotor.

LPT rotor.

Booster rotor.

Fan rotor.

70. 55. (228) Which components comprise the torquemeter assembly?

Torque shaft, torquemeter housing, and front coupling assembly.

Two concentric shafts, torquemeter housing, and torquemeter pickup.

Torquemeter housing, bearing lock tube, and front coupling assembly.

Two outer shafts, torquemeter pickup assembly, and torquemeter backup assembly.

71. 50. (225) In the T56 engine, which RGB component rotates at the same speed as the power unit rotors?

Sun gear.

Ring gear.

Main drive gear.

Pinion input gear.

72. 84. (240) External flanges on the F100 engine are referred to by

Letter designations.

Number designations.

Directional references.

Accessories references.

73. 68. (233) What type of compressor rotor assembly is used on the AE2100D3 engine?

14 stage axial-flow.

14 stage centrifugal-flow.

16 stage axial-flow.

16 stage centrifugal-flow.

74. 22. (211) In a dual-spool compressor, rpm of the N2 compressor are determined by the

Starter.

Fuel pump.

Fuel control.

Low-pressure turbine.

75. 32. (216) The exhaust duct connects the turbine outlet and the

Fan duct.

Jet nozzle.

Bifurcated duct.

76. 85. (241) On an F100–PW–220 engine, the No. 1 bearing assembly is located in the

Diffuser case.

Rear fan duct.

Intermediate case.

Front compressor stator inlet shroud.

77. 52. (226) What is not a propeller brake positions?

Locked.

Applied.

Engaged.

Released.

78. 63. (231) In the T56 engine, turbine rotor torque is transferred to the compressor rotor by the

Turbine coupling shaft.

Torquemeter outer shaft.

Compressor extension shaft.

Turbine to compressor tie bolt.

79. 82. (239) On the F108 engine, what connects the IGB to the TGB bevel gears?

Radial drive shaft.

Vertical drive shaft.

Horizontal drive shaft.

Power take-off drive shaft.

80. 96. (248) On an F119–PW–100 engine, what function does the diffuser case serve other than housing the combustor?

Increases the velocity of compressor discharge air.

Reduces the velocity of compressor discharge air.

Increases the velocity turbine discharge air.

Reduces the velocity of turbine discharge air.

81. 64. (232) The purpose of the guide vane support is to direct airflow

Out of the turbine section.

Into the combustion section.

Onto the turbine rotor blades.

Toward the compressor stator blades.

82. 76. (235) Which F108 major engine module provides for mounting of the front of the engine to the airframe?

Fan major module.

Accessory major module.

Core engine major module.

LPT major module.

83. 95. (248) Which bearing compartment is contained in the intermediate case of the F119–PW–100 engine?

No. 1 and No. 2 bearing.

No. 2 and No. 3 bearing.

No. 3 and No. 4 bearing.

No. 4 and No. 5 bearing.

84. 69. (233) What AE2100D3 nacelle access door contains a fire access door?

Lower right turbine access door.

Lower left turbine access door.

Upper right turbine access door.

Upper left turbine access door.

85. 78. (235) The F108 engine can be broken down into how many individual modules?

5.

7.

10.

17.

86. 92. (247) How many hollow struts/inlet guide vanes are contained in the inlet fan case of the F119 engine?

15.

18.

21.

23.

87. 67. (233) On the AE2100D3, the forward engine mounts are located on the

Air inlet housing.

Diffuser assembly.

Sides of the PGB.

Aft side of the PGB.

88. 75. (234) The T700 power turbine drive shaft assembly is made up of what two components?

Overspeed and Np sensor.

Drive shaft and overspeed sensor.

Torque sensor tube and Np sensor.

Drive shaft and torque sensor tube.

89. 62. (230) Which T56 compressor component supports the compressor rear bearing labyrinth seal?

Compressor rotor.

Air inlet housing.

Compressor diffuser.

First-stage compressor wheel hub.

90. 100. (250) What is the nozzle module mounted to on the F119–PW–100 engine?

Core module.

LPT module.

HPT assembly.

Augmentor assembly.

91. 70. (233) The AE2100D3 engine mount is divided into how many major structures?

Two

Three.

Four.

Five.

92. 98. (249) Which bearing is located in the LPT of the F119–PW–100 engine?

No. 2 bearing.

No. 3 bearing.

No. 4 bearing.

No. 5 bearing.

93. 91. (246) How many stages are in the inlet fan module of the F119–PW–100 engine?

Two.

Three.

Four.

Five.

94. 94. (248) Which is not a part of the core module of a F119–PW–100 engine?

Diffuser case.

Intermediate case.

Low pressure compressor.

High pressure compressor.

95. 89. (244) Major components of the F100–PW–220 engine augmentor duct and nozzle module are nozzle actuators, nozzle assembly, and

Spray bars.

Flameholder.

Combustion chamber control.

Combustion chamber liner and duct.

96. 73. (234) What components mount on the front face of the AGB on the T700 engine?

Alternator and oil cooler.

Scavenge pump and oil cooler.

Alternator and fuel boost pump.

Scavenge pump and fuel boost pump.

97. 87. (243) On an F100–PW–220 engine, the front compressor drive turbine shaft is connected to the front compressor rotor by

The compressor drive shaft coupling.

The turbine drive shaft coupling.

Eight connecting tie-rod bolts.

Six connecting tie-rod bolts.

98. 88. (243) Which bearing is located in the fan drive turbine module on an F100–PW–220 engine?

No. 1

No. 3

No. 4

No. 5

99. 90. (245) On an F100–PW–220 engine, the gearbox module is driven by the rear compressor through

A transfer drive shaft.

A gearbox drive shaft.

A radial drive shaft.

An axial drive shaft.

100. 97. (249) What drives the IFM in the F119–PW–100 engine?

Gearbox assembly.

HPT assembly.

LPT module.

Core engine module.

2A651 CDC 2

1. 10. (206) To measure barometric pressure, you would use a

2.

What first name or nickname would you like us to use?

2. 3. (201) "The combination of decreased pressure above an airfoil, and the increased pressure below the airfoil produces lift" is best described by

3. 6. (203) Which section of a jet engine keeps the compressor rotating?

4. 5. (203) Which section of a jet engine introduces and burns fuel?

5. 25. (213) Fuel that accumulates after a failed start is

6. 27. (213) What is the most common type of fuel nozzle system?

7. 38. (219) The bearing removal tools that are most commonly used include

8. 4. (202) The tendency of an object at rest to remain at rest and the tendency of an object in motion to continue its motion in a straight line at the same speed is called

9. 11. (206) What is the sea-level atmospheric pressure at "standard day" conditions?

10. 33. (216) The purpose of the exhaust duct is to

11. 37. (218) Before inspecting new jet engine bearings, you should

12. 42. (221) The recommended method of heating inner races of bearings before installing them is

13. 43. (222) Which component reduces the engine rotor speed to the rpm required for accessories?

14. 15. (208) When two or more turbine wheels are used in a jet engine, which component is placed directly in front of each turbine wheel

15. 21. (211) Stationary vanes positioned between rotor discs in a compressor are used to

16. 34. (217) The purpose of an augmentor (afterburner) in a jet engine is to

17. 44. (223) On an F108 engine, the radial drive shaft connects the core engine to the

18. 47. (224) On the T56 turboprop engine, what is the overall reduction ratio of the RGB's main reduction gear train?

19. 2. (201) Which type of duct would decrease the velocity and increase the pressure of a gas as it passes through?

20. 13. (207) Which engine component meters fuel for combustion?

21. 14. (208) What directs the gases onto the first-stage turbine wheel blades in a jet engine?

22. 26. (213) The parts on a can-annular combustion section must be removed in a specific order because of the

23. 28. (213) Swirl-type fuel nozzles usually are used to provide what type of flame speed?

24. 51. (225) What is the total gear reduction ratio of the RGB?

25. 16. (209) The three major sections of all jet engines are compressor, combustion, and

26. 24. (213) The excess airflow that is not burned in the combustion section is used to

27. 36. (218) When you handle jet engine bearings, you must change cotton gloves frequently because they

28. 7. (204) Which method of producing thrust does a turboprop engine use?

29. 8. (204) Which type of horsepower is delivered to the propeller for useful work?

30. 12. (206) What effect does the divergent design of a diffuser have on air pressure?

31. 17. (209) Vane-type fuel pumps used in jet engines are similar to

32. 18. (210) The two forces that air is subjected to after it is drawn into the guide vanes of a centrifugal compressor are

33. 40. (220) Which type of defect appears on bearings as a result of small particles of foreign material becoming lodged between the rollers?

34. 9. (205) The heat content per pound of kerosene is how many Btu's?

35. 39. (220) Which type of defect appears on bearings as a result of bearing parts striking together?

36. 29. (214) Three types of turbine and vane assemblies used in jet engines are impulse, reaction, and

37. 31. (215) Why is the "fir tree" method of attaching turbine blades (buckets) to the turbine rotor disc preferred?

38. 81. (238) On the F108 engine, the LPT shaft assembly connects the fan shaft with the

39. 19. (210) A constructional feature of the centrifugal compressor is that the impeller

40. 23. (212) Which facet of engine design helps prevent igniter plug fouling?

41. 60. (230) The stationary (stator) vane blades on the T56 compressor are used to

42. 72. (234) What routes oil and fuel through the T700 engine AGB?

43. 77. (235) Primary airflow in the F108 engine is through all of the following components except the

44. 45. (224) The major sections of a turboprop engine are the power unit, torquemeter assembly, and 45. (224) The major sections of a turboprop engine are the power unit, torquemeter assembly, and

45. 41. (220) Excessive bearing wear can usually be detected by

46. 49. (224) On the T56 turboprop engine, which compressor section assembly disperses compressor discharge air and directs it to the combustion chambers?

47. 1. (201) "An unbalanced force on a body produces or tends to produce an acceleration in the direction of the force and that the acceleration, if any, is directly proportional to the force and inversely proportional to the mass of the body." This statement is

48. 35. (218) How many different types of loads can be imposed on a jet engine bearing?

49. 59. (229) For the safety coupling to disconnect the power unit from the RGB, torque must reach between

50. 54. (227) Which valve in the propeller control assembly is actuated by the NTS actuator rod to increase propeller blade angle?

51. 79. (236) What percentage of the total engine thrust does the secondary airflow on the F108 engine produce?

52. 57. (228) The torquemeter exciter wheels are in phase when

53. 66. (233) The AE2100D3 power plant major assemblies are the PGB, torquemeter assembly, power section, accessory drives, and the

54. 30. (214) What is placed in front of the rotating blades in an engine turbine section?

55. 53. (226) The propeller brake is in which position when the aircraft is on the ground and the engine is stopped?

56. 61. (230) What type of bearings support the T56 compressor rotor at the front and rear?

57. 74. (234) The T700 gas generator turbine rotor drives the

58. 86. (242) When blending fourth stage compressor blades on an F100–PW–220 engine, a maximum of how many blends are allowed on any single edge?

59. 93. (247) Where is the Tt2 located on a F119–PW–100 engine?

60. 20. (210) The forward end of the shaft on a centrifugal compressor is hollow in order to

61. 46. (224) On the T56 turboprop engine, how many stages of reduction are in the RGB's main reduction gear train?

62. 48. (224) On the T56 turboprop engine, there are mounting pads on the aft side of the accessory drive for the fuel control, fuel pump, and

63. 56. (228) The amount of twisting deflection is determined by the

64. 65. (232) What are used to retain the turbine buckets in the first-stage wheel of the T56–A–15 engine?

65. 83. (240) On which module of an F100–PW–220 engine is the stator generator mounted?

66. 99. (249) On the F119–PW–100 engine, which of the following is not attached to the gearbox assembly?

67. 58. (229) The purpose of the T56 safety coupling is to

68. 71. (234) The T700 engine consists of what four modules?

69. 80. (237) On the F108 engine, the purpose of the HPT nozzle assembly is to accelerate the energy from the combustion gases to drive the

70. 55. (228) Which components comprise the torquemeter assembly?

71. 50. (225) In the T56 engine, which RGB component rotates at the same speed as the power unit rotors?

72. 84. (240) External flanges on the F100 engine are referred to by

73. 68. (233) What type of compressor rotor assembly is used on the AE2100D3 engine?

74. 22. (211) In a dual-spool compressor, rpm of the N2 compressor are determined by the

75. 32. (216) The exhaust duct connects the turbine outlet and the

76. 85. (241) On an F100–PW–220 engine, the No. 1 bearing assembly is located in the

77. 52. (226) What is not a propeller brake positions?