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87 Cards in this Set
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1. (201) “An unbalanced force on a body produces or tends to produce 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 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. |
c. Newton’s second law of motion.
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2. (201) 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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3. (202) 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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4. (203) Which section of a jet engine continually supplies air and maintains pressure? a. Turbine. b. Diffuser. c. Compressor. d. Combustion. |
c. Compressor.
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5. (203) Which section of a jet engine introduces and burns fuel? a. Turbine. b. Diffuser. c. Compressor. d. Combustion. |
d. Combustion. |
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6. (203) Which section of a jet engine keeps the compressor rotating? a. Turbine. b. Exhaust. c. Diffuser. d. Combustion. |
a. Turbine.
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7. (203) Through which section of a jet engine is energy expended into the atmosphere, resulting in thrust? a. Turbine. b. Exhaust. c. Diffuser. d. Combustion. |
b. Exhaust.
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8. (204) How many British thermal units (Btu) does the heat content per pound of kerosene produce? a. 10,500. b. 15,000. c. 18,500. d. 40,000. |
c. 18,500.
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9. (205) To measure barometric pressure, you would use a a. potentiometer. b. psychrometer. c. pyrometer. d. barometer. |
d. barometer. |
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10. (205) What is the sea-level atmospheric pressure in pounds per square inch (psi) at “standard day” conditions? a. 13.5 psi. b. 14.7 psi. c. 49.94 psi. d. 40.55 psi. |
b. 14.7 psi.
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11. (205) What effect does moisture content or humidity have on density of air in a jet engine? a. More moisture, less dense. b. More moisture, more dense. c. Less moisture, less dense. d. None. |
a. More moisture, less dense.
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12. (205) What effect does the divergent design of a diffuser have on air pressure in a jet engine? a. Increases pressure. b. Decreases pressure. c. Has no effect on pressure. d. Results in pressure fluctuations. |
a. Increases pressure.
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13. (205) 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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14. (205) Where is the highest point of temperature reached in a jet engine? a. Tailpipe. b. Exhaust cone. c. Turbine section. d. Combustion section. |
d. Combustion section.
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15. (206) Which jet 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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16. (207) What is the required velocity for air and gases flowing through a jet engine? a. Low velocity at all times. b. Less velocity exiting than entering. c. Equal velocity entering and exiting. d. Greater velocity exiting than entering |
d. Greater velocity exiting than entering |
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17. (207) What is the general flow of gases from the combustion chamber of the jet engine? a. At right angles to the rotor shaft. b. Parallel to the axis of the rotor shaft. c. At the same velocity as the rotor shaft. d. In a reverse direction from the rotor shaft. |
b. Parallel to the axis of the rotor shaft.
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18. (207) What directs the gases onto the first-stage turbine wheel blades in a jet engine? a. Compressor stator vanes. b. Combustion chamber. c. Turbine stator. d. Flameholder. |
c. Turbine stator.
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19. (207) When two or more turbine wheels are used in a jet engine, which component is placed directly in front of each turbine wheel? a. Diffuser. b. Jet nozzle. c. Combustion chamber. d. Turbine stator (nozzle diaphragm). |
d. Turbine stator (nozzle diaphragm).
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20. (208) The operation of any gas turbine engine, regardless of type, requires the provisions to be made for three major functions. What are they? a. Compression of air, expansion of air by burning fuel, and extraction of power from gases for driving the compressor and engine driven accessories. b. Expansion of air, burning of fuel, and burning of gases to power the N1 compressor. c. Expansion of gases, burning the air, and power off of the N1 compressor. d. Compression of gases, burning of air, and burning of fuel. |
a. Compression of air, expansion of air by burning fuel, and extraction of power from gases for driving the compressor and engine driven accessories
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21. (208) The three major sections of all jet engines are compressor, combustion, and a. turbo. b. turbine. c. exhaust. d. diffuser. |
b. turbine.
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22. (208) 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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23. (209) 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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24. (209) A constructional feature of the centrifugal compressor is that the impeller a. has two matching plates. b. is forged as a single unit. c. has a lightweight design. d. is constructed in rows of blades and stators. |
b. is forged as a single unit.
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25. (210) In a dual-spool compressor, revolutions per minute (rpm) of the N2 compressor are determined by the a. starter. b. fuel pump. c. fuel control. d. low-pressure turbine. |
c. fuel control.
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26. (210) 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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27. (210) Which is a constructional feature of an axial-flow compressor casing? a. Split horizontal centerline. b. Solid casting mount lines. c. Access maintenance ports. d. Accessory and oil pump mount pads. |
a. Split horizontal centerline.
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28. (211) 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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29. (211) Which facet of jet engine design helps prevent igniter plug fouling? a. Gold plating on the plug. b. Split electrode on the plug. c. Ceramic coating on the plug. d. Directing air around the plug. |
d. Directing air around the plug
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30. (211) 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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31. (212) What is the most chemically correct ratio for burning fuel in a combustion chamber of a jet engine? a. 10:1. b. 10:4. c. 15:1. d. 15:4. |
c. 15:1.
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32. (212) The excess airflow that is not burned in the combustion section of the jet engine is used to a. cool the burner surfaces. b. operate pneumatic accessories. c. decrease the mass of exhaust gases. d. increase air in the compressor section |
a. cool the burner surfaces.
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33. (212) 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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34. (212) Fuel that accumulates after a failed engine 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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35. (212) 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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36. (212) 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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37. (213) Three types of turbine and vane assemblies used in jet engines are impulse, reaction, and a. fir tree. b. shrouded. c. unshrouded. d. reaction-impulse. |
d. reaction-impulse. |
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38. (213) In the reaction type turbine, what in the design causes the rotor to turn? a. The increase in pressure and the reduction in velocity of the exhaust gases occur in the passage between the blades. b. The increase in pressure and the increase in velocity of the exhaust gases occur in the passage between the rotor blades. c. The reduction in pressure and the increase in velocity of the exhaust gases occur in the passage between the rotor blades. d. The reduction in pressure and the reduction in velocity of the exhaust gasses in the passage between the rotor blades. |
c. The reduction in pressure and the increase in velocity of the exhaust gases occur in the passage between the rotor blades.
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39. (214) 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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40. (214) 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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41. (215) 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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42. (215) The design of an exhaust duct straightens the exhaust gases as it leaves the last stage of the turbine section to provide for a. larger total thrust in a more efficient manner. b. larger total thrust in a less efficient manner. c. reduced total thrust in a more efficient manner. d. reduced total thrust in a less efficient manner. |
a. larger total thrust in a more efficient manner.
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43. (216) The rear opening of the exhaust duct on the jet engine is referred to as the a. turbine. b. compressor. c. exhaust case. d. exhaust nozzle. |
d. exhaust nozzle. |
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44. (216) Some jet engines are trimmed/adjusted to their correct exhaust gas temperature by an alteration of what? a. Low-pressure turbine (LPT). b. Turbine exhaust case. c. Exhaust nozzle area. d. Compressor. |
c. Exhaust nozzle area.
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45. (217) 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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46. (217) 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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47. (218) Next to contamination and improper lubrication, what is the greatest enemy of antifriction bearings? a. Heat. b. Dirt. c. Improper removal. d. Using wrong type of oil. |
c. Improper removal.
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48. (218) 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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49. (219) 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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50. (219) Which type of bearing defect results from inadequate lubrication? a. Bands. b. Galling. c. Grooves. d. Brinelling. |
b. Galling.
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51. (219) Excessive bearing wear can usually be detected by a. pits. b. bands. c. misalignment. d. roughness of the metal. |
d. roughness of the metal. |
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52. (220) Before you install separable bearings in a jet engine, you must make sure 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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53. (221) 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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54. (221) On an F108 engine, the radial drive shaft connects the core engine to the a. hydraulic actuator motor. b. accessory drive assembly. c. variable bleed valves. d. fan booster rotor. |
b. accessory drive assembly.
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55. (222) Which F108 major engine module provides for mounting of the front of the engine to the airframe? a. Fan major module. b. Accessory major module. c. Core engine major module. d. Low-pressure turbine (LPT) major module. |
a. Fan major module.
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56. (222) 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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57. (222) 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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58. (222) Primary airflow in the F108 engine is through all of the following components except the a. booster. b. core engine. c. accessory gearbox. d. low-pressure turbine. |
c. accessory gearbox.
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59. (223) Which types of load does the No. 2 bearing take up in the F108 engine? a. Axial. b. Radial. c. Tangential. d. Radial and axial. |
b. Radial.
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60. (224) The F108 engine has an air duct through the inside diameter of the core compressor rotor that forms a flow path for a. secondary and pressurizing airflow. b. pressurizing and cooling airflow. c. primary and secondary airflow. d. primary and cooling airflow. |
b. pressurizing and cooling airflow.
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61. (224) On the F108 engine, the combustion chamber is of which design type? a. Can-annular. b. Annular. c. Dome. d. Can. |
b. Annular.
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62. (225) 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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63. (225) On the F108 engine, as gases flow through the convergent passageways of the low-pressure turbine (LPT) nozzle their pressure drops, and their axial velocity a. increases. b. decreases. c. first increases, then decreases. d. neither increases nor decreases. |
a. increases.
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64. (225) The F108 engine turbine frame is the engine rear main structural component, and it supports the a. high-pressure turbine (HPT) rotor front section. b. low-pressure turbine (LPT) rotor front section. c. HPT rotor rear section. d. LPT rotor rear section. |
d. LPT rotor rear section. |
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65. (226) On the F108 engine, what connects the inlet gearbox (IGB) to the transfer gearbox (TGB) bevel gears? a. Radial drive shaft. b. Vertical drive shaft. c. Horizontal drive shaft. d. Power take-off drive shaft. |
a. Radial drive shaft.
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66. (226) On the F108 engine, how is the transfer gearbox (TGB) is mounted to the fan case? a. By a single clevis-and-link rod-mounting arrangement. b. With four studs with washers and nuts. c. With three “dog bone” mount links. d. By a V-band coupling. |
a. By a single clevis-and-link rod-mounting arrangement.
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67. (227) On the TF34 jet engine, the fan forward shaft, bolted to the aft side of the double disc, is supported by a. the No. 1 thrust ball bearing. b. the No. 2 roller bearing. c. the No. 1 roller bearing. d. both the No. 1 thrust ball bearing and the No. 2 roller bearing. |
d. both the No. 1 thrust ball bearing and the No. 2 roller bearing. |
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68. (227) The single-stage fan rotor on the TF34 jet engine provides what percentage of the engines thrust? a. 65 percent. b. 75 percent. c. 85 percent. d. 95 percent. |
c. 85 percent
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69. (228) On the TF34 jet engine ,which strut does the fan speed pickup protrude through to the number two bearing locknut? a. 3 o’clock. b. 5 o’clock. c. 9 o’clock. d. 11 o’clock. |
c. 9 o’clock.
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70. (228) The compressor inlet temperature sensor is mounted on the outer surface of the splitter nose at what “o’clock” position on the TF34 jet engine? a. 5 o’clock. b. 9 o’clock. c. 10 o’clock. d. 12 o’clock. |
b. 9 o’clock.
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71. (229) How many stages of compressor blades are in the TF34 engine? a. 10. b. 14. c. 18. d. 22. |
b. 14.
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72. (229) Why is the compressor stator case split horizontally? a. For ease of access to borescope ports. b. To allow access to the compressor rotor. c. To allow access to the low pressure turbine. d. To allow access to the high pressure turbine. |
b. To allow access to the compressor rotor.
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73. (229) What stages of compressor vanes are variable in the TF34 engine? a. Stages 1−5. b. Stages 1−6. c. Stages 1−10. d. Stages 1−14. |
a. Stages 1−5.
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74. (230) What type of combustion liner does the TF34 have? a. Circumferential. b. Can annular. c. Annular. d. Circular. |
c. Annular.
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75. (231) On the TF34 jet engine, the first-stage nozzle consists of 24 cast segments with how many vanes in each segment? a. 4. b. 2. c. 1. d. 0. |
b. 2.
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76. (231) What is purpose of the low-pressure turbine (LPT) transition assembly? a. To funnel cool air from the high-pressure turbine (HPT) rotor to the larger diameter LPT rotor. b. To funnel hot air from the combustion chamber to the larger diameter LPT rotor. c. To funnel hot gases from the HPT rotor to the larger diameter LPT rotor. d. To funnel hot gasses from the HPT rotor to the smaller diameter LPT rotor |
c. To funnel hot gases from the HPT rotor to the larger diameter LPT rotor.
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77. (232) On the TF34 jet engine, which strut is used to port seventh stage compressor air into the C-sump area to pressurize the number six carbon seal? a. 3 o’clock. b. 6 o’clock. c. 9 o’clock. d. 12 o’clock. |
d. 12 o’clock. |
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78.(233) Which of these items does not belong to the TF34engine accessories section? a.Power take-off (PTO) assembly. b.Compressor stator. c.Radial drive shaft. d.Accessory gearbox (AGB) and the engine and airframe accessories. |
b.Compressor stator.
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79.(233) In order to facilitate borescoping the engine, what is provided for rotating the high-pressurerotor system and where is it located? a.A gearbox cranking pad located between the lube and hydraulic pump pads. b.A gearbox cranking pad located between the lube and fuel pump pads. c.Borescope viewing ports located in various locations on the engine. d.A compressor rotor located between the fan and turbine. |
b.A gearbox cranking pad located between the lube and fuel pump pads.
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80.(234) Which one of these compressor section subsystems does not belong on the F117−PW−100jet engine?a.Low-pressure compressor (LPC) group. b.High-pressure turbine (HPT) group. c.Low-pressure compressor (LPC) drive shaft group. d.Intermediate case group. |
b.High-pressure turbine (HPT) group.
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81.(234) The high-pressure compressor (HPC) group on the F117−PW−100 jet engine consists ofhow many rotor stages and how many stages of stators surrounded by a two section titanium andsteel case? a.12 rotors and 10 stators. b.12 rotors and 12 stators. c.10 rotors and 10 stators. d.10 rotors and 12 stators. |
b.12 rotors and 12 stators.
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82.(235) How many exit vanes make up the compressor exit stator assembly on the F117−PW−100jet engine a. 42. b. 52. c. 62. d. 72. |
d. 72. |
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83.(235) The combustion chamber assembly provides the optimum environment for combustion anddirects the flow of a.cool gases to the turbine nozzle. b.cool gases to the turbine blades. c.hot gases to the turbine nozzle. d.hot gases to the turbine blades. |
c.hot gases to the turbine nozzle.
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84.(236) Which of these turbine section subsystems does not belong on the F117−PW−100 jet engine? a.Turbine nozzle group. b.Low-pressure compressor (LPC) nozzle group. c.High-pressure turbine (HPT) module. d.Low-pressure turbine (LPT) module. |
b.Low-pressure compressor (LPC) nozzle group
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85. (237) Which one of these components is not an engine accessory component on the F117−PW−100 jet engine? a. Permanent magnet alternator (PMA). b. Radial drive shaft. c. Oil pump module. d. Fuel pump/fuel control. |
b. Radial drive shaft.
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86. (237) Which one of the listed components is not an aircraft accessory component on the F117−PW−100 jet engine? a. Integrated drive generator (IDG). b. Starter. c. Two hydraulic pumps. d. Low=pressure turbine (LPT) module. |
d. Low=pressure turbine (LPT) module
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