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Powerplant 4

COMENTARIOS ESTADÍSTICAS RÉCORDS
REALIZAR TEST
Título del Test:
Powerplant 4

Descripción:
AME Powerplant

Fecha de Creación: 2025/07/13

Categoría: Otros

Número Preguntas: 90

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1. In a gas turbine engine, combustion occurs at a constant. Volume. Density. Pressure. Velocity.

2. At higher subsonic speed, the type of engine which affords the most efficient propulsive power is the. Turbofan. Turboprop. Turbojet. Turboshaft.

3. A typical cool-down period for an APU is. 3 minutes. 6 minutes. 10 minutes. Not required.

4. When a gas or fluid is supplied through a divergent duct, if pressure increases. Thrust will increase. Velocity will increase. Velocity will decrease. Temperature will decrease.

5. Engine manufacturers’ calculations of static thrust are based on a temperature of. 13°C. 15°C. 17°C. 20°C.

6. What is meant by “shrouded turbine blades”?. The turbine blades are shaped so that their ends form a band or a shroud. The turbine wheel is enclosed in a protective shroud to contain the blades in case of failure. The turbine wheel has a shroud or duct which provides cooling air to the turbine blades. The turbine wheel is enclosed in a protective shroud to contain the blades and provide cooling air to the turbine blades.

7. In a turbine engine, the highest pressure is found. Immediately aft of the turbine section. At the entrance of the turbine section. In the diffuser section, entrance of the burner section. At the outlet of the tail pipe section.

8. High EGT, high fuel flow and low rpm at all engine power settings is most likely caused by. Turbine damage. Misaligned exhaust duct. FCU out of adjustment. Unserviceable variable inlet guide vanes.

9. Compressor blades which have a reduced thickness at the tips are referred to as. Blisk or creeper blades. Profile or squeeler blades. Shrouded tip profile blades. Twist-tip or creep blades.

10. The primary airflow through a combustor. Is approximately 75% ofthe total airflow. Is routed to the fuel nozzle area for combustion. Dilutes the mixture to an acceptable temperature. Provides a cooling blanket on either side of the combustor liner.

11. In a reverse flow annular combustor, the main airflow enters the combustor from. The rear of the engine. The front of the engine. Holes drilled around the combustor. Deflectors located at the rear of the combustor.

12. The most common method of attaching turbine blades to a turbine wheel is with. Rivets and roll pins. Locktabs and roll pins. The dove tail design. The fir-tree design.

13. On turbine engines, the type of bearing better equipped to support radial loads rather than thrust loads is the. Roller bearing. Ball bearing. Plain bearing. Duplex ball bearing.

14. On a free turbine engine, engine control rigging is required for. N₁ only. N₂ only. both N₁ and N₂. none of the above.

15. If a minute crack is found on a turbine disk. it must be further inspected with dye penetrant. it must be blended by stoning and polishing. is immediate cause for rejection of the turbine disk. is acceptable and must be monitored daily.

16. Turbine blade replacements are identified by code letters indicating the. weight in grams. weight in ounces. moment weight in inch-ounces. weight in one-tenth of an ounce increments.

17. Variable inlet guide vanes are actuated by means of cylinders which receive operating pressure from. the engine fuel control system. compressor bleed air. the IGV controller. ambient air pressure and compressor bleed air.

18. A permanent elongation which occurs on turbine blades due to centrifugal force is known as. blisk. twist. creep. deformation.

19. The type of fuel pump designed to deliver a continuous supply of high pressure fuel to the fuel control unit at a quantity which is in excess of what the engine needs is the. standby pump. engine driven pump. electrical booster pump. auxiliary pump.

20.The two types of turbine engine fuel nozzles generally used are. simplex and duplex. flow divider and simplex. flow divider and duplex. atomizer and flow divider.

21. With no change in power setting parameters, high oil temperatures indicates. gearbox seal leakage. high oil sump pressure. engine main bearing distress. abnormal scavenge pump oil flow.

22. The type of oil system usually found on most turbojet engines is. dry sump, splash and spray. wet sump, dip and pressure. wet sump, splash and spray. dry sump, pressure and spray.

23. In a gas turbine engine, oil picks up most heat from the. exhaust turbine bearing. compressor bearing. combustor shroud. accessory drive bearings.

24.What will happen to the return line if the oil line between the scavenge pump and the oil cooler separates?. the oil will accumulate in the engine. the return oil will be pumped overboard. the cooler check valve will close and force the oil to bypass the cooler and return to the tank via the cold oil line. the scavenge return check valve will close and force the oil to bypass directly to the intake side of the pressure pump.

25. The capacity of the oil scavenge system must be __________________ the capacity of the pressure system. more than ¼ and less than ½. more than ½ and less than ¾. equal to. at least double.

26. The normal starting sequence for a turbojet engine is. ignition, starter, fuel. fuel, starter, ignition. starter, ignition, fuel. starter, fuel, ignition.

27. In-flight, turbine engine flameouts are usually caused by. fuel nozzle clogging. fouling of the igniter plugs. interruption of the inlet airflow. high exhaust gas temperature.

28. The two common classifications of capacitor ignition systems are. AC and DC. low voltage and high voltage. low voltage and high current. high voltage and high current.

29. On a turbine engine, a starter-generator requires a. compound motorfor the starter only. shunt motorfor both starter and generator. drive spline which disengages from the accessory gearbox. drive spline which stays permanently engaged to the engine.

30.The air source supplied to an air-turbine starter is. low pressure, low volume. low pressure, high volume. high pressure, low volume. high pressure, high volume.

31. A carbon seal found on turbine engines. normally rides on a highly polished surface. maintains an air gap clearance. is similar in design to a labyrinth seal. will have grooves forming sealing rings in a concentric path similar to a screw thread.

32. Temperature taken aft of the turbine wheel(s) is known as. EGT. ITT. TIT. T4.

33. Which of the following are the most common types of thrust reversers used on turbine engine powered aircraft. cascade vane and blocker door. mechanical-blockage and aerodynamic blockage. convergent and divergent. rotary air vane and stationary air vane.

34. Turbine engines utilize a capacitor-discharge ignition system that has a high voltage and... reduces the possibility of a hot start. very high heat intensity. very low amperage. very little tendency to create flashover at high altitudes.

35. Air enters the centrifugal flow compressor impeller at the. perimeter. center. side. rear.

36. Which of the following could cause flameout. wind. rain. turbulence. reverse thrust.

37. Cracks in turbine blades are. not acceptable. acceptable within limits. not a problem as they relieve stress. turbine blades don’t crack.

38. What is “Creep” in relation to a turbine blade. tendency to move sideways. tendency to elongate due rotation. refers to blades rubbing the shroud. term used in referring to turbine blades.

39. What is considered a standard day. temperature 75°F, pressure 30.00. temperature 915°F, pressure 29.92. temperature 59°F, pressure 29.92. temperature 535°F, pressure 30.00.

40. Which of the following engine fire detection systems measures temperature rise compared to a reference temperature. Lindberg. Fenwall. Thermocouple. All of the above.

41. An engine reduction gear is designed to. reduce wear on the thrust bearing. provide a reduced RPM for the governor. provide an engine RPM lower than that of the propeller or transmission shaft. provide a propeller or transmission RPM lower than that of the engine.

42. The brake horsepower (BHP) of an engine is. the calculated theoretical power output. the total power developed, disregarding friction losses. the total energy expended in all combustion chambers. the total power output actually delivered.

43. Manifold pressure is defined as. the atmosphere pressure when the engine is operating. the absolute pressure in the intake manifold. the differential pressure in the intake manifold. the pressure measured at the venturi ofthe carburetor.

44. Which of the following results in a decrease in volumetric efficiency?. Short intake pipes of large diameter. Cylinder head temperature too low. Carburetor air temperature too low. Part-throttle operation.

45. Piston rings are usually made of. stainless steel. gray cast iron. cast aluminum. nickel steel.

46. The reason why choke-type cylinders are used is to. compensate for normal cylinder barrel wear. increase the compression for starting purposes. provide a straight cylinder bore at operating temperature. reduce the possibility of piston rings sticking in the ring grooves.

47. To allow surplus oil to return to the crankcase, holes are drilled in. the piston pin. the piston oil control ring grooves. the oil scraper ring grooves. both the oil control and the oil scraper rings.

48. Excessive valve clearance will cause the duration of valve opening to. increase for both intake and exhaust valves. decrease for both intake and exhaust valves. decrease for intake valves and increase for exhaust valves. increase for intake valves and decrease for exhaust valves.

49. Cam-ground pistons are installed in some aircraft engines to. provide a better fit at operating temperatures. equalize the wear on pistons that do not operate in a vertical plane. act as a compensating feature so that a compensated magneto is required. none of the above.

50. Knuckle pins form the hinge between. the master rod and the crankshaft. the pistons and the connecting rods. the pinion gears and the reduction gear cage. the articulating rods and the master rod flanges.

51. At what speed range is a fixed pitch propeller designed to be most efficient?. ground idle. cruise. flight idle. none ofthe above.

52. What happens to the blade angle of a constant speed propeller in flight if the throttle is advanced?. it will stay the same. it will be decreased. it will be increased. none of the above.

53. What is the flat side of the propeller blade called?. the back. the face. the tip. the butt.

54. The thrust reverser accounts for how much percentage of braking?. 12%. 10%. 20%. 40%.

55. The following be a significant factor in the failure of an engine to develop full power at take-off. improper adjustment of the carburetor heat valve control leakage. null.

56. Why should a Px carburetor be “soaked” before its installation is considered complete?. it conditions the diaphragm to the exact pliability with which they were calibrated. null.

57. Correct idle mixture adjustment is indicated if movement of the mixture control to the cut-off position rejects in. slight RPM increase (50 RPM) and then it drops off. none.

58. The difference between a “cold” and a “hot” spark plug is the variation in. plug reach. spark gap. length of the insulator core nose. sealing between the insulator and electrode.

59. An aircraft magneto is shut off by. opening the primary circuit. opening the secondary circuit. grounding the primary circuit. grounding the secondary circuit.

60. The fourth electrode in the magneto sparking order of a nine cylinder radial engine serves cylinder #. 2. 4. 7. 9.

61. The magneto timing should ensure that the E-gap position occurs when the breaker points are. open. closed. just opening. just closing.

62. At what speed must a crankshaft turn if each cylinder of a four stroke cylinder engine is to be fired 200 times a minute. 100 RPM. 200 RPM. 300 RPM. 400 RPM.

63. A magneto impulse coupling. is used to provide a high voltage advanced spark during start. is used to provide a high voltage retarded spark during start. is electrically energized by the booster coil. supplies voltage to the retard points during start.

64. During routine inspection of a magneto, the breaker points are found to be badly pitted and burned. A likely cause would be. an incorrect E-gap setting. too wide a spark plug gap. a faulty primary capacitor. a faulty secondary coil.

65. A manifold pressure gauge indicates. the Brake Mean Effective Pressure. the differential pressure between the intake manifold and atmosphere. variations of atmospheric pressure at different altitudes. the absolute pressure in the intake manifold.

66. A hissing sound from the exhaust stacks when the propeller is being pulled manually indicates. cracked exhaust stack. worn piston ring. a rich mixture. exhaust valve blow–by.

67. How should the exhaust system be inspected on an aircraft that utilizes an exhaust heat exchanger as a source of cabin heat. hydrostatically tested. X-ray the exchanger to detect cracks. with the heater air shroud removed. with an exhaust gas analyzer.

68. By use of a differential pressure tester, it is determined that #3 cylinder of a nine-cylinder radial engine will not hold pressure after the crankshaft has been rotated from top dead center compression stroke #1 cylinder. How can this indication usually be interpreted. a normal indication. exhaust valve blow-by. Badly worn or damaged piston rings. A damaged exhaust valve or insufficient exhaust valve clearance.

69. Immediately after installing a new set of piston rings, the most likely reason for excessive blow-by could be. improper valve seating. insufficient end gap. worn valve guides. failure to stagger the ring gaps.

70. On a twin-engine aircraft with fuel-injected reciprocating engines, one fuel flow indicator reads considerably higher and the other in all engine operating configuration. What is the probable cause of this indication. carburetor icing. alternate air door stuck open. excessive intake valve clearance. one or more fuel nozzles are clogged.

71. What is the type of connecting rod normally used on a horizontal opposed engine. ball type. plain type. fork and blade type. master and articulated type.

72. The piston ring installed below the compression rings is called. oil scraper ring. oil control ring. oil wiper ring. none ofthe above.

73. Cylinders that have been chrome plated are identified by. green paint. white paint. blue paint. orange paint.

74. If a 0.003 oversize stud is identified by the prefix P003 after the part number, what will be the color painted on the stud. Orange. White. Red. none of the above.

75. A six-cylinder engine with a bore of 4.375 inches and a stroke of 5.125 inches has a piston displacement of ____________ cubic inches. 422.6. 1649.0. 462.25. 1849.0.

76. The cambered side of a propeller blade is known as. the blade face. the blade back. the blade loft. the blade chord.

77. _____ is simply a reference position on a propeller blade that is specified distance from the center of the hub. the blade datum point. the blade center of gravity. a blade center of pressure. a blade station.

78. The actual distance a propeller moves through the air in one revolution is known as. the effective pitch. the relative pitch. the resultant pitch. the geometric pitch.

79. In reference to propellers, slip is known as the difference between. the geometric pitch and the effective pitch. the propeller pitch and the dynamic pitch. the propeller pitch and the effective pitch. the propeller pitch and the aerodynamic pitch.

80. In cruising flight, a propeller will normally be operating in. the alpha range. the beta range. the negative thrust range. the theta range.

81. Tractor propellers are mounted. on the front of an engine and pull the aircraft through the air. on the front of an engine and push the aircraft through the air. on the aft end of an engine and pull the aircraft through the air. on the aft end of an engine and push the aircraft through the air.

82. The most efficient angle of attack of a propeller blade is in the range of. -2° to +2°. +2° to +4°. +4° to +8°. +8° to +10°.

83. A propeller blade cuff. distributes anti-icing fluid. strengthens the propeller blade. reduces drag. increases cooling air flow.

84. Which of the following occurs to cause front cone bottoming during propeller installation. the front cone becomes bottomed in the front propeller hub cone seat before the rear propeller hub cone seat has engaged the rear cone. the front cone becomes bottomed in the front propeller hub cone seat before the retaining nut has engaged sufficient threads to be safetied properly. the front cone enters the front propeller hub cone seat at an angle causing the propeller retaining nut to appear tight when it is only partially tightened. the front cone contacts the ends of the shaft splines, preventing the front and rear cones from being tightened against the cone seats in the propeller hub.

85. Normally, for a light aircraft with metal propellers of up to approximately 6 feet in diameter, the propellers can be out of track no more than. 1/32". 1/16". 1/8". 1/4".

86. In cruising flight, at a constant RPM. the propeller is on its high pitch stop. the centrifugal force of the governor flyweights is less than the force of the speeder spring. centrifugal force of the governor flyweights balance the force of the speeder spring. centrifugal force of the governor flyweights exceeds the force of the speeder spring.

87. Propeller Synchronising systems are intended to ensure that all propellers. operate at the same RPM. produce the same thrust. maintain their angular relationships. maintain the same angle of attack.

88. An aircraft’s propeller system beta range. is used to produce zero or negative thrust. is the pitch range used for cruising speeds. is used to achieve maximum thrust during takeoff. refers to the most fuel efficient pitch range to use at a given RPM.

89. If a hydraulic propeller is feathered and then immediately unfeathers itself, a probable cause of the trouble is that the. governor is not cutting out in high pitch. pressure cutout switch is struck in the closed position. distributor relief valve is struck in the closed position. dome pressure relief valve is struck in the closed position.

90. Proper operation of the electric deicing boots on individual propeller blades may be best determined by. feeling the boots to see ifthey are heating. observing the ammeter or loadmeterfor currentflow. timing the inflation and deflation sequence. checking the ammeter for flickering and feeling the boots for sequence of heating.

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