#1. On most modern airliners the cabin pressure is controlled by regulating the:
#2. If the maximum operating altitude of an airplane is limited by the pressurized cabin, this limitation is due to the maximum:
#3. The “”cabin differential pressure”” is:
#4. The cabin rate of descent is:
#5. The maximum differential pressure of a transonic transport category airplane is approximately:
#6. An aircraft with a pressurized cabin is settled at its cruise level.During the flight, a malfunction of the pressure controller is detected by the crew and the cabin rate of climb indicator reads -200ft/min.Given that :DELTA P: Differential pressureZc: Cabin altitude
#7. An aircraft with a pressurized cabin flies at level 310.Following a malfunction of the pressure controller, the outflow valve runs to the open position. Given :VZc: Cabin rate of climb indicationZc: Cabin pressure altitudeDELTA P: Differential pressureThis will result in a:
#8. In a manually operated system, the cabin altitude rate of change is normally controlled by :
#9. The term “”pressure cabin”” applies when an aeroplane :
#10. Under normal flight conditions, cabin pressure is controlled by :
#11. Assuming cabin differential pressure has attained the required value in normal flight conditions, if flight altitude is maintained :
#12. Assuming cabin pressure decreases, the cabin rate of climb indicator should indicate :
#13. Assume that during cruise flight with airconditioning packs ON, the outflow valve(s) would close. The result would be that:
#14. A cabin pressure controller maintains a pre-set cabin altitude by regulating the :
#15. If the pressure in the cabin tends to become lower than the outside ambient air pressure the :
#16. The pneumatic ice protection system is mainly used for:
#17. With regard to the pneumatic mechanical devices which afford protection against the formation of ice, the only correct statement is:
#18. A pneumatic de-ice system should be operated ..
#19. Concerning the sequential pneumatic impulses used in certain leading edge deicing devices, one can affirm that :1 – They prevent ice formation.2 – They are triggered from the flight deck after icing has become visible.3 – A cycle lasts more than ten seconds.4 – There are more than ten cycles per second.The combination which regroups all the correct statements is :
#20. The pneumatic system accumulator is useful :
#21. In the pneumatic supply system of a modern transport aircraft, the air pressure is regulated. This pressure regulation occurs just before the manifold by the :
#22. In the air cycle system the air is cooled down by expansion:
#23. Main cabin temperature is:
#24. Environmental system: in the air refrigeration unit, the water separation unit is placed:
#25. The air-conditioning pack of a present-day aircraft consists of several components: these include two heat exchangers, the primary exchanger (P) and the secondary exchanger (S).The functions of these heat exchangers are as follows:
#26. “”Conditioned”” air is air that has:
#27. The term “”cabin pressure”” applies when an aeroplane:
#28. When air is compressed for pressurization purposes, the percentage oxygen content is:
#29. The term “”bootstrap””, when used to identify a cabin air conditioning and pressurisation system, refers to the:
#30. In a bootstrap cooling system the supply air is first:
#31. In a cabin air conditioning system, equipped with a bootstrap, the mass air flow is routed via the:
#32. Engine bleed air used for air conditioning and pressurization in turbo-jet aeroplanes is usually taken from the:
#33. What is the purpose of the pack cooling fans in the air conditioning system?
#34. The cabin air for modern airplanes is usually supplied by:
#35. Cabin air for modern aircraft is usually taken from:
#36. In an aircraft air conditioning system the air cannot be treated for:
#37. In a bootstrap system, the purpose of the heat exchangers is to:
#38. The turbine in a cold air unit (air cycle machine):
#39. In large modern aircraft, in the air conditioning system, reduction of air temperature and pressure is achieved by:
#40. In a “”bootstrap”” cooling system, the charge air is first compressed in the cold air unit to:
#41. A turbo-fan cold air unit will:
#42. The cabin heating supply in a heavy jet transport aircraft is obtained from :
#43. The pack cooling fan provides:
#44. The water separator of an air-conditioning unit is located at the cooling unit :
#45. The term “”Bootstrap””, when used to identify a cabin air conditioning and pressurisation system, refers to the :
#46. In a bootstrap cooling system the supply air is first :
#47. The function of an air cycle machine is to :
#48. “”Conditioned”” air is air that has :
#49. In flight, the most commonly used anti-icing method for the wings of modern commercial aircraft fitted with turbo-jet units is:
#50. Concerning electrically powered ice protection devices, the only true statement is:
#51. The elements specifically protected against icing on transport aircraft are:1) engine air intake and pod.2) front glass shield.3) radome.4) pitot tubes and waste water exhaust masts.5) leading edge of wing.6) cabin windows.7) trailing edge of wings.8) electronic equipment compartment.The combination regrouping all the correct statements is :
#52. The ice protection system currently used for the most modern jet aeroplanes is the
#53. During flight, the wing anti-ice system has to protect
#54. In jet aeroplanes the ‘thermal anti-ice system’ is primary supplied by
#55. The anti-ice or de-icing system which is mostly used for the wings of modern turboprop aeroplanes is :
#56. The ice protection for propellers of modern turboprop aeroplanes works
#57. The advantages of thermal anti-icing are :1. Simple and reliable system2. Profiles maintained3. Greater efficiency than that of an electrical resistor4. Direct use of the hot air from the jet engine without substantial reduction in engine thrustThe combination of correct statements is:
#58. On modern transport aircraft, cockpit windows are protected against icing by :
#59. Usually, electric heating for ice protection is used on:
#60. The heating facility for the windshield of an aircraft is:
#61. The correct statement about rain protection for cockpit windshields is that :
#62. The purpose of the baffles in an aircraft’s integral fuel tank is to:
#63. On a transport type aircraft the fuel tank system is vented through:
#64. The types of fuel tanks used on most modern transport aircraft are:
#65. The purpose of baffle check valves fitted in aircraft fuel tanks is to :
#66. The pressurization of tanks is maintained by the fuel:
#67. The automatic fuelling shut off valve:
#68. Fire precautions to be observed before refuelling are :
#69. The function of a feed box in the fuel tank is to
#70. On most transport aircraft, the low pressure pumps of the fuel system are:
#71. The fuel supply system on a jet engine includes a fuel heating device, upstream of the main fuel filter so as to:
#72. On most transport jet aircraft, the low pressure pumps of the fuel system are supplied with electric power of the following type:
#73. The fuel crossfeed system:
#74. On most transport aircraft, the low pressure pumps of the fuel system are:
#75. On a jet aircraft fuel heaters are :
#76. During fuelling the automatic fuelling shut off valves will switch off the fuel supply system when:
#77. The cross-feed fuel system is used to :
#78. The fuel system boost pumps are submerged in the fuel ..
#79. The refueling in a transport jet aircraft is made …
#80. The vapor lock is :
#81. The fuel system boost pumps are used to :
#82. The cross-feed fuel system enables:
#83. Fuel pumps submerged in the fuel tanks of a multi-engine aircraft are:
#84. Fuel dump systems are required:
#85. The maximum quantity of fuel that can be dumped with the jettisoning system is:
#86. The capacitance type fuel gauging system indicates the fuel quantity by measuring the:
#87. In a compensated capacitance type quantity indicating system, the contents gauge of a half-full fuel tank indicates a fuel mass of 8000 lb. If a temperature rise increased the volume of fuel by 5 %, the indicated fuel weight would :
#88. Fuses are rated to a value by :
#89. The difference between (1) a fuse and (2) a circuit breaker is:
#90. An aircraft electrical circuit which uses the aircraft structure as a return path to earth, may be defined as a
#91. When an “”open circuit”” occurs in an electrical supply system, the :
#92. If a current is passed through a conductor which is positioned in a magnetic field :
#93. A current limiter fuse in a DC generation system is used to :
#94. The true statement among the following in relation to the application of Ohm’s law is :
#95. A condenser in parallel with breaker points will
#96. The connection in parallel of two 12 volt/ 40 amphours batteries, will create a unit with the following characteristics,
#97. The resistors R1 and R2 are connected in parallel. The value of the equivalent resistance (Req) so obtained is given by the following formula:
#98. If one of the 12 cells of a lead-acid battery is dead, the battery:
#99. In aeronautics, the most commonly used batteries are NiCd because…
#100. On board present aircraft, the batteries used are mainly Cadmium-Nickel. Their advantages are:1. low risk of thermal runaway2. high internal resistance, hence higher power3. good charging and discharging capability at high rating4. wider permissible temperature range5. good storage capability6. sturdiness owing to its metal casing7. the electrolyte density remains unchanged during charging.The combination of correct statement is:
