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INDIGO PISTON ENGINES

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#1. DURALUMIN alloys :1 have an aluminium-copper base.2 have an aluminiummagnesium base.3 are easy to weld.4 are difficult to weld.5 have a good thermal conductivity.6 have a poor air corrosion resistanceThe combination regrouping all the correct statements is :

#2. Among the different types of aircraft structures, the shell structures efficiently transmit the:1. normal bending stresses2. tangent bending stresses3. torsional moment4. shear stressesThe combination regrouping all the correct statements is :

#3. 'Fail safe construction' is :

#4. The fuselage of an aircraft consists, among others, of stringers whose purpose is to:

#5. The reason for the fact that an aeroplane designed for long distances cannot simply be used for short haul flights at higher frequencies is that

#6. The wing of an aircraft in flight, powered by engines located under the wing, is subjected to a bending moment which causes its leading edge, from the wing root to the wing tip, to operate in:

#7. In flight the wing of an aircraft containing fuel is subjected to vertical loads that produce a bending moment which is:

#8. The Maximum Zero Fuel Mass:1 Is a limitation set by regulation.2 Is designed for a maximum load factor.3 Is due to the maximum bending moment at wing root.4 Requires to empty external tanks first.5 Requires to empty internal tanks first.The correct combination of true statements is :

#9. On a non-stressed skin type wing, the wing structure elements which take up the vertical bending moments Mx are:

#10. The advantage of mounting the tailplane on top of the vertical stabilizer is :

#11. A torsion link assembly is installed on the landing gear to :

#12. In a commercial transport aircraft the landing gear operating system is usually:

#13. Generally, on modern jet transport aircraft, how can the landing gear be extended if there is a complete hydraulic system failure

#14. If the profile grooves or the tread of a new aircraft tyre are worn, the tyre can be:

#15. The operating principle of an anti skid system is as follows : the brake pressure will be :

#16. The type of brake unit found on most transport aeroplanes is a:

#17. The reason for fitting thermal plugs to aircraft wheels is that they :

#18. Thermal plugs are installed in:

#19. When a landing gear wheel is hydroplaning, its friction factor is equal to:

#20. Shimmy occurs on the nosewheel landing gear during taxiing when:1. the wheels tend to describe a sinusoidal motion on the ground2. the wheels no longer respond to the pilot's actionsThis effect is overcome by means of:3. the torque link4. an accumulator associated with the steering cylinderThe combination of correct statements is:

#21. The illumination of the green landing gear light indicates that the landing gear is :

#22. A tubeless tyre has :1- a built-in-air tube.2- no built-in-air tube.3- a crossed side casing.4- a radial side casing.The combination of correct statements is:

#23. In a hydraulic braking system, the accumulator is:

#24. Which is (are) the damping element(s) in a landing gear shock absorber used on larger aircraft ?

#25. In some aircraft, there is a protection device to avoid the landing gear being inadvertently retracted on the ground. It consists of :

#26. A tubeless tyre is a tyre:1. which requires solid or branched wheels2. whose valve can be sheared in sudden accelerations3. whose mounting rim must be flawless4. which requires no rim protection between rim flange and tire removing device5. which does not burst in the event of a tire puncture6. which eliminates internal friction between the tube and the tireThe combination regrouping all the correct statements is :

#27. Landing gear torque links are used to:

#28. A main landing gear is said to be ""locked down"" when:

#29. The modern anti-skid processes are based on the use of a computer whose input data is:1. idle wheel speed (measured)2. braked wheel speed (measured)3. brake temperature (measured)4. desired idle wheel train slipping rate5. tire pressureThe combination regrouping all the correct statements is :

#30. On large aeroplanes equipped with power brakes, the main source of power is derived from :

#31. ""Nose wheel shimmy"" may be described as :

#32. The part of the flight that will cause the highest loads on the torsion link in a bogie gear is

#33. Tyre ""creep"" may be described as the :

#34. The ABS (Auto Brake System) is being diconnected after landing ..

#35. The purposes of the oil and the nitrogen in an oleo-pneumatic strut are :

#36. The function of a fusible plug is to

#37. (For this question use appendix )Associate the correct legend to each of the numbered diagrams :

#38. A scissor is a component found on landing gears. Its function is to :

#39. Compared to a tyre fitted with an inner tube, a tubeless tyre presents the following characteristics :1 - high heating2 - valve fragility3 - lower risk of bursting4 - better adjustment to wheelsThe combination containing all the correct statements is:

#40. On a modern aeroplane, to avoid the risk of tyre burst from overheating, due for example to prolonged braking during an aborted take-off, there is:

#41. On an aircraft landing gear, an under-inflated tyre:

#42. The trim tab :

#43. The purpose of a trim tab (device) is to:

#44. An artificial feel unit is necessary in the pitch channel when:

#45. An artificial feel unit system:

#46. A Yaw Damper is :

#47. In a steep turn to the left, when using spoilers ...

#48. The advantages of fly-by-wire control are:1. reduction of the electric and hydraulic power required to operate the control surfaces2. lesser sensitivity to lightning strike3. direct and indirect weight saving through simplification of systems4. immunity to different interfering signals5. improvement of piloting quality throughout the flight envelopeThe combination regrouping all the correct statements is :

#49. Which of these signals are inputs, at least, in the stall warning computers?

#50. On an aircraft, the Krueger flap is a:

#51. The reason for the trim switch on a control column to consist of two separate switches is

#52. On an aeroplane, spoilers are :

#53. On an airplane, the Krueger flaps are:

#54. Hydraulic fluids must have the following characteristics:1. thermal stability2. low emulsifying characteristics3. corrosion resistance4. good resistance to combustion5. high compressibility6. high volatility7. high viscosityThe combination regrouping all the correct statements is :

#55. In a hydraulic braking system, an accumulator is precharged to 1200 psi.An electrically driven hydraulic pump is started and provides a system pressure of 3000 psi. The hydraulic pressure gauge which is connected to the gas section of the accumulator, reads:

#56. Hydraulic fluids :

#57. Hydraulic fluids used in systems of large modern airliners are:

#58. Hydraulic power is a function of :

#59. Large transport aeroplane hydraulic systems usually operate with a system pressure of approximately:

#60. In hydraulic systems of large modern transport category aircraft the fluids used are:

#61. The type of hydraulic oil used in modern hydraulic systems is:

#62. The type of hydraulic fluid which has the highest resistance against cavitation is :

#63. The component that transforms the hydraulic pressure into a linear motion is called ...

#64. The aircraft hydraulic system is designed to produce:

#65. Hydraulic fluids of synthetic origin are:

#66. Internal leakage in a hydraulic system will cause :

#67. Discounting the possibility of leak, the level in a hydraulic reservoir will :

#68. Assuming a hydraulic accumulator is pre-charged with air to 1000 psi. If the hydraulic system is then pressurised to its operating pressure of 3000 psi, the indicated pressure on the air side of the accumulator should be :

#69. For an aeroplane hydraulic supply circuit, the correct statement is :

#70. Where in a hydraulic system might overheat indicators be installed?

#71. In a modern hydraulic system, ""hydraulic fuses"" can be found. Their function is :

#72. In a hydraulic system, the reservoir is pressurized in order to:

#73. The purpose of a shuttle valve is to:

#74. Shuttle valves will automatically:

#75. In addition to energy storage the accumulator of the hydraulic system is used :

#76. The hydraulic device similar to an electronic diode is a :

#77. The function of the selector valve is to:

#78. Assuming an accumulator is pre-charged with air to 1000 psi and the hydraulic system is pressurised to 1500 psi, the accumulator gauge will read :

#79. An accumulator in a hydraulic system will :

#80. In hydraulic system, a shuttle valve :

#81. To allow for failure of the normal method of system pressure limiting control, a hydraulic system often incorporates

#82. The hydraulic oil, entering the hydraulic pump, is slightly pressurised to :

#83. The Ram Air Turbine (RAT) provides emergency hydraulic power for :

#84. The tanks of a hydraulic system are pressurized:

#85. The low pressure switch of a hydraulic circuit sets off an alarm if :

#86. If the cabin altitude rises (aircraft in level flight), the differential pressure:

#87. The purpose of the cabin pressure controller, in the automatic mode, is to perform the following functions:1. control of cabin altitude,2. control of cabin altitude rateof- change,3. limitation of differential pressure4. balancing aircraft altitude with cabin altitude5. cabin ventilation6. keeping a constant differential pressure throughout all the flight phases.The combination regrouping all the correct statements is :

#88. During a normal pressurised climb after take-off:

#89. The purpose of cabin air flow control valves in a pressurization system is to :

#90. Assuming cabin differential pressure has attained the required value in normal flight conditions, if flight altitude is maintained:

#91. Cabin pressure is controlled by :

#92. During level flight at a constant cabin pressure altitude (which could be decreased, even at this flight level), the cabin outflow valves are:

#93. The purpose of a ditching control is to:

#94. The cabin pressure is regulated by the:

#95. The pressurization of the cabin is controlled by :

#96. Cabin differential pressure means the pressure difference between:

#97. Under normal conditions (JAR 25) the cabin pressure altitude is not allowed to exceed:

#98. Cabin altitude means the:

#99. A warning device alerts the crew in case of an excessive cabin altitude. This warning must be triggered on reaching the following altitude:

#100. On a modern large pressurized transport aircraft, the maximum cabin differential pressure is approximately:

#101. On most modern airliners the cabin pressure is controlled by regulating the:

#102. If the maximum operating altitude of an airplane is limited by the pressurized cabin, this limitation is due to the maximum:

#103. The ""cabin differential pressure"" is:

#104. The cabin rate of descent is:

#105. The maximum differential pressure of a transonic transport category airplane is approximately:

#106. 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

#107. 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:

#108. In a manually operated system, the cabin altitude rate of change is normally controlled by :

#109. The term ""pressure cabin"" applies when an aeroplane :

#110. Under normal flight conditions, cabin pressure is controlled by :

#111. Assuming cabin differential pressure has attained the required value in normal flight conditions, if flight altitude is maintained :

#112. Assuming cabin pressure decreases, the cabin rate of climb indicator should indicate :

#113. Assume that during cruise flight with airconditioning packs ON, the outflow valve(s) would close. The result would be that:

#114. A cabin pressure controller maintains a pre-set cabin altitude by regulating the :

#115. If the pressure in the cabin tends to become lower than the outside ambient air pressure the :

#116. The pneumatic ice protection system is mainly used for:

#117. With regard to the pneumatic mechanical devices which afford protection against the formation of ice, the only correct statement is:

#118. A pneumatic de-ice system should be operated ..

#119. 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 :

#120. The pneumatic system accumulator is useful :

#121. 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 :

#122. In the air cycle system the air is cooled down by expansion:

#123. Main cabin temperature is:

#124. Environmental system: in the air refrigeration unit, the water separation unit is placed:

#125. 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:

#126. ""Conditioned"" air is air that has:

#127. The term ""cabin pressure"" applies when an aeroplane:

#128. When air is compressed for pressurization purposes, the percentage oxygen content is:

#129. The term ""bootstrap"", when used to identify a cabin air conditioning and pressurisation system, refers to the:

#130. In a bootstrap cooling system the supply air is first:

#131. In a cabin air conditioning system, equipped with a bootstrap, the mass air flow is routed via the:

#132. Engine bleed air used for air conditioning and pressurization in turbo-jet aeroplanes is usually taken from the:

#133. What is the purpose of the pack cooling fans in the air conditioning system?

#134. The cabin air for modern airplanes is usually supplied by:

#135. Cabin air for modern aircraft is usually taken from:

#136. In an aircraft air conditioning system the air cannot be treated for:

#137. In a bootstrap system, the purpose of the heat exchangers is to:

#138. The turbine in a cold air unit (air cycle machine):

#139. In large modern aircraft, in the air conditioning system, reduction of air temperature and pressure is achieved by:

#140. In a ""bootstrap"" cooling system, the charge air is first compressed in the cold air unit to:

#141. A turbo-fan cold air unit will:

#142. The cabin heating supply in a heavy jet transport aircraft is obtained from :

#143. The pack cooling fan provides:

#144. The water separator of an air-conditioning unit is located at the cooling unit :

#145. The term ""Bootstrap"", when used to identify a cabin air conditioning and pressurisation system, refers to the :

#146. In a bootstrap cooling system the supply air is first :

#147. The function of an air cycle machine is to :

#148. ""Conditioned"" air is air that has :

#149. In flight, the most commonly used anti-icing method for the wings of modern commercial aircraft fitted with turbo-jet units is:

#150. Concerning electrically powered ice protection devices, the only true statement is:

#151. 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 :

#152. The ice protection system currently used for the most modern jet aeroplanes is the

#153. During flight, the wing anti-ice system has to protect

#154. In jet aeroplanes the 'thermal anti-ice system' is primary supplied by

#155. The anti-ice or de-icing system which is mostly used for the wings of modern turboprop aeroplanes is :

#156. The ice protection for propellers of modern turboprop aeroplanes works

#157. 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:

#158. On modern transport aircraft, cockpit windows are protected against icing by :

#159. Usually, electric heating for ice protection is used on:

#160. The heating facility for the windshield of an aircraft is:

#161. The correct statement about rain protection for cockpit windshields is that :

#162. The purpose of the baffles in an aircraft's integral fuel tank is to:

#163. On a transport type aircraft the fuel tank system is vented through:

#164. The types of fuel tanks used on most modern transport aircraft are:

#165. The purpose of baffle check valves fitted in aircraft fuel tanks is to :

#166. The pressurization of tanks is maintained by the fuel:

#167. The automatic fuelling shut off valve:

#168. Fire precautions to be observed before refuelling are :

#169. The function of a feed box in the fuel tank is to

#170. On most transport aircraft, the low pressure pumps of the fuel system are:

#171. The fuel supply system on a jet engine includes a fuel heating device, upstream of the main fuel filter so as to:

#172. On most transport jet aircraft, the low pressure pumps of the fuel system are supplied with electric power of the following type:

#173. The fuel crossfeed system:

#174. On most transport aircraft, the low pressure pumps of the fuel system are:

#175. On a jet aircraft fuel heaters are :

#176. During fuelling the automatic fuelling shut off valves will switch off the fuel supply system when:

#177. The cross-feed fuel system is used to :

#178. The fuel system boost pumps are submerged in the fuel ..

#179. The refueling in a transport jet aircraft is made ...

#180. The vapor lock is :

#181. The fuel system boost pumps are used to :

#182. The cross-feed fuel system enables:

#183. Fuel pumps submerged in the fuel tanks of a multi-engine aircraft are:

#184. Fuel dump systems are required:

#185. The maximum quantity of fuel that can be dumped with the jettisoning system is:

#186. The capacitance type fuel gauging system indicates the fuel quantity by measuring the:

#187. 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 :

#188. Fuses are rated to a value by :

#189. The difference between (1) a fuse and (2) a circuit breaker is:

#190. An aircraft electrical circuit which uses the aircraft structure as a return path to earth, may be defined as a

#191. When an ""open circuit"" occurs in an electrical supply system, the :

#192. If a current is passed through a conductor which is positioned in a magnetic field :

#193. A current limiter fuse in a DC generation system is used to :

#194. The true statement among the following in relation to the application of Ohm's law is :

#195. A condenser in parallel with breaker points will

#196. The connection in parallel of two 12 volt/ 40 amphours batteries, will create a unit with the following characteristics,

#197. The resistors R1 and R2 are connected in parallel. The value of the equivalent resistance (Req) so obtained is given by the following formula:

#198. If one of the 12 cells of a lead-acid battery is dead, the battery:

#199. In aeronautics, the most commonly used batteries are NiCd because...

#200. 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:

#201. The voltage of a fully charged lead-acid battery cell is :

#202. Batteries are rated in :

#203. When carrying out battery condition check using the aircraft's voltmeter :

#204. Connecting two 12 volt 40 ampere-hour capacity batteries in series will result in a total voltage and capacity respectively of :

#205. The capacity of a battery is expressed in terms of :

#206. A test to assess the state of charge of a lead-acid battery would involve :

#207. When a battery is almost fully discharged there is a tendency for the :

#208. Immediately after starting engine(s) with no other electrical services switched on, an ammeter showing a high charge rate to the battery :

#209. A relay is :

#210. A relay is :

#211. When a conductor cuts the flux of a magnetic field :

#212. A circuit breaker :

#213. Circuit breakers protecting circuits may be :

#214. A ""trip-free"" type circuit breaker is a circuit protection device which :

#215. In order to produce an alternating voltage of 400 Hz, the number of poles required in an AC generator running at 6000 rpm is:

#216. In a generator, the Constant Speed Drive (CSD):1- may be disconnected from the engine shaft.2- may be disconnected from the generator.3- is a hydro-mechanical system.4- is an electronic system.5- may not be disconnected in flight.6- may be disconnected in flight.The combination regrouping all the correct statements is :

#217. In an alternator rotor coil you can find :

#218. Assume a constant speed DC generator providing a constant output voltage. If the electrical load increases, the voltage regulator will :

#219. The essential difference between aircraft AC alternators and DC generators (dynamos) is that the:

#220. A feeder fault on a direct current circuit results from a flux unbalance between the:

#221. The detection of a feeder fault on a direct current circuit results in:1. automatic disconnection of the generator from the aircraft AC busbar2. opening of generator field current relay3. opening of the main relay of the generator breaker4. opening of balancing circuit connecting two generators5. lighting of an indicator lampThe combination of correct statements is:

#222. A DC generator fitted to a aircraft is cooled by :

#223. The voltage regulator of a DC generator is connected in :

#224. The output of a generator is controlled by :

#225. In order that DC generators will achieve equal load sharing when operating in parallel, it is necessary to ensure that :

#226. On-board electrical systems are protected against faults of the following type:1. AC generator over-voltage2. AC generator under-voltage3. over-current4. overspeed5. under-frequency6. undue vibration of AC generatorsThe combination of correct statements is :

#227. The frequency of the current provided by an alternator depends on...

#228. The function of the Generator Breaker is to close when the voltage of the :

#229. The so-called ""hot buses"" or ""direct buses"" are:

#230. The type of windings commonly used in DC starter motors are :

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