1. The fuel system boost pumps are used to:

2. Why is the capacitance-type fuel quantity gauge system the system that is most often used on large turbine aircraft?

3. An electrically activated and operated fuel valve is called a(n):

4. During fuelling operations

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

6. Fuel booster pumps are necessary in large aircraft:

7. 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:

8. A fuel system booster pump other than pumping fuel to the engine may also be used for:

9. How much fuel is required for a retained sample?

10. To indicate that a refuelling bowser carries JET Al aviation kerosene:

11. An aircraft using MOGAS:

12. The CROSS-FEED fuel system enables:

13. The refuelling in a transport jet aircraft is made...

14. On a jet aircraft, when installed, fuel heaters are:

15. The fuel tanks in small aircraft are mainly located:

16. The advantage of a capacitor type fuel contents gauging system is that the circuit:

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

18. The cross-feed fuel system is used to:

19. Special fuel consumption schedules during flight are designed due:

20. Fuel jettisoning is:

21. Prior to fuelling an aircraft, which of the following precautions must be carried out?

22. JET A1:

23. When refuelling a swept-wing aircraft, the order of filling the fuel tanks should be

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

25. A failed capacitance fuel contents gauge would:

26. The purpose of the barometric correction in a fuel controller is to:

27. On A/C with a fuel pressure gauge, where is the pressure normally measured? (Aircraft with fuel injection)

28. During refuelling operations:

29. If a fuel tank with a capacitive quantity system was filled with water instead of fuel, the gauge would indicate:

30. Adjustments may have to made to an aircraft's engine fuel system if it has been refuelled with JET B instead of its normal JET Al fuel, these adjustments are to cater for:

31. A one way check valve will:

32. What will be the effect on the indicated fuel contents if a capacitive system fuel contents gauge fails in flight?

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

34. AVTUR Jet A1:

35. Unusable fuel is:

36. What are the advantages of a Flexible Fuel Tank over an Integral Tank?

37. When baffles are fitted to aircraft fuel tanks, the purpose is to:

38. The fuel system boost pumps are submerged in the fuel :

39. In the event an APU is required to be running during fuelling operations, which of the following precautions must be observed?

40. Fuel is pressurized to:

41. The indications of a failure of the capacitive fuel indication system will be:

42. An integral type fuel tank is:

43. Waxing is:

44. How much fuel can be jettisoned?

45. The fuel required for a planned flight is 28,000kg. The fuel in the tanks is 24,000 litres (SG of the fuel is 0,8). The required fuel volume is:

46. While refuelling with passengers on board, when a loading bridge is in use:

47. The pressurization of tanks is maintained by the fuel

48. The pressure usually produced by the Boost Pumps (BP) of the fuel supply system is within the following range:

49. What is the ratio between the litre and the US gallon?

50. If the specific gravity of a fuel is known to be 0.7 the weight of 20 imperial gallons of that fuel would be:

51. From the statements below, which aircraft should have a fuel dumping system?

52. Baffles are fitted in aircraft fuel tanks:

53. Fuel is heated:

54. On an aircraft equipped with a compensated capacitance type fuel quantity indication system graduated to read in kg, the temperature increases just after the tanks are half filled with fuel. If the fuel expands by 10%, the gauges will show:

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

56. The Maximum Zero Fuel Weight:
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:

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

58. The automatic fuelling shut off valve:

59. Why are baffles fitted to aircraft fuel tanks?

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

61. Adjustment may have to be made to an aircraft fuel system if it has been refuelled with JET B instead of its normal JET A1 fuel. These adjustments are to cater for:

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

63. When checking the fuel for possible water content, the presence of water will be indicated by

64. The aircraft cannot be refuelled while:

65. AVTUR or JET A1:

66. An integral fuel tank:

67. The fuel cross feed valves are fitted in order to facilitate:

68. Capacitive fuel quantity measurement systems compensate for fuel movement in the tanks by:

69. Cloudiness of a sample of AVTUR is an indication of:

70. Refuelling with passengers on board is not permissible:

71. To what distance should a fuelling zone extend from a fuelling point or vent point?

72. Fuel tanks are vented so that:

73. The Low Pressure engine driven pump:

74. Fire precautions to be observed before refuelling are:

75. Fuel tank booster pumps are:

76. The colour of AVGAS 100 is:

77. Booster pumps as fitted in a fuel system are:

78. Un-dissolved water in a fuel sample:

79. The disadvantage of refuelling the aircraft to " tanks full" the night before a departure in the heat of the day is that:

80. Fuel dump systems are required:

81. During fuel jettison, the aircraft is protected against running out of fuel by:

82. When fuelling an aircraft, what action may be taken to reduce the build up of static electricity?

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

84. In a typical fuel/oil heat exchanger:

85. If a fuel sample appears cloudy or hazy, the most probable cause is:

86. The LP fuel pump is driven by:

87. In an aircraft low pressure refuelling system, what is fitted to prevent a fuel tank from becoming over pressurised?

88. In an aircraft low pressure refuelling system, what is fitted to prevent a fuel tank from becoming over pressurised?

89. Refuelling a fixed wing aircraft with passengers embarking is permissible:

90. AVGAS 100LL is:

91. Fuel stored in aircraft tanks will accumulate moisture. The most practical way to minimize this when a plane is used every day or so is to:

92. The vapour lock is:

93. The function of a feed box in the fuel tank is to:

94. The purpose of the fuel cooled oil cooler is to:

95. Baffles can be mounted inside the tanks to:

96. Drain cocks are fitted:

97. The fuel crossfeed system:

98. The flash point of a fuel is:

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

100. A fuel booster pump, which is used to provide positive fuel flow to the engine, can also be used for:

101. Fuel pumps submerged in the fuel tanks of a modern jet aircraft are:

102. In a compensated capacitance fuel contents system what happens to a fuel weight of 8000lbs if its volume increases by 5%?

103. VAPOR LOCK is the phenomenon by which:

104. The vent pipe of an aircraft's fuel tank must not become blocked because:

105. What pressure does booster pump supply fuel at?

106. When ice forms on the Vibrating Rod ice detector:

107. To prevent propeller elements overheating:

108. In flight airframe icing does not occur:

109. Regarding carburettor ice, state the environmental caution areas for the formation of this type of ice.

110. Freezing point depressant (FPD) is supplied in two types:

111. The ice protection for propellers of modern turboprop aeroplanes works:

112. The electrical supply to the propeller blades for de-icing purposes

113. The accurate method of removing snow and ice that has accumulated on the aircraft during parking, is:

114. 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:

115. Ice detectors are used primarily to warn the crew:

116. A typical electrical anti-icing/de-icing system would consist of the following components:

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

118. In order to prevent/eliminate ice build-ups on a pitot tube on light aircraft, the pilot can use:

119. Fluid is delivered to a propeller by:

120. When anti-icing fluid is applied to an aircraft, which of the following icing conditions would give the longest holdover times?

121. Modern Turboprop aircraft are anti-iced by which method

122. The electrical power which is supplied to the propeller blades for de-icing purposes:

123. Propeller electrical de-icing systems:

124. An aircraft is to be de-iced and then enter the line up for departure. Which de-ice fluid will have the best holdover time at 0° C with precipitation:

125. Generally, for large aeroplanes, electrical heating for ice protection is used on:

126. The probe heater operates:

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

128. The effect of frost on an aircraft:

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

130. Propeller blade heating elements are:

131. The hot rod ice detector:

132. When an aircraft is de-iced prior to departure, if the temperature is 0° C in precipitation, which type of fluid and application method will provide the longest holdover period:

133. The methods used to provide de-icing in flight can be:

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

135. Engine bleed-air which is used for pressurisation of the cabin is:

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

137. Which is the most suitable relative humidity for an environmental control system to maintain in an aircraft?

138. In an air cycle type air conditioning system, reduction of air temperature and pressure is achieved by:

139. A Vapor Cycle Cooling system may be fitted to enhance the cooling cycle of an aircraft air conditioning system. On leaving the evaporator, in the correct sequence, which components does the gas pass through?

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

141. The purpose of a spill valve in a cabin air supply system is:

142. The maximum differential pressure of a transonic transport category airplane is approximately

143. If the forward oil seal in an axial flow compressor fails, compressed air:

144. An ACM produces a drop in temperature by:

145. Inward vent valves operate when:

146. Cabin differential pressure is the pressure difference between

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

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

149. In level pressurised flight the outflow valve:

150. Typically, icing does not occur above about...

151. When an aircraft has reached a flight level where pressure differential is at its maximum, the pressure controller:

152. Cabin air for modern airplanes is usually taken from:

153. An air cycle cooling system uses the principle of:

154. A cabin humidifier is sometimes used:

155. The pressure relief valve operates

156. In a climatisation system, temperature control is achieved by:

157. 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 indication

Zc = Cabin pressure altitude

DELTA P = Differential pressure

This will result in a:

158. The term " pressure differential" can be defined as the pressure difference between:

159. Pressurisation control ensures that:

160. What must be isolated when carrying out a cabin pressurisation ground tests?

161. Essential information whether to use the engine anti-ice system or not, is?

162. A heat exchanger functions by:

163. Cabin altitude in pressured flight is:

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

165. 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 pressure

Zc = Cabin altitude

166. A humidifier is fitted to:

167. The aircraft inhibiting switch connected to the A/C landing gear:

168. Cabin altitude in pressurised flight is:

169. The function of an air cycle machine is to:

170. In normal operation, the maximum cabin altitude for a large passenger aircraft is:

171. With a gas turbine engine, should engine anti-icing be selected " ON" :

172. When taking off and when pressurisation is initiated, cabin rate of climb will show:

173. During a normal take-off and climb:

174. The power source for hot air in de-ice / anti ice systems on jet A/C is:

175. In a pressurized aircraft whose cabin altitude is 8000 ft, a crack in a cabin window makes it necessary to reduce the differential pressure to 5 psi. The flight level to be maintained in order to keep the same cabin altitude is:

176. Some pressure controllers have a ditching control. When activated:

177. Which statement is true about the pressurisation system?

178. Safety valves operate:

179. De-icer boots consist of layers of... and... between which are disposed flat inflatable tubes... at the ends.

180. Safety valves and inward relief valves operate:

181. The function of spill valves is to control:

182. The rate of change of cabin pressure should be kept to the minimum. Is this more important:

183. The pneumatic actuators are normally of the:

184. In a Bootstrap Bleed Air air-conditioning system, if the cabin temperature is reduced:

185. Cabin altitude means the:

186. The mass flow delivery from the engine driven mechanical compressors is controlled by:

187. Ditching Cocks are operated:

188. " Conditioned" air is air that has:

189. Rate of change of cabin altitude is shown on a:

190. If in cruise at 30000ft the cabin altitude is adjusted from 4000ft to 6000ft:

191. A turbo-fan cold air unit will:

192. A pneumatic de-ice system should be operated..

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

194. What controls cabin pressurisation?

195. If in flight a door warning light illuminates:

196. When would negative differential be exceeded?

197. In jet aeroplanes the 'thermal anti-ice system' is primarily supplied by:

198. With reference to a vapour cycle cooling system, which statement is correct:

199. Cabin differential pressure means the pressure difference between:

200. Choke valves in a mechanically driven cabin air compressor provide extra heating by:

201. The boots of a pneumatic de-icing system are normally made of:

202. To maintain a steady and constant airflow regardless of altitude or cabin pressure:

203. The term " pressurisation cycle" means:

204. After take-off during a normal pressurised climb:

205. On landing, the cabin pressure is equalized with atmospheric pressure by the operation of:

206. At maximum cabin differential pressure the:

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

208. At max differential phase, the discharge valve is:

209. State the function of a heat exchanger:

210. The cabin heating supply in a heavy jet transport aircraft is obtained from

211. If the cabin pressure increases in level flight, the cabin VSI shows:

212. A pressurisation circuit (normal operation) is designed so that the:

213. The pneumatic ice protection system is mainly used for:

214. An aircraft with pressurised cabin has maximum cabin altitude of 8000 feet, which equals 10.9 PSI. Present flight altitude is 30.000 feet, which equals 4.36 PSI. Pressure at sea level equals 14.7 PSI. Calculate the difference pressure that influence the cabin structure:

215. One advantage of a pneumatic system is:

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

217. The rate of change of cabin pressure should be kept to the minimum. This is more important:

218. Would you operate the flying controls during a cabin pressurisation ground test?

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

220. When pressurising the cabin of an aircraft, the cabin pressure controller operates the:

221. If an aircraft is descending, what will happen to the cabin pressure differential?

222. Most of the cabin pressurisation systems have two modes of operation:

223. If the discharge or outflow valve closes:

224. The air-cycle cooling system produces cold air by:

225. The main elements of a vapour cycle cooling system are?

226. During normal descent, the discharge valve (outflow valve) position is:

227. In a climatisation system, an air to air heat exchanger is provided to:

228. Assume that during cruise flight with air-conditioning packs ON, the outflow valve(s) would close. The result would be that:

229. The vapour cycle cooler works on the principle of changing:

230. In pressurised aircraft, temperature control is mainly achieved by:

231. Concerning the sequential pneumatic impulses used in certain leading edge de-icing 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:

232. What is the purpose of the duct relief valve?

233. Water collected by the water separator may be sprayed into the ram air duct. This has the effect of:

234. In an air conditioning system, a pack valve is used to:

235. In a bootstrap air cooling system the secondary heat exchanger:

236. Main cabin temperature is:

237. A typical MP pneumatic main system pressure would be:

238. The cabin altitude selector on the flight deck works in conjunction with:

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

240. A pressurisation system works by:

241.

The pneumatic system accumulator is useful:

242. In level pressurised flight does the outflow valve:

243. A drop in temperature by a cold air unit is produced by:

244. A cabin pressurisation system is often installed onboard turbine powered aircraft. If installed, it normally has:

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

246. The picollo duct is part of the:

247. The term " cabin pressure" applies when an aeroplane:

248. In a Bleed Air (Bootstrap) air conditioning system, where is the water extractor located?

249. If pressurisation is selected before take-off the cabin rate of change indicator indicates

250. The disadvantage of a HP pneumatic system when compared to a comparable hydraulic system would be:

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

252. Air for conditioning and pressurisation is taken from:

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

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

255. In which sequence does the refrigerant of a vapour cycle refrigeration system pass through the different components?

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

257. Assuming cabin differential pressure has reached the required value in normal flight conditions, if flight altitude and air conditioning system setting are maintained:

258. Which of the following statements are correct?

259. In level pressurised flight, the outflow valve:

260. In a turbo cooler system, the cooling air is:

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

262. The primary heat exchanger in a turbo-compressor cooling system: