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B737-300/500 System Review Questions

Airplane General Section 1

1. Is there a speed limit for the outboard landing lights?NO

2. Crewmember life vests can only be inflated using CO2 cartridges?False

3. Are the flashlights charged off the aircraft electrical system?NO

4. The nose wheel taxi light will automatically extinguish with gear retraction?False

5. What type classification are the cargo compartments?Class C

6. Where is the water tank located and how many gallons does it hold?Behind the aft cargo compartment, 20 gallons

7. How is the water system pressurized?Air from the APU or engine #1

8. Must the battery be on to illuminate the position lights?Yes

9. If normal electrical power is lost what cockpit lights will be available from the BAT BUS?Standby compassDome lightsFloodlightsWarning lights

10. Will the loss of one AC Bus remove all cabin lights?NO

11. When will the emergency lights illuminate automatically?28 volt DC bus #1 fails or the loss of AC power

12. Do the emergency lights charge in the ARM position?YES

13. Does the battery have to be on to read the crew O2 pressure on the flight deck?Yes

14. What is the approach category for the B-737?Category C except for Circling, which is Cat D

15. Which B-737’s are approved for ETOPS?700-800-900 series

16. What is the maximum runway slope?+/- 2%

17. What is the maximum takeoff tailwind component?10kts

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18. What is the maximum operating altitude?37,000’

19. What is the maximum takeoff / landing altitude?8,400’

20. What are the maximum flight operating latitudes?73 degrees north and 60 degrees south

21. What is the minimum quick turn time should the landing weight exceed the charted value?53 minutes then check the thermal plugs

22. What is the maximum severe turbulent air penetration speed?Climb and descent 280kts or .73MCruise TURB N1 settingIf severe turbulence is encountered below 15,000’ and below max landing weight the airplane may beslowed to 250kts

23. What is the indication for an un-locked cargo door?FWD / AFT cargo door annunciation light and master caution

24. How many Megaphones are installed on the 737?2

25. If a passenger cabin PSU O2 compartment fails to open can it be opened manually?YES

26. How can you shut off the O2 to the crew mask when it is not stowed in the box?Close the left side stowage door and slide the test/reset switch

27. What is the maximum tire speed?195kts

28. What is the recommended crosswind component?Takeoff 35ktsWet runway 23ktsSlush 16ktsSnow covered 21kts

29. When are rolling takeoffs recommended?When crosswinds exceed 20kts

30. What is the recommended crosswind component for landing?Dry 35ktsWet 35ktsSlush 20ktsSnow covered 35kts

31. How many portable Oxygen bottles should be on board?At least one for each flight attendant

32. How long will the passenger O2 generators last?12 minutes and cannot be shut off

33. How long will the PBE provide O2?15-30 minutes depending on the users work rate

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34. What is the operating life of the emergency radio beacon? Where is it located?100 hoursJust inside the main cabin door opposite the flight attendant jump seat

35. Which lights are not tested during the lights test?Marker Beacon A/T A/PNAV/COMM frequencies Fire relatedTransponder code MCP lightsClock LCD

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Air Systems Section 2

36. Where does external air enter the pneumatic manifold?Right of the isolation valve

37. How is potable water pressurized?From the left side of the pneumatic manifold

38. On the ground what is the proper indication of the Ram Door position lights?RAM DOOR FULL OPEN lights illuminated

39. When are the RAM DOOR FULL OPEN lights extinguished?In-flight or flaps fully retracted

40. Illumination of the DUCT OVHT means what?Duct has over heated and mix valves are driven full cold

i. Requires a reset

41. What’s the maximum differential pressure allowed by a pressure relief valve?8.65psi

i. 2 pressure relief valves installed

42. What’s the maximum takeoff differential pressure?.125psi

43. Where is the main outflow valve located?On the belly of the aircraft aft of the main cargo compartment

44. Where are the pressure relief valves located?2 located on either side of the main outflow valve

45. What does the PACK TRIP OFF light indicate?An overheat condition exists in the cooling cycle of the pack; causes pack valve to closeautomatically. Mix valve will then drive to full cold

46. What does the left WING BODY OVHT light indicate? What about the right?There’s a leak in the bleed air duct

i. LEFT: L engine strut, L inboard wing leading edge, L air conditioning bay, keel beam,or bleed duct from APU

ii. RIGHT: R engine strut, R inboard wing leading edge, R air conditioning bayiii. WING BODY OVHT cannot be reset

47. With one pack not operating, when will the other pack automatically switch to HIGH AIRFLOW?In-flight with flaps up

48. AUTO FAIL light indicates what?DCPCS CPCS

i. Loss of DC power i. Loss of auto AC powerii. Controller fault ii. Excessive rate of cabiniii. Excessive rate of cabin pressure change +/- 1800 ft/min pressure change +/- 2000 ft/min iii. High cabin altitude 13,875’iv. High cabin altitude 15,800’

49. When is the limitation on the DUAL BLEED light?When the APU and engine bleeds would permit a possible backpressure to the APU

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50. What powers the isolation valve?AC power

51. When does the FWD outflow valve close?When the recirculation fan is operating

52. How is engine bleed air temperature regulated?Engine fan air is ducted through the pre-cooler at a rate determined by the thermostatic pre-coolervalve

53. How many packs can the APU power on the ground? In-flight?2 packs on the ground (only for heating) 1 pack in-flight

54. A temperature higher than the DUCT OVHT causes the appropriate pack valve to close andilluminate what light?Pack Trip off light

55. What powers the recirculation fansAC

56. What aural warning on the ground indicates an overheat in the E & E compartment?Call horn in the nose wheel well

57. When does the flow control valve open in-flight?. Un-pressurized. Pressurized with the cabin differential less than 2.5psi

58. How is the engine start valve powered?DC battery bus

59. What does the pressurization controller sense?Only psi

60. How is the DCPCS (digital cabin pressure controller system) outflow valve operated?Brushless DC motor

61. What schedule does the pressurization controller follow cabin altitudes?<28,000’ 7.45>28,000’ 7.8

62. What is the maximum differential pressure?8.65psi

63. What is the maximum cabin differential pressure for takeoff / landing?.125psi

64. What limitation is placed on when engine bleeds are on and the operation of both packs on high?Not for takeoff and landing

65. Duct pressure for max cooling is what?20-25psi

66. Minimum duct pressure for two-pack operation from one bleed source?20-25psi

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Anti-ice and Rain Section 3

67. What does an illuminated COWL ANTI-ICE light indicate?High pressure or high temp in the duct from the cowl anti-ice valve to the cowl lip

68. What does a dim WING ANTI ICE VALVE OPEN light indicate?Respective wing anti-ice control valve is OPEN with the switch selected ON

69. The engine anti-ice system does what?Heats the engine inlet cowl

70. Engine anti-ice valve is controlled and operated by?Electrically controlled and pneumatically operated

71. What is indicated when the engine anti-ice valve fails OPEN?The COWL VALVE OPEN light remains bright blue indicating a disagreement between switchand valve position, and an amber TAI indication illuminates on the CDS after a short delay

72. How many TAT probes are installed on the 737?One

73. Is the alternate static source heated?NO

74. How many pitot tubes are there?6

75. What does the amber light mean on the pitot static panel?Not heated

76. On the ground when throttles are advanced to take off power and the wing anti-ice is selected on,the wing ant-ice valves close.TRUE, the switch must be cycled off then back on above 800’ AGL or acceleration height,whichever is higher

77. What are the icing limitations for climb and descent?Must be on for all operations when icing conditions exist or are anticipated except during climb orcruise when the temperature is below –40C SAT

78. What part of the wing does the wing anti-ice heat?Slats

79. What windows in the cockpit are not heated?3 L/R

80. How long must window heat be on prior to takeoff?10 minutes

81. When do icing conditions exist?OAT on the ground or TAT airborne is below 10C AND in visible moisture (less than one mile onthe ground), or standing water, ice, slush, or surface snow exists

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82. When must engine anti-ice be on?. All ground operations in icing conditions. All flight operations in icing conditions, except climb and cruise below -40C SAT. Prior to and during descent in all icing conditions. Engine ignition must be selected to CONT prior to and during anti-ice operations

83. When must wing anti-ice be selected ON?. All ground operations between engine start and takeoff when icing conditions exist. Do not operate wing anti-ice on the ground when OAT is above 10C. Do not use wing anti-ice as a substitute for de-icing / anti-icing

84. When must wing anti-ice not be used?During takeoff below 800’ AGL or acceleration height, whichever, is higher.

85. What is the source of bleed air for wing anti-ice?Pneumatic manifold after engine bleed valve

86. What happens when either thrust lever is moved beyond the takeoff-warning threshold with winganti-ice operating on the ground?. Both wing anti-ice valves close, but the switch remains on. Light turns bright blue

87. When should the wipers not be used?On a dry windshield

88. When must the window heat be selected on?10 minutes before takeoff

89. When must pitot heat be on?Prior to takeoff

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Auto flight Section 4

90. What will cause an A/P (auto pilot) to disengage?. Pushing either A/P disengage switch . Trim switch. TO/GA switch with a single A/P . Stab Trim A/P cutout switch engaged below 2000’ RA . Either IRS system fail or. TO/GA after touchdown with both FAULT light illuminated

A/P in CMD . Loss of electrical power. Pushing A/P engage switch . Respective HYD system

91. Which mode is FD mode and not A/P mode?Takeoff

92. Only one A/P can be engaged at a given time unless APP mode is engaged.TRUE

93. During pre-flight, the bank angle is set to 25 degrees. What does this affect?The VOR and HDG SEL only

94. What mode allows both A/P’s to be engaged?APP mode

95. At what speed is the A/T mode annunciated THR HOLD?84kts

96. When does the A/T disengage after landing?2 seconds

97. What is the minimum altitude for A/P engagement (climb and cruise)?1000’ AGL

98. Does the F/D have landing flare capability?NO

99. In normal operation the FMC provides the A/T system with what limitations?N1

100. On takeoff when does the F/D command 15 degrees nose up?64kts

101. What is displayed on the MCP display window when VNAV is engaged?Nothing

102. A/T is available with FD________or A/P on or off.ON or OFF

103. How is a single channel, speed trim fail condition recalled?Push either MASTER CAUTION annunciator panel

104. What action is required to stop a runaway stabilizer trim?Move control column in opposite direction of runaway trim, which removes power to A/Ptrim switch and stab trim

105. When does the main electric trim move faster?With flaps extended

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106. During cruise in A/P A, how do you select A/P B?Select B and A will automatically trip off

107. What mode engages automatically when ALT ACQ engages and a new MCPaltitude is selected?

VS

108. What does VOR consider when capturing a selected course?Closure rate and intercept angle

109. During take off with the F/D in TO/GA mode below 400’, roll commands what?Maintains wings level

110. When is the F/D GA mode armed?Below 2000’ AGL

111. What is the initial F/D GA pitch command during a two engine missed approach?15 degrees nose up

112. Is an A/P go-around available in a single A/P mode?NO

113. What is displayed on the IAS/MACH display on a F/D go-around? SE go-around?Goes blankDisplays target speed

114. On takeoff when does the A/T annunciate THR HLD?84kts

115. After takeoff the A/T remains in THR HLD until when?What does it change to?400RA and 18 secondsARM

116. For coupled singled channel approaches with electronic glide slope when mustthe A/P be selected off?Below 50 AGL

117. May the aileron trim be used with the A/P engaged?NO

118. What flap settings are approved for AUTOLAND?30 and 40 with both engines operative

119. What are the allowable headwind / crosswind / tailwind components for the useof AUTOLAND?25 /15 /10

120. May the AUTOLAND be used for over weight landings?Should not be

121. May the A/P or A/T be used for approach if the respective RA is inoperative?NO

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Communications section 5

122. FA’s talk to pilots over what?The service interphone. Pilots communicate with each other on the flight interphone and toMX through a jack on the external power panel

123. What frequency should be avoided on VHF COM #2 or #3?120.0 MHZ

124. Which is correct for the MASK position of the MASK-BOOM switch?Allows transmission over O2 mask’s microphone

125. Where is the flight recorder located?Behind an access door in the in the aft cabin ceiling

126. CVR is powered by?115V AC. 30-minute loop

127. The service interphone must be on for the pilots to communicate with theF/A’sFalse, maintenance uses this switch

128. When should VHF #3 not be used for ATC communications?ACARS or audio entertainment system in use

129. What frequency should not be used for primary communications on COMM #2and #3120.0 MHZ

130. How many COMM radios are there?3, (#3 used for ACARS, but can be used to transmit by putting freq into ACARS)

131. What information does the flight recorder on the 737-300’s need?Flight# and date

132. What does the TEST switch do for the flight recorder?Bypasses oil pressure requirement and fakes that the aircraft is airborne

133. Where is audio heard when ALTERNATE position on audio panel is selected?Receives audio on headset only

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Electrical Section 6

134. What is the function of the AUTO position of the STBY PWR switch with a loss of allgenerators? 6.6.21Allow the BATT BUS to be the source of power for both busses INFLIGHT.

135. How is the failure of the TR1 indicated with TR3 disconnect relay closed?0 amps on the DC ammeter at TR1 position

136. What is the function of the OFF position of the BUSS XFR switch?Prevents closing of the BUS XFR relaysi. Also opens the TR3 disconnect relayii. Isolates the transfer busses

137. What is the normal power source for TR1 & TR2?AC XFR BUS

138. What is the normal source of power for the BAT BUS?TR3

139. On the ground alternate power for the STBY BUS requires:STBY POWER switch on BAT position.

140. The GROUND SERVICE BUS is located where?Forward F/A panel

141. Normal source of power for the AC XFER BUS?Respective GENERATOR BUS

142. How does the TR3 disconnect relay function during an AP of FD ILS approach?The relay opens at glide slope capture. This isolates the DC BUSSES to prevent a single failurefrom affecting both navigation receivers and flight control computers.

143. How is the failure of TR1 indicated with the TR3 disconnect CLOSED?Will indicate 0 amps on the DC meter at the TR1 position

144. What is the alternate source of the BAT BUS?Hot BAT BUS

145. CSD warning lights indicate what?An electrical problem

146. What is the function of the AC ground service BUS?Cabin lighting and battery charging

147. If either the DC BUS 1 or #1 XFR BUS loses power, when will the respective standby bussesautomatically switch to the BAT BUS?In flight only

148. What CB’s can you not reset?Fuel boost pumps – LAV motor – Fuel Quantity

149. All power sources to a GEN BUS must be connected manuallyTRUE

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150. GEN BUS 1 or 2 OFF illuminated indicates what?The GEN BUS is not being powered

151. What busses are powered from the battery following a loss of all generators?BAT BUSHOT BAT BUSSwitched HOTT BAT BUSAC standby BAT Bus through the inverter

152. What is the maximum engine driven generator load?125 AMPS

153. What is the maximum TR load?65 amps / 50 amps on the ground without cooling

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Engines and APU Section 7

154. What is the AUTO function of the PMC during climb?Maintains initial N1 climb thrust.

155. What electrical power source is required for APU start?Aircraft battery

156. Turning the BAT switch off in-flight will cause the APU to shutdownFalse…only on the ground.

157. When is starter cutout?46% N2 RPM

158. What is the maximum engine start EGT?725

159. What are the respective N1 high and low settings?High 32%Low 22%

160. Engine must be shut down if OIL TEMP exceeds?165

161. What powers the fuel cross-feed valve?BAT BUS

162. With the BATT switch on, 23 volts, and APU switch set to START, there is no DC ammeterdeflection for one minute. What should you do?. Select the APU switch OFF for 20 seconds and try again. Shutdown cycle wasn’t completed on the previous flight because the BAT switch was turned off before the shutdown sequence finished.

163. Will turning the BAT switch to off cause the APU to shutdown?Ground -YesIn-flight - No

164. When is the yellow band on the OIL Pressure valid?With takeoff thrust

165. What causes the APU over-speed light to illuminate?APU RPM exceedsAborted APU start prior to reaching operating speedOver-speed test failure during APU shutdown

166. With the engine at normal operating idle and temperature the oil pressure must be?Above the red radial line

167. What does the REVERSER light indicate when on?The isolation valve or the thrust reverser control valve is not in the commanded position. Or thethrust reverser sleeve position sensors are I disagreement for more than 2 seconds. Or the auto-stow has been activated (usually lasts 10 seconds)Reverser commanded to stow and isolation valve did not close in 12 seconds then light illuminatesindicating a malfunction has occurred.

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168. What does the LOW IDLE light indicate in-flight?You should be in high idle and your not. Always in high idle in-flight and changes to low idle 4seconds after touchdown.

i. Either engine speed below 25% N1 in-flight

169. How do you start the number one engine with external air?Open the isolation valve

170. When is high idle reduced to low idle?4 seconds after touch down

171. What powers the ground position of the engine start switch?DC power from the battery bus

172. How are the thrust reversers powered?Hydraulically

173. When should the ignition be switched to flight?Air-startsSevere turbulenceModerate to severe icingHeavy precipitation or Hail

174. How are the igniters powered?Right – AC Standby busLeft – AC transfer bus

175. How is engine oil cooled. Fuel flow

. Fuel oil heat exchanger

176. What is the APU max EGT?760 C

177. What is the APU max continuous EGT?710 C

178. What is the maximum altitude the APU may power a bleed and electrical?10000’

179. What is the maximum altitude that the APU may power a bleed?17,000’

180. What is the maximum altitude that the APU may power electrics?35,000’

181. What is the maximum operating altitude for the APU?35,000’

182. How many aborted starts are permitted for the APU on the Ground?2 start attempts4 minutes between starts

183. How many aborted starts are permitted for the APU in-flight?4 start attempts maximum4 minutes between starts

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184. Above what altitude is successful APU starts not assured?25,000’

185. May reverse thrust be used in flight?NO

186. May takeoffs with assumed temperature reduced takeoff thrust be made with anti-skidinoperative?NO

187. When must engine ignition be onTake offLandingEngine anti-iceHeavy Rain

188. What is the maximum N1?106%

189. What is the maximum N2?105%

190. What is the maximum EGT for takeoff? (5 min)930C

191. What is the maximum EGT for takeoff? (Transient 20 seconds)931-940C

192. What is the maximum EGT for MAX CONT?895C

193. What is the maximum EGT for START?725C

194. What is the minimum oil pressure?13psi

195. What is the maximum oil temperature?165C

196. What is the maximum continuous oil temperature?160C

197. What is the maximum allowable oil temperature 15 minute limit?160-165C

198. May takeoffs with assumed temperature reduced thrust be made with PMC in OFF mode?NO

199. What limitations are placed on the PMC’s for takeoff?Either both must be ON or OFF

200. May takeoffs with assumed temperature reduced thrust be made with EEC in alternate mode?NO

201. What mode must the EEC’s be in for takeoff?ON or ALTERNATE

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202. What is the minimum duct pressure for engine start?30psi at sea level decreasing 1/2psi per 1000’ above sea level

203. What is the starter duty cycle for engine starts?2 minutes on, 20 seconds off (first 2 starts) 3 minutes cooling required before 3rd and subsequentconsecutive starts

204. Minimum oil quantity before engine start is?3 gallons

205. At what temperature must the engine remain in idle for 2 minutes prior to changing thrust leverposition?-35C

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Fire Protection Section 8

206. What happens when the fire handle is pulled?. Closes main fuel shutoff Valve. Closes engine bleed air valve. Trips generator. Shuts off engine driven hydraulics. Disables thrust reverser. Arms fire bottle squib

207. How is the cargo compartment smoke detection system and extinguishing system powered?HOT BAT BUS

208. What does an illumination of the fire control panel FAULT lights indicate when no fire test isbeing performed? Both loops on one engine have failed in the dual loop position OR the selected single loop on an engine has failed

209. Which describes the wheel well fire warning system?#1 AC XFR BUS powers the single loop

210. What are the power sources for the engine fire detection and fire extinguishingBAT BUS – HOT BAT BUS

211. In flight what happens if a single engine fire loop fails during DUAL loop operation?The loop is automatically deselected and the fire warning capability is not lost on that engine.Goes into single loop operation.

212. Where are the discs for the APU fire bottle located?Yellow / Red, aft right side of fuselage

213. Bottle discharge light indicates what?Bottle has discharged

214. APU fire on the ground sends what signal to the wheel well?Intermittent horn and blinking red light

215. What five lights are on the fire fault test?MASTER CAUTIONOVHT/DET annunciatorFault lightAPU DET INOP

216. What powers the fire bottle squibs?HOT BAT BUS

217. Will fire fault lights set off the Master Caution?NO

218. In a dual loop operation, what does the fault light mean?Both loops have failed

219. Is there a fault light for the wheel well loop?NO

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220. What time limit is placed on landing at the nearest suitable airport after activation of the cargosuppression system?60 minutes

221. When must the cargo compartment smoke detector and fire suppression system be verified to beoperational?Before carrying cargo

222. What is the engine fire extinguishing system pressure?800psi at 70F

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Flight Controls Section 9

223. Which statement is correct for the Mach Trim operation?Operates automatically above .615 Mach, moves the elevator

224. What is the function of the STAB TRIM CUTOUT switch?Shuts off the AP and MAIN ELEC TRIM motors

225. YAW DAMPER uses what hydraulic system?System B, and provides rudder deflection commands and turn coordination

226. Speed brakes in-flight: (limitation) Not to be used at RA less than 1000’ or with flaps beyond 15 degrees

227. What senses TE Flap asymmetry?TE FLAP position indicators. No asymmetry protection through alternate electrical

228. What ways will give you Standby Rudder?By manually selecting the STBY RUD; or positioning the Alternate flaps master switch to arm;or automatically when there’s a loss of system A or B with flaps extended and airborne; or wheelspeed greater than 60kts

228. When do the flight spoilers extend on landing?Main wheel spin up

229. When do the ground spoilers extend on landing?On right main gear compression

230. When will all spoilers extend automatically if takeoff rejected?After wheel spin up to 60kts

231. How do you know if a single channel of the SPEED TRIM has failed?Press RECALL

232. The amber LE flaps transit light on the forward instrument panel is inhibited when the auto-slatsystem is moving the leading edge slats?TRUE

233. What happens at touchdown with all spoiler panels deployed and either throttle is advanced?Speed brake lever moves to the DOWN detent, ground and flight spoilers retract

234. Approaching a stall angle of attack, what does the Auto Slat system do?Automatically goes to FULL EXTEND position with TE FLAPS 1 – 5 degrees

235. What’s the maximum flap extend altitude?20,000’

236. What’s the Mach limit with the MACH TRIM FAIL light illuminated?.74 Mach

237. What does the FEEL DIF PRESS light indicate?The elevator feel computer sense either hydraulic system, or elevator feel pitot system fails,resulting in a differential pressure.

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238. What does the MACH TRIM FAIL light indicate?Dual channel failure. Can be single channel failure but will only illuminate when master cautionannunciator RECALL is activated. (Above .615 mach trim is working, if inop limited to .74M)

239. When does the elevator differential light deactivate?When flaps are extended

240. If the B flight control switch is moved from FLT to STBY, what does this do?. Opens up the STBY pump. Isolates the B system. Operates the STBY PUMP

241. The flight control low-pressure light illuminates while the STBY HYD pump is on; what doesthis mean?STBY pump is not getting pressure

242. What is the maximum flap extension altitude?20,000’

243. May the speed brake lever be extended beyond the flight detent?NO

244. What are the flap limit speeds?1-230, 2-230, 5-225, 10-210, 15-195, 25-190, 30-185, 400158

245. What is the maximum airspeed for alternate flap operation?230kts

246. When should the speed brakes not be deployed?RA below 1000’Flaps extended beyond 15 degrees

247. What are the speed limits of the Mach Trim Fail?280kts / .74Mach

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Flight Instruments Displays Section 10

248. When the CA has the FD with VOR LOC selected and the A Autopilot engaged, where is hegetting his signal from?. #1 VHF NAV radio, the FO with B autopilot engaged would be using #2 VHF NAV radio

249. What information does standby attitude indicator display?. Raw data only

250. Where does the Captains EADI get its information?Left IRS. Powered by AC STBY BUS

251. What is the maximum difference between CA and FO altitude displays for operation in RSVM?. 200’

252. What is the static source for the standby altimeter?. Alternate static source

253. Where does the IVSI get its information on the 737-500 EFIS. Respective IRS

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Flight Management NAV Section 11

254. Which AT modes allow the levers thrust levers to be repositioned manually?. ARM, THROTTLE HOLD

255. During takeoff with the FD in TO/GA mode, below 400’, roll commands will maintain wingslevel?. TRUE

256. What will TO/GA mode do for your heading during a go around?. Will give the last heading to maintain the ground track from the previous approach attempt.

257. What A/T thrust is generated during a FD go around when TO/GA is pressed once?. Reduced N1 and 1000 – 2000 fpm climb, pressed twice MAX go around power.

258. When does FMC speed mode engage?. VNAV

259. What info is lost and cannot be restored when in-flight and alignment of an IRS is lost?. Present position

260. How long will the R IRS operate on BAT power?. 5 minutes

261. Can the crew update the IRS in-flight?. NO

262. Left IRS is powered how?. AC STBY BUS

263. IRS performance uses what?. Latitude only

264. If you lose IRS in-flight do you lose TRACK and GROUND SPEED information?. YES

265. ON DC light during initial alignment means what?. It’s doing a DC power test, temporarily from the SWITCHED HOT BAT BUS

266. What does the Fault light indicate on the IRS panel?. A system fault, which affects the respective IRS ATT and / or NAV modes, has been detected.

267. What does the DC fail light mean?. Back-up DC power is not available

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Fuel Section 12

268. What does a dim FUEL VALVE CLOSED light indicate?. Valve and switch agree. Fuel shutoff valve is closed

269. What assures that the center tank fuel is used before the main tank fuel with all boost pumpsoperating?. The center tanks check valves open at a lower differential pressure than the check valves in the #1 and #2 main tanks.

270. Auxiliary Fuel tanks feed first because?. It has higher pressure boost pumps

271. Which tanks can suction feed? What about loss of all generators?. Tank #1 to Engine #1 and Tank #2 to engine #2, same with loss of all GEN

272. If there’s no AC power on GEN BUSSES, the center fuel tank is no longer usable?. TRUE

273. Will there be a MASTER CAUTION for one FUEL LOW PRESS light in the #1 fuel tank?. No, will be indicated when recall is pushed.

274. How is the main fuel shutoff valve closed?. Fire Switch. Start lever cutoff. The valves are DC powered from the HOT BAT BUS

275. Minimum fuel tank temperature in flight when the freezing point of the fuel in the tank is -53Cis what?. -45C

276. What is the maximum fuel tank temperature?. 49C

277. What is the minimum fuel tank temperature in-flight?. At least 3 degrees above the freezing point of the fuel being used or –45C whichever is higher.

278. What is the maximum random fuel imbalance?. 1000lbs

279. When must the fuel cross feed be in the OFF position?. Takeoff and landing

280. When must the center tank pumps switches not be placed in the ON position?. Below 1000lbs in the center tank except when de-fueling or transferring fuel. When both center FUEL PRESSURE lights illuminate. Personal are NOT available on the flight deck to monitor the low-pressure lights

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281. Must the center tank quantity gauge be operational to dispatch a flight with fuel in the centertank?. YES

282. What figure is used for fuel density?. 6.7lbs per gallon

283. May a fuel pump circuit breaker be reset if tripped?. NO

284. Where is the fuel tank temperature sensor located?. Left side fuel tank

285. What are the quantity of the wing, center, and aux fuel tanks?. 10,043lbs. 15.497lbs. 2620lbs

286. What do the fuel quantity indicators indicate?. Usable fuel

287. What is the minimum fuel required to be in each wing tank for operation of electric hydraulicpumps?. 1,676lbs

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Hydraulics Section 13

288. A leak in the engine driven #2 HYD pump will drain the B system.. FALSE

289. What would be the first indication of a leak in the STBY hydraulic system?. System B quantity decreases

290. Alternate brakes are on what system?. System A

291. With a loss of hydraulic system A, the FEEL DIFF PRESSURE light illuminates. The elevator-feel system is operative?. TRUE

292. How is the hydraulic fluid cooled? Is there a limitation?. Fuel. Minimum for ground operations of electric pumps is 1676lbs in the related tank

293. What action would extinguish an engine driven HYD LOW PRESS light?. Start the engine. Pull the respective engines fire switch

294. When is the STBY HYD LOW PRESS light armed?. When the standby pump has been selected or automatic standby function is activated

295. When is the STBY HYD LOW QUANTITY light armed?. Always

296. When does the STBY HYD come on?. Positioning either FLT control switch to STBY RUDDER. Positioning either ALT flaps master switch to ARM. Loss of SYS A or B HYD and flaps extended airborne, or wheel speed greater than 60kts

297. When are ground spoilers available?. Right main gear compression

298. PTU is driven by hydraulic pressure from system ( A ) and uses fluid from system ( B )

299. What’s the power source for the system B ELEC 1 HYD PUMP? System A?. GEN BUS #1. GEN BUS #2

300. What’s the first indication of a leak in the STBY hydraulic system?. The LOW QUANTITY light illuminates as the standby reservoir’s quantity decreases to zero. The system B level decreases and stabilizes at the standby interconnect line level (64%)

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301. What items are on the A hydraulic system? 302. What items are on the B system?. Ailerons . Ailerons. Rudder . Rudder. Elevator and Elevator Feel . Elevator and Elevator Feel. Autopilot A . Autopilot B. Landing Gear . Landing Gear Transfer Unit. Ground Spoilers . Trailing Edge Flaps. Inboard Flight Spoilers . Outboard Flight Spoilers. Alternate Brakes . Yaw Damper. Normal Nose Wheel Steering . Normal Brakes. Thrust Reverser #1 . Alternate Nose wheel Steering. Power Transfer Unit . Leading Edge Flaps and Slats

. Auto Slats . Thrust Reverser #2

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Landing Gear Section 14

304. How is wheel rotation stopped during gear retraction?. Mains by hydraulic braking. Nose wheel by snubbers

305. Auto Brakes may be disarmed after landing by? . Apply manual brakes, advancing thrust, moving speed-brake lever down.

(Note: except in the first 3 seconds)

306. Which situation would cause ANTI-SKID INOP?Fault in the parking brake system

. System malfunction or disagreement between parking brake lever and the parking brake shutoff valve

307. In cruise Brake Pressure reads 0psi, system B pressure reads 3000psi, B quantity reads full, what’swrong?

. Loss of Brake Accumulator Pre-charge

308. What occurs during a rejected takeoff if between 60-90kts?. Auto brake disarm light illuminates, use of manual brakes is now in effect

309. How do the Alternate Brakes engage?. Automatically

310. What does the illumination of the tire screen light indicate?. Tire screen is not secure

311. When the Aircraft is being towed, the _______ should be OFF or a steering lockout pininstalled.

. System A pressure

312. How does the landing gear transfer unit work?. Automatically when engine #1 fails. Airborne, gear handle UP, either main LDG not up, engine #1 RPM drops below limit value

313. When do you use accumulator pressure for braking?. Loss of A and B systems

314. In-flight, with the landing gear up, retarding one of the throttles to idle will cause the redGEAR lights to illuminate?

. TRUE

315. When are AUTOBRAKES available?. Only on system B

316. If both hydraulic systems are lost what will the tire pressure indicator read?1000psi

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317. Must we use RTO brakes if available?YES

318. When does the PTU come on? (Operates Auto Slats and LE Flaps). Airborne. System B hydraulic pressure drops below limits. Flaps are less than 10 degrees but not up

319. What are the limitations for Gear operation?. Retract 235kts. Extend 270kts/.82 Mach. Extended 320kts/.82 Mach

320. Must the AUTO BRAKES be used on every takeoff if operable?. YES

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Warning Systems Section 15

321. How is the GPWS glide slope deviation alert inhibited?. Press either BELOW G/S light when in the soft warning area

322. What are the stall warning components?. 2 computers and 2 shakers

323. How is the crew alerted if the cabin pressure altitude is >10,000’?. Intermittent horn (same as takeoff CONFIG warning!)

324. Wind shear aural warnings take precedence over other GPWS warnings?. TRUE

325. Can ILS soft warnings be cancelled pushing the G/S inhibit switch?. YES

326. What sets off the CONFIG warning?. Speed brake lever, TE Flaps, LE Flaps, Trim, Parking brake

327. May the terrain display be used for navigation?. NO

328. When are takeoffs with forward looking predictive wind shear warning alerts permitted?. NEVER

329. What are the limits of the clacker?. 340kts until 26,000’. .82 Mach above 26,000’

330. Name three ways to get the wheel well call horn in the nose wheel well:. IRS on DC power draining the battery. E&E compartment overheat. Press the ground call button

331. When does the Altitude acquisition alert activate?. 900’ before reaching the selected altitude. deviating more than 300’ from the selected altitude

332. When does the predictive wind shear mode operate automatically?. Below 1500’ AGL. One engine running. Transponder not in OFF or STBY

333. When will you get wind shear warnings on takeoff?. Below 90kts

334. What annunciations will cabin altitude above 10,000’ give you?. No lights, intermittent horn only

335. When can the MACH/AIRSPEED and stall warning systems be tested?. Only on the ground

336. When is the use of terrain awareness and terrain display functions prohibited?. When FMC is in IRS only operation, for takeoff if position verification has not been completed, when within 15NM and approaching to land at an airport not in the EGPWS terrain database.