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Boeing 737 · Electrical 题库（177 题）

Boeing 737 机型「Electrical」相关知识共 177 道题。想练习或模拟考试，请到 题库 · 模拟考试。
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1.The STANDBY PWR OFF light (amber) illuminated means one or more of the following are unpowered

  1. Battery Bus, AC standby bus, DC standby bus ✓
  2. AC standby bus, DC standby bus
  3. AC standby bus
正确答案：Battery Bus, AC standby bus, DC standby bus　·　737　·　来源 b737.org.uk

2.Generator Drive Disconnect switch when operated

  1. Disconnects the Generator Drive from the engine in the event of a Generator Drive malfunction. ✓
  2. Disconnects the Generator Drive from the generator in the event of a Generator Drive malfunction.
  3. Disconnects the Generator Drive from the engine in the event of a Generator Drive malfunction, only if the engine has been shut down first.
正确答案：Disconnects the Generator Drive from the engine in the event of a Generator Drive malfunction.　·　737　·　来源 b737.org.uk

3.Recoupling of the Generator Drive drive shaft to the engine may be accomplished

  1. At any time on the ground or in flight.
  2. At any time in flight provided the Generator Breaker and the Generator Control Relay have previously been tripped.
  3. Only on the ground. ✓
正确答案：Only on the ground.　·　737　·　来源 b737.org.uk

4.After operating the Generator Drive Disconnect switch the Generator Drive HIGH OIL TEMP (if illuminated) will

  1. Flash repeatedly indicating successful Generator Drive uncoupling.
  2. Immediately extinguish as the power to the light comes from the Generator Drive Disconnect Switch.
  3. Remain on, until the Generator Drive oil has cooled. ✓
正确答案：Remain on, until the Generator Drive oil has cooled.　·　737　·　来源 b737.org.uk

5.The Generator DRIVE lights are caused by

  1. IDG failure, engine shutdown, IDG automatic disconnect due to low oil pressure or IDG disconnected through generator drive DISCONNECT switch.
  2. IDG failure, engine shutdown, IDG automatic disconnect due to high oil temperature or IDG disconnected through generator drive DISCONNECT switch. ✓
  3. IDG failure, engine shutdown, IDG automatic disconnect due to low oil quantity or IDG disconnected through generator drive DISCONNECT switch.
正确答案：IDG failure, engine shutdown, IDG automatic disconnect due to high oil temperature or IDG disconnected through generator drive DISCONNECT switch.　·　737　·　来源 b737.org.uk

6.One of the basic principles of the electrical system is

  1. The AC sources of power can be connected in parallel if necessary.
  2. The AC sources of power are always connected in parallel.
  3. There is no paralleling of the AC sources of power. ✓
正确答案：There is no paralleling of the AC sources of power.　·　737　·　来源 b737.org.uk

7.The AC STANDBY BUS power can be supplied from

  1. The APU or engine generators only.
  2. The APU or engine generators, external power or the battery through the Static Inverter. ✓
  3. The APU or engine generators, external power or directly from the Hot Battery Bus.
正确答案：The APU or engine generators, external power or the battery through the Static Inverter.　·　737　·　来源 b737.org.uk

8.A Generator Breaker can be closed

  1. When power quality from the generator is correct. ✓
  2. At any time the engine is running at or above idle power.
  3. Irrespective of power quality from the generator.
正确答案：When power quality from the generator is correct.　·　737　·　来源 b737.org.uk

9.Should a Generator Drive develop a fault and be disconnected from the engine, before corrective action is taken by the pilots

  1. No electrical systems (loads) supplied by that generator will be lost as the Bus Transfer systems supplies all the aircraft's electrical systems ( loads ).
  2. All electrical systems (loads) supplied by that generator will be lost.
  3. A few non-essential electrical systems (loads) will be lost. ✓
正确答案：A few non-essential electrical systems (loads) will be lost.　·　737　·　来源 b737.org.uk

10.When both engines are running with external power connected then

  1. External power will automatically disconnect when either engine generator is brought on-line.
  2. External power will automatically disconnect when both engine generators are brought on line. ✓
  3. External power must be selected OFF before the engine generators are brought on-line.
正确答案：External power will automatically disconnect when both engine generators are brought on line.　·　737　·　来源 b737.org.uk

11.737-1/2/3/4/500: When the Generator Drive Temperature switch is selected to RISE, a higher than normal generator drive oil temperature indicates

  1. An excessive generator load or inadequate cooling of the engine oil.
  2. Inadequate cooling of the Generator Drive oil.
  3. An excessive generator load or poor condition of the Generator Drive. ✓
正确答案：An excessive generator load or poor condition of the Generator Drive.　·　737　·　来源 b737.org.uk

12.Under normal flight, if the Battery switch is selected to OFF then

  1. The Battery Bus loses power. ✓
  2. The Battery Bus is automatically connected to the Hot Battery Bus.
  3. The Battery Bus is automatically connected directly to the Battery.
正确答案：The Battery Bus loses power.　·　737　·　来源 b737.org.uk

13.If the No. 2 TRU fails in the cruise

  1. The Master Caution and ELEC annunciator lights would illuminate.
  2. There would be no immediate indication. ✓
  3. The Battery Ammeter would show a discharge.
正确答案：There would be no immediate indication.　·　737　·　来源 b737.org.uk

14.The auxiliary 28V DC power receptacle is fitted

  1. To 737-1/2/3/4/500 only and is located near the Battery in the electronic compartment. ✓
  2. To all series of 737 and is located near the Battery in the electronic compartment.
  3. To 737NG only and is located near the Battery in the electronic compartment.
正确答案：To 737-1/2/3/4/500 only and is located near the Battery in the electronic compartment.　·　737　·　来源 b737.org.uk

15.A fully charged battery has sufficient capacity to provide power for a minimum of

  1. 30 minutes. ✓
  2. 45 minutes.
  3. 20 minutes.
正确答案：30 minutes.　·　737　·　来源 b737.org.uk

16.The Switched Hot Battery Bus is powered from

  1. The Battery whenever the Battery switch is OFF.
  2. The Battery Bus whenever the Battery Switch is OFF.
  3. The Hot Battery Bus whenever the Battery Switch is ON. ✓
正确答案：The Hot Battery Bus whenever the Battery Switch is ON.　·　737　·　来源 b737.org.uk

17.The APU can power both AC Busses

  1. On the ground, or one AC bus in-flight.
  2. In flight only.
  3. On the ground or in flight. ✓
正确答案：On the ground or in flight.　·　737　·　来源 b737.org.uk

18.The T.R. voltage range is

  1. 28 - 30 volts.
  2. 26 - 35 volts.
  3. 24 - 30 volts. ✓
正确答案：24 - 30 volts.　·　737　·　来源 b737.org.uk

19.The battery voltage range is

  1. 22 - 30 volts. ✓
  2. 24 - 28 volts.
  3. 26 - 28 volts.
正确答案：22 - 30 volts.　·　737　·　来源 b737.org.uk

20.The TR UNIT light means:

  1. on the ground, any TR has failed; in flight, TR2 or TR1 and TR3 have failed
  2. on the ground, any TR has failed; in flight, TR1 or TR2 and TR3 have failed ✓
  3. on the ground, any TR has failed; in flight, TR3 or TR1 and TR2 have failed
正确答案：on the ground, any TR has failed; in flight, TR1 or TR2 and TR3 have failed　·　737　·　来源 b737.org.uk

21.The Transfer Buses supply

  1. The Non Essential Loads.
  2. The Essential Loads. ✓
  3. The Non Essential and Heavy Loads.
正确答案：The Essential Loads.　·　737　·　来源 b737.org.uk

22.With the aircraft on the ground (both engine generators on-line) and external power connected up to the aircraft, momentarily positioning the Ground Power switch to ON

  1. Will trip both engine generators and connect external power to both generator busses. ✓
  2. Will trip the right engine generator only and connect external power to the right generator bus.
  3. Will trip the left engine generator only and connect external power to the left generator bus.
正确答案：Will trip both engine generators and connect external power to both generator busses.　·　737　·　来源 b737.org.uk

23.If, in flight, both engine generators fail, the APU generator should be connected to

  1. The No. 1 Generator Bus.
  2. The No. 2 Generator Bus. ✓
  3. Both No. 1 and No. 2 Generator Busses.
正确答案：The No. 2 Generator Bus.　·　737　·　来源 b737.org.uk

24.The blue GRD POWER AVAILABLE light when illuminated indicates

  1. That the External Power Bus is powered by the ground power supply. Light remains illuminated as long as ground power is connected. ✓
  2. That both Generator Busses are powered by the ground power supply. Light remains illuminated as long as ground power is connected.
  3. That either Generator Bus is powered by the ground power supply. Light remains illuminated as long as ground power is connected.
正确答案：That the External Power Bus is powered by the ground power supply. Light remains illuminated as long as ground power is connected.　·　737　·　来源 b737.org.uk

25.Under normal conditions the Standby AC bus is energised from the

  1. The Static Invertor.
  2. 115-volt Transfer bus No. 2.
  3. 115-volt Transfer bus No. 1. ✓
正确答案：115-volt Transfer bus No. 1.　·　737　·　来源 b737.org.uk

26.After operating the Generator Drive Disconnect switch

  1. The Standby Power switch should be selected to BAT.
  2. The Generator switch should be momentarily held to OFF to trip the Generator Control Relay.
  3. The APU should be started and the APU generator selected on-line. ✓
正确答案：The APU should be started and the APU generator selected on-line.　·　737　·　来源 b737.org.uk

27.The first action to be taken in the event of electrical failure of a generator is

  1. Select the associated Generator switch to ON. ✓
  2. Start the APU (if available) and select it on line.
  3. Select the associated Generator switch to OFF.
正确答案：Select the associated Generator switch to ON.　·　737　·　来源 b737.org.uk

28.The normal power source for the Battery Charger is the AC Ground Service Bus, with provisions for automatic switching to

  1. Either Transfer Bus.
  2. The No. 1 Main Bus.
  3. The No. 2 Main Bus. ✓
正确答案：The No. 2 Main Bus.　·　737　·　来源 b737.org.uk

29.Pulling up an engine fire handle will

  1. Trip the associated Generator Control Relay and Breaker. ✓
  2. Trip the associated Generator Control Relay and disconnects the Generator Drive.
  3. Trip the associated Generator Control Relay only.
正确答案：Trip the associated Generator Control Relay and Breaker.　·　737　·　来源 b737.org.uk

30.If the Battery switch is selected OFF, the airstairs can be lowered from the outside

  1. By using the NORMAL system with ground power plugged in.
  2. By using the STANDBY system. ✓
  3. By using the STANDBY system, but can only be raised again by use of the NORMAL system.
正确答案：By using the STANDBY system.　·　737　·　来源 b737.org.uk

31.To have all three Generators (APU and engines) on-line simultaneously

  1. Is possible on the ground only.
  2. Is possible in flight only.
  3. Is not possible. ✓
正确答案：Is not possible.　·　737　·　来源 b737.org.uk

32.With an engine Generator switch selected OFF and the associated engine is running, the voltage of that generator will read

  1. Residual volts when the residual volts switch is pressed. ✓
  2. 115 volts.
  3. Approximately 3 volts.
正确答案：Residual volts when the residual volts switch is pressed.　·　737　·　来源 b737.org.uk

33.To connect the External Ground power to the aircraft's Generator busses

  1. The Battery switch must be OFF.
  2. The Battery switch must be ON. ✓
  3. The Bus Transfer switch must be in the AUTO position.
正确答案：The Battery switch must be ON.　·　737　·　来源 b737.org.uk

34.Standby D.C. power is normally supplied from

  1. The Hot Battery Bus.
  2. The Battery Bus.
  3. DC Bus No. 1. ✓
正确答案：DC Bus No. 1.　·　737　·　来源 b737.org.uk

35.Failure of the No. 1 Generator Bus will

  1. Will cause failure of the System B Electric hydraulic pump. ✓
  2. Will cause failure of the System A Electric hydraulic pump.
  3. Have no effect on either electric hydraulic pump.
正确答案：Will cause failure of the System B Electric hydraulic pump.　·　737　·　来源 b737.org.uk

36.Placing the BUS TRANS switch to 'OFF' inflight with both generators operating and connected

  1. Isolates the transfer busses by preventing operation of the bus transfer relay, opens the TR 1 and 2 disconnect relays and prevents connection of the battery to the Static Invertor.
  2. Isolates the transfer busses by preventing operation of the bus transfer relay, opens the TR 3 disconnect relay and prevents connection of the battery charger to its alternate power source ( Main Bus 2 ). ✓
  3. Isolates the transfer busses by preventing operation of the bus transfer relay and opens the TR 3 disconnect relay only.
正确答案：Isolates the transfer busses by preventing operation of the bus transfer relay, opens the TR 3 disconnect relay and prevents connection of the battery charger to its alternate power source ( Main Bus 2 ).　·　737　·　来源 b737.org.uk

37.Which of the following statements is correct

  1. TR 3 normally backs up TR 1 and TR 2 provided that the BUS TRANS switch is in AUTO. ✓
  2. TR 3 normally backs up TR 1 and TR 2 provided that the BUS TRANS switch is in OFF.
  3. TR 3 backs up TR 2 only.
正确答案：TR 3 normally backs up TR 1 and TR 2 provided that the BUS TRANS switch is in AUTO.　·　737　·　来源 b737.org.uk

38.Standby A.C. power is available on touch down after a total electrical failure providing

  1. The Battery switch is selected to ON and the Standby Power switch is selected to AUTO.
  2. The Standby Power switch is selected to BAT. ✓
  3. The Standby Power switch is selected to AUTO.
正确答案：The Standby Power switch is selected to BAT.　·　737　·　来源 b737.org.uk

39.The APU generator has

  1. No Generator drive unit since the APU itself is governed and will maintain a constant generator speed. ✓
  2. A Generator drive unit which will automatically disconnect when its oil temperature is high.
  3. A Generator drive unit which will disconnect when the APU Generator drive disconnect switch is activated from the flight deck.
正确答案：No Generator drive unit since the APU itself is governed and will maintain a constant generator speed.　·　737　·　来源 b737.org.uk

40.If ground power is available and the Ground Service switch on the forward attendant's panel is switched on, then power is supplied to

  1. The Ground Service bus for utility outlets, cabin lighting and battery charger. ✓
  2. The Ground Service bus for utility outlets and cabin lighting only.
  3. All the aircraft electrical busses.
正确答案：The Ground Service bus for utility outlets, cabin lighting and battery charger.　·　737　·　来源 b737.org.uk

41.An engine electrical generator is rated at

  1. 35 KVA
  2. 55 KVA
  3. 45 KVA ✓
正确答案：45 KVA　·　737　·　来源 b737.org.uk

42.The T/R No. 3 disconnect relay automatically opens at glideslope capture to

  1. Provide backup power to the Standby DC bus.
  2. Prevent a single bus failure from affecting both the navigation receivers and flight control computers. ✓
  3. Off-load the battery charger from the 115V AC GND SERVICE Bus.
正确答案：Prevent a single bus failure from affecting both the navigation receivers and flight control computers.　·　737　·　来源 b737.org.uk

43.After disconnecting a Generator Drive, its associated oil temperature indicator

  1. Will immediately show a decrease in temperature.
  2. May show an increase on the IN scale and/or the RISE scale. ✓
  3. Will maintain the same temperature reading.
正确答案：May show an increase on the IN scale and/or the RISE scale.　·　737　·　来源 b737.org.uk

44.The Battery Switch must be

  1. ON or OFF for the GRD PWR Switch to be operable.
  2. OFF for the GRD PWR Switch to be operable.
  3. ON for the GRD PWR Switch to be operable. ✓
正确答案：ON for the GRD PWR Switch to be operable.　·　737　·　来源 b737.org.uk

45.The Battery Switch is ON and the GRD PWR is connected to the aircraft's Busses. If the Battery Switch is selected OFF then

  1. The GRD PWR switch will not automatically disconnect.
  2. The GRD PWR switch will automatically disconnect. ✓
  3. The GRD POWER AVAILABLE light will extinguish.
正确答案：The GRD PWR switch will automatically disconnect.　·　737　·　来源 b737.org.uk

46.A high oil temperature in the IDG would cause an automatic disconnect of the IDG.rnrnrn

  1. True. ✓
  2. False.
正确答案：True.　·　MAX　·　来源 smartcockpit.com

47.The IDGs contain the generator and drive in a common housing, and are lubricated and cooled by a external oil system attached to the gearbox.

  1. True.
  2. False. ✓
正确答案：False.　·　MAX　·　来源 smartcockpit.com

48.Because engine generators power the transfer busses directly, and transfer busses are connected by a bus tie system, the loss of an engine driven generator will not necessarily result in the loss of any bus(ses).

  1. True. ✓
  2. False.
正确答案：True.　·　MAX　·　来源 smartcockpit.com

49.The main battery charger is powered through:

  1. DC bus 1
  2. AC ground service bus 2 ✓
  3. AC main bus 1
  4. Transfer Bus 1
正确答案：AC ground service bus 2　·　MAX　·　来源 smartcockpit.com

50.The purpose of the AC ground service bus is to power:

  1. The cabin lighting
  2. The utility outlets
  3. The battery charger
  4. All statements are correct. ✓
正确答案：All statements are correct.　·　MAX　·　来源 smartcockpit.com

51.The main and auxiliary batteries also provide backup power for the DC standby system only.

  1. True.
  2. False. ✓
正确答案：False.　·　MAX　·　来源 smartcockpit.com

52.AUTOMATIC LOAD SHEDDING (ENGINE GENERATORS) - For single generator operation, the system is designed to shed electrical load incrementally based on actual load sensing. What is the first bus that is shed?

  1. The galleys and main bus on transfer bus 1 are shed first
  2. The galleys and main bus on transfer bus 2 are shed first ✓
  3. The AC standby bus is shed first.
  4. The DC standby bus is shed first.
正确答案：The galleys and main bus on transfer bus 2 are shed first　·　MAX　·　来源 smartcockpit.com

53.The Engine Integrated Drive Generators (IDGs):

  1. Are used in conjunction with a separate generator drive unit (CSD)
  2. Adjust varying generator speeds to maintain a constant frequency throughout normal range of operation
  3. Allow the generator to maintain a constant speed throughout the normal range of operation ✓
  4. Operate whenever the engine is operating and cannot be completely isolated from their associated generator.
正确答案：Allow the generator to maintain a constant speed throughout the normal range of operation　·　MAX　·　来源 smartcockpit.com

54.One basic principle of operation for the B737 electrical system is:

  1. All generator bus sources can be automatically connected by the Standby Power System.
  2. There is no paralleling of the AC power sources. ✓
  3. There is no paralleling of any power source.
  4. An AC power source may be used in parallel with a DC power source.
正确答案：There is no paralleling of the AC power sources.　·　MAX　·　来源 smartcockpit.com

55.Which is the power source for the AC standby bus?

  1. Transfer bus 1 under normal conditions ✓
  2. Transfer bus 2
  3. AC main bus 1
  4. Battery Bus through the Static Inverter under normal conditions
正确答案：Transfer bus 1 under normal conditions　·　MAX　·　来源 smartcockpit.com

56.Both On the ground and in flight a amber ELEC light comes on to indicate that a fault exists in DC power system or standby power system.

  1. True.
  2. False. ✓
正确答案：False.　·　MAX　·　来源 smartcockpit.com

57.In flight if APU is the only source of electrical power:

  1. All galley busses are automatically shed ✓
  2. Only galley bus A & B are automatically shed
  3. Only galley bus C & D are automatically shed
  4. No galley busses are automatically shed
正确答案：All galley busses are automatically shed　·　MAX　·　来源 smartcockpit.com

58.DC voltage and amperage may be read on the DC voltmeter and ammeter for the battery and each of the three TRs. The standby power and battery bus displays only DC voltage. Normal indication is:

  1. 12 +/- 4 volts.
  2. 24 +/- 10 volts.
  3. 26 +/- 4 volts. ✓
  4. 14 +/- 4 volts.
正确答案：26 +/- 4 volts.　·　MAX　·　来源 smartcockpit.com

59.For ground service, a ground service switch is available on:

  1. Aft overhead panel on the Flight Deck
  2. Aft attendantu00b4s panel
  3. Forward attendantu00b4s panel ✓
  4. The overhead panel in the flight deck.
正确答案：Forward attendantu00b4s panel　·　MAX　·　来源 smartcockpit.com

60.What is the significance of an illuminated ELEC light?

  1. One of the three TRs has failed.
  2. The DC system or standby system equipment has failed. ✓
  3. The battery is discharged.
  4. Two or more TRs have failed.
正确答案：The DC system or standby system equipment has failed.　·　MAX　·　来源 smartcockpit.com

61.The 115V AC Standby Bus is powered by:

  1. The 115V Transfer Bus No.1 under normal conditions.
  2. The Battery Bus through the Static Inverter under normal conditions.
  3. The Battery through the Static Inverter with a failure of both engine driven generators.
  4. The 115V Transfer Bus No.1 under normal conditions and the Battery through the Static Inverter with a failure of both engine driven generators. ✓
正确答案：The 115V Transfer Bus No.1 under normal conditions and the Battery through the Static Inverter with a failure of both engine driven generators.　·　MAX　·　来源 smartcockpit.com

62.Either generator or the APU can power both transfer buses. In the event a power source fails, what is required for that transfer bus to be powered by the opposite transfer bus power source?

  1. The generator switch must be OFF.
  2. The battery switch must be ON.
  3. The BUS TRANS switch must be in the AUTO position. ✓
  4. The battery switch must be OFF.
正确答案：The BUS TRANS switch must be in the AUTO position.　·　MAX　·　来源 smartcockpit.com

63.It is possible to power one transfer bus with external power and the other transfer bus with the APU?

  1. Yes.
  2. No. ✓
正确答案：No.　·　MAX　·　来源 smartcockpit.com

64.Both AC Transfer busses can be powered simultaneously by:

  1. A single IDG on the ground or inflight
  2. A single IDG on the ground or inflight and the APU generator while on the ground or inflight ✓
  3. No single source can power both AC Transfer busses simultaneously
  4. The APU generator while on the ground or inflight
正确答案：A single IDG on the ground or inflight and the APU generator while on the ground or inflight　·　MAX　·　来源 smartcockpit.com

65.AUTOMATIC LOAD SHEDDING (ENGINE GENERATORS) - For single generator operation, the system is designed to shed electrical load incrementally based on actual load sensing. When configuration changes to more source capacity (two generator operation), automatic load restoration of the main busses, galley busses and IFE buses occurs. Manual restoration of galley and main bus power can be attempted by:

  1. Moving the CAB/UTIL Power Switch to OFF, then back ON. ✓
  2. Moving the CAB/UTIL Power Switch to OFF for 5 minutes minimum, then back ON.
  3. Moving the CAB/UTIL Power Switch to OFF for 2 minutes minimum, then back ON.
  4. Moving the CAB/UTIL Power Switch to OFF for 3 minutes minimum, then back ON.
正确答案：Moving the CAB/UTIL Power Switch to OFF, then back ON.　·　MAX　·　来源 smartcockpit.com

66.Normal AC voltmeter indication for the APU generator with the AC busses loaded:

  1. 100 to 125 volts.
  2. 110 to 125 volts. ✓
  3. 10 to 135 volts.
  4. 115 to 125 volts.rn
正确答案：110 to 125 volts.　·　MAX　·　来源 smartcockpit.com

67.The TR UNIT will illuminate in flight if:

  1. Any TR unit fails.
  2. TR1 fails or TR2 and TR3 fail. ✓
  3. TR2 fails.
  4. TR3 fails.
正确答案：TR1 fails or TR2 and TR3 fail.　·　MAX　·　来源 smartcockpit.com

68.Transformer rectifier (TR) units and the main battery/battery charger supply DC power.

  1. True. ✓
  2. False.
正确答案：True.　·　MAX　·　来源 smartcockpit.com

69.If the AC source powering a transfer bus fails, the transfer bus will remain unpowered.

  1. True ✓
  2. False.
正确答案：True　·　MAX　·　来源 smartcockpit.com

70.On the ground, with the BATTERY switch OFF and STANDBY POWER Switch in BAT, the switched hot battery bus is:

  1. Not powered ✓
  2. Powered by TR 3
  3. Powered by the Hot Battery Bus
  4. Powered by the Battery
正确答案：Not powered　·　MAX　·　来源 smartcockpit.com

71.In flight, if the APU is supplying both AC Transfer busses, positioning the BUS TRANS switch to OFF will:

  1. Cause AC Transfer bus No.1 to lose power
  2. Cause AC Transfer bus No.2 to lose power ✓
  3. Cause both AC Transfer busses to lose power
  4. Not cause either AC Transfer bus to fail.
正确答案：Cause AC Transfer bus No.2 to lose power　·　MAX　·　来源 smartcockpit.com

72.During cruise, one engine driven generator drops off-line. Indications that the crew should see include:

  1. A TRANSFER BUS OFF light and a GEN OFF BUS light
  2. A SOURCE OFF light and a GEN OFF BUS light ✓
  3. Illumination of the fuel pump, probe heat, respective hydraulic pumps powered by the associated Transfer bus
  4. All statements are correct.
正确答案：A SOURCE OFF light and a GEN OFF BUS light　·　MAX　·　来源 smartcockpit.com

73.Illumination of the blue GEN OFF BUS light indicates:

  1. The associated generator bus is not powered
  2. he associated transfer bus is not powered
  3. The IDG is not supplying power to its associated transfer bus ✓
  4. The generator is not supplying power to its associated generator bus.
正确答案：The IDG is not supplying power to its associated transfer bus　·　MAX　·　来源 smartcockpit.com

74.When the STANDBY POWER Switch is OFF:

  1. The STANDBY PWR OFF light will be illuminated ✓
  2. Automatic switching is provided from normal power sources to alternate power sources
  3. The STANDBY PWR OFF light will be extinguished
  4. The Static Inverter provides 28V DC power to Transfer Bus No.1.
正确答案：The STANDBY PWR OFF light will be illuminated　·　MAX　·　来源 smartcockpit.com

75.With external DC power connected to the external DC power receptacle:

  1. The APU can be started using DC external power. ✓
  2. The battery is paralleled with the DC External power source.
  3. All circuits normally powered by the battery are powered.
  4. There is no external DC power receptacle.rn
正确答案：The APU can be started using DC external power.　·　MAX　·　来源 smartcockpit.com

76.What is the purpose of the GROUND SERVICE switch?

  1. Provides automatic control of ground service bus.
  2. Provide automatic control of ground service busses.
  3. Provide manual control of ground service bus.
  4. Provide manual control of ground service busses. ✓
正确答案：Provide manual control of ground service busses.　·　MAX　·　来源 smartcockpit.com

77.The switched hot battery bus is powered whenever:

  1. TR1 is powered.
  2. Transfer bus 1 is powered.
  3. AC ground service bus is powered.
  4. The battery switch is ON. ✓
正确答案：The battery switch is ON.　·　MAX　·　来源 smartcockpit.com

78.On the ground, with the battery switch OFF and STANBY POWER Switch in AUTO, the Battery Bus is:

  1. Not powered. ✓
  2. Powered by TR3.
  3. Powered by the Hot Battery Bus.
  4. Powered by the Battery.
正确答案：Not powered.　·　MAX　·　来源 smartcockpit.com

79.What is the source of power for TR3?

  1. Transfer bus 1.
  2. Transfer bus 2. ✓
  3. AC standby bus.
  4. Transfer bus 1 or 2.
正确答案：Transfer bus 2.　·　MAX　·　来源 smartcockpit.com

80.Illumination of the BAT DISCHARGE light indicates:

  1. The battery is being overcharged.
  2. Excessive battery discharge is detected with the battery switch ON. ✓
  3. The DC meter is in the BAT position with the battery switch ON.
  4. The battery bus is not powered.
正确答案：Excessive battery discharge is detected with the battery switch ON.　·　MAX　·　来源 smartcockpit.com

81.The cross bus tie relay:

  1. Must be manually opened using the BUS TRANSFER Switch during a Flight Director approach
  2. Normally powers the Battery Charger and backs-up TR units 1 and 2 through a diode
  3. Opens up if BUS TRANSFER switch is moved to OFF ✓
  4. Will trip off when AC volts reaches 26 volts (plus or minus 4 volts) as displayed on the AC voltmeter
正确答案：Opens up if BUS TRANSFER switch is moved to OFF　·　MAX　·　来源 smartcockpit.com

82.Illumination of the STANDBY POWER OFF light indicates:

  1. DC bus 1 unpowered
  2. DC bus 2 unpowered
  3. AC standby bus unpowered ✓
  4. Hot battery bus unpowered
正确答案：AC standby bus unpowered　·　MAX　·　来源 smartcockpit.com

83.What is the source of power for TR2?

  1. Transfer bus 1.
  2. Transfer bus 2. ✓
  3. AC Standby bus
  4. Transfer bus 2 or Transfer bus 1.
正确答案：Transfer bus 2.　·　MAX　·　来源 smartcockpit.com

84.DC busses powered from the battery following a loss of both generators are:

  1. Battery bus, DC Standby bus, Hot battery bus.
  2. DC standby Bus, Hot Battery Bus & Switched hot battery bus.
  3. Battery bus, DC Standby bus, Hot battery bus & Switched hot battery bus (even when the battery switch is OFF).
  4. Battery bus, DC Standby bus, Hot battery bus & Switched hot battery bus. ✓
正确答案：Battery bus, DC Standby bus, Hot battery bus & Switched hot battery bus.　·　MAX　·　来源 smartcockpit.com

85.Galley busses are powered from:

  1. The AC Transfer busses. ✓
  2. The generator busses.
  3. The Battery bus.
  4. The main busses.
正确答案：The AC Transfer busses.　·　MAX　·　来源 smartcockpit.com

86.The ELEC light will illuminate in flight if:

  1. A fault exists in the AC or Standby power system.
  2. A fault exists in the DC or Standby system.
  3. A fault exists in the AC, DC or the Standby system.
  4. The ELEC light only operates on the ground. ✓
正确答案：The ELEC light only operates on the ground.　·　MAX　·　来源 smartcockpit.com

87.Each IDG supplies its own bus system in normal operation and can also supply essential and non-essential loads of the opposite side bus system when one IDG is inoperative.

  1. True. ✓
  2. False.
正确答案：True.　·　MAX　·　来源 smartcockpit.com

88.The purpose of the cross tie relay is to:

  1. Isolate transfer bus 1 and 2
  2. Isolate DC bus 1 from DC bus 2 ✓
  3. Disconnect TR1 and TR3
  4. Disconnect TR2 and TR3
正确答案：Isolate DC bus 1 from DC bus 2　·　MAX　·　来源 smartcockpit.com

89.Illumination of the GEN BUS OFF light indicates:

  1. The associated generator bus is not powered.
  2. The associated transfer bus is not powered.
  3. The IDG is not supplying power to its associated Transfer bus. ✓
  4. The generator is not supplying power to its associated generator bus.
正确答案：The IDG is not supplying power to its associated Transfer bus.　·　MAX　·　来源 smartcockpit.com

90.The TR3 Disconnect Relay:

  1. Must be manually opened using the BUS TRANSFER Switch during a Flight Director approach ✓
  2. Normally powers the Battery Charger and backs-up TR units 1 & 2 through a diode
  3. Automatically opens at glide slope capture during a Flight Director or Autopilot ILS approach
  4. Will trip off when AC volts reaches 26 volts (+ or - 4 Volts) as dispalyed on the AC Voltmeter.
正确答案：Must be manually opened using the BUS TRANSFER Switch during a Flight Director approach　·　MAX　·　来源 smartcockpit.com

91.After the loss of all generators, two fully charged batteries have sufficient capacity to provide standby power for a minimum of:Two fully charged batteries have sufficient capacity to provide standby power forrna minimum of

  1. 20 minutes
  2. 30 minutes
  3. 45 minutes
  4. 60 minutes ✓
正确答案：60 minutes　·　MAX　·　来源 smartcockpit.com

92.DC voltage and amperage may be read on the DC voltmeter and ammeter for the battery and each of the 3 TRs. The Standby power and battery bus displays only Dc voltage. Normal indication is ______ volts

  1. 24 +/- 4
  2. 26 +/- 6
  3. 24 +/-2
  4. 26 +/-4 ✓
正确答案：26 +/-4　·　MAX　·　来源 smartcockpit.com

93.With the STANDBY switch in the AUTO position, the loss of all engine or APU electrical power results in the automatic switching from the normal power source to the alternate source for standby power:

  1. Inflight only.
  2. On the ground only.
  3. Either inflight or on the ground. ✓
  4. Will not occur.
正确答案：Either inflight or on the ground.　·　MAX　·　来源 smartcockpit.com

94.The TR3 cross bus tie relay automatically opens at glide slope capture to:

  1. Prevent a single bus failure from affecting both navigation receivers and Flight Control Computers (FCCs). ✓
  2. Provide more power to the AC STANDBY Bus.
  3. Ensure that the STANDBY DC is powered.
  4. Provide more power to DC bus 1.
正确答案：Prevent a single bus failure from affecting both navigation receivers and Flight Control Computers (FCCs).　·　MAX　·　来源 smartcockpit.com

95.Which bus supplies electrical power to the auxiliary battery charger?

  1. AC ground service bus 1 ✓
  2. AC ground service bus 2
  3. Transfer bus 2
  4. Transfer bus 1
正确答案：AC ground service bus 1　·　MAX　·　来源 smartcockpit.com

96.The GROUND POWER AVAILABLE light will extinguish when:

  1. The GROUND POWER switch is positioned ON
  2. The GROUND SERVICE switch is positioned ON
  3. The pneumatic ground cart is disconnected
  4. The AC ground power cart has been disconnected ✓
正确答案：The AC ground power cart has been disconnected　·　MAX　·　来源 smartcockpit.com

97.The illumination of the GND POWER AVAILABLE light indicates:

  1. Ground power is connected and meets airplane power quality standards. ✓
  2. Ground power is connected however no airplane power quality is measured.
  3. The Ground Service Bus is powered by a ground power supply.
  4. The external power bus is powered by a ground power supply.
正确答案：Ground power is connected and meets airplane power quality standards.　·　MAX　·　来源 smartcockpit.com

98.The auxiliary battery operates in parallel with the main battery when the battery is powering the standby bus.

  1. True. ✓
  2. False.
正确答案：True.　·　MAX　·　来源 smartcockpit.com

99.When the aircraft batteries is the only source of power:

  1. The Captain's inboard and outboard displays operate until the battery is discharged and the First Officer's inboard and outboard displays operate for a minimum of 5 minutes
  2. The Captain's inboard and outboard displays operate until the battery is discharged ✓
  3. The Captain's inboard and the First Officer's inboard and outboard displays are inoperative
  4. Both the Captain's and First Officer's PFD/ND displays remain operative but only DEU No 1 is powered until the battery is discharged
正确答案：The Captain's inboard and outboard displays operate until the battery is discharged　·　MAX　·　来源 smartcockpit.com

100.What is the significance of an illuminated ELEC light?

  1. One of the three TRs has failed.
  2. The DC system or standby system equipment has failed. ✓
  3. The battery is discharged.
  4. Two or more TRs have failed.
正确答案：The DC system or standby system equipment has failed.　·　NG　·　来源 smartcockpit.com

101.The IDGs contain the generator and drive in a common housing, and are lubricated and cooled by a external oil system attached to the gearbox.

  1. True.
  2. False. ✓
正确答案：False.　·　NG　·　来源 smartcockpit.com

102.The TR3 cross bus tie relay automatically opens at glide slope capture to:

  1. Prevent a single bus failure from affecting both navigation receivers and Flight Control Computers (FCCs). ✓
  2. Provide more power to the AC STANDBY Bus.
  3. Ensure that the STANDBY DC is powered.
  4. Provide more power to DC bus 1.
正确答案：Prevent a single bus failure from affecting both navigation receivers and Flight Control Computers (FCCs).　·　NG　·　来源 smartcockpit.com

103.The 115V AC Standby Bus is powered by:

  1. The 115V Transfer Bus No.1 under normal conditions.
  2. The Battery Bus through the Static Inverter under normal conditions.
  3. The Battery through the Static Inverter with a failure of both engine driven generators.
  4. The 115V Transfer Bus No.1 under normal conditions and the Battery through the Static Inverter with a failure of both engine driven generators. ✓
正确答案：The 115V Transfer Bus No.1 under normal conditions and the Battery through the Static Inverter with a failure of both engine driven generators.　·　NG　·　来源 smartcockpit.com

104.When the STANDBY POWER Switch is OFF:

  1. The STANDBY PWR OFF light will be illuminated ✓
  2. Automatic switching is provided from normal power sources to alternate power sources
  3. The STANDBY PWR OFF light will be extinguished
  4. The Static Inverter provides 28V DC power to Transfer Bus No.1.
正确答案：The STANDBY PWR OFF light will be illuminated　·　NG　·　来源 smartcockpit.com

105.What is the purpose of the GROUND SERVICE switch?

  1. Provides automatic control of ground service bus.
  2. Provide automatic control of ground service busses.
  3. Provide manual control of ground service bus.
  4. Provide manual control of ground service busses. ✓
正确答案：Provide manual control of ground service busses.　·　NG　·　来源 smartcockpit.com

106.Illumination of the blue GEN OFF BUS light indicates:

  1. The associated generator bus is not powered
  2. he associated transfer bus is not powered
  3. The IDG is not supplying power to its associated transfer bus ✓
  4. The generator is not supplying power to its associated generator bus.
正确答案：The IDG is not supplying power to its associated transfer bus　·　NG　·　来源 smartcockpit.com

107.A high oil temperature in the IDG would cause an automatic disconnect of the IDG.

  1. True. ✓
  2. False.
正确答案：True.　·　NG　·　来源 smartcockpit.com

108.The GROUND POWER AVAILABLE light will extinguish when:

  1. The GROUND POWER switch is positioned ON
  2. The GROUND SERVICE switch is positioned ON
  3. The pneumatic ground cart is disconnected
  4. The AC ground power cart has been disconnected ✓
正确答案：The AC ground power cart has been disconnected　·　NG　·　来源 smartcockpit.com

109.DC voltage and amperage may be read on the DC voltmeter and ammeter for the battery and each of the three TRs. The standby power and battery bus displays only DC voltage. Normal indication is:

  1. 12 +/- 4 volts.
  2. 24 +/- 10 volts.
  3. 26 +/- 4 volts. ✓
  4. 14 +/- 4 volts.
正确答案：26 +/- 4 volts.　·　NG　·　来源 smartcockpit.com

110.With the STANDBY switch in the AUTO position, the loss of all engine or APU electrical power results in the automatic switching from the normal power source to the alternate source for standby power:

  1. Inflight only.
  2. On the ground only.
  3. Either inflight or on the ground. ✓
  4. Will not occur.
正确答案：Either inflight or on the ground.　·　NG　·　来源 smartcockpit.com

111.For ground service, a ground service switch is available on:

  1. Aft overhead panel on the Flight Deck
  2. Aft attendant´s panel
  3. Forward attendant´s panel ✓
  4. The overhead panel in the flight deck.
正确答案：Forward attendant´s panel　·　NG　·　来源 smartcockpit.com

112.Normal AC voltmeter indication for the APU generator with the AC busses loaded:

  1. 100 to 125 volts.
  2. 110 to 125 volts. ✓
  3. 10 to 135 volts.
  4. 115 to 125 volts.
正确答案：110 to 125 volts.　·　NG　·　来源 smartcockpit.com

113.On the ground, with the battery switch OFF and STANBY POWER Switch in AUTO, the Battery Bus is:

  1. Not powered. ✓
  2. Powered by TR3.
  3. Powered by the Hot Battery Bus.
  4. Powered by the Battery.
正确答案：Not powered.　·　NG　·　来源 smartcockpit.com

114.Both AC Transfer busses can be powered simultaneously by:

  1. A single IDG on the ground or inflight
  2. A single IDG on the ground or inflight and the APU generator while on the ground or inflight ✓
  3. No single source can power both AC Transfer busses simultaneously
  4. The APU generator while on the ground or inflight
正确答案：A single IDG on the ground or inflight and the APU generator while on the ground or inflight　·　NG　·　来源 smartcockpit.com

115.The Engine Integrated Drive Generators (IDGs):

  1. Are used in conjunction with a separate generator drive unit (CSD)
  2. Adjust varying generator speeds to maintain a constant frequency throughout normal range of operation
  3. Allow the generator to maintain a constant speed throughout the normal range of operation ✓
  4. Operate whenever the engine is operating and cannot be completely isolated from their associated generator.
正确答案：Allow the generator to maintain a constant speed throughout the normal range of operation　·　NG　·　来源 smartcockpit.com

116.With external DC power connected to the external DC power receptacle:

  1. The APU can be started using DC external power. ✓
  2. The battery is paralleled with the DC External power source.
  3. All circuits normally powered by the battery are powered.
  4. There is no external DC power receptacle.
正确答案：The APU can be started using DC external power.　·　NG　·　来源 smartcockpit.com

117.Illumination of the BAT DISCHARGE light indicates:

  1. The battery is being overcharged.
  2. Excessive battery discharge is detected with the battery switch ON. ✓
  3. The DC meter is in the BAT position with the battery switch ON.
  4. The battery bus is not powered.
正确答案：Excessive battery discharge is detected with the battery switch ON.　·　NG　·　来源 smartcockpit.com

118.DC voltage and amperage may be read on the DC voltmeter and ammeter for the battery and each of the 3 TRs. The Standby power and battery bus displays only Dc voltage. Normal indication is ______ volts

  1. 24 +/- 4
  2. 26 +/- 6
  3. 24 +/-2
  4. 26 +/-4 ✓
正确答案：26 +/-4　·　NG　·　来源 smartcockpit.com

119.The illumination of the GND POWER AVAILABLE light indicates:

  1. Ground power is connected and meets airplane power quality standards. ✓
  2. Ground power is connected however no airplane power quality is measured.
  3. The Ground Service Bus is powered by a ground power supply.
  4. The external power bus is powered by a ground power supply.
正确答案：Ground power is connected and meets airplane power quality standards.　·　NG　·　来源 smartcockpit.com

120.The cross bus tie relay:

  1. Must be manually opened using the BUS TRANSFER Switch during a Flight Director approach
  2. Normally powers the Battery Charger and backs-up TR units 1 and 2 through a diode
  3. Opens up if BUS TRANSFER switch is moved to OFF ✓
  4. Will trip off when AC volts reaches 26 volts (plus or minus 4 volts) as displayed on the AC voltmeter
正确答案：Opens up if BUS TRANSFER switch is moved to OFF　·　NG　·　来源 smartcockpit.com

121.The auxiliary battery operates in parallel with the main battery when the battery is powering the standby bus.

  1. True. ✓
  2. False.
正确答案：True.　·　NG　·　来源 smartcockpit.com

122.The purpose of the AC ground service bus is to power:

  1. The cabin lighting
  2. The utility outlets
  3. The battery charger
  4. All statements are correct. ✓
正确答案：All statements are correct.　·　NG　·　来源 smartcockpit.com

123.The main battery charger is powered through:

  1. DC bus 1
  2. AC ground service bus 2 ✓
  3. AC main bus 1
  4. Transfer Bus 1
正确答案：AC ground service bus 2　·　NG　·　来源 smartcockpit.com

124.Both On the ground and in flight a amber ELEC light comes on to indicate that a fault exists in DC power system or standby power system.

  1. True.
  2. False. ✓
正确答案：False.　·　NG　·　来源 smartcockpit.com

125.Each IDG supplies its own bus system in normal operation and can also supply essential and non-essential loads of the opposite side bus system when one IDG is inoperative.

  1. True. ✓
  2. False.
正确答案：True.　·　NG　·　来源 smartcockpit.com

126.After the loss of all generators, two fully charged batteries have sufficient capacity to provide standby power for a minimum of:Two fully charged batteries have sufficient capacity to provide standby power for a minimum of

  1. 20 minutes
  2. 30 minutes
  3. 45 minutes
  4. 60 minutes ✓
正确答案：60 minutes　·　NG　·　来源 smartcockpit.com

127.The TR UNIT will illuminate in flight if:

  1. Any TR unit fails.
  2. TR1 fails or TR2 and TR3 fail. ✓
  3. TR2 fails.
  4. TR3 fails.
正确答案：TR1 fails or TR2 and TR3 fail.　·　NG　·　来源 smartcockpit.com

128.One basic principle of operation for the B737 electrical system is:

  1. All generator bus sources can be automatically connected by the Standby Power System.
  2. There is no paralleling of the AC power sources. ✓
  3. There is no paralleling of any power source.
  4. An AC power source may be used in parallel with a DC power source.
正确答案：There is no paralleling of the AC power sources.　·　NG　·　来源 smartcockpit.com

129.When the aircraft batteries is the only source of power:

  1. The Captain's inboard and outboard displays operate until the battery is discharged and the First Officer's inboard and outboard displays operate for a minimum of 5 minutes
  2. The Captain's inboard and outboard displays operate until the battery is discharged ✓
  3. The Captain's inboard and the First Officer's inboard and outboard displays are inoperative
  4. Both the Captain's and First Officer's PFD/ND displays remain operative but only DEU No 1 is powered until the battery is discharged
正确答案：The Captain's inboard and outboard displays operate until the battery is discharged　·　NG　·　来源 smartcockpit.com

130.What is the source of power for TR3?

  1. Transfer bus 1.
  2. Transfer bus 2. ✓
  3. AC standby bus.
  4. Transfer bus 1 or 2.
正确答案：Transfer bus 2.　·　NG　·　来源 smartcockpit.com

131.DC busses powered from the battery following a loss of both generators are:

  1. Battery bus, DC Standby bus, Hot battery bus.
  2. DC standby Bus, Hot Battery Bus & Switched hot battery bus.
  3. Battery bus, DC Standby bus, Hot battery bus & Switched hot battery bus (even when the battery switch is OFF).
  4. Battery bus, DC Standby bus, Hot battery bus & Switched hot battery bus. ✓
正确答案：Battery bus, DC Standby bus, Hot battery bus & Switched hot battery bus.　·　NG　·　来源 smartcockpit.com

132.Because engine generators power the transfer busses directly, and transfer busses are connected by a bus tie system, the loss of an engine driven generator will not necessarily result in the loss of any bus(ses).

  1. True. ✓
  2. False.
正确答案：True.　·　NG　·　来源 smartcockpit.com

133.On the ground, with the BATTERY switch OFF and STANDBY POWER Switch in BAT, the switched hot battery bus is:

  1. Not powered ✓
  2. Powered by TR 3
  3. Powered by the Hot Battery Bus
  4. Powered by the Battery
正确答案：Not powered　·　NG　·　来源 smartcockpit.com

134.Illumination of the STANDBY POWER OFF light indicates:

  1. DC bus 1 unpowered
  2. DC bus 2 unpowered
  3. AC standby bus unpowered ✓
  4. Hot battery bus unpowered
正确答案：AC standby bus unpowered　·　NG　·　来源 smartcockpit.com

135.The ELEC light will illuminate in flight if:

  1. A fault exists in the AC or Standby power system.
  2. A fault exists in the DC or Standby system.
  3. A fault exists in the AC, DC or the Standby system.
  4. The ELEC light only operates on the ground. ✓
正确答案：The ELEC light only operates on the ground.　·　NG　·　来源 smartcockpit.com

136.The TR3 Disconnect Relay:

  1. Must be manually opened using the BUS TRANSFER Switch during a Flight Director approach ✓
  2. Normally powers the Battery Charger and backs-up TR units 1 & 2 through a diode
  3. Automatically opens at glide slope capture during a Flight Director or Autopilot ILS approach
  4. Will trip off when AC volts reaches 26 volts (+ or - 4 Volts) as dispalyed on the AC Voltmeter.
正确答案：Must be manually opened using the BUS TRANSFER Switch during a Flight Director approach　·　NG　·　来源 smartcockpit.com

137.Galley busses are powered from:

  1. The AC Transfer busses. ✓
  2. The generator busses.
  3. The Battery bus.
  4. The main busses.
正确答案：The AC Transfer busses.　·　NG　·　来源 smartcockpit.com

138.Which bus supplies electrical power to the auxiliary battery charger?

  1. AC ground service bus 1 ✓
  2. AC ground service bus 2
  3. Transfer bus 2
  4. Transfer bus 1
正确答案：AC ground service bus 1　·　NG　·　来源 smartcockpit.com

139.Transformer rectifier (TR) units and the main battery/battery charger supply DC power.

  1. True. ✓
  2. False.
正确答案：True.　·　NG　·　来源 smartcockpit.com

140.AUTOMATIC LOAD SHEDDING (ENGINE GENERATORS) - For single generator operation, the system is designed to shed electrical load incrementally based on actual load sensing. What is the first bus that is shed?

  1. The galleys and main bus on transfer bus 1 are shed first
  2. The galleys and main bus on transfer bus 2 are shed first ✓
  3. The AC standby bus is shed first.
  4. The DC standby bus is shed first.
正确答案：The galleys and main bus on transfer bus 2 are shed first　·　NG　·　来源 smartcockpit.com

141.The switched hot battery bus is powered whenever:

  1. TR1 is powered.
  2. Transfer bus 1 is powered.
  3. AC ground service bus is powered.
  4. The battery switch is ON. ✓
正确答案：The battery switch is ON.　·　NG　·　来源 smartcockpit.com

142.Either generator or the APU can power both transfer buses. In the event a power source fails, what is required for that transfer bus to be powered by the opposite transfer bus power source?

  1. The generator switch must be OFF.
  2. The battery switch must be ON.
  3. The BUS TRANS switch must be in the AUTO position. ✓
  4. The battery switch must be OFF.
正确答案：The BUS TRANS switch must be in the AUTO position.　·　NG　·　来源 smartcockpit.com

143.The purpose of the cross tie relay is to:

  1. Isolate transfer bus 1 and 2
  2. Isolate DC bus 1 from DC bus 2 ✓
  3. Disconnect TR1 and TR3
  4. Disconnect TR2 and TR3
正确答案：Isolate DC bus 1 from DC bus 2　·　NG　·　来源 smartcockpit.com

144.During cruise, one engine driven generator drops off-line. Indications that the crew should see include:

  1. A TRANSFER BUS OFF light and a GEN OFF BUS light
  2. A SOURCE OFF light and a GEN OFF BUS light ✓
  3. Illumination of the fuel pump, probe heat, respective hydraulic pumps powered by the associated Transfer bus
  4. All statements are correct.
正确答案：A SOURCE OFF light and a GEN OFF BUS light　·　NG　·　来源 smartcockpit.com

145.If the AC source powering a transfer bus fails, the transfer bus will remain unpowered.

  1. True ✓
  2. False.
正确答案：True　·　NG　·　来源 smartcockpit.com

146.AUTOMATIC LOAD SHEDDING (ENGINE GENERATORS) - For single generator operation, the system is designed to shed electrical load incrementally based on actual load sensing. When configuration changes to more source capacity (two generator operation), automatic load restoration of the main busses, galley busses and IFE buses occurs. Manual restoration of galley and main bus power can be attempted by:

  1. Moving the CAB/UTIL Power Switch to OFF, then back ON. ✓
  2. Moving the CAB/UTIL Power Switch to OFF for 5 minutes minimum, then back ON.
  3. Moving the CAB/UTIL Power Switch to OFF for 2 minutes minimum, then back ON.
  4. Moving the CAB/UTIL Power Switch to OFF for 3 minutes minimum, then back ON.
正确答案：Moving the CAB/UTIL Power Switch to OFF, then back ON.　·　NG　·　来源 smartcockpit.com

147.Which is the power source for the AC standby bus?

  1. Transfer bus 1 under normal conditions ✓
  2. Transfer bus 2
  3. AC main bus 1
  4. Battery Bus through the Static Inverter under normal conditions
正确答案：Transfer bus 1 under normal conditions　·　NG　·　来源 smartcockpit.com

148.In flight if APU is the only source of electrical power:

  1. All galley busses are automatically shed ✓
  2. Only galley bus A & B are automatically shed
  3. Only galley bus C & D are automatically shed
  4. No galley busses are automatically shed
正确答案：All galley busses are automatically shed　·　NG　·　来源 smartcockpit.com

149.The main and auxiliary batteries also provide backup power for the DC standby system only.

  1. True.
  2. False. ✓
正确答案：False.　·　NG　·　来源 smartcockpit.com

150.Illumination of the GEN BUS OFF light indicates:

  1. The associated generator bus is not powered.
  2. The associated transfer bus is not powered.
  3. The IDG is not supplying power to its associated Transfer bus. ✓
  4. The generator is not supplying power to its associated generator bus.
正确答案：The IDG is not supplying power to its associated Transfer bus.　·　NG　·　来源 smartcockpit.com

151.In flight, if the APU is supplying both AC Transfer busses, positioning the BUS TRANS switch to OFF will:

  1. Cause AC Transfer bus No.1 to lose power
  2. Cause AC Transfer bus No.2 to lose power ✓
  3. Cause both AC Transfer busses to lose power
  4. Not cause either AC Transfer bus to fail.
正确答案：Cause AC Transfer bus No.2 to lose power　·　NG　·　来源 smartcockpit.com

152.What is the source of power for TR2?

  1. Transfer bus 1.
  2. Transfer bus 2. ✓
  3. AC Standby bus
  4. Transfer bus 2 or Transfer bus 1.
正确答案：Transfer bus 2.　·　NG　·　来源 smartcockpit.com

153.It is possible to power one transfer bus with external power and the other transfer bus with the APU?

  1. Yes.
  2. No. ✓
正确答案：No.　·　NG　·　来源 smartcockpit.com

154.What is the direct result of low oil pressure in the No2 IDG?

  1. No immediate affect noticeable as the Bus Tie Brakers (BTB) automatically connect the No1 IDG to drive both AC Transfer Bus 1 and AC Transfer Bus 2.
  2. Power automatically trips to the STANDBY system.
  3. Power is lost on the First Officer's displays after a delay of 5 minutes.
  4. The No2 Drive light illuminates amber. ✓
正确答案：The No2 Drive light illuminates amber.　·　NG　·　来源 Chair Flight B737 Question Bank

155.With a loss of system B pressure the standby system can be used to extend the leading and trailing edge devices, the leading edge devices cannot be retracted again once extended by the standby system, but the trailing edge flaps can be retracted by electric motors using the ALTERNATE FLAPS position switch, but no asymmetry or skew protection is then provided.

  1. True
  2. False ✓
正确答案：False　·　NG　·　来源 Chair Flight B737 Question Bank

156.In the unlikely situation of total generator failure, at high altitude thrust deterioration may occur. Why?

  1. The fuel will be suction fed, which may cause dissolved air released from the fuel to restrict fuel flow in the suction feed line. ✓
  2. Loss of AC power will affect the ignition system and therefore create a potential risk of flameout
  3. When on STBY power the fuel pumps run a little slower
  4. When on STBY power the HMU will be unreliable, therefore thrust deterioration might occur at high altitude
正确答案：The fuel will be suction fed, which may cause dissolved air released from the fuel to restrict fuel flow in the suction feed line.　·　NG　·　来源 Chair Flight B737 Question Bank

157.The flap slat electronic unit (FSEU) will close the trailing edge bypass valve if it detects trailing edge flap asymmetry, skew or uncommanded motion; thus stopping the movement of the flaps via the normal system. However, the flaps can still be moved by means of electric motors.

  1. True ✓
  2. False
正确答案：True　·　NG　·　来源 Chair Flight B737 Question Bank

158.In flight, with the APU as the only source of electrical power; if the electrical load exceeds the APU Generator design limit, the galley busses and the IFE busses are the first to be automatically shed.

  1. True
  2. False ✓
正确答案：False　·　NG　·　来源 Chair Flight B737 Question Bank

159.At what point during a normal start is the EEC supplied with electrical power?

  1. When the engines accelerates to a speed greater than 15% N2
  2. When the engine start switch is positioned to GRD ✓
  3. When the battery switch is placed ON
  4. When the engines accelerates to a speed greater than 25% N2 or max motoring
正确答案：When the engine start switch is positioned to GRD　·　NG　·　来源 Chair Flight B737 Question Bank

160.What is the normal source of power for the Battery Bus?

  1. The hot battery bus
  2. the switched hot battery bus
  3. The battery
  4. TR3 ✓
正确答案：TR3　·　NG　·　来源 Chair Flight B737 Question Bank

161.What is the voltage of the DC Busses under normal circumstances?

  1. 24v
  2. 115v
  3. 28v ✓
  4. 22-30v
正确答案：28v　·　NG　·　来源 Chair Flight B737 Question Bank

162.If an IDG fails and the APU is not available to power the related Transfer Bus, what occur first if an electrical overload is sensed?

  1. Automatic load shedding of the galleys and main bus on Transfer Bus 1.
  2. Automatic load shedding of the IFE Busses.
  3. Automatic load shedding of the galleys and main bus on Transfer Bus 2 ✓
  4. Automatic load shedding of the galley and main busses on on both Transfer Busses.
正确答案：Automatic load shedding of the galleys and main bus on Transfer Bus 2　·　NG　·　来源 Chair Flight B737 Question Bank

163.Which bus(ses) will be automatically shed if the APU is the only source of electrical power in flight?

  1. Transfer bus 2
  2. The galley busses
  3. The main busses
  4. All galley and main busses ✓
正确答案：All galley and main busses　·　NG　·　来源 Chair Flight B737 Question Bank

164.The Static Inverter, converts the Battery's 22-30V DC voltage range to a constant 24V.

  1. True
  2. False ✓
正确答案：False　·　NG　·　来源 Chair Flight B737 Question Bank

165.Under what conditions are DC bus 1 and DC bus 2 isolated.

  1. Switching the Bus Transfer switch to OFF.
  2. All the other answers are true. ✓
  3. When the cross bus tie relay opens.
  4. At glide slope capture during a a flight director or autopilot ILS apporach.
正确答案：All the other answers are true.　·　NG　·　来源 Chair Flight B737 Question Bank

166.With the STANDBY POWER switch (located on the Generator Drive and Standby Power Panel) in the AUTO position, will the loss of a single DC Bus result in automatic switching from normal to alternate power?

  1. Only if power from DC Bus 2 is lost
  2. Only if power from from DC Bus 1 is lost and power from AC Transfer Bus 1 is also lost
  3. Only if power from DC Bus 1 is lost ✓
  4. No, for automatic switching to occur power must be lost from both DC Busses
正确答案：Only if power from DC Bus 1 is lost　·　NG　·　来源 Chair Flight B737 Question Bank

167.Which electrical bus is always connected and powered whenever the aircraft battery is fitted?

  1. DC Standby bus - power to important systems that require to be in standby mode.
  2. Battery bus - power immediately available to important systems such as fire extinguishers.
  3. Hot Battery Bus - power immediately available to important systems such as fire extinguishers. ✓
  4. AC standby bus- powered through Transformer Rectifier to ensure no power interuption to GPS system.
正确答案：Hot Battery Bus - power immediately available to important systems such as fire extinguishers.　·　NG　·　来源 Chair Flight B737 Question Bank

168.What is the normal AC power source for TR3?

  1. Main Bus 2
  2. Transfer Bus 1
  3. Transfer Bus 2 ✓
  4. Main Bus 1
正确答案：Transfer Bus 2　·　NG　·　来源 Chair Flight B737 Question Bank

169.The main battery charger is powered by?

  1. AC Ground Service Bus 1
  2. Transfer Bus 1
  3. AC Ground Service Bus 2 ✓
  4. Transfer Bus 2
正确答案：AC Ground Service Bus 2　·　NG　·　来源 Chair Flight B737 Question Bank

170.The 2 basic rules of the B737-800 electrical system are: Only one AC power source can be connected at one time. A second source connecting to a transfer bus will automatically disconnect the existing source.

  1. True ✓
  2. False
正确答案：True　·　NG　·　来源 Chair Flight B737 Question Bank

171.What indications will you see on the electrical panel when selecting GRD PWR ON?

  1. GRD POWER light extinguished, SOURCE OFF lights illuminated, GEN OFF BUS lights illuminated, TRANSFER BUS OFF lights extinguished, APU GEN OFF BUS light illuminated.
  2. GRD POWER AVAILABLE light extinguished, SOURCE OFF lights extinguished, GEN OFF BUS lights illuminated, TRANSFER BUS OFF lights extinguished, APU GEN OFF BUS light illuminated.
  3. GRD POWER AVAILABLE light illuminated, SOURCE OFF lights extinguished, GEN OFF BUS lights illuminated, TRANSFER BUS OFF lights extinguished, APU GEN OFF BUS light illuminated.
  4. GRD POWER AVAILABLE light illuminated, SOURCE OFF lights extinguished, GEN OFF BUS lights illuminated, TRANSFER BUS OFF lights extinguished, APU GEN OFF BUS light extinguished. ✓
正确答案：GRD POWER AVAILABLE light illuminated, SOURCE OFF lights extinguished, GEN OFF BUS lights illuminated, TRANSFER BUS OFF lights extinguished, APU GEN OFF BUS light extinguished.　·　NG　·　来源 Chair Flight B737 Question Bank

172.If operating on a single IDG and an overload is sensed, the electrical system will shed the galleys and main bus from Transfer Bus 1 and then Transfer Bus 2 before then shedding the IFE busses if an overload is still sensed.

  1. True
  2. False ✓
正确答案：False　·　NG　·　来源 Chair Flight B737 Question Bank

173.Under normal conditions, what powers DC Bus 1?

  1. TR2
  2. TR1 and TR2 ✓
  3. TR1
  4. TR2 and TR3
正确答案：TR1 and TR2　·　NG　·　来源 Chair Flight B737 Question Bank

174.How is the auxiliary battery charger powered?

  1. Through the AC Standby Bus
  2. Through the AC Ground Service Bus ✓
  3. Through Ground Service Bus 2
  4. Through DC Bus 1
正确答案：Through the AC Ground Service Bus　·　NG　·　来源 Chair Flight B737 Question Bank

175.In the event of the loss of all engine and APU IDGs, the Standby Power system will provide what electrical power?

  1. 115V AC and 22 to 30V DC.
  2. 24V DC .
  3. 22-30V DC
  4. 115V AC and 24V DC ✓
正确答案：115V AC and 24V DC　·　NG　·　来源 Chair Flight B737 Question Bank

176.The SOURCE OFF light illuminates whenever an IDG has tripped offline due to overheating.

  1. True
  2. False ✓
正确答案：False　·　NG　·　来源 Chair Flight B737 Question Bank

177.The Aircraft battery need to be selected ON for STANDBY operation of the Forward Airstairs from the FWD Attendant's Panel?

  1. True ✓
  2. False
正确答案：True　·　NG　·　来源 Chair Flight B737 Question Bank
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