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AAL 737 > Electrical > Flashcards

Electrical Flashcards

1
Q

With Standby Power OFF light illuminated, you could power the standby busses directly from the battery by ____.

a. placing the standby power switch to BAT
b. turning the APU off
c. leaving the transfer bus switch in AUTO
d. placing the battery switch to ON

A

A. placing the standby power switch to BAT

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2
Q

DC power is supplied by ____.

a. voltage regulators and the transfer switch
b. the static inverter and the battery
c. transformer rectifier units, the battery charger, and the battery
d. DC generators

A

C. transformer rectifier units, the battery charger, and the battery

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3
Q

Normally, the AC electrical system is run ____.

a. paralleled
b. in sequence
c. alternately between AC Transfer Bus 1 and AC Transfer bus 2
d. isolated

A

D. isolated

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4
Q

The static inverter is powered by ____.

a. TR3
b. the battery
c. DC Bus #1
d. DC Bus #2

A

B. the battery

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5
Q

The Ground Service Switch is located _________________.

a. next to the Galley Power Switch
b. on the forward attendant panel
c. on the aft attendant panel
d. Both 1 and 3 are correct.

A

B. on the forward attendant pane

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6
Q

The DC Cross Bus Tie Relay will open ____.

a. when TR3 fails
b. at glideslope capture during a flight director or autopilot ILS approach
c. when power for one DC bus fails
d. when the Battery Switch is moved to BAT

A

B. at glideslope capture during a flight director or autopilot ILS approach

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7
Q

Circuit breakers are allowed to be pulled and reset ____.

a. if necessary for flight, only after a one minute cooling period
b. anytime on the ground or in flight
c. only for galleys or the fuel quantity indicating system
d. only if specified in a QRH procedure

A

D. only if specified in a QRH procedure

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8
Q

What conditions cause the GND POWER AVAILABLE light to be illuminated?

a. Ground power is plugged in and available.
b. Ground power is plugged in and meets airplane power quality standards.
c. Ground power is plugged in, and the Ground Power Available switch is moved to ON.
d. Ground power is plugged in and already in use.

A

B. Ground power is plugged in and meets airplane power quality standards.

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9
Q

After engine start, the crew forgets to put the generators on line and uses the APU to power the Transfer Busses for takeoff. If the APU fails, the ____.

a. galleys are load shed for the duration of flight
b. generators are automatically placed on line
c. system reverts to standby power only
d. airplane loses all electrical power

A

B. generators are automatically placed on line

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10
Q

On the ground with the APU powering the electrical systems, the APU GEN OFF BUS light will be _____.

a. OFF
b. ON
c. OFF until you turn off the APU when it comes back on
d. ON until you select GEN 1 or GEN 2 ON

A

A. OFF

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11
Q

When moved to OFF, the BUS TRANSFER switch will ____.

a. isolate the AC and DC Busses on Electrical System 1 from the AC and DC Busses on Electrical System 2
b. isolate the AC system from the DC system
c. immediately shift the primary source of power for the AC Standby Bus from AC Transfer Bus 1 to AC Transfer Bus 2
d. disconnect the battery from the electrical system

A

A. isolate the AC and DC Busses on Electrical System 1 from the AC and DC Busses on Electrical System 2

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12
Q

In a normally operating AC electrical system, if the Bus Transfer Switch is moved to OFF, ____.

a. both Transfer Busses are unpowered
b. the AC Standby Bus reverts to battery through the inverter
c. power is removed from AC Transfer Bus 2 only
d. and if a generator subsequently fails, the bus ties will not close to transfer power

A

D. and if a generator subsequently fails, the bus ties will not close to transfer power

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13
Q

If the Standby Power “OFF” light illuminates, it means ____ is/are not powered.

a. the AC Standby Bus
b. the DC Standby Bus
c. the Battery Bus
d. one or more of the above

A

D. one or more of the above

a. the AC Standby Bus
b. the DC Standby Bus
c. the Battery Bus
d. one or more of the above

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14
Q

With standby electrical power only, the Captain will be able to fly _____ instrument approaches.

a. LOC only
b. VOR
c. ILS
d. All of the above

A

D. All of the above

a. LOC only
b. VOR
c. ILS
d. All of the above

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15
Q

The AC standby bus can be powered by ____ if its normal power source fails.

a. the essential bus
b. the battery (through the static inverter)
c. Generator Bus No. 2
d. AC Transfer Bus No. 1

A

B. the battery (through the static inverter)

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16
Q

During an ILS approach, the cross bus tie relay automatically opens at glideslope capture to ____.

a. prevent single bus failure from affecting both navigation receivers and flight control computers
b. provide more power to the AC Standby bus
c. ensure that the Standby DC bus is powered
d. All of the above

A

A. prevent single bus failure from affecting both navigation receivers and flight control computers

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17
Q

With a normally operating electrical system, placing the Battery Switch OFF ____.

a. removes power to the Battery Bus and the Switched Hot Battery Bus
b. removes power to the Switched Hot Battery Bus only
c. causes all electrical power to fail
d. unpowers all five busses in the standby electrical system

A

A. removes power to the Battery Bus and the Switched Hot Battery Bus

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18
Q

The DC Standby Bus can be powered by ____.

a. TR1, TR2, TR3, and the battery
b. AC Transfer Bus 1 and the battery
c. the battery only
d. AC Transfer Bus 2 only

A

A. TR1, TR2, TR3, and the battery

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19
Q

Under what conditions can External power be used to power one AC Transfer Bus, and the APU the other Transfer Bus?

a. Only if you are on the ground
b. If the Bus Transfer Switch is in AUTO
c. If volts and frequencies check good
d. No condition. The electrical system will not allow it.

A

D. No condition. The electrical system will not allow it.

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20
Q

What does an illuminated ELEC light, on the AC and DC Metering Panel, mean?

a. A fault exists in the AC or standby power system.
b. TRs # 2 and 3 have failed.
c. A Standby Power or DC system fault has occurred.
d. TR # 1 has failed

A

C. A Standby Power or DC system fault has occurred.

21
Q

The BAT DISCHARGE light illuminated indicates excessive battery discharge is detected with the battery switch on. How long will the battery provide power?

a. A fully charged battery provides a minimum of 40 minutes of standby power.
b. A fully charged battery provides a minimum of 15 minutes of standby power.
c. A fully charged battery provides a minimum of 30 minutes of standby power.
d. A fully charged battery provides a minimum of 35 minutes of standby power.

A

C. A fully charged battery provides a minimum of 30 minutes of standby power

22
Q

If the TR Unit light illuminates, inflight, it means ____ have failed

a. TR1, TR2, and TR3
b. TR3 has failed or TR1 and TR2
c. TR2 has failed or TR1 and TR3
d. TR1 has failed or TR2 and TR3

A

D. TR1 has failed or TR2 and TR3

23
Q

If the TR Unit light illuminates on the ground, it means ____ has/have failed

a. any TR unit
b. TR3 has failed or TR1 and TR2
c. TR2 has failed or TR1 and TR3
d. TR1 has failed or TR2 and TR3

A

A. any TR unit

24
Q

In flight, if an engine generator fails, load shedding ____.

a. is designed to shed the main busses only
b. would not occur if the Bus Transfer Switch is in AUTO
c. would occur in the main busses first, followed by all galleys
d. is designed to shed electrical load incrementally

A

D. is designed to shed electrical load incrementally

25
Q

If you see these lights in flight, what do they indicate?

a. Power has been lost to both AC Transfer Busses.
b. The Standby AC Bus is not powered.
c. The Standby DC Bus is not powered.
d. The Battery Bus and Switched Hot Battery Bus are not powered.

A

A. Power has been lost to both AC Transfer Busses

26
Q

The QRH directs the crew to attempt a start of the APU. If the aircraft is below 25,000 ft, the APU __.

a. Will not start since AC power is lost
b. Will not start because there is no fuel boost pump pressure
c. should start with battery power and fuel suction feed
d. should start using power from TR1 and fuel suction feed

A

C. should start with battery power and fuel suction feed

27
Q

APU power is not available. Since we are on emergency power, the Right IRS is on DC power and will remain on DC for ____ minutes.

a. 12
b. 10
c. 5
d. 2

A

C. 5

28
Q

With these lights illuminated, ____.

a. the AC Transfer Bus 1 is no longer powered
b. the AC Transfer Bus 1 is being powered by lDG 2
c. the AC Transfer Bus 2 is no longer powered
d. all the busses are powered

A

A. the AC Transfer Bus 1 is no longer powered

29
Q

Which of the following is also true?

a. AC Main Bus 1 is still powered.
b. AC Standby Bus is being powered by the static inverter.
c. TR1 is powered.
d. All Galley Busses are still powered.

A

B. AC Standby Bus is being powered by the static inverter.

30
Q

Since AC Transfer Bus 1 is dead, ____.

a. the battery is not being charged because AC Ground Service Bus 1 is also dead
b. the battery is being charged through the static inverter
c. TR3 is powering the Battery Bus and charging the battery
d. the battery charger is being powered by AC Ground Service Bus 2

A

D. the battery charger is being powered by AC Ground Service Bus 2

31
Q

In flight, these two lights indicate that _____. Select the MOST CORRECT answer

a. IDG 1 has failed
b. engine 1 has failed and the APU failed to start
c. engine 1 has flamed out
d. either IDG 1 has failed or engine 1 has flamed out

A

D. either IDG 1 has failed or engine 1 has flamed out

32
Q

Which statement is true?

a. IDG 2 is powering both AC Transfer Busses.
b. IDG 2 is powering AC Transfer Bus 2, while the APU is powering AC Transfer Bus 1.
c. IDG 2 is powering AC Transfer Bus 2. AC Transfer Bus 1 is not powered.
d. Neither of the AC Transfer Busses are powered

A

A. IDG 2 is powering both AC Transfer Busses.

33
Q

Since IDG 1 is not powering AC Transfer Bus 1, the SOURCE OFF light remains illuminated. The QRH directs a start of the APU and a connection to the affected bus. Once this step is accomplished, what happens on the left side?

a. SOURCE OFF and GEN OFF BUS lights would extinguish.
b. SOURCE OFF and GEN OFF BUS lights would remain illuminated.
c. SOURCE OFF light and APU light would extinguish, and the GEN OFF BUS light would remain illuminated.
d. SOURCE OFF light remains illuminated and the GEN OFF BUS light extinguishes

A

C. SOURCE OFF light and APU light would extinguish, and the GEN OFF BUS light would remain illuminated.

34
Q

The illumination of this light means ___.

a. DC Bus 1 is not powered
b. DC Bus 2 is not powered
c. the Switched Hot Gallery Bus is not powered
d. Either the AC Standby Bus, the DC Standby Bus, the Battery Bus, or any combination of these three busses has lost power

A

D. Either the AC Standby Bus, the DC Standby Bus, the Battery Bus. or any combination of these three busses has lost power

35
Q

Select the correct answer to solve this problem

a. You should be able to repower the affected bus by moving the Battery Switch to BAT.
b. You should be able to repower the affected bus by moving the STANDBY POWER switch to OFF.
c. You should be able to repower the affected bus by moving the STANDBY POWER switch to BAT.
d. There is no way to re-power the affected bus.

A

C. You should be able to repower the affected bus by moving the STANDBY POWER switch to BAT.

36
Q

The QRH directs moving the STANDBY POWER switch to BAT. What source are you now using to re-power the affected bus?

a. TR1
b. TR2 and TR3
c. AC Main Busses 1 and 2
d. The battery

A

D. The battery

37
Q

Inflight, engine #1 experiences a loss of all thrust. This situation would also be accompanied by which of the following electrical system lights on the overhead panel.

a. #1 EEC ALTN light
b. #1 GEN OFF BUS, SOURCE OFF and DRIVE lights.
c. #1 ENGIN E CONTROL light
d. A steady OIL FILTER BYPASS alert for Engine # 1

A

B. #1 GEN OFF BUS, SOURCE OFF and DRIVE lights.

38
Q

If the engine #1 experiences a loss of thrust, illumination of the #1 DRIVE light is the result of ____.

a. Low IDG pressure
b. Engine failure
c. IDG Auto Disconnect
d. IDG Manual Disconnect

A

B. Engine failure

39
Q

You have confirmed that the #1 Engine and IDG have failed. The QRH will direct the crew to start the APU. If the APU is to be used as an electrical source only, the maximum altitude for APU operation is __ feet MSL.

a. 10,000
b. 17,000
c. 25,000
d. 41,000

A

D. 41,000

40
Q

The aircraft has been struck by lightning. You observe these conditions on the Electrical Panel and the MASTER CAUTION and ELEC Annunciator Lights illuminated. Before any corrections are attempted, which of the following components is still available?

a. Left EFIS Control Panel
b. Right EFIS Control Panel
c. VHF NAV No.2
d. Automatic cabin pressurization control

A

A. Left EFIS Control Panel

41
Q

The crew can’t restore normal electrical power and elects to divert and land ASAP. Focusing on the Left EFIS Control Panel, momentarily pressing the Radio Minimums Reset (RST) Switch ____.

a. Blanks the minimums display if the alert is active.
b. Resets the alert minimums annunciation.
c. If STD was displayed in the PFD Barometric Setting, resets the preselected barometric reference.
d. Resets the alert minimums annunciation and blanks the minimums display if the alert is active.

A

B. Resets the alert minimums annunciation.

42
Q

Since the aircraft is still on standby power, the Captain flies the approach and presses the Center (CTR) Switch on the Left EFIS Control Panel. This provides a full compass rose on the Left Nav Display in the __ Mode. Select the most correct answer.

a. APP
b. VOR
c. MAP
d. All of the above are correct.

A

D. All the above are correct

a. APP
b. VOR
c. MAP
d. All of the above are correct.

43
Q

If this combination of lights comes on, including the ELEC light on the overhead panel, _____.

a. resetting the Master Caution will not extinguish any of the lights
b. resetting the Master Caution will extinguish all of the lights, indicating a minor fault
c. resetting the Master Caution will not extinguish the ELEC light, thus the aircraft cannot be dispatched
d. and if the ELEC light does not extinguish after resetting the Master Caution, the aircraft can still be dispatched.

A

C. resetting the Master Caution will not extinguish the ELEC light, thus the aircraft cannot be dispatched

44
Q

When illuminated, the ELEC light indicates ____.

a. a fault located in one or more of the AC main systems, and you cannot be dispatched
b. a fault exists in the DC or AC system and you can be dispatched
c. a normal situation, and it will go out after the APU is started
d. a fault exists in the DC or standby power systems and you cannot be dispatched

A

D. a fault exists in the DC or standby power systems and you cannot be dispatched

45
Q

This ELEC light illuminates ____.

a. any time when faults exist and flaps are not up
b. only with the airplane on the ground
c. only on the ground after landing
d. only on the ground with flaps not down

A

B. only with the airplane on the ground

46
Q

During the APU Start, without AC power available, this light illuminates and ____.

a. indicates the battery is extremely weak, but the APU start should be accomplished
b. is a non-normal situation because the APU starts with AC power
c. is a temporary situation that should resolve itself when AC power is connected
d. the situation leads to a possible APU hot start and therefore needs to be monitored closely

A

C. is a temporary situation that should resolve itself when AC power is connected

47
Q

The APU is now started and AC power is applied. Assuming that everything is normal, the BAT DISCHARGE light should ______.

a. Extinguish indicating the battery charger is operational
b. remain on approximately five minutes before it will extinguish
c. take up to ten minutes to extinguish, depending on battery condition
d. extinguish immediately indicating TR3 is now charging the battery

A

A. Extinguish indicating the battery charger is operational

48
Q

If during flight, the master caution light and the electric annunciator alert you to the Bat Discharge light being on, ____.

a. this happens occasionally and the light should extinguish shortly when the battery charger reconnects
b. the battery charger is now charging the battery through the battery bus
c. the battery is possibly discharging while the battery charger switches to the number one ground service bus
d. the battery is indicating excessive discharge

A

D. the battery is indicating excessive discharge

AAL 737 (32 decks)

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