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Electrical Flashcards

1
Q 
Q 01: The engine generators and APU generator are rated at \_\_\_\_\_ KVA. 
A: 50
B: 70
C: 90
D: 110
A

C

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2
Q

Q 02: The number 1 AC bus channel normally supplies power to _____ and to the _____ bus which supplies power to the ______ bus.
A: TR2 / AC ESS SHED / DC ESS SHED B: TR1 / AC ESS SHED / DC ESS
C: TR1 / AC ESS / AC ESS SHED
D: TR1 / AC ESS / DC ESS SHED

A

C

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3
Q

Q 03: The normal priority for supplying electrical power to the AC busses is:
A: External power, engine generators then APU
B: External power, APU, then engine generators
C: APU, external power then engine generators
D: Engine generators, external power then APU

A

D

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4
Q

Q 04: The BATTERY BUS is normally powered by:
A: DC BUS 2
B: DC BUS 1 and DC BUS 2
C: DC bus 1 through a DC tie control relay.
D: DC bus 2 through a DC tie control relay.

A

C

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5
Q 
Q 05: The A-320 has \_\_\_\_\_\_\_ batteries in its main electrical system. 
A: 1
B: 2
C: 3
D: 3 (4 when ETOPS capable)
A

B

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6
Q

Q 06: When no other power is available in flight, the static inverter converts _____ power to AC power for the ______ bus; and ______ powers the _______ bus.
A: BAT1 DC / AC ESS bus / BAT2 / DC ESS
B: BAT1 DC / AC ESS SHED / BAT2 / DC ESS SHED
C: BAT1 DC / AC ESS bus / BAT2 / DC ESS SHED
D: BAT1 DC / AC ESS bus / DC ESS

A

A

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7
Q

Q 07: An AC ESS FEED switch located on the overhead panel shifts the power source for the AC ESS bus from:
A: AC bus1 to AC bus 2
B: AC bus 1 to AC Grnd/Flt bus
C: AC bus 2 to AC bus 1

A

A

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8
Q

Q 08: Which of the following AC busses can be powered by the emergency generator?
A: AC bus 1
B: AC bus 2
C: AC ESS bus / AC ESS SHED bus

A

C

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9
Q

Q 09: The RAT is connected directly (mechanically) to the Emergency Generator
A: True
B: False

A

B

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10
Q 
Q 10: After landing, in the emergency electrical configuration: the batteries automatically connect to the DC BAT bus when speed decreases below \_\_\_\_\_\_\_ knots.
A: 50 
B: 70 
C: 90 
D: 100
A

D

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11
Q

Q 11: The BAT FAULT light will illuminate when:
A: Battery voltage is low
B: Charging current increases at an abnormal rate
C: Charging current decreases at an abnormal rate.

A

B

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12
Q 
Q 12: Do not depress the IDG DISCONNECT switch for more than \_\_\_\_\_\_\_ to prevent damage to the disconnect mechanism.
A: 3 seconds
B: 7 seconds 
C: 10 seconds 
D: 15 seconds
A

A

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13
Q 
Q 13: The IDG Fault light indicates:
A: An IDG oil overheat
B: IDG low oil pressure.
C: IDG low oil pressure or IDG oil overheat
 D: IDG has been disconnected
A

C

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14
Q

Q 14: If normal electrical power is lost; essential cockpit lighting is maintained for the:
A: Captain’s instrument panel.
B: Standby compass
C: Right dome light (provided the dome selector is not off).
D: All of the above.

A

D

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15
Q

Q 15: You enter a dark cockpit, what action is necessary before checking the battery voltages?
A: You have to check that the external power is on.
B: You have to ensure that at least one battery is on.
C: You have to ensure that both batteries are on.
D: You have to verify that both batteries are off.

A

D

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16
Q

Q 16: Having started the APU, how can you get the APU generator to power the electrical system?
A: The APU generator must be switch on.
B: By pushing the EXT PWR pushbutton thus disconnecting the external power.
C: By pushing the BUS TIE pushbutton.
D: You are unable to as the APU power output is outside normal parameters.

A

B

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17
Q

Q 17: Are there any limitations associated with disconnecting an IDG?
A: Never disconnect an IDG in flight, or push the IDG disconnect push button for more than 30 seconds.
B: There is no limitation
C: Never disconnect an IDG in flight, or push the IDG disconnect push button for more than 5 seconds.
D: Never disconnect an IDG unless the engine is running, nor push the IDG disconnect push button for more than 3 seconds

A

D

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18
Q

Q 18: Which voltage requires recharging or replacing the batteries? A: 20 volts or less.
B: 24 volts or less.
C: 25 volts or less.
D: 26 volts or less.

A

C

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19
Q 
Q 19: The APU is supplying the electrical system. What is the order of priority for the different generators?
A: Engines, external power, APU.
B: APU, engines, external power. 
C: External power, engines, APU. 
D: APU, external power, engines.
A

A

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20
Q

Q 20: What is the significance of the green collared circuit breakers?
A: Green collared circuit breakers are pulled when flying on battery power only.
B: Green collared circuit breakers are monitored by the ECAM.
C: Green collared circuit breakers are not to be reset.
D: Green collared circuit breakers are AC powered.

A

B

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21
Q

Q 21: If batteries are the only source of power in flight, how long will battery power be available?
A: Between 22 and 30 minutes depending on equipment in use.
B: Until the APU is started.
C: Two hours and 30 minutes dependent on equipment in use.
D: 45 minutes dependent on equipment in use.

A

A

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22
Q

Q 22: What is the minimum voltage when conducting a BATTERY CHECK? A: 28 volts.
B: Less than 60 amps in 10 seconds.
C: Greater than 24 volts.
D: Greater than 25 volts.

A

D

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23
Q

Q 23: A battery fault light will illuminate when:
A: The batteries have auto disconnected due to low voltage.
B: Battery voltage drops below a predetermined level.
C: Battery charging current increases at an abnormal rate.

A

C

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24
Q 
Q 24: Which flight control computer will be inoperative with gear extension while in the Emergency Electrical Configuration? 
A: FAC 1 and ELAC 1.
B: SEC 1
C: SEC 1 and ELAC 1
D: FAC 1
A

D

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25
Q

Q 25: If the battery voltages are below the minimum, how do you charge them?
A: You have to call a mechanic because the batteries can only be charged by maintenance.
B: I have to check that the BAT pushbuttons are on and switch the external power on.
C: I have to switch the external power to ON and switch the batteries off.
D: I have to start the APU as the batteries can only be charged by the APU generator.

A

B

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26
Q

Q 26: What is the function of APU GEN push button located on the overhead electrical panel?
A: Push this button to automatically start the APU.
B: When selected to OFF the APU generator field is de-energized.
C: Both are correct.

A

B

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27
Q

Q 27: Is it possible to parallel generators?
A: Of course yes.
B: Only with the RAT deployed.
C: The electrical system will not allow “paralleling” of generators.
D: Only one engine generator may be paralleled with the APU.

A

C

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28
Q 
Q 28: While operating on Emergency Electrical Power with the landing gear lowered which of the following control laws is in effect? 
A: Backup.
B: Direct.
C: Alternate.
D: Backup or alternate
A

B

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29
Q

Q 29: What cockpit lighting is available during an emergency electrical situation?
A: Emergency path lighting only.
B: Right side Dome light, main panel flood lights (left two columns only), and the standby compass light.
C: Located on normal circuit breaker panels.
D: Right side dome light, main panel flood lights, and the standby compass light.

A

B

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30
Q

Q 30: What is the function of the GEN 1 LINE push button?
A: When selected OFF the avionics compartment isolation valves close.
B: When selected OFF the #1 generator powers all AC busses.
C: When selected OFF generator # 1 is removed from all busses but continues to power one fuel pump in each wing.

A

C

31
Q

Q 31: During a routine flight, which of the following would result after the loss of Gen #2 and the subsequent start of the APU?
A: The APU would now power both sides of the electrical system.
B: All systems return to normal and the RAT must be restowed.
C: Eng gen #1 continues to power AC bus #1 and downstream systems. The APU powers AC bus #2 and downstream systems.

A

C

32
Q

Q 32: When does the RAT automatically deploy?
A: With the loss of two hydraulic systems.
B: Electrical power to both AC BUS #1 & #2 is lost and the aircraft speed is above 100 knots.
C: Both are correct.

A

B

33
Q

Q 33: During the five seconds it takes for the RAT to extend:
A: The BATTERIES power both BATT HOT busses, ESS DC SHED, and ESS AC SHED through the STATIC INVERTER. B: The BATTERIES power both BATT HOT busses, ESS DC, and ESS AC through the STATIC INVERTER.
C: The STATIC INVERTER powers both BATT HOT busses, ESS DC, and ESS AC through the ESS AC SHED busses.
D: The BATTERIES power both BATT HOT busses.

A

B

34
Q

Q 34: The purpose of the AUTO BUS TIE is to allow either engine-driven IDG to automatically power both main AC buses in the event of a generator loss until either ground power or the APU generator is activated.
A: True.
B: False.

A

A

35
Q

B: False.
Q 35: When will the RAT & EMER GEN red FAULT light illuminate?
A: When the EMER GEN is not supplying electrical power, AC busses #1 & #2 are unpowered and the nose gear is up.
B: When the RAT is deployed using hydraulic RAT MAN ON push button. C: Both are correct.

A

A

36
Q

Q 36: What is the significance of the circuit breakers on the overhead panel?
A: They are not monitored by ECAM.
B: Cannot be reset.
C: They may be operational in the Emergency Electrical Configuration.
D: They are mainly AC powered.

A

C

37
Q

Q 37: If both engine generators are powering the system, and one subsequently fails, are any busses unpowered?
A: Only the AC ESS shed bus.
B: No, but some loads are shed in both main galleys.
C: Yes, those associated with the failed generator.

A

B

38
Q

Q 38: How many times can you reset a circuit breaker?
A: Once.
B: Once, if authorized by the procedures.
C: Twice.
D: Twice, if authorized by the procedures.

A

B

39
Q

Q 39: On the cockpit overhead panel, there is a three position EMERGENCY EXIT Light switch. What lights are associated with this switch?
A: Exit signs, emergency lights, and escape path lighting.
B: Exit signs, emergency lights, main panel flood lights, and escape path lighting.
C: Exit signs, emergency lights, dome lights, main panel flood lights, and the standby compass light.

A

A

40
Q 
Q 40: Which flight control computers are operational in the Emergency Electrical Power configuration (gear down and batteries powering the system)?
A: All are operational.
B: ELAC 1, SEC 1, and FAC 1.
C: ELAC 1 and 2, SEC 1 and 2, FAC 1. 
D: ELAC 1 and SEC 1.
A

D

41
Q

Q 41: The emergency generator supplies power as long as:
A: The landing gear is down.
B: The RAT is deployed
C: The RAT is deployed and the landing gear is down
D: The landing gear is up*

A

D

42
Q

Q 42: Which radios are inoperative with gear extension while in the emergency electrical configuration?
A: DME 1 and transponder 1
B: DME 1, DDRMI, and transponder 1. C: DME, and transponder 1.
D: ILS 2, DME, and ADF

A

A

43
Q

Q 43: While operating on Emergency Electrical Power with the landing gear lowered which of the following statements is correct?
A: If the APU is not operating it should be started at this time.
B: The APU will not start until the aircraft has come to a complete stop and all power has been removed for 15 seconds.
C: On the ground at 100 knots, the DC BATTERY BUS automatically reconnects to the batteries allowing APU start.
D: At 70 knots ESS AC is disconnected from the batteries.

A

C

44
Q

Q 44: If during a normal flight the BUS TIE push button is depressed to “OFF”, what effect would this have on power to the busses?
A: None.
B: All power would be lost and the aircraft would be powered by the batteries until the RAT was up to speed.
C: The power transfer would switch to the opposite bus.
D: This is not possible as the bus tie contactors are locked out during flight.

A

A

45
Q 
Q 45: While operating on Emergency Electrical Power (EMER GEN powering the system, FAC #1 reset) which of the following control laws are in effect?
A: Manual
B: Alternate.
C: Backup
D: Manual and backup
A

B

46
Q

Q 46: Can you reconnect an IDG in flight?
A: Yes, but only after contacting maintenance control.
B: Yes, push and hold the IDG pb until the GEN fault light is no longer illuminated.
C: No, it is not possible.

A

C

47
Q

C: No, it is not possible.
Q 47: Which communication and navigation radios are operational in the Emergency Electrical Configuration with the EMER GEN powering the system?
A: ACP 1 and 2, VHF 1, HF, RMP 1, VOR 1, and ILS 1.
B: VHF 1, RMP 1, VOR 1.
C: RMP #1 & #2, VHF #1, HF (if equipped), ACP #1, VOR #1 and ILS #1. D: All radios are lost.

A

A

48
Q

Q 48: What is the meaning of the green AVAIL light?
A: External power is plugged in and parameters are normal. You must push the external power to connect it
B: External power is available to the batteries only.
C: The external power panel door has been opened
D: External power is supplying the aircraft systems

A

A

49
Q

D: External power is supplying the aircraft systems
Q 50: What does the blue EXT PWR ON light mean?
A: External power is plugged in and parameters are normal
B: External power is supplying the aircraft’s electrical system.
C: There is a fault with the external power.

A

B

50
Q

Q 51: If EXTERNAL power is available and within limits:
A: It will automatically close the bus tie contactors when connected by the ground crew.
B: The green AVAIL light will illuminate on the EXT PWR push button.
C: The BUS TIE push button illuminates.

A

B

51
Q

Q 52: Is it possible to determine the source of power for aircraft busses
A: It is indicated on the electrical schematic overhead.
B: No it is not possible.
C: Yes, press the ECAM ELEC push button and view the electrical schematic on the ECAM
D: Only when operating in the Emergency Electrical Configuration.

A

C

52
Q 
Q 53: Both batteries are charged by the external power unit. Approximately how long does the charging process take? 
A: 10 minutes.
B: 20 minutes.
C: 30 minutes.
D: Between 30 and 45 minutes.
A

B

53
Q

Q 54: The GALLEY FAULT light illuminates when any generator is exceeding 80% of its rated output.
A: True.
B: False.

A

B

54
Q

Q 55: While operating on Emergency Electrical Power (EMER GEN powering the system) what should the crew accomplish prior to lowering the landing gear?
A: Check to see that the FMGC has auto tuned the appropriate NAV facility for the approach to be accomplished.
B: Depress the guarded RMP NAV push button and tune the appropriate NAV facility and course for the approach to be accomplished
C: Both are correct.

A

B

55
Q

Q 56: What would cause the GALLEY fault light to illuminate?
A: The flight attendants have all the coffee makers and ovens on at once. B: The Main Galley has shed.
C: The load on any generator is above 100% of its rated output.
D: The Aft Galley has shed.

A

C

56
Q

Q 57: While operating on Emergency Electrical Power (EMER GEN powering the system) how is it possible to properly complete the ECAM checklist with only an upper display?
A: Depress and hold the specific ECAM page push button on the ECAM control panel.
B: Transfer occurs automatically.
C: This is not possible. Use the cockpit operating manual.

A

A

57
Q

C: This is not possible. Use the cockpit operating manual.
Q 58: After IDG disconnection why do you get a GALLEY SHED indication on the SD?
A: It is a reminder to push the GALLEY pushbutton to manually shed the main galley.
B: It is a reminder to get the flight attendants to switch off galley equipment to decrease the load on the remaining generator.
C: It is a reminder that the main galley has been shed automatically following the loss of one generator.

A

C

58
Q

Q 59: Which busses will be powered after the RAT is extended and the EMER GEN begins producing power?
A: BATT HOT busses, ESS DC, ESS DC SHED, ESS AC and ESS AC SHED.
B: The STATIC INVERTER would power both HOT BATT busses, ESS DC and ESS AC through the ESS AC SHED busses.
C: The BATTERIES would power both HOT BATT busses, ESS DC and ESS AC through the STATIC INVERTER.
D: ESS DC, ESS DC SHED, ESS AC and ESS AC SHED.

A

A

59
Q

Q 60: Engine #1 has just been started and the APU is inoperative. The EXT PWR push button blue ON light is illuminated. Which of the statements below is correct?
A: External power is supplying all electrical needs.
B: Engine Gen #1 is supplying AC bus #1 and the downstream systems, and AC bus #2 through the bus tie contactors.
C: Gen #1 supplies AC bus #1 and (generally) the downstream systems; Ext power supplies AC bus #2

A

C

60
Q

Q 61: In cruise, you have suddenly a Master Warning and caution comes on with ELEC EMER CONFIG and APP OFF. You notice a red FAULT light on the RAT & EMER GEN pushbutton. What do you think of this indication?
A: The EMER GEN is not yet supplying the system.
B: The RAT has failed. You will have to turn the batteries to OFF.
C: The FAULT light is always on when are in ELEC EMER CONFIG.
D: The RAT has failed, you have to try to reconnect both IDG’s.

A

A

61
Q

Q 62: When are the Essential Shed buses powered by the battery?
A: Never. The purpose of the shed buses is to reduce the load on the batteries.
B: In case of double generator failure. C: After every IDG connection

A

A

62
Q

Q 63: The AC Essential bus is powered by the battery at speed above 50 kt.
A: True.
B: False.

A

A

63
Q 
Q 64: In normal electrical configuration, how is DC ESS bus supplied:
A: From TR 1 via DC Bus 1 and DC Bat Bus
B: From ESS TR 
C: From TR 2 
D: From Bat 2
A

A

64
Q

Q 65: What happens in case of total loss of main generators?
A: The RAT is automatically extended and powers the yellow system which drives the emergency generator
B: The RAT is automatically extended and powers the blue system which drives the emergency generator
C: The RAT has to be manually extended
D: The RAT is extended and mechanically connected to the emergency generator.

A

B

65
Q

Q 66: DC Bat Bus can be supplied by: A: DC Bus 1 or batteries
B: DC Bus 1, DC Bus 2 or batteries
C: DC Bus 2 or batteries
D: DC Bus 1 only

A

B

66
Q 
Q 67: Normal minimum battery voltage before APU start is: 
A: No minimum
B: 27.5 Volts
C: 25.5 Volts
D: 22.5 Volts
A

C

67
Q 
Q 68: When disconnecting the IDG the button should be pressed: 
A: For no more than 5 seconds
B: Until the fault light goes out
C: For longer than 3 seconds
D: For no more than 3 seconds
A

D

68
Q

Q 69: Where can the battery voltage be checked?
A: On the ECAM elec. Page only
B: On the elec. overhead panel and ECAM E/WD
C: On the elec. overhead panel only
D: On the elec. overhead panel and ECAM elec. Page

A

D

69
Q 
Q 70: In flight on batteries only, the AC ESS Shed bus and DC ESS Shed bus are lost.
A: Yes
B: No
C: Only A/C ESS Shed Bus is lost 
D: Only D/C ESS Shed Bus is lost
A

A

70
Q 
Q 71: The static inverter works:
A: Always
B: When aircraft speed is > 50 kt and on batteries only 
C: When one main generator fails
D: Only when generator 2 fails
A

B

71
Q

Q 72: If a TR fails:
A: The other TR automatically replaces the faulty one and the ESS TR supplies the DC Ess Bus
B: The static inverter replaces the faulty TR
C: The DC Bus on the faulty side is lost
D: The Emergency generator supplies DC power on the faulty side.

A

A

72
Q

Q 73: In flight in case of loss of all main generators, emergency generator not running, the DC ESS Bus is supplied by:
A: Hot bus 2
B: ESS TR
C: Hot Bus and ESS TR D: Hot Bus 1

A

A

73
Q 
Q 74: If AC Bus 1 fails the AC ESS bus is supplied by: 
A: Emer Gen.
B: The RAT
C: Static Inverter
D: AC Bus 2
A

D

Airbus (16 decks)

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