Electrical Flashcards by Robert Savu

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

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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

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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

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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.

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

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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

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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

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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

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

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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

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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.

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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

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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

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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.

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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.

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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.

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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

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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.

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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.

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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.

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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.

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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.

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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.

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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

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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.

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.

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.

``` 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 ```

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

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.

``` 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. ```

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*

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

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.

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.

``` 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 ```

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.

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.

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

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.

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.

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.

``` 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. ```

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

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.

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.

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.

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.

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.

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

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.

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

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

``` 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 ```

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.

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

``` 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 ```

``` 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 ```

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

``` 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 ```

``` 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 ```

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.

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

``` 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 ```