Question Bank - Airbus A320 06

Electricals

VI of XVIII

Q 01: The engine generators and APU generator are rated at _____ KVA.

A: 50

B: 70

C: 90

D: 110

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

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

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.

Q 05: The A-320 has _______ batteries in its main electrical system.

A: 1

B: 2

C: 3

D: 3 (4 when ETOPS capable)

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

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

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

Q 09: The RAT is connected directly (mechanically) to the Emergency Generator

A: True

B: False

Q 10: 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 11: 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

Q 12: 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.

Q 13: 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

Q 14: 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

Q 15: 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.

Q 16: 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.

Q 17: 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.

Q 18: 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.

Q 19: 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.

Q 20: 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.

Q 21: 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.

Q 22: With the EMER EXIT LT selector in the ARM position, which situation will activate the emergency lights and exit signs?

A: AC SHED bus unpowered

B: AC bus #1 unpowered

C: DC ESS SHED bus unpowered

D: DC bus #2 unpowered

Q 23: 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.

Q 24: 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.

Q 25: 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.

Q 26: 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

Q 27: 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 28: 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 29: 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 30: 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 31: 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 32: 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 33: 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 34: 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 35: 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 36: 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.

Q 37: 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 38: 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 39: 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 40: 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 41: 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 42: 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 43: 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 44: 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 45: 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 46: 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 47: 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.

Q 48: 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 49: Which condition will automatically illuminate the escape lights?

A: AC ESS SHED bus not powered.

B: Loss of power to the AC bus 1.

C: DC ESS BUS not powered.

D: DC ESS SHED bus not powered.

Q 50: 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

Q 51: 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 52: If EXTERNAL power is available and within limits:

A: It will automatically close the bus tie contactors’s 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 53: 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 54: 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 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: The GALLEY FAULT light illuminates when any generator is exceeding 80% of its rated output.

A: True.

B: False.

(Note - The GALLEY FAULT light illuminates when any generator is exceeding 100% of its rated output.)

Q 57: If the source of power for the ESS AC bus is lost, does another source of power automatically power the bus?

A: Yes, transfer is automatic.

B: Yes, only if AUTO was selected on the AC ESS FEED push button.

C: No, this must be done by the crew.

Q 58: 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 59: 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.

Q 60: 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 61: 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 62: 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 63: 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 64: 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 65: The AC Essential bus is powered by the battery at speed above 50 kt.

A: True.

B: False.

(Note - Below 50 kt the Essential bus is automatically shed and the CRT’s are lost.)

Q 66: 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 67: 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 68: 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 69: Normal minimum battery voltage before APU start is:

A: No minimum

B: 27.5 Volts

C: 25.5 Volts

D: 22.5 Volts

Q 70: 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 71: 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 72: 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 73: 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 74: 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 75: 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 76: 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