Vayudoot Aviation

1. 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.

False

True

2. When does the RAT automatically deploy?

Electrical power to both AC BUS #1 & #2 is lost and the aircraft speed is above 100 knots.

Both are correct.

With the loss of two hydraulic systems.

3. If normal electrical power is lost; essential cockpit lighting is maintained for the:

Right dome light (provided the dome selector is not off).

All of the above.

Captain’s instrument panel.

Standby compass

4. The normal priority for supplying electrical power to the AC busses is:

Engine generators, external power then APU

APU, external power then engine generators

External power, APU, then engine generators

External power, engine generators then APU

5. The number 1 AC bus channel normally supplies power to _____ and to the _____ bus which supplies power to the ______ bus.

TR2 / AC ESS SHED / DC ESS SHED

TR1 / AC ESS / DC ESS SHED

TR1 / AC ESS SHED / DC ESS

TR1 / AC ESS / AC ESS SHED

6. While operating on Emergency Electrical Power with the landing gear lowered which of the following control laws is in effect?

Alternate.

Backup

Direct.

Backup or alternate

7. What is the function of the GEN 1 LINE push button?

When selected OFF the #1 generator powers all AC busses.

When selected OFF the avionics compartment isolation valves close.

When selected OFF generator # 1 is removed from all busses but continues to power one fuel pump in each wing.

8. Which of the following AC busses can be powered by the emergency generator?

AC bus 2

AC bus 1

AC ESS bus / AC ESS SHED bus

9. The BAT FAULT light will illuminate when:

Charging current decreases at an abnormal rate.

Charging current increases at an abnormal rate

Battery voltage is low

10. During the five seconds it takes for the RAT to extend:

The BATTERIES power both BATT HOT busses, ESS DC, and ESS AC through the STATIC INVERTER.

The BATTERIES power both BATT HOT busses.

The STATIC INVERTER powers both BATT HOT busses, ESS DC, and ESS AC through the ESS AC SHED busses.

The BATTERIES power both BATT HOT busses, ESS DC SHED, and ESS AC SHED through the STATIC INVERTER.

11. Which flight control computer will be inoperative with gear extension while in the Emergency Electrical Configuration?

FAC 1

FAC 1 and ELAC 1.

SEC 1 and ELAC 1

SEC 1

12. The IDG Fault light indicates:

IDG low oil pressure or IDG oil overheat

An IDG oil overheat

IDG has been disconnected

IDG low oil pressure.

13. A battery fault light will illuminate when:

Battery charging current increases at an abnormal rate.

Battery voltage drops below a predetermined level.

The batteries have auto disconnected due to low voltage.

14. If the battery voltages are below the minimum, how do you charge them?

I have to switch the external power to ON and switch the batteries off.

You have to call a mechanic because the batteries can only be charged by maintenance.

I have to check that the BAT pushbuttons are on and switch the external power on.

I have to start the APU as the batteries can only be charged by the APU generator.

15. Do not depress the IDG DISCONNECT switch for more than _______ to prevent damage to the disconnect mechanism.

7 seconds

3 seconds

10 seconds

15 seconds

16. On the cockpit overhead panel, there is a three position EMERGENCY EXIT Light switch. What lights are associated with this switch?

Exit signs, emergency lights, dome lights, main panel flood lights, and the standby compass light.

Exit signs, emergency lights, main panel flood lights, and escape path lighting.

Exit signs, emergency lights, and escape path lighting.

17. Are there any limitations associated with disconnecting an IDG?

Never disconnect an IDG unless the engine is running, nor push the IDG disconnect push button for more than 3 seconds.

There is no limitation

Never disconnect an IDG in flight, or push the IDG disconnect push button for more than 30 seconds.

Never disconnect an IDG in flight, or push the IDG disconnect push button for more than 5 seconds.

18. The RAT is connected directly (mechanically) to the Emergency Generator

False

True

19. The engine generators and APU generator are rated at _____ KVA.

50

110

70

90

20. The emergency generator supplies power as long as:

The landing gear is down.

The RAT is deployed and the landing gear is down

The RAT is deployed.

The landing gear is up.

21. When will the RAT & EMER GEN red FAULT light illuminate?

Both are correct.

When the EMER GEN is not supplying electrical power, AC busses #1 & #2 are unpowered and the nose gear is up.

When the RAT is deployed using hydraulic RAT MAN ON push button.

22. If both engine generators are powering the system, and one subsequently fails, are any busses unpowered?

Only the AC ESS shed bus.

No, but some loads are shed in both main galleys.

Yes, those associated with the failed generator.

23. The APU is supplying the electrical system. What is the order of priority for the different generators?

External power, engines, APU.

APU, engines, external power.

APU, external power, engines.

Engines, external power, APU.

24. What is the significance of the green collared circuit breakers?

Green collared circuit breakers are monitored by the ECAM.

Green collared circuit breakers are AC powered.

Green collared circuit breakers are not to be reset.

Green collared circuit breakers are pulled when flying on battery power only.

25. You enter a dark cockpit, what action is necessary before checking the battery voltages?

You have to check that the external power is on.

You have to ensure that both batteries are on.

You have to ensure that at least one battery is on.

You have to verify that both batteries are off.

26. How many times can you reset a circuit breaker?

Once, if authorized by the procedures.

Twice.

Once.

Twice, if authorized by the procedures.

27. What is the minimum voltage when conducting a BATTERY CHECK?

Less than 60 amps in 10 seconds.

Greater than 25 volts.

28 volts.

Greater than 24 volts.

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

AC bus #1 unpowered

AC SHED bus unpowered

DC ESS SHED bus unpowered

DC bus #2 unpowered

29. The A-320 has _______ batteries in its main electrical system.

3 (4 when ETOPS capable)

2

3

1

30. Is it possible to parallel generators?

The electrical system will not allow “paralleling” of generators.

Only with the RAT deployed.

Of course yes.

Only one engine generator may be paralleled with the APU.

31. Having started the APU, how can you get the APU generator to power the electrical system?

You are unable to as the APU power output is outside normal parameters.

The APU generator must be switch on.

By pushing the BUS TIE pushbutton.

By pushing the EXT PWR pushbutton thus disconnecting the external power.

32. After landing, in the emergency electrical configuration: the batteries automatically connect to the DC BAT bus when speed decreases below _______ knots.

90

70

100

50

33. During a routine flight, which of the following would result after the loss of Gen #2 and the subsequent start of the APU?

All systems return to normal and the RAT must be restowed.

The APU would now power both sides of the electrical system.

Eng gen #1 continues to power AC bus #1 and downstream systems. The APU powers AC bus #2 and downstream systems.

34. Which voltage requires recharging or replacing the batteries?

24 volts or less

20 volts or less.

26 volts or less.

25 volts or less.

35. What cockpit lighting is available during an emergency electrical situation?

Located on normal circuit breaker panels.

Right side dome light, main panel flood lights, and the standby compass light.

Right side Dome light, main panel flood lights (left two columns only), and the standby compass light.

Emergency path lighting only.

36. An AC ESS FEED switch located on the overhead panel shifts the power source for the AC ESS bus from:

AC bus 1 to AC Grnd/Flt bus

AC bus1 to AC bus 2

AC bus 2 to AC bus 1

37. If batteries are the only source of power in flight, how long will battery power be available?

Two hours and 30 minutes dependent on equipment in use.

Until the APU is started.

45 minutes dependent on equipment in use.

Between 22 and 30 minutes depending on equipment in use.

38. What is the function of APU GEN push button located on the overhead electrical panel?

When selected to OFF the APU generator field is de-energized.

Both are correct.

Push this button to automatically start the APU.

39. The BATTERY BUS is normally powered by:

DC bus 1 through a DC tie control relay.

DC BUS 1 and DC BUS 2

DC BUS 2

DC bus 2 through a DC tie control relay.

40. What is the significance of the circuit breakers on the overhead panel?

They may be operational in the Emergency Electrical Configuration.

They are not monitored by ECAM.

They are mainly AC powered.

Cannot be reset.

41. When no other power is available in flight, the static inverter converts _____ power to AC power for the ______ bus; and ______ powers the _______ bus.

BAT1 DC / AC ESS SHED / BAT2 / DC ESS SHED

BAT1 DC / AC ESS bus / BAT2 / DC ESS

BAT1 DC / AC ESS bus / BAT2 / DC ESS SHED

BAT1 DC / AC ESS bus / DC ESS

Question Bank

Questions for Electricals A320