Vayudoot Aviation

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

50

70

100

90

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

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

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

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

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

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.

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

4. The emergency generator supplies power as long as:

The landing gear is up.

The RAT is deployed and the landing gear is down

The landing gear is down.

The RAT is deployed.

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

DC ESS SHED bus unpowered

DC bus #2 unpowered

AC bus #1 unpowered

AC SHED bus unpowered

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

You have to verify that both batteries are off.

You have to ensure that both batteries are on.

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

You have to check that the external power is on.

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

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

When selected OFF the avionics compartment isolation valves close.

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

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

Both are correct.

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

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

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

Push this button to automatically start the APU.

Both are correct.

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

10. 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 bus / BAT2 / DC ESS

BAT1 DC / AC ESS bus / DC ESS

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

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

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

True

False

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

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

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

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

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

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

Engines, external power, APU.

External power, engines, APU.

APU, external power, engines.

APU, engines, external power.

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

2

3 (4 when ETOPS capable)

3

1

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

110

50

90

70

16. The IDG Fault light indicates:

IDG low oil pressure or IDG oil overheat

IDG has been disconnected

An IDG oil overheat

IDG low oil pressure.

17. The BATTERY BUS is normally powered by:

DC bus 2 through a DC tie control relay.

DC bus 1 through a DC tie control relay.

DC BUS 1 and DC BUS 2

DC BUS 2

18. Is it possible to parallel generators?

Only with the RAT deployed.

Of course yes.

Only one engine generator may be paralleled with the APU.

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

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

SEC 1 and ELAC 1

SEC 1

FAC 1

FAC 1 and ELAC 1.

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

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

Only the AC ESS shed bus.

Yes, those associated with the failed generator.

21. 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

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

AC bus1 to AC bus 2

AC bus 2 to AC bus 1

AC bus 1 to AC Grnd/Flt bus

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

AC ESS bus / AC ESS SHED bus

AC bus 1

AC bus 2

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

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

The APU generator must be switch on.

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

By pushing the BUS TIE pushbutton.

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

They are not monitored by ECAM.

Cannot be reset.

They may be operational in the Emergency Electrical Configuration.

They are mainly AC powered.

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

Backup

Alternate.

Backup or alternate

Direct.

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

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

Green collared circuit breakers are not to be reset.

Green collared circuit breakers are monitored by the ECAM.

Green collared circuit breakers are AC powered.

28. The BAT FAULT light will illuminate when:

Battery voltage is low

Charging current increases at an abnormal rate

Charging current decreases at an abnormal rate.

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

Greater than 25 volts.

Less than 60 amps in 10 seconds.

28 volts.

Greater than 24 volts.

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

APU, external power then engine generators

External power, APU, then engine generators

Engine generators, external power then APU

External power, engine generators then APU

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

Once.

Twice, if authorized by the procedures.

Once, if authorized by the procedures.

Twice.

32. Which voltage requires recharging or replacing the batteries?

26 volts or less.

20 volts or less.

24 volts or less

25 volts or less.

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

Captain’s instrument panel.

Standby compass

All of the above.

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

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

TR1 / AC ESS SHED / DC ESS

TR1 / AC ESS / AC ESS SHED

TR1 / AC ESS / DC ESS SHED

TR2 / AC ESS SHED / DC ESS SHED

35. 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

36. 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.

Between 22 and 30 minutes depending on equipment in use.

Until the APU is started.

45 minutes dependent on equipment in use.

37. When does the RAT automatically deploy?

Both are correct.

With the loss of two hydraulic systems.

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

38. 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.

39. A battery fault light will illuminate when:

The batteries have auto disconnected due to low voltage.

Battery voltage drops below a predetermined level.

Battery charging current increases at an abnormal rate.

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

Emergency path lighting only.

Located on normal circuit breaker panels.

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

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

41. 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 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.

The BATTERIES power both BATT HOT busses.

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