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Airbus A320-231 > A320-ATA-24 Electrical > Flashcards

A320-ATA-24 Electrical Flashcards

1
Q

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

A

90

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2
Q

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

A

TR1 / AC ESS / AC ESS SHED

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3
Q

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

A

Engine generators, external power then APU

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4
Q

The BATTERY BUS is normally powered by:

A

DC bus 1 through a DC tie control relay.

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5
Q

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

A

2

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6
Q

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

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7
Q

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

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8
Q

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

A

AC ESS bus / AC ESS SHED bus

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9
Q

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

A

FALSE

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10
Q

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

A

100

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11
Q

The BAT FAULT light will illuminate when:

A

Charging current increases at an abnormal rate

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12
Q

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

A

3 seconds

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13
Q

The IDG Fault light indicates:

A

IDG low oil pressure or IDG oil overheat

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14
Q

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

A

A: Captain’s instrument panel.
B: Standby compass
C: Right dome light (provided the dome selector is not off).

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15
Q

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

A

You have to verify that both batteries are off.

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16
Q

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

A

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

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17
Q

Are there any limitations associated with disconnecting an IDG?

A

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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18
Q

Which voltage requires recharging the batteries?

A

25.5 or less

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19
Q

What is the significance of the green collared circuit breakers?

A

Green collared circuit breakers are monitored by the ECAM

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20
Q

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.

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21
Q

What is the minimum voltage when conducting a BATTERY CHECK?

A

Greater than 25.5 volts.

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22
Q

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

A

FAC 1

23
Q

Is it possible to parallel generators?

A

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

24
Q

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

A

Direct.

25
Q

What cockpit lighting is available during an emergency electrical situation?

A

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

26
Q

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

A

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

27
Q

During a routine flight, what will be the result after the loss of Gen #2 and the subsequent start of the APU?

A

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

28
Q

When does the RAT automatically deploy?

A

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

29
Q

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

A

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

30
Q

True or False?

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.

31
Q

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.

32
Q

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

A

They may be operational in the Emergency Electrical Configuration.

33
Q

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

A

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

34
Q

How many times can you reset a circuit breaker?

A

Once, if authorized by the procedures.

35
Q

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.

36
Q

Which flight control computers are operational in the Emergency Electrical Power configuration (gear down and batteries powering the system)?

A

ELAC 1 and SEC 1.

37
Q

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.

38
Q

While operating on Emergency Electrical Power (EMER GEN powering the system, FAC #1 reset) which of the following control laws are in effect?

A

Alternate.

39
Q

Can you reconnect an IDG in flight?

A

No, it is not possible.

40
Q

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.

41
Q

Both batteries are charged by the external power unit. Approximately how long does the charging process take?

A

20 minutes.

42
Q

What would cause the GALLEY fault light to illuminate?

A

The load on any generator is above 100% of its rated output.

43
Q

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.

44
Q

After IDG disconnection why do you get a GALLEY SHED indication on the SD?

A

It is a reminder that the main galley has been shed automatically following the loss of one generator.

45
Q

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

Gen #1 supplies AC bus #1 and (generally) the downstream systems; Ext power supplies AC bus #2.

46
Q

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.

47
Q

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.

48
Q

In normal electrical configuration, how is DC ESS bus supplied:

A

From TR 1 via DC Bus 1 and DC Bat Bus

49
Q

What happens in case of total loss of main generators?

A

The RAT is automatically extended and powers the blue system which drives the emergency generator

50
Q

DC Bat Bus can be supplied by:

A

DC Bus 1, DC Bus 2 or batteries

51
Q

The static inverter works:

A

When aircraft speed is > 50 kt and on batteries only *

52
Q

If a TR fails:

A

The other TR automatically replaces the faulty one and the ESS TR supplies the DC Ess Bus

53
Q

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

54
Q

If AC Bus 1 fails the AC ESS bus is supplied by:

A

AC Bus 2

Airbus A320-231 (7 decks)

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