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A320 SKV > Electrical System > Flashcards

Flashcards in Electrical System Deck (36)
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1

In descending order, the priority for electrical power is

Onside engine generator, external power, APU, remaining engine generator

2

According to the graphic, what she powering the airplane

Engine driven generators (from the synoptic page)

3

What is a characteristic of the APU electrical system?

Can power the entire plane on the ground

4

What is a characteristic of the electrical system

System operation is normally automatic

5

The bus tie contractors open or close automatically to maintain power supply to AC busses 1 and 2 when the bus tie switch is in the _____ position

Auto (lights out)

6

While the APU is running and external power plugged in, what is the indication that the APU generator is powering the AC tie bus?

EXT PWR AVAIL light illuminated

7

EXT PWR AVAIL light indicates external power is

Plugged in and electrical parameters are normal

8

Following pushback, what is the configuration of the electrical system when engine 1 is running and the APU is operating

GEN 1 powers AC bus 1 and the APU generator powers AC bus 2

9

Do not hold the IDG disconnect switch for more than _____ to prevent possible damage to the disconnect mechanism

3 seconds

10

In the event of a single IDG failure, the remaining IDG powers

The entire electrical system, except for the main galley bus

11

Do not disconnect the IDG when the

Engine is not running or not windmilling

12

If the IDG 1 switch is pushed in-flight

IDG 1 can only be reconnected on the ground by maintenance

13

What occurs when an IDG is disconnected

The corresponding generator can no longer supply power

14

GALY & CAB FAULT light indicates

A generator load exceeds 100% of rated output

15

A GEN FAULT light indicates

The line contactor is open without selecting the respective GEN switch OFF

16

In flight, with only one-engine generator operating, how is the electrical system configured

The main galley power supply is automatically shed

17

In the event of a single TR failure, how is the DC system affected?

DC busses 1 and 2 will interconnect through the DC BAT bus. ESS TR powers the DC ESS bus

18

With the loss of TR 1, what pilot action is required

No action required: system automatically powers DC bus 1 with TR 2

19

Which bus normally powers the AC ESS bus

AC bus 1

20

AC ESS FEED FAULT light

Illuminates amber when AC ESS bus is not electrically powered

21

In case of AC bus 1 failure, the AC ESS bus can be transferred to AC bus 2 by

Doing nothing, system switching is automatic

22

AC and DC ESS SHED busses

Are shed when aircraft is on battery power only

23

What is a characteristic of the battery power system

An automatic cutoff logic prevents the batteries from becoming completely discharged on the ground

24

When flying on battery power only, what is the approximate battery endurance

22 minutes

25

A battery with low voltage can be charged by

Switching external power to ON and ensuring the affected BAT switch is ON

26

How are batteries charged

Automatically when DC power is supplied to the DC BAT bus and the BAT switches are ON

27

According to the graphic the batteries are

Being Charged (from the graphic on the slide)

28

BAT FAULT light indicates

Charging current is outside normal limits

29

The Emergency Electrical Configuration

Is the result of loss of AC busses 1 and 2 above 100 knots

30

In the Emergency Electrical Configuration, which Electronic Instrument System (EIS) displays are powered

PFD 1, ND 1, and upper ECAM