Systems - Electrical

Question 1

In descending order, the priority for electrical power is (FM: 8.60.10.1)

Answer 1

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

Question 2

According to the graphic, what is powering the airplane? (FM: 8.60.20.6)

Answer 2

Engine driven generators.

Question 3

What is a characteristic of the APU electrical system? (FM: 8.60.10.1)

Answer 3

Can power the entire airplane on the ground.

Question 4

What is a characteristic of the electrical system? (FM: 8.60.10.1)

Answer 4

System operation is normally automatic.

Question 5

The bus tie contactors open or close automatically to maintain power supply to AC busses 1 and 2 when the bus tie switch is in the _____ position. (FM: 8.60.20.3)

Answer 5

AUTO (lights out)

Question 6

With the APU running and external power plugged in, what is the indication that the APU generator is powering the AC tie bus?
(FM: 8.60.20.3)

Answer 6

EXT PWR AVAIL light illuminated.

Question 7

EXT PWR AVAIL light indicates external power is (FM: 8.60.20.3)

Answer 7

Plugged in and electrical parameters are normal.

Question 8

Following pushback, what is the configuration of the electrical system when engine 1 is running and the APU is operating. (FM: 8.60.20.6)

Answer 8

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

Question 9

Do not hold the IDG disconnect switch for more than ____ to prevent possible damage to the disconnect mechanism (FM: 8.60.20.2)

Answer 9

3 seconds

Question 10

In the event of a single IDG failure, the remaining IDG powers
(FM: 8.60.20.14)

Answer 10

The entire electrical system, except for the main galley bus.

Question 11

Do not disconnect the IDG when the (FM: 8.60.20.2)

Answer 11

Engine is not running or not windmilling.

Question 12

If the IDG 1 switch is pushed in-flight, (FM: 8.60.20.2)

Answer 12

IDG 1 can only be reconnected on the ground by maintenance.

Question 13

What occurs when an IDG is disconnected? (FM: 8.60.20.2)

Answer 13

The corresponding generator can no longer supply power.

Question 14

GALY & CAB FAULT light indicates (FM: 8.60.20.1)

Answer 14

A generator load exceeds 100% of rated output.

Question 15

A GEN FAULT light indicates (FM: 8.60.20.2)

Answer 15

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

Question 16

In flight, with only one engine generator operating, how is the electrical system configured? (FM: 8.60.20.14)

Answer 16

The main galley power supply is automatically shed.

Question 17

In the event of a TR failure, how is the DC system reconfigured?
(FM: 8.60.20.17)

Answer 17

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

Question 18

With a loss of TR 1, what pilot action is required? (FM: 8.60.10.3)

Answer 18

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

Question 19

In the normal configuration, which bus feeds the AC ESS bus?
(FM: 8.60.10.1)

Answer 19

AC bus 1.

Question 20

AC ESS FEED FAULT light (FM: 8.60.20.2)

Answer 20

Illuminates amber when AC ESS bus is not electrically powered.

Question 21

What bus provides an alternate source of power for the AC ESS bus?
(FM: 8.60.10.4)

Answer 21

AC bus 2

Question 22

To power the AC essential bus from AC bus 2 due to a loss of AC bus 1, what pilot action is required? (FM: 8.60.10.4)

Answer 22

No action required; system is automatic.

Question 23

What occurs with the AC and DC ESS SHED busses when the airplane is on battery power only? (FM: 8.60.10.3)

Answer 23

Both busses are shed.

Question 24

What is a characteristic of the battery power system? (FM: 8.60.10.2)

Answer 24

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

Question 25

When flying on battery power only, what is the approximate battery endurance? (FM: 8.60.10.2)

Answer 25

22 minutes.

Question 26

How are the batteries charged? (FM: 8.60.10.2)

Answer 26

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

Question 27

According to the graphic, the batteries are (FM: 8.60.20.7)

Answer 27

Being charged.

Question 28

BAT FAULT light indicates (FM: 8.60.20.2)

Answer 28

Charging current is outside normal limits.

Question 29

What will cause the aircraft to revert to the emergency electrical configuration? (FM: 8.60.10.3)

Answer 29

Loss of AC busses 1 and 2 above 100 knots.

Question 30

In the Emergency Electrical Configuration, which Electronic Instrument System (EIS) displays are powered (FM: 2.60.34)

Answer 30

PFD 1, ND 1, and upper ECAM.

Question 31

Pushing the MAN ON switch extends the RAT (FM: 8.60.20.5)

Answer 31

Anytime since it is always powered.

Question 32

On earlier A320s, the emergency generator operates only with (FM: 8.60.20.6)

Answer 32

The landing gear retracted.

Question 33

On later A320s and all A319s, the emergency generator operates (FM: 8.60.20.6)

Answer 33

Until touchdown (greater than 125 knots), regardless of landing gear position.

Question 34

If the gear is retracted in the emergency electrical configuration, the EMERG ELEC PWR MAN ON switch must be pushed to regain the emergency generator on which airplanes? (FM: 8.60.10.3)

Answer 34

Earlier 320s.

Question 35

How is fuel fed to the engines in the emergency electrical configuration? (FM: 2.60.28)

Answer 35

No pumps operate, the engines are gravity fed.

Question 36

What is a characteristic of the ECAM monitored circuit breakers? (FM: 8.60.10.2)

Answer 36

Cause an ECAM "C/B TRIPPED“ caution to appear if tripped or pulled for more than one minute.