Electrical Panel

Question 1

When performing the PRELIMINARY FLIGHT DECK PREPARATION, what is the minimum battery voltage?

Answer 1

25.5

Question 2

What do you do if it is below 25.5V?

Answer 2

Select BATT push buttons to ON with EXT PWR on aircraft. This starts the charging cycle (roughly 20 min required)

Question 3

When performing the FLIGHT DECK PREPARATION, what are we looking for on the ELEC panel BAT check?

Answer 3

EMAM ELEC page - select
BAT 1& 2 - OFF then ON
Check BATT current is <60 amps after 10 seconds and continues to decrease

Question 4

Will the batteries completely drain if you leave the BAT switches in AUTO after AC power is removed on the ground?

Answer 4

No. Battery cut - off logic prevents complete discharge when the aircraft is on the ground and unpowered - 22VDC

Question 5

How is the BATTERY BUS normally powered?

Answer 5

DC BUS 1 through a DC tie contactor

Question 6

What does the amber FAULT light in the GALLEY pushbutton indicate?

Answer 6

At least 1 generator load is above 100% rated output

Question 7

How does the GALLEY pushbutton work in AUTO?

Answer 7

Sheds main galley, IFE and in seat power supply if:
Only 1 generator (APU or Engine) is available in FLIGHT, or
Only 1 ENGINE generator is available on the GROUND

Question 8

What does a FAULT on the ENG GEN pushbutton indicate?

Answer 8

The generator line contactor is open because of a fault detected by the Generator Control Unit (GCU) which could include:
Overload
Over/Under voltage
Differential fault (short), and/or
The generator line contactor is open

Question 9

What does the APU GEN FAULT light indicate?

Answer 9

The generator line contactor is open because of a fault detected by the GCU

Question 10

When is the APU GEN FAULT light inhibited?

Answer 10

APU speed to low
Line contactor OPEN after EXT PWR or ENG GEN takes over

Question 11

What is the function of the BUS TIE in the AUTO position?

Answer 11

Allows the BUS TIE CONTACTORS to open and close automatically to maintain power to both AC BUS 1 &n 2:
Allows a single source to power the entire system
Allows connection of the APU GEN or EXT PWR to the system
Inhibits multiple sources to connect simultaneously

Question 12

What does an IDG FAULT light indicate?

Answer 12

Oil pressure low (inhibited when N2 <14%)
Oil outlet temperature overheat
Light is inhibited when IDG is disconnected

Question 13

What precautions must you take when disconnecting an IDG?

Answer 13

Do not disconnect when the engine is not operating or windmilling
Do not hold the disconnect button longer than 3 seconds

Question 14

How can an IDG be reset?

Answer 14

On the ground by maintenance

Question 15

What is the function of the AC ESS FEED pushbutton in the normal position?

Answer 15

Allows AC BUS 1 to power the AC ESS BUS

Question 16

How is AC ESS FEED transferred from AC BUS 1 to AC BUS 2?

Answer 16

Manually by selecting ALTN on the AC ESS FEED pushbutton or automatically if AC BUS 1 is lost and the switch is in the normal position

Question 17

What does the AC ESS FEED pushbutton white ALTN light indicate?

Answer 17

AC BUS 2 is powering the AC ESS BUS

Question 18

What is the purpose of the static inverter?

Answer 18

To provide AC power to the AC ESS bus from the battery when the EMG GEN is not online when in the Emergency Electrical Configuration

Question 19

What are the 3 times the batteries are connected to the BATTERY BUS?

Answer 19

APU start
Battery charging
AC BUS 1 & 2 not powered and airspeed below 100 knots

Question 20

What is the priority sequence for electrical power?

Answer 20

(GEARB)
Generators - Engine
EXT PWR (manually selected)
APU Generator
RAT Emergency Generator
Batteries

Question 21

With the APU green AVAIL light ON and the EXT PWR blue ON light illuminated, which system is powering the aircraft?

Answer 21

EXT PWR

Question 22

What is the significance of the green and red collared circuit breakers on the flight deck?

Answer 22

Green - Monitored by ECAM
Red - Wing tip brake C/B
Black - Not monitored by ECAM