Systems - Electrical Flashcards
In descending order, the priority for electrical power is (FM: 8.60.10.1)
Onside engine generator, external power, APU, remaining engine generator.
According to the graphic, what is powering the airplane? (FM: 8.60.20.6)
Engine driven generators.
What is a characteristic of the APU electrical system? (FM: 8.60.10.1)
Can power the entire airplane on the ground.
What is a characteristic of the electrical system? (FM: 8.60.10.1)
System operation is normally automatic.
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)
AUTO (lights out)
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)
EXT PWR AVAIL light illuminated.
EXT PWR AVAIL light indicates external power is (FM: 8.60.20.3)
Plugged in and electrical parameters are normal.
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)
GEN 1 powers AC bus 1 and the APU generator powers AC bus 2.
Do not hold the IDG disconnect switch for more than ____ to prevent possible damage to the disconnect mechanism (FM: 8.60.20.2)
3 seconds
In the event of a single IDG failure, the remaining IDG powers
(FM: 8.60.20.14)
The entire electrical system, except for the main galley bus.
Do not disconnect the IDG when the (FM: 8.60.20.2)
Engine is not running or not windmilling.
If the IDG 1 switch is pushed in-flight, (FM: 8.60.20.2)
IDG 1 can only be reconnected on the ground by maintenance.
What occurs when an IDG is disconnected? (FM: 8.60.20.2)
The corresponding generator can no longer supply power.
GALY & CAB FAULT light indicates (FM: 8.60.20.1)
A generator load exceeds 100% of rated output.
A GEN FAULT light indicates (FM: 8.60.20.2)
The line contactor is open without selecting the respective GEN switch OFF.
In flight, with only one engine generator operating, how is the electrical system configured? (FM: 8.60.20.14)
The main galley power supply is automatically shed.
In the event of a TR failure, how is the DC system reconfigured?
(FM: 8.60.20.17)
DC busses 1 and 2 will interconnect through the DC BAT bus. ESS TR powers the DC ESS bus.
With a loss of TR 1, what pilot action is required? (FM: 8.60.10.3)
No action required; system automatically powers DC bus 1 with TR 2.
In the normal configuration, which bus feeds the AC ESS bus?
(FM: 8.60.10.1)
AC bus 1.
AC ESS FEED FAULT light (FM: 8.60.20.2)
Illuminates amber when AC ESS bus is not electrically powered.
What bus provides an alternate source of power for the AC ESS bus?
(FM: 8.60.10.4)
AC bus 2
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)
No action required; system is automatic.
What occurs with the AC and DC ESS SHED busses when the airplane is on battery power only? (FM: 8.60.10.3)
Both busses are shed.
What is a characteristic of the battery power system? (FM: 8.60.10.2)
An automatic cutoff logic prevents the batteries from becoming completely discharged on the ground.
When flying on battery power only, what is the approximate battery endurance? (FM: 8.60.10.2)
22 minutes.
How are the batteries charged? (FM: 8.60.10.2)
Automatically when DC power is supplied to the DC BAT bus and the BAT switches are ON.
According to the graphic, the batteries are (FM: 8.60.20.7)
Being charged.
BAT FAULT light indicates (FM: 8.60.20.2)
Charging current is outside normal limits.
What will cause the aircraft to revert to the emergency electrical configuration? (FM: 8.60.10.3)
Loss of AC busses 1 and 2 above 100 knots.
In the Emergency Electrical Configuration, which Electronic Instrument System (EIS) displays are powered (FM: 2.60.34)
PFD 1, ND 1, and upper ECAM.
Pushing the MAN ON switch extends the RAT (FM: 8.60.20.5)
Anytime since it is always powered.
On earlier A320s, the emergency generator operates only with
(FM: 8.60.20.6)
The landing gear retracted.
On later A320s and all A319s, the emergency generator operates
(FM: 8.60.20.6)
Until touchdown (greater than 125 knots), regardless of landing gear position.
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)
Earlier 320s.
How is fuel fed to the engines in the emergency electrical
configuration? (FM: 2.60.28)
No pumps operate, the engines are gravity fed.
What is a characteristic of the ECAM monitored circuit breakers?
(FM: 8.60.10.2)
Cause an ECAM “C/B TRIPPED“ caution to appear if tripped or pulled for more than one minute.
