A 320 Electrical System

Less than 60 amps in 10 seconds.

Greater than 34 volts.

Greater than 25 volts.

Battery charging current increases at an abnormal rate .

Battery voltage drops below a predeterminate level.

The batteries have auto disconnected due to low voltage.

APU , External power , Gen 1 or Gen 2 .

APU ,Gen 2 or 1, External power

Gen 1 or Gen 2, External power (if selected ) , APU .

External power is supplying all electrical needs.

Eng Gen 1 is supplying Ac bus 1 and the downstream system and AC bus 2 through the bus tie contractors.

Gen 1 supplies AC bus 1 and (generally )the downstream system , Ext Pwr supplies AC bus 2.

It will automatically close the Bus Tie contractors when connected by the ground crew.

The green AVAIL light will illuminate on the EXT PWR button.

The BUS TIE push button illuminates .

The power transfer would switch to the opposite bus.

All power would be lost and the aircraft would be powered by the batteries until the RAT was up to speed.

None

Yes.

Only with the RAT deployed.

The electrical system will not allow paralleling of generators.

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

Only the AC ESS shed bus .

None of the above .

The flight attendants have all the coffee makers and ovens on at once .

The Main Galley has shed.

The load on any generator is above 100% of it´s rated output.

NO

Only when operating in the Emergency Electrical Configuration.

Yes , press the ECAM ELEC , push button and view the electrical schematic on the ECAM .

Yes , transfer is automatic .

Yes, only if AUTO was selected on the AC ESS FEED push button.

No this must be done by the crew .

Never disconnect an IDG in flight or push the IDG disconnect push button for more then 30 seconds.

Never disconnect an IDG in flight or push the IDG disconnect push button for more then 5 seconds.

Never disconnect an IDG unless the engine is running , nor push the IDG isconnect push button for more then 3 seconds.

Yes , but only after contacting maintenance control .

Yes , push and hold the IDG pb until the GEN fault light is no longer illuminated .

NO

All systems return to normal and the RAT must be restored .

The APU would now power both sides of the electrical system.

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

Push this button to automatically start the APU

When selected to OFF the APU generator field is de_energized.

Both A and B are correct.

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

With the loss of two Hydraulic systems.

A or B

When the EMER GEN is not supplying electrical power ,AC busses 1 and 2 are unpowered and the nose gear is up

When the RAT is displayed using hydraulic RAT MAN ON push button .

Both A and B are correct

Between 22 and 30 minutes depending on equipment in use .

Until the APU IS STARTED

TWO HOURS AND 30 MINUTES DEPENDENT ON THE EQUIPMENT IN USE

BATT HOT busses Will be power ESS DC , ESS DC SHED ,ESS AC ,and ESS AC SHED 

The BATTERIES busses would power Booth HOT BATT busses , ESS DC and ESS AC through the STATIC INVERTER 

The STATIC INVERTER would power Both HOT BATT busses ESS DC and ESS AC through the ESS AC SHED busses.

VHF 1 ,RMP 1 VOR 1

ACP 1 ,& ACP 2  ,VHF 1 ,HF1 , RMP 1 ,VOR 1 and ILS 1.

 RMP 1&2 ,VHF 1 , HF , ACP 1 ,VOR ,ILS 1

Check to see that FMGC has auto tuned the appropiate NAV facility for the approach to be accomplish.

Depress the guarded RMP NAV puso button and tune the aprópiate NAV facility and Course for the aproach to be acomplish.

A & B 

SEC 1

FÁC 1 

ELAC 1

DME , and Transponder 1.

DME 1, DDRMI and Transponder.

DME 1 and Transponder 1.

Depress and hold the specific ECAM page push button on the ECAM control panel.

Transfer occurs automatically.

This is not posible .Use the cockpit operating manual.

ELAC 1 , SEC 1 and FAC 1

ELAC 1 and 2 SEC 1 and 2 , FAC 1

ELAC 1 , and  SEC 1.