Airbus A330 - Electrical

Either the APU generator or external power may supply the complete system (with some galley shedding in case of overload).

True.

False.

Correct! Wrong!

Engine GEN 1 supplies power to:

Its assigned AC BUS 1 in normal operation.

Only AC BUS 1 in all cases.

AC BUS 1 and AC BUS 2 in normal operation.

Correct! Wrong!

What is the true statement according to these ECAM ELEC page indications?

EXT POWER is not plugged and APU GEN is connected.

EXT POWER is plugged and available when started.

EXT POWER is plugged, but is not available because parameters are out of limits.

Correct! Wrong!

When ECAM shows " ELEC ECMU 1 FAULT ":

ECMU 1 controls GLC 1 and you should try to reset corresponding generator.

ECMU 1 controls GLC 1 and you should not reset corresponding generator.

ECMU 1 controls GLC 1 (Generator Line Contactor). You should reset GEN 2.

Correct! Wrong!

What does this "ELEC TR 2 FAULT" message indicate?

TR 2 is faulty, DC BUS 2 is powered by TR 1 through DC 1 and DC BUS BAT.

TR 2 is not providing power because the AC BUS which supplies TR 2 is unpowered.

TR 2 is faulty, therefore DC BUS 2 is unpowered.

Correct! Wrong!

As shown on this ECAM ELEC page, the ESS TR is normally supplied by:

AC BUS 2.

AC ESS BUS.

AC BUS 1.

Correct! Wrong!

One of ECMU's function is:

TR contactors monitoring.

Automate management of contactors.

Control of AC and DC bus ties, except TR contactor.

Correct! Wrong!

On the C/B ECAM page, the flight crew reads "NORMAL". What does it mean?

Electric supply to C/B is normal.

No fault detected in Electronics Equipment Bay.

There are no C/B tripped or pulled.

Correct! Wrong!

Loss of one generator or TR provide (except if lost is due to overcurrent detection):

Loss of the corresponding AC or DC bus.

Requirement of APU generator.

No effects on flight management.

Correct! Wrong!

An engine generator is driven:

At a ratio of five to engine speed.

By an Integrated Drive Generator (IDG).

Direct from the Accessory Gear Box (AGB).

Correct! Wrong!

When the MAINT BUS switch is on:

It is for the purpose of operating the cargo door only.

The DC buses are powered only.

The electric network supply is limited to ground service items.

Correct! Wrong!

In case of main generators loss, the emergency generator automatically supplies DC power to the aircraft electrical system.

False.

True.

Correct! Wrong!

The emergency generator automatically supplies AC power to the aircraft electrical system.

What does this "ELEC DC BUS 2 FAULT" message indicate?

TR 2 is faulty.

DC BUS 2 is not powered due to a short circuit.

BAT 2 is faulty.

Correct! Wrong!

According to the information below:

GEN 2 p/b is set ON and engine 2 is not running.

GEN 2 p/b is set OFF and engine 2 is running.

GEN 2 p/b is set OFF and engine 2 is not running.

Correct! Wrong!

The minimum number of generators required to supply all the network is:

One engine generator.

One engine generator and the EMER generator.

One engine generator and APU generator.

Correct! Wrong!

What does this "ELEC GEN 2 FAULT" message indicate?

A TR (Transformer Rectifier) overload.

An engine generator fault.

An ECMU (Electrical Contactor Management Unit) fault.

Correct! Wrong!

When the LAND RECOVERY pb-sw is pressed in EMER ELEC configuration, ADR 3 is lost, and consequently:

AP 1 is lost.

AP 2 is lost.

AP 1 and AP 2 are lost.

Correct! Wrong!

What does this red FAULT light indicate?

The emergency generator is inoperative on ground or in flight.

The emergency generator is not supplying and normal AC supply is lost in flight.

The emergency generator is not available on ground or in flight and AC supply is unavailable.

Correct! Wrong!

According to these indications which AC BUS supplies the ESS TR?

AC 1 BUS.

AC ESS.

AC 2 BUS.

Correct! Wrong!

On ground, the inverter is activated, if only the batteries are supplying electrical power to the aircraft, and both BAT 1 and BAT 2 pushbuttons are on.

True.

False.

Correct! Wrong!

On ground, when only ground services are required, external power can supply the AC and DC GND/FLT buses directly, without supplying the aircraft's entire network. This configuration is selected via the MAINT BUS switch, located in the cockpit.

False.

True.

Correct! Wrong!

This configuration is selected via the MAINT BUS switch, located in the forward entrance area. This switch allows maintenance and ground service personnel to energize electrical circuits for ground servicing, without energizing the aircraft's entire electrical system.

Emergency generator deactivation occurs only automatically in flight at slats extension. If powered by the RAT only (both engines are lost) it can be reactivated _____.

After slats or flaps retraction.

After slats retraction via the MAN ON pushbutton.

After flaps retraction.

Correct! Wrong!

On the ground it can be after both engines shutdown.

If the EMER GEN TEST pb (guarded) is pressed and held:

The emergency generator runs (provided the green hydraulic system is pressurized) and supplies the DC ESS BUS and the AC ESS BUS.

The emergency generator is tested (provided any hydraulic system is available ) and supplies the DC ESS BUS or the AC ESS BUS.

The emergency generator relay is tested and supplies the AC ESS BUS.

Correct! Wrong!

The main function of the MAINT BUS switch is:

To allow EXT PWR to supply AC and DC ESS buses and their respective shed buses.

To power the AC and DC systems when the aircraft is on ground.

To allow selected ground equipment to be powered without powering the entire electric system.

Correct! Wrong!

The APU battery:

Is dedicated to APU start only.

Can be used as a backup for BAT 1 or BAT 2.

May be used for engine start when the APU is not available.

Correct! Wrong!

Two Electrical Contactor Management Units (ECMU) provide:

Control AC and DC contactors (except for TR contactors).

Control of TR contactors.

Control and monitoring AC and DC contactors (except TR which have their own control), galley shedding and no break power transfer.

Correct! Wrong!

According to this ECAM ELEC page

The APU BAT BUS is discharging at a rate of 4 A.

There is no degradation in the capability of DC system.

The Static Inverter is powered because TR 1 is not powered.

Correct! Wrong!

According to this ECAM ELEC page:

APU is running and APU GEN is failed.

APU is not running.

APU is running and APU GEN is set to OFF.

Correct! Wrong!

Two main Transformer Rectifiers TR1 and TR2 and one essential TR supply the aircraft’s electrical system with DC current. A fourth TR is dedicated to APU start or APU battery charging.

True.

False.

Correct! Wrong!

Each TR controls its contactor by internal logic.

The MAINT BUS switch is located:

On the Overhead system panel in the cockpit.

On the Purser's Control Panel in the FWD cabin.

On the FWD Circuit Breaker Panel behind the cockpit.

Correct! Wrong!

What does this ELEC BAT 1 FAULT " message indicate?

Battery line contactor inoperative.

Charging current BAT 1 increasing at abnormal rate.

Abnormal voltage.

Correct! Wrong!

In flight, APU not running, an engine generator has failed. What is supplying the corresponding AC BUS?

Corresponding AC BUS is not powered. APU must be started to recover BUS.

The EMER GEN.

The other engine generator.

Correct! Wrong!

With APU GEN and External Power supplying the network:

APU supplies AC 1 and AC 2 only.

APU supplies AC ESS only.

APU is supplying left side and external power is supplying the right side.

Correct! Wrong!

The Emergency generator is powered by:

The green hydraulic system when pressurized by engine 1 or 2 hydraulic driven pump or by a Ram Air Turbine.

A Ram Air Turbine.

The Static Inverter.

Correct! Wrong!

What is the true statement according to this ECAM ELEC page?

BAT 1 and BAT 2 are connected to all DC network.

BAT 1 and BAT 2 are faulty.

BAT 1 and BAT 2 are supplying the DC ESS BUS and discharge current 40A.

Correct! Wrong!

The EMER GEN is being powered by a hydraulic system pressurized by an engine driven hydraulic pump. Pressing the LAND RECOVERY p/b switch will:

Energize the landing gear.

Operate when the gear is down.

Normally recover the AC and DC LAND RECOVERY BUSES and the components for approach and landing.

Correct! Wrong!

Airbus A330 – Electrical

Quiz

Airbus A330 - Electrical

Either the APU generator or external power may supply the complete system (with some galley shedding in case of overload).

Engine GEN 1 supplies power to:

What is the true statement according to these ECAM ELEC page indications?

When ECAM shows " ELEC ECMU 1 FAULT ":

What does this "ELEC TR 2 FAULT" message indicate?

As shown on this ECAM ELEC page, the ESS TR is normally supplied by:

One of ECMU's function is:

On the C/B ECAM page, the flight crew reads "NORMAL". What does it mean?

Loss of one generator or TR provide (except if lost is due to overcurrent detection):

An engine generator is driven:

When the MAINT BUS switch is on:

In case of main generators loss, the emergency generator automatically supplies DC power to the aircraft electrical system.

What does this "ELEC DC BUS 2 FAULT" message indicate?

According to the information below:

The minimum number of generators required to supply all the network is:

What does this "ELEC GEN 2 FAULT" message indicate?

When the LAND RECOVERY pb-sw is pressed in EMER ELEC configuration, ADR 3 is lost, and consequently:

What does this red FAULT light indicate?

According to these indications which AC BUS supplies the ESS TR?

On ground, the inverter is activated, if only the batteries are supplying electrical power to the aircraft, and both BAT 1 and BAT 2 pushbuttons are on.

On ground, when only ground services are required, external power can supply the AC and DC GND/FLT buses directly, without supplying the aircraft's entire network. This configuration is selected via the MAINT BUS switch, located in the cockpit.

Emergency generator deactivation occurs only automatically in flight at slats extension. If powered by the RAT only (both engines are lost) it can be reactivated _____.

If the EMER GEN TEST pb (guarded) is pressed and held:

The main function of the MAINT BUS switch is:

The APU battery:

Two Electrical Contactor Management Units (ECMU) provide:

According to this ECAM ELEC page

According to this ECAM ELEC page:

Two main Transformer Rectifiers TR1 and TR2 and one essential TR supply the aircraft’s electrical system with DC current. A fourth TR is dedicated to APU start or APU battery charging.

The MAINT BUS switch is located:

What does this ELEC BAT 1 FAULT " message indicate?

In flight, APU not running, an engine generator has failed. What is supplying the corresponding AC BUS?

With APU GEN and External Power supplying the network:

The Emergency generator is powered by:

What is the true statement according to this ECAM ELEC page?

The EMER GEN is being powered by a hydraulic system pressurized by an engine driven hydraulic pump. Pressing the LAND RECOVERY p/b switch will: