Airbus A330 - Electrical

According to this ECAM ELEC page:

APU is not running.

APU is running and APU GEN is failed.

APU is running and APU GEN is set to OFF.

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!

What does this red FAULT light indicate?

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.

The emergency generator is inoperative on ground or in flight.

Correct! Wrong!

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

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

BAT 1 and BAT 2 are faulty.

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

Correct! Wrong!

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

AC ESS.

AC 2 BUS.

AC 1 BUS.

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.

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!

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

True.

False.

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!

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!

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.

True.

False.

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.

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!

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

There are no C/B tripped or pulled.

No fault detected in Electronics Equipment Bay.

Electric supply to C/B is normal.

Correct! Wrong!

Engine GEN 1 supplies power to:

Only AC BUS 1 in all cases.

AC BUS 1 and AC BUS 2 in normal operation.

Its assigned AC BUS 1 in normal operation.

Correct! Wrong!

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 GEN 2 FAULT" message indicate?

A TR (Transformer Rectifier) overload.

An engine generator fault.

An ECMU (Electrical Contactor Management Unit) fault.

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.

False.

True.

Correct! Wrong!

Each TR controls its contactor by internal logic.

The APU battery:

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

Is dedicated to APU start only.

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

Correct! Wrong!

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

Requirement of APU generator.

No effects on flight management.

Loss of the corresponding AC or DC bus.

Correct! Wrong!

When ECAM shows " ELEC ECMU 1 FAULT ":

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

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

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

Correct! Wrong!

An engine generator is driven:

Direct from the Accessory Gear Box (AGB).

At a ratio of five to engine speed.

By an Integrated Drive Generator (IDG).

Correct! Wrong!

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

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

EXT POWER is plugged and available when started.

EXT POWER is not plugged and APU GEN is connected.

Correct! Wrong!

Two Electrical Contactor Management Units (ECMU) provide:

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.

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

Correct! Wrong!

With APU GEN and External Power supplying the network:

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

APU supplies AC 1 and AC 2 only.

APU supplies AC ESS only.

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:

Operate when the gear is down.

Energize the landing gear.

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

Correct! Wrong!

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

AP 1 and AP 2 are lost.

AP 1 is lost.

AP 2 is lost.

Correct! Wrong!

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!

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 other engine generator.

The EMER GEN.

Correct! Wrong!

One of ECMU's function is:

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

TR contactors monitoring.

Automate management of contactors.

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 faulty, therefore DC BUS 2 is unpowered.

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

Correct! Wrong!

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 flaps retraction.

After slats retraction via the MAN ON pushbutton.

After slats or flaps retraction.

Correct! Wrong!

On the ground it can be after both engines shutdown.

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.

False.

True.

Correct! Wrong!

What does this ELEC BAT 1 FAULT " message indicate?

Charging current BAT 1 increasing at abnormal rate.

Battery line contactor inoperative.

Abnormal voltage.

Correct! Wrong!

The Emergency generator is powered by:

The Static Inverter.

A Ram Air Turbine.

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

Correct! Wrong!

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

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

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

Correct! Wrong!

According to the information below:

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

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

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

Correct! Wrong!

Airbus A330 – Electrical

Quiz

Airbus A330 - Electrical

According to this ECAM ELEC page:

According to this ECAM ELEC page

What does this red FAULT light indicate?

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

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

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

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

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

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

When the MAINT BUS switch is 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.

The main function of the MAINT BUS switch is:

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

Engine GEN 1 supplies power to:

The MAINT BUS switch is located:

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

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 APU battery:

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

When ECAM shows " ELEC ECMU 1 FAULT ":

An engine generator is driven:

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

Two Electrical Contactor Management Units (ECMU) provide:

With APU GEN and External Power supplying the network:

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:

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

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

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

One of ECMU's function is:

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

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 _____.

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.

What does this ELEC BAT 1 FAULT " message indicate?

The Emergency generator is powered by:

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

According to the information below: