Airbus A330 - Electrical

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

TR 2 is faulty.

BAT 2 is faulty.

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

Correct! Wrong!

The MAINT BUS switch is located:

On the FWD Circuit Breaker Panel behind the cockpit.

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

On the Overhead system panel in the cockpit.

Correct! Wrong!

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

The other engine generator.

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

The EMER GEN.

Correct! Wrong!

An engine generator is driven:

Direct from the Accessory Gear Box (AGB).

By an Integrated Drive Generator (IDG).

At a ratio of five to engine speed.

Correct! Wrong!

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

One engine generator and the EMER generator.

One engine generator and APU generator.

One engine generator.

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.

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!

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

A TR (Transformer Rectifier) overload.

An ECMU (Electrical Contactor Management Unit) fault.

An engine generator fault.

Correct! Wrong!

When ECAM shows " ELEC ECMU 1 FAULT ":

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

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.

Correct! Wrong!

Engine GEN 1 supplies power to:

AC BUS 1 and AC BUS 2 in normal operation.

Its assigned AC BUS 1 in normal operation.

Only AC BUS 1 in all cases.

Correct! Wrong!

What does this ELEC BAT 1 FAULT " message indicate?

Charging current BAT 1 increasing at abnormal rate.

Abnormal voltage.

Battery line contactor inoperative.

Correct! Wrong!

One of ECMU's function is:

Automate management of contactors.

TR contactors monitoring.

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

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!

With APU GEN and External Power supplying the network:

APU supplies AC ESS only.

APU supplies AC 1 and AC 2 only.

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

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, 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.

According to the information below:

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

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.

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!

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.

Two Electrical Contactor Management Units (ECMU) provide:

Control of TR contactors.

Control AC and DC contactors (except for 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!

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

AC ESS BUS.

AC BUS 2.

AC BUS 1.

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

EXT POWER is plugged and available when started.

Correct! Wrong!

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

AP 2 is lost.

AP 1 and AP 2 are lost.

AP 1 is lost.

Correct! Wrong!

When the MAINT BUS switch is on:

The DC buses are powered only.

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

The electric network supply is limited to ground service items.

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

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

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.

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

Energize the landing gear.

Correct! Wrong!

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!

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!

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!

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!

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

BAT 1 and BAT 2 are faulty.

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

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

Correct! Wrong!

What does this red FAULT light indicate?

The emergency generator is inoperative on ground or in flight.

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

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

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!

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!

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 or flaps retraction.

After slats retraction via the MAN ON pushbutton.

Correct! Wrong!

On the ground it can be after both engines shutdown.

Airbus A330 – Electrical

Quiz

Airbus A330 - Electrical

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

The MAINT BUS switch is located:

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

An engine generator is driven:

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

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

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

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

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

When ECAM shows " ELEC ECMU 1 FAULT ":

Engine GEN 1 supplies power to:

What does this ELEC BAT 1 FAULT " message indicate?

One of ECMU's function is:

The Emergency generator is powered by:

With APU GEN and External Power supplying the network:

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

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.

According to the information below:

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

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.

Two Electrical Contactor Management Units (ECMU) provide:

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

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

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

When the MAINT BUS switch is on:

The main function of the MAINT BUS switch is:

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:

According to this ECAM ELEC page:

The APU battery:

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

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

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

What does this red FAULT light indicate?

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.

According to this ECAM ELEC page

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 _____.