Airbus A330 - Electrical

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 relay is tested and supplies 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.

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 not plugged and APU GEN is connected.

EXT POWER is plugged and available when started.

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!

According to the information below:

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.

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

Correct! Wrong!

The main function of the MAINT BUS switch is:

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

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.

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!

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.

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!

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 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 does this red FAULT light indicate?

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

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.

Correct! Wrong!

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

AC ESS.

AC 2 BUS.

AC 1 BUS.

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!

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 not reset corresponding generator.

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

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!

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!

According to this ECAM ELEC page

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

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

There is no degradation in the capability of DC system.

Correct! Wrong!

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

An engine generator fault.

An ECMU (Electrical Contactor Management Unit) fault.

A TR (Transformer Rectifier) overload.

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!

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

BAT 2 is faulty.

TR 2 is faulty.

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

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 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!

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!

According to this ECAM ELEC page:

APU is running and APU GEN is set to OFF.

APU is not running.

APU is running and APU GEN is failed.

Correct! Wrong!

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

One engine generator.

One engine generator and APU generator.

One engine generator and the EMER generator.

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.

False.

True.

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.

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

False.

True.

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 slats or flaps retraction.

After flaps retraction.

After slats retraction via the MAN ON pushbutton.

Correct! Wrong!

On the ground it can be after both engines shutdown.

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

Loss of the corresponding AC or DC bus.

No effects on flight management.

Requirement of APU generator.

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!

When the MAINT BUS switch is on:

The electric network supply is limited to ground service items.

The DC buses are powered only.

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

Correct! Wrong!

What does this ELEC BAT 1 FAULT " message indicate?

Abnormal voltage.

Battery line contactor inoperative.

Charging current BAT 1 increasing at abnormal rate.

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 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!

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!

Airbus A330 – Electrical

Quiz

Airbus A330 - Electrical

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

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

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

According to the information below:

The main function of the MAINT BUS switch is:

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

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.

One of ECMU's function is:

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

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

What does this red FAULT light indicate?

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

Engine GEN 1 supplies power to:

When ECAM shows " ELEC ECMU 1 FAULT ":

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:

The Emergency generator is powered by:

According to this ECAM ELEC page

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

An engine generator is driven:

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

With APU GEN and External Power supplying the network:

The MAINT BUS switch is located:

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

According to this ECAM ELEC page:

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

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.

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.

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

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 _____.

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

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

When the MAINT BUS switch is on:

What does this ELEC BAT 1 FAULT " message indicate?

The APU battery:

Two Electrical Contactor Management Units (ECMU) provide:

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