Airbus A330 - Electrical

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!

One of ECMU's function is:

TR contactors monitoring.

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

Automate management of contactors.

Correct! Wrong!

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

EXT POWER is plugged and available when started.

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

EXT POWER is not plugged and APU GEN is connected.

Correct! Wrong!

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

An ECMU (Electrical Contactor Management Unit) fault.

A TR (Transformer Rectifier) overload.

An engine generator fault.

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 supplying the DC ESS BUS and discharge current 40A.

BAT 1 and BAT 2 are faulty.

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!

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

AC ESS.

AC 1 BUS.

AC 2 BUS.

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

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

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!

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!

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.

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!

Engine GEN 1 supplies power to:

AC BUS 1 and AC BUS 2 in normal operation.

Only AC BUS 1 in all cases.

Its assigned AC BUS 1 in normal operation.

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!

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!

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!

The APU battery:

Is dedicated to APU start only.

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

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

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!

When ECAM shows " ELEC ECMU 1 FAULT ":

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.

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

Correct! Wrong!

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

No effects on flight management.

Requirement of APU generator.

Loss of the corresponding AC or DC bus.

Correct! Wrong!

Two Electrical Contactor Management Units (ECMU) provide:

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).

Control of TR contactors.

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!

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

One engine generator and the EMER generator.

One engine generator.

One engine generator and APU generator.

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!

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!

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!

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.

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

Operate when the gear is down.

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.

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 retraction via the MAN ON pushbutton.

After flaps retraction.

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.

True.

False.

Correct! Wrong!

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

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

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.

Correct! Wrong!

What does this red FAULT light indicate?

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.

The emergency generator is inoperative on ground or in flight.

Correct! Wrong!

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

True.

False.

Correct! Wrong!

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

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 2 is lost.

AP 1 is lost.

Correct! Wrong!

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

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

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!

Airbus A330 – Electrical

Quiz

Airbus A330 - Electrical

According to the information below:

One of ECMU's function is:

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

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

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

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

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

The main function of the MAINT BUS switch is:

With APU GEN and External Power supplying the network:

What does this "ELEC DC BUS 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.

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

Engine GEN 1 supplies power to:

According to this ECAM ELEC page

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

The MAINT BUS switch is located:

The APU battery:

The Emergency generator is powered by:

When ECAM shows " ELEC ECMU 1 FAULT ":

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

Two Electrical Contactor Management Units (ECMU) provide:

An engine generator is driven:

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

According to this ECAM ELEC page:

What does this ELEC BAT 1 FAULT " message indicate?

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

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:

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 _____.

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 TR 2 FAULT" message indicate?

What does this red FAULT light indicate?

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

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

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

When the MAINT BUS switch is on: