Airbus A330 – Electrical - SmartCockpit - Airline training guides, Aviation, Operations, Safety

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!

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!

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!

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!

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

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 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.

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!

Engine GEN 1 supplies power to:

Only AC BUS 1 in all cases.

Its assigned AC BUS 1 in normal operation.

AC BUS 1 and AC BUS 2 in normal operation.

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!

According to this ECAM ELEC page:

APU is running and APU GEN is set to OFF.

APU is running and APU GEN is failed.

APU is not running.

Correct! Wrong!

The MAINT BUS switch is located:

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

On the FWD Circuit Breaker Panel behind the cockpit.

On the Overhead system panel in the cockpit.

Correct! Wrong!

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

AC 1 BUS.

AC ESS.

AC 2 BUS.

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 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.

The Emergency generator is powered by:

A Ram Air Turbine.

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

The Static Inverter.

Correct! Wrong!

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

An ECMU (Electrical Contactor Management Unit) fault.

An engine generator fault.

A TR (Transformer Rectifier) overload.

Correct! Wrong!

One of ECMU's function is:

Automate management of contactors.

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

TR contactors monitoring.

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 1 and AP 2 are lost.

AP 2 is lost.

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 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 not running.

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!

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!

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!

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

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.

False.

True.

Correct! Wrong!

Each TR controls its contactor by internal logic.

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!

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 (Generator Line Contactor). You should reset GEN 2.

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

Correct! Wrong!

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

AC BUS 1.

AC BUS 2.

AC ESS BUS.

Correct! Wrong!

An engine generator is driven:

By an Integrated Drive Generator (IDG).

Direct from the Accessory Gear Box (AGB).

At a ratio of five to engine speed.

Correct! Wrong!

When the MAINT BUS switch is on:

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

The electric network supply is limited to ground service items.

The DC buses are powered only.

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 not plugged and APU GEN is connected.

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

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!

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 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.

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!

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!

Airbus A330 – Electrical