Airbus A340 - Electrical Power - SmartCockpit - Airline training guides, Aviation, Operations, Safety

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 of TR contactors.

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

Correct! Wrong!

Each engine generator supplies power to:

Only its assigned BUS in all cases.

Its assigned AC BUS in normal operation.

The BUS on the opposite side in normal operation.

Correct! Wrong!

According to this ECAM ELEC DC page:

The BAT 2 is discharging at a rate of 4 A.

There is no degradation in the capability of DC system.

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

Correct! Wrong!

According to this ECAM ELEC page:

BAT1 and BAT2 are faulty.

BAT1 and BAT2 are supplying the DC network and discharge current is 40 A.

BAT1 and BAT2 are not connected to the DC network.

Correct! Wrong!

An engine generator is driven:

At a ratio of 5 to engine speed.

By an Integrated Drive Generator (IDG).

Direct from the Accessory Gear Box (AGB).

Correct! Wrong!

When ECAM shows "ELEC ECMU 1 FAULT":

ECMU 1 controls GLC 1 and 2 and you should not reset corresponding generators.

ECMU 1 controls Generator Line Contactors (GLC 3 and 4) and you should reset generator 3 and 4.

ECMU 1 controls GLC 1 and 2 and you should try to reset corresponding generators.

Correct! Wrong!

This ECAM ELEC page shows:

GEN 4 pb is set to Off and engine 4 is not running.

GEN 4 pb is set to On and engine 4 is running.

GEN 4 pb is set to Off and engine 4 is running.

Correct! Wrong!

As shown on this ECAM ELEC page, which BUS is normally supplying the ESS TR?

AC 1-1.

AC 2-4.

AC ESS BUS.

Correct! Wrong!

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!

The Emergency generator is powered by:

The GREEN hydraulic system when pressurized by engine 1 or 4 driven hydraulic pump or by a Ram Air Turbine.

A Ram Air Turbine (RAT).

The Static Inverter.

Correct! Wrong!

The MAINT BUS switch is located:

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

On the overhead system panel in the cockpit.

On the FWD Circuit Breaker Panel behind the cockpit.

Correct! Wrong!

What is the meaning of this ECAM?

There is an engine generator fault.

There is an ECMU fault.

There is a TR overload.

Correct! Wrong!

When the MAINT BUS switch is on:

The electric network supply is limited to Ground Service items.

Only the DC buses are powered.

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

Correct! Wrong!

The EMER GEN is 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 extended.

Supply the landing gear.

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

Correct! Wrong!

During EMER GEN automatic start up sequence:

It is not recommended to push the MAN ON p/b to confirm EMER ELEC CONFIG on the EMER ELEC PWR Panel.

Red fault light on EMER ELEC PWR Panel will remain on until the EMER GEN reaches its normal output.

The MAN ON p/b must be pushed to extinguish red fault light on the EMER ELEC PWR Panel.

Correct! Wrong!

According to these indications:

EXT POWER is being plugged and available for use when started.

EXT POWER is plugged, but is not available.

EXT POWER is not plugged and APU GEN is connected.

Correct! Wrong!

What is the meaning of this ECAM?

TR 2 is faulty.

BAT 2 is faulty.

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

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

One engine generator and the EMER GEN.

One engine generator.

Two engine generators.

Correct! Wrong!

The TR 2 pb is set to OFF

The TR 2 is faulty, DC 2 BUS is powered by TR 1 through DC 1 and DC BAT BUS.

The TR 2 is faulty, then the DC 2 BUS is unpowered.

Correct! Wrong!

With APU GEN and external powers supplying the network:

APU supplies AC ESS only.

APU is supplying left side, external power A is supplying the right side.

APU supplies AC 1-1 and AC 1-2 only.

Correct! Wrong!

According to this ECAM ELEC page:

APU is not running.

APU GEN pb is set to Off.

APU GEN is failed.

Correct! Wrong!

One function of the Electrical Contactor Management Units (ECMU) is:

TR contactors monitoring.

Automatic management of contactors.

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

Correct! Wrong!

Loss of one generator or TR (except, if lost is due to over current detection) provides:

No effects on flight management.

APU generator required operational.

Loss of the corresponding AC or DC bus.

Correct! Wrong!

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

AC ESS.

AC 1-2 BUS.

AC 1-1 BUS.

Correct! Wrong!

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

There are no CB tripped or pulled.

No fault detected in Electronics Equipment Bay.

Electric supply to CB is normal.

Correct! Wrong!

What is the meaning of this ECAM?

Abnormal voltage.

Battery line contactor inoperative.

Charging current BAT1 increasing at abnormal rate.

Correct! Wrong!

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

The other side outer engine generator.

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

The other generator on the same side as the failed generator.

Correct! Wrong!

Airbus A340 - Electrical Power

Airbus A340 – Electrical Power

Two Electrical Contactor Management Units (ECMU) provide:

Each engine generator supplies power to:

According to this ECAM ELEC DC page:

According to this ECAM ELEC page:

An engine generator is driven:

When ECAM shows "ELEC ECMU 1 FAULT":

This ECAM ELEC page shows:

As shown on this ECAM ELEC page, which BUS is normally supplying the ESS TR?

The APU battery:

The Emergency generator is powered by:

The MAINT BUS switch is located:

What is the meaning of this ECAM?

When the MAINT BUS switch is on:

The EMER GEN is powered by a hydraulic system pressurized by an engine driven hydraulic pump. Pressing the LAND RECOVERY p/b switch will:

During EMER GEN automatic start up sequence:

According to these indications:

What is the meaning of this ECAM?

The main function of the MAINT BUS switch is:

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

With APU GEN and external powers supplying the network:

According to this ECAM ELEC page:

One function of the Electrical Contactor Management Units (ECMU) is:

Loss of one generator or TR (except, if lost is due to over current detection) provides:

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

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

What is the meaning of this ECAM?

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