Airbus A330 - Pneumatic

Which of the following statements is true?

APU bleed is controlled and monitored either by BMC 1 or BMC 2.

Each engine bleed is pneumatically controlled and electrically operated.

Each engine bleed system is controlled and monitored by one Bleed Monitoring Computer (BMC).

Correct! Wrong!

The temperature regulation of bleed air is achieved by a precooler, that is mounted downstream of the bleed valve. The precooler is an air-to-air heat exchanger, which uses cooling air that is bled from the engine fan, to regulate the temperature to 200 deg.C.

True.

False.

Correct! Wrong!

The X-Bleed Valve is AUTO. It will open automatically when the air is coming from:

APU.

ASU.

Engines.

Correct! Wrong!

Air is supplied to the aircraft’s pneumatic system via one HP ground connector only. The crossbleed valve has to be opened manually to provide air for both sides.

True.

False.

Correct! Wrong!

Air is supplied to the aircraft’s pneumatic system via two HP ground connectors. The crossbleed valve has to be opened manually to provide air for both sides.

In flight, with Wing anti-ice On, if there is a wing leak detection:

Only one wing will be de-iced.

The X-Bleed Valve opens automatically to allow normal de-icing.

The Wing anti-ice is automatically stopped.

Correct! Wrong!

The opening of the APU Bleed Valve when X-Bleed is set on AUTO, causes:

All statements are true.

The closing of the ENG Bleed Valves.

The opening of the X-Bleed Valve.

Correct! Wrong!

On ECAM BLEED page the 'GND' message is displayed in white. What does it mean?

External air may be connected, turns amber if pressure is out of limit.

It is on stand by, turns green when external air is connected.

The aircraft is on ground. It is not displayed in flight.

Correct! Wrong!

The Engine Bleed system is controlled and monitored by:

Two EBS computers, one primary and one stand-by.

An Engine Bleed System (EBS) computer.

One dedicated Bleed Monitoring Computer (BMC) for each engine.

Correct! Wrong!

Bleed air supply from the APU:

Is not available in flight.

Is not available for air conditioning.

Is controlled by the APU Bleed Valve and is available on ground and in flight.

Correct! Wrong!

The pneumatic system supplies high pressure air:

Only for air conditioning, engine starting, and wing anti-ice.

For air conditioning, engine starting, wing anti-ice, as well as for hydraulic and water reservoir pressurization.

Only for the hydraulic and water reservoir pressurization.

Correct! Wrong!

It also supplies air to Pack bay ventilation turbofan actuation, Cargo heating and Fuel Tank Inerting System (FTIS).

In case of APU leak signal:

The APU Bleed Valve closes automatically.

The X-Bleed Valve must be closed manually as soon as possible.

The APU Bleed Valve must be closed manually as soon as possible.

Correct! Wrong!

X-BLEED is actuated by 2 electric motors:

One for the automatic mode, the other for the manual mode.

One is supplied by AC generation, the other is supplied by DC generation.

One is MAIN, the other one is STBY.

Correct! Wrong!

When AIR ENG 1 BLEED FAULT appears on ECAM:

FAULT light in ENG BLEED pb remains on as long as the failure is present.

FAULT light goes out if ENG BLEED pb is pushed off with failure still present.

Amber FAULT light and white OFF light appear in ENG BLEED pb.

Correct! Wrong!

When the APU Bleed is ON and the X-Bleed Valve is in AUTO:

Both Engine Bleed Valves are automatically closed.

Only ENG 1 Bleed Valve is automatically closed.

Only ENG 2 Bleed Valve is automatically closed.

Correct! Wrong!

Each BMC (Bleed Monitoring Computer) is provided with bleed pressure, temperature and valve position information, and is interconnected to other systems involved with the bleed system and the other BMC.

False.

True.

Correct! Wrong!

In flight, when APU Bleed Valve is opened, if a wing leak is detected, Engine Bleed Valve and HP Valve on related side close and:

APU Bleed Valve closes automatically if the wing leak concern the left wing.

APU Bleed Valve closes automatically if the wing leak concern the right wing.

Wing anti-ice must not be used.

Correct! Wrong!

On ground when using an Air Supply Unit (ASU) to have pneumatic pressure on both sides:

The X-Bleed selector must be OPEN and both packs will go On.

The X-Bleed selector must be OPEN and both packs will go Off.

The X-Bleed selector must be AUTO and both packs will go On.

Correct! Wrong!

If an engine bleed pylon leak is detected, the bleed valve on the same side closes, the X-Bleed valve receives a closure signal, and:

A FAULT light appears only in the ENG BLEED pb associated with the pylon leak and wing anti-ice must not be selected.

Wing anti-ice may be selected.

OFF light appears in the ENG BLEED pb associated with the closed Engine Bleed Valve.

Correct! Wrong!

The APU Bleed Valve has the priority on the ENG Bleed Valves:

False.

Only for engines start up.

True.

Correct! Wrong!

Airbus A330 – Pneumatic

Quiz

Airbus A330 - Pneumatic

Which of the following statements is true?

The temperature regulation of bleed air is achieved by a precooler, that is mounted downstream of the bleed valve. The precooler is an air-to-air heat exchanger, which uses cooling air that is bled from the engine fan, to regulate the temperature to 200 deg.C.

The X-Bleed Valve is AUTO. It will open automatically when the air is coming from:

Air is supplied to the aircraft’s pneumatic system via one HP ground connector only. The crossbleed valve has to be opened manually to provide air for both sides.

In flight, with Wing anti-ice On, if there is a wing leak detection:

The opening of the APU Bleed Valve when X-Bleed is set on AUTO, causes:

On ECAM BLEED page the 'GND' message is displayed in white. What does it mean?

The Engine Bleed system is controlled and monitored by:

Bleed air supply from the APU:

The pneumatic system supplies high pressure air:

In case of APU leak signal:

X-BLEED is actuated by 2 electric motors:

When AIR ENG 1 BLEED FAULT appears on ECAM:

When the APU Bleed is ON and the X-Bleed Valve is in AUTO:

Each BMC (Bleed Monitoring Computer) is provided with bleed pressure, temperature and valve position information, and is interconnected to other systems involved with the bleed system and the other BMC.

In flight, when APU Bleed Valve is opened, if a wing leak is detected, Engine Bleed Valve and HP Valve on related side close and:

On ground when using an Air Supply Unit (ASU) to have pneumatic pressure on both sides:

If an engine bleed pylon leak is detected, the bleed valve on the same side closes, the X-Bleed valve receives a closure signal, and:

The APU Bleed Valve has the priority on the ENG Bleed Valves: