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Engine bleed air temperature is controlled by:
A pre-cooler that uses fan air Conditioned air from the mixing unit. Engine oil.
If BMG1 fails BMC2 takes over all monitoring functions except Engine 1 and APU leak detection Overheat detection Automatic crossbleed valve control.
Bleed air normally comes from the _______ of the engine.
Intermediate stage High pressure stage Low pressure stage.
In flight if the air pressure is insufficient even with the HP valve open:
The engine spools up automatically Engine power has to be increased by the pilot. Push the High Pressure P/B on the ovhd panel.
The pressure regulating and shutoff valve will close if _______ pressure is _______ or _______ airflow occurs Upstream / low / reverse Downstream / low / reverse Downstream / High / reverse.
The crossbleed valve has two electric motors; one for the automatic mode and one for the manual mode: True. False.
The overheat detection system uses a single loop for:
The pylons and APU. The wings and pylons The wings and fuselage.
The APU BLEED FAULT light illuminates amber for an APU:
Bleed leak. Malfunction. Overheat.
The AUTO position of the X BLEED selector opens the crossbleed if:
The APU bleed valve is open An engine bleed valve is open. When engine start is selected.
Recirculation fans in the air conditioning system direct filtered cabin air to which area?
The Mixing unit. The pneumatic duct; upstream of the packs The avionics compartment.
Temperature regulation for the A320 is controlled by:
One zone controller and two pack controllers Two pack controllers and the BMC’s The BMC's.
Should both channels fail in a zone controller:
Temperature optimization and the backup mode are lost. Temperature optimization is still available for that zone from another controller The pack is not affected.
The lavatory/galley extract fan operates:
Continuously when electrical power is available. Only on the ground Only in flight.
If bleed air is being supplied by the APU or if one pack fails; pack flow will go to what rate?
High. Medium. Low.
What happens to the outflow valve when the RAM AIR switch is selected ON?
The outflow valve opens if cabin differential pressure is less than 1 psi. Normal outflow valve control is maintained The outflow valve opens immediately.
When either the BLOWER or EXTRACT switches are in OVRD; air from the air conditioning system is added to ventilation air.
How many motors are available for the outflow valve?
1 2 3.
Transfer between the two cabin pressure controllers is:
Automatic after landing or in case the operating controller fails. Automatically at each takeoff. Accomplished with a switch overhead.
The maximum cabin descent rate is limited in automatic to 750 ft/min 1000 ft/min 300 ft/min.
The third motor (manual) in the pressurization system is activated:
When the CABIN PRESS MODE SEL switch is positioned to MAN. Automatically if both automatic motors fail. In sequence after each landing.
When the cabin vertical speed exceeds _______ fpm; the vertical speed display on ECAM _______.
1800 / flashes green 2800 / flashes green 800 / flashes green.
The pneumatic system supplies high pressure air for:
All of the above Hydraulic reservoir pressurization. Wing anti-icing. Air Conditioning, water pressurization and engine starting.
High pressure air has ______ sources.
2 3 4 5.
With both engines operating, an ENG BLEED pb FAULT light will illuminate when: The valve position differs from that of the push button. The X BLEED selector is selected to SHUT. The X BLEED selector is selected to OPEN. The X BLEED selector is selected to OPEN or to SHUT.
Air bleed from the engines is: Cooled in a heat exchanger by cooling air bleed from Fan section. Not cooled prior to being used by the systems Cooled using ambient air. Only cooled in air conditioning part.
If a Bleed Monitoring Computer (BMC) fails:
The remaining BMC will automatically assume most of the failed BMC's functions. All systems associated with the failed BMC also fail. The associated bleed valves close.
A leak detection system detects any overheating in the vicinity of hot air ducts.
When engine and wing anti-ice are in use, and a BMC detects a bleed leak:
The wing anti-ice on the associated side will be lost, and the engine anti-ice on the associated side will continue to function. Only the engine anti-ice on the associated side will be lost The wing and engine anti-ice on the associated side will be lost.
Each bleed valve is electrically operated and controlled pneumatically by its associated BMC.
If a BMC detects a bleed leak:
All valves that could supply pneumatic air to the area of the bleed leak will automatically close. The crew must isolate the affected leak. All pneumatic valves close automatically.
If one BMC fails, the adjacent BMC takes over the monitoring of the bleed system to issue the following ECAM warnings if necessary Overpressure Overtemperature All of the above Wing leak.
Bleed leak protection for the APU pneumatic duct is provided by:
Detection loops associated with BMC #1. Detection loops associated with BMC #2. The APU BMC. All of the above.
With the loss of pneumatic system pressure, the engine bleed valve will:
Assume the closed position. Remain in its current position Assume the open position. Assume the mid position.
Pneumatic system operation is controlled and monitored by:
Two bleed monitoring computers One bleed monitoring computer Two bleed valve computers.
ECAM BLEED page: when is the GND symbol displayed?
Whenever the aircraft is on the ground Only when a ground air supply is connected All the time.
In automatic mode, the rossbleed valve opens when the system is using APU bleed air It closes if the system detects an air leak (except during engine start). It closes if the system detects an air leak (except in flight). It closes automatically if the system detects an air leak.
What happens when pressure and temperature are not sufficient to supply the corresponding engine bleed valve?
HP valve opens, IP stage remains in the same configuration. HP valve closes HP valve opens, if stage closed.
When additional pneumatic air is required for anti-ice, engine starting, or air conditioning:
Additional pneumatic air will be requested by the BMC to the FADECs or the APU. The crew must observe minimum N1 limits Both are correct.
When selected, APU bleed air: Has priority over engine bleed air. Will supply bleed air only if the X BLEED selector is selected OPEN. Does not have priority over engine bleed air. Will supply bleed air only if the ENG BLEED pb's are selected OFF.
With the APU running, the APU BLEED push button selected ON and the X BLEED selector to AUTO, the APU will:
Supply pneumatic air to both sides of the aircraft because the pneumatic crossbleed valve automatically opens. Will supply bleed air only to the left side unless the X BLEED selector is selected OPEN Only supply bleed air to the right side. Only supply bleed air to the left side.
Which source controls the crossbleed valve?
The crew may directly control the following bleed valves:
Engine, APU, crossbleed. Engine, engine high pressure, APU. Engine, intermediate pressure, APU. Crossbleed.
APU bleed air supplies the pneumatic system if the APU speed is above _____: 80 % 85 % 90 % 95 %.
A check valve near the crossbleed duct protects the APU when bleed air comes from another source:
Following an ENGINE 1 BLEED FAULT, why can you only use one pack if Wing Anti Ice (WAI) is on?
Only ENG BLEED system cannot supply 2 packs and WAI. Only one user can be supplied via the X BLEED duct If you use WAI, the X BLEED valve is automatically closed. Therefore, pack 1 will no longer be supplied One engine bleed system can either supply both packs or one pack plus WAI.
Temperature regulation is achieved by the precooler which regulates and limits the temperature at:
200°C 60°C 150°C 85°C.