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A320 Systems > PNEUMATICS > Flashcards

PNEUMATICS Flashcards

1
Q

Q 01: Engine bleed air temperature is controlled by:
A: Engine oil.
B: A pre-cooler that uses fan air.
C: Conditioned air from the mixing unit.

A

B: A pre-cooler that uses fan air.

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2
Q

Q 02: If BMC1 fails BMC2 takes over all monitoring functions except:
A: Engine 1 and APU leak detection.
B: Overheat detection.
C: Automatic cross-bleed valve control.

A

A: Engine 1 and APU leak detection.

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3
Q

Q 03: Bleed air normally comes from the _______ of the engine.
A: High pressure stage.
B: Intermediate stage.
C: Low pressure stage.

A

B: Intermediate stage.

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4
Q

Q 04: In flight if the air pressure is insufficient even with the HP valve open:
A: The engine spools up automatically.
B: Engine power has to be increased by the pilot.
C: Push the High Pressure P/B on the ovhd panel.

A

A: The engine spools up automatically.

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5
Q

Q 05: The pressure regulating and shutoff valve will close if _______ pressure is _______ or _______ airflow occurs
A: Downstream / low / reverse
B: Downstream / High / reverse
C: Upstream / low / reverse

A

C: Upstream / low / reverse

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6
Q

Q 06: The crossbleed valve has two electric motors; one for the automatic mode and one for the manual mode:
A: True
B: False

A

A: True

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7
Q

Q 07: The overheat detection system uses a single loop for:
A: The pylons and APU.
B: The wings and pylons.
C: The wings and fuselage.

A

A: The pylons and APU.

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8
Q

Q 08: The APU BLEED FAULT light illuminates amber for an APU:
A: Overheat.
B: Malfunction.
C: Bleed leak.

A

C: Bleed leak.

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9
Q

Q 09: The AUTO position of the X BLEED selector opens the crossbleed if:
A: An engine bleed valve is open.
B: The APU bleed valve is open.
C: When engine start is selected.

A

B: The APU bleed valve is open.

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10
Q

Q 10: Recirculation fans in the air conditioning system direct filtered cabin air to which area?
A: The pneumatic duct; upstream of the packs.
B: The avionics compartment.
C: The Mixing unit.

A

C: The Mixing unit.

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11
Q

Q 11: Temperature regulation for the A320 is controlled by:
A: One zone controller and two pack controllers.
B: Two pack controllers and the BMC’s.
C: The BMC’s

A

A: One zone controller and two pack controllers.

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12
Q

Q 12: Should both channels fail in a zone controller:
A: Temperature optimization is still available for that zone from another controller.
B: Temperature optimization and the backup mode are lost.
C: The pack is not affected.

A

B: Temperature optimization and the backup mode are lost.

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13
Q

Q 13: The lavatory/galley extract fan operates:
A: Only on the ground.
B: Only in flight.
C: Continuously when electrical power is available.

A

C: Continuously when electrical power is available.

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14
Q

Q 14: If bleed air is being supplied by the APU or if one pack fails; pack flow will go to what rate?
A: Low.
B: Medium.
C: High.

A

C: High.

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15
Q

Q 15: What happens to the outflow valve when the RAM AIR switch is selected ON?
A: The outflow valve opens immediately.
B: The outflow valve opens if cabin differential pressure is less than 1 psi.
C: Normal outflow valve control is maintained.

A

B: The outflow valve opens if cabin differential pressure is less than 1 psi.

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16
Q

Q 16: When either the BLOWER or EXTRACT switches are in OVRD; air from the air conditioning system is added to ventilation air.
A: True.
B: False

A

A: True.

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17
Q

Q 17: How many motors are available for the outflow valve?
A: 1
B: 2
C: 3

A

C: 3

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18
Q

Q 18: Transfer between the two cabin pressure controllers is:
A: Accomplished with a switch overhead.
B: Automatic after landing or in case the operating controller fails.
C: Automatically at each takeoff.

A

B: Automatic after landing or in case the operating controller fails.

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19
Q

Q 19: The maximum cabin descent rate is limited in automatic to:
A: 300 ft/min.
B: 750 ft/min.
C: 1000 ft/min.

A

B: 750 ft/min.

20
Q

Q 20: The third motor (manual) in the pressurization system is activated:
A: Automatically if both automatic motors fail.
B: In sequence after each landing.
C: When the CABIN PRESS MODE SEL switch is positioned to MAN.

A

C: When the CABIN PRESS MODE SEL switch is positioned to MAN.

21
Q

Q 21: When the cabin vertical speed exceeds _______ fpm; the vertical speed display on ECAM _______.
A: 800 / flashes green
B: 2800 / flashes green
C: 1800 / flashes green

A

C: 1800 / flashes green

22
Q

Q 22: The pneumatic system supplies high pressure air for:
A: Air Conditioning, water pressurization and engine starting
B: Wing anti-icing.
C: Hydraulic reservoir pressurization.
D: All of the above.

A

D: All of the above.

23
Q 
Q 23: High pressure air has \_\_\_\_\_\_ sources. 
A: 2 
B: 3 
C: 4 
D: 5
A

B: 3

* Engine bleed systems, APU load compressor and HP ground connection.

24
Q

Q 24: With both engines operating, an ENG BLEED pb FAULT light will illuminate when:
A: The valve position differs from that of the push button.
B: The X BLEED selector is selected to SHUT.
C: The X BLEED selector is selected to OPEN.
D: The X BLEED selector is selected to OPEN or to SHUT.

A

A: The valve position differs from that of the push button.

25
Q

Q 25: Air bleed from the engines is:
A: Not cooled prior to being used by the systems.
B: Cooled in a heat exchanger by cooling air bleed from Fan section.
C: Cooled using ambient air.
D: Only cooled in air conditioning part.

A

B: Cooled in a heat exchanger by cooling air bleed from Fan section.

26
Q

Q 26: If a Bleed Monitoring Computer (BMC) fails:
A: All systems associated with the failed BMC also fail.
B: The associated bleed valves close.
C: The remaining BMC will automatically assume most of the failed BMC’s functions.

A

C: The remaining BMC will automatically assume most of the failed BMC’s functions.

27
Q

Q 27: A leak detection system detects any overheating in the vicinity of hot air ducts.
A: True.
B: False.

A

A: True.

28
Q

Q 28: When engine and wing anti-ice are in use, and a BMC detects a bleed leak:
A: Only the engine anti-ice on the associated side will be lost.
B: The wing and engine anti-ice on the associated side will be lost.
C: The wing anti-ice on the associated side will be lost, and the engine anti-ice on the associated side will continue to function.

A

C: The wing anti-ice on the associated side will be lost, and the engine anti-ice on the associated side will continue to function.

29
Q

Q 29: Each bleed valve is electrically operated and controlled pneumatically by its associated BMC.
A: True.
B: False.

A

B: False.

30
Q

Q 30: If a BMC detects a bleed leak:
A: The crew must isolate the affected leak.
B: All valves that could supply pneumatic air to the area of the bleed leak will automatically close.
C: All pneumatic valves close automatically.

A

B: All valves that could supply pneumatic air to the area of the bleed leak will automatically close.

31
Q 
Q 31: If one BMC fails, the adjacent BMC takes over the monitoring of the bleed system to issue the following ECAM warnings if necessary: 
A: Overpressure 
B: Overtemperature 
C: Wing leak 
D: All of the above.
A

D: All of the above.

32
Q

Q 32: Bleed leak protection for the APU pneumatic duct is provided by:
A: Detection loops associated with BMC #1.
B: Detection loops associated with BMC #2.
C: The APU BMC.
D: All of the above.

A

A: Detection loops associated with BMC #1.

33
Q 
Q 33: With the loss of pneumatic system pressure, the engine bleed valve will: 
A: Remain in its current position. 
B: Assume the mid position. 
C: Assume the open position. 
D: Assume the closed position.
A

D: Assume the closed position.

34
Q

Q 34: Pneumatic system operation is controlled and monitored by:
A: One bleed monitoring computer.
B: Two bleed valve computers.
C: Two bleed monitoring computers.

A

C: Two bleed monitoring computers.

35
Q

Q 35: ECAM BLEED page: when is the GND symbol displayed?
A: Whenever the aircraft is on the ground.
B: All the time.
C: Only when a ground air supply is connected.

A

A: Whenever the aircraft is on the ground.

36
Q

Q 36: In automatic mode, the crossbleed valve opens when the system is using APU bleed air.
A: It closes if the system detects an air leak (except during engine start).
B: It closes if the system detects an air leak (except in flight).
C: It closes automatically if the system detects an air leak.

A

A: It closes if the system detects an air leak (except during engine start).

37
Q

Q 37: What happens when pressure and temperature are not sufficient to supply the corresponding engine bleed valve?
A: HP valve closes.
B: HP valve opens, if stage closed.
C: HP valve opens, IP stage remains in the same configuration.

A

C: HP valve opens, IP stage remains in the same configuration.

38
Q

Q 38: When additional pneumatic air is required for anti-ice, engine starting, or air conditioning:
A: Additional pneumatic air will be requested by the BMC to the FADECs or the APU.
B: The crew must observe minimum N1 limits.
C: Both are correct.

A

A: Additional pneumatic air will be requested by the BMC to the FADECs or the APU.

39
Q

Q 39: When selected, APU bleed air:
A: Will supply bleed air only if the ENG BLEED pb’s are selected OFF.
B: Has priority over engine bleed air.
C: Will supply bleed air only if the X BLEED selector is selected OPEN.
D: Does not have priority over engine bleed air.

A

B: Has priority over engine bleed air.

40
Q

Q 40: With the APU running, the APU BLEED push button selected ON and the X BLEED selector to AUTO, the APU will:
A: Only supply bleed air to the left side.
B: Supply pneumatic air to both sides of the aircraft because the pneumatic crossbleed valve automatically opens.
C: Will supply bleed air only to the left side unless the X BLEED selector is selected OPEN.
D: Only supply bleed air to the right side.

A

B: Supply pneumatic air to both sides of the aircraft because the pneumatic crossbleed valve automatically opens.

41
Q

Q 41: Which source controls the crossbleed valve?
A: Pneumatic.
B: Electric.

A

B: Electric.

42
Q 
Q 42: The crew may directly control the following bleed valves: 
A: Engine, engine high pressure, APU. 
B: Engine, intermediate pressure, APU. 
C: Engine, APU, crossbleed. 
D: Crossbleed.
A

C: Engine, APU, crossbleed.

43
Q 
Q 43: APU bleed air supplies the pneumatic system if the APU speed is above \_\_\_\_\_: 
A: 80% 
B: 85% 
C: 92% 
D: 95%
A

D: 95%

44
Q

Q 44: A check valve near the crossbleed duct protects the APU when bleed air comes from another source:
A: True.
B: False.

A

A: True.

45
Q 
Q 45: Temperature regulation is achieved by the precooler which regulates and limits the temperature at: 
A: 150°C 
B: 85°C 
C: 60°C 
D: 200°C
A

D: 200°C

A320 Systems (7 decks)

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