A330 DSC-36 Pneumatic

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Author:
Julianojae
ID:
286001
Filename:
A330 DSC-36 Pneumatic
Updated:
2014-10-22 10:48:49
Tags:
A330QR A330QRpneumatic
Folders:
A330
Description:
A330 202/302/243F DSC-36 Pneumatic System. When diferences apply they are shown in the Question.
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  1. The pneumatic system supplies high pressure air for:
    (aplicable to all A330-202, A330-302)
    • 1.Air Conditioning.
    • 2.Engine starting
    • 3.Thrust reversers.
    • 4.Wing anti-icing.
    • 5.Water pressurization
    • 6.Hydraulic reservoir pressurization.
    • 7.Pack bay ventilation turbofan actuation.





    NOTE: A330-243F Bleeding System does not provide to Thrust reversers.
  2. The pneumatic system supplies high pressure air for:
    (aplicable to all A330-243F)
    • 1.Air Conditioning. 
    • 2.Engine starting
    • 3.Wing anti-icing.
    • 4.Water pressurization
    • 5.Hydraulic reservoir pressurization.
    • 6.Pack bay ventilation turbofan actuation.




    NOTE: A330-202/302 Bleeding System also provides to Thrust reversers.
  3. High pressure air has ______ sources.
    • 3
    • Engine bleed systems
    • APU load compressor
    • Two HP ground connection.
  4. Pneumatic system operation is controlled and monitored by:
    • 1.Two Bleed Monitoring Computers (BMC 1 and 2, each engine bleed system is controlled and monitored by one dedicated BMC.)
    • 2.Overhead Panel.
    • 3.ECAM
  5. The APU Bleed supply is controlled by the:
    APU Electronic Control Box (ECB).
  6. Each engine bleed system is designed to:
    • 1.Select the air source compressor stage.
    • 2.Regulate bleed air pressure.
    • 3.Regulate bleed air temperature.
  7. In case of failure of one BMC, the other one:
    A) takes over most of the monitoring functions.
    B) takes over all the monitoring functions.
    C) does not take over the monitoring functions.
    A) takes over most of the monitoring functions.
    (this multiple choice question has been scrambled)
  8. Each bleed valve is __1__ controlled by the __2__ and __3__ operated.
    • 1.electrically-controlled 
    • 2.BMC
    • 3.pneumatic operated
  9. Air is normally bled from the Intermediate Pressure Stage (IP) of the Engine HP Compressor to:
    A) minimize fuel penalty.
    B) minimize bleed air pressure.
    C) minimize thrust penalty.
    A) minimize fuel penalty.
    (this multiple choice question has been scrambled)
  10. When pressure from the IP is not sufficient (low engine speed), air is bled from the High Pressure Stage (HP) thru the HP valve which limits downstream pressure to:
    (aplicable to all A330-202, A330-302)
    36 +- 4 PSI.
  11. When pressure from the IP is not sufficient (low engine speed), air is bled from the High Pressure Stage (HP) thru the HP valve which limits downstream pressure to:
    (aplicable to all A330-243F)
    40 +- 4 PSI.
  12. Downstream of the junction of HP and IP ducting, air is admitted into the bleed valve. This bleed valve acts as a shut-off, and as a Pressure Regulating Valve (PRV).
    Delivery pressure is regulated between __ and __ PSI , depending on the flow.
    • 44 and 52 PSI
  13. In case of a pressure regulation failure, the Overpressure Valve (OPV) closes, when the pressure isgreater than ___ PSI.
    85 PSI.

  14. The bleed valve is fully closed Pneumatically in case of :
    • 1.Upstream pressure less than 8 PSI, or
    • 2.Engine fire (thermal fuse)

  15. The bleed valve is fully closed Electrically through the:
    • 1.BLEED pushbutton, when switched OFF
    • 2.ENG FIRE pushbutton when pushed
    • 3.BMC, in the following cases :
    • a) Overtemperature
    • b) Overpressure
    • c) Leak detection
    • d) APU bleed ON (for Engine 2, provided crossbleed valve is not closed).
    • e) Starting sequence

  16. 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 _ °C.
    • 200 °C.
  17. Fan airflow is controlled by the fan Air Valve. When wing anti-ice is selected off, the temperature may be regulated to __°C, upon zone controller demand.
    150 °C.

    NOTE: The fan air valve is spring-loaded closed, in the absence of pressure.
  18. The APU bleed valve is controlled by the APU BLEED pushbutton, located on the AIR panel.
    When, the pushbutton is set to ON, APU bleed air supplies the pneumatic system, provided APU N (speed) is greater than __%.
    95 %.

    NOTE: This causes the crossbleed valve to open and the engine bleed valves to close.

  19. Air is supplied to the aircraft’s pneumatic system via two HP ground connectors. In order to provide air for both sides, the crossbleed valve is opened:
    A) manually
    B) automatically when X-Bleed PB is set to AUTO.
    C) automatically
    A) manually
    (this multiple choice question has been scrambled)
  20. How many ground units can be connected to the crossbleed duct?
    one or two
  21. How many motors control de Crossbleed Valve?
    Two electric motors control the crossbleed valve One is for automatic mode, the other is for manual mode.
  22. In automatic mode, the Crossbleed Valve is normally ____. When APU bleed air is used it ___.
    A) opened/closes
    B) opened/closes if AUTO is selected.
    C) closed/opens
    C) closed/opens

    (this multiple choice question has been scrambled)
  23. (checar)With both engines operating, an ENG BLEED pb FAULT light will illuminate when:
    The valve position differs from that of the push button.
  24. A leak detection system detects any overheating:

    a) in the vicinity of hot air ducts, in the
    fuselage, pylons and wings.
    b) in the hot air ducts, in thefuselage, pylons and wings.
    c) in the system valves, in thefuselage, pylons and wings.
    a) in the vicinity of hot air ducts, in thefuselage, pylons and wings.
  25. The Leak Detection System sensing elements are tied to form a ___ loop, for pylon or, a ____ loop for the wing and APU.

    A) single/double
    B) double/triple
    C) double/single
    A) single/double

    NOTE: A wing or APU leak signal is activated when the two loops detect a leak, or when one loop detects the leak and the other is inoperative.
    (this multiple choice question has been scrambled)
  26. For engine start, air supplied from the ground air source:
    A) Is regulated by the BMC.
    B) Is not regulated.
    C) Is regulated.
    B) Is not regulated.
    (this multiple choice question has been scrambled)
  27. If one BMC is failed the other BMC takes over monitoring of the bleed system and ensures the
    following ECAM warnings:
    • 1.ENG BLEED FAULT (overpressure and overtemperature only)
    • 2.WING LEAK
    • 3.APU BLEED LEAK
    • 4.BLEED LO TEMP (if wing anti ice is on)
  28. If one BMC fails, what happens with the:
    1. Associated FAULT light on the Air Panel?
    2. Bleed Valve?
    3. ENG BLEED LEAK warning?
    • 1. The associated FAULT light on the AIR panel is lost.
    • 2. The bleed valve does not close automatically.
    • 3. ENG BLEED LEAK warning is lost for the associated engine.
  29. When ENG 1 (2) BLEED pb switch is On,
    The bleed valve opens, provided:
    • 1. Upstream pressure is above 8 PSI.
    • 2. The APU BLEED pb-sw is OFF, or the APU bleed valve is closed.
    • 3. There is no onside wing or pylon leak, overpressure, or over temperature detected.
    • 4. The ENG FIRE pushbutton is not released out
    • 5. The ENG start valve is closed.
  30. The ENG 1 (2) BLEED FAULT LIGHT illuminates amber, associated with ECAM caution in case of:
    • 1. Bleed valve is not closed during engine start
    • 2. Bleed valve is not closed with APU bleed ON (and for RH engine X-bleed 
    • 3. Overpressure downstream of the bleed valve.
    • 4. Bleed overheat
    • 5. Wing or engine leak on the related side.

    NOTE: It goes off, when the ENG BLEED pushbutton is OFF, provided the failure has disappeared.
  31. With APU BLEED pb switch set to ON , APU valve opens provided:
    • 1. N > 95 %
    • 2. Altitude < 25 000 ft climbing
    •             or < 23 000 ft descending
    • 3. No leak detected on APU or LH bleed (Should a leak occur on the RH side, the X-bleed would close).
  32. The APU BLEED FAULT LIGHT illuminates amber, associated with ECAM caution when:
    APU Leak is detected.
  33. When the X-BLEED selector is set to AUTO:
    • 1. The Crossbleed Valve is open if APU Bleed valve is open.
    • 2. The Crossbleed Valve is closed if APU Bleed valve is closed.
  34. 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.
  35. If a BMC detects a bleed leak:
    All valves that could supply pneumatic air to the area of the bleed leak will automatically close.
  36. With the loss of pneumatic system pressure, the engine bleed valve will:
    Assume the closed position.
  37. ECAM BLEED page: when is the GND symbol displayed?
    Whenever the aircraft is on the ground.

    GND symbol shown in number 6.

    (checar essa questão! é mostrado quando a aeronave está no solo ou quando a fonte está conectada?)

  38. The precooler inlet pressure indication, on the ECAM Bleed page, becomes amber if lower than _____PSI or in case of overpressure above _____PSI detected by the BMC.
    • 4 PSI
    • 60 PSI
  39. When selected, APU bleed air:
    A) Supplies bled Air to the system together with air bled from the engines.
    B) Has priority over engine bleed air.
    C) Does not have priority over engine bleed air.
    B) Has priority over engine bleed air.
    (this multiple choice question has been scrambled)
  40. The Precooler outlet temperature visible on the ECAM is normally in green. It becomes amber, if the BMC detects an overheat or low temperature.
    TRUE

    • Over temperature if more than:
    • a) 290 °C for more than 5 seconds
    • b) 270 °C for more than 15 seconds.
    • c) 257 °C for more than 55 seconds.

    Low temperature is lower than 150 °C and if Wing Anti Ice is ON. (due to OAT)
  41. A check valve near the crossbleed duct protects the APU when bleed air comes from another source:
    true or false?
    True.
  42. 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.
    • One engine bleed system can either supply both packs or one pack plus WAI.
  43. The Arrows of the INNER/OUTER ANTI ICE VALVE are normally displayed in GREEN if the Valve is normally open or in AMBER if the the valve is open and at least one of the conditions are met:

    1. Bleed Air pressure High or Low.
    2. WAI PB set to OFF position.
    3. Open for more than ___ , while the Aircraft is on the Ground.
    35s

    Arrows shown as number 8.



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