Air Conditioning / Pressurization/ Pneumatics Flashcards
Recall the function of each position of the X BLEED selector.
SHUT:
▪ Commands crossbleed valve closed, overriding auto logic.
Recall the function of each position of the X BLEED selector.
AUTO:
Auto logic controls opening and closing of the crossbleed valve
• crossbleed valve commanded open when the APU bleed valve is open
• crossbleed valve commanded closed when APU bleed valve is closed
• crossbleed valve commanded closed when a bleed leak is detected
Recall the function of each position of the X BLEED selector.
OPEN:
Commands the crossbleed valve open, overriding the auto logic.
Recall the indications when APU bleed air is in use.
❇️APU bleed valve indicates open on the ECAM BLEED page.
❇️APU BLEED is displayed in green on the memo section of the E/WD.
Recall the areas of the aircraft where a bleed air leak can be detected.
Wings:
each wing’s bleed air duct
Recall the areas of the aircraft where a bleed air leak can be detected.
Engine pylons:
area from the engine to the respective wing bleed duct
Recall the areas of the aircraft where a bleed air leak can be detected.
Aft fuselage:
area surrounding the APU bleed air duct
Recall which cargo compartment is heated and ventilated.
▪ Only the aft cargo compartment is temperature controlled, using the controls located on the overhead CARGO HEAT panel.
▪ Temperature of the aft cargo compartment can be monitored by referencing the ECAM COND or CRUISE pages.
Recall how many Cabin Pressure Controllers are installed and where the active system is displayed on ECAM.
▪ There are two Cabin Pressure Controllers (CPC) installed.
▪ Designated as SYS 1 and SYS 2, the current active system can be viewed on the ECAM CAB PRESS page.
Describe how the active and standby pressurization controllers (CPCs) switch roles.
Automatically:
▪ Shortly after each landing.
▪ In the event the active controller fails.
Describe how the active and standby pressurization controllers (CPCs) switch roles.
Manually:
▪ Placing the MODE SEL pb to MAN for 10 seconds, and then returning it back to the AUTO (lights out) mode.
Describe the function of the LDG ELEV selector.
In AUTO (detent) position:
FMGCs provide the pressurization system with the landing field elevation.
Describe the function of the LDG ELEV selector
Outside of AUTO (turning clockwise):
Landing field elevation is set manually.
▪ Used when both FMCGs have failed or when landing airport is not in the FMS data base.
NOTE: Selector is calibrated in thousands, not hundreds of feet.
Describe the function of the manual pressurization controls.
❇️MODE SEL pb:
▪ selecting MAN (light on) enables the use of the MAN V/S CTL toggle switch to manually control the outflow valve.
▪ Deactivates the AUTO pressurization mode.
Describe the function of the manual pressurization controls.
MAN V/S CTL toggle switch:
❇️UP commands the outflow valve open, reducing cabin pressure – increasing cabin’s altitude- “taking the cabin up”.
❇️DN commands the outflow valve close, increasing cabin pressure – decreasing cabin’s altitude- “taking the cabin down”.
NOTE: Pressurization system performance can be monitored on either the ECAM CAB PRESS or Cruise page.
Recall, in the event the flight must return to the departure airport immediately after takeoff, what pressurization system action must be taken by the pilot?
No pilot action is required. The pressurization system will automatically return the cabin to match the takeoff altitude. This is referred to as the system’s Abort Mode.
Describe the function of the DITCHING pb.
Placing the DITCHING pb to ON commands the following openings to close:
▪ Outflow valve (if the MODE SEL pb is AUTO)
▪ Emergency Ram Air Inlet
▪ Avionics ventilation inlet and outlet valves
▪ Pack flow control valves
NOTE: Each valve listed above is located below the aircraft’s flotation line.
Recall which areas of the wings and engines are provided ice protection.
Wings?
outboard three slats (Slats 3, 4, and 5).
Recall which areas of the wings and engines are provided ice protection.
Engines?
Engine nacelle leading edge
Recall whether an engine bleed valve must be open in order to use its respective engine anti-ice system.
No. Engine anti-ice is plumbed independently from the high-pressure compressor therefore, the engine’s bleed valve does not have to be open in order to use engine anti-ice.
Describe the indications when engine anti-ice is selected on.
▪ ON (blue) illuminates on the respective ENG 1(2) pb.
▪ ENG A.ICE and IGNITION (green) appears on the E/WD memo section.
Describe the indications of wing anti-ice being selected on.
▪ ON (blue) illuminates on the WING pb.
▪ WING A. ICE (green) appears on the E/WD memo section.
▪ ANTI ICE (white) appears on each side of the BLEED page.
▪ Green arrows appear on each side of the BLEED page when the respective wing anti-ice valve is open for that wing.
Recall the meaning of the FAULT (amber) light in the WING and ENG 1(2) ANTI ICE pbs.
▪ Appears momentarily during valve transition.
▪ Represents disagreement between the selected position and actual respective valve’s position.
▪ The FAULT light on the WING pb also indicates low bleed air pressure is being detected
Recall the operation of the Probe and Window heating system with the PROBE/WINDOW HEAT pb in AUTO (light out).
▪ On the ground, with at least one engine running:
all flight deck windows/windshields, pitot probes, static ports, and AOA probes are automatically heated at a low heat level.
▪ Once airborne, heat levels are increased, and the TAT probes are heated.
Recall the operation of the Probe and Window heating system with the PROBE/WINDOW HEAT pb selected ON.
▪ On the ground, with engines not running: o all flight deck windows/windshields, pitot probes, static ports, and AOA probes are heated at a low heat level.
