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FCOM 19 AUG 10
GENERAL
Applicable to:
There is a crossbleed valve on the crossbleed duct. This valve enables the isolation or
interconnection of the LH (ENG 1 and 2) and RH (ENG 3 and 4) air supply system.
The crossbleed valve is electrically controlled from a rotary selector that is located on the overhead
AIR panel.
Two electric motors control the crossbleed valve : One is for automatic mode, the other is for manual
mode.
In automatic mode, the crossbleed valve is normally closed. It opens when APU bleed air is used.
GENERAL
Applicable to: ,
There is a crossbleed valve on the crossbleed duct. This valve enables the isolation or
interconnection of LH (ENG1) and RH (ENG2) air supply system.
The crossbleed valve is electrically controlled from a rotary selector that is located on the overhead
AIR panel.
Two electric motors control the crossbleed valve : One is for automatic mode, the other is for manual
mode.
In automatic mode, the crossbleed valve is normally closed. It opens when APU bleed air is used.
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
PNEUMATIC
DESCRIPTION - CROSSBLEED
A330/A340 FLEET DSC-36-10-50 P 2/4
FCOM 19 AUG 10
CROSSBLEED VALVE CONTROL LOGIC
Applicable to:
X-BLEED VALVE CONTROL LOGIC
Applicable to: ,
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
PNEUMATIC
DESCRIPTION - CROSSBLEED
A330/A340 FLEET DSC-36-10-50 P 3/4
FCOM 19 AUG 10
ECAM INDICATION
Applicable to:
ECAM INDICATION
Applicable to: ,
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
PNEUMATIC
DESCRIPTION - CROSSBLEED
Intentionally left blank
A330/A340 FLEET DSC-36-10-50 P 4/4
FCOM 19 AUG 10
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
PNEUMATIC
DESCRIPTION - LEAK DETECTION
A330/A340 FLEET DSC-36-10-60 P 1/4
FCOM 19 AUG 10
LEAK DETECTION
Applicable to:
The air leakage detection loops detect any ambient overheat in the vicinity of the hot air ducts in the
fuselage, pylons and wings.
The sensing elements are tied to form a single loop, for pylon and APU, or, a double loop for the
wing.
A wing leak signal is activated when the two loops detect a leak, or when one loop detects the leak
and the other is inoperative.
The system has identical control logic included in each BMC.
‐ In case of wing leak signal
• Both engine bleed valves and HP valves on the affected wing are automatically closed.
• Both associated ENGINE BLEED FAULT light on the AIR panel are illuminated
• The X-bleed valve automatically closes (except when manually selected open).
• If the APU bleed valve is open, and if the leak affects the left wing, the APU bleed valve
automatically closes.
‐ In case of pylon leak signal
• Both bleed valves and both HP valves on the affected side are automatically closed
• Both associated FAULT lights on the AIR panel are illuminated.
• The X-bleed valve automatically closes (except during an engine start or manually selected
open).
• If the APU bleed valve is opened, and if the leak affects pylon 1 or 2, the APU bleed valve
automatically closes (except during engine start).
‐ In case of APU leak signal
• The APU bleed valve automatically closes
• The FAULT light illuminates on the APU BLEED pushbutton on the AIR panel.
• The X-bleed valve automatically closes (except when manually selected open).
• If the APU bleed valve is closed, the engine bleed valves and HP valves on the left hand side
automatically close.
APU bleed leak detection is performed only by BMC 2.
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
PNEUMATIC
DESCRIPTION - LEAK DETECTION
A330/A340 FLEET DSC-36-10-60 P 2/4
FCOM 19 AUG 10
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
PNEUMATIC
DESCRIPTION - LEAK DETECTION
A330/A340 FLEET DSC-36-10-60 P 3/4
FCOM 19 AUG 10
LEAK DETECTION
Applicable to: ,
The air leakage detection loops detect any ambient overheat in the vicinity of the hot air ducts in the
fuselage, pylons and wings.
The sensing elements are tied to form a single loop, for pylon or, a double loop for the wing and
APU.
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.
The system has identical control logic included in each BMC.
‐ In case of wing leak signal
• The engine bleed valve and HP valve on the affected wing are automatically closed.
　
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