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‐ APU load compressor
‐ HP ground connection
A crossbleed duct interconnects the engine bleed systems and receives air from the APU and ground
sources when appropriate.
A valve mounted on the crossbleed duct allows the left side (engine 1) and right side (engine 2) to be
interconnected.
Two Bleed Monitoring Computers (BMC1 and BMC2), the overhead control panel, and the ECAM
control and monitor the operation of the pneumatic system.
A leak detection system detects any overheating in the vicinity of hot air ducts.
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
PNEUMATIC
DESCRIPTION - GENERAL
Intentionally left blank
A318/A319/A320/A321 FLEET DSC-36-10-10 P 2/2
FCOM 19 AUG 10
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
PNEUMATIC
DESCRIPTION - ENGINE BLEED SYSTEM
A318/A319/A320/A321 FLEET DSC-36-10-20 P 1/10
FCOM 19 AUG 10
GENERAL
Applicable to: ALL
The aircraft has two similar engine bleed air systems.
Each system is designed to :
select the compressor stage ‐ to use as a source of air
‐ regulate the bleed air temperature
‐ regulate the bleed air pressure.
A Bleed Monitoring Computer (BMC) controls and monitors each system.
Each BMC receives information about bleed pressure and temperature and valve position.
Each is connected with :
‐ other systems using air or information from the bleed system
‐ the other BMC.
Each supplies indications and warnings to the ECAM and CFDS.
If one BMC fails, the other one takes over most of the monitoring functions.
Each bleed valve is pneumatically operated and controlled electrically by its associated BMC.
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
PNEUMATIC
DESCRIPTION - ENGINE BLEED SYSTEM
A318/A319/A320/A321 FLEET DSC-36-10-20 P 2/10
FCOM 19 AUG 10
ARCHITECTURE
Applicable to:
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
PNEUMATIC
DESCRIPTION - ENGINE BLEED SYSTEM
A318/A319/A320/A321 FLEET DSC-36-10-20 P 3/10
FCOM 19 AUG 10
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
PNEUMATIC
DESCRIPTION - ENGINE BLEED SYSTEM
A318/A319/A320/A321 FLEET DSC-36-10-20 P 4/10
FCOM 19 AUG 10
ARCHITECTURE
Applicable to:
,
,
MSN,
4719,,,
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
PNEUMATIC
DESCRIPTION - ENGINE BLEED SYSTEM
A318/A319/A320/A321 FLEET DSC-36-10-20 P 5/10
FCOM 19 AUG 10
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
PNEUMATIC
DESCRIPTION - ENGINE BLEED SYSTEM
A318/A319/A320/A321 FLEET DSC-36-10-20 P 6/10
FCOM 19 AUG 10
AIR BLEED SELECTION
Applicable to:
Air is normally bled from the intermediate pressure stage (IP) of engine’s high-pressure (HP)
compressor to minimize fuel penalty.
At low engine speed, when the pressure and temperature of the IP air are too low, the system bleeds
air from the HP stage and maintains it at 36 ± 4 PSI.
An intermediate pressure check valve downstream of the IP port closes to prevent air from the HP
stage from being circulated to the IP stage.
L3 The HP valve closes automatically
‐ pneumatically
• in case of low upstream pressure
• in case of excessive upstream pressure
‐ electrically when the bleed valve is closed electrically.
L1ECAM INDICATION
AIR BLEED SELECTION
Applicable to:
, ,
MSN
Air is normally bled from the intermediate pressure stage (IP) of engine’s high-pressure (HP)
compressor to minimize fuel penalty.
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
PNEUMATIC
DESCRIPTION - ENGINE BLEED SYSTEM
A318/A319/A320/A321 FLEET DSC-36-10-20 P 7/10
FCOM 19 AUG 10
At low engine speed, when the pressure and temperature of the IP air are too low, the system bleeds
air from the HP stage and maintains it at 36 ± 4 PSI.
An intermediate pressure check valve downstream of the IP port closes to prevent air from the HP
stage from being circulated to the IP stage.
L3 The HP valve closes automatically
‐ pneumatically
• in case of low upstream pressure
• in case of excessive upstream pressure
‐ electrically when the bleed valve is closed electrically.
L1ECAM INDICATION
AIR BLEED SELECTION
Applicable to:
Air is normally bled from the intermediate pressure stage (IP) of engine’s high-pressure (HP)
compressor to minimize fuel penalty.
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A320机组操作手册FLIGHT CREW OPERATING MANUAL 4(63)
