-
two presssure transducers which monitor the pressure in the ducts,
-
two Bleed-air Monitoring Computers (BMC1 and BMC2) which receive information from the sensors. They monitor the system and control its operation,
-several temperature sensors (provided for regulation) which detect overtemperature in ducts and give temperature indication.
**ON A/C ALL
B. The Bleed Air and Crossbleed (Crossfeed) System of the Auxiliary Power Unit (APU) (Ref. 36-12-00)
**ON A/C 001-049, 051-099, 101-105, 151-199, 201-210,
(Ref. Fig. 006)
R **ON A/C 106-149, 211-299, 301-399, 401-499,
(Ref. Fig. 006A)
**ON A/C ALL
This system is installed in the MID and AFT fuselage and contains:
-a crossbleed valve which isolates or connects the right and left bleed air and distribution systems,
-
an APU bleed load valve which is a part of the APU. This valve controls the bleed air flow from the compressor of the APU when the supply system of the engine is off or does not operate,
-
an APU bleed check valve in the APU duct which protects the APU against bleed air from the engine(s).
C. The Ground Supply of Compressed Air (Ref. 36-13-00) (Ref. Fig. 007) This system is installed in the lower MID fuselage on the left side and includes a ground connector behind panel 191DB. A check valve is installed inside the ground connector. This stops the loss of air when the ground supply unit is not connected. The HP air is supplied to the distribution systems through the ground connector.
Component Location - MID and AFT Fuselage
Figure 006
R 1EFF : 001-049, 051-099, 101-105, 151-199, 1 36-10-00Page 12 1201-210, 1May 01/05 1 1 1CES 1
Component Location - MID and AFT Fuselage
Figure 006A
R 1EFF : 106-149, 211-299, 301-399, 401-499, 1 36-10-00Page 13 1 1 Aug 01/05 1 1 1CES 1
Component Location - Lower Fuselage
Figure 007
1EFF : ALL 1 36-10-00 Page 14
1 1 Aug 01/02
1 1
1CES 1
D. Environment Protection (Ref. 36-14-00)
-Protection of the Pylon and the Nacelles This system is installed between the engine pylons and the fuselage. It has a protection function of the wing leading edge and the nacelle. If there is a major leak in the pneumatic system, a door opens and the pressure is released.
ENGINE BLEED AIR SUPPLY SYSTEM - DESCRIPTION AND OPERATION
__________________________________________________________
R 1. General_______ The purpose of the engine bleed air supply system is to: - select one of the two different compressor stages of the engine HP compressor in agreement with the supplied pressure - regulate the bleed air pressure in order to prevent too high pressures - regulate the bleed air temperature in order to prevent too high temperatures. 2. Component Location__________________ **ON A/C 001-049, 051-099, 101-149, 201-299, 301-399,
R (Ref. Fig. 001, 002, 003) **ON A/C 001-049, 052-099, 101-105, 201-220, 224-224,
R (Ref. Fig. 004) **ON A/C 051-051,
R R (Ref. Fig. 004A) **ON A/C 106-149, 221-223, 225-299, 301-399,
R (Ref. Fig. 004B) **ON A/C 001-049, 052-099, 101-105, 201-220, 224-224,
R (Ref. Fig. 005) **ON A/C 051-051,
R R (Ref. Fig. 005A) **ON A/C 106-149, 221-223, 225-299, 301-399,
(Ref. Fig. 005B)
R **ON A/C 001-049, 051-099, 101-149, 201-299, 301-399,
-------------------------------------------------------------------------------FIN I FUNCTIONAL DESIGNATION I PANELIZONEIACCESS I ATA
I I I I DOOR I REF. -------------------------------------------------------------------------------1HA1 BMC-1 95VU 121 811 36-11-34 1HA2 BMC-2 96VU 122 811 36-11-34 5HA1 VALVE-OVERPRESSURE, ENG 1 453 36-11-53 5HA2 VALVE-OVERPRESSURE, ENG 2 463 36-11-53 6HA1 SENSOR-EXCHANGER OUT TEMP ENG 1 471 36-11-17 6HA2 SENSOR-EXCHANGER OUT TEMP ENG 2 481 36-11-17 7HA1 XDCR-BLEED TRANSFER PRESS, ENG 1 415 36-11-15 7HA2 XDCR-BLEED TRANSFER PRESS, ENG 2 425 36-11-15 8HA1 XDCR-BLEED REGULATED PRESS, ENG 1 415 36-11-16 8HA2 XDCR-BLEED REGULATED PRESS, ENG 2 425 36-11-16 9HA1 VALVE-FAN AIR, ENG1 453 36-11-54 9HA2 VALVE-FAN AIR, ENG2 463 36-11-54 10HA1 SOLENOID-BLEED PRESS REG V CTL, 413 36-11-55
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：A320飛機維護手冊 AMM PNEUMATIC 氣源 1(21)
