R **ON A/C 151-199, 401-499,
R **ON A/C 151-199,
R (Ref. Fig. 004C)
R **ON A/C 401-499,
R (Ref. Fig. 004D)
R **ON A/C 151-199,
R (Ref. Fig. 005C)
R **ON A/C 401-499,
R (Ref. Fig. 005D)
R **ON A/C 151-199, 401-499,
-------------------------------------------------------------------------------BUSBAR VOLTAGE FUNCTIONS ATA NO. AND POWER SUPPLY -------------------------------------------------------------------------------
801PP 28 VDC ESS Power Supply to : Bleed Air Monitoring Computer 1 (BMC 1) Relay ENG 1 BLEED LAMP TEST AND INTERFC Pressure Transducers 36-11-0036-20-0036-21-00
202PP 28 VDC NORM Power Supply to : Bleed Air Monitoring Computer 2 (BMC 2) Relay ENG 2 BLEED LAMP TEST AND INTERFC Pressure Transducers 36-11-0036-20-0036-21-00
801PP 28 VDC ESS Power Supply to : Bleed Air Monitoring Computer 1 (BMC 1) ENG 1 BLEED Pushbutton Switch 36-11-0036-20-00
ENG 1 FIRE Handle 26-00-00
202PP 28 VDC NORM Relay ENG 1 HP BLEED OVRD SOL Power Supply to : Bleed Air Monitoring Computer 2 (BMC 2) ENG 2 BLEED Pushbutton Switch 36-11-0036-11-0036-20-00
ENG 2 FIRE Handle 26-00-00
Relay ENG 2 HP BLEED OVRD SOL 36-11-00
**ON A/C ALL
6. Operation_________
**ON A/C 001-049, 051-099, 101-149, 201-299, 301-399, (Ref. Fig. 006) R **ON A/C 151-199, 401-499, (Ref. Fig. 006A)
**ON A/C ALL
(Ref. Fig. 011, 013)
**ON A/C 001-003, 051-054, 056-056,
(Ref. Fig. 022)
R R **ON A/C 004-049, 055-055, 057-099, 101-149, 151-199, 201-299, 301-399, 401-499,
(Ref. Fig. 022A)
**ON A/C 001-001, 051-052,
(Ref. Fig. 024)
**ON A/C 002-049, 053-099, 101-149, 151-199, 201-299, 301-399,
(Ref. Fig. 024A)
R **ON A/C 401-499,
R (Ref. Fig. 024B)
**ON A/C ALL
A. Function - The bleed systems of engines 1 and 2 are similar and operate independently of each other. - Air is tapped either from intermediate HP compressor stage through an IP bleed check valve or from high HP compressor stage through an HP bleed valve according to engine speed. - When engine speed is low, especially during aircraft descent with engine at iddle, IP port pressure is insufficient. The air is automatically bled from the HP port (high pressure, on the 9th stage) through the HP Bleed Valve and IP Bleed Check Valve is closed to prevent air recirculation.
-When engine speed is high, the engine air bleed is in normal configuration. The air is bled from the IP port (intermediate pressure, on the 5th stage) through the IP Bleed Check Valve and HP Bleed Valve closes.
-Dowstream of the HP bleed valve and IP check valve, the bleed pressure regulator valve regulates the bleed air pressure to a predetermined value. The valve can be controlled in closed position through a solenoid installed downstream of the precooler exchanger. As the PRV is connected to the HPV by a sense line, when the bleed is controlled OFF, both PRV and HPV are vented and close simultaneously.
-To prevent any ducting damage caused by an incorrect regulation of the PRV (high pressure) an overpressure valve has been installed downstream of the PRV. It will close when downstream PRV pressure reaches the OPV closing value.
-Pressure regulated air is then routed to the users through the bleed air precooler exchanger where it is be cooled. Cooling is achieved by modulation of cold airflow from the engine fan, through a fan air valve controlled by a fan air valve control thermostat.
B. Fault Detection and Monitoring of the System The monitoring system detects failures and abnormal operation of the engine bleed air supply system. It warns the crew and transmitts the relevant information to the upper and lower ECAM display units. Additionally the MASTER CAUT light comes on and a single chime sounds. The system also enables abnormal operation and failure to be detected during flight in order to facilitate replacement on the ground of faulty components (Line Replaceable Units, LRU).
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