DOC AIRBUS | AMM A320FDISTRIBUTION - DESCRIPTION AND OPERATION
** ON A/C NOT FOR ALL
Pneumatic System-SchematicA. Temperature and Pressure Regulating System for the Bleed Air from the Engine Compressor (Ref. 36-11-00).
This system is installed in the nacelle and pylon of each engine and includes:
This system is installed in the nacelle and pylon of each engine and includes:
- An Intermediate-Pressure Bleed-Check Valve (IPC)
- A High Pressure Bleed-Valve (HPV)
- A Pressure Regulator Bleed-Valve (PRV) which permits or stops the bleed air supply. A distribution clapper allows feed the closing chamber while the opening chamber comes to ambient pressure, ensuring the closing function.
- An Over-Pressure Valve (OPV) which protects the downstream pneumatic system if the PRV does not operate
- A bleed-air precooler-exchanger (PCE) (air-to-air) which controls the air temperature downstream of the system. The engine fan supplies cooling air through a Fan Air Valve (FAV) to the precooler.
- A Bleed Temperature Sensor (BTS) which monitors the temperature in the ducts
- Two pressure 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
- One Differential Pressure Sensor (18HA) (DPS) which detect differential pressure between the inlet and the outlet of the Precooler.
B. Bleed Air and Crossbleed (Crossfeed) System of the Auxiliary Power Unit (APU) (Ref. 36-12-00)
This system is installed in the MID and AFT fuselage and contains:
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. Ground Compressed-Air Supply System (Ref. 36-13-00)
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.
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.
D. Environment Protection (Ref. 36-14-00)
- Ventilation of the Wing Leading Edge
This system is installed between the engine pylons and the fuselage. The air which flows into the NACA ram air inlet decreases the temperature of the wing leading edge in this area and ensures correct removal of fuel fumes. - Protection of the Wing Leading Edge, Pylon and the Nacelles
The protection systems of the wing leading edge, the pylon and the nacelles keep the pressure in these areas to a limit. The protection systems operate if a pneumatic duct or a wing anti-ice duct bursts or has a large leak. This prevents damage to the structure and the systems installed.