DOC AIRBUS | AMM A320FPNEUMATIC - DESCRIPTION AND OPERATION
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1. General
The pneumatic system gets compressed air from the pneumatic air sources and supplies the compressed air through ducts to the user systems. The ducts are installed in the fuselage, the belly fairing and the wings.
The control of the pneumatic system is usually automatic. Bleed-Air Monitoring Computers (BMCs) control the automatic function. The BMCs are installed in the avionics compartment. There is one BMC for each engine.
You can also control the system manually. The pushbutton and selector switches on the overhead panel 30VU in the cockpit, control the manual function.
You can monitor the operation of the pneumatic system on the ECAM System Display (SD). The pushbutton switches on the overhead panel 30VU have no indication when the system operates correctly.
The pneumatic system gets compressed air from the pneumatic air sources and supplies the compressed air through ducts to the user systems. The ducts are installed in the fuselage, the belly fairing and the wings.
The control of the pneumatic system is usually automatic. Bleed-Air Monitoring Computers (BMCs) control the automatic function. The BMCs are installed in the avionics compartment. There is one BMC for each engine.
You can also control the system manually. The pushbutton and selector switches on the overhead panel 30VU in the cockpit, control the manual function.
You can monitor the operation of the pneumatic system on the ECAM System Display (SD). The pushbutton switches on the overhead panel 30VU have no indication when the system operates correctly.
A. Pneumatic Air Sources
The aircraft engines, the APU or a ground air source can supply compressed air to the pneumatic system. The distribution system supplies the compressed air from the different sources to the user systems.
The aircraft engines, the APU or a ground air source can supply compressed air to the pneumatic system. The distribution system supplies the compressed air from the different sources to the user systems.
The aircraft engines, the APU or a ground air source can supply compressed air to the pneumatic system. The distribution system supplies the compressed air from the different sources to the user systems.
The aircraft engines, the APU or a ground air source can supply compressed air to the pneumatic system. The distribution system supplies the compressed air from the different sources to the user systems.
(1) The aircraft engines are the primary source of compressed air in flight. The air is bled from the 5th (IP) or 9th stage (CFMI engines) of the engine High Pressure (HP) compressor. The engine bleed air is temperature and pressure controlled.
(2) The Auxiliary Power Unit (APU) is the primary source of compressed air on the ground. The air is bled from the APU load-compressor module. You can also use the APU to supply bleed air to the user systems during flight. The APU can supply bleed air up to an altitude of 20000 ft. (6096 m).
(3) A ground air source is an alternative to the APU for the supply of compressed air on the ground. There is one High Pressure (HP) ground connector installed on the aircraft. You can use it to let the ground air source supply compressed air to the pneumatic system.
(4) The aircraft engines are the primary source of compressed air in flight. The air is bled from the 7th or 10th stage of the engine High Pressure (HP) compressor. The engine bleed air is temperature and pressure controlled.
(5) The Auxiliary Power Unit (APU) is the primary source of compressed air on the ground. The air is bled from the APU load-compressor module. You can also use the APU to supply bleed air to the user systems during flight. The APU can supply bleed air up to an altitude of 20000 ft. (6096 m).
(6) A ground air source is an alternative to the APU for the supply of compressed air on the ground. There is one High Pressure (HP) ground connector installed on the aircraft. You can use it to let the ground air source supply compressed air to the pneumatic system.
B. User Systems
The pneumatic system supplies the subsequent aircraft systems:
The pneumatic system supplies the subsequent aircraft systems:
- the wing ice protection system (Ref. AMM D/O 30-11-00-00),
- the air conditioning system (Ref. AMM D/O 21-00-00-00),
- the engine starting system (Ref. AMM D/O 80-00-00-00),
- the hydraulic reservoir pressurizing system (Ref. AMM D/O 29-14-00-00),
- the pressurized water system (Ref. AMM D/O 38-42-00-00),
- the nacelle anti-ice valve (servo pressure) (Ref. AMM D/O 30-00-00-00)
- the wing ice protection system (Ref. AMM D/O 30-11-00-00),
- the air conditioning system (Ref. AMM D/O 21-00-00-00),
- the engine starting system (Ref. AMM D/O 80-00-00-00),
- the hydraulic reservoir pressurizing system (Ref. AMM D/O 29-14-00-00),
- the pressurized water system (Ref. AMM D/O 38-42-00-00),
2. Component Location
Component Location - Fuselage ** ON A/C NOT FOR ALL
Component Location - Fuselage ** ON A/C NOT FOR ALL
Component Location - Cockpit ** ON A/C NOT FOR ALL
Component Location - Cockpit ** ON A/C NOT FOR ALL
** ON A/C NOT FOR ALL Component Location - Fuselage ** ON A/C NOT FOR ALL Component Location - Fuselage ** ON A/C NOT FOR ALL Component Location - Cockpit ** ON A/C NOT FOR ALL Component Location - Cockpit ** ON A/C NOT FOR ALL 3. System Description
Pneumatic System - Schematic ** ON A/C NOT FOR ALL
Pneumatic System - Schematic ** ON A/C NOT FOR ALL
Pneumatic System - Schematic ** ON A/C NOT FOR ALL
The pneumatic system has the subsequent subsystems:
Pneumatic System - Schematic ** ON A/C NOT FOR ALL Pneumatic System - Schematic ** ON A/C NOT FOR ALL Pneumatic System - Schematic ** ON A/C NOT FOR ALL - distribution (Ref. AMM D/O 36-10-00-00),
- indicating (Ref. AMM D/O 36-20-00-00).
A. Distribution
The distribution system supplies the bleed air from the different bleed air sources to the user systems.
The distribution system has the subsequent subsystems:
The distribution system supplies the bleed air from the different bleed air sources to the user systems.
The distribution system has the subsequent subsystems:
- the engine bleed-air supply-system (Ref. AMM D/O 36-11-00-00),
- the APU bleed-air supply and crossfeed system (Ref. AMM D/O 36-12-00-00),
- the ground compressed-air supply-system (Ref. AMM D/O 36-13-00-00),
- environment protection (Ref. AMM D/O 36-14-00-00).
B. Indicating
The indicating system has the subsequent subsystems:
The indicating system has the subsequent subsystems:
- pressure and temperature monitoring (Ref. AMM D/O 36-21-00-00),
- leak detection (Ref. AMM D/O 36-22-00-00).
- the pressure and the temperature of the bleed air in the ducts,
- the valve position of the different valves,
- the overheat detection sensing-elements which are installed on or near to the ducts.
4. Power Supply
Pneumatic System - Electrical Schematic ** ON A/C NOT FOR ALL
Pneumatic System - Electrical Schematic ** ON A/C NOT FOR ALL
Pneumatic System - Electrical Schematic ** ON A/C NOT FOR ALL
Pneumatic System - Electrical Schematic ** ON A/C NOT FOR ALL
Pneumatic System - Electrical Schematic ** ON A/C NOT FOR ALL
Pneumatic System - Electrical Schematic ** ON A/C NOT FOR ALL
The pneumatic system gets electrical power from the DC system of the aircraft. The DC system supplies 28 V DC through the circuit breakers 2HA1, 2HA2, 3HA1 and 3HA2 to:
** ON A/C NOT FOR ALL Pneumatic System - Electrical Schematic ** ON A/C NOT FOR ALL Pneumatic System - Electrical Schematic ** ON A/C NOT FOR ALL Pneumatic System - Electrical Schematic ** ON A/C NOT FOR ALL Pneumatic System - Electrical Schematic ** ON A/C NOT FOR ALL Pneumatic System - Electrical Schematic ** ON A/C NOT FOR ALL Pneumatic System - Electrical Schematic ** ON A/C NOT FOR ALL - the Bleed Air Monitoring Computers,
- the relays of the AIR COND overhead panel,
- the FIRE overhead panel,
- the pressure transducers.
5. Operation/Control and Indicating
Component Location - Cockpit ** ON A/C NOT FOR ALL
Component Location - Cockpit ** ON A/C NOT FOR ALL
Pneumatic System - Schematic ** ON A/C NOT FOR ALL
Pneumatic System - Schematic ** ON A/C NOT FOR ALL
Pneumatic System - Schematic ** ON A/C NOT FOR ALL
The operation and control of the pneumatic system is usually automatic. The BMCs monitor and control the automatic operation. You can also control the system manually from the cockpit. The pushbutton and selector switches on the overhead panel 30VU control the manual function.
You can monitor the operation of the pneumatic system on the BLEED page of the SD. The APU page of the SD also shows some information related to the APU bleed air. The pushbutton switches on the overhead panel 30VU have no indication when the system operates correctly. If there is a failure, the failure data are available on the ECAM Engine/Warning Display (EWD), the SD and the Centralized Fault Display System (CFDS). The pushbutton switches on the overhead panel 30VU can also show some failures. (Ref. AMM D/O 36-20-00-00).
** ON A/C NOT FOR ALL Component Location - Cockpit ** ON A/C NOT FOR ALL Component Location - Cockpit ** ON A/C NOT FOR ALL Pneumatic System - Schematic ** ON A/C NOT FOR ALL Pneumatic System - Schematic ** ON A/C NOT FOR ALL Pneumatic System - Schematic ** ON A/C NOT FOR ALL You can monitor the operation of the pneumatic system on the BLEED page of the SD. The APU page of the SD also shows some information related to the APU bleed air. The pushbutton switches on the overhead panel 30VU have no indication when the system operates correctly. If there is a failure, the failure data are available on the ECAM Engine/Warning Display (EWD), the SD and the Centralized Fault Display System (CFDS). The pushbutton switches on the overhead panel 30VU can also show some failures. (Ref. AMM D/O 36-20-00-00).
6. Bite Test
The Centralized Fault Display System (CFDS) gives the maintenance crew a maintenance aid. It permits to test the BMC or to get the maintenance data of the bleed air system.
The CFDS gets the information through the Centralized Fault Display Interface Unit (CFDIU) (Ref. AMM D/O 31-32-00-00) from the BMC. The Multi-purpose Control Display Units (MCDU) in the cockpit displays this information in clear text.
The Centralized Fault Display System (CFDS) gives the maintenance crew a maintenance aid. It permits to test the BMC or to get the maintenance data of the bleed air system.
The CFDS gets the information through the Centralized Fault Display Interface Unit (CFDIU) (Ref. AMM D/O 31-32-00-00) from the BMC. The Multi-purpose Control Display Units (MCDU) in the cockpit displays this information in clear text.