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OPERATING MANUAL
AIRCRAFT SYSTEMS
POWER PLANT
OIL SYSTEM
A318/A319/A320/A321 FLEET DSC-70-50 P 3/4
FCOM 19 AUG 10
GENERAL
Applicable to: MSN
4566,,,
The oil system lubricates the engine components.
It contains :
‐ the oil tank
‐ the lube and scavenge pump modules
‐ the fuel/oil heat and air/oil heat exchangers
‐ the filters, chip detectors, pressure relief and bypass valves.
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
POWER PLANT
OIL SYSTEM
A318/A319/A320/A321 FLEET DSC-70-50 P 4/4
FCOM 19 AUG 10
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
POWER PLANT
AIRBLEED SYSTEM
A318/A319/A320/A321 FLEET DSC-70-60 P 1/4
FCOM 19 AUG 10
GENERAL
Applicable to:
, ,
MSN
The air bleed system supplies the aircraft with compressed air.
It uses the air for :
‐ pneumatic system (Refer to DSC-36-10-10 GENERAL)
‐ cooling the engine compartment and the turbines.
GENERAL
Applicable to: MSN
4566,,,
The air bleed system supplies the aircraft with compressed air.
It uses the air for :
‐ pneumatic system (Refer to DSC-36-10-10 GENERAL)
‐ cooling the engine compartment and the turbines
‐ engine stability.
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
POWER PLANT
AIRBLEED SYSTEM
A318/A319/A320/A321 FLEET DSC-70-60 P 2/4
FCOM 19 AUG 10
COOLING
Applicable to:
, ,
MSN
ROTOR ACTIVE CLEARANCE CONTROL (RACC) SYSTEM
The FADEC controls the RACC system through the HMU. The RACC system controls the
clearance between the rotor blades of the HP compressor and its stator case.
The RACC system uses fifth-stage compressor bleed air that has been modulated according to
the N2 and the flight parameters. The bleed air goes to the N°3 bearing compartment, where it is
mixed with fan boost discharge.
Clearances are at the maximum when the RACC valve is closed.
HP TURBINE CLEARANCE CONTROL (HPTCC) SYSTEM
The FADEC controls the HPTCC system through the HMU. The HPTCC system controls the HP
turbine clearance by modulating the HP compressor bleed air flow for cooling the HP turbine case.
It optimizes HP turbine performance and reduces exhaust gas temperature.
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
POWER PLANT
AIRBLEED SYSTEM
A318/A319/A320/A321 FLEET DSC-70-60 P 3/4
FCOM 19 AUG 10
LP TURBINE CLEARANCE CONTROL (LPTCC) SYSTEM
The FADEC controls the LPTCC system through the HMU. The LPTCC system controls LP turbine
clearance by modulating the fan bleed air flow for cooling the LP turbine case.
COOLING
Applicable to: MSN
4566,,,
Active clearance control for the high and low pressure turbines is ‐ to optimize the turbine blade tip
clearance by cooling the related turbine cases.
This control is made by the FADEC through the FMU as a function of the high pressure rotor
speed, and altitude.
In case of failures the system is designed to failsafe to the closed position.
Should this happen, fuel consumption would be slightly higher.
‐ LP/HP turbine cooling air.
Under FADEC control as a function of N2 and altitude, cooling air is taken from the 10th stage of
the HPC to cool the HPT second stage blade. The control valve is either fully open or closed and
is normally (failsafe) open.
ENGINE STABILITY
Applicable to: MSN
4566,,,
Two air bleed systems (station 2.5 of the LPC and stages 7th and 10th) provide greater compressor
stability in the different flight phases.
The LPC 2.5 bleed valve moves under FADEC control as a function ‐ of the low rotor speed,
altitude and Mach and is dedicated to improve stall margin during starting, low power or transient
operation. The failsafe position of this valve is open.
‐ The 7th and 10th stage bleed valves are normally closed for most engine operation but fully open
for engine starting. Their failsafe position is open. Theses valves are controlled by FADEC through
FMU.
In the two cases, the air is vented to the fan air stream.
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
POWER PLANT
AIRBLEED SYSTEM
Intentionally left blank
A318/A319/A320/A321 FLEET DSC-70-60 P 4/4
FCOM 19 AUG 10
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
POWER PLANT
THRUST REVERSER SYSTEM
A318/A319/A320/A321 FLEET DSC-70-70 P 1/12
FCOM 19 AUG 10
GENERAL
Applicable to: MSN
4566,,,
The reverse thrust is obtained by deflecting the fan airstream. This is done when the translating
　
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