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OVERHEAD PANEL......................................................................................................................................... 4/16
ECAM................................................................................................................................................................ 4/16
WARNINGS AND CAUTIONS........................................................................................................................ 11/16
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
POWER PLANT
PRELIMINARY PAGES - TABLE OF CONTENTS
A330/A340 FLEET DSC-70-PLP-TOC P 4/4
FCOM 19 AUG 10
DSC-70-97 A330 ELECTRICAL SUPPLY
BUS EQUIPMENT LIST......................................................................................................................................1/2
DSC-70-98 A340 ELECTRICAL SUPPLY
BUS EQUIPMENT LIST......................................................................................................................................1/2
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
POWER PLANT
ENGINE
A330/A340 FLEET DSC-70-10 P 1/4
FCOM 19 AUG 10
GENERAL
Applicable to:
The CFM 56-5C engine is a high bypass ratio turbofan.
GENERAL
Applicable to: ,
The RR RB 211 TRENT engine is a high bypass ratio turbofan.
DESCRIPTION
Applicable to:
‐ Low-pressure (LP) compressor / turbine
The low-speed rotor (N1) consists of a front fan (single stage) and a four-stage LP compressor
connected to a five-stage LP turbine.
‐ High-pressure (HP) compressor / turbine
The high-speed rotor (N2) consists of a nine-stage HP compressor connected to a single-stage HP
turbine.
‐ Combustion chamber
The annular combustion chamber is fitted with 20 fuel nozzles and 2 igniters.
‐ Accessory gearbox
The accessory gearbox, located at the bottom of the fan case, receives torque from horizontal
HP rotor drive shaft and drives gearbox mounted accessories such as : IDG, hydraulic pump, oil
pump, engine driven pump, HMU and electrical generator for the FADEC.
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
POWER PLANT
ENGINE
A330/A340 FLEET DSC-70-10 P 2/4
FCOM 19 AUG 10
DESCRIPTION
Applicable to: ,
‐ Low-pressure (LP) compressor / turbine
The low-speed rotor (N1) consists of single stage LP compressor (front fan) connected to a four
stage LP turbine.
‐ Intermediate pressure compressor / turbine
The intermediate speed rotor (N2) consists of a eight-stage intermediate pressure compressor
connected to a single-stage IP turbine.
‐ High-pressure (HP) compressor / turbine
The high-speed rotor (N3) consists of a six-stage HP compressor connected to a single-stage HP
turbine.
‐ Combustion chamber
The annular combustion chamber is fitted with 24 fuel nozzles and 2 igniters.
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
POWER PLANT
ENGINE
A330/A340 FLEET DSC-70-10 P 3/4
FCOM 19 AUG 10
‐ Accessory gearbox
The accessory gearbox, located at the bottom of the fan case, receives torque from horizontal HP
rotor drive shaft and drives gearbox mounted accessories.
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
POWER PLANT
ENGINE
Intentionally left blank
A330/A340 FLEET DSC-70-10 P 4/4
FCOM 19 AUG 10
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
POWER PLANT
FADEC
A330/A340 FLEET DSC-70-20 P 1/10
FCOM 19 AUG 10
GENERAL - GENERAL
Applicable to:
Each powerplant has a FADEC (Full Authority Digital Engine Control) system.
FADEC, also called the electronic control unit (ECU), is a digital control system that performs
complete engine management.
FADEC has two-channel redundancy, with one channel active and one standby.
If one channel fails, the other automatically takes control.
The system has a magnetic alternator for an internal power source.
FADEC is mounted on the fan case.
The engine interface unit (EIU) transmits the data it uses for engine management to the FADEC.
GENERAL - GENERAL
Applicable to: ,
Each powerplant has a FADEC (Full Authority Digital Engine Control) system.
FADEC, also called the electronic engine control (EEC), is a digital control system that performs
complete engine management.
FADEC has two-channel redundancy, with one channel active and one standby.
If one channel fails, the other automatically takes control.
The system has a magnetic alternator for an internal power source.
FADEC is mounted on the fan case.
The engine interface unit (EIU) transmits the data it uses for engine management to the FADEC.
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A330/A340机组操作手册 FLIGHT CREW OPERATING MANUAL FCOM 4(59)
