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when the fuel temperature is above 15 °C). When the temperature is above 70 °C, the idle speed is
increased.
For some cases of failure, the fuel flow is reduced to a lower value.
FUEL RECIRCULATION INHIBITION
Applicable to:
The recirculation to tank is inhibited (Fuel Return Valve (FRV) closed) in the following cases:
‐ Engine starting
‐ Engine shutdown (N2 below 50 %)
‐ When fuel flow is above 2 700 kg/h (take-off power)
‐ Upon fuel system request which occurs in the following conditions :
• Inner tank temperature above 59,5 °C or,
• Engines feed by gravity or,
• Inner tank quantity below 500 kg or,
• Inner tank high level and vent tank sensors are wet and at least one X-feed valve on each wing
is open.
This closure signal is inhibited if all the following conditions are met :
‐ Fuel flow below 1 000 kg/h
Engine ‐ oil temperature above 115 °C
‐ Altitude above 15 000 ft.
‐ When fuel flow is above 1 300 kg/h in emergency electrical configuration.
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
POWER PLANT
OIL SYSTEM
A330/A340 FLEET DSC-70-50 P 1/2
FCOM 19 AUG 10
GENERAL
Applicable to:
The oil system lubricates the engine components.
It contains the :
‐ Oil tank
‐ Lube and scavenge pump modules
‐ Fuel/oil heat exchanger
‐ Filters, pressure relief and bypass valves.
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
POWER PLANT
OIL SYSTEM
A330/A340 FLEET DSC-70-50 P 2/2
FCOM 19 AUG 10
GENERAL
Applicable to: ,
The oil system lubricates the engine components.
It contains the :
‐ Oil tank
‐ Lube and scavenge pump modules
‐ Fuel/oil and air/oil heat exchanger
‐ Filters, pressure relief and bypass valves.
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
POWER PLANT
AIRBLEED SYSTEM
A330/A340 FLEET DSC-70-60 P 1/4
FCOM 19 AUG 10
GENERAL
Applicable to:
The air bleed system is used for :
‐ The pneumatic system (Refer to DSC-36-10-10 GENERAL).
‐ Cooling the engine compartment and the turbine.
GENERAL
Applicable to: ,
The air bleed system is used for :
‐ The pneumatic system (Refer to DSC-36-10-10 GENERAL).
‐ Cooling the engine compartment and the turbine.
‐ Cooling the engine and IDG oil
‐ Engine stability.
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
POWER PLANT
AIRBLEED SYSTEM
A330/A340 FLEET DSC-70-60 P 2/4
FCOM 19 AUG 10
COOLING
Applicable to:
ROTOR ACTIVE CLEARANCE CONTROL START BLEED SYSTEM
The rotor active clearance (RAC) and the start bleed (SB) control systems use air from 5th stage
to control the clearance of the high pressure compressor rotor blades relative to the high pressure
compressor stator case, and 9th stage to unload the compressor during starts and accelerations.
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
POWER PLANT
AIRBLEED SYSTEM
A330/A340 FLEET DSC-70-60 P 3/4
FCOM 19 AUG 10
The function of the RAC system is to improve compressor efficiency during cruise, and the
function to the SB system is to improve stall margin during engine start and acceleration.
HP TURBINE CLEARANCE CONTROL (HPTCC) SYSTEM
The HPTCC system is controlled by the FADEC, through the HMU, and controls the high pressure
turbine clearance. The FADEC modulates the high pressure compressor bleed air flow for the high
pressure turbine case cooling.
It provides optimization of high pressure turbine performance and EGT reduction.
LP TURBINE CLEARANCE CONTROL (LPTCC) SYSTEM
The LPTCC system is controlled by the FADEC, through the HMU, and controls low pressure
turbine clearance.
The FADEC modulates the fan bleed air flow for the low pressure turbine case cooling.
COOLING
Applicable to: ,
TURBINE CASE COOLING (TCC)
The TCC system is controlled by the FADEC to improve engine performance by controlling the
intermediate pressure turbine blade tip clearance, and cooling intermediate pressure and low
pressure turbine cases.
The TCC valve is controlled by the FADEC to modulate air flow depending on flight conditions.
The valve is fully open in cruise for optimal engine performance.
INTERNAL GEARBOX COOLING
The internal gearbox cooling system is controlled by the FADEC to regulate air pressure and
temperature within the engine center bearing. The HP 3 air to gearbox is cooled in the Air Cooled
Air Cooler (ACAC) using fan air and modulated by a dual valve controlled by the FADEC. The
valve is fully open during hot day take-off and climb conditions.
　
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