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PRIM 1(2)(3) PITCH FAULT 3, 4, 5, 7, 8
TURB DAMP FAULT
longitudinal or lateral turbulence damping lost due
to accelerometer failure.
3, 4, 5, 7, 8
RUD PRIM 1 FAULT 3, 4, 5, 7, 8
RUD SEC 1 FAULT
NIL NIL
NIL
3 to 8
(1) The red SIDESTICK PRIORITY lt is illuminated as soon as the sidestick is inoperative.
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
FLIGHT CONTROL SYSTEM - WARNINGS AND CAUTIONS
A330/A340 FLEET DSC-27-20-40 P 9/10
FCOM 19 AUG 10
MEMO
‐ SPEED BRK memo display logic :
• When the speedbrakes are extended in Flight Phase 2, 3, 4, and 5, the SPEED BRK memo
flashes amber.
• When the speedbrakes are extended in Flight Phase 6 , the SPEED BRK memo appears in
green.. It flashes amber, after 50 s, if at least one engine is above idle.
• When the speedbrakes are extended in Flight Phase 7, the “SPEED BRK” memo appears
in green. After 5 s , it flashes in amber, and the associated “SPD BRK STILL OUT” caution
appears on the ECAM, regardless of the landing configuration.
The "GND SPLRS ARMED" message appears in green, when ‐ the ground spoilers are armed.
‐ The "TURB DAMP OFF" message appears in green, when the TURB DAMP pushbutton is set
to OFF.
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
FLIGHT CONTROL SYSTEM - WARNINGS AND CAUTIONS
Intentionally left blank
A330/A340 FLEET DSC-27-20-40 P 10/10
FCOM 19 AUG 10
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
FLIGHT CONTROL SYSTEM - ELECTRICAL SUPPLY
A330/A340 FLEET DSC-27-20-50 P 1/2
FCOM 19 AUG 10
BUS EQUIPMENT LIST
Applicable to:
L3
NORM EMER ELEC
AC DC DC
BAT
AC
ESS
DC
ESS HOT
PRIM 1 X X(1)
PRIM 2 DC2(2)
PRIM 3 DC2(2)
SEC 1 X X(1)
SEC 2 DC2
FCDC1 X
MAIN FLT CTL
COMPUTERS
FCDC2 DC2
RATE GYRO 1 X X(1)
RATE GYRO 2 X X(1)
ACCELRM 1 X X(1) SENSORS
ACCELRM 2 DC2(2)
ACTUATOR 1 SHED
PITCH TRIM ACTUATOR 2 DC2(2)
ACTUATOR 3 DC 2
RUDDER TRIM AACCTTUUAATTOORR 12 DC 2 SHED
RUDDER TRAVEL AACCTTUUAATTOORR 12 DC 2 X
(1) Hot bus supplies, when DC ESS BUS fails.
(2) Normal supply is from DC BUS 2. DC BUS 1 supplies, in case of a DC BUS 2 failure.
BUS EQUIPMENT LIST
Applicable to: ,
L3
NORM EMER ELEC
AC DC DC
BAT
AC
ESS
DC
ESS HOT
PRIM 1 X X(1)
PRIM 2 DC2
PRIM 3 DC2(2)
SEC 1 X X(1)
MAIN FLT CTL
COMPUTERS
SEC 2 DC2(3)X
To be continued on next page
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
FLIGHT CONTROL SYSTEM - ELECTRICAL SUPPLY
A330/A340 FLEET DSC-27-20-50 P 2/2
FCOM 19 AUG 10
Continued from previous page
NORM EMER ELEC
AC DC DC
BAT
AC
ESS
DC
ESS HOT
FCDC1 X
FCDC2 DC2
RATE GYRO 1 X X(1)
RATE GYRO 2 X X(1)
ACCELRM 1 X X(1) SENSORS
ACCELRM 2 DC2
ACTUATOR 1 SHED
PITCH TRIM ACTUATOR 2 DC2
ACTUATOR 3 DC 2
PFTU-RUDDER TRIM AACCTTUUAATTOORR 12 DC 2(4) SSHHEEDD
(1) Hot bus supplies, when DC ESS BUS fails.
(2) Normal supply is from DC BUS 2. DC BUS 1 supplies, in case of a DC BUS 2 failure.
(3) Normal supply is from DC BUS 2. DC ESS BUS supplies, in case of a DC BUS 2 failure.
(4) Normal supply is from DC BUS 2. DC ESS SHED supplies, in case of a DC BUS 2 failure.
In case of a total electrical failure, or a loss of rudder control due to a Flight Control Computer
Failure, the rudder is controlled by the BCM. The BCM has its own independent electrical generator :
The Backup Power Supply (BPS).
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
FLAPS AND SLATS - DESCRIPTION
A330/A340 FLEET DSC-27-30-10 P 1/8
FCOM 19 AUG 10
GENERAL
Applicable to: ALL
Lift augmentation is achieved on each wing by :
‐ 2 flaps surfaces
‐ 7 slats surfaces
‐ 2 ailerons (aileron droop function)
These surfaces are electrically-signalled and hydraulically-operated.
Slats and flaps are selected by the "FLAPS" lever, located on the center pedestal, which has 5
positions.
MAIN COMPONENTS
Applicable to: ALL
Slats and Flaps systems are similar, and consist of :
‐ Two Slats/Flaps Control Computers (SFCC), each containing one flap and one slat channel.
‐ A Power Control Unit (PCU), consisting of 2 independent hydraulic motors coupled to a differential
　
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