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ARMING
The pilot arms the ground spoiler function by pulling the speedbrake control lever up into the
armed position.
FULL EXTENSION - REJECTED TAKEOFF PHASE
�� If the ground spoilers are armed and the speed exceeds 72 kt the ground spoilers will
automatically extend as soon as all thrust levers are set to idle.
�� If the ground spoilers are not armed and the speed exceeds 72 kt the ground spoilers
will automatically extend as soon as reverse is selected on at least one engine
(remaining engine at idle).
FULL EXTENSION - LANDING PHASE
�� If the ground spoilers are armed and all thrust levers are at idle the ground spoilers
will automatically extend as soon as both main landing gears have touched down.
�� If the ground spoilers are not armed and both main landing gears have touched down
the ground spoilers will automatically extend as soon as reverse is selected on at
least one engine (remaining engine at idle).
�� If the speedbrakes are not retracted and all thrust levers are at idle the ground
spoilers will automatically extend as soon as both main landing gears have touched
down.
Note: The spoiler roll function is inhibited when spoilers are used for the ground spoiler
function.
PARTIAL EXTENSION
The ground spoilers partially extend when reverse is selected on at least one engine (other
engine at idle) and one main landing gear is compressed.
This partial extension, by decreasing the lift, will ease the compression of the second main
landing gear, and consequently will lead to the normal ground spoiler extension.
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
GENERAL - ARCHITECTURE
A330/A340 FLEET DSC-27-10-20 P 12/22
FCOM 19 AUG 10
RETRACTION
The ground spoilers retract when :
‐ One thrust lever is above idle, or
‐ All thrust levers are at forward idle, and the speedbrake control lever is pushed down.
L3 (*) Condition on wheel speed is inhibited after GND/FLT transition.
This condition is rearmed if wheel rotation stops.
As a result, after an aircraft bounce (aircraft airborne), if the ground spoilers are extended:
‐ The ground spoilers remain extended, with the thrust levers at idle
‐ The ground spoilers retract, if thrust is increased above idle (go-around), and extend
again after the next touchdown.
The thrust levers are considered to be at idle when they are :
• Below 4.7 °, when the RA is above 6 ft,
• Below 32 °, when the RA is below 6 ft.
L1 Surfaces partially/fully extend to :
• 14 °/35 ° for spoiler 1,
• 20 °/50 ° for spoilers 2 to 6.
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
GENERAL - ARCHITECTURE
A330/A340 FLEET DSC-27-10-20 P 13/22
FCOM 19 AUG 10
Applicable to: ALL
ROLL CONTROL - SCHEMATIC
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
GENERAL - ARCHITECTURE
A330/A340 FLEET DSC-27-10-20 P 14/22
FCOM 19 AUG 10
YAW CONTROL
Applicable to:
GENERAL
Yaw control is achieved by one rudder surface (rudder deflection ± 31.6 °).
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
GENERAL - ARCHITECTURE
A330/A340 FLEET DSC-27-10-20 P 15/22
FCOM 19 AUG 10
Applicable to: ,
GENERAL
Yaw control is achieved by one rudder surface (rudder deflection ± 35 °).
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
GENERAL - ARCHITECTURE
A330/A340 FLEET DSC-27-10-20 P 16/22
FCOM 19 AUG 10
Applicable to:
GENERAL
Yaw control is achieved by one rudder surface (rudder deflection ± 31.6 °).
Applicable to:
ELECTRICAL RUDDER CONTROL
In flight, yaw damping and turn coordination functions are automatic, and are controlled by the
PRIMs and SECs. (Refer to DSC-27-10-20-D YAW CONTROL - SCHEMATIC).
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
GENERAL - ARCHITECTURE
A330/A340 FLEET DSC-27-10-20 P 17/22
FCOM 19 AUG 10
Applicable to: ,
ELECTRICAL RUDDER CONTROL
In normal operation, PRIM 1 controls the green hydraulic ‐ jack, PRIM 2 controls the blue
hydraulic jack, and PRIM 3 controls the yellow hydraulic jack.
‐ If all the 3 PRIMs 1 fail, SEC 1 controls the green hydraulic jack.
‐ In case of a total electrical failure, or loss of rudder control due to flight control computers
failure, the Backup Control Module (BCM) controls the yellow hydraulic jack, or the blue
hydraulic jack, if the yellow hydraulic jack is not available.
　
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