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OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
GENERAL - ARCHITECTURE
A318/A319/A320/A321 FLEET DSC-27-10-20 P 14/22
FCOM 19 AUG 10
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 both 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 one engine (the other
thrust lever remains 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 one
engine (the other thrust lever remains at idle).
Note: The spoiler roll function is inhibited when spoilers are used for the ground spoiler
function.
PARTIAL EXTENSION
The ground spoilers partially extend (10 °) when reverse is selected on at least one engine
(other engine at idle), and one main landing gear strut is compressed. This partial extension,
by decreasing the lift, eases the compression of the second main landing gear strut, and
consequently leads to full ground spoiler extension.
RETRACTION
The ground spoilers retract :
• After landing, or after a rejected takeoff, when the ground spoilers are disarmed.
Note: If ground spoilers are not armed, they extend at the reverse selection and retract
when idle is selected.
• During a touch and go, when at least one thrust lever is advanced above 20 °.
Note: After an aircraft bounce, the ground spoilers remain extended with the thrust levers at
idle.
L3 The landing gear touchdown condition is triggered for both main landing gear, either when
their wheel speed is greater than 72 kt, or when their landing gear struts are, confirmed to be
compressed by the radio altitude (RA < 6 ft).
The thrust levers are considered to be at idle when they are :
• Below 4 °, when the RA is above 10 ft,
• Below 15 °, when the RA is below 10 ft.
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
GENERAL - ARCHITECTURE
A318/A319/A320/A321 FLEET DSC-27-10-20 P 15/22
FCOM 19 AUG 10
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
GENERAL - ARCHITECTURE
A318/A319/A320/A321 FLEET DSC-27-10-20 P 16/22
FCOM 19 AUG 10
Applicable to:
ROLL CONTROL - SCHEMATIC
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
GENERAL - ARCHITECTURE
A318/A319/A320/A321 FLEET DSC-27-10-20 P 17/22
FCOM 19 AUG 10
Applicable to:
,
,
MSN,,,,
ROLL CONTROL - SCHEMATIC
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
GENERAL - ARCHITECTURE
A318/A319/A320/A321 FLEET DSC-27-10-20 P 18/22
FCOM 19 AUG 10
YAW CONTROL
Applicable to: ALL
GENERAL
One rudder surface controls yaw.
Applicable to: ALL
ELECTRICAL RUDDER CONTROL
The yaw damping and turn coordination functions are automatic.
The ELACs compute yaw orders for coordinating turns and damping yaw oscillations, and transmit
them to the FACs.
Applicable to: ALL
MECHANICAL RUDDER CONTROL
The pilots can use conventional rudder pedals to control the rudder.
Applicable to: ALL
RUDDER ACTUATION
Three independent hydraulic servojacks, operating in parallel, actuate the rudder. In automatic
operation (yaw damping, turn coordination) a green servo actuator drives all three servojacks. A
yellow servo actuator remains synchronized and takes over if there is a failure.
There is no feedback to the rudder pedals from the yaw damping and turn coordination functions.
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
GENERAL - ARCHITECTURE
A318/A319/A320/A321 FLEET DSC-27-10-20 P 19/22
FCOM 19 AUG 10
Applicable to:
, ,
MSN,,,,
RUDDER TRAVEL LIMIT
The rudder and pedal deflection limit depends on speed.
Each channel of the limiter is controlled and monitored by its associated FAC. If both FACs fail,
maximum deflection is available, when the slats are extended.
Applicable to:
RUDDER TRAVEL LIMIT
The rudder and pedal deflection limit depends on speed.
Each channel of the limiter is controlled and monitored by its associated FAC. If both FACs fail,
　
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