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with the manually-selected position).
The THS is manually-controlled on ground for the THS setting, before takeoff and in flight,
when in direct law.
‐ Before takeoff, the pilot sets the THS to the angular value, determined as a function of the
aircraft CG, using the CG scale on the wheel. The relationship between the aircraft CG and
the THS setting shown on the trim wheel is only applicable for takeoff. The limits of the THS
normal setting range for takeoff are indicated by a green band on the pitch trim wheel.
‐ In flight, when in direct law, the pilot uses the THS conventionally to fly in trim. In flight, the
aircraft pitch trim setting depends on aircraft CG, weight, altitude and speed. Consequently,
the relation between the aircraft CG, and the THS setting displayed on the pitch trim wheel,
does not apply in flight.
Following nosewheel touchdown, as the pitch attitude becomes less than 2.5 ° for more than
5 s, pitch trim is automatically reset to zero.
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
A318/A319/A320/A321 FLEET DSC-27-20-30 P 4/28
FCOM 19 AUG 10
Note: This function is inoperative, when the green or yellow hydraulic system is not
pressurized.
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
A318/A319/A320/A321 FLEET DSC-27-20-30 P 5/28
FCOM 19 AUG 10
PEDESTAL
Applicable to:
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
A318/A319/A320/A321 FLEET DSC-27-20-30 P 6/28
FCOM 19 AUG 10
(1) RUD TRIM Rotary Switch
Controls the rudder trim actuator, which moves the neutral point of the artificial feel by the
equivalent of one degree of rudder travel per second.
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
A318/A319/A320/A321 FLEET DSC-27-20-30 P 7/28
FCOM 19 AUG 10
Note: The rudder trim rotary switch has no effect, when the autopilot is engaged.
(2) RESET Pushbutton
By pushing the RESET pushbutton, the zero trim position is ordered at 1.5 °/s.
Note: The RESET pushbutton is not active, when the autopilot is engaged.
(3) Position Indicator
Displays the rudder trim direction (L or R) and value (0 to 25 °).
(4) SPEEDBRAKE Lever
The lever controls :
The position ‐ of the speedbrake surfaces.
To set speedbrake surfaces to a required position, the lever has to be pushed down and set
to the required position. A “hardpoint” is provided at “½” SPEEDBRAKE position.
The manual ‐ preselection of the ground spoilers.
To arm the ground spoilers, the lever must be pulled up when in the RET position.
When the lever is armed (or reverse thrust is selected), all spoiler's surfaces will
automatically extend at landing, or in case of a rejected takeoff.
(5) PITCH TRIM Wheel
Both pitch trim wheels provide mechanical control of the THS and have priority over electrical
control. A pilot action on the pitch trim wheel disconnects the autopilot.
Note: Crew action on the pitch trim wheel does not disconnect the ELACs (micro-switches,
actuated by the override mechanism, ensure that the computers remain synchronized
with the manually-selected position).
The THS is manually-controlled on ground for the THS setting, before takeoff and in flight,
when in direct law.
‐ Before takeoff, the pilot sets the THS to the angular value, determined as a function of the
aircraft CG, using the CG scale on the wheel. The relationship between the aircraft CG and
the THS setting shown on the trim wheel is only applicable for takeoff. The limits of the THS
normal setting range for takeoff are indicated by a green band on the pitch trim wheel.
‐ In flight, when in direct law, the pilot uses the THS conventionally to fly in trim. In flight, the
aircraft pitch trim setting depends on aircraft CG, weight, altitude and speed. Consequently,
the relation between the aircraft CG, and the THS setting displayed on the pitch trim wheel,
does not apply in flight.
Following nosewheel touchdown, as the pitch attitude becomes less than 2.5 ° for more than
5 s, pitch trim is automatically reset to zero.
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
FLIGHT CONTROL SYSTEM - CONTROLS AND INDICATORS
A318/A319/A320/A321 FLEET DSC-27-20-30 P 8/28
FCOM 19 AUG 10
Note: This function is inoperative, when the green or yellow hydraulic system is not
　
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