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maximum deflection is available, when the slats are extended.
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
GENERAL - ARCHITECTURE
A318/A319/A320/A321 FLEET DSC-27-10-20 P 20/22
FCOM 19 AUG 10
Applicable to:
, ,
MSN,,,,
RUDDER TRIM
The two electric motors that position the artificial feel unit also trim the rudder. In normal operation,
motor N° 1 (controlled by FAC1), drives the trim, and FAC2 with motor N° 2 remains synchronized
as a backup.
In manual flight, the pilot can apply rudder trim with the rotary RUD TRIM switch on the pedestal.
‐ Maximum deflection is ± 20 °.
‐ Rudder trim speed is one degree per second.
‐ In addition to limitation by the TLU, if rudder trim is applied, maximum rudder deflection may be
reduced in the opposite direction.
The pilot can use a button on the RUD TRIM panel to reset the rudder trim to zero.
Note: With the autopilot engaged, the FMGC computes the rudder trim orders. The rudder trim
rotary switch and the rudder trim reset pushbutton are not active.
Applicable to:
RUDDER TRIM
The two electric motors that position the artificial feel unit also trim the rudder. In normal operation,
motor N° 1 (controlled by FAC1), drives the trim, and FAC2 with motor N° 2 remains synchronized
as a backup.
In manual flight, the pilot can apply rudder trim with the rotary RUD TRIM switch on the pedestal.
‐ Maximum deflection is ± 25 °.
‐ Rudder trim speed is one degree per second.
‐ In addition to limitation by the TLU, if rudder trim is applied, maximum rudder deflection may be
reduced in the opposite direction.
The pilot can use a button on the RUD TRIM panel to reset the rudder trim to zero.
Note: With the autopilot engaged, the FMGC computes the rudder trim orders. The rudder trim
rotary switch and the rudder trim reset pushbutton are not active.
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
GENERAL - ARCHITECTURE
A318/A319/A320/A321 FLEET DSC-27-10-20 P 21/22
FCOM 19 AUG 10
Applicable to: ALL
SCHEMATIC
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
GENERAL - ARCHITECTURE
Intentionally left blank
A318/A319/A320/A321 FLEET DSC-27-10-20 P 22/22
FCOM 19 AUG 10
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
FLIGHT CONTROL SYSTEM - NORMAL LAW
A318/A319/A320/A321 FLEET DSC-27-20-10-10 P 1/2
FCOM 19 AUG 10
GENERAL
GENERAL
Applicable to: ALL
Flight control normal law covers :
‐ three-axis control
‐ flight envelope protection
‐ alleviation of maneuver loads
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
FLIGHT CONTROL SYSTEM - NORMAL LAW
Intentionally left blank
A318/A319/A320/A321 FLEET DSC-27-20-10-10 P 2/2
FCOM 19 AUG 10
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
FLIGHT CONTROL SYSTEM - NORMAL LAW
A318/A319/A320/A321 FLEET DSC-27-20-10-20 P 1/10
FCOM 19 AUG 10
PITCH CONTROL
GROUND MODE
Applicable to:
Ground mode is active when the aircraft is on the ground. It is a direct relationship between sidestick
deflection and elevator deflection, without auto trim.
It automatically sets the trimmable horizontal stabilizer (THS) at 0 ° (inside the green band).
A setting that the pilot enters manually to adjust for CG has priority for takeoff.
When the aircraft reaches 70 kt during the takeoff roll, the system reduces the maximum up elevator
deflection from 30 ° to 20 °, and the aircraft performs the rotation maneuver in direct law.
As soon as the aircraft becomes airborne, the system blends in the flight mode.
The reverse process occurs after touchdown.
GROUND MODE
Applicable to:
, ,
MSN,,,,
Ground mode is active when the aircraft is on the ground. It is a direct relationship between sidestick
deflection and elevator deflection, without auto trim.
It automatically sets the trimmable horizontal stabilizer (THS) at 0 ° (inside the green band).
If the pitch attitude on ground exceeds 2.5 °, the automatic THS reset to zero stops and remains
frozen.
A setting that the pilot enters manually to adjust for CG has priority for takeoff.
When the aircraft reaches 70 kt during the takeoff roll, the system reduces the maximum up elevator
deflection from 30 ° to 20 °, and the aircraft performs the rotation maneuver in direct law.
　
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