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A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
FLIGHT CONTROL SYSTEM - RECONFIGURATION CONTROL LAWS
A318/A319/A320/A321 FLEET DSC-27-20-20 P 5/10
FCOM 19 AUG 10
LATERAL CONTROL
When the aircraft flying in pitch alternate law, lateral control follows the roll direct law associated
with yaw alternate or mechanical.
ROLL DIRECT LAW
Refer to DSC-27-20-20 DIRECT LAW.
YAW ALTERNATE LAW
Only the yaw damping function is available. Damper authority is limited to ± 5 ° of rudder
deflection.
REDUCED PROTECTIONS
LOAD FACTOR LIMITATION
The load factor limitation is similar to that under normal law.
PITCH ATTITUDE PROTECTION
There is no pitch attitude protection. Amber Xs replace the green double bars “=” on the PFD.
LOW SPEED STABILITY
An artificial low speed stability replaces the normal angle-of-attack protection. It is available
for all slat/flap configurations, and the low speed stability is active from about 5 kt up to about
10 kt above stall warning speed, depending on the aircraft’s gross weight and slats/flaps
configuration.
A gentle progressive nose down signal is introduced, which tends to keep the speed from falling
below these values.
The system also injects bank-angle compensation, so that operation effectively maintains a
constant angle of attack.
In addition, audio stall warnings (crickets + “STALL” synthetic voice message) is activated at an
appropriate margin from the stall condition.
The PFD speed scale is modified to show a black/red barber pole below the stall warning.
The α floor protection is inoperative.
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
FLIGHT CONTROL SYSTEM - RECONFIGURATION CONTROL LAWS
A318/A319/A320/A321 FLEET DSC-27-20-20 P 6/10
FCOM 19 AUG 10
HIGH SPEED STABILITY
Above VMO or MMO, a nose up demand is introduced to avoid an excessive increase in speed.
The pilot can override this demand.
In addition, the aural overspeed warning (VMO + 4 or MMO + 0.006) remains available.
BANK ANGLE PROTECTION
Not provided.
Note: The AP will disconnect, if speed exceeds VMO/MMO, or if the bank angle exceeds
45 °.
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
FLIGHT CONTROL SYSTEM - RECONFIGURATION CONTROL LAWS
A318/A319/A320/A321 FLEET DSC-27-20-20 P 7/10
FCOM 19 AUG 10
ALTERNATE LAW WITHOUT REDUCED PROTECTION
Applicable to: ALL
This is identical to alternate law except that it does not include the low-speed stability or the
high-speed stability. It includes only the load factor limitation.
DIRECT LAW
Applicable to: ALL
PITCH CONTROL
The pitch direct law is a direct stick-to-elevator relationship (elevator deflection is proportional to
stick deflection).
In all configurations the maximum elevator deflection varies as a function of CG.
It is a compromise between adequate controllability with the CG forward, and not-too-sensitive
control with the CG aft.
There is no automatic trim : the pilot must trim manually.
The PFD displays in amber the message “USE MAN PITCH TRIM”.
No protections are operative.
The α floor function is inoperative.
Overspeed and stall warnings are available as for alternate law.
LATERAL CONTROL
When flying in “direct law”, the roll direct law associated with mechanical yaw control governs
lateral control.
ROLL DIRECT LAW
The roll direct law is a direct stick-to-surface-position relationship. System gains are set
automatically to correspond to slat/flap configuration.
With the aircraft in the clean configuration, the maximum roll rate is about 30 °/s.
With slats extended, it is about 25 °/s.
To limit roll rate, the roll direct law uses only ailerons and spoilers N° 4 and 5.
If spoiler N° 4 has failed, spoiler N° 3 replaces it.
If the ailerons have failed, all roll spoilers become active.
YAW MECHANICAL CONTROL
The pilot controls yaw with the rudder pedals.
The yaw damping and turn coordination functions are lost.
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
FLIGHT CONTROL SYSTEM - RECONFIGURATION CONTROL LAWS
A318/A319/A320/A321 FLEET DSC-27-20-20 P 8/10
FCOM 19 AUG 10
ABNORMAL ATTITUDE LAWS
Applicable to:
The system applies an abnormal-attitude law in pitch and roll, if the aircraft exceeds any of these
limits in flight :
Pitch attitude > 50 ‐ ° nose up or 30 ° nose down
　
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