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FLIGHT CONTROL SYSTEM - NORMAL LAW
A318/A319/A320/A321 FLEET DSC-27-20-10-20 P 9/10
FCOM 19 AUG 10
Applicable to: MSN,
HIGH SPEED PROTECTION
The aircraft automatically recovers, following a high speed upset. Depending on the flight
conditions (high acceleration, low pitch attitude), High Speed Protection is activated at/or above
VMO/MMO.
When it is activated, the THS setting is limited between the setting at the aircraft’s entry into this
protection and 11 ° nose-up. Positive spiral static stability is introduced to 0 ° bank angle (instead
of 33 ° in normal law), so that with the sidestick released, the aircraft always returns to a bank
angle of 0 °. The bank angle limit is reduced from 67 °to 45 °.
As the speed increases above VMO/MMO, the sidestick nose-down authority is progressively
reduced, and a permanent nose-up order is applied to aid recovery to normal flight conditions.
High Speed Protection is deactivated, when the aircraft speed decreases below VMO/MMO,
where the usual normal control laws are recovered.
The autopilot disconnects, when High Speed Protection becomes active.
Note: The ECAM displays an “O/SPEED” warning at VMO +4 kt and MMO +0.006.
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 10/10
FCOM 19 AUG 10
Applicable to: ALL
LOW ENERGY WARNING ( IF INSTALLED)
The low energy warning is computed by the FAC (Refer to DSC-22_40-10 GENERAL).
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
FLIGHT CONTROL SYSTEM - NORMAL LAW
A318/A319/A320/A321 FLEET DSC-27-20-10-30 P 1/2
FCOM 19 AUG 10
LATERAL CONTROL
NORMAL LAW
Applicable to: ALL
When the aircraft is on the ground (in “on ground” mode), the sidestick commands the aileron and roll
spoiler surface deflection. The amount of control surface deflection that results from a given amount
of sidestick deflection depends upon aircraft speed. The pedals control rudder deflection through a
direct mechanical linkage.
When the aircraft is in the “in flight” mode, normal law combines control of the ailerons, spoilers
(except N° 1 spoilers), and rudder (for turn coordination) in the sidestick. While the system thereby
gives the pilot control of the roll and heading, it also limits the roll rate and bank angle, coordinates
the turns, and damps the dutch roll.
The roll rate requested by the pilot during flight is proportional to the sidestick deflection, with a
maximum rate of 15 °/s when the sidestick is at the stop.
When the aircraft is in “flare” mode, the lateral control is the same as in “in flight” mode.
BANK ANGLE PROTECTION
Applicable to: ALL
Inside the normal flight envelope, the system maintains positive spiral static stability for bank angles
above 33 °. If the pilot releases the sidestick at a bank angle greater than 33 °, the bank angle
automatically reduces to 33 °. Up to 33 °, the system holds the roll attitude constant when the
sidestick is at neutral. If the pilot holds full lateral sidestick deflection, the bank angle goes to 67 °
(indicated by a pair of green bar lines “=” on the PFD) and no further.
If the angle-of-attack protection or high speed protection is operative, the bank angle goes to 45 °
and no further, if the pilot holds full lateral sidestick deflection. If high speed protection is operative,
the system maintains positive spiral static stability from a bank angle of 0 °, so that with the sidestick
released, the aircraft always returns to a bank angle of 0 °.
When bank angle protection is active, auto trim is inoperative.
If the bank angle exceeds 45 °, the autopilot disconnects and the FD bars disappear. The FD bars
return when the bank angle decreases to less than 40 °.
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
FLIGHT CONTROL SYSTEM - NORMAL LAW
A318/A319/A320/A321 FLEET DSC-27-20-10-30 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-27-20-10-40 P 1/2
FCOM 19 AUG 10
LOAD ALLEVIATION FUNCTION
LOAD ALLEVIATION FUNCTION (LAF)
Applicable to:
The load alleviation function, which operates through the ailerons and spoilers 4 and 5, becomes
active only in turbulence conditions (pilot control authority is not modified), in order to relieve wing
　
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