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OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
FLIGHT CONTROL SYSTEM - NORMAL LAW
A330/A340 FLEET DSC-27-20-10-40 P 1/2
FCOM 19 AUG 10
MANEUVER LOAD ALLEVIATION (MLA)
MANEUVER LOAD ALLEVATION (MLA)
Applicable to: ALL
The purpose of MLA is to redistribute the lift over the wing to relieve structural loads on the outer
wing surfaces (bending moment).
The demanded load factor is maintained.
MLA utilises spoilers 4, 5, and 6 and the ailerons.
The MLA becomes active when the sidestick is pulled more than 8 °, and the load factor is more than
2 g, in which case :
‐ The ailerons are symmetrically-deflected upwards :
• Maximum of11 ° added to roll demand, if any.
‐ Spoilers 4, 5, 6 are symmetrically-deflected :
• Maximum of9 ° is added to roll demand, if any.
• Deflection is proportional to load factor, in excess of 2 g.
An elevator demand is simultaneously applied to compensate for ‐ the pitching moment induced by
spoilers and ailerons.
The load alleviation is only available, when :
‐ The aircraft speed is above 250 kt.
‐ The FLAPS lever is in the 0 position.
‐ In normal or alternate law flight mode.
The MLA has priority over the speedbrakes.
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
FLIGHT CONTROL SYSTEM - NORMAL LAW
Intentionally left blank
A330/A340 FLEET DSC-27-20-10-40 P 2/2
FCOM 19 AUG 10
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
FLIGHT CONTROL SYSTEM - NORMAL LAW
A330/A340 FLEET DSC-27-20-10-60 P 1/2
FCOM 19 AUG 10
TURBULENCE DAMPING FUNCTION
TURBULENCE DAMPING FUNCTION
Applicable to: ALL
The purpose of the turbulence damping function is to damp the structural modes induced by
atmosphere turbulence.
The function uses the Nz accelerometer and two dedicated Ny accelerometers. The PRIMs compute
a turbulence damping command, which is added to the normal law command for the elevator and the
yaw damper.
This function is automatically monitored and becomes inoperative for the remainder of the flight,
when a failure is detected. In addition, it may be manually inhibited by switching off the TURB DAMP
pushbutton on the overhead panel, when it is considered that comfort is degraded instead of being
improved, and no failure is detected.
It is only available if the following conditions are met :
‐ Aircraft in flight.
‐ Aircraft speed greater than 200 kt.
‐ Autopilot engaged or normal law active.
‐ Aircraft within the normal flight envelope.
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
FLIGHT CONTROL SYSTEM - NORMAL LAW
Intentionally left blank
A330/A340 FLEET DSC-27-20-10-60 P 2/2
FCOM 19 AUG 10
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
FLIGHT CONTROL SYSTEM - RECONFIGURATION CONTROL LAWS
A330/A340 FLEET DSC-27-20-20-10 P 1/2
FCOM 19 AUG 10
GENERAL
GENERAL
Applicable to: ALL
Depending on the type of failures affecting the flight control system, or its peripherals, there are 3
possible reconfiguration levels :
‐ Alternate law (ALT 1 or ALT 2)
‐ Direct law, or
‐ Mechanical.
(*) Only in case the AOA, of the remaining ADRs, disagrees with the AOA (as computed by the
PRIM's).
(1) Protection is totally lost, in case of VS1g computation failure (loss of weight, or slat/flap
position).
(2) Protection is lost, in case of a triple ADR failure (or ADR DISAGREE).
(3) Bank angle limitation remains effective in ALT 1, which uses roll normal.
However, since ALT 1 is generally an unprotected law, all protection marks on the PFD are in
amber for simplicity.
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
FLIGHT CONTROL SYSTEM - RECONFIGURATION CONTROL LAWS
A330/A340 FLEET DSC-27-20-20-10 P 2/2
FCOM 19 AUG 10
(4) When both elevators have failed, only pitch mechanical backup is available, by using the
manual pitch trim (THS). “MAN PITCH TRIM ONLY” is displayed in red on the PFDs.
Note: 1. In case of dual RA failure, flare law is introduced when the landing gear is extended and
both autopilots are disengaged. The specific normal law pitch down effect at 50 ft no
longer applies.
2. A jerk may be felt, in the case of flight control computers reconfiguration (due to hydraulic
failure, computer failure, electrical transient...).
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
FLIGHT CONTROL SYSTEM - RECONFIGURATION CONTROL LAWS
　
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