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In case all PRIM computers are lost, each SEC is its own master and controls its associated
servoloop in direct law.
A single SEC can provide complete aircraft control in direct law.
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
GENERAL - GENERAL
A330/A340 FLEET DSC-27-10-10 P 7/10
FCOM 19 AUG 10
Applicable to:
2 SEC computers
(Flight Control Secondary Computer – FCSC), each of which is used for :
Direct control ‐ laws, including yaw damper function.
‐ Rudder trim, rudder travel limit, and pedal travel limit.
One computer of any type is capable of controlling the aircraft and of assuring safe flight and
landing.
In normal operation, one PRIM computer is declared to be the master (P1). It processes the orders
and sends them to the other computers (P1 / P2 / P3 / S1 / S2), which will then execute them on
their related servo-control.
If one computer is unable to execute the orders sent by the master, another computer executes
the task of the affected computer (except for spoiler control).
If the master computer (P1) cannot be the master, then P2 (or P3, if P2 is not available) becomes
the master.
Note: When the green hydraulic system is lost, P2 replaces P1 as the master computer.
In case all PRIM computers are lost, each SEC is its own master and controls its associated
servoloop in direct law.
A single SEC can provide complete aircraft control in direct law.
Applicable to: ALL
2 FCDC computers
(Flight Control Data Concentrators) acquire data from the PRIMs and SECs and send this data to
EIS and CMC.
Applicable to: ,
1 backup control module (BCM) computer
The BCM computer provides yaw damping, and direct rudder command with pedals, via an
independent unit, in case of :
‐ Total electrical failure, or
‐ Loss of rudder control due to a Flight Control Computer (PRIM and SEC) failure.
It includes :
‐ Its own electrical generator, referred to as the Backup Power Supply (BPS), which is supplied
by the B or Y hydraulic system
Its own sensors (gyrometers ‐ and pedals deflection)
‐ Control of the B and Y hydraulic actuators.
When activated, as in yaw alternate law, there is no turn coordination.
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
GENERAL - GENERAL
A330/A340 FLEET DSC-27-10-10 P 8/10
FCOM 19 AUG 10
Applicable to:
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
GENERAL - GENERAL
A330/A340 FLEET DSC-27-10-10 P 9/10
FCOM 19 AUG 10
Applicable to: ,
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
GENERAL - GENERAL
Intentionally left blank
A330/A340 FLEET DSC-27-10-10 P 10/10
FCOM 19 AUG 10
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
GENERAL - ARCHITECTURE
A330/A340 FLEET DSC-27-10-20 P 1/22
FCOM 19 AUG 10
GENERAL ARCHITECTURE
Applicable to:
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
GENERAL - ARCHITECTURE
A330/A340 FLEET DSC-27-10-20 P 2/22
FCOM 19 AUG 10
GENERAL ARCHITECTURE
Applicable to: ,
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
FLIGHT CONTROLS
GENERAL - ARCHITECTURE
A330/A340 FLEET DSC-27-10-20 P 3/22
FCOM 19 AUG 10
PITCH CONTROL
Applicable to: ALL
GENERAL
Two elevators and the trimmable horizontal stabilizer (THS) control the aircraft in pitch. The
maximum elevator deflection is 30 ° nose up and 15 ° nose down. The maximum THS deflection is
14 ° nose up and 2 ° nose down.
ELECTRICAL CONTROL
In normal operations, the PRIM 1 controls the elevators ‐ and the horizontal stabilizer, and the
green hydraulic jacks drive the left and right elevator surfaces.
The THS is driven by N° 1 of three electric motors.
‐ If a failure occurs in PRIM 1 or the associated hydraulic systems or hydraulic jacks, the system
shifts pitch control to PRIM 2. PRIM 2 then controls the elevators via the blue and yellow
hydraulic jacks and controls the THS via the N° 2 electric motor.
‐ If neither PRIM 1 nor PRIM 2 is available, the system shifts pitch control either to
SEC 1 for elevator control, and to PRIM 3 for THS control via the N° 3 electric motor.
In case of 3 PRIM failure the SEC 1 controls the elevator.
Electrical control of THS is lost. THS actuation is still available through manual pitch trim wheel
control.
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
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A330/A340机组操作手册 FLIGHT CREW OPERATING MANUAL FCOM 2(135)
