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setting (maximum authorized deflection).
RUDDER TRAVEL LIMITATION
Applicable to:
This function limits rudder deflection is based on speed in order to avoid high structural loads. It is
governed by the following law :
If both FACs lose the rudder travel limitation function, the value of the rudder deflection limit is locked
at the time of the second failure.
When the slats are extended, the FACs automatically set the rudder deflection limit at the low-speed
setting (maximum authorized deflection).
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT AUGMENTATION
FLIGHT ENVELOPE FUNCTION
A318/A319/A320/A321 FLEET DSC-22_40-30 P 1/6
FCOM 19 AUG 10
GENERAL
Applicable to: ALL
As long as one Flight Augmentation Computer (FAC) is valid, it governs the flight envelope function,
the rudder position display, and the rudder trim indication regardless of what the flight crew does with
the FAC pushbutton.
PFD SPEED SCALE MANAGEMENT
Applicable to:
The FAC controls the speed scale on the PFD (Refer to DSC-31-40 ATTITUDE DATA).
When both FACs are operative, FAC1 supplies data to PFD1 and FAC2 supplies it to PFD2.
The FAC computes :
‐ The minimum and maximum speeds :
▪ VSW (stall warning)
▪ VLS
▪ VFE and VFE for the next configuration
▪ VLE
▪ VMO/MMO
‐ The maneuvering speeds :
▪ Green Dot Speed
▪ S speed
▪ F speed
(Refer to PRO-SUP-10 Characteristic Speeds for speed definition).
The FAC also computes the speed trend and displays it as an arrow on the PFD speed scale.
The PFD displays these various speeds as appropriate, and they also go to the FMGC to be used as
limits for various guidance modes.
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT AUGMENTATION
FLIGHT ENVELOPE FUNCTION
A318/A319/A320/A321 FLEET DSC-22_40-30 P 2/6
FCOM 19 AUG 10
Note: The principle of the speed computation is as follows :
‐ First, the FAC computes VS1G (stall speed). From VS1G it computes the Gross Weight
(GW) which is also sent to the Elevator Aileron computers :
▪ When the aircraft is below 14 500 ft and 250 kt, it computes this from current angle of
attack, speed/Mach, altitude, thrust, and CG.
▪ When the aircraft is above 14 500 ft or 250 kt, it computes this out of the GW, which it
has memorized and updated with a fuel consumption model set in the FAC.
‐ Finally the FAC computes the various minimum and maneuvering speeds, Vα prot and
Vsw.
‐ The accuracies of the various minimum and maximum speeds are functions of the
accuracy with which the FAC computes aircraft gross weight. Normal accuracy for VLS in
CONFIG FULL is about ± 3 kt.
PFD SPEED SCALE MANAGEMENT
Applicable to:
,
,
MSN,,,,
The FAC controls the speed scale on the PFD (Refer to DSC-31-40 ATTITUDE DATA).
When both FACs are operative, FAC1 supplies data to PFD1 and FAC2 supplies it to PFD2.
The FAC computes :
‐ The minimum and maximum speeds :
▪ VSW (stall warning)
▪ VLS
▪ VFE and VFE for the next configuration
▪ VLE
▪ VMO/MMO
‐ The maneuvering speeds :
▪ Green Dot Speed
▪ S speed
▪ F speed
(Refer to PRO-SUP-10 Characteristic Speeds for speed definition).
The FAC also computes the speed trend and displays it as an arrow on the PFD speed scale.
The PFD displays these various speeds as appropriate, and they also go to the FMGC to be used as
limits for various guidance modes.
A318/A319/A320/A321 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT AUGMENTATION
FLIGHT ENVELOPE FUNCTION
A318/A319/A320/A321 FLEET DSC-22_40-30 P 3/6
FCOM 19 AUG 10
Note: The FAC computes the operating speeds based on the FMS gross weight. This allows
to have consistent and accurate operating speeds between the PFD and the MCDU. In
parallel, the FAC also computes its own GW and CG, based on aerodynamic data, which
is used by the ELAC and the FMS for gross weight crosscheck (“CHECK GW” MCDU
message), and as a backup for speeds computation in case of dual FMS failure. The
principle of the FAC GW/CG computation based on aerodynamic data is as follows :
‐ First, the FAC computes VS1G (stall speed). From VS1G it computes the FAC gross
weight which is also sent to the ELAC:
• When the aircraft is below 14 500 ft and 250 kt, it computes this from current angle of
attack, speed/Mach, altitude, thrust, and CG.
• When the aircraft is above 14 500 ft or 250 kt, it computes this out of the GW, which it
　
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