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The GW and CG, computed by the FE part, are used :
‐ As backup, in case of a dual FCMC failure.
‐ To trigger the aft CG caution and warning signals (independently of the FCMC).
FE WEIGHT COMPUTATION (BACKUP)
‐ When the aircraft is below 14 625 ft, and 255 kt :
GW=f(α,CAS,N1/EPRactual,CGfromFEpart,altitude)
‐ When the aircraft is above 14 625 ft, or 255 kt :
GW = TOGW – WFU
TOGW : Takeoff Gross Weight
WFU : Weight Fuel Used, acquired from the FADECs.
FE CENTER OF GRAVITY COMPUTATION (BACKUP/AFT CG WARNING)
The CG is computed from the position of the horizontal stabilizer, and is function of the N1/EPR,
Vc, ALT, MACH and GW from FE part.
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT ENVELOPPE
WEIGHT AND CENTER OF GRAVITY COMPUTATION
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A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT ENVELOPPE
AFT CG MONITORING
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AFT CG MONITORING
Applicable to: ALL
The flight envelope only uses its own computed Gross Weight (GW) and Center of Gravity (CG) to
trigger the aft CG signals.
The current CG is compared to the aft CG limit, computed from the GW.
If the CG > CG limit -1 %, an aft CG caution signal is sent to the FCMCs. The target CG is then
shifted forward by 1.5 % (only one time). If the CG becomes higher than the CG limit, the aft CG
warning signal is sent to the FWCs, which trigger a red warning.
Note: AFT CG monitoring is available above 20 000 ft, if the aircraft is in clean configuration with
the speedbrakes retracted.
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT ENVELOPPE
AFT CG MONITORING
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A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT ENVELOPPE
WINDSHEAR DETECTION
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WINDSHEAR DETECTION
Applicable to: ALL
A windshear detection signal is generated whenever the aircraft encounters a windshear and
the predicted energy level falls below a predetermined safe minimum energy threshold (reactive
windshear detection).
Note: The energy threshold is expressed as an angle of attack threshold αo.
The aircraft predicted energy level is α + ▵α where :
• α is the current angle of attack
• ▵α is the equivalent AOA computed from measured vertical drafts and longitudinal
shears.
If α + ▵α > αo the windshear conditions are detected.
The windshear detection function is provided in takeoff and approach phase under the following
conditions :
At takeoff, ‐ from lift off up to 1 300 ft.
‐ At landing from 1 300 ft to 50 ft.
‐ With at least CONF 1 selected.
The warning consists of :
‐ A visual “WINDSHEAR” red message displayed on both PFDs for a minimum of 15 s.
‐ An aural synthetic voice announcing ”WINDSHEAR” three times.
A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
AUTO FLIGHT - FLIGHT ENVELOPPE
WINDSHEAR DETECTION
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FCOM 19 AUG 10
AIRCRAFT SYSTEMS
AUTO FLIGHT - ACARS INTERFACE
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A330/A340 FLIGHT CREW
OPERATING MANUAL
AIRCRAFT SYSTEMS
AUTO FLIGHT - ACARS INTERFACE
PRELIMINARY PAGES - TABLE OF CONTENTS
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DSC-22_45-PLP PRELIMINARY PAGES
TABLE OF CONTENTS......................................................................................................................................1/2
GENERAL............................................................................................................................................................1/8
FLIGHT PLAN INITIALIZATION FUNCTION........................................................................................................1/8
TAKEOFF DATA FUNCTION............................................................................................................................. 3/8
WIND DATA FUNCTION.................................................................................................................................... 4/8
FLIGHT REPORTS............................................................................................................................................. 5/8
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A330/A340机组操作手册 FLIGHT CREW OPERATING MANUAL FCOM 2(71)
