AFS/EFCS Interface
Figure 007
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1
(2) Rudder Control (Ref. Fig. 008) Each FAC receives two deflection commands from each FMGC for rudder control
-Aileron deflection command: DELTA P AIL (label 310) This command is used for turn coordination and is carried out by the YAW DAMPER function (Ref. 22-63-00) in cruise. It is also used for rudder autotrim by the RUDDER TRIM function (Ref. 22-62-00).
-Guidance command: DELTA R (label 312) This command is used by the YAW DAMPER function for yaw axis stabilization in automatic landing.
Acknowledgement of these command signals by the FACs is a function of:
-AP engagement (wired discretes, 2 per computer in command and monitoring channels)
-
monitoring of labels of deflection commands DELTA P AIL and DELTA
R. FAC 1 has priority at engagement of either AP (CHANGE OVER logic unchanged). When both APs are engaged, FMGC1 commands have priority.
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Rudder Control
Figure 008
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1R **ON A/C 001-049, 051-099, 101-149, 151-199, 201-299, 401-499,
(3) Pitch and Aileron Control (Ref. Fig. 009, 010) Each ELAC receives two deflection commands from each FMGC:
-Elevator deflection command: DELTA Q (label 314) This command is used for elevator and Trimmable Horizontal Stabilizer (THS) control.
-Aileron deflection command: DELTA P AIL (label 310). The ELAC limits these commands:
-
DELTA Q command: load factor limit between 0.4 g and 1.5 g. This limit is a function of VC, Mach, THS position and load factor.
-
DELTA P command : roll attitude limit equal to plus or minus 60 deg and rolling speed limit equal to plus or minus 10 deg (in landing configuration, this limit is equal to plus or minus 20 deg/s). These limits are a function of Vc.
FMGC command acknowledge logic is with respect to AP engagement wired discretes (2 discretes per AP: command and monitoring), status matrix monitoring of these labels, and concordance between AP engagement wired discretes and boolean information. In answer, each ELAC generates two ELAC AP DISC discretes (control and monitoring) to command AP disconnection when one of the following conditions is present:
-
loss of computation channel validity (comparators)
-
loss of power loop validity . theta, phi, Vc, Mach and alpha values out of limits . incidence protection active . speed protection active
-controls used (side stick controller or pitch trim control wheel).
The AP can be engaged whatever the type of the EFCS control laws:
normal, alternate, direct.
In approach phase, upon loss of both radio altimeters, the ELACs
inhibit AP engagement with the direct law and in landing gear
extended configuration.
The AP disconnects when it receives at least one disconnection
command (control and monitoring) from the 2 ELACs.
A disconnection command from one ELAC only leads to a landing
capability reduction.
An ELAC priority logic exists for control surface control.
This logic is unchanged with AP engaged :
-
ELAC 2 has priority for elevator and THS control
-
ELAC 1 has priority for aileron control.
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Pitch Control
Figure 009
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Aileron Control
Figure 010
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**ON A/C 301-399,
(3) Pitch and Aileron Control (Ref. Fig. 009, 010) Each ELAC receives two deflection commands from each FMGC:
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