1EFF : ALL 1 22-32-00Page 12 1 1 Feb 01/98 1 1 1CES 1 The figures which show the display of AP/FD-A/THR messages according to the various typical flight cases are given in 22-10-00 AP/FD.

 (4) Principle of messages displayed All the messages are generated in the FMGCs and sent to the DMCs through discrete data, by the FCU on ARINC 429 bus. The 3 DMCs acquire these discrete data to generate specific codes which correspond to the messages to be displayed on the PFDs.
 1EFF : ALL 1 22-32-00Page 13 1 1 Feb 01/98 1 1 1CES 1 FLIGHT AUGMENTATION (FAC) - DESCRIPTION AND OPERATION

_____________________________________________________
 1. General
_______
 The Flight Augmentation Computer (FAC) fulfills the functions given below:

 A. Yaw Damper
 The yaw damper function ensures:

 -
In manual control, the accomplishment of the yaw orders from the elevator aileron computer (ELAC) (stabilization and manual turn coordination). It also provides a yaw-damping degraded law in the event of ELAC failure (alternate law).

 -
In automatic control, the accomplishment of the autopilot orders from the Flight Management and Guidance Computer (FMGC) for:

R  . Turn coordination (ILS approach mode and roll out). . Guidance (align and roll out). It also ensures in automatic flight: . Engine failure recovery. . Yaw stability.

R  . Turn coordination (cruise).

 B. Rudder Trim
 The rudder trim function ensures:

 -
In manual control: . The accomplishment of the pilot trim orders from the manual trim control (control and reset)

 -
In automatic control: . The accomplishment of the autopilot orders (autotrim on the yaw axis) . The generation and the accomplishment of the engine failure recovery function.

 C. Rudder Travel Limiting
 The rudder travel limiting function ensures:

 -
The limitation of the rudder travel as a function of a predetermined law

 -
The return to low speed limitation in case of loss of function as soon as the slats are extended.

 D. Calculation of Characteristic Speeds and Protection of Flight Envelope The FAC generates, independently of the engage status of the pushbutton switches, different functions necessary to:
 -
The control of the speed scale on the PFDs

 -
The adaptation of gains for the FMGC and ELAC

 -
The distribution of signals necessary to the FMGC control laws

 -
The flight envelope protection in automatic flight (speed limits for

 the FMGC, alpha floor for the autothrust) R - The display of the rudder trim order and the rudder travel limiter R position if available
 1EFF : ALL 1 22-60-00Page 1 1 1 Feb 01/03 1 1 1CES 1

 -
The windshear detection (option activated by pin program)

 -
The low energy detection (option activated by pin program).

 E. Maintenance The Centralized Fault-Display System (CFDS) has two modes of operation (Ref. 22-90-00):
 (1)
 Normal mode In this mode, the system FIDS (BITE concentrator) stores all the analysis results of the various BITE. It may perform a crosscheck to determine the faulty LRU. It transmits the reference of the LRUs which have failed during the current flight to the Centralized Fault-Display Interface-unit (CFDIU).

 (2)
 Menu mode
 In this mode:

 -It is possible to activate the various AFS tests and to display maintenance snapshots.
 2. Component Location
__________________
 **ON A/C 001-049, 051-099, 101-149, 201-299, 301-399,
 (Ref. Fig. 001)
R **ON A/C 151-199, 401-499,
 (Ref. Fig. 001A)
 **ON A/C ALL
 (Ref. Fig. 002)
 -------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF.
 -------------------------------------------------------------------------------1CC1 FAC-1 83VU 127 824 22-66-34 1CC2 FAC-2 84VU 128 824 22-66-34 8CC P/BSW-RUD TRIM/RESET 110VU 210 831 22-62-12 9CC CTL SW-RUDDER TRIM 110VU 210 831 22-62-11 12CC1 P/BSW-FLT CTL/FAC1 23VU 211 831 22-65-00 12CC2 P/BSW-FLT CTL/FAC2 24VU 212 831 22-65-00 17CC IND-RUDDER TRIM 110VU 210 831 22-62-21
 1EFF : ALL 1 22-60-00Page 2 1 1 Aug 01/05 1 1 1CES 1

 FAC - Component Location (Cockpit)
 Figure 001

 FAC - Component Location (Cockpit)
 Figure 001A

 FAC - Component Location (Electronics Rack) Figure 002
 1EFF : 1 1R 1CES  ALL  1 11 1 22-60-00 Page 5 Feb 01/00

 3. System Description
　
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