-
MCDU 1 through 115VAC ESS SHED BUS 801XP-A

 -
MCDU 2 through 115VAC BUS2 202XP-C

 C. 26VAC Supply
 The 26VAC power supplies:

 -
sensors associated with FAC 1 through 26VAC BUS1 431XP

 -
sensors associated with FAC 2 through 26VAC BUS2 231XP.

 General Architecture of the AFS
 Figure 003

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 AFS - Controls and Indicating Figure 004
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 D. 5VAC Supply A 115VAC/5VAC step-down transformer provides power for the integral lighting and lighting of the LCD display. Potentiometers control the lighting brightness. The 5VAC power which supplies the pushbutton switches is reduced to 3VAC in DIM conditions.
 E. List of the AFS circuit-breakers
 -------------------------------------------------------------------------------PANEL DESIGNATION FIN LOCATION -------------------------------------------------------------------------------
49VU AUTO FLT/FCU/1 9CA1 121VU AUTO FLT/FCU/2 9CA2 49VU AUTO FLT/FMGC/1 10CA1 121VU AUTO FLT/FMGC/2 10CA2 49VU AUTO FLT/MCDU/1 11CA1 121VU AUTO FLT/MCDU/2 11CA2 121VU AUTO FLT/STICK/LOCK 13CA 121VU AUTO FLT/RUDDER/ARTF/FEEL 14CA 49VU AUTO FLT/FAC1/28VDC 5CC1 121VU AUTO FLT/FAC2/28VDC 5CC2 49VU AUTO FLT/FAC1/26VAC 14CC1 121VU AUTO FLT/FAC2/26VAC 14CC2
 5. Interface
_________
 A. Interconnection with Peripherals The interconnection between the FACs, the FMGCs and the peripherals makes sure that a single failure of a peripheral has no effect on the AFS/FMS functions.
 B. Interconnection with Flight Controls
 (1)
 FMGC

 (a)
 Pitch and roll axes The FMGC 1 and 2 send autopilot orders through output buses to the ELACs. The ELACs then transmit deflection commands to the surfaces on the pitch and roll axes. The ELACs use the buses from the FMGC 1 or FMGC 2 according to the autopilot engaged (AP1 has priority when both APs are engaged in ILS approach).

 (b)
 Yaw axis The FMGC 1 and 2 send autopilot orders to the FACs which control both yaw damper servo actuators (transient commands) and rudder trim actuator (permanent commands). The FACs use the same priority logic as the ELACs.

 (2)
 FAC The FACs send yaw damper commands to two hydraulic servo actuators (one per FAC). They also send commands to four electrical actuators for rudder trim and rudder travel limiting (one per FAC and per function). All the servomotors operate using the automatic changeover.

 C. Interconnection with Engine Controls (Ref. Fig. 005) The FMGCs compute and transmit data to the engines through the FCU, EIU and ECU/EEC using ARINC Specification 429 bus. To consolidate engine data, the priority FMGC compares the output parameters from the FCU with its own available data by means of associated logic. Each FMGC receives four ARINC buses for computation : two buses associated with the own side, two others associated with the opposite side.
 6. Component Description
_____________________ The AFS components (FAC,FCU,MCDU,FMGC) are described in the following topics (ATA REF):
 -FAC : 22-66-00
 -FCU : 22-81-00
 -MCDU: 22-82-00
 -FMGC: 22-83-00

 Interconnection Between the AFS and the Engines Figure 005
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 7. Operation
_________
 A. Flight Augmentation (FAC)
 (1) General
 (a) Functions
 The FAC performs the functions given below:

 -yaw damper
 -
rudder trim (manual and automatic)

 -
rudder travel limiting

 -monitoring of the flight envelope and computations of maneuvering speed
 -achievement of yaw autopilot order using power loops of yaw
 damper and rudder trim. In addition the FAC 1 performs the BITE function of the AFS.
 (b) Operating principles The FAC is a dual-dual type system for yaw damper, rudder trim and rudder travel functions. FACs 1 and 2 can be engaged at the same time through FAC 1 and FAC 2 pushbutton switches on the overhead panel. Only one system is active at a time : FAC 1 has priority, FAC 2 being in standby and synchronized on FAC 1 orders. An automatic changeover occurs on FAC 2 in case of disengagement or failure of FAC 1. Partial changeover function per function (yaw damper, rudder trim, RTL) is possible. When the aircraft electrical network is energized, the functions that follow will operate independently of the FAC pushbutton switches:
 -monitoring of the flight envelope

 -computation of maneuvering speed.
　
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