R Layout of the AFS Components Figure 001
1EFF : 1 1 1CES ALL 1 111 22-00-00 Page 3 Aug 01/05
R Location of the AFS Computers Figure 002
1EFF : 1 1 1CES ALL 1 111 22-00-00 Page 4 Aug 01/05
-------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. -------------------------------------------------------------------------------
R 3CC1 SERVO ACTR-YAW DAMPER, 1
R 3CC2 SERVO ACTR-YAW DAMPER, 2
R 4CC LIMITATION UNIT-RUDDER TRAVEL
R 10CC ACTUATOR-RUDDER TRIM
R 7CA1 P/BSW-A/THR INST DISC, CAPT
R 7CA2 P/BSW-A/THR INST DISC, F/O
R 12CC1 P/BSW-FLT CTL/FAC1
R 12CC2 P/BSW-FLT CTL/FAC2
R 47CE1 RELAY-TAKEOVER & PRIORITY 1
R 47CE2 RELAY-TAKEOVER & PRIORITY 2
R **ON A/C ALL
3. System Description__________________
(Ref. Fig. 003, 004)
325 325BL 27-26-51 325 325BR 27-26-51 325 325DL 27-23-51 325 325AL 27-22-51 211VU 210 831 22-31-00 210VU 210 831 22-31-00 23VU 211 831 22-65-00 24VU 212 831 22-65-00 187VU 127 824 27-92-00 188VU 128 824 27-92-00
The AFS/FMS includes four computers: two FACs and two FMGCs (8 MCU each)
located in the aft electronics rack 80VU.
(Ref. Fig. 002)
The actuators associated with the FAC are directly connected to the flight
controls.
All the controls and displays are in the cockpit:
on the glareshield, overhead panel, maintenance panel and center pedestal.
The system buses which transfer the digital information of the ARINC
specification 429 perform:
-interconnections between the computers
-
connections between the computers, control units and sensors.
A.
Architecture of AFS The AFS comprises two sub-systems:
-
Flight Augmentation Computer system
-
Flight Management and Guidance Computer system.
These sub-systems include the computers, actuators, control units and
associated peripherals.
There are no servo actuators for the autopilot and the autothrust
functions.
The system (FMGS) sends the surface deflection commands for the autopilot
function to:
-ELAC 1 and ELAC 2 for pitch and roll commands
-FAC 1 and FAC 2 for yaw commands.
The system (FMGS) sends the thrust command for the autothrust function
to:
-ECU 1 /EEC 1 (to set the thrust command on the engine 1)
1EFF : ALL 1 22-00-00Page 5 1 1 Feb 01/99 1 1 1CES 1
-ECU 2 /EEC 2 (to set the thrust command on the engine 2).
The side stick controllers and the throttle control levers do not move
when the autopilot and the A/THR are engaged.
B. Controls and Indicating
(Ref. Fig. 004)
(1)
Controls
-FAC pushbutton switches on FLT CTL panels 23VU and 24VU
-Flight Control Unit (FCU) on the glareshield
-Multipurpose Control and Display Units (MCDU)
-Takeover and priority pushbutton switches
-A/THR instinctive disconnect pushbutton switches.
(2)
Indicating and Warnings
-Primary Flight Display (CAPT and F/O PFDs)
-Navigation Display (CAPT and F/O NDs)
-upper and lower display units of the ECAM system
-rudder trim indicator on the RUD TRIM panel on the center pedestal
-MASTER WARN, MASTER CAUT and AUTO LAND lights.
4. Power Supply
____________
A. 28VDC Supply
The 28VDC power supplies:
-FMGC 1 and FAC 1 through 28VDC ESS SHED BUS 801PP
-FCU (side 1) through 28VDC ESS BUS 401PP
-FMGC 2 , FAC 2, FCU (side 2), Rudder Trim Indicator through 28VDC BUS2 206PP
-stick lock and rudder artificial feel relays through 28VDC BAT BUS 301PP.
B. 115VAC Supply
The 115VAC power supplies:
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：A320飞机维护手册 AMM AUTO FLIGHT 自动飞行1(22)
