R **ON A/C 062-099, 106-149, 151-199, 204-299, 301-399, 401-499,
(Ref. Fig. 002A)
**ON A/C ALL
The computers (SIDE 1 and SIDE 2) have separate power supplies.
Each side is associated with the controls on the front panel of the unit.
The display is common to both sides, whereas the signals are routed via
separate paths.
2. Component Location
__________________
(Ref. Fig. 003)
-------------------------------------------------------------------------------FIN | FUNCTIONAL DESIGNATION | PANEL|ZONE|ACCESS | ATA | | | | DOOR | REF. -------------------------------------------------------------------------------2CA FCU 13VU 211 831 22-81-12
3. Component Description
_____________________
A. Face of FCU The FCU comprises three panels: - one center panel (auto flight control section) which features the
controls and the displays associated with the AFS
-two symmetrical panels (EFIS control sections) located on the left side and on the right side of the center panel. These panels include the controls and the displays associated respectively with the Captain and the First Officer EFIS display units.
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R R Flight Control Unit (FCU) Figure 001
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FCU - Internal Arrangement
Figure 002
FCU - Internal Arrangement
Figure 002A
FCU - Component Location Figure 003
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B. Architecture
**ON A/C 001-049, 051-061, 101-105, 201-203,
(Ref. Fig. 004)
R **ON A/C 062-099, 106-149, 151-199, 204-299, 301-399, 401-499,
(Ref. Fig. 004A)
**ON A/C ALL
Each part (or computer) of the FCU can manage the controls and the
displays located on the front panel of the unit.
Architecture is configured to provide physical separation between the two
channels and segregate electrical routing.
4. System Description
__________________
**ON A/C 001-049, 051-061, 101-105, 201-203,
A. Monitoring of FCU The validity of a channel is contingent upon the types of monitoring below:
-power monitoring (cutoff longer than 200 ms)
-watchdog monitoring
-ARINC monitoring by the associated FMGC (Ref. Fig. 005) Certain data transmitted by the FMGC are fed back to the FMGC through the FCU bus. These data are therefore compared with the source data. In the event of a discrepancy the FMGC delivers a discrete : FCU FAIL. This discrete is taken into account by the FCU if transmitted by the FMGC which has priority.
-refresh monitoring of the ARINC signals delivered by the opposite channel. The non-refresh of the ARINC signals on the opposite channel, on the condition that it is on-line, causes the validity loss of the channel which receives these signals. This monitoring permits to avoid data synchronization loss between the two channels in the event of failures affecting the exchange of the ARINC signals.
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FCU - Architecture
Figure 004
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1
FCU - Architecture
Figure 004A
Monitoring of FCU by FMGC
Figure 005
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1 1 May 01/01
1 1
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B. Changeover (Ref. Fig. 006) In order to ensure segregation of barometric selections and displays, the CAPT and F/O BARO parameters are controlled, in normal operation, independently by two different processors. If both processors are healthy, the FCU1 is active and controls CAPT BARO selection, AFS display, AFS and EFIS pushbutton switches as well as ARINC 1 bus (S1=0 and S3=1). The FCU2 controls F/O BARO selection and ARINC 2 bus (S2=0). When processor 1 is failed, there is a changeover on processor 2 which becomes active. It then controls the whole FCU (S1=1, S2=0 and S3=0). When processor 2 is failed, processor 1 remains active and also controls F/O BARO selection and ARINC 2 bus (S1=0, S2=1 and S3=1). The changeover occurs as soon as a channel is no longer valid, and especially for power supply cutoffs longer than 200 ms. 中國航空網(wǎng) m.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：A320飛機(jī)維護(hù)手冊 AMM AUTO FLIGHT 自動飛行4(79)
