R **ON A/C 106-149, 155-199, 208-299, 301-399, 401-499, Subtask 31-38-34-740-050
F. Do the BITE Test of the Data Loading Routing Box (Ref. TASK 31-38-00-740-001).
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5. Close-up
________
Subtask 31-38-34-410-050
A. Close Access
(1)
Make sure that the work area is clean and clear of tool(s) and other items.
(2)
Remove the warning notice(s).
(3)
Close the access door 824 (Ref. TASK 52-41-00-410-002).
(4)
Remove the access platform(s).
Subtask 31-38-34-862-050
B.
De-energize the aircraft electrical circuits
(Ref. TASK 24-41-00-862-002).
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CENTRAL WARNING SYSTEMS - DESCRIPTION AND OPERATION
___________________________________________________
1.
General
_______ The central warning system called the Flight Warning System comprises various items of equipment which allow the crew to be aware, by means of audio and visual devices and two display units (the ECAM display units), of the main aircraft equipment behaviour, and aircraft dangerous configurations. It also provides the appropriate corrective actions. (Ref. Fig. 001)
2.
Component Location
__________________
The following figures show the location of the system components.
(Ref. Fig. 002, 003)
The complete system includes the following components:
-2 DUs called EWD and SD housed in racks on the center instrument panel,
-3 DMCs (Display Management Computers) common to the EFIS and ECAM systems, located in the avionics compartment.
The DMC standard is adapted to each aircraft through pin programming,
-
2 FWCs (Flight Warning Computers) located in the avionics compartment.
The FWC standard is adapted to each aircraft through pin programming,
-
2 SDACs (System Data Acquisition Concentrators) located in the avionics compartment,
-1 ECAM control panel, located on the center pedestal,
-
two sets of visual devices, located on the glareshield, on either side of the FCU, each including a MASTER WARN light and a MASTER CAUT light; these lights are of the pushbutton switch type,
-
two loudspeakers, located on panels 2VU and 6VU, just in front of each side stick controller,
-an audio mixing box located in the avionics compartment,
-maintenance and test controls accessible through the MCDUs,
-circuit breakers:
. those connected to ESSENTIAL bus bars are located on the rear part of the overhead panel,
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ECAM breakdown
Figure 001
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R Component Location in the Cockpit Figure 002
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Component Location in the Avionics Compartment
Figure 003
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. the others are located on the rear cockpit partition.
3. System Description
__________________
(Ref. Fig. 004)
A. General Description
(1) System Architecture and Interface The system architecture has been designed in a way as to ensure an actual segregation between EFIS, engine indicating system and ECAM information, although each DMC receives all three kinds of information. The EIS components receive from the aircraft systems all the information necessary for the elaboration of the various EFIS and ECAM displays. For any EIS computer (DMC, FWC, SDAC), note that all the signals from the various sensors are sent in parallel to the concerned EIS equipment of side 1 and 2 (and possibly 3 for the DMCs). In fact, all the signals entering the EIS computers are acquired redundantly. For example, the SDAC 1 receives signals from A/C systems, computers and sensors of the side 1 and of the side 2, and identically for the SDAC 2. This allows FWS to be transparent to any single failure. (Ref. Fig. 005, 006) This principle of redundancy provides numerous advantages :
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