Subtask 22-10-00-860-058
C. Aircraft Maintenance Configuration
(1)
Do the EIS stop procedure (Ref. TASK 31-60-00-860-002).
(2)
De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).
TASK 22-10-00-710-008
Operational Test of the Indicator Lights and Displays of the FCU
WARNING : MAKE SURE THAT ALL THE CIRCUITS IN MAINTENANCE ARE ISOLATED BEFORE
_______ YOU SUPPLY ELECTRICAL POWER TO THE AIRCRAFT.
1. Reason for the Job
__________________
To do a check of the indicator lights and displays of the FCU.
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
24-41-00-861-002 Energize the Aircraft Electrical Circuits from the External Power 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied from the External Power
3. Job Set-up
__________
Subtask 22-10-00-861-061
A. Energize the aircraft electrical circuits
(Ref. TASK 24-41-00-861-002).
Subtask 22-10-00-865-069
B. Make sure that this(these) circuit breaker(s) is(are) closed:
-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------49VU AUTO FLT/FCU/1 9CA1 B05 49VU AUTO FLT/FMGC/1 10CA1 B02 121VU AUTO FLT/FCU/2 9CA2 M21 121VU AUTO FLT/FMGC/2 10CA2 M17 122VU LIGHTING/TST/BOARD/SPLY 30LP X06
1EFF : ALL 1 22-10-00Page 532 1 1 Aug 01/01 1 1 1CES 1
4. Procedure
_________
Subtask 22-10-00-710-062
A. Do this test:
-------------------------------------------------------------------------------ACTION RESULT -------------------------------------------------------------------------------
1. On the overhead panel, on the panel 25VU:
-Make sure that the ANN LT switch is set to DIM.
2. On the panel 25VU:
-Set the ANN LT switch to TEST.
3. Set the ANN LT switch to DIM.
5. Close-up
________
Subtask 22-10-00-862-061On the FCU:
-The 3 green bars on the pushbutton switches come on.
-All the segments in the display windows and the three associated indicator lights come on.
You must get the same result as in step 1.
A. De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).
1EFF : ALL 1 22-10-00Page 533 1 1 Aug 01/01 1 1 1CES 1 AP/FD ENGAGEMENT - DESCRIPTION AND OPERATION
____________________________________________
1.
General
_______ The engagement of the Flight Director (FD) and the Autopilot (AP) for flight guidance are described in this section.
2.
System Description
__________________
A. FD Engagement
(1)
General (Ref. Fig. 001) The FDs are engaged automatically upon energization of the computers in flight or on the ground.
(a)
Energization on ground
After the safety tests, at power rise:
-The two FDs engage if no failure is detected by internal monitoring. The FMA indications appear on the PFDs but the FD bars are removed. The FD orders will be displayed on the PFD for a given axis when a mode is active on this axis.
-If an FD does not engage (FMGC failure detected by internal monitoring), the two PFDs are switched to the valid FD (same FD indication on both PFDs).
(b)
Energization in flight The safety test at power rise is not performed. The two FDs engage in V/S and HDG modes.
(2)
FD - Engage Hardware Logic (Ref. Fig. 002) A part of the FD engage logic is accomplished through the hardware. This logic takes into account the FD ENGD signals (generated in the software) and the FG HLTY signals from the command and monitoring channels: Loss of the FD ENGD signal is spread over a period of 200 ms. The safeguard of the engage signals is ensured by back-up current Vs over a brief period. The CMD and MON FD ENGD wired signals which are obtained are used by:
-
The DMCs (FMGC bus selection logic).
-
The FCU (FMGC bus selection logic).
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