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1. On the center pedestal, on the MCDU:
-Get the SYSTEM REPORT/TEST page (Ref. TASK 31-32-00-860-001).
-
Push the line key adjacent to the AFS indication.
-
Push the line key adjacent to the WINDSHEAR TEST indication.
On the MCDU:
-
The SYSTEM REPORT/TEST page comesinto view.
-
The AFS MAIN MENU page comes intoview.
-
The AFS/WINDSHEAR TEST-1 page comesinto view.
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ACTION RESULT
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2. Do the test, steps 1 thru 7, as specified on the MCDU display (Ref. Fig. 501/TASK 22-60-00-991-001) - The WINDSHEAR TEST OK indicationcomes into view.
R R R R NOTE : For AFS/WINDSHEAR TEST -3____ & -6 pages: CHECK (WARNING) ON ECAM WINDSHEAR DET FAULT or
R R R REAC W/S DET FAULT if predictive windshear activation.
R
R R CHECK (INOP SYS) ON ECAM STATUS PAGE
R R R WINDSHEAR DET or REAC W/S DET if predictive windshear activation.
NOTE : Make sure to press TEST____ key not longer than 2.5 min. after having pressed WINDSHEAR TEST key. If yes, do the windshear test again through the MCDU.
NOTE : In the related____ AFS/WINDSHEAR TEST-2 and 5 pages, the red WINDSHEAR indication on the PFDs is
flashing during the first seconds (audio announcement).
NOTE : Push the pushbutton____ switches on the FLT CTL
panel 23VU(24VU) to engage or disengage the FAC 1(2).
3. On the MCDU:
- Push the line key adjacent to the RETURN indication until the
MAIN MENU page comes into view.
R Procedure Test Figure 501/TASK 22-60-00-991-001- 12 (SHEET 1)
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R Procedure Test Figure 501/TASK 22-60-00-991-001- 22 (SHEET 2)
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5. Close-up
________ Subtask 22-60-00-860-057
A. Put the aircraft back to its initial configuration.
(1)
On the overhead panel, on the ADIRS CDU, set the OFF/NAV/ATT selector switches to OFF.
(2)
Do the EIS stop procedure (Ref. TASK 31-60-00-860-002).
(3)
De-energize the aircraft electrical circuits (Ref. TASK 24-41-00-862-002).
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ARTIFICIAL FEEL AND RUDDER TRAVEL LIMITING COMPUTATION______________________________________________________ DESCRIPTION AND OPERATION_________________________
R 1. General_______
R R R R The rudder travel-limiting function provides: - The limitation of the rudder travel through a control law function of Vc - The return to the low speed limitation in case of failure The rudder travel limiting actuation is described in 27-23-00.
2. System Description__________________
A. Composition The system consists of: - Two engagement pushbutton switches common to the yaw damper and rudder trim functions
- Two Flight Augmentation Computers (FAC 1 and FAC 2) - An electro-mechanical rudder travel-limitation unit with two motors
- Two position transducers integrated in the unit.
B. Architecture
The rudder travel-limiting system operates using the changeover technique i.e when both sides are engaged the side 1 has priority, the side 2 is in standby. The side 2 is active when the side 1 is disengaged (case of failure). The motor of the standby side is not supplied (the FAC which has no priority does not deliver the enable signal). A synchronization is achieved on the rudder position prior to engagement Amplitude and speed limitations are introduced: - The amplitude limitation is such that the travel remains compatible with the limits on the aircraft structure
- The speed limitation prevents saturation of the limitation unit. Upon total loss of the rudder travel-limiting function, a control enables to bring back the stops to the low speed conditions to restore maximum rudder deflection as soon as slats are extended.
3. Power Supply____________
A. Power Supply of the Rudder Travel-Limitation Unit The 26 V/400 Hz power is applied to the primary windings of the position transducers directly from the busbars via the FAC circuit breakers. The emergency control of the motor operates on the same power supply. The 28VDC power is applied to the power electronic set from the FAC circuit breakers through a cut-off relay. This relay is controlled by the monitoring logic of the FAC.
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