(c) Supply a test signal for 5 seconds and read the shown resistance value
(d) the resistance value must be greater than 100Megohms.
(e) For the GREEN Soleniod do the same operation as in 4.A.(7) and (8).
(9) If the BRAKE-R WING TIP (36CV) fails one of the two tests at Para 4.A.(7) or (8) replace the Solenoid valve (Ref. AMM TASK 27-81-51-000-004) (Ref. AMM TASK 27-81-51-400-002)
(10) Do the System BITE test as given in Para 3.A.(1).
(11) Set the MCDU to MENU MODE and access the SLT ON GROUND FAULTS page and make sure that the ground log is clear.
5. Close-up
________
A. Remove the ground support and maintenance equipment, the special and standard tools and all other items.
B. Put the aircraft back to its initial configuration.
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May 01/04R CES
Slat Speed Commanded but Slat Half Speed Detected.
1. Possible Causes
_______________
- 25CV
- 26CV
- aircraft wiring
- POB SOLENOID
- FILTERS
2. Job Set-up Information
______________________
A. Fixtures, Tools, Test and Support Equipment
-------------------------------------------------------------------------------REFERENCE QTY DESIGNATION -------------------------------------------------------------------------------
No specific Multimeter
No specific 45Vdc Isolation Tester
B. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM 27-54-52-000-001 Removal of the Pressure-Off Brake of the Flap Power
Control Unit AMM 27-84-00-710-001 Operational Test of the Slat System AMM 27-84-52-000-001 Removal of the Pressure-Off Brake of the Slat Power
Control Unit AMM 27-84-52-400-001 Installation of the Pressure-Off Brake of the Slat Power Control Unit AMM 27-84-53-000-001 Removal of the Valve Blocks 25CV, 26CV of the Power
Control Unit (Slat) AMM 27-84-53-000-003 Removal of the Filters of the Valve Blocks AMM 27-84-53-400-001 Installation of the Valve Blocks 25CV, 26CV of the
Power Control Unit (Slat)
AMM 27-84-53-400-003 Installation of the Filters of the Valve Blocks
ASM 27-81/02
ASM 27-81/03
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May 01/04R CES
3. Fault Confirmation
__________________
A. Table of the circuit breakers used in this procedure:
-------------------------------------------------------------------------------PANEL DESIGNATION IDENT. LOCATION -------------------------------------------------------------------------------
49VU FLIGHT CONTROLS/SLT/CTL AND MONG/SYS1 5CV B06 121VU FLIGHT CONTROLS/SLT/CTL/SYS2 7CV R21
B. SFCC Reset and Initialization.
(1) At the circuit breakers.
(a) Open the circuit breakers.
(b) Wait for 3 seconds and close the circuit breakers.
(c) Wait for 60 seconds
(d) Check the UPPER ECAM and the SD FLT/CTL page for the fault warnings.
(e) Access the SLT ON GROUND FAULTS page and do a check of the ground log.
(f) If the ECAM warning and the ground log is clear:
- no further maintenance actions are required
(g) If the ECAM warning and the ground log fault message stays displayed do the fault Isolation.
4. Fault Isolation
_______________
A. Procedure.
(1) Do the operational test of the slats system (Ref. AMM TASK 27-84-00-710-001)
NOTE : : For this operational test it is necessary that the Power
____
Tranafer Unit (PTU) be in operation.
(2) During the procedure in para. 4.A.(1) if the fault gives a slow extension or slow retraction and there is no Hyd. fault.
(3) Isolate the PCU fault, do a comparison between both motor speeds:
- de-activate SFCC 1 and move the flaps, time the extension.
- energize SFCC 1 and de-activate SFCC 2.
- move the flaps and time the extension.
(a) The time difference shows the slowest system.
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1 EFF : ALL ∞∞27-81-00∞∞∞∞∞∞∞∞∞∞Page 257
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 飛行操縱 2(75)
