(b) The slowest system is the PCU with possible internal friction.
(c) Go to Para.4.A.(12).
(4) During the procedure at Para.4.A.(3).
(a) If one SFCC is energized and a flap extension is commanded and a system jam occurs.
(b) Do a check of the POB solenoid circuit.
(5) Do a check of the POB electrical circuit
(a) Refer to: (Ref. AMM TASK 27-54-52-000-001) Figure 401/Task 27-54-52-991-001.
(b) Find the electrical connector for the valveblock 25CV or 26CV POB solenoids and release.
(c) Do a check of the aircraft wiring from the SFCC ARINC tray interface to the POB solenoid electrical connectors 25CV-A/26CV-A. (Ref. ASM 27-81/02) (Ref. ASM 27-81/03)
(d) If there is a wiring/interface fault do the repair.
(6) If the A/C wiring is satisfactory, do a check of the circuit resistance and circuit isolation of the fault related solenoid valve.
(a) On the valveblock use a Multimeter and do a check of the resistance between For SFCC1 -25CV = POB pins L and K ASM/278102S01
For SFCC2 -26CV = POB pins L and K ASM/278103S01
(b) The reistance for the POB solenoid:
- P/N 667C0000-02 must be between 71 ohms and 84 ohms
- P/Ns 903A0000-01; 1106A0000-01 and 1111A0000-01 must be between 53 ohms and 60 ohms
(7) On the Valveblock, do a check for circuit isolation.
(a) For the POB solenoid connect the pins L & K together.
(b) Connect one test lead of the 45Vdc Isolation Tester to the pins LK and the other test lead to pin G.
(c) Supply a test signal for 5 seconds and read the shown resistance value
(d) the resistance value must be greater than 100Megohms.
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(8) If the POB SOLENOID fails one of the two tests at Para 4.A.(2) and
(3) replace the POB solenoid (Ref. AMM TASK 27-84-52-000-001) (Ref. AMM TASK 27-84-52-400-001)
(9) If the tests at Para 4.A(2). and (3) are satisfactory.
(10) Do the operation given in Para 4.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.
(12) If the CFDS shows the same fault message,then the fault is with the PCU valveblock
(a) Examine the valveblock FILTERS (Ref. AMM TASK 27-84-53-000-003) (Ref. AMM TASK 27-84-53-400-003) and clean/replace the examined item.
(b) Do the test at Para.4.A.(1) and do a check of the SLT ON GROUND FAULTS page, If the fault stays.
(c) Examine the valveblock 25CV 26CV and replace the faulty item. (Ref. AMM TASK 27-84-53-000-001) (Ref. AMM TASK 27-84-53-400-001)
(d) Do the operation at Para.4.A.(1) and make sure the ground log is clear.
(e) Do the SFCC 1 (2) reset, refer to Para.3.B. slow retraction do a check of the EXT/RET electrical circuit,
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CES SFCC 1 SLT 1 no ADIRU 2 Data or SFCC 2 SLT 2 no ADIRU 2 Data.
1. Possible Causes
_______________
- SFCC-1 (21CV)
- SFCC-2 (22CV)
- ADIRU-2 (1FP2)
- aircraft wiring
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION
-------------------------------------------------------------------------------
AMM 27-51-34-000-001 Removal of the SFCC (21CV,22CV)
AMM 27-51-34-400-001 Installation of the SFCC (21CV,22CV)
AMM 31-32-00-860-006 Procedure to Get Access to the SYSTEM REPORT/TEST
F/CTL Page AMM 34-12-34-000-001 Removal of the ADIRU (1FP1, 1FP2, 1FP3) AMM 34-12-34-400-001 Installation of the ADIRU (1FP1, 1FP2, 1FP3) ASM 27-81/08
3. Fault Confirmation
__________________
A. Test
(1) At the MCDU aet the MENU MODE and get access to the SYSTEM REPORT/TEST F/CTL page. (Ref. AMM TASK 31-32-00-860-006).
(a) Get access to the SFCC 1 (2) SYSTEM DATA SLAT page and push the line key adjacent to the ARINC 429 INPUT STATUS indication:
- if the ARINC input status shows ADIRU 2 LABEL *** NO DATA, do the Fault Isolation Procedure.
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 飛行操縱 2(76)
