- release the FLT CTL/SEC2 pushbutton switch (the OFF legend comes on).
(3) On the overhead panel 24VU:
- push the FLT CTL/SEC2 pushbutton switch (the OFF legend goes off).
(4) On the central pedestal 11VU:
- put the right throttle lever in TO/GA and MAX REV during 5 seconds.
B. Test
(1) Do the BITE test of the EFCS (Ground Scanning) (Ref. AMM TASK 27-96-00-740-001).
4. Fault Isolation
_______________
A. If the BITE test gives the maintenance message: SEC2 PERMANENT IDLE OF R THROTTLE CTL UNIT 8KS2
- replace the SEC-2 (1CE2), (Ref. AMM TASK 27-94-34-000-001) and (Ref. AMM TASK 27-94-34-400-001).
(1) If the fault continues:
- replace the CTL UNIT-THROTTLE, ENG 2 (8KS2), (Ref. AMM TASK 76-11-19-000-040) and (Ref. AMM TASK 76-11-19-400-040).
B. Do the operational test and the BITE test given in Para. 3.
Unwanted Permanent Idle of the Right Throttle Control Unit for the SEC 3
1. Possible Causes
_______________
- SEC-3 (1CE3)
- CTL UNIT-THROTTLE, ENG 2 (8KS2)
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM 24-41-00-861-002 Energize the Aircraft Electrical Circuits from the
External Power
AMM 27-94-34-000-001 Removal of the SEC (1CE1,1CE2,1CE3)
AMM 27-94-34-400-001 Installation of the SEC (1CE1,1CE2,1CE3)
R AMM 27-96-00-740-001 BITE Test of the EFCS (Ground Scanning) AMM 76-11-19-000-040 Removal of the Throttle Control Unit (8KS1, 8KS2) AMM 76-11-19-400-040 Installation of the Throttle Control Unit (8KS1,
8KS2)
3. Fault Confirmation
__________________
A. Job Set-Up
(1) Energize the aircraft electrical circuits (Ref. AMM TASK 24-41-00-861-002).
(2) On the overhead panel 24VU:
- release the FLT CTL/SEC3 pushbutton switch (the OFF legend comes on).
(3) On the overhead panel 24VU:
- Push the FLT CTL/SEC3 pushbutton switch (the OFF legend goes off).
(4) On the central pedestal 11VU:
- put the right throttle lever in TO/GA and MAX REV during 5 seconds.
B. Test
(1) Do the BITE test of the EFCS (Ground Scanning) (Ref. AMM TASK 27-96-00-740-001).
4. Fault Isolation
_______________
A. If the BITE test gives the maintenance message: SEC3 PERMANENT IDLE OF R THROTTLE CTL UNIT 8KS2
- replace the SEC-3 (1CE3), (Ref. AMM TASK 27-94-34-000-001) and (Ref. AMM TASK 27-94-34-400-001).
(1) If the fault continues:
- replace the CTL UNIT-THROTTLE, ENG 2 (8KS2), (Ref. AMM TASK 76-11-19-000-040) and (Ref. AMM TASK 76-11-19-400-040).
B. Do the operational test and the BITE test given in Para. 3.
Loss of the Wheel Tachometer Signal for the SEC 2
1. Possible Causes_______________
R R R R - SEC-2 (1CE2) - wiring of ANI-6 signal from the SEC 2 (1CE2) to the related TACHOMETER-WHEEL - DRIVE ASSY-TACHOMETER - TACHOMETER-WHEEL
2. Job Set-up Information______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
R AMM 27-94-34-000-001 AMM 27-94-34-400-001 AMM 32-42-57-000-001 Removal of the SEC (1CE1,1CE2,1CE3)Installation of the SEC (1CE1,1CE2,1CE3) Removal of the Tachometer
R AMM 32-42-57-400-001 Installation of the Tachometer
R AMM 32-42-68-000-003 Removal of the MLG Tachometer-Drive
R AMM 32-42-68-400-003 Installation of the MLG Tachometer-Drive
ASM 27-92/25
3. Fault Confirmation__________________
A. Test
Not applicable, you cannot confirm this fault on the ground.
4. Fault Isolation
_______________
R A. If the Post Flight Report gives the maintenance message:
SEC 2 OR INPUT OF WHEEL TACHOMETER R - do a check and repair, if necessary, the wiring of ANI-6 signal from R the SEC 2 (1CE2) to the related TACHOMETER-WHEEL for the SEC 2 COM part
and MON part (Ref. ASM 27-92/25).
(1) If the wiring is correct: R - examine the DRIVE ASSY-TACHOMETER of the related wheels.
R (a) If the DRIVE ASSY-TACHOMETER is damaged:
R - replace it (Ref. AMM TASK 32-42-68-000-003) and (Ref. AMM TASK
R 32-42-68-400-003).
R (b) If the DRIVE ASSY-TACHOMETER is not damaged and there is no 中国航空网 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：A320 Trouble Shooting Manual 排故手册 飞行操纵 3(98)
