3. Fault Confirmation
__________________
A. Test
(1) Do the operational test of the side stick assembly (activation for the BITE test) (Ref. AMM TASK 27-96-00-710-020).
(2) Do the BITE test of the EFCS (ground scanning) (Ref. AMM TASK 27-96-00-740-001).
4. Fault Isolation
_______________
A. If the test gives the maintenance message:
L G AIL SERVO VLV 33CE1
- replace the servovalve of the servo control 33CE1, (Ref. AMM TASK 27-14-51-000-003) and (Ref. AMM TASK 27-14-51-400-003).
NOTE : The resistance must be 500 ohms +/- 10 %.
____
「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 ∞∞27-10-00∞∞∞∞∞∞∞∞∞∞Page 230
Aug 01/00R CES
(1) If the fault continues:
- do a check of the wiring POS XDCR signal from the servocontrol (33CE1) to the ELAC 2 (2CE2) COM and MON side, (Ref. ASM 27-93/03).
(2) If the fault continues:
- replace the ELAC-2 (2CE2), (Ref. AMM TASK 27-93-34-000-001) and (Ref. AMM TASK 27-93-34-400-001).
(3) If the fault continues:
- replace the SERVO CTL-L AILERON, INBD G (33CE1), (Ref. AMM TASK 27-14-51-000-001) and (Ref. AMM TASK 27-14-51-400-001).
B. Do the test given in Para. 3.
「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 ∞∞27-10-00∞∞∞∞∞∞∞∞∞∞Page 231
Aug 01/00R
CES Failure of the Left Green Aileron Servo Control Solenoid Valve
CAUTION : DO NOT SWAP FLIGHT CONTROL COMPUTERS. IF THERE IS A SHORT CIRCUIT,
_______ YOU WILL CAUSE DAMAGE TO A SERVICEABLE COMPUTER WHEN YOU SWAP THEM.
1. Possible Causes
_______________
- SERVO CTL-L AILERON, INBD G (33CE1)
- ELAC-2 (2CE2)
- solenoid valve of the servo control (33CE1)
- wiring of the SOL VLV signal from the servo control (33CE1) to the ELAC2 (2CE2)
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------REFERENCE DESIGNATION -------------------------------------------------------------------------------
AMM 27-14-51-000-001 Removal of the Aileron Servo Control AMM 27-14-51-000-004 Removal of the Aileron Servo-Control Solenoid Valve AMM 27-14-51-400-001 Installation of the Aileron Servo Control AMM 27-14-51-400-004 Installation of the Aileron Servo-Control Solenoid
Valve AMM 27-93-34-000-001 Removal of the ELAC (2CE1,2CE2) AMM 27-93-34-400-001 Installation of the ELAC (2CE1,2CE2) AMM 27-96-00-740-001 BITE Test of the EFCS (Ground Scanning) AMM 29-10-00-863-003 Pressurize the Blue Hydraulic System with a Ground
Power Supply AMM 29-10-00-864-003 Depressurize the Blue Hydraulic System AMM 29-23-00-863-001 Pressurize the Green Hydraulic System from the Yellow
Hydraulic System through the PTU with the Electric Pump AMM 29-23-00-864-001 Depressurize the Green and Yellow Hydraulic Systems after Operation of the PTU AMM 29-24-00-863-001 Pressurize the Yellow Hydraulic System with the
Electric Pump
AMM 29-24-00-864-001 Depressurize the Yellow Hydraulic System
ASM 27-93/03
3. Fault Confirmation
__________________
A. Job Set-Up
(1) Pressurize the aircraft hydraulic systems (Ref. AMM TASK 29-10-00-863-003), (Ref. AMM TASK 29-23-00-863-001), (Ref. AMM TASK 29-24-00-863-001).
「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 ∞∞27-10-00∞∞∞∞∞∞∞∞∞∞Page 232
Aug 01/00R CES
B. Test
(1) Do the BITE test of the EFCS (ground scanning) (Ref. AMM TASK 27-96-00-740-001).
NOTE : Before you push the line key adjacent to the START GROUND SCAN
____ indication, release the FLT CTL/ELAC 2 pushbutton switch on the overhead panel 24VU (on this pushbutton switch the OFF legend comes on) and wait for 30 s.
C. Put the aircraft back to its initial configuration.
(1) Depressurize the aircraft hydraulic systems (Ref. AMM TASK 29-10-00-864-003), (Ref. AMM TASK 29-23-00-864-001), (Ref. AMM TASK 29-24-00-864-001).
(2) On the overhead panel 24VU:
- push the FLT CTL/ELAC 2 pushbutton switch (on this pushbutton switch, the OFF legend goes off).
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊(cè) 飛行操縱 1(11)
