「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1R EFF : 001-049, 051-099, 101-149, 151-199, ∞∞24-20-00∞∞∞∞∞∞∞∞∞∞Page A228
201-299, 301-399, Aug 01/05 CES (1) If the fault continues:
- replace the IDG oil cooler (Ref. AMM TASK 73-11-60-000-002) and (Ref. AMM TASK 73-11-60-400-002).
B. Do this operational test to make sure that the system operates correctly.
(1) Aircraft Maintenance Configuration
(a) Energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-861-002).
(b) Do the EIS start procedure (Upper ECAM DU and lower ECAM DU only) (Ref. AMM TASK 31-60-00-860-001).
(2) On the ELEC panel 35VU:
- push, release and push again the GEN 2 pushbutton switch (3XU2).
(3) Do the operational test of the GPCU (Ref. AMM TASK 24-41-00-740-002).
(4) Start the engine 2 (Ref. AMM TASK 71-00-00-710-003).
C. Do this test:
-------------------------------------------------------------------------------ACTION RESULT -------------------------------------------------------------------------------
On the ECAM control panel: On the lower ECAM display unit:
- get the ELEC page. - the correct electrical parameters of GEN 2 are shown and AC 2 busbar is supplied by GEN 2.
5. Close-up
________
A. Put the aircraft back to its initial configuration.
(1) Stop the engine 2 (Ref. AMM TASK 71-00-00-710-028).
(2) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF.
(3) De-energize the aircraft electrical circuits
(Ref. AMM TASK 24-41-00-862-002).
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1R EFF : 001-049, 051-099, 101-149, 151-199, ∞∞24-20-00∞∞∞∞∞∞∞∞∞∞Page A229
201-299, 301-399, Aug 01/05 CES
TASK 24-20-00-810-851
Failure of the IDG1 Disconnect Circuit
1. Possible Causes
_______________
- GCU-1 (1XU1)
- IDG (4000XU)
- RELAY-IDG1 DISC CTL (3XT)
- RELAY-FUNCTION (7XT)
- IDG1 disconnect wiring
2. Job Set-up Information
______________________
A. Referenced Information
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REFERENCE DESIGNATION
-------------------------------------------------------------------------------
AMM 24-21-00-720-041 Operational Test of the IDG Disconnect and Reconnect (Reset) Function - Engine in Operation AMM 24-21-51-000-040 Removal of the Integrated Drive Generator -IDG 1(2),(4000XU) AMM 24-21-51-400-040 Installation of the Integrated Drive Generator -IDG
1(2),(4000XU)
AMM 24-22-34-000-001 Removal of the GCU-1(2) (1XU1, 1XU2)
AMM 24-22-34-400-001 Installation of the GCU-1(2) (1XU1, 1XU2)
ASM 24-21/01
3. Fault Confirmation
__________________
A. Test
Not applicable, you cannot confirm this fault on the ground.
4. Fault Isolation
_______________
A. If the fault symptom is identified by the CFDS message: CHECK IDG1 DISCONNECT CKT and by the warnings IDG1 OIL LO PR and IDG1 OIL OVHT on the upper ECAM display unit:
- replace the GCU-1 (1XU1) (Ref. AMM TASK 24-22-34-000-001) and (Ref. AMM TASK 24-22-34-400-001).
(1) If the fault continues:
- replace the RELAY-IDG1 DISC CTL (3XT).
(2) If the fault continues:
- replace the RELAY-FUNCTION (7XT).
「一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一一1R EFF : 001-049, 051-099, 101-149, 151-199, ∞∞24-20-00∞∞∞∞∞∞∞∞∞∞Page A230
201-299, 301-399, Aug 01/05 CES
(3) If the fault continues:
- do a check of the IDG1 disconnect wiring between: the pin 2 of the circuit breaker (1XT) and the pin B3 of the ELEC/IDG1 pushbutton switch (5XT) the pin 2 of the circuit breaker (1XT) and the pin A2 of the relay (3XT) the pin B1 of the ELEC/IDG1 pushbutton switch (5XT) and the pin X1 of the relay (3XT) the pin A1 of the relay (3XT) and successively the pin A/3B of the GCU1 (1XU1) and the pin A/12 of the IDG2 (4000XU) the pins B2 and X2 of the relay (3XT) and the ground the pin A/13 of the IDG1 (4000XU) and the ground the pin A/14 of the IDG1 (4000XU) and the pin A/6B of the EGIU1 (22XU1) the pin B1 of the relay (3XT) and the pin A/4B of the EGIU1 (22XU1) (Ref. ASM 24-21/01). 中國(guó)航空網(wǎng) www.k6050.com 航空翻譯 www.aviation.cn 本文鏈接地址：A320 Trouble Shooting Manual 排故手冊(cè) 電源 2(3)
