3. Fault Confirmation
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A. Test Not applicable.
Removal of the IDG Cooling Oil-in Tubes and HosesRemoval of the IDG Cooling Oil-out Tubes and HosesInstallation of the IDG Cooling Oil-in Tubes and HosesInstallation of the IDG Cooling Oil-out tubes and HosesOperational Test of the Ground power Control Unit (GPCU)Energize the Aircraft Electrical Circuits from the External PowerDe-energize the Aircraft Electrical Circuits Supplied from the External PowerEIS Start ProcedureEngine Automatic StartEngine ShutdownRemoval of the Integrated Drive Generator (IDG) Oil Cooler AssemblyInstallation of the Integrated Drive Generator (IDG) Oil Cooler Assembly
NOTE : As the GEN2 was set to OFF because of a true failure, the fault
____
confirmation is not necessary.
「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 A240
201-299, 301-399, Aug 01/05 CES
4. Fault Isolation
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A. If the fault symptom is identified by the CFDS message IDG COOLER 2 and the warning IDG2 OIL OVHT on the upper ECAM DU:
- replace the IDG2 oil cooler (Ref. AMM TASK 73-11-60-000-002) and (Ref. AMM TASK 73-11-60-400-002).
(1) If the fault continues:
- do a check for cooler tubing blockage and replace the IDG2 oil cooling tubing which is blocked (Ref. AMM TASK 24-21-49-000-003) (Ref. AMM TASK 24-21-49-000-004) and (Ref. AMM TASK 24-21-49-400-003) (Ref. AMM TASK 24-21-49-400-004).
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 GEN2 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 -------------------------------------------------------------------------------
1. On the ECAM control panel: On the lower ECAM display unit:
- get the ELEC page. - the correct electrical parameters of GEN2 are shown and AC2 busbar is supplied by GEN2.
5. Close-up
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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 A241
201-299, 301-399, Aug 01/05 CES
TASK 24-20-00-810-858
Loss of the ECAM and EFIS Displays during Engine Start at IDG 1 Connection
1. Possible Causes
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- IDG 1 (4000XU)
2. Job Set-up Information
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A. Referenced Information
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REFERENCE DESIGNATION
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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 71-00-00-710-003 Engine Automatic Start
3. Fault Confirmation
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A. Test
(1) Start the engine 1 (Ref. AMM TASK 71-00-00-710-003).
(2) The fault is confirmed if during the engine start:
- the ECAM and EFIS display units go blank with a diagonal line for more than one second,
- and the IDG 1 is connected below 55% N2.
4. Fault Isolation
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