R NOTE : Two mechanics are required (one located on each side of the
____ R engine core) to properly perform this task.
R (4) If a leak developer is not available, an air leak can usually be R detected by a tactile test (an air stream can be felt by hand).
R (5) Correct the hot air leaks where applicable.
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R (6) Remove the straps from the fan rotor blades.
R D. Leakage Identification at Idle using Leak Developer.
R (1) Apply a leak developer Ardrox 9D4A (Material No. CP3010) around
R duct/air pipe joints and on valves, sensor seatings on combustor, HP
R compressor and turbine cases.
R (2) Do a minimum idle leak check (Ref. AMM TASK 71-00-00-710-006).
R - On the AIR COND panel 30VU, push the ENG 2 BLEED pushbutton switch
R (4HA2) to operate the engine bleed system.
R - On the ANTI-ICE section of the panel 25VU, push the ANTI ICE/ENG 2
R pushbutton switch (2DN2) to operate the engine anti-ice system.
R (3) Stop the engine (Ref. AMM TASK 71-00-00-710-028)
R (4) Do a visual inspection of the hardware and check for evidence of an
R air leak. Correct the hot air leaks where applicable.
R - Remove the material used to check leaks.
R E. If the fault continues or if no leak is found:
R - Do a check for correct sealing and torquing of the fuel nozzles (Ref.
R AMM TASK 73-11-40-790-002). Fuel nozzles located on the top of the
R engine must be inspected first.
R (1) If the fault continues:
R - Do a resistance and insulation check of the electrical wiring
R between the nacelle temperature sensor (13KS2) and the EIU2 (1KS2)
R (Ref. ASM 73-25/07). The wiring resistance must be less than 2.4
R ohms. Repair the aircraft wiring as required.
R (2) If nothing is found:
R - replace the SENSOR-TEMP, ENG 2 NACELLE (13KS2) (Ref. AMM TASK 75-R 41-15-000-041) and (Ref. AMM TASK 75-41-15-400-041).
R (3) If the fault continues:
R - replace the EIU-2 (1KS2) (Ref. AMM TASK 73-25-34-000-040) and (Ref.
R AMM TASK 73-25-34-400-040) (less probable cause for this failure).
R F. Do a check that the fault does not continue on subsequent flight.
R (1) If the fault continues:
R - repeat the fault isolation procedure.
R
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TASK 75-41-00-810-807
Nacelle Temperature above 310 deg.C (590 deg.F) or Loss of the Nacelle
Temperature Data on Engine 1
1. Possible Causes
_______________
- SENSOR-TEMP, ENG 1 NACELLE (13KS1)
- EIU-1 (1KS1)
- aircraft wiring
2. Job Set-up Information
______________________
A. Referenced Information
-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------
75-41-00-810-805 High Nacelle Temperature Indication on Engine 1
AMM 73-25-34-000-040 Removal of the Engine Interface Unit (EIU)
AMM 73-25-34-400-040 Installation of the Engine Interface Unit (EIU)
AMM 73-25-34-710-043 Operational Test of the Engine Interface Unit
AMM 75-41-15-000-041 Removal of the Nacelle Temperature Sensor
AMM 75-41-15-400-041 Installation of the Nacelle Temperature Sensor
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本文鏈接地址：A320 Trouble Shooting Manual 排故手冊 大氣 AIR(85)
