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 (13KS1) and the EIU1 (1KS1)
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 1 NACELLE (13KS1) (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-1 (1KS1) (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
R - repeat the fault isolation procedure.
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TASK 75-41-00-810-806
High Nacelle Temperature Indication on Engine 2
1. Possible Causes
_______________
R - hot air leaks from the ECS R - hot air leaks from the engine R
- aircraft wiring R - SENSOR-TEMP, ENG 2 NACELLE (13KS2) R - EIU-2 (1KS2)
2. Job Set-up Information
______________________
R A. Consumable Materials
R -------------------------------------------------------------------------------R REFERENCE DESIGNATION
R -------------------------------------------------------------------------------
R Material No. CP2170 *
R leak-tek 16-OX (Ref. 70-30-00)
R Material No. CP3010 USA MIL-I-25135
R Ardrox 9D4A (Ref. 70-30-00)
R B. Referenced Information
-------------------------------------------------------------------------------
REFERENCE DESIGNATION
-------------------------------------------------------------------------------
R AMM 71-00-00-710-001
R AMM 71-00-00-710-006
R AMM 71-00-00-710-028
R AMM 73-11-40-790-002
R AMM 73-21-70-400-001
R
AMM 73-25-34-000-040
AMM 73-25-34-400-040
AMM 75-41-15-000-041
AMM 75-41-15-400-041
R AMM 77-21-10-200-002
R
R AMM 77-23-10-400-002
R
R AMM 78-36-00-010-040
R AMM 78-36-00-410-040
ASM 73-25/07
F EEFF : ALL E E ECES Dry Motoring Check Minimum Idle Check Engine Shutdown Leak Check of the Fuel Nozzles Installation of the High Pressure Turbine Clearance Control (HPTCC) SensorRemoval of the Engine Interface Unit (EIU)Installation of the Engine Interface Unit (EIU)Removal of the Nacelle Temperature SensorInstallation of the Nacelle Temperature Sensor Inspection/Check of the T495 Thermocouple Wiring Harness Installation of the Compressor Discharge Temperature (T3) Sensor Opening of the Thrust Reverser Doors Closing of the Thrust Reverser Doors
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3. Fault Confirmation
__________________
R A. Test
R (1) Not applicable.
R NOTE : The following trouble shooting procedure must be completed at
____ R first opportunity not interfering with revenue service R operation within subsequent 10 days or 150 flight hours of R operation that follow the first exceedance of nacelle R temperature above 240 deg.C (464 deg.F) pending there is no R ECAM warning related to ENG2 FIRE LOOP A (B) FAULT.
R
4. Fault Isolation
_______________
R A. Do the following checks:
R NOTE : The maintenance message CHECK HOT AIR LEAKS ENG2 is generated and
____ R the advisory for nacelle temperature is flashing green on the R upper ECAM if the air temperature at the top of the core R compartment area is higher than 240 deg.C (464 deg.F).
R (1) Open both reverser cowls (Ref. AMM TASK 78-36-00-010-040).
R (2) Do a check for hot air leaks from the ECS:
R - make sure that the engine bleed ducts are in the correct condition
R and correctly installed (ECS and engine bleed ducts and pneumatic
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