W DOC AIRBUS | TSM A320F

High Nacelle Temperature Indication on Engine 2

TASK 75-41-00-810-806-A
High Nacelle Temperature Indication on Engine 2

1. Possible Causes
  • hot air leaks from the ECS
  • hot air leaks from the engine
  • aircraft wiring
  • SENSOR-TEMP, ENG 2 NACELLE [13KS2]
  • EIU-2 [1KS2]
2. Job Set-up Information
 A. Consumable Materials
REFERENCE
DESIGNATION
(Material No.CP2170)
leak-tek 16-OX
(Material No.CP3010)
Ardrox 9D4A
 B. Referenced Information
REFERENCE
DESIGNATION
AMM 21-00-00-615-001
Decontamination of the Environmental Control System (ECS) when the Temperature is below 24 deg.C (APU)
AMM 21-00-00-615-002
Decontamination of the Environmental Control System (ECS) when the Temperature is above 24 deg.C (APU)
AMM 71-00-00-710-001
Dry Motoring Check
AMM 71-00-00-710-003
Engine Automatic Start
AMM 71-00-00-710-006
Minimum Idle Check
AMM 71-00-00-710-028
Engine Shutdown
AMM 73-11-40-400-001
Installation of the Fuel Nozzles
AMM 73-11-40-400-002
Installation of the Fuel Nozzle for SAC Engines
AMM 73-11-40-790-001
Leak Check of the Fuel Nozzles
AMM 73-11-40-790-002
Leak Check of the Fuel Nozzles for SAC Engines
AMM 73-21-70-400-001
Installation of the High Pressure Turbine Clearance Control (HPTCC) Sensor
ASM 732507
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 75-41-15-000-040
Removal Nacelle Temperature Sensor
AMM 75-41-15-000-041
Removal of the Nacelle Temperature Sensor
AMM 75-41-15-400-040
Installation Nacelle Temperature Sensor
AMM 75-41-15-400-041
Installation of the Nacelle Temperature Sensor
AMM 77-21-10-200-001
Inspection/Check of the T495 Thermocouple Wiring Harness
AMM 77-21-10-200-002
Inspection/Check of the T495 Thermocouple Wiring Harness
AMM 77-23-10-400-001
Installation of the Compressor Discharge Temperature (T3) Sensor
AMM 77-23-10-400-002
Installation of the Compressor Discharge Temperature (T3) Sensor
AMM 78-36-00-010-040
Opening of the Thrust Reverser Doors
AMM 78-36-00-410-040
Closing of the Thrust Reverser Doors
3. Fault Confirmation
Subtask 75-41-00-710-060-A ** ON A/C NOT FOR ALL
A. Test
   (1) Not applicable.
NOTE: The following trouble shooting procedure must be completed at first opportunity not interfering with revenue service operation within subsequent 10 days or 150 flight hours of operation that follow the first exceedance of nacelle temperature above 240 deg.C (464 deg.F) pending there is no ECAM warning related to ENG2 FIRE LOOP A (B) FAULT. In case of ENG2 FIRE LOOP A (B) FAULT or ENG2 FIRE warning, the following troubleshooting procedure must be completed without any relief condition.
4. Fault Isolation
Subtask 75-41-00-810-055-A ** ON A/C NOT FOR ALL
A. Do the following checks:
NOTE: The maintenance message CHECK HOT AIR LEAKS ENG2 is generated and the advisory for nacelle temperature is flashing green on the upper ECAM if the air temperature at the top of the core compartment area is higher than 240 deg.C (464 deg.F).
   (1) Open both reverser cowls AMM 78-36-00-010-040.
   (2) Do a check for hot air leaks from the ECS :
  • make sure that the engine bleed ducts are in the correct condition and correctly installed (ECS and engine bleed ducts and pneumatic valves). Pay particular attention to clamp installation.
   (3) Do a check for evidence of overheat on the inner wall of both reverser cowls. If hot spots are visible, do a check for leaks in the area next to the spot.
   (4) Do a check for excessive presence of black deposit streaks on the hot section of the engine. If black streaks are visible, do a check for leaks in the area next to the spot.
   (5) Make sure that the 12 o'clock EGT probe deflector is correctly installed.
NOTE: The purpose of this deflector is to avoid EGT probe hot air impingement onto the nacelle temperature sensor.
   (6) Do a check of the cooling holes in the inner wall of the reverser cowls for blockage.
   (7) Do a check for proper installation of all engine and bleed valves located in the core compartment.
   (8) Do a visual check for cracks in the combustor casing, HP compressor casing and turbine casing.
   (9) Do a visual inspection of the nacelle temperature sensor and wiring for any signs of external damage. Do a check on connectors of the nacelle temperature sensor (13KS2) and associated harness for contamination/corrosion and for damaged pins. Clean repair wiring or replace the sensor as required AMM 75-41-15-000-040 and AMM 75-41-15-400-040.
   (10) If nothing is found:
   (11) Do a check for correct installation and sealing of the TCC sensor(s) AMM 73-21-70-400-001:
  • replace the gasket seal if suspect.
   (12) Do a check for correct torquing and sealing of the borescope plugs located on the HP compressor, HP and LP turbines and combustor case.
   (13) Do a check for correct installation and sealing of the T3 sensor on the combustor case AMM 77-23-10-400-001:
  • replace the gasket seal if suspect.
   (14) Do a check for correct torquing and sealing of the 2 LPT pipes fitted at 11:30 and 2:30 on the HPT case:
  • replace the gasket seal if suspect.
   (15) Do a check for correct torquing and sealing of the cover plates and bleed bias adaptor installed on the combustor case just upfront of the fuel manifold:
  • replace the gasket seal if suspect.
   (16) If no evidence of hot air leaks from the engine is found:
  • do one of the following procedures for leakage identification (leakage identification with engine at idle using aluminum foil or leakage identification with engine motoring or leakage identification with engine at idle using leak developer).
Subtask 75-41-00-810-064-A ** ON A/C NOT FOR ALL
B. Leakage Identification at Idle using Aluminum Foil.
NOTE: This procedure is mainly applicable if you suspect a leak located at a piping or duct joint.
   (1) Install aluminum foils around all pneumatic bleed ducts and engine air piping connections.
   (2) Close the thrust reverser doors AMM 78-36-00-410-040.
   (3) Do a minimum idle leak check AMM 71-00-00-710-006.
  • On the AIR COND panel 30VU, push the ENG 2 BLEED pushbutton switch (4HA2) to operate the engine bleed system.
  • On the ANTI-ICE section of the panel 25VU, push the ANTI ICE/ENG 2 pushbutton switch (2DN2) to operate the engine anti-ice system.
   (4) Stop the engine AMM 71-00-00-710-028.
   (5) Open the thrust reverser doors AMM 78-36-00-010-040.
   (6) Do a visual inspection of the aluminum foil condition. Correct the hot air leaks where applicable.
   (7) If no leak identified:
  • repeat the inspection of the aluminum foils after a few flights.
Subtask 75-41-00-810-065-A ** ON A/C NOT FOR ALL
C. Leakage Identification with Engine Motoring.
CAUTION: POSITIVE DELTA PRESSURE IS NEEDED TO ENSURE FULL PROOFNESS OF THE SUMPS, WITH THE FAN STRAPPED THERE IS NO DELTA PRESSURE ON THE FORWARD SUMP, THEREFORE THERE IS A POTENTIAL RISK OF OIL LEAK IN THE PRIMARY FLOW. AN ENGINE RUN IS RECOMMENDED TO ENSURE THAT THERE IS NO OIL ODOURS/FUMES IN THE CABIN.
   (1) Secure the fan rotor blades with straps.
NOTE: Use straps between one fan blade and a fan frame strut at two locations to block the rotation of the fan rotor. Make sure no metallic locking device is in contact with the fan blade, the OGV or the fan frame strut to avoid damage.
   (2) Do a dry motoring of the engine for 2 minutes AMM 71-00-00-710-001.
NOTE: Several air motoring runs may be required to allow all checks to be done per next steps.
   (3) While the engine is motoring, spray a soap base leak-tek 16-OX (Material No.CP2170) on all hardware connections (ducts, pipes, valves, sensor pads, fuel nozzle pads) and look for evidence of an air leak.
NOTE: Two mechanics are required (one located on each side of the engine core) to properly perform this task.
   (4) If a leak developer is not available, an air leak can usually be detected by a tactile test (an air stream can be felt by hand).
   (5) Correct the hot air leaks where applicable.
   (6) Remove the straps from the fan rotor blades.
   (7) Do an engine run to ensure there is no oil odour neither smoke in the cabin.
     (a) Start the engine, Let the engine run at idle for 5 minutes AMM 71-00-00-710-003.
     (b) After five minutes from engine start, do the following
       1 Press the corresponding engine BLEED pushbutton switch to operate the engine bleed system.
       2 Make sure that Pressure Regulating Valve (PRV) and High Pressure Valve (HPV) are open on ECAM BLEED page with engine running at this speed.
     (c) Turn the cross bleed valve rotary selector to AUTO position.
       1 Press the PACK 1 and 2 pushbutton switches to operate the air conditioning packs.
       2 Make sure that the OFF legend of the PACKS 1 and 2 pushbutton switches go off.
       3 Let the engine operating at idle for 5 additional minutes
       4 Check for evidence of oil odour/smoke in the cabin.
  • If evidence is found, continue to operate the engine at idle until no odour/smoke remains in the cabin.
  • After 10 minutes engine running, if continuous odor/smoke remains in the cabin, shutdown the engine (note that the APU Bleed valve must be open before engine shutdown) AMM 71-00-00-710-028 and decontaminate the Environmental Control System (ECS):
  • when Ambient Air Temperature is below 24 deg.C (75.20 deg.F) AMM 21-00-00-615-001
  • when Ambient Air Temperature is above 24 deg.C (75.20 deg.F) AMM 21-00-00-615-002
     (d) If no evidence is found, shutdown the engine AMM 71-00-00-710-028.
Subtask 75-41-00-810-066-A ** ON A/C NOT FOR ALL
D. Leakage Identification at Idle using Leak Developer.
   (1) Apply a leak developer Ardrox 9D4A (Material No.CP3010) around duct/air pipe joints and on valves, sensor seatings on combustor, HP compressor and turbine cases.
   (2) Do a minimum idle leak check AMM 71-00-00-710-006.
  • On the AIR COND panel 30VU, push the ENG 2 BLEED pushbutton switch (4HA2) to operate the engine bleed system.
  • On the ANTI-ICE section of the panel 25VU, push the ANTI ICE/ENG 2 pushbutton switch (2DN2) to operate the engine anti-ice system.
   (3) Stop the engine AMM 71-00-00-710-028
   (4) Do a visual inspection of the hardware and check for evidence of an air leak. Correct the hot air leaks where applicable.
  • Remove the material used to check leaks.
Subtask 75-41-00-810-067-A ** ON A/C NOT FOR ALL
E. If the fault continues or if no leak is found:
   (1) If the fault continues:
  • Do a resistance and insulation check of the electrical wiring between the nacelle temperature sensor (13KS2) and the EIU2 (1KS2) ASM 732507. The wiring resistance must be less than 2.4 ohms. Repair the aircraft wiring as required.
   (2) If nothing is found:
   (3) If the fault continues:
Subtask 75-41-00-810-055-B ** ON A/C NOT FOR ALL
F. Do the following checks:
NOTE: The maintenance message CHECK HOT AIR LEAKS ENG2 is generated and the advisory for nacelle temperature is flashing green on the upper ECAM if the air temperature at the top of the core compartment area is higher than 240 deg.C (464 deg.F).
   (1) Open both reverser cowls AMM 78-36-00-010-040.
   (2) Do a check for hot air leaks from the ECS :
  • make sure that the engine bleed ducts are in the correct condition and correctly installed (ECS and engine bleed ducts and pneumatic valves). Pay particular attention to clamp installation.
   (3) Do a check for evidence of overheat on the inner wall of both reverser cowls. If hot spots are visible, do a check for leaks in the area next to the spot.
   (4) Do a check for excessive presence of black deposit streaks on the hot section of the engine. If black streaks are visible, do a check for leaks in the area next to the spot.
   (5) Make sure that the 12 o'clock EGT probe deflector is correctly installed.
NOTE: The purpose of this deflector is to avoid EGT probe hot air impingement onto the nacelle temperature sensor.
   (6) Do a check of the cooling holes in the inner wall of the reverser cowls for blockage.
   (7) Do a check for proper installation of all engine and bleed valves located in the core compartment.
   (8) Do a visual check for cracks in the combustor casing, HP compressor casing and turbine casing.
   (9) Do a visual inspection of the nacelle temperature sensor and wiring for any signs of external damage. Do a check on connectors of the nacelle temperature sensor (13KS2) and associated harness for contamination/corrosion and for damaged pins. Clean repair wiring or replace the sensor as required AMM 75-41-15-000-041 and AMM 75-41-15-400-041.
   (10) If nothing is found:
   (11) Do a check for correct installation and sealing of the TCC sensor(s) AMM 73-21-70-400-001:
  • replace the gasket seal if suspect.
   (12) Do a check for correct torquing and sealing of the borescope plugs located on the HP compressor, HP and LP turbines and combustor case.
   (13) Do a check for correct installation and sealing of the T3 sensor on the combustor case AMM 77-23-10-400-002:
  • replace the gasket seal if suspect.
   (14) Do a check for correct torquing and sealing of the 2 LPT pipes fitted at 11:30 and 2:30 on the HPT case:
  • replace the gasket seal if suspect.
   (15) Do a check for correct torquing and sealing of the cover plates and bleed bias adaptor installed on the combustor case just upfront of the fuel manifold:
  • replace the gasket seal if suspect.
   (16) If no evidence of hot air leaks from the engine is found:
  • do one of the following procedures for leakage identification (leakage identification with engine at idle using aluminum foil or leakage identification with engine motoring or leakage identification with engine at idle using leak developer).
Subtask 75-41-00-810-064-B ** ON A/C NOT FOR ALL
G. Leakage Identification at Idle using Aluminum Foil.
NOTE: This procedure is mainly applicable if you suspect a leak located at a piping or duct joint.
   (1) Install aluminum foils around all pneumatic bleed ducts and engine air piping connections.
   (2) Close the thrust reverser doors AMM 78-36-00-410-040.
   (3) Do a minimum idle leak check AMM 71-00-00-710-006.
  • On the AIR COND panel 30VU, push the ENG 2 BLEED pushbutton switch (4HA2) to operate the engine bleed system.
  • On the ANTI-ICE section of the panel 25VU, push the ANTI ICE/ENG 2 pushbutton switch (2DN2) to operate the engine anti-ice system.
   (4) Stop the engine AMM 71-00-00-710-028.
   (5) Open the thrust reverser doors AMM 78-36-00-010-040.
   (6) Do a visual inspection of the aluminum foil condition. Correct the hot air leaks where applicable.
   (7) If no leak identified:
  • repeat the inspection of the aluminum foils after a few flights.
Subtask 75-41-00-810-065-B ** ON A/C NOT FOR ALL
H. Leakage Identification with Engine Motoring.
CAUTION: POSITIVE DELTA PRESSURE IS NEEDED TO ENSURE FULL PROOFNESS OF THE SUMPS, WITH THE FAN STRAPPED THERE IS NO DELTA PRESSURE ON THE FORWARD SUMP, THEREFORE THERE IS A POTENTIAL RISK OF OIL LEAK IN THE PRIMARY FLOW. AN ENGINE RUN IS RECOMMENDED TO ENSURE THAT THERE IS NO OIL ODOURS/FUMES IN THE CABIN.
   (1) Secure the fan rotor blades with straps.
NOTE: Use straps between one fan blade and a fan frame strut at two locations to block the rotation of the fan rotor. Make sure no metallic locking device is in contact with the fan blade, the OGV or the fan frame strut to avoid damage.
   (2) Do a dry motoring of the engine for 2 minutes AMM 71-00-00-710-001.
NOTE: Several air motoring runs may be required to allow all checks to be done per next steps.
   (3) While the engine is motoring, spray a soap base leak-tek 16-OX (Material No.CP2170) on all hardware connections (ducts, pipes, valves, sensor pads, fuel nozzle pads) and look for evidence of an air leak.
NOTE: Two mechanics are required (one located on each side of the engine core) to properly perform this task.
   (4) If a leak developer is not available, an air leak can usually be detected by a tactile test (an air stream can be felt by hand).
   (5) Correct the hot air leaks where applicable.
   (6) Remove the straps from the fan rotor blades.
   (7) Do an engine run to ensure there is no oil odour neither smoke in the cabin.
     (a) Start the engine, Let the engine run at idle for 5 minutes AMM 71-00-00-710-003.
     (b) After five minutes from engine start, do the following:
       1 Press the corresponding engine BLEED pushbutton switch to operate the engine bleed system.
       2 Make sure that Pressure Regulating Valve (PRV) and High Pressure Valve (HPV) are open on ECAM BLEED page with engine running at this speed
     (c) Turn the cross bleed valve rotary selector to AUTO position.
       1 Press the PACK 1 and 2 pushbutton switches to operate the air conditioning packs.
       2 Make sure that the OFF legend of the PACKS 1 and 2 pushbutton switches go off.
       3 Let the engine operating at idle for 5 additional minutes
       4 Check for evidence of oil odour/smoke in the cabin.
  • If evidence is found, continue to operate the engine at idle until no odour/smoke remains in the cabin.
  • After 10 minutes engine running, if continuous odor/smoke remains in the cabin, shutdown the engine (note that the APU Bleed valve must be open before engine shutdown) AMM 71-00-00-710-028 and decontaminate the Environmental Control System (ECS):
  • when Ambient Air Temperature is below 24 deg.C (75.20 deg.F) AMM 21-00-00-615-001
  • when Ambient Air Temperature is above 24 deg.C (75.20 deg.F) AMM 21-00-00-615-002
     (d) If no evidence is found, shutdown the engine AMM 71-00-00-710-028.
Subtask 75-41-00-810-066-B ** ON A/C NOT FOR ALL
I. Leakage Identification at Idle using Leak Developer.
   (1) Apply a leak developer Ardrox 9D4A (Material No.CP3010) around duct/air pipe joints and on valves, sensor seatings on combustor, HP compressor and turbine cases.
   (2) Do a minimum idle leak check AMM 71-00-00-710-006.
  • On the AIR COND panel 30VU, push the ENG 2 BLEED pushbutton switch (4HA2) to operate the engine bleed system.
  • On the ANTI-ICE section of the panel 25VU, push the ANTI ICE/ENG 2 pushbutton switch (2DN2) to operate the engine anti-ice system.
   (3) Stop the engine AMM 71-00-00-710-028
   (4) Do a visual inspection of the hardware and check for evidence of an air leak. Correct the hot air leaks where applicable.
  • Remove the material used to check leaks.
Subtask 75-41-00-810-067-B ** ON A/C NOT FOR ALL
J. If the fault continues or if no leak is found:
   (1) If the fault continues:
  • Do a resistance and insulation check of the electrical wiring between the nacelle temperature sensor (13KS2) and the EIU2 (1KS2) ASM 732507. The wiring resistance must be less than 2.4 ohms. Repair the aircraft wiring as required.
   (2) If nothing is found:
   (3) If the fault continues:
Subtask 75-41-00-710-061-A ** ON A/C NOT FOR ALL
K. Do a check that the fault does not continue on subsequent flight.
   (1) If the fault continues:
  • repeat the fault isolation procedure.
[Rev.8 from Aug 2018] 2026.04.04 04:39:09 UTC
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