W DOC AIRBUS | TSM A320F

EGT Overlimit on Engine 1 or 2

TASK 77-00-00-810-849-A
EGT Overlimit on Engine 1 or 2

1. Possible Causes
  • engine
  • VBV system
  • VSV system
  • IP Bleed Check Valve
  • J13 harness
  • ECU [4000KS]
  • HPTACC valve
  • HJ13 harness
2. Job Set-up Information
 A. Fixtures, Tools, Test and Support Equipment
REFERENCE
QTY
DESIGNATION
No specific
AR
BRUSH - BRISTLED
 B. Consumable Materials
REFERENCE
DESIGNATION
(Material No.CP2010)
white spirit
(Material No.CP2011)
stoddard solvent
 C. Referenced Information
REFERENCE
DESIGNATION
TSM TASK 36-11-00-810-829-A
Loss of the Non-Return Function and Temperature Limitation Function of the Bleed Pressure-Regulator Valve of the Engine 1
TSM TASK 36-11-00-810-830-A
Loss of the Non-Return Function and Temperature Limitation Function of the Bleed Pressure-Regulator Valve of the Engine 2
AMM 31-32-00-860-001
Procedure to Get Access to the SYSTEM REPORT/TEST Menu Page
AMM 31-69-00-00-
AMM 36-11-00-710-001
Operational Test to read the CURRENT STATUS of the Engine Bleed Air System
AMM 72-00-00-100-009
Washing of the Engine Gas Path with Pure Water
AMM 72-00-00-100-026
Washing of the Engine Gas Path with Pure Water
AMM 72-00-00-200-001
Inspection/Check of Foreign Object Damage (FOD) (Bird Strike Included)
AMM 72-00-00-200-003
Procedure After the Engine has Exceeded the Operational Limits
AMM 72-00-00-200-006
Inspection/Check of Foreign Object Damage (FOD) (Bird Strike Included)
AMM 72-00-00-200-008
Inspection/Check After the Engine has Exceeded the Operational Limits
AMM 73-11-40-000-001
Removal of the Fuel Nozzles
AMM 73-11-40-000-002
Removal of the Fuel Nozzle for SAC Engines
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 73-21-50-000-005
Removal of the CJ13 Harness
AMM 73-21-50-000-012
Removal of the J13 Harness
AMM 73-21-50-000-029
Removal of the CJ13 Harness
AMM 73-21-50-000-046
Removal of the HJ13 Harness for SAC Engines
AMM 73-21-50-210-001
Visual Inspection of the Wiring Harness
AMM 73-21-50-210-002
Visual Inspection of the Wiring Harnesses
AMM 73-21-50-400-005
Installation of the CJ13 Harness
AMM 73-21-50-400-012
Installation of the J13 Harness
AMM 73-21-50-400-029
Installation of the CJ13 Harness
AMM 73-21-50-400-046
Installation of the HJ13 Harness for SAC Engines
AMM 73-21-60-000-001
Removal of the Electronic Control Unit (ECU)
AMM 73-21-60-400-001
Installation of the Electronic Control Unit (ECU)
AMM 73-21-60-740-007
Correct Time Limited Faults (Non Asterisked) of the Engine Scheduled Maintenance Report
AMM 73-21-60-740-027
Read the Specific Data Report
AMM 73-29-00-710-040
Operational Test of the FADEC on the ground (with Engine Motoring)
AMM 75-21-10-000-002
Removal of the High Pressure Turbine Active Clearance Control (HPTACC) Valve
AMM 75-21-10-200-002
Inspection/Check of the High Pressure Turbine Active Clearance Control Valve (HPTACC)
AMM 75-21-10-400-002
Installation of the High Pressure Turbine Active Clearance Control (HPTACC) Valve
AMM 75-31-00-210-001
Visual Inspection of the Variable Bleed Valve (VBV) System
AMM 75-31-00-210-002
Visual Inspection of the Variable Bleed Valve (VBV) System
AMM 75-32-10-210-001
Visual Inspection of the Variable Stator Vane Actuator
AMM 75-32-10-210-002
Inspection of the Variable Stator Vane Actuator
AMM 77-00-00-710-044
Read of the N1,N2 and EGT Max Pointers
3. Fault Confirmation
Subtask 77-00-00-710-123-A ** ON A/C NOT FOR ALL
A. Test
   (1) Read the DMU exceedence report and the DMC Max Value Report AMM 77-00-00-710-044 to note the max EGT value that was recorded during the event as well as the duration of the exceedence (if available).
  • If none of these reports are available, get the data from the AIDS or the DFDR.
NOTE: There are many causes that can lead to an EGT overtemperature, such as engine deterioration, engine stall, temperature inversion during take off, engine bleed selected during take off after throttle push, engine warm-up not sufficient before take off, FOD, dirty compressor airfoils, etc...
NOTE: Trend Monitoring should be reviewed first to determine whether the EGT overlimit can be explained based on the level of deterioration of the engine or based on the contributing conditions explained in the above note. Also, a shift on Trend Monitoring only noted on EGT and not affecting N2 and VSV should definitively concentrate the troubleshooting on the EGT indication system.
NOTE: The ECAM warning is triggered if the indicated EGT is greater than 890 deg.C.
Subtask 77-00-00-710-123-C ** ON A/C NOT FOR ALL
A. Test
   (1) Read the DMU exceedence report and the Specific Data Report AMM 73-21-60-740-027 to note the max EGT value that was recorded during the event as well as the duration of the exceedence (if available).
  • If none of these reports are available, get the data from the AIDS or the DFDR.
NOTE: There are many causes that can lead to an EGT overtemperature, such as engine deterioration, engine stall, temperature inversion during take off, engine bleed selected during take off after throttle push, engine warm-up not sufficient before take off, FOD, dirty compressor airfoils, etc...
NOTE: Trend Monitoring should be reviewed first to determine whether the EGT overlimit can be explained based on the level of deterioration of the engine or based on the contributing conditions explained in the above note. Also, a shift on Trend Monitoring only noted on EGT and not affecting N2 and VSV should definitively concentrate the troubleshooting on the EGT indication system.
NOTE: The ECAM warning is triggered if the indicated EGT is greater than 950 deg.C during take-off, and greater than 915°C during climb or cruise.
4. Fault Isolation
Subtask 77-00-00-810-101-A ** ON A/C NOT FOR ALL
A. If the fault symptom is identified by the ECAM warning EGT OVER LIMIT, if the EGT overlimit is confirmed through the data contained in the DMC report AMM 31-69-00-00- or AIDS data, or DFDR or QAR data and if there was no stall reported by the Crew or ECAM warning ENG1(2) STALL:
   (1) Do the procedure after the engine has exceeded the operational limits AMM 72-00-00-200-003.
     (a) If the engine is still operable, do the following:
       1 If nothing is found but the EGT overlimit can be explained due to a TAT inversion during take off or a warm-up before take off not sufficient:
  • no additional maintenance is required.
       2 If nothing is found but the EGT overlimit can be explained due to engine deterioration:
       3 Do a check of the Post Flight Report (PFR), of the Scheduled Maintenance Report (SMR) or Class 3 report AMM 73-21-60-740-007 and of the FADEC Last Leg Report for FMV, VBV, T495, T25, N2 SNSR, ECU, HMU, VSV, PS3, PRESS REG-V, HP BLEED-V failure messages.
         a if a failure message is present:
  • do the related troubleshooting procedure.
         b if nothing is found, continue the troubleshooting as follows:
     (b) Do a visual inspection of the VBV system AMM 75-31-00-210-001. Check for VBV flexible shaft failure and for offset between the VBV actuator doors (doors set in different positions).
       1 If damage is found:
  • repair as necessary.
       2 If nothing is found, continue the troubleshooting as follows:
     (c) Do an inspection/check for Foreign Object Damage AMM 72-00-00-200-001 .
       1 If damage is found:
  • repair as necessary.
       2 If nothing is found, continue the troubleshooting as follows:
     (d) Do a visual inspection of the VSV system AMM 75-32-10-210-001 .
       1 If damage is found:
  • repair as necessary.
       2 If nothing is found, continue the troubleshooting as follows:
     (e) Do a visual inspection of the IP Bleed Check Valve for free operation and condition of the flappers AMM 36-11-00-710-001 .
       1 If damage is found:
  • repair as necessary.
       2 If nothing is found and the cause of the EGT overlimit cannot be explained (troubleshooting preferably to be done on a cold engine), continue the troubleshooting as follows:
     (f) If nothing is found:
     (g) Disconnect the J13 harness from the ECU (4000KS) and visually examine the ECU receptacle and the harness connector for damaged pins or contamination AMM 73-21-50-210-001.
       1 If the J13 harness connector or the ECU receptacle is damaged:
  • repair as required.
       2 If nothing is found, continue the troubleshooting as follows:
     (h) Do an electrical resistance test through the J13 harness between:
. pins 12 and 13 (1 to 10 ohms)
. pins 12 and 24 (> 20 megohms)
. pin 12 and the ground (> 20 megohms).
       1 If the resistances are out of the specified limits:
  • Disconnect the CJ13 harness from the T495 main junction box (located in the left core compartment) and visually examine the T495 junction box receptacle and the CJ13 harness connector for damaged pins or contamination AMM 73-21-50-210-001.
    Clean the connector and the receptacle using a BRUSH - BRISTLED and stoddard solvent (Material No.CP2011) or white spirit (Material No.CP2010) .
         a If nothing is found:
  • Do an electrical resistance test through the main junction box between:
    . pins A and B (1 to 10 ohms)
    . pin A and the ground (> 20 megohms)
  • If the resistances are in the specified limits:
    - reconnect the CJ13 harness to the main junction box, and repeat the electrical resistance test through the J13 harness at the ECU connector between:
    . pins 12 and 13 (1 to 10 ohms)
    . pins 12 and 24 (> 20 megohms)
    . pin 12 and the ground (> 20 megohms).
    * if the resistances are in the specified limits:
    - no further maintenance is required.
    * if the resistances are out of the specified limits:
    - replace the CJ13 harness AMM 73-21-50-000-005 and AMM 73-21-50-400-005.
    ** if the fault continues during subsequent flights:
    - replace the J13 harness AMM 73-21-50-000-012 and AMM 73-21-50-400-012;
       2 If the resistances are in the specified limits:
  • Disconnect the CJ13 harness from the T495 main junction box (located in the left core compartment) and visually examine the T495 junction box receptacle and the CJ13 harness connector for damaged pins or contamination AMM 73-21-50-210-001.
    Clean the connector and the receptacle using a BRUSH - BRISTLED and stoddard solvent (Material No.CP2011) or white spirit (Material No.CP2010) .
         a Reconnect the CJ13 harness to the main junction box.
     (i) If the fault continues during subsequent flights:
       1 replace the ECU [4000KS] AMM 73-21-60-000-001 and AMM 73-21-60-400-001.
     (j) If the fault continues during subsequent flights:
NOTE: Only if Service Bulletin 73-133 is not incorporated
       1 Replace the 3 fuel nozzles (position 1, 3 and 5) AMM 73-11-40-000-001 and AMM 73-11-40-400-001.
NOTE: Fuel nozzles (position 1, 3 and 5) are the most exposed to contamination in case of fuel manifold coking.
         a If the fault does not continue during subsequent flights:
NOTE: If the EGT exceedence is determined to be caused by fuel manifold coking, then replacement of all other fuel nozzles as well as replacement of the fuel manifolds is required.
Subtask 77-00-00-810-196-A ** ON A/C NOT FOR ALL
B. If the fault symptom is identified by the ECAM warning EGT OVER LIMIT, if the EGT overlimit is confirmed through the data contained in the DMC report(s) or AIDS data, or DFDR data and if there was a stall reported by the Crew or an ECAM warning STALL is printed in the Post Flight Report (PFR):
   (1) Do the procedure after overshoot of the engine operational limits AMM 72-00-00-200-003.
   (2) Do the troubleshooting related to ECAM warning STALL
Subtask 77-00-00-810-197-A ** ON A/C NOT FOR ALL
C. If the fault symptom is identified by the ECAM warning EGT OVER LIMIT and if the EGT overlimit is not confirmed through the data contained in the DMC report(s) AMM 31-69-00-00- or AIDS data, or DFDR data:
   (1) If the FWC part number is 350E017248685, the warning is spurious and should be disregarded. No further maintenance action is required.
Subtask 77-00-00-810-101-C ** ON A/C NOT FOR ALL
D. If the fault symptom is identified by the ECAM warning EGT OVER LIMIT, if the EGT overlimit is confirmed through the data contained in the Specific Data Report AMM 73-21-60-740-027 or AIDS data, or DFDR or QAR data and if there was no stall reported by the Crew or ECAM warning ENG1(2) STALL:
   (1) Do the procedure after the engine has exceeded the operational limits AMM 72-00-00-200-008.
     (a) If the engine is still operable, do the following:
       1 If nothing is found but the EGT overlimit can be explained due to a TAT inversion during take off or a warm-up before take off not sufficient:
  • no additional maintenance is required.
       2 If nothing is found but the EGT overlimit can be explained due to engine deterioration:
       3 Do a check of the Post Flight Report (PFR), of the Scheduled Maintenance Report (SMR) or Class 3 report AMM 73-21-60-740-007 and of the FADEC Last Leg Report for FMV, VBV, T495, T25, N2 SNSR, ECU, HMU, VSV, PS3, PRESS REG-V, HP BLEED-V failure messages.
         a if failure message is present:
  • do the related troubleshooting procedure.
         b if nothing is found, continue the troubleshooting as follows:
       4 Do an inspection check of the HPTACC valve for movement of the ceramic insulators AMM 75-21-10-200-002
         a if there is movement of the ceramic insulators
         b if there is no movement of the ceramic insulators, continue the troubleshooting as follows:
     (b) Do a visual inspection of the VBV system AMM 75-31-00-210-002. Check for VBV flexible shaft failure and for offset between the VBV actuator doors (doors set in different positions).
       1 If damage is found:
  • repair as necessary.
       2 If nothing is found, continue the troubleshooting as follows:
     (c) Do an inspection/check for Foreign Object Damage AMM 72-00-00-200-006 .
       1 If damage is found:
  • repair as necessary.
       2 If nothing is found, continue the troubleshooting as follows:
     (d) Do a visual inspection of the VSV system AMM 75-32-10-210-002 .
       1 If damage is found:
  • repair as necessary.
       2 If nothing is found, continue the troubleshooting as follows:
     (e) Do a visual inspection of the IP Bleed Check Valve for free operation and condition of the flappers AMM 36-11-00-710-001 .
       1 If damage is found:
  • repair as necessary.
       2 If nothing is found and the cause of the EGT overlimit cannot be explained (troubleshooting preferably to be done on a cold engine), continue the troubleshooting as follows:
     (f) If nothing is found:
     (g) Disconnect the HJ13 harness from the ECU (4000KS) and visually examine the ECU receptacle and the harness connector for damaged pins or contamination AMM 73-21-50-210-002.
       1 If the HJ13 harness connector or the ECU receptacle is damaged:
  • repair as required.
       2 If nothing is found, continue the troubleshooting as follows:
     (h) Do an electrical resistance test through the HJ13 harness between:
. pins 12 and 13 (1 to 10 ohms)
. pins 12 and 24 (> 20 megohms)
. pin 12 and the ground (> 20 megohms).
       1 If the resistances are out of the specified limits:
  • Disconnect the CJ13 harness from the T495 main junction box (located in the left core compartment) and visually examine the T495 junction box receptacle and the CJ13 harness connector for damaged pins or contamination AMM 73-21-50-210-002.
    Clean the connector and the receptacle using a BRUSH - BRISTLED and stoddard solvent (Material No.CP2011) or white spirit (Material No.CP2010) .
         a If nothing is found:
  • Do an electrical resistance test through the main junction box between:
    . pins A and B (1 to 10 ohms)
    . pin A and the ground (> 20 megohms)
  • If the resistances are in the specified limits:
    - reconnect the CJ13 harness to the main junction box, and repeat the electrical resistance test through the HJ13 harness at the ECU connector between:
    . pins 12 and 13 (1 to 10 ohms)
    . pins 12 and 24 (> 20 megohms)
    . pin 12 and the ground (> 20 megohms).
    * if the resistances are in the specified limits:
    - no further maintenance is required.
    * if the resistances are out of the specified limits:
    - replace the CJ13 harness AMM 73-21-50-000-029 and AMM 73-21-50-400-029.
    ** if the fault continues during subsequent flights:
    - replace the HJ13 harness AMM 73-21-50-000-046 and AMM 73-21-50-400-046.
       2 If the resistances are in the specified limits:
  • Disconnect the CJ13 harness from the T495 main junction box (located in the left core compartment) and visually examine the T495 junction box receptacle and the CJ13 harness connector for damaged pins or contamination AMM 73-21-50-210-002.
    Clean the connector and the receptacle using a BRUSH - BRISTLED and stoddard solvent (Material No.CP2011) or white spirit (Material No.CP2010) .
         a Reconnect the CJ13 harness to the main junction box.
     (i) If the fault continues during subsequent flights:
       1 replace the ECU [4000KS] AMM 73-21-60-000-001 and AMM 73-21-60-400-001.
     (j) If the fault continues during subsequent flights:
NOTE: Only if Service Bulletin 73-052 is not incorporated
       1 Replace the 3 fuel nozzles (position 1, 3 and 5) AMM 73-11-40-000-002 and AMM 73-11-40-400-002.
NOTE: Fuel nozzles (position 1, 3 and 5) are the most exposed to contamination in case of fuel manifold coking.
         a If the fault does not continue during subsequent flights:
NOTE: If the EGT exceedence is determined to be caused by fuel manifold coking, then replacement of all other fuel nozzles as well as replacement of the fuel manifolds is required.
Subtask 77-00-00-810-196-C ** ON A/C NOT FOR ALL
E. If the fault symptom is identified by the ECAM warning EGT OVER LIMIT, if the EGT overlimit is confirmed through the data contained in the Specific Data Report AMM 73-21-60-740-027 or AIDS data, or DFDR data and if there was a stall reported by the Crew or an ECAM warning STALL is printed in the Post Flight Report (PFR):
   (1) Do the procedure after overshoot of the engine operational limits AMM 72-00-00-200-008.
   (2) Do the troubleshooting related to ECAM warning STALL
Subtask 77-00-00-810-197-C ** ON A/C NOT FOR ALL
F. If the fault symptom is identified by the ECAM warning EGT OVER LIMIT and if the EGT overlimit is not confirmed through the data contained in the Specific Data Report AMM 73-21-60-740-027 or AIDS data, or DFDR data:
   (1) If the FWC part number is 350E017248685, the warning is spurious and should be disregarded. No further maintenance action is required.
Subtask 77-00-00-710-124-A ** ON A/C NOT FOR ALL
G. Do the operational test of the FADEC 1A and 1B on the ground (with engine non motoring) AMM 73-29-00-710-040 unless above troubleshooting requires an other engine test.
   (1) No additionnal maintenance action is required if the fault is not confirmed.
   (2) Repeat the fault isolation procedure if the fault continues.
[Rev.8 from Aug 2018] 2026.04.04 04:37:31 UTC
"WTRUIB" 2025