W DOC AIRBUS | TSM A320F

EGT Higher than the Limit on Engine 2 (No Surge or Stall) (Above Idle)


1. Possible Causes
· VSV mechanism
· HP Compressor
· HPT Blades
· LP Turbine
2 Job Set-up Information
A. Referenced Information
REFERENCE DESIGNATION
75-00-00-810-804-B Hung Start/Hot Start/Stall - Effect of HPC Bleed System on Engine Operation
75-30-00-810-844-A Failure of the Variable Stator Vane Actuator on Engine 2, Channel A
75-30-00-810-846-A Failure of the Variable Stator Vane Actuator on Engine 2, Channel B
REFERENCE DESIGNATION
Ref. AMM 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied from the External
Power
Ref. AMM 31-60-00-860-002 EIS Stop Procedure
Ref. AMM 72-00-00-200-012 Borescope Inspection of the LP Turbine
Ref. AMM 72-00-00-200-013 Borescope Inspection of inside of Combustion Chamber and HP turbine
stage 1 Vanes
Ref. AMM 72-00-00-200-014 Borescope Inspection of the Stage 1 High Pressure Turbine (HPT)
Blades and Duct Segments
Ref. AMM 72-00-00-200-015 Borescope Inspection of the Stage 2 HPT Blades and Duct Segments
Ref. AMM 72-00-00-200-016 Inspection of the HP Compressor
Ref. AMM 72-32-60-200-011 Inspection of the LPC Bleed Duct Seal
Ref. AMM 75-32-42-200-010 Inspection of the VSV Mechanism
Ref. AMM 75-32-51-700-010 Functional Test of the HPC Stage 7 Solenoid Valve with Test Set
IAE2R19437
Ref. AMM 75-32-52-700-011 Functional Test of the HPC Stage 7 Bleed Valve with Test Set
IAE2R19437
Ref. AMM 75-32-53-700-010 Functional Test of the HPC Stage 10 Solenoid Valve with Test Set
IAE2R19437
Ref. AMM 75-32-54-700-011 Functional Test of the HPC Stage 10 Bleed Valve with Test Set
IAE2R19437
Ref. AMM 77-00-00-710-041 Reset of the N1, N2 and EGT Max Pointers
Ref. AMM 77-21-43-300-801 EGT Harness - Wire Braid Repair (VRS3812)
Ref. AMM 77-21-43-350-801 EGT Harness and Junction Box Dry-Out Procedure
Ref. AMM 77-21-43-700-010 Functional Test of the EGT Harness, Junction Box and Thermocouples
70-00-00-03-13 STANDARD PRACTICES - ENGINE - GENERAL - TASK SUPPORTING
DATA
EGT Overtemperature Limits (V2530-A5, V2533-A5) (Idle and above) SHEET 1
EGT Overtemperature Limits (V2500-A1, V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5) (Idle
and above) SHEET 1
Turbine Cooling Air Supply Tubes Locations SHEET 1
Figure 77(IAE)-00-00-991-00500-B / SHEET 1/1 - EGT Overtemperature Limits (V2530-A5, V2533-A5)
(Idle and above) not printed, as per printing preferences
Figure 77(IAE)-00-00-991-00500-A / SHEET 1/1 - EGT Overtemperature Limits (V2500-A1, V2522-A5,
V2524-A5, V2527-A5, V2527E-A5, V2527M-A5) (Idle and above) not printed, as per printing preferences
Figure 77(IAE)-00-00-991-00600-A / SHEET 1/1 - Turbine Cooling Air Supply Tubes Locations not
printed, as per printing preferences
3. Fault Confirmation
Subtask 77-00-00-710-238-A
A. Test
(1) Get the EIS (DMC1) ENGINE OVER SPD/TEMP menu on the MCDU Ref. AMM 77-00-00-710-041 .
(2) On the EIS (DMC1) ENGINE OVER SPD/TEMP menu, push the line key adjacent to EGT E2 to get
the EGT2 OVERTEMP menu.
(3) On the EGT2 OVERTEMP menu, get the overtemperature record. If the record is not available, see
the log book or other available records to find the time and magnitude of overtemperature.
4. Fault Isolation
(Ref. Fig. EGT Overtemperature Limits (V2530-A5, V2533-A5) (Idle and above) SHEET 1)
Figure 77(IAE)-00-00-991-00500-B / SHEET 1/1 - EGT Overtemperature Limits (V2530-A5, V2533-A5) (Idle
and above) not printed, as per printing preferences
(Ref. Fig. EGT Overtemperature Limits (V2500-A1, V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527MA5)
(Idle and above) SHEET 1)
Figure 77(IAE)-00-00-991-00500-A / SHEET 1/1 - EGT Overtemperature Limits (V2500-A1, V2522-A5,
V2524-A5, V2527-A5, V2527E-A5, V2527M-A5) (Idle and above) not printed, as per printing preferences
PRE SB 73-1104 for A/C 0101-0102, 0951-0951
Subtask 77-00-00-810-206-A
CAUTION: IF YOU DO NOT OBEY THE INSTRUCTIONS THAT FOLLOW, DAMAGE TO THE ENGINE
CAN BE THE RESULT.
A. Record the Following Information
NOTE: If the cause of the overtemperature is determined during this procedure, it is permitted to stop the
troubleshooting.
NOTE: If troubleshooting for surge or stall has required a borescope inspection the steps to borescope the
previously inspected components may be skipped.
(1) Engine serial number.
NOTE: If engine serial number displayed on MCDU is in the range between 13191 and 15000, then
add 5000 to this value to get the actual engine serial number.
(2) Maximum temperature.
(3) Time of overtemperature above 635 deg.C (1175 deg.F).
NOTE: If the fault symptom ENG2-EGT more than 610 deg.C (1130 deg.F) was identified by crew observation,
you must also record the time engine was above 610 deg.C (1130 deg.F).
** ON A/C
POST SB 73-1104 for A/C 0101-0102, 0951-0951
Subtask 77-00-00-810-206-B
CAUTION: IF YOU DO NOT OBEY THE INSTRUCTIONS THAT FOLLOW, DAMAGE TO THE ENGINE
CAN BE THE RESULT.
A. Record the Following Information
NOTE: If the cause of the overtemperature is determined during this procedure, it is permitted to stop the
troubleshooting.
NOTE: If troubleshooting for surge or stall has required a borescope inspection the steps to borescope the
previously inspected components may be skipped.
(1) Engine serial number.
(2) Maximum temperature.
(3) Time of overtemperature above 635 deg.C (1175 deg.F).
NOTE: If the fault symptom ENG2-EGT more than 610 deg.C (1130 deg.F) was identified by crew observation,
you must also record the time engine was above 610 deg.C (1130 deg.F).
Subtask 77-00-00-810-238-A
B. Find out if the EGT overtemperature was because of indication system error. If the condition that follows is
met continue with step C otherwise continue with step D.
(1) EGT fluctuates with no related change in N1 or fuel consumption.
NOTE: A general trend of declining EGT margin associated with a rise in fuel consumption could be a
sign of deteriorating HPT stage 1 outer air seals.
Subtask 77-00-00-810-239-A
C. Do the steps that follow if any of the conditions in step B occurred.
(1) Do a visual inspection of the EGT harness, junction box and thermocouples.
(a) If the EGT harness is chafed, repair per Ref. AMM 77-21-43-300-801 .
(b) If there is moisture accumulation in the junction box, use hot air or nitrogen to remove the
moisture Ref. AMM 77-21-43-350-801 .
(c) If there are broken stud short circuits because of misplaced safety wire or physical damage other
than harness chafing, remove, replace, or correct the applicable hardware.
(2) If you do not find a problem, do electrical checks of the EGT system Ref. AMM 77-21-43-700-010 .
(3) If you find a problem with the EGT hardware, replace the applicable hardware and return the engine
to service.
(4) If the EGT hardware is serviceable, continue to step D.
Subtask 77-00-00-810-240-A
D. Refer to Overtemperature Limits for Necessary Action
NOTE: If Exhaust Gas Temperature (EGT) overtemperature occurs in area A1 during take-off through
3000 feet above ground level and the conditions that follow are true, troubleshooting by step E can
be delayed for 5 cycles.
(1) Outside Air Temperature (OAT) is more than 30 deg.C (86.00 deg.F).
(2) Maximum EGT overtemperature is 10 deg.C (50.00 deg.F) or less.
(3) EGT overtemperature duration is 30 seconds or less.
(4) EGT at normal and expected readings (no elevated readings) during the remainder of the flight.
(5) No other related fault messages (except EGT overtemperature).
(6) Examination of the exhaust area of the engine found no signs of damage.
Subtask 77-00-00-810-241-A
E. Necessary Action
(1) If overtemperature was in the transient area for five seconds or less, no action is necessary.
(2) If overtemperature was in area A1 or A2 with one or more events, or if overtemperature was in area B
with less than ten EGT overtemperature events, perform the troubleshooting in step F.
(3) If overtemperature was in area B with ten or more EGT overtemperature events or area C with one or
more events, remove the engine from service.
NOTE: It is permissible to ferry-fly a non-revenue engine with overtemperature to a maintenance
base, but a visual inspection and a hot section borescope inspection Ref.
AMM 72-00-00-200-013 Ref. AMM 72-00-00-200-014 and Ref. AMM 72-00-00-200-015
must show the hardware is within limits and shows no visual damage. This condition is permissible
for only one engine per aircraft.
Subtask 77-00-00-810-208-A
F. Do the steps that follow to find the cause of Exhaust Gas Temperature (EGT) that is too high.
(1) Examine the turbine exhaust case for debris.
(a) If debris is found, remove the engine from service.
(2) Read the LAST LEG REPORT of the FADEC 2A and the FADEC 2B menu on the MCDU
(Ref. TSM 70-00-00-03) and make a record of the maintenance message.
(a) If you have received the following maintenance message CHA VSV ACT/HC/EEC2 FADEC 2A:
· Do the following task (Ref. TSM 75-30-00-810-844) as necessary by the engine build
standard.
(b) If you have received the following maintenance message CHB VSV ACT/HC/EEC2 for FADEC
2B:
· Do the following task (Ref. TSM 75-30-00-810-846) as necessary by the engine build
standard.
(c) If you do not receive one of the above fault messages go to the next step.
(3) Inspect the VSV mechanism Ref. AMM 75-32-42-200-010 .
(4) Do the functional check of the bleed valve and solenoid operation on engine 2 Ref.
AMM 75-32-51-700-010 Ref. AMM 75-32-52-700-011 Ref. AMM 75-32-53-700-010 and Ref.
AMM 75-32-54-700-011 .
NOTE: Refer to (Ref. TSM 75-00-00-810-804) for more information on the bleed valve effects on engine
operation.
(5) Examine for broken turbine cooling air supply tubes.
(Ref. Fig. Turbine Cooling Air Supply Tubes Locations SHEET 1)
(6) Do an inspection of the Low Pressure (LP) compressor bleed duct for a detached seal Ref.
AMM 72-32-60-200-011 .
(7) Borescope the gaspath:
(a) Borescope inspect the HP Compressor Ref. AMM 72-00-00-200-016 .
(b) Borescope inspect the Combustion Chamber Ref. AMM 72-00-00-200-013 .
(c) Borescope inspect the HPT Blades .
1 Borescope inspect the Stage 1 High Pressure Turbine (HPT) Blades Ref.
AMM 72-00-00-200-014 .
2 Borescope inspect the Stage 2 HPT Blades Ref. AMM 72-00-00-200-015 .
(d) Borescope inspect the LP Turbine Ref. AMM 72-00-00-200-012 .
(8) Examine the EGT margin as follows:
PRE SBE 72-0483
(a) Do a 360 degree borescope inspection of the stage 1 HPT duct segment Ref.
AMM 72-00-00-200-014 if one or more of the conditions that follow are true:
1 EGT margin is less than 45 deg.C (113 deg.F) and the engine has accumulated more than
6000 hours or more than 3500 cycles.
2 EGT margin is less than 10 deg.C (50 deg.F).
3 EGT margin is not available.
END of PRE SBE 72-0483
POST SBE 72-0423
(b) Do a 360 degree borescope inspection of the stage 1 HPT duct segments Ref.
AMM 72-00-00-200-014 if one or more of the conditions that follow are true:
1 EGT margin is less than 10 deg.C (50 deg.F).
2 EGT margin is not available.
NOTE: If a 360 degree borescope inspection of the stage 1 HPT duct segment has been
done within 300 hours and the engine is not on a reduced BSI interval for stage 1
HPT duct segment distress, then this borescope inspection is not necessary.
END of POST SBE 72-0483
(9) If you do not know the cause of EGT that is too high, do a functional test of the EGT harness and
junction box Ref. AMM 77-21-43-700-010 .
5. Close-up
Subtask 77-00-00-860-091-A
A. Put the aircraft back to its initial configuration.
(1) On the ECAM control panel, set the UPPER DISPLAY and LOWER DISPLAY potentiometers to OFF.
Ref. AMM 31-60-00-860-002 .
(2) De-energize the aircraft electrical circuits
Ref. AMM 24-41-00-862-002 . [Rev.6 from Feb 2017] 2026.04.04 04:37:49 UTC
"WTRUIB" 2025