On A/C All: Reference Designation
On A/C All: Reference Designation
On A/C All: Reference Designation
** ON A/C ALL
TASK 77-00-00-810-817-B
Exhaust Gas Temperature (EGT) Higher than the Limit on Engine 1 (Above Idle)
NOTE: It is acceptable to perform a visual inspection of the engine exhaust for obvious damage or debris that
would be cause for an engine removal before starting this procedure.
1. Possible Causes
· EGT Indication System
· VSV mechanism
· HP Compressor
· Hight Pressure Turbine (HPT) Blades
· LP Turbine
2 Job Set-up Information
A. Referenced Information
REFERENCE DESIGNATION
(Ref. 75-00-00-810-804-B). Hung Start/Hot Start/Stall - Effect of HPC Bleed System on Engine Op-
eration
(Ref. 75-30-00-810-843-A). Failure of the Variable Stator Vane Actuator on Engine 1, Channel A
(Ref. 75-30-00-810-845-A). Failure of the Variable Stator Vane Actuator on Engine 1, Channel B
Ref. AMM 24-41-00-862-002 De-energize the Aircraft Electrical Circuits Supplied from the External
Power
Ref. AMM 31-37-73-01
Ref. AMM 31-60-00-860-002 EIS Stop Procedure
Ref. AMM 71-00-00-710-022 Test No.6 : ELectronic Engine Control (EEC) System Idle Test
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 tur-
bine 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 77-21-43-300-801 EGT Harness - Wire Braid Repair (VRS3812)
Ref. AMM 77-21-43-700-010 Functional Test of the EGT Harness, Junction Box and Thermocouples
(Ref. 70-00-00-03-13). STANDARD PRACTICES - ENGINE - GENERAL - TASK SUPPORT-
ING DATA
REFERENCE DESIGNATION
EGT Overtemperature Limits (V2500-A1, V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-A5) (Idle
and above)
Locations of Turbine Cooling-Air Supply-Tubes SHEET 1
660 B
655
C
650 A2
EXHAUST GAS TEMPERATURE C
o
645
640 A1
TRANSIENT AREA
5 SECONDS
635
630
625
A1
620
615
610
NO PROCEDURE NECESSARY
1 2 3 4 5 6 7 8 9 10 11 12
TIME OF OVERTEMPERATURE - MINUTES
NOTE:
IF QAR/DFDR DATA IS USED TO DETERMINE MANTENANCE ACTIONS, THEN THE OVERTEMPERATURE
CHART - VERSION 2 MUST BE USED REGARDLESS THE FWC AND FDIMU VERSIONS.
IF A TRANSIENT OVERTEMPERATURE OF 670 DEG. C MAXIMUM OCCURS DURING NOT MORE THAN FIVE
pwzxxb8938d
SECONDS WITH THE EGT MARGIN (EGTM) CALCULATION LESS THAN 10 DEG. C, A 360-DEGREE
BORESCOPE INSPECTION OF THE STAGE 1 HIGH PRESSURE TURBINE (HPT) DUCT SEGMENTS IS
NECESSARY AS SPECIFIED IN PARAGRAPH 4.F OF THIS TASK.
IF A TRANSIENT OVERTEMPERATURE OF 670 DEG. C MAXIMUM OCCURS DURING NOT MORE THAN FIVE
PWV
SECONDS WITH THE EGT MARGIN (EGTM) CALCULATION OF AT LEAT 10 DEG. C, NO PROCEDURE IS
NECESSARY. N_TS_770000_2_XBM0_01_05
660 B
655
C
650 A2
EXHAUST GAS TEMPERATURE °C
645
640 A1
TRANSIENT AREA
5 SECONDS
635
630
625
A1
620 NO PROCEDURE
NECESSARY
615
610
NO PROCEDURE NECESSARY
1 2 3 4 5 6 7 8 9 10 11 12
TIME OF OVERTEMPERATURE - MINUTES
NOTE:
DATA IS USED TO DETERMINE MAINTENANCE ACTIONS, THIS CHART MUST ALWAYS BE USED
REGARDLESS THE FWC AND FDIMU VERSIONS.
IF A TRANSIENT OVERTEMPERATURE OF 670 DEG. C MAXIMUM OCCURS DURING NOT MORE THAN FIVE
pwzxxb8938d
SECONDS WITH THE EGT MARGIN (EGTM) CALCULATION LESS THAN 10 DEG. C, A 360-DEGREE
BORESCOPE INSPECTION OF THE STAGE 1 HIGH PRESSURE TURBINE (HPT) DUCT SEGMENTS IS
NECESSARY AS SPECIFIED IN PARAGRAPH 4.F OF THIS TASK.
IF A TRANSIENT OVERTEMPERATURE OF 670 DEG. C MAXIMUM OCCURS DURING NOT MORE THAN FIVE
PWV
SECONDS WITH THE EGT MARGIN (EGTM) CALCULATION OF AT LEAT 10 DEG. C, NO PROCEDURE IS
NECESSARY. N_TS_770000_2_XBM0_02_02
TURBINE COOLING-AIR
SUPPLY-TUBE
HP COMPRESSOR
HP TURBINE
TURBINE COOLING-AIR
SUPPLY-TUBE
19557
N_TS_770000_2_XBP0_01_01
3. Fault Confirmation
Subtask 77-00-00-710-236-G
A. Test
NOTE: There are two EGT limits that must be obeyed: the Amber limit of 610 deg.C (1130.00 deg.F) and
the Redline limit of 635 deg.C (1175.00 deg.F).
(1) It is necessary to determine the time during which the EGT was more than the highest limit.
(2) If the EGT was more than 610 deg.C (1130.00 deg.F), get the Gas Path Advisory Report (GPAR),
Ref. AMM 31-37-73-01 Report 06, code 5200, that was triggered when the EGT became higher than
this limit.
(3) If the EGT was more than 635 deg.C (1175.00 deg.F), get the Gas Path Advisory Report (GPAR),
Ref. AMM 31-37-73-01 Report 06, code 5100, that was triggered when the EGT became higher than
this limit.
NOTE: These two reports are not triggered at the same time. The GPAR is with code 5100 triggered
before the GPAR with code 5200.
(4) If the GPAR is not available, you can use the DMC1 EGT report with the QAR/DFDR data to confirm
the EGT limits as specified in the steps below.
NOTE: When only the amber value of the EGT becomes more than its limit of 610 deg.C (1130.00
deg.F), there is no DMC1 report of an EGT overtemperature.
4. Fault Isolation
(Ref. Fig. EGT Overtemperature Limits (V2500-A1, V2522-A5, V2524-A5, V2527-A5, V2527E-A5, V2527M-
A5) (Idle and above))
** ON A/C ALL
PRE SB 73-1104 for A/C 001-002
Subtask 77-00-00-810-205-D
CAUTION: IF YOU DO NOT OBEY THE INSTRUCTIONS THAT FOLLOW, DAMAGE TO THE ENGINE
CAN BE THE RESULT.
NOTE: If you find the cause of the overtemperature during this procedure, it is permitted to stop the
troubleshooting.
NOTE: You will get the EGT data with the methods given in the Para. Fault Confirmation.
NOTE: If a borescope inspection of components was necessary for the troubleshooting for surge or stall,
you can ignore the steps applicable for the borescope inspection of these components.
(1) Engine serial number (from the engine data plate or other records)
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.
(3) Amount of time over the EGT limit: it is necessary to determine the amount of time over the highest
limit exceeded, either 610 deg.C (1130.00 deg.F) or 635 deg.C (1175.00 deg.F).
** ON A/C
POST SB 73-1104 for A/C 001-002
Subtask 77-00-00-810-205-J
CAUTION: IF YOU DO NOT OBEY THE INSTRUCTIONS THAT FOLLOW, DAMAGE TO THE ENGINE
CAN BE THE RESULT.
NOTE: If you find the cause of the overtemperature during this procedure, it is permitted to stop the
troubleshooting.
NOTE: You will get the EGT data with the methods given in the Para. Fault Confirmation.
NOTE: If a borescope inspection of components was necessary for the troubleshooting for surge or stall,
you can ignore the steps applicable for the borescope inspection of these components.
(1) Engine serial number (from the engine data plate or other records).
(2) Maximum EGT temperature.
(3) Amount of time over the EGT limit: it is necessary to determine the amount of time over the highest
limit exceeded, either 610 deg.C (1130.00 deg.F) or 635 deg.C (1175.00 deg.F).
** ON A/C ALL
Subtask 77-00-00-810-234-A
B. Find out if the cause of the EGT overtemperature was an EGT Indication System error. If one of the
conditions that follow is applicable, continue with step C, otherwise continue with step D.
(1) There is an EGT overteperature when the fuel flow is zero.
(2) EGT fluctuation or rise with no related change in N1 or fuel flow.
Subtask 77-00-00-810-235-A
C. Do the steps that follow if one of the conditions in step B occurred:
(1) Do a visual inspection of the EGT Harness, Junction box and EGT Thermocouples.
(a) If the EGT Harness is chafed, repair per Ref. AMM 77-21-43-300-801 .
(2) Do a functional test of the EGT Harness, Junction Box and Thermocouples Ref. AMM 77-21-43-700-
010 .
(3) If the cause of the EGT indication error was determined to be the hardware (and that hardware has
been repaired or replaced) then the engine may be returned to service. No further maintenance action
is necessary.
(4) If the cause of the EGT indication error could not be determined then do an engine idle run Ref.
AMM 71-00-00-710-022 . If all indications are normal and there are no fault messages then return the
engine to service. No further maintenance action is necessary.
Subtask 77-00-00-810-236-C
D. Refer to the Overtemperature Charts for the Necessary Action
(Ref. Fig. EGT Overtemperature Limits (V2500-A1, V2522-A5, V2524-A5, V2527-A5, V2527E-A5,
V2527M-A5) (Idle and above))
(1) Determine which the Overtemperature Chart to use:
(a) If the Flight Warning Computer (FWC) standard is F10 (or later version) and the Flight Data
Interface and Management Unit (FDIMU) standard is POST MOD 154589 / POST SB 31-1418
(for SAGEM) or POST MOD 150989 / POST SB 31-1341 (for TELEDYNE), then use Chart
Version 1.
(b) Use Chart Version 2 for all the other combinations of the FWC and the FDIMU.
(2) Use the EGT data that you collected to determine on the applicable chart the area in which the
overtemperature occurred.
NOTE: If the EGT overtemperature occurs in area A1 during take-off through the 3000 feet above
ground level and in the conditions that follow you can delay the troubleshooting that is given in
step E for five cycles.
(3) The Outside Air Temperature (OAT) is more than 30 deg.C (86.00 deg.F).
(4) The EGT is more than the limit by 10 deg.C (18 deg.F) or less. The EGT limit can be 610 deg.C
(1130.00 deg.F) or 635 deg.C (1175.00 deg.F) depending upon which A1 zone is used.
(5) The EGT overtemperature time is 30 seconds or less.
(6) The EGT was at the correct limit and the indications were correct (not elevated) during the remaining
flight.
(7) There is no fault message other than the EGT overtemperature.
(8) You found no signs of damage on the exhaust area of the engine.
Subtask 77-00-00-810-237-A
E. Necessary Action
(1) If the overtemperature was in the transient area for five seconds or less, and the EGT margin is at a
minimum of 10 deg.C (18 deg.F), no action is necessary.
(2) If the overtemperature was in the transient area for 5 seconds or less, and the EGT margin is less
than 10 deg.C (18 deg.F), do a 360 degree borescope inspection of the stage 1 High Pressure
Turbine (HPT) Duct Segments Ref. AMM 72-00-00-200-014 .
(3) If the overtemperature was in area A1 or A2 with one or more events, or if the overtemperature was in
area B with less than ten EGT overtemperature events and the EGT overtemperature occurred less
than ten times, do the troubleshooting in step F.
(4) If the overtemperature was in area B with ten or more EGT overtemperature events or in area C with
one or more events, remove the engine from operation.
It is recommended that you get the QAR/DFDR data to verify the time EGT was exceeded to confirm
engine removal. Contact IAE if further assistance is necessary.
(a) It is permitted to ferry-fly a non-revenue engine with overtemperature to a maintenance base
(for engine replacement) 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 that the hardware is within the limits and shows no visual damage. This condition is
permitted for only one engine for each aircraft.
Subtask 77-00-00-810-207-B
F. Do the steps that follow to find the cause of an EGT overlimit:
(1) Examine the turbine exhaust case for debris.
(a) If debris is found, remove the engine from operation.
(2) On the MCDU, read the LAST LEG REPORT of the FADEC 1A and the FADEC 1B menu
(Ref. TSM 70-00-00-03) and make a record of the maintenance message.
(a) If you received the maintenance message CHA VSV ACT/HC/EEC1 for FADEC 1A:
· Do the task that follows (Ref. TSM 75-30-00-810-843) if necessary (refer to the engine build
standard).
(b) If you have received the maintenance message CHB VSV ACT/HC/EEC1 for FADEC 1B:
· Do the task that follows (Ref. TSM 75-30-00-810-845) is necessary (refer to the engine build
standard).
(c) If you do not receive one of the above fault messages, refer 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 1 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 the
engine operation.
NOTE: If a 360-degree borescope inspection of the stage 1 HPT duct segments occurred in
less than 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 document