DOC AIRBUS | AMM A320FVisual Examination (after an Exhaust Gas Temperature (EGT) Overtemperature) [PW11]
TASK 72-00-00-210-809-A
Visual Examination (after an Exhaust Gas Temperature (EGT) Overtemperature)
Do an inspection of the engine after Exhaust Gas Temperature (EGT) overtemperature.
For more information about the power plant, refer to (72-00-00-00U).
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Work Zones and Access Panels
C. Referenced Information
3. Job Set-up
Subtask 72-00-00-860-114-A ** ON A/C NOT FOR ALL
Subtask 72-00-00-210-175-A ** ON A/C NOT FOR ALL
[Rev.10 from 2021]
2026.04.01 02:47:17 UTC
Visual Examination (after an Exhaust Gas Temperature (EGT) Overtemperature)
WARNING:
BE CAREFUL WHEN YOU DO WORK ON THE ENGINE AFTER SHUTDOWN. THE ENGINE CAN STAY HOT FOR A LONG TIME. IF YOU DO NOT OBEY THIS INSTRUCTION, INJURY CAN OCCUR.
ZONE: 400
1. Reason for the JobDo an inspection of the engine after Exhaust Gas Temperature (EGT) overtemperature.
For more information about the power plant, refer to (72-00-00-00U).
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | AR | COVER - PROTECTION |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 400 | POWER PLANT, NACELLES AND PYLONS |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 72-00-00-210-812-A | General Visual Inspection (GVI) of the Engine Exhaust Area |
| TASK 72-41-00-290-802-A | Borescope Inspection of Combustion Chamber and HPT Nozzle Guide Vanes |
| TASK 72-51-00-290-802-A | Borescope Inspection of the 1st and 2nd Stage Turbine Blades |
| TASK 72-52-00-290-802-A | Borescope Inspection of the Turbine Intermediate Case (TIC) Assembly |
| TASK 74-21-61-000-802-A | Removal of the Ignition Cables |
| TASK 74-21-61-400-802-A | Installation of the Ignition Cables |
Inspection of the Engine after Exhaust Gas Temperature (EGT) Overtemperature - (EGT Overtemperature Limits - Engine Operation)Subtask 72-00-00-860-114-A ** ON A/C NOT FOR ALL
A. Not Applicable
4. ProcedureSubtask 72-00-00-210-175-A ** ON A/C NOT FOR ALL
A. Visual Examination (after an Exhaust Gas Temperature (EGT) Overtemperature)
(2) An EGT overtemperature condition occurs when the engine is operated beyond the exhaust gas temperature limits. The EGT limits are shown as follows:
(a) Correct the cause of exceeded overtemperature limits, refer to the Trouble Shooting Manual (TSM), Fault Isolation for a high EGT. Check and make sure that the EGT indication system is in satisfactory operation before you continue with the overtemperature inspection.
(b) Do the inspections and procedures shown in the EGT Overtemperature Limits - Engine Operation Table, based on the maximum EGT overtemperature and time at
this overtemperature.
(c) Do the inspections and procedures shown in the EGT Overtemperature Limits - Starting Table if the overtemperature occurred during start
(4) Do a visual inspection of the turbine exhaust area and LPT 3rd stage blades (Ref. AMM TASK 72-00-00-210-812).
(a) You must examine all of the low pressure turbine blades and vane stages that it is possible to see for damage.
1 Look for burning or distortion of parts.
2 Look for pieces of metal in the exhaust area.
(5) If you find damage during the visual inspection of the turbine exhaust area LPT 3rd stage blades, you must then do a borescope inspection as follows:
(a) Do a borescope inspection of the combustion chamber and fuel nozzles and high pressure turbine 1st stage vanes. Refer to (Ref. AMM TASK 72-41-00-290-802) for detailed inspection and limits.
(b) Do a borescope inspection of the high pressure turbine 1st and 2nd stage blades and 2nd stage vanes. Refer to (Ref. AMM TASK 72-51-00-290-802) for detailed inspection and limits.
(c) Do a borescope inspection of the low pressure turbine blades and vanes (Ref. AMM TASK 72-52-00-290-802).
(6) Do a visual examination of the ignition cables as follows:
(b) Examine the ignition cable ends for damage or overheating.
(c) Examine the ignition rubber bushings for damage and burning.
(d) Examine the ignition cable ends for electrical arcing. Arcing is caused by damaged insulators.
(e) If the ignition cables or bushings are damaged from the heat, replace the damaged parts (Ref. AMM TASK 74-21-61-400-802).
(7) If the engine must be removed from the aircraft because of high overtemperature condition, you must do the steps that follow:
(a) Make a record of the maximum temperature and time at this temperature.
(b) Make a record if the overtemperature occurred at a steady state or a surge condition.
(c) Make a record of any other important information that happened during the overtemperature condition.
(d) All of the overtemperature records must go with the engine history records.
(e) Send the engine to the shop for disassembly, detailed inspection, and repair.
(8) Examine the assembly for foreign objects, damage and correct assembly. the engine.
(9) Installation of the protection covers
CAUTION:
WIPE CLEAN ALL PARTS AND TOOLS AS NECESSARY TO REMOVE UNWANTED DEBRIS AND PREVENT DAMAGE TO THE ENGINE.
(1) Removal of the protection covers CAUTION:
REMOVE THE PROTECTION COVERS FROM THE OPENINGS AS NECESSARY TO PREVENT ENGINE DAMAGE.
(a) Make sure that you remove all the necessary COVER - PROTECTION to prevent damage to the engine. (2) An EGT overtemperature condition occurs when the engine is operated beyond the exhaust gas temperature limits. The EGT limits are shown as follows:
- EGT Overtemperature Limits - Engine operation chart
- EGT Overtemperature Limits - Starting chart
(a) Correct the cause of exceeded overtemperature limits, refer to the Trouble Shooting Manual (TSM), Fault Isolation for a high EGT. Check and make sure that the EGT indication system is in satisfactory operation before you continue with the overtemperature inspection.
(b) Do the inspections and procedures shown in the EGT Overtemperature Limits - Engine Operation Table, based on the maximum EGT overtemperature and time at
this overtemperature.
- Table 601 - EGT Overtemperature Limits - Engine Operation
| Chart Area | No. of Occurrences | Inspection Requirements |
|---|---|---|
| A | Any | Visually inspect the engine after EGT overtemperature. If you find damage during the visual inspection, borescope-inspect the combustion chamber and fuel nozzles, high pressure turbine and low pressure turbine. |
| B | 1-9 | Visually inspect the engine after an EGT overtemperature. In 25 hours or less, borescope-inspect the combustion chamber and fuel nozzles, high pressure turbine and low pressure turbine. |
| | 10 or more | Remove the engine from the aircraft. Send the engine to the shop for disassembly, detailed inspection and repair. |
| C | 1 - 9 | Make a record of the occurrence. Perform borescope-inspections of the combustion chamber and fuel nozzles, high pressure turbine and low pressure turbine. |
| | 10 or more | Remove the engine from the aircraft. Send the engine to the shop for the disassembly, detailed inspection and repair. |
| D | Any | Remove the engine from the aircraft. Send the engine to the shop for disassembly, detailed inspection and repair. |
- Table 602 - EGT Overtemperature Limits - Starting
| Chart Area | No. of Occurrences | Inspection Requirements |
|---|---|---|
| A | Any | Make a record of the occurrence. It is not necessary to do any inspections if the overtemperature was during a transient operation. The transient must be five seconds or less and the maximum overtemperature 2038 deg.F (1114 deg.C). |
| B | 1-9 | Visually inspect the engine after an EGT overtemperature. |
| | 10 or more | Visually inspect the engine after an EGT overtemperature. In 25 hours or less, borescope-inspect the combustion chamber and fuel nozzles, high pressure turbine and low pressure turbine. |
| C | Any | Remove the engine from the aircraft. Send the engine to the shop for the disassembly, detailed inspection and repair. |
(a) You must examine all of the low pressure turbine blades and vane stages that it is possible to see for damage.
1 Look for burning or distortion of parts.
2 Look for pieces of metal in the exhaust area.
(5) If you find damage during the visual inspection of the turbine exhaust area LPT 3rd stage blades, you must then do a borescope inspection as follows:
(a) Do a borescope inspection of the combustion chamber and fuel nozzles and high pressure turbine 1st stage vanes. Refer to (Ref. AMM TASK 72-41-00-290-802) for detailed inspection and limits.
(b) Do a borescope inspection of the high pressure turbine 1st and 2nd stage blades and 2nd stage vanes. Refer to (Ref. AMM TASK 72-51-00-290-802) for detailed inspection and limits.
(c) Do a borescope inspection of the low pressure turbine blades and vanes (Ref. AMM TASK 72-52-00-290-802).
(6) Do a visual examination of the ignition cables as follows:
NOTE: If the engine was shut down quickly for an emergency shutdown, it is possible for the heat to damage the rubber insulation in the ignition cables and the rubber bushings. This can cause arcing of the ignition electrical system, unsatisfactory engine starts and damaged engine parts.
(a) Remove the ignition cables (Ref. AMM TASK 74-21-61-000-802). (b) Examine the ignition cable ends for damage or overheating.
(c) Examine the ignition rubber bushings for damage and burning.
(d) Examine the ignition cable ends for electrical arcing. Arcing is caused by damaged insulators.
(e) If the ignition cables or bushings are damaged from the heat, replace the damaged parts (Ref. AMM TASK 74-21-61-400-802).
(7) If the engine must be removed from the aircraft because of high overtemperature condition, you must do the steps that follow:
(a) Make a record of the maximum temperature and time at this temperature.
(b) Make a record if the overtemperature occurred at a steady state or a surge condition.
(c) Make a record of any other important information that happened during the overtemperature condition.
(d) All of the overtemperature records must go with the engine history records.
(e) Send the engine to the shop for disassembly, detailed inspection, and repair.
(8) Examine the assembly for foreign objects, damage and correct assembly. the engine.
(9) Installation of the protection covers
CAUTION:
INSTALL PROTECTION COVERS ON ALL THE OPENINGS IMMEDIATELY TO PREVENT DAMAGE TO THE ENGINE.
(a) Make sure that you install COVER - PROTECTION as necessary to prevent damage to the engine.