TASK 71-00-00-810-017-A00 EGT Overtemperature, Fault Isolation-017

DMC:V2500-A0-71-00-0000-08B-421A-B|Issue No:001.00|Issue Date:2014-05-01

Export Control

EAR Export Classification: Not subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3), except for the following Service Bulletins which are currently published as EAR Export Classification 9E991: SBE70-0992, SBE72-0483, SBE72-0580, SBE72-0588, SBE72-0640, SBE73-0209, SBE80-0024 and SBE80-0025.

Copyright

© IAE International Aero Engines AG (2001, 2014 - 2021) The information contained in this document is the property of © IAE International Aero Engines AG and may not be copied or used for any purpose other than that for which it is supplied without the express written authority of © IAE International Aero Engines AG. (This does not preclude use by engine and aircraft operators for normal instructional, maintenance or overhaul purposes.).

Applicability

All

Common Information

TASK 71-00-00-810-017-A00 EGT Overtemperature, Fault Isolation-017

General

This fault isolation procedure gives the EGT overtemperature limits, inspection requirements and corrective actions for EGT overtemperature during engine start and engine run.

Preliminary Requirements

Pre-Conditions

NONE

Support Equipment

NONE

Consumables, Materials and Expendables

NONE

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 71-00-00-810-051 EGT Overtemperature Limits During Engine Start and Below Idle Operation,

    1. Refer to Figure and Figure.

      2. For an EGT overtemperature in Area A of the chart do the steps that follow.

      1. Correct the cause of overtemperature. Refer to Step.

        2. Record:

        1. Engine Serial No.

        2. Maximum temperature.

        3. Quantity of time.

        4. If the condition was steady-state or surge.

        3. Examine the exhaust area for signs of damage.

        1. If there are no signs of damage, the engine can be started again and continue to operate.

        2. If damage is seen, borescope inspect the combustion chamber, Stage 1 HP turbine vanes, Stage 1 and 2 HP turbine blades and the Stage 3 LP turbine blades. Refer to TASK 72-00-00-200-000 (INSPECTION/CHECK-000) for the applicable TASK numbers.

      4. Examine for broken turbine cooling air supply tubes. Refer to Figure.

      3. For an EGT overtemperature in Area B of the chart do the steps that follow.

      1. Correct the cause of overtemperature. Refer to Step.

        2. Record:

        1. Engine Serial No.

        2. Maximum temperature.

        3. Quantity of time.

        4. If the condition was steady-state or surge.

        3. Examine the exhaust area for signs of damage and examine for broken turbine cooling air supply tubes. Refer to Figure.

        1. If there are no signs of damage, the engine can be started again and continue to operate. In less than 60 hours, borescope inspect the combustion chamber, Stage 1 HP turbine vanes, Stage 1 and 2 HP turbine blades and the Stage 3 LP turbine blades. Refer to TASK 72-00-00-200-000 (INSPECTION/CHECK-000) for the applicable TASK number.

        2. If damage is seen, borescope inspect the combustion chamber, the Stage 1 HP turbine vanes, Stage 1 and 2 HP turbine blades and the Stage 3 LP turbine blades. Refer to TASK 72-00-00-200-000 (INSPECTION/CHECK-000) for the applicable TASK numbers.

      4. Only one engine per aircraft can be in this group.

      4. For an EGT overtemperature in Area C of the chart do the steps that follow.

      1. Correct the cause of overtemperature. Refer to Step.

        2. Record:

        1. Engine Serial No.

        2. Maximum temperature.

        3. Quantity of time.

        4. If the condition was steady-state or surge.

      3. Remove the engine for hot section inspection and metallurgical analysis (Refer to SPM TASK 70-02-03-220-501) of the Stage 1 and 2 HP turbine blades.

      4. Examine for broken turbine cooling air supply tubes. Refer to Figure.

    2. SUBTASK 71-00-00-810-054 EGT Overtemperature Limits During Engine Run

    1. Refer to Figure and Figure.

      2. For an EGT in the Transient Area (5 seconds) do the step that follows.

      1. If overtemperature was transient up to 1175 deg F (635 deg C) for 5 seconds or less no action is necessary.

      3. For an EGT in Area A of the chart do the steps that follow.

      1. Correct the cause of overtemperature. Refer to Step.

        2. Record:

        1. Engine Serial No.

        2. Maximum temperature.

        3. Quantity of time.

        4. If the condition was steady-state or surge.

        3. Examine the exhaust area for signs of burning or distortion and metal particles from upstream damage.

        1. If there are no signs of damage, the engine can continue to operate.

        2. If damage is seen, borescope inspect the combustion chamber, Stage 1 HP turbine vanes, Stage 1 and 2 HP turbine blades and the Stage 3 LP turbine blades. Refer to TASK 72-00-00-200-000 (INSPECTION/CHECK-000) for the applicable TASK numbers.

      4. Examine for broken turbine cooling air supply tubes. Refer to Figure.

      4. For an EGT in Area B of the chart when the overtemperature has occured between 1 and 9 times do the steps that follow. If the overtemperature has occured 10 times go to step D.

      1. Correct the cause of overtemperature. Refer to Step.

        2. Record:

        1. Engine Serial No.

        2. Maximum temperature.

        3. Quantity of time.

        4. If the condition was steady-state or surge.

        3. Examine the exhaust area for signs of burning or distortion and metal particles from upstream damage and examine for broken turbine cooling air supply tubes. Refer to Figure.

        1. If there are no signs of damage, the engine can be started again and continue to operate. In less than 60 hours, borescope inspect the combustion chamber, Stage 1 HP turbine vanes, Stage 1 and 2 HP turbine blades and the Stage 3 LP turbine blades. Refer to TASK 72-00-00-200-000 (INSPECTION/CHECK-000) for the applicable TASK numbers.

        2. If damage is seen, borescope inspect the combustion chamber, Stage 1 HP turbine vanes, Stage 1 and 2 HP turbine blades and the Stage 3 LP turbine blades. Refer to TASK 72-00-00-200-000 (INSPECTION/CHECK-000) for the applicable TASK numbers.

      4. Only one engine per aircraft can be in this group.

      5. For an EGT in Area B of the chart when the overtemperature has occured 10 times do the steps that follow.

      1. Correct the cause of overtemperature. Refer to Step.

        2. Record:

        1. Engine Serial No.

        2. Maximum temperature.

        3. Quantity of time.

        4. If the condition was steady-state or surge.

      3. Remove the engine for hot section inspection and metallurgical analysis (Refer to SPM TASK 70-02-03-220-501) of the Stage 1 and 2 HP turbine blades.

      4. Examine for broken turbine cooling air supply tubes. Refer to Figure.

      6. For an EGT in Area C of the chart do the steps that follow.

      1. Correct the cause of overtemperature. Refer to Step.

        2. Record:

        1. Engine Serial No.

        2. Maximum temperature.

        3. Quantity of time.

        4. If the condition was steady-state or surge.

      3. Remove the engine for hot section inspection and metallurgical analysis (Refer to SPM TASK 70-02-03-220-501) of the Stage 1 and 2 HP turbine blades.

      4. Examine for broken turbine cooling air supply tubes. Refer to Figure.

    3. SUBTASK 71-00-00-810-053 Correct the Cause of Overtemperature

    1. Check the EEC fault messages and do the necessary procedures to correct the defects. Refer to TASK 71-00-00-810-000(FAULT ISOLATION-001) for EEC fault messages.

    2. Check the VSV mechanism. Refer to TASK 72-00-40-700-001 (TESTING-001).

    3. Check the bleed valve operation. Refer to TASK (TBD).

    4. Figure: EGT overtemperature limits during engine start

    EGT overtemperature limits during engine start

    Figure: EGT overtemperature limits during engine run

    EGT overtemperature limits during engine run

    Figure: Turbine cooling air supply tubes locations

    Turbine cooling air supply tubes locations

Requirements After Job Completion

Follow-On Conditions

NONE