Borescope Inspection of the Engine [PW11]

TASK 72-00-00-290-811-A
Borescope Inspection of the Engine

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.

WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.

ZONE: 400

1. Reason for the Job
Use this task for general information about borescope port locations and requirements.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	1	ACCESS PLATFORM 1M(3 FT)
CTE8003	1	SYSTEM BOROSCOPE (VIDEO)

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
400	POWER PLANT, NACELLES AND PYLONS
FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENG 1)
437AL, 438AR, 451AL, 452AR
FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENG 2)
447AL, 448AR, 461AL, 462AR

C. Referenced Information

REFERENCE	DESIGNATION
TASK 71-00-00-860-833-A	Procedure to Prevent Engine Motoring
TASK 71-13-00-010-802-A	Opening of the Fan Cowl Doors
TASK 71-13-00-410-802-A	Closing of the Fan Cowl Doors
TASK 78-30-00-040-805-A	Deactivation of the Thrust Reverser System for Ground Maintenance
TASK 78-30-00-440-805-A	Reactivation of the Thrust Reverser System after Ground Maintenance
TASK 78-36-00-010-802-A	Opening of the Thrust Reverser Cowl-Doors
TASK 78-36-00-410-802-A	Closing of the Thrust Reverser Cowl-Doors
Inspection of the Engine after Surge or Stall - (Borescope Examination for LPC Damage)
High Pressure Compressor (HPC) and Diffuser
High Pressure Compressor (HPC) and Diffuser - POST SB C72-00-0043A (Config-2 Case Assembly Durability Improvement Configuration)
High Pressure Turbine (HPT) and Turbine Intermediate Case (TIC)
Low Pressure Turbine (LPT)

3. Job Set-up
Subtask 72-00-00-941-204-A ** ON A/C NOT FOR ALL

A. Safety Precautions
(1) Do the procedure to prevent engine motoring
(Ref. AMM TASK 71-00-00-860-833).

Subtask 72-00-00-010-275-A ** ON A/C NOT FOR ALL

B. Get Access
(1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-802):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENG 1)
437AL, 438AR
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENG 2)
447AL, 448AR.
(2) Put the ACCESS PLATFORM 1M(3 FT) in position.

Subtask 72-00-00-040-137-A ** ON A/C NOT FOR ALL

C. Deactivation of the Thrust Reverser for Maintenance

WARNING: YOU MUST DEACTIVATE THE THRUST REVERSER BEFORE YOU DO WORK ON OR AROUND IT. IF YOU DO NOT, THE THRUST REVERSER CAN OPERATE ACCIDENTALLY AND CAUSE AN INJURY AND/OR DAMAGE.

(1) Do the deactivation of the thrust reverser system for maintenance (Ref. AMM TASK 78-30-00-040-805).

Subtask 72-00-00-010-276-A ** ON A/C NOT FOR ALL

D. Get Access
(1) Open the thrust reverser cowl-doors (Ref. AMM TASK 78-36-00-010-802):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENG 1)
451AL, 452AR
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENG 2)
461AL, 462AR.

4. Procedure

CAUTION: WIPE CLEAN ALL PARTS AND TOOLS AS NECESSARY TO REMOVE UNWANTED DEBRIS AND PREVENT DAMAGE TO THE ENGINE.

Subtask 72-00-00-290-130-A ** ON A/C NOT FOR ALL

A. General
(1) The engine has 17 borescope inspection access-ports to examine the engine gaspath. There is also access through the fan blades, through the upper and lower igniter ports on the diffuser case and between the turbine exhaust case struts.
(2) The engine gaspath parts are examined for damage, cracks, wears and missing material.
(3) The borescope ports are identified by an Access Port (AP) number as shown in Table 601 below.

Inspection of the Engine after Surge or Stall - (Borescope Examination for LPC Damage) ** ON A/C NOT FOR ALL

High Pressure Compressor (HPC) and Diffuser ** ON A/C NOT FOR ALL

High Pressure Compressor (HPC) and Diffuser - POST SB C72-00-0043A (Config-2 Case Assembly Durability Improvement Configuration) ** ON A/C NOT FOR ALL

High Pressure Turbine (HPT) and Turbine Intermediate Case (TIC) ** ON A/C NOT FOR ALL

Low Pressure Turbine (LPT) ** ON A/C NOT FOR ALL

(4) Rotation of the engine:

CAUTION: ONLY TURN THE ENGINE IN THE CORRECT DIRECTION OF OPERATION. IF YOU DO NOT OBEY THIS INSTRUCTION, YOU WILL CAUSE DAMAGE TO THE ENGINE.

(a) Turn the engine in the direction consistent with operation for the given module under inspection.
(5) Use the CTE8003 SYSTEM BOROSCOPE (VIDEO) or equivalent. Follow the general engine borescope specifications for flexible borescopes.

NOTE: Where possible, a rigid borescope or video equipment are optional for all other access locations.

Table 601 - Borescope Inspection Access Ports

Access port	Location - Clockwise from rear	Parts that you can see for this inspection
See the figure: Inspection of the Engine after Surge or Stall - (Borescope Examination for LPC Damage) ** ON A/C NOT FOR ALL
AP LPC-1	2 o'clock NOTE: LPC front case P/N 5377500-01 will have the plug installed at the 8 o'clock position.	LPC variable inlet stator vanes and 1st stage integrally bladed rotor airfoils
AP LPC-2	2 o'clock	LPC 1st stage stator vanes and 2nd stage integrally bladed rotor airfoils
AP LPC-3	2 o'clock	LPC 2nd stage stator vanes and 3rd stage airfoils
See the figure: High Pressure Compressor (HPC) and Diffuser ** ON A/C NOT FOR ALL
AP HPC-1	3 o'clock	HPC variable inlet guide vanes and 1st stage integrally bladed rotor airfoils
AP HPC-2	2 o'clock	HPC 1st stage Variable Stator Vanes (VSV) and 2nd stage integrally bladed rotor airfoils
AP HPC-3	4 o'clock	HPC 2nd stage VSV and 3rd stage integrally bladed rotor airfoils
AP HPC-4	2 o'clock	HPC 3rd stage VSV and 4th stage integrally bladed rotor airfoils
AP HPC-5	3 o'clock	HPC 4th stage stator and 5th stage integrally bladed rotor airfoils
AP HPC-6	2:30 o'clock	HPC 5th stage stator and 6th stage integrally bladed rotor airfoils
AP HPC-7	2:30 o'clock	HPC 6th stage stator and 7th stage integrally bladed rotor airfoils
AP HPC-8	3 o'clock	HPC 7th stage stator and 8th stage integrally bladed rotor airfoils
AP DIFF-1	3 o'clock	Combustion chamber inner and outer liners, bulkhead, fuel nozzles, HPT 1st stage blades and HPT 1st vanes
Ignitor, Upper (optional)	3:30 o'clock	Combustion chamber inner and outer liners, bulkhead, fuel nozzles, HPT 1st stage blades and HPT 1st vanes
Ignitor, Lower (optional)	4 o'clock	Combustion chamber inner and outer liners, bulkhead, fuel nozzles, HPT 1st stage blades and HPT 1st vanes
POST SB C72-00-0043A (Config-2 Assembly Durability Improvement Configuration)
See the figure: High Pressure Compressor (HPC) and Diffuser - POST SB C72-00-0043A (Config-2 Case Assembly Durability Improvement Configuration) ** ON A/C NOT FOR ALL
AP DIFF-2	10 o'clock	HPC 7th and 8th stage heatshield
END OF POST SB C72-00-0043A (Config-2 Assembly Durability Improvement Configuration)
See the figure: High Pressure Turbine (HPT) and Turbine Intermediate Case (TIC) ** ON A/C NOT FOR ALL
AP HPT-1	5 o'clock	HPT 1st stage rotor blades, 2nd stage vanes and 2nd stage rotor blades
AP TIC-1	1:30 o'clock	HPT 2nd stage rotor blades and LPT 1st stage rotor blades
See the figure: Low Pressure Turbine (LPT) ** ON A/C NOT FOR ALL
AP LPT-1	2:30 o'clock	LPT 1st stage rotor blades, LPT 1st stage vanes and LPT 2nd stage blades
AP LPT-2	2:30 o'clock	LPT 2nd stage rotor blades, LPT 2nd stage vanes and LPT 3rd stage blades

(6) Borescope inspection interval information:
(a) See the Pratt & Whitney engine maintenance program for recommended intervals for each engine module.
(b) These inspection intervals can be adjusted based on operator experience and approval of the local regulatory agency.
(c) Operation at regular inspection interval limit:
1 If part damage meets regular inspection interval criteria, the engine can continue-in-service.
2 The parts will be examined again at the next regular inspection interval.
(7) Operation at reduced inspection interval limit:
(a) If the parts are damaged to the reduced inspection interval limits, the engine can continue-in-service as noted in the inspection procedure.
Parts must be examined again at the reduced inspection interval. Reduced interval is 1/2 the regular interval, unless specified differently. Contact Pratt & Whitney for further disposition.
(8) Operation at additional reduced inspection interval limit:
(a) If the parts are damaged to the additional reduced inspection interval limits, the engine can continue-in-service as noted in the inspection procedure.
Parts must be examined again at the reduced inspection interval. Reduced interval is 1/4 the regular interval, unless specified differently. Contact Pratt and Whitney for further disposition.
(9) Operation at more than the additional reduced inspection interval limit:
(a) If the parts are damaged more than the additional reduced inspection interval limits, the engine cannot be continued-in-service for more than five additional flight cycles unless otherwise specified in the inspection procedure for the parts.
(b) The engine must be disassembled for repair or replacement of the damaged parts.
(10) Examine the assembly for foreign objects, damage, and correct assembly.

5. Close-up
Subtask 72-00-00-410-235-A ** ON A/C NOT FOR ALL

A. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Close the thrust reverser cowl-doors (Ref. AMM TASK 78-36-00-410-802):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENG 1)
451AL, 452AR
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENG 2)
461AL, 462AR.

Subtask 72-00-00-440-130-A ** ON A/C NOT FOR ALL

B. Do the reactivation of the thrust reverser system after maintenance (Ref. AMM TASK 78-30-00-440-805).

Subtask 72-00-00-410-236-A ** ON A/C NOT FOR ALL

C. Close Access
(1) Close the fan cowl doors (Ref. AMM TASK 71-13-00-410-802):
(a) FOR [4020KM1] (POWER PLANT-DEMOUNTABLE, ENG 1)
437AL, 438AR
(b) FOR [4020KM2] (POWER PLANT-DEMOUNTABLE, ENG 2)
447AL, 448AR.
(2) Remove the access platform(s).
(3) Remove the WARNING NOTICE(S).

[Rev.10 from 2021] 2026.04.01 02:47:29 UTC