Borescope Inspection of the High Pressure Compressor (HPC) Assembly [PW11]

TASK 72-35-00-290-801-A
Borescope Inspection of the High Pressure Compressor (HPC) Assembly

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: DO THE BORESCOPE INSPECTION IN AN AREA WHICH HAS PROTECTION FROM THE WEATHER. IF A BORESCOPE INSPECTION IS DONE IN WET CONDITIONS, USE SUFFICIENT PROTECTION TO PREVENT POSSIBLE ELECTRICAL SHOCK TO THE OPERATOR OR DAMAGE TO THE EQUIPMENT. AN ELECTRICAL SHOCK CAN KILL A PERSON OR CAUSE A BAD INJURY.

CAUTION: MAKE SURE THE TEMPERATURE IN THE ENGINE IS LESS THAN 150 DEG.F (65.6 DEG.C) BEFORE YOU INSTALL THE FLEXIBLE BORESCOPE IN THE ENGINE. IF THE ENGINE IS HOTTER THAN 150 DEG.F (65.6 DEG.C), THE FLEXIBLE BORESCOPE CAN MELT AND BE DAMAGED.

CAUTION: WAIT UNTIL THE TEMPERATURE OF THE HPC INTERNAL CAVITY IS LESS THAN 150 DEG.F (65.6 DEG.C) BEFORE YOU REMOVE THE HPC BORESCOPE PLUGS. CASE MISALIGNMENT CAN CAUSE THE HPC BORESCOPE PLUGS TO BREAK AND DAMAGE TO THE HPC CAN OCCUR.

ZONE: 400

1. Reason for the Job
Use this inspection procedure to do a borescope inspection of the HPC assembly.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	1	ACCESS PLATFORM 1M(3 FT)
No specific	1	BORESCOPE - FLEXIBLE
No specific	1	THERMOMETER - METAL PROBE TYPE, 0 TO 400 DEG.F
No specific	1	WRENCH - STANDARD
CTE8003	1	SYSTEM BOROSCOPE (VIDEO)
PWA115120	1	KIT, CONTROL

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 72-00-00-000-804-A	Removal of the Borescope Plugs
TASK 72-00-00-000-805-A	Removal of the High (N2) Rotor-Turning Equipment
TASK 72-00-00-400-804-A	Installation of the Borescope Plugs
TASK 72-00-00-400-805-A	Installation of the High (N2) Rotor Turning Equipment
TASK 75-31-02-000-801-A	Removal of the High Pressure Compressor (HPC) Stator Vane Actuator (SVA) Primary
TASK 75-31-02-400-801-A	Installation of the High Pressure Compressor (HPC) Stator Vane Actuator (SVA) Primary
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
HPC Access Port AP Locations
HPC Vane and Blade Locations
HPC IGVs and 1st, 2nd and 3rd Stage Variable Vanes
HPC 1st, 2nd, 3rd and 4th Stage Integrally Bladed Rotor Airfoils
HPC 4th and 5th Stage Stators
HPC 5th Stage Integrally Bladed Rotor Airfoils
HPC 6th and 7th Stage Stators
HPC 6th and 7th Stage Integrally Bladed Rotor Airfoils
HPC 8th Stage Integrally Bladed Rotor Airfoils
HPC 1st through 8th Stage Airfoil/Blade Outer Rubstrips and HPC 4th through 7th Stage Stator Inner Rubstrips
360-Degree Inspection of the HPC Assembly (Borescope Installation and Removal Direction)

3. Job Set-up
Subtask 72-35-00-941-052-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 72-35-00-010-050-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 72-35-00-040-050-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 72-35-00-010-051-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 72-35-00-290-050-A ** ON A/C NOT FOR ALL

A. Borescope Inspection of the HPC Assembly of the Engine
(1) If the engine has been run recently, do a check of the temperature in the HPC with the THERMOMETER - METAL PROBE TYPE, 0 TO 400 DEG.F:
(a) It is recommended that you wait three to five hours after engine shutdown and the engine internal temperature is less than 150 deg.F (65.6 deg.C) before you do a borescope inspection.
(b) As an option, you can dry-motor the engine with the starter to decrease the engine core temperature.
(2) Remove borescope plugs AP HPC-1 PLUG, AP HPC-2 PLUG, AP HPC-3 PLUG, AP HPC-4 PLUG, AP HPC-5 PLUG, AP HPC-6 PLUG, AP HPC-7 PLUG and AP HPC-8 PLUG as necessary (Ref. AMM TASK 72-00-00-000-804).

HPC Access Port AP Locations ** ON A/C NOT FOR ALL

(3) Install the high (N2) rotor turning equipment, if necessary (Ref. AMM TASK 72-00-00-400-805).
(4) The HPC stages and quantities are listed for reference only and are as follows:

Stage	Quantity
Inlet Guide Vane (IGV)	39
HPC stage 1 integrally bladed rotor airfoil	26
HPC stage 1 variable vanes	46
HPC stage 2 integrally bladed rotor airfoil	38
HPC stage 2 variable vanes	61
HPC stage 3 integrally bladed rotor airfoil	52
HPC stage 3 variable vanes	78
HPC stage 4 integrally bladed rotor airfoil	58
HPC stage 4 stator segment (PN 30G3274 and PN 30G3374)	14
HPC stage 4 stator segment (PN 30G3474 and PN 30G3574)	13
HPC stage 5 integrally bladed rotor airfoil	68
HPC stage 5 stator segment (PN 30G3275 and PN 30G3575)	15
HPC stage 5 stator segment (PN 30G3375 and PN 30G3475)	14
HPC stage 5 stator segment (PN 30G3675)	16
HPC stage 6 integrally bladed rotor airfoil	73
HPC stage 6 stator segment (PN 30G3276 and PN 30G3376)	18
HPC stage 6 stator segment (PN 30G3476)	17
HPC stage 7 integrally bladed rotor airfoil	70
HPC stage 7 stator segment (PN 30G3277, PN 30G3377 and PN 30G3477)	16
HPC stage 7 stator segment (PN 30G3577)	17
HPC stage 8 integrally bladed rotor airfoil	66

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.

(5) The HPC assembly must be turned clockwise (aft looking forward) while you do this inspection.
(6) Turn the HPC with the electric rotator in the PWA115120 KIT, CONTROL or the WRENCH - STANDARD at the main gearbox.
(7) Examine the HPC integrally bladed rotors during the borescope inspection for blend repairs.
(a) It is possible to see an area that is worn more than the permitted damage limits because of a previous blend repair. You must examine this area very carefully to find if this area is a new defect or an area that was blend-repaired before. A blend-repaired area will have a minimum 5 to 1 length-to-depth blend ratio with smooth round corners.

WARNING: BE CAREFUL TO EXAMINE THE POWER CABLE OF THE LIGHT SOURCE BEFORE YOU USE IT. DO NOT USE THE CABLE IF THE INSULATION HAS CUTS OR WORN OR BROKEN AREAS. INSULATION WITH THIS TYPE OF DAMAGE IS DANGEROUS BECAUSE OF POSSIBLE ELECTRICAL SHOCK TO THE OPERATOR.

CAUTION: INSTALL PROTECTION COVERS ON ALL OPENINGS AS SOON AS POSSIBLE TO PREVENT ENGINE DAMAGE.

(8) Do the inspection with the CTE8003 SYSTEM BOROSCOPE (VIDEO) as follows:

NOTE: As an option, the BORESCOPE - FLEXIBLE can be used for all the steps.

(a) Use the electric rotator or the WRENCH - STANDARD to turn the HPC rotor.

NOTE: This examination is limited to what can be seen with the BORESCOPE - FLEXIBLE through borescope access ports AP HPC-1 thru AP HPC-8.

(b) Do the HPC borescope inspection as follows:

NOTE: This inspection of all vane stages is not mandatory for 360 degrees for AP HPC-1 through AP HPC-8. Limits are given for when damage is seen when the borescope is inserted into one of the HPC access ports. This is only applicable to vanes that are immediately in view and to which you have access.

1 For AP port locations:

HPC Access Port AP Locations ** ON A/C NOT FOR ALL

and

HPC Vane and Blade Locations ** ON A/C NOT FOR ALL

2 For damage examples:

HPC IGVs and 1st, 2nd and 3rd Stage Variable Vanes ** ON A/C NOT FOR ALL

HPC 1st, 2nd, 3rd and 4th Stage Integrally Bladed Rotor Airfoils ** ON A/C NOT FOR ALL

HPC 4th and 5th Stage Stators ** ON A/C NOT FOR ALL

HPC 5th Stage Integrally Bladed Rotor Airfoils ** ON A/C NOT FOR ALL

HPC 6th and 7th Stage Stators ** ON A/C NOT FOR ALL

HPC 6th and 7th Stage Integrally Bladed Rotor Airfoils ** ON A/C NOT FOR ALL

HPC 8th Stage Integrally Bladed Rotor Airfoils ** ON A/C NOT FOR ALL

and

HPC 1st through 8th Stage Airfoil/Blade Outer Rubstrips and HPC 4th through 7th Stage Stator Inner Rubstrips ** ON A/C NOT FOR ALL

(9) Examine the HPC through AP HPC-1.

HPC Vane and Blade Locations ** ON A/C NOT FOR ALL

(a) Examine the variable Inlet Guide Vanes (IGV). Refer to table 2.

HPC Access Port AP Locations ** ON A/C NOT FOR ALL

and

HPC IGVs and 1st, 2nd and 3rd Stage Variable Vanes ** ON A/C NOT FOR ALL

1 Separation between two dents in the airfoil areas must be a minimum of two times the size of the dent and must be more than 0.039 in. (0.991 mm).
2 Separation between two nicks or scratches in the airfoil areas must be more than three times the size of the nick or scratch.
(b) Examine the 1st stage integrally bladed rotor airfoils. Refer to table 3.

HPC 1st, 2nd, 3rd and 4th Stage Integrally Bladed Rotor Airfoils ** ON A/C NOT FOR ALL

and

HPC 1st through 8th Stage Airfoil/Blade Outer Rubstrips and HPC 4th through 7th Stage Stator Inner Rubstrips ** ON A/C NOT FOR ALL

1 The leading and trailing edges of the airfoils must be free of sharp, curled or blunt edges.
2 On the leading edges, a maximum of two damage locations per airfoil is permitted, as well as shallow round bottom dents as defined in table 3.
3 You must blend the airfoil areas with indications that have compressed material, raised edges and/or damage with small radii or ragged edges.
4 On the convex side of the airfoils (areas B and C), a maximum of two damage locations for each airfoil is permitted.
5 A maximum of 26 surface damage locations is permitted in the integrally bladed rotor airfoil areas.
(10) Examine the HPC through AP HPC-5.

HPC Vane and Blade Locations ** ON A/C NOT FOR ALL

(a) Examine the 4th stator vanes. Refer to table 4.

HPC 4th and 5th Stage Stators ** ON A/C NOT FOR ALL

and

HPC 1st through 8th Stage Airfoil/Blade Outer Rubstrips and HPC 4th through 7th Stage Stator Inner Rubstrips ** ON A/C NOT FOR ALL

(b) Examine the 5th stage integrally bladed rotor airfoils. Refer to table 5.

HPC 5th Stage Integrally Bladed Rotor Airfoils ** ON A/C NOT FOR ALL

and

HPC 1st through 8th Stage Airfoil/Blade Outer Rubstrips and HPC 4th through 7th Stage Stator Inner Rubstrips ** ON A/C NOT FOR ALL

CAUTION: DAMAGE TO THE BORESCOPE CAN OCCUR IF CAUTION IS NOT USED WHILE ACCESSING AP HPC-8. A 4 MM SCOPE IS REQUIRED BECAUSE OF LIMITED CLEARANCE. USE CAUTION WHEN ROTATING THE ROTOR, THE SCOPE CAN BE DAMAGED WHEN TRAPPED BETWEEN THE BLADES AND INNER CASE OPENING.

(11) Examine the HPC through AP HPC-8.

HPC Vane and Blade Locations ** ON A/C NOT FOR ALL

(a) You must view all of the HPC stages behind the stage that shows new damage and all stages forward to the previous normal borescope AP location if new damage is found at one of the above noted stages.
(b) Remove the applicable borescope AP plugs for the additional HPC stages to be inspected.
(c) Examine the 7th stator vanes. Refer to table 6.

HPC 6th and 7th Stage Stators ** ON A/C NOT FOR ALL

and

HPC 1st through 8th Stage Airfoil/Blade Outer Rubstrips and HPC 4th through 7th Stage Stator Inner Rubstrips ** ON A/C NOT FOR ALL

(d) Examine the 8th stage integrally bladed rotor airfoils. Refer to table 8.

HPC 8th Stage Integrally Bladed Rotor Airfoils ** ON A/C NOT FOR ALL

and

HPC 1st through 8th Stage Airfoil/Blade Outer Rubstrips and HPC 4th through 7th Stage Stator Inner Rubstrips ** ON A/C NOT FOR ALL

NOTE:

HPC 8th Stage Integrally Bladed Rotor Airfoils ** ON A/C NOT FOR ALL

(e) Examine the HPC 7th stage stator inner rubstrip. Refer to table 9.

HPC 1st through 8th Stage Airfoil/Blade Outer Rubstrips and HPC 4th through 7th Stage Stator Inner Rubstrips ** ON A/C NOT FOR ALL

(12) Examine the additional HPC stages with a borescope as necessary to identify damage.
(a) Examine the HPC through AP HPC-2 to examine the HPC 1st stage variable vanes, HPC 1st stage locating ring segment and HPC 2nd stage integrally bladed rotor airfoils.

HPC Vane and Blade Locations ** ON A/C NOT FOR ALL

1 Examine the 1st stage variable vanes. Refer to table 2.

HPC IGVs and 1st, 2nd and 3rd Stage Variable Vanes ** ON A/C NOT FOR ALL

a Separation between two dents in the airfoil areas must be a minimum of two times the size of the dent and must be more than 0.039 in. (0.991 mm).
b Separation between two nicks or scratches in the airfoil areas must be more than three times the size of the nick or scratch.
2 Examine the 1st stage locating ring segment and ring vane support for RTV seal missing or seal protruding. Missing or protruding condition of the RTV seal is permitted as is, and the removal of the RTV silicone that is seen is not mandatory for engine operation.

HPC IGVs and 1st, 2nd and 3rd Stage Variable Vanes ** ON A/C NOT FOR ALL

3 Examine the 2nd stage integrally bladed rotor airfoils. Refer to table 3.

HPC 1st, 2nd, 3rd and 4th Stage Integrally Bladed Rotor Airfoils ** ON A/C NOT FOR ALL

and

HPC 1st through 8th Stage Airfoil/Blade Outer Rubstrips and HPC 4th through 7th Stage Stator Inner Rubstrips ** ON A/C NOT FOR ALL

a The leading and trailing edges of the airfoils must be free of sharp, curled or blunt edges.
b On the leading edges, a maximum of two damage locations per airfoil is permitted, as well as shallow round bottom dents as defined in table 3.
c You must blend airfoil areas with indications that have compressed material, raised edges and/or damage with small radii or ragged edges.
d On the convex side of the airfoils (areas B and C), a maximum of two areas of damage for each airfoil is permitted.
e A maximum of 38 surface damage locations is permitted in the airfoil areas of the integrally bladed rotor.
(b) Examine the HPC through AP HPC-3 to examine the HPC 2nd stage variable vanes, HPC 2nd locating ring segment and HPC 3rd stage integrally bladed rotor airfoils.

HPC Vane and Blade Locations ** ON A/C NOT FOR ALL

NOTE: To improve access, it can be necessary to turn the vanes.

1 Examine the 2nd stage variable vanes. Refer to table 2.

HPC IGVs and 1st, 2nd and 3rd Stage Variable Vanes ** ON A/C NOT FOR ALL

a Separation between two dents in the airfoil areas must be a minimum of two times the size of the dent and must be more than 0.039 in. (0.991 mm).
b Separation between two nicks or scratches in the airfoil areas must be more than three times the size of the nick or scratch.
2 Examine the 2nd stage locating ring segment and ring vane support for RTV seal missing or seal protruding. Missing or protruding condition of the RTV seal is permitted as is, and the removal of the RTV silicone that is seen is not mandatory for engine operation.

HPC IGVs and 1st, 2nd and 3rd Stage Variable Vanes ** ON A/C NOT FOR ALL

3 Examine the 3rd stage integrally bladed rotor airfoils. Refer to table 3.

HPC 1st, 2nd, 3rd and 4th Stage Integrally Bladed Rotor Airfoils ** ON A/C NOT FOR ALL

and

HPC 1st through 8th Stage Airfoil/Blade Outer Rubstrips and HPC 4th through 7th Stage Stator Inner Rubstrips ** ON A/C NOT FOR ALL

a The leading and trailing edges of the airfoils must be free of sharp, curled or blunt edges.
b On the leading edges, a maximum of two damage locations per airfoil is permitted, as well as shallow round bottom dents as defined in table 3.
c You must blend the airfoil areas with indications that have compressed material, raised edges and/or damage with small radii or ragged edges.
d On the convex side of the airfoils (areas B and C), a maximum of two areas of damage for each airfoil is permitted.
e A maximum of 52 surface damage locations is permitted in the airfoil areas of the integrally bladed rotor.
(c) Examine the HPC through AP HPC-4 to examine the HPC 3rd variable vanes, HPC 3rd locating ring segment and HPC 4th stage integrally bladed rotor airfoils.

HPC Vane and Blade Locations ** ON A/C NOT FOR ALL

1 Examine the 3rd stage variable vanes as follows. Refer to table 2.

HPC IGVs and 1st, 2nd and 3rd Stage Variable Vanes ** ON A/C NOT FOR ALL

a Loosen or disconnect the hydraulic fuel pressure tube (CP03) and the hydraulic fuel return tube (CR03) to remove hydraulic pressure from the HPC Stator Vane Actuators (SVA), if necessary (Ref. AMM TASK 75-31-02-000-801).

CAUTION: WHEN YOU OPERATE THE HPC VANES, USE ONLY THE SPECIFIED WRENCHING PAD. IF YOU DO NOT OBEY THIS INSTRUCTION, DAMAGE TO ENGINE COMPONENTS CAN OCCUR.

b Use the WRENCH - STANDARD on the wrenching feature to move the primary HPC SVA from the fully closed (actuator rod retracted) to the fully open (actuator rod extended) position. Operation must be smooth with no binding.
c Examine the 3rd stage variable vanes:

Separation between two dents in the airfoil areas must be a minimum of two times the size of the dent and must be more than 0.039 in. (0.991 mm).
Separation between two nicks or scratches in the airfoil areas must be more than three times the size of the nick or scratch.

d Return the HPC SVA to the fully closed position (actuator rod retracted).
e Connect the hydraulic fuel pressure tube (CP03) and hydraulic fuel return tube (CR03) to the actuator, if necessary (Ref. AMM TASK 75-31-02-400-801).
2 Examine the 3rd stage locating ring segment and ring vane support for RTV seal missing or seal protruding. Missing or protruding condition of the RTV seal is permitted as is, and the removal of the RTV silicone that is seen is not mandatory for engine operation.

HPC IGVs and 1st, 2nd and 3rd Stage Variable Vanes ** ON A/C NOT FOR ALL

3 Examine the 4th stage integrally bladed rotor airfoils. Refer to table 3.

HPC 1st, 2nd, 3rd and 4th Stage Integrally Bladed Rotor Airfoils ** ON A/C NOT FOR ALL

and

HPC 1st through 8th Stage Airfoil/Blade Outer Rubstrips and HPC 4th through 7th Stage Stator Inner Rubstrips ** ON A/C NOT FOR ALL

a The leading and trailing edges of the airfoils must be free of sharp, curled or blunt edges.
b On the leading edges, a maximum of two damage locations per airfoil is permitted, as well as shallow round bottom dents as defined in table 3. A maximum of 58 damage locations is permitted on the leading edges along the full circumference of the disk.
c You must blend the airfoil areas with indications that have compressed material, raised edges and/or damage with small radii or ragged edges.
d On the convex side of the airfoils (areas B and C), a maximum of two areas of damage for each airfoil is permitted. A maximum of 58 damage locations is permitted on the airfoil convex side along the full circumference of the disk.
(d) Examine the HPC through AP HPC-6 to examine the HPC 5th stator vanes and HPC 6th stage integrally bladed rotor airfoils.

HPC Vane and Blade Locations ** ON A/C NOT FOR ALL

1 Examine the 5th stator vanes. Refer to table 4.

HPC 4th and 5th Stage Stators ** ON A/C NOT FOR ALL

and

HPC 1st through 8th Stage Airfoil/Blade Outer Rubstrips and HPC 4th through 7th Stage Stator Inner Rubstrips ** ON A/C NOT FOR ALL

2 Examine the 6th stage integrally bladed rotor airfoils. Refer to table 7.

HPC 6th and 7th Stage Integrally Bladed Rotor Airfoils ** ON A/C NOT FOR ALL

and

HPC 1st through 8th Stage Airfoil/Blade Outer Rubstrips and HPC 4th through 7th Stage Stator Inner Rubstrips ** ON A/C NOT FOR ALL

3 Examine the HPC 5th stage stator inner rubstrip. Refer to table 9.

HPC 1st through 8th Stage Airfoil/Blade Outer Rubstrips and HPC 4th through 7th Stage Stator Inner Rubstrips ** ON A/C NOT FOR ALL

(e) Examine the HPC through AP HPC-7 to examine the HPC and HPC components.

HPC Vane and Blade Locations ** ON A/C NOT FOR ALL

1 Examine the 6th stator vanes. Refer to table 6.

HPC 6th and 7th Stage Stators ** ON A/C NOT FOR ALL

and

HPC 1st through 8th Stage Airfoil/Blade Outer Rubstrips and HPC 4th through 7th Stage Stator Inner Rubstrips ** ON A/C NOT FOR ALL

2 Examine the 7th stage integrally bladed rotor airfoils. Refer to table 7.

HPC 6th and 7th Stage Integrally Bladed Rotor Airfoils ** ON A/C NOT FOR ALL

and

HPC 1st through 8th Stage Airfoil/Blade Outer Rubstrips and HPC 4th through 7th Stage Stator Inner Rubstrips ** ON A/C NOT FOR ALL

3 Examine the HPC 6th stage stator inner rubstrip. Refer to table 9.

HPC 1st through 8th Stage Airfoil/Blade Outer Rubstrips and HPC 4th through 7th Stage Stator Inner Rubstrips ** ON A/C NOT FOR ALL

EXAMINE	DAMAGE	DISPOSITION
All visible areas of IGVs and 1st, 2nd and 3rd stage vanes for:
Cracks	All quantities	Not permitted. Contact Pratt & Whitney.
Area A (IGV outer fillet radius) for:
Nicks, dents and pits	All quantities more than 0.026 in. (0.660 mm) depth	Not permitted. Contact Pratt & Whitney.
Area A (1st stage variable guide vane) for:
Nicks, dents and pits	All quantities more than 0.017 in. (0.432 mm) depth	Not permitted. Contact Pratt & Whitney.
Area A (2nd stage variable guide vane) for:
Nicks, dents and pits	All quantities more than 0.022 in. (0.559 mm) depth	Not permitted. Contact Pratt & Whitney.
Area A (3rd stage variable guide vane) for:
Nicks, dents and pits	All quantities more than 0.030 in. (0.762 mm) depth	Not permitted. Contact Pratt & Whitney.
Area B (IGV airfoil) for:
Nicks, dents and pits	All quantities more than 0.010 in. (0.254 mm) depth	Not permitted. Contact Pratt & Whitney.
Area B (1st, 2nd and 3rd stage variable guide vane) for:
Nicks, dents and pits	All quantities more than 0.020 in. (0.508 mm) depth	Not permitted. Contact Pratt & Whitney.
Area C (IGV leading and trailing edges) for:
Nicks, dents and pits	All quantities more than 0.019 in. (0.483 mm) depth	Not permitted. Contact Pratt & Whitney.
Area C (1st stage variable guide vane) for:
Nicks, dents and pits	All quantities more than 0.025 in. (0.635 mm) depth	Not permitted. Contact Pratt & Whitney.
Area C (2nd stage variable guide vane) for:
Nicks, dents and pits	All quantities more than 0.031 in. (0.787 mm) depth	Not permitted. Contact Pratt & Whitney.
Area C (3rd stage variable guide vane) for:
Nicks, dents and pits	All quantities more than 0.024 in. (0.610 mm) depth	Not permitted. Contact Pratt & Whitney.
Area D (IGV airfoil leading and trailing edges (area C not included)) for:
Nicks, dents and pits	All quantities more than 0.010 in. (0.254 mm) depth	Not permitted. Contact Pratt & Whitney.
Area D (1st and 2nd stage variable guide vane) for:
Nicks, dents and pits	All quantities more than 0.015 in. (0.381 mm) depth	Not permitted. Contact Pratt & Whitney.
Area D (3rd stage variable guide vane) for:
Nicks, dents and pits	All quantities more than 0.012 in. (0.305 mm) depth	Not permitted. Contact Pratt & Whitney.
Area E (IGV and 1st stage variable guide vane inner fillet radius) for:
Nicks, dents and pits	All quantities more than 0.009 in. (0.229 mm) depth	Not permitted. Contact Pratt & Whitney.
Area E (2nd stage variable guide vane inner fillet radius) for:
Nicks, dents and pits	All quantities more than 0.020 in. (0.508 mm) depth	Not permitted. Contact Pratt & Whitney.
Area E (3rd stage variable guide vane inner fillet radius) for:
Nicks, dents and pits	All quantities more than 0.039 in. (0.991 mm) depth	Not permitted. Contact Pratt & Whitney.
Area F (IGV and 1st, 2nd and 3rd stage variable guide vane outer and inner platform (area A and area E not included)) for:
Nicks, dents and pits	All quantities more than 0.020 in. (0.508 mm) depth	Not permitted. Contact Pratt & Whitney.
Area G (IGV tips) for:
Bent or broken tip corners	All quantities more than 0.118 in. (2.997 mm) by 0.118 in. (2.997 mm) size	Not permitted. Contact Pratt & Whitney.
Area G (1st stage variable guide vane tips) for:
Bent or broken tip corners	All quantities more than 0.098 in. (2.489 mm) by 0.098 in. (2.489 mm) size	Not permitted. Contact Pratt & Whitney.
Area G (2nd stage variable guide vane tips) for:
Bent or broken tip corners	All quantities more than 0.079 in. (2.007 mm) by 0.079 in. (2.007 mm) size	Not permitted. Contact Pratt & Whitney.
Area G (3rd stage variable guide vane tips) for:
Bent or broken tip corners	All quantities more than 0.059 in. (1.499 mm) by 0.059 in. (1.499 mm) size	Not permitted. Contact Pratt & Whitney.
Reference dimension 1 for IGV and 1st and 2nd stage variable guide vane	0.079 in. (2.007 mm) maximum
Reference dimension 1 for 3rd stage variable guide vane	0.095 in. (2.413 mm) maximum
Reference dimension 2 for IGV	0.394 in. (10.008 mm) maximum
Reference dimension 2 for 1st stage variable guide vane	0.276 in. (7.010 mm) maximum
Reference dimension 2 for 2nd and 3rd stage variable guide vane	0.237 in. (6.020 mm) maximum
Dimension 3 for IGV	0.118 in. (2.997 mm) maximum
Dimension 3 for 1st stage variable guide vane	0.098 in. (2.489 mm) maximum
Dimension 3 for 2nd stage variable guide vane	0.079 in. (2.007 mm) maximum
Dimension 3 for 3rd stage variable guide vane	0.059 in. (1.499 mm) maximum
Reference dimension 4 for IGV	0.283 in. (7.188 mm) maximum
Reference dimension 4 for 1st stage variable guide vane	0.177 in. (4.496 mm) maximum
Reference dimension 4 for 2nd stage variable guide vane	0.209 in. (5.309 mm) maximum
Reference dimension 4 for 3rd stage variable guide vane	0.236 in. (5.994 mm) maximum

Table - Borescope Inspection/Limits for HPC IGVs and 1st, 2nd and 3rd Stage Variable Vanes

EXAMINE	DAMAGE	DISPOSITION
All visible areas of 1st, 2nd, 3rd and 4th stage integrally bladed rotor airfoils for:
Cracks or tears	All quantities	Not permitted. Contact Pratt & Whitney.
Bulging	All quantities	Not permitted. Contact Pratt & Whitney.
Overheating (burning or intensified local blueing)	All quantities	Not permitted. Contact Pratt & Whitney.
Area A (1st and 2nd stage integrally bladed rotor) for:
Nicks, dents and pits	All quantities more than 0.008 in. (0.203 mm) depth	Not permitted. Contact Pratt & Whitney.
Area A (3rd and 4th stage integrally bladed rotor) for:
Nicks, dents and pits	All quantities more than 0.004 in. (0.102 mm) depth	Not permitted. Contact Pratt & Whitney.
Area B (1st stage integrally bladed rotor outer airfoil) for:
Nicks, dents and pits	All quantities more than 0.012 in. (0.305 mm) depth	Not permitted. Contact Pratt & Whitney.
Area B (2nd stage integrally bladed rotor outer airfoil) for:
Nicks, dents and pits	All quantities more than 0.004 in. (0.102 mm) depth	Not permitted. Contact Pratt & Whitney.
Area B (3rd stage integrally bladed rotor outer airfoil) for:
Nicks, dents and pits	All quantities more than 0.005 in. (0.127 mm) depth	Not permitted. Contact Pratt & Whitney.
Area B (4th stage integrally bladed rotor outer airfoil) for:
Nicks, dents and pits	All quantities more than 0.008 in. (0.203 mm) depth	Not permitted. Contact Pratt & Whitney.
Area C (1st stage integrally bladed rotor inner airfoil) for:
Nicks, dents and pits	All quantities more than 0.012 in. (0.305 mm) depth	Not permitted. Contact Pratt & Whitney.
Area C (2nd and 4th stage integrally bladed rotor inner airfoil) for:
Nicks, dents and pits	All quantities more than 0.008 in. (0.203 mm) depth	Not permitted. Contact Pratt & Whitney.
Area C (3rd stage integrally bladed rotor inner airfoil) for:
Nicks, dents and pits	All quantities more than 0.005 in. (0.127 mm) depth	Not permitted. Contact Pratt & Whitney.
Area D (1st, 2nd, 3rd and 4th stage integrally bladed rotor leading and trailing edges) for:
Nicks, dents and pits	All quantities more than 0.031 in. (0.787 mm) depth	Not permitted. Contact Pratt & Whitney.
Area D (1st and 2nd stage integrally bladed rotor shallow round bottom dents) for:	All quantities more than 0.004 in. (0.102 mm) maximum depth with a 5 to 1 − 10 to 1 diameter-to-depth ratio	Not permitted. Contact Pratt & Whitney.
Area D (3rd and 4th stage integrally bladed rotor shallow round bottom dents) for:	All quantities more than 0.002 in. (0.051 mm) maximum depth with a 5 to 1 − 10 to 1 diameter-to-depth ratio	Not permitted. Contact Pratt & Whitney.
Area E (1st, 2nd, 3rd and 4th stage integrally bladed rotor fillet radius) for:
Nicks, dents and pits	All quantities	Not permitted. Contact Pratt & Whitney.
Area F (1st, 2nd, 3rd and 4th stage integrally bladed rotor airfoil annular surface) for:
Nicks, dents and pits	All quantities	Not permitted. Contact Pratt & Whitney.
Area G (1st stage integrally bladed rotor airfoil tip corner) for:
Bent or broken tip corners	All quantities more than 0.120 in. (3.048 mm) by 0.120 in. (3.048 mm)	Not permitted. Contact Pratt & Whitney.
Area G (2nd stage integrally bladed rotor airfoil tip corner) for:
Bent or broken tip corners	All quantities more than 0.100 in. (2.540 mm) by 0.100 in. (2.540 mm)	Not permitted. Contact Pratt & Whitney.
Area G (3rd stage integrally bladed rotor airfoil tip corner) for:
Bent or broken tip corners	All quantities more than 0.080 in. (2.032 mm) by 0.080 in. (2.032 mm)	Not permitted. Contact Pratt & Whitney.
Area G (4th stage integrally bladed rotor airfoil tip corner) for:
Bent or broken tip corners	All quantities more than 0.060 in. (1.524 mm) by 0.060 in. (1.524 mm)	Not permitted. Contact Pratt & Whitney.
Area H (1st, 2nd, 3rd and 4th stage integrally bladed rotor squealer tip) for:
Nicks, dents and pits	All quantities more than 0.002 in. (0.051 mm) depth	Not permitted. Contact Pratt & Whitney.
Reference dimension 1 for 1st stage integrally bladed rotor	1.502 in. (38.151 mm) minimum
Reference dimension 1 for 2nd stage integrally bladed rotor	0.9857 in. (25.0367 mm) minimum
Reference dimension 1 for 3rd stage integrally bladed rotor	0.681 in. (17.297 mm) minimum
Reference dimension 1 for 4th stage integrally bladed rotor	0.469 in. (11.913 mm) minimum
Reference dimension 2 for 1st stage integrally bladed rotor	0.080 in. (2.032 mm) minimum
Reference dimension 2 for 2nd, 3rd and 4th stage integrally bladed rotor	0.060 in. (1.524 mm) minimum
Dimension 3 for 1st stage integrally bladed rotor	0.120 in. (3.048 mm) maximum
Dimension 3 for 2nd stage integrally bladed rotor	0.100 in. (2.540 mm) maximum
Dimension 3 for 3rd stage integrally bladed rotor	0.080 in. (2.032 mm) maximum
Dimension 3 for 4th stage integrally bladed rotor	0.060 in. (1.524 mm) maximum
Reference dimension 4 for 1st stage integrally bladed rotor	0.350 in. (8.890 mm) minimum
Reference dimension 4 for 2nd stage integrally bladed rotor	0.260 in. (6.604 mm) minimum
Reference dimension 4 for 3rd stage integrally bladed rotor	0.180 in. (4.572 mm) minimum
Reference dimension 4 for 4th stage integrally bladed rotor	0.160 in. (4.064 mm) minimum

Table - Borescope Inspection/Limits for HPC 1st, 2nd, 3rd and 4th Stage Integrally Bladed Rotor Airfoils

EXAMINE	DAMAGE	DISPOSITION
Area A (vane leading and trailing edges (does not include outer radius and inner tip areas)) for:
Cracks	All quantities	Not permitted. Remove the engine from service.
Tears	All quantities	Not permitted. Contact Pratt & Whitney.
Nicks and dents	All quantities not more than 0.010 in. (0.254 mm) depth	Permitted
	All quantities more than 0.010 in. (0.254 mm) to 0.015 in. (0.381 mm) depth	Permitted for a maximum inspection interval of five flight cycles.
	All quantities more than 0.015 in. (0.381 mm) depth	Not permitted. Contact Pratt & Whitney.
	Nicks or dents at two or more locations on the leading edge with 0.250 in. (6.350 mm) or more separation	Permitted
	Nicks or dents at two or more locations on the leading edge with less than 0.250 in. (6.350 mm) separation	Not permitted. Contact Pratt & Whitney.
	Nicks or dents at two or more locations on the trailing edge with 0.250 in. (6.350 mm) or more separation	Permitted
	Nicks or dents at two or more locations on the trailing edge with less than 0.250 in. (6.350 mm) separation	Not permitted. Contact Pratt & Whitney.
	Nicks or dents at both trailing edge and leading edge that are radially apart by 0.250 in. (6.350 mm) minimum	Permitted
	Nicks or dents at both trailing edge and leading edge that are directly opposite each other or radially apart by less than 0.250 in. (6.350 mm)	Not permitted. Contact Pratt & Whitney.
Area A (vane convex and concave surfaces) for:
Cracks	All quantities	Not permitted. Remove the engine from service.
Nicks and dents	All quantities not more than 0.010 in. (0.254 mm) depth, must be 0.250 in. (6.350 mm) apart from other nicks or dents	Permitted
	All quantities more than 0.010 in. (0.254 mm) depth with less than 0.250 in. (6.350 mm) separation from other nicks or dents	Not permitted. Contact Pratt & Whitney.
Area K (vane airfoil tip (leading or trailing edge)) for:
Bent or broken corners, missing material, nicks and dents	All quantities not more than 0.125 in. (3.175 mm) by 0.125 in. (3.175 mm)	Permitted
	All quantities more than 0.125 in. (3.175 mm) by 0.125 in. (3.175 mm)	Not permitted. Contact Pratt & Whitney.
Area J (vane airfoil tip area (does not include the leading and trailing edges)) for:
Cracks	All quantities	Not permitted. Remove the engine from service.
Tears	All quantities	Not permitted. Contact Pratt & Whitney.
Nicks and dents	All quantities not more than 0.020 in. (0.508 mm) depth	Permitted
	All quantities more than 0.020 in. (0.508 mm) to 0.030 in. (0.762 mm) depth	Permitted for a maximum inspection interval of five flight cycles.
	All quantities more than 0.030 in. (0.762 mm) depth	Not permitted. Contact Pratt & Whitney.
Area B (vane outer radius area) for:
Cracks	All quantities	Not permitted. Remove the engine from service.
Nicks and dents	All quantities	Not permitted. Contact Pratt & Whitney.
Area C (vane outer platform) for:
Cracks	All quantities	Not permitted. Remove the engine from service.
Nicks and dents	All quantities not more than 0.030 in. (0.762 mm) depth	Permitted
	All quantities more than 0.030 in. (0.762 mm) depth	Not permitted. Contact Pratt & Whitney.

Table - Borescope Inspection/Limits for HPC 4th and 5th Stage Stators

EXAMINE	DAMAGE	DISPOSITION
Area A (blade tip area (does not include the leading and trailing edges)) for:
Cracks	All quantities	Not permitted. Remove the engine from service.
Tears	All quantities	Not permitted. Contact Pratt & Whitney.
Nicks and dents	All quantities not more than 0.020 in. (0.508 mm) depth	Permitted
	All quantities more than 0.020 in. (0.508 mm) to 0.030 in. (0.762 mm) depth	Permitted for a maximum inspection interval of five flights.
	All quantities more than 0.030 in. (0.762 mm) depth	Not permitted. Contact Pratt & Whitney.
Tip wear	All quantities	Permitted
Abradable transfer from OAS to airfoil concave side	All quantities	Permitted
Discoloration	All quantities	Not permitted. Contact Pratt & Whitney.
Burrs on airfoil convex side	All quantities	Not permitted. Contact Pratt & Whitney.
Area B (blade tip (at leading and trailing edges)) for:
Bent or broken corners, missing material, nicks and dents	All quantities not more than 0.125 in. (3.175 mm) by 0.125 in. (3.175 mm)	Permitted
	All quantities more than 0.125 in. (3.175 mm) by 0.125 in. (3.175 mm)	Not permitted. Contact Pratt & Whitney.
Cracks	All quantities	Not permitted. Remove the engine from service.
Tip wear	All quantities	Permitted
Abradable transfer from OAS to airfoil concave side	All quantities	Permitted
Discoloration	All quantities	Not permitted. Contact Pratt & Whitney.
Burrs on airfoil convex side	All quantities	Not permitted. Contact Pratt & Whitney.
Area C (blade root radius) for:
Cracks	All quantities	Not permitted. Remove the engine from service.
Nicks and dents	All quantities	Not permitted. Contact Pratt & Whitney.
Area D (blade root platform) for:
Cracks	All quantities	Not permitted. Remove the engine from service.
Nicks and dents	All quantities not more than 0.020 in. (0.508 mm) depth	Permitted
	All quantities 0.020 in. (0.508 mm) to 0.030 in. (0.762 mm) depth	Permitted for a maximum inspection interval of five flight cycles.
	All quantities more than 0.030 in. (0.762 mm) depth	Not permitted. Contact Pratt & Whitney.
Area E (blade airfoil leading and trailing edges (does not include the tip and root radius)) for:
Cracks	All quantities	Not permitted. Remove the engine from service.
Tears	All quantities	Not permitted. Contact Pratt & Whitney.
Nicks and dents	All quantities not more than 0.010 in. (0.254 mm) depth	Permitted
	All quantities more than 0.010 in. (0.254 mm) to 0.020 in. (0.508 mm) depth	Permitted for a maximum inspection interval of five flight cycles.
	All quantities more than 0.020 in. (0.508 mm) depth	Not permitted. Contact Pratt & Whitney.
	Nicks or dents at two or more locations on the leading edge with 0.125 in. (3.175 mm) or more separation	Permitted
	Nicks or dents at two or more locations on the leading edge with less than 0.125 in. (3.175 mm) separation	Not permitted. Contact Pratt & Whitney.
	Nicks or dents at two or more locations on the trailing edge with 0.125 in. (3.175 mm) or more separation	Permitted
	Nicks or dents at two or more locations on the trailing edge with less than 0.125 in. (3.175 mm) separation	Not permitted. Contact Pratt & Whitney.
	Nicks or dents at the trailing edge and leading edge that are radially apart by 0.125 in. (3.175 mm) minimum	Permitted
	Nicks or dents at the trailing edge and leading edge that are directly opposite each other or are radially apart by less than 0.125 in. (3.175 mm)	Not permitted. Contact Pratt & Whitney.
Area E (blade airfoil (does not include the leading edge, trailing edge and blade tip)) for:
Cracks	All quantities	Not permitted. Remove the engine from service.
Nicks and dents	All quantities 0.008 in. (0.203 mm) depth or less	Permitted
	All quantities more than 0.008 in. (0.203 mm) depth	Not permitted. Contact Pratt & Whitney.

Table - Borescope Inspection/Limits for 5th Stage Integrally Bladed Rotor Airfoils

EXAMINE	DAMAGE	DISPOSITION
Area A (vane leading and trailing edges (does not include the outer radius and inner tip areas)) for:
Cracks	All quantities	Not permitted. Remove the engine from service.
Tears	All quantities	Not permitted. Contact Pratt & Whitney.
Nicks and dents	All quantities not more than 0.008 in. (0.203 mm) depth	Permitted
	All quantities more than 0.008 in. (0.203 mm) to 0.012 in. (0.305 mm) depth	Permitted for a maximum inspection interval of five flight cycles.
	All quantities more than 0.012 in. (0.305 mm) depth	Not permitted. Contact Pratt & Whitney.
	Nicks or dents at two or more locations on the leading edge with 0.080 in. (2.032 mm) or more separation	Permitted
	Nicks or dents at two or more locations on the leading edge with less than 0.080 in. (2.032 mm) or more separation	Not permitted. Contact Pratt & Whitney.
	Nicks or dents at two or more locations on the trailing edge with 0.080 in. (2.032 mm) or more separation	Permitted
	Nicks or dents at two or more locations on the trailing edge with less than 0.080 in. (2.032 mm) separation	Not permitted. Contact Pratt & Whitney.
	Nicks or dents at the trailing edge and the leading edge that are radially apart by 0.080 in. (2.032 mm) minimum	Permitted
	Nicks or dents at the trailing edge and the leading edge that are directly opposite each other or radially apart by less than 0.080 in. (2.032 mm)	Not permitted. Contact Pratt & Whitney.
Area A (vane convex and concave surfaces) for:
Cracks	All quantities	Not permitted. Remove the engine from service.
Nicks and dents	All quantities not more than 0.005 in. (0.127 mm) depth	Permitted
	All quantities more than 0.005 in. (0.127 mm) depth with more than 0.080 in. (2.032 mm) separation from other nicks or dents	Permitted
Area K (vane airfoil tip (leading or trailing edge)) for:
Bent or broken corners, missing material, nicks and dents	All quantities not more than 0.080 in. (2.032 mm) by 0.080 in. (2.032 mm)	Permitted
	All quantities more than 0.080 in. (2.032 mm) by 0.080 in. (2.032 mm)	Not permitted. Contact Pratt & Whitney.
Area J (vane airfoil tip area (does not include the leading and trailing edges)) for:
Cracks	All quantities	Not permitted. Remove the engine from service.
Tears	All quantities	Not permitted. Contact Pratt & Whitney.
Nicks and dents	All quantities not more than 0.015 in. (0.381 mm) depth	Permitted
	All quantities more than 0.015 in. (0.381 mm) to 0.020 in. (0.508 mm) depth	Permitted for a maximum inspection interval of five flight cycles.
	All quantities more than 0.020 in. (0.508 mm) depth	Not permitted. Contact Pratt & Whitney.
Area B (vane outer radius area) for:
Cracks	All quantities	Not permitted. Remove the engine from service.
Nicks and dents	All quantities	Not permitted. Contact Pratt & Whitney..
Area C (vane outer platform) for:
Cracks	All quantities	Not permitted. Remove the engine from service.
Nicks and dents	All quantities 0.015 in. (0.381 mm) depth or less	Permitted
	All quantities more than 0.015 in. (0.381 mm) depth	Not permitted. Contact Pratt & Whitney.

Table - Borescope Inspection/Limits for HPC 6th and 7th Stage Stators

EXAMINE	DAMAGE	DISPOSITION
Area D (blade airfoil leading and trailing edges (does not include the tip and root radius)) for:
Cracks	All quantities	Not permitted. Remove the engine from service.
Tears	All quantities	Not permitted. Contact Pratt & Whitney.
Nicks and dents	All quantities not more than 0.012 in. (0.305 mm) depth	Permitted
	Quantity of one per airfoil more than 0.012 in. (0.305 mm) to 0.015 in. (0.381 mm) depth	Permitted
	All quantities more than 0.015 in. (0.381 mm) depth	Not permitted. Contact Pratt & Whitney.
	Nicks or dents at two or more locations on the leading edge with 0.080 in. (2.032 mm) or more separation	Permitted
	Nicks or dents at two or more locations on the leading edge with less than 0.080 in. (2.032 mm) separation	Not permitted. Contact Pratt & Whitney.
	Nicks or dents at two or more locations on the trailing edge with 0.080 in. (2.032 mm) or more separation	Permitted
	Nicks or dents at two or more locations on the trailing edge with less than 0.080 in. (2.032 mm) separation	Not permitted. Contact Pratt & Whitney.
	Nicks or dents at the trailing edge and the leading edge that are radially apart by 0.080 in. (2.032 mm) minimum	Permitted
	Nicks or dents at the trailing edge and the leading edge that are directly opposite each other or are radially apart by less than 0.080 in. (2.032 mm)	Not permitted. Contact Pratt & Whitney.
Area D (blade airfoil (does not include the leading and trailing edges or blade tip)) for:
Cracks	All quantities	Not permitted. Remove the engine from service.
Nicks and dents	All quantities not more than 0.005 in. (0.127 mm) depth	Permitted
	All quantities more than 0.005 in. (0.127 mm) depth	Not permitted. Contact Pratt & Whitney.
Area E (blade tip (at leading and trailing edges)) for:
Bent or broken corners, missing material, nicks and dents	All quantities not more than 0.08 in. (2.032 mm) by 0.08 in. (2.032 mm)	Permitted
	All quantities more than 0.08 in. (2.032 mm) by 0.08 in. (2.032 mm)	Not permitted. Contact Pratt & Whitney.
Cracks	All quantities	Not permitted. Remove the engine from service.
Tip wear	All quantities	Permitted
Abradable transfer from OAS to airfoil concave side	All quantities	Permitted
Discoloration	All quantities	Not permitted. Contact Pratt & Whitney.
Burrs on airfoil convex side	All quantities	Not permitted. Contact Pratt & Whitney.
Area F (blade tip area (does not include the leading and trailing edges)) for:
Cracks	All quantities	Not permitted. Remove the engine from service.
Tears	All quantities	Not permitted. Contact Pratt & Whitney.
Nicks and dents	All quantities not more than 0.020 in. (0.508 mm) depth	Permitted
	All quantities more than 0.020 in. (0.508 mm) to 0.030 in. (0.762 mm) depth	Permitted for a maximum inspection interval of five flight cycles.
	All quantities more than 0.030 in. (0.762 mm) depth	Not permitted. Contact Pratt & Whitney.
Tip wear	All quantities	Permitted
Abradable transfer from OAS to airfoil concave side	All quantities	Permitted
Discoloration	All quantities	Not permitted. Contact Pratt & Whitney.
Burrs on airfoil convex side	All quantities	Not permitted. Contact Pratt & Whitney.
Area G (blade root radius) for:
Cracks	All quantities	Not permitted. Remove the engine from service.
Nicks and dents	All quantities	Not permitted. Contact Pratt & Whitney.
Area H (blade root platform) for:
Cracks	All quantities	Not permitted. Contact Pratt & Whitney.
Nicks and dents	All quantities not more than 0.010 in. (0.254 mm) depth	Permitted
	All quantities more than 0.010 in. (0.254 mm) to 0.020 in. (0.508 mm) depth	Permitted for a maximum inspection interval of five flight cycles.
	All quantities more than 0.020 in. (0.508 mm) depth	Not permitted. Contact Pratt & Whitney.

Table - Borescope Inspection/Limits for HPC 6th and 7th Stage Integrally Bladed Rotor Airfoils

EXAMINE	DAMAGE	DISPOSITION
Area D (blade airfoil leading and trailing edges (does not include the tip and root radius)) for:
Cracks	All quantities	Not permitted. Remove the engine from service.
Tears	All quantities	Not permitted. Contact Pratt & Whitney.
Nicks and dents	All quantities no more than 0.012 in. (0.305 mm) depth	Permitted
	Quantity of one each airfoil more than 0.012 in. (0.305 mm) to 0.015 in. (0.381 mm) depth	Permitted
	All quantities more than 0.015 in. (0.381 mm) depth	Not permitted. Contact Pratt & Whitney.
	Nicks or dents at two or more locations on the leading edge with 0.080 in. (2.032 mm) or more separation	Permitted
	Nicks or dents at two or more locations on the leading edge with less than 0.080 in. (2.032 mm) separation	Not permitted. Contact Pratt & Whitney.
	Nicks or dents at two or more locations on the trailing edge with 0.080 in. (2.032 mm) or more separation	Permitted
	Nicks or dents at two or more locations on the trailing edge with less than 0.080 in. (2.032 mm) separation	Not permitted. Contact Pratt & Whitney.
	Nicks or dents at the trailing edge and the leading edge that are radially separated by 0.080 in. (2.032 mm) minimum	Permitted
	Nicks or dents at the trailing edge and the leading edge that are opposite each other or are radially separated by less than 0.080 in. (2.032 mm)	Not permitted. Contact Pratt & Whitney.
Area D (blade airfoil (does not include the leading and trailing edges or blade tip)) for:
Cracks	All quantities	Not permitted. Remove the engine from service.
Nicks and dents	All quantities no more than 0.005 in. (0.127 mm) depth	Permitted
	All quantities more than 0.005 in. (0.127 mm) depth	Not permitted. Contact Pratt & Whitney.
Area E (blade tip (at leading and trailing edges)) for:
Bent or broken corners, missing material, nicks and dents	All quantities no more than 0.080 in. (2.032 mm) by 0.080 in. (2.032 mm)	Permitted
	All quantities more than 0.080 in. (2.032 mm) by 0.080 in. (2.032 mm)	Not permitted. Contact Pratt & Whitney.
Cracks	All quantities	Not permitted. Remove the engine from service.
Airfoil tip coat for 8th stage integrally bladed rotors with Cubic Boron Nitride (CBN)	Tip coat (CBN) overspray	HPC 8th Stage Integrally Bladed Rotor Airfoils ** ON A/C NOT FOR ALL
Abradable transfer from OAS to airfoil concave side	All quantities	Permitted
Discoloration	All quantities	Not permitted. Contact Pratt & Whitney.
Burrs on airfoil convex side	All quantities	Not permitted. Contact Pratt & Whitney.
Area F (blade tip area (does not include the leading and trailing edges)) for:
Cracks	All quantities	Not permitted. Remove the engine from service.
Tears	All quantities	Not permitted. Contact Pratt & Whitney.
Nicks and dents	All quantities no more than 0.020 in. (0.508 mm) depth	Permitted
	All quantities more than 0.020 in. (0.508 mm) to 0.030 in. (0.762 mm) depth	Permitted for a maximum inspection interval of five flight cycles.
	All quantities more than 0.030 in. (0.762 mm) depth	Not permitted. Contact Pratt & Whitney.
Airfoil tip coat for 8th stage integrally bladed rotors with Cubic Boron Nitride (CBN)	Tip coat (CBN) overspray	HPC 8th Stage Integrally Bladed Rotor Airfoils ** ON A/C NOT FOR ALL
Abradable transfer from OAS to airfoil concave side	All quantities	Permitted
Discoloration	All quantities	Not permitted. Contact Pratt & Whitney.
Burrs on airfoil convex side	All quantities	Not permitted. Contact Pratt & Whitney.
Area G (blade root radius) for:
Cracks	All quantities	Not permitted. Remove the engine from service.
Nicks and dents	All quantities	Not permitted. Contact Pratt & Whitney.
Area H (blade root platform) for:
Cracks	All quantities	Not permitted. Remove the engine from service.
Nicks and dents	All quantities no more than 0.010 in. (0.254 mm) depth	Permitted
	All quantities more than 0.010 in. (0.254 mm) to 0.020 in. (0.508 mm) depth	Permitted for a maximum inspection interval of five flight cycles.
	All quantities more than 0.020 in. (0.508 mm) depth	Not permitted. Contact Pratt & Whitney.
Integrally bladed rotor airfoil general surfaces for:
	Loose or flaking scale	Permitted
Area J (blade airfoil leading edge (does not include the tip)) for:
Cracks	All quantities	Not permitted. Remove the engine from service.
Tears	All quantities	Not permitted. Contact Pratt & Whitney.
Nicks and dents	All quantities no more than 0.012 in. (0.305 mm) depth	Permitted
	Quantity of one each airfoil more than 0.012 in. (0.305 mm) to 0.018 in. (0.457 mm) depth	Permitted
	All quantities more than 0.018 in. (0.457 mm) depth	Not permitted. Contact Pratt & Whitney.
	Nicks or dents at two or more locations on the leading edge with 0.080 in. (2.032 mm) or more separation	Permitted
	Nicks or dents at two or more locations on the leading edge with less than 0.080 in. (2.032 mm) separation	Not permitted. Contact Pratt & Whitney.
	Nicks or dents at the leading edge that are radially separated by 0.080 in. (2.032 mm) minimum	Permitted
	Nicks or dents at the leading edge that are opposite each other or are radially separated by less than 0.080 in. (2.032 mm)	Not permitted. Contact Pratt & Whitney.
Area J (blade airfoil (does not include the leading and trailing edges or blade tip)) for:
Cracks	All quantities	Not permitted. Remove the engine from service.
Nicks and dents	All quantities not more than 0.005 in. (0.127 mm) depth	Permitted
	All quantities more than 0.005 in. (0.127 mm) depth	Not permitted. Contact Pratt & Whitney.

Table - Borescope Inspection/Limits for HPC 8th Stage Integrally Bladed Rotor Airfoils

EXAMINE	DAMAGE	DISPOSITION
Inner rubstrip for:
Missing or rubbed out material	Cumulative coat loss for stages 4 thru 7 less than 40 percent of the total coated rubstrip area without damage to bond coat.	Permitted
	Cumulative loss for stages 4 thru 7 more than or equal to 40 percent of the total coated rubstrip area or all loss of bond coat.	Not permitted. Contact Pratt & Whitney.
	NOTE: Complete delamination along all four stages is 400 percent of the total coated rubstrip area.

Table - Borescope Inspection/Limits for HPC Stator Inner Rubstrips, Stages 4 through 7

(13) If necessary, do the 360-degree inspection of the HPC outer rubstrips:
(a) Put the borescope through the applicable HPC borescope port.

HPC Access Port AP Locations ** ON A/C NOT FOR ALL

and

HPC Vane and Blade Locations ** ON A/C NOT FOR ALL

(b) Examine the HPC outer rubstrip. Refer to table 10.

HPC 1st through 8th Stage Airfoil/Blade Outer Rubstrips and HPC 4th through 7th Stage Stator Inner Rubstrips ** ON A/C NOT FOR ALL

1 Engage the flexible borescope through the borescope port in the counterclockwise direction (with engine aft as you look forward) until the borescope port is in view.

360-Degree Inspection of the HPC Assembly (Borescope Installation and Removal Direction) ** ON A/C NOT FOR ALL

2 Record a video as you slowly retract the borescope to get a clear view of the outer rubstrip.

NOTE: The borescope must stay in focus on the outer rubstrip.

EXAMINE	DAMAGE	DISPOSITION
5th stage outer rubstrip for:
Missing or rubbed out material	All quantities not more than 1.00 in.2 (645.16 mm2) in one area or a maximum of 10 percent of the rubstrip area.	Permitted
	All quantities more than 1.00 in.2 (645.16 mm2) in one area or a total quantity more than 10 percent of the rubstrip area.	Not permitted. Contact Pratt & Whitney.
6th - 8th stage outer rubstrip for:
Missing or rubbed out material	All quantities not more than 0.750 in.2 (483.87 mm2) in one area and a total quantity not more than 10 percent of the rubstrip area.	Permitted
	All quantities more than 0.750 in.2 (483.87 mm2) in one area or a total quantity more than 10 percent of the rubstrip area.	Not permitted. Contact Pratt & Whitney.
General outer rubstrip for:
Metal smearing	Light metal smearing onto abradable rubstrip. Transferred metal "islands" do not connect.	Permitted
	Metal smearing with transferred metal that connects circumferentially.	Not permitted. Contact Pratt & Whitney.
	Metal smearing with transferred metal that connects circumferentially with crack formation.	Not permitted. Contact Pratt & Whitney.
	Smeared metal liberation and pullout	Not permitted. Contact Pratt & Whitney.
Gouging	All quantities	Not permitted. Contact Pratt & Whitney.

Table - Borescope Inspection/Limits for HPC 5th thru 8th Stage Outer Rubstrips

(14) Remove the high (N2) rotor turning equipment, if necessary (Ref. AMM TASK 72-00-00-000-805).
(15) Install borescope plugs AP HPC-1 PLUG, AP HPC-2 PLUG, AP HPC-3 PLUG, AP HPC-4 PLUG, AP HPC-5 PLUG, AP HPC-6 PLUG, AP HPC-7 PLUG and AP HPC-8 PLUG as necessary (Ref. AMM TASK 72-00-00-400-804).

HPC Access Port AP Locations ** ON A/C NOT FOR ALL

(16) Examine the assembly for foreign objects, damage and correct assembly.

5. Close-up
Subtask 72-35-00-860-050-A ** ON A/C NOT FOR ALL

A. Put the aircraft back to its initial configuration.
(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 72-35-00-440-050-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 72-35-00-410-050-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 WARNING NOTICE(S).
(3) Remove the access platform(s).

[Rev.10 from 2021] 2026.04.01 13:02:00 UTC