TASK 72-00-00-200-005-A00 Engine General - Examine (Borescope) The HPT Stage 2 Blades, Inspection-005

DMC:V2500-A1-72-00-0000-07A-312A-B|Issue No:005.00|Issue Date:2019-11-01

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

V2500-A1

Common Information

TASK 72-00-00-200-005-A00 Engine General - Examine (Borescope) The HPT Stage 2 Blades, Inspection-005

General

All Fig/item numbers in the procedure agree with those used in the IPC. Only the primary Fig/item numbers are used. For the service bulletin alpha variants refer to the IPC.

For all parts identified in a different Chapter/Section/Subject, the applicable Chapter/Section/Subject comes before the Fig/item number,

For standard torque data and procedures refer to SPM TASK 70-41-00-400-501, SPM TASK 70-41-00-400-501 and SPM TASK 70-41-01-400-501.

Special torque data is identified with the symbol * after the torque value.

Assembly tolerances are included in this procedure.

Lubricate all threads and abutment faces of nuts and bolts with CoMat 10-077 APPROVED ENGINE OILS unless other lubricants are referred to in the procedure.

The number for each radial location must be identified in a clockwise direction. These start at the engine top position when you look from the rear of the engine, unless stated differently in the procedure.

Definitions and General Information

Refer to Figure, Figure, Figure and Figure.

This TASK gives the procedure for the borescope inspection of the stage 2 HPT blades.

Borescope ports are identified in Figure and Figure.

The names of the different parts, areas and dimensional references of the Stage 2 HPT blades are shown in Figure and Figure.

Use the names which follow when you identify a blade condition seen at borescope inspection:

Erosion: A smooth area at the tip that shows material is gone.

Leading Edge Burn-Through: A hole in the leading edge open to the cooling air passage.

Burns: A local area that is rough, not the initial color, or where there is no material.

Coating damage: Chipping, flaking, blistering, peeling or oxidation of the blade confined to coating.

Nick or dent: A distorted area that can be smooth, have cracks, a hole that is open to the cooling air passages, or a combination of holes and cracks.

NOTE

To identify the consumable materials refer to the PCI.

NOTE

Special tools are identified in the procedure by the tool primary number.

NOTE

If damage is not listed contact your IAE representative.

Preliminary Requirements

Pre-Conditions

NONE

Support Equipment

NameManufacturerPart Number / IdentificationQuantityRemark
Rigid borescopeLOCALRigid borescope
Flexible borescope (probe dia. 0.24 to 0.31 in. (6.0 to 8.0 mm) with view capability of 180 degrees up and down)LOCALFlexible Borescope
Cover (eye)LOCALCover (eye)
Motor Drive UnitLOCALMotor Drive Unit
Torque wrench, range 96 to 900 lbf.in (10 to 100 Nm)LOCALTorque Wrench 96-900
IAE 1P16184 Puller0AM53IAE 1P161841

Consumables, Materials and Expendables

NameManufacturerPart Number / IdentificationQuantityRemark
CoMat 02-141 LOCKWIRELOCALCoMat 02-141
CoMat 10-077 APPROVED ENGINE OILSX333XCoMat 10-077
CoMat 10-094 ANTI-SEIZE COMPOUND, PURE Ni-SPECIALK2147CoMat 10-094
CoMat 10-129 ANTI-SEIZE PASTE34568CoMat 10-129

Spares

NameManufacturerPart Number / IdentificationQuantityRemark
Gasket2

72-45-00, 01-120

Safety Requirements

WARNING

THE ENGINE IS HOT IMMEDIATELY AFTER SHUTDOWN AND CAN CAUSE BURNS AND DAMAGE TO THE BORESCOPE EQUIPMENT. WAIT 2 TO 3 HOURS AFTER SHUTDOWN BEFORE YOU DO A BORESCOPE INSPECTION.

CAUTION

THE LIMITS WHICH FOLLOW ARE APPLICABLE ON A CONTINUE IN SERVICE BASIS ONLY. EACH LIMIT IS BASED ON WHAT THE STRUCTURE OF THE BLADE MUST BE AND DOES NOT INDICATE THAT THERE WILL NOT BE A DETERIORATION OF THE ENGINE PERFORMANCE, STABILITY, OPERATING LIMITS OR PART REPAIRABILITY.

Procedure

    1. SUBTASK 72-00-00-420-061 Install the Foot-Operated Motor Drive Unit to the Gearbox Crank Pad

    1. Refer to Figure.

    2. SUBTASK 72-00-00-020-060 Get Access to the Stage 2 HPT Blades through the T1/2L or T1/2R or T2/3L or T2/3R Ports

      WARNING

      MAKE SURE THAT THE BLANKING PLUG IS SUFFCIENTLY COOL BEFORE REMOVAL. THE TEMPERATURE STAY HIGH FOR A SHORT TIME AFTER ENGINE SHUTDOWN.

      NOTE

      Removal of the plugs at both of the locations will permit you to examine both leading and trailing edges.

    1. Refer to: Figure, Figure and Figure

      2. Get access to the T1/2L and the T1/2R ports, Figure.

      1. Remove the lockwire and the bolts which hold the plugs.

      2. Put the IAE 1P16184 Puller 1 off in to the center hole of the plug (use if required).

      3. Remove the plug from the port with the puller.

      4. Remove the gasket from the plug.

      5. Remove the plug from the puller.

      6. Do Step to Step for the other plug.

      3. Get access to the T2/3L and the T2/3R ports, Figure.

      1. Remove the lockwire and the bolts which hold the plugs.

      2. CAUTION

        MAKE SURE THAT THE SLEEVE FLANGED BUSHINGS DO NOT FALL OUT. IF THE PART FALLS OUT IT CAUSES DAMAGE.

        NOTE

        Do not change the spacer plates as they are adjusted to the related blanking plug.

        Remove the plugs together with the spacer plates.

      3. Remove the sleeve flanged bushings.

    3. SUBTASK 72-00-00-220-124 Do a Borescope Inspection of the Stage 2 HPT Blades

      NOTE

      A cover for the eye which is not used will decrease eye tension.

    1. Put the rigid borescope through the T1/2L or T1/2R port, Figure.

    2. Examine the blades for damage.

    3. Put a flexible borescope through the T1/2L or T1/2R port, Figure.

    4. Examine the blades for damage on the concave and convex sides from the leading edge back.

    5. Put a rigid borescope through the T2/3L or T2/3R port, Figure.

    6. Examine the blades for damage.

    4. SUBTASK 72-00-00-220-078 Examine the Blades for Nicks, Dents and Holes on the Airfoil of the Stage 2 HPT Blades

    1. Refer to Figure, Figure and Figure.

      Time/Cycle Limits Interval

      Area A

      Area B

      Area C

      Area D

      Area TE

      Area Platform

      600 Hours

      The nick or dent has cracks and the total length of the nick or dent plus the cracks is less than 0.150 inch (3.81 mm) long axially or less than 0.180 inch (4.57 mm) long radially

      The nick or dent has a hole or a hole with cracks and the total length of the nick or dent plus the hole or hole with a crack is less than 0.100 inch (2.54 mm) long axially or less than 0.180 in. (4.57 mm) long radially

      The hole is less than 0.040 inch (1.01 mm) long axially and less than 0.050 inch (1.27 mm) long radially

      300 Hours

      The nick or dent has cracks, a hole or a hole with cracks and the total length of the nick or dent plus the crack is less than 0.120 inch (3.05 mm) long axially or less than 0.140 inch (3.55 mm) long radially

      The nick or dent has cracks, a hole or a hole with cracks and the total length of the nick or dent plus the crack is between 0.150 inch (3.81 mm) and 0.200 inch (5.08 mm) long axially or between 0.180 inch (4.57 mm) and 0.450 inch (11.43 mm) long radially

      The nick or dent has cracks, a hole or a hole with cracks and the total length of the nick or dent plus the crack is between 0.150 inch (3.81 mm) and 0.250 inch (6.35 mm) long axially or between 0.180 inch (4.57 mm) and 0.450 inch (11.43 mm) long radially

      There is a nick

      The hole is between 0.040 inch (1.01 mm) and 0.080 inch (2.03 mm) long axially or is between 0.050 inch (1.27 mm) and 0.100 inch (2.54 mm) long radially

      There is a dent with a depth greater than 0.015 inch (0.381 mm) or the dent does not have a smooth bottom

      150 Hours

      Reject if

      The nick or dent has cracks, a hole or a hole with cracks and the total length of the nick or dent plus the crack is more than 0.120 inch (3.05 mm) long axially or more than 0.140 inch (3.55 mm) long radially

      The nick or dent has cracks, a hole or a hole with cracks and the total length of the nick or dent plus the crack is more than 0.200 inch (5.08 mm) long axially or more than 0.450 inch (11.43 mm) long radially

      The nick or dent has cracks, a hole or a hole with cracks and the total length of the nick or dent plus the crack is more than 0.250 inch (6.35 mm) long axially or more than 0.450 inch (11.43 mm) long radially

      There is a nick or dent with signs of burns, torn metal or cracks

      The nick or dent is in the trailing edge of Area D and has a depth greater than 0.005 inch (0.13 mm) or less than 0.350 inch (8.89 mm) from the blade platform

      There is a hole larger than 0.080 inch (2.03 mm) axially or 0.100 inch (2.54 mm) radially

      There is a hole

      There is more than one hole

      NOTE

      The trailing edge of the Stage 2 HPT blade can be blended per EM repair VRS3240. Blends on the trailing edge of the blade will be smooth and round bottomed and made in the shape of the initial contour. Blades that have been blended in accordance with VRS3240 are acceptable and can continue on in service.

      NOTE

      Manufacturer's holes are not included.

      NOTE

      Axial tip cracks may have the potential of releasing the blade tip, which may cause minor gaspath downstream damage.

      NOTE

      The most restrictive limits apply.

    5. SUBTASK 72-00-00-220-079 Examine the Blades for Erosion or Burns on the Airfoil or Platform of the Stage 2 HPT Blades

    1. Refer to Figure, Figure and Figure.

      Time/Cycle Limits Interval

      Area A

      Area B

      Area C

      Area D

      Area TE

      Area Platform

      600 Hours

      The erosion or burn is on the airfoil trailing edge in Area D

      The erosion or burn is on the airfoil trailing edge in Area C and is longer than 0.100 inch (2.54 mm) long axially or 0.200 inch (5.08 mm) long radially

      The erosion or burn is on the leading edge and extends more than one-quarter of the airfoil radial length

      The erosion or burn on the platform has gone through the coating

      The erosion or burn on the leading edge has changed the shape of the airfoil

      The erosion or burn on the airfoil has gone through the coating. This does not include burns on the leading edge

      300 Hours

      150 Hours

      Reject if

      The erosion or burn is in Area C and is more than 0.250 inch (6.35 mm) long axially

      The erosion or burn is in Area D and is more than 0.050 inch (1.27 mm) long radially

      The burn on the platform increases the gap with the adjacent blade platform to more than 0.050 inch (1.27 mm)

      The burn on the platform goes into the airfoil fillet radius

      The erosion or burn has an adjacent area which shows signs of cracks

      The erosion or burn on the airfoil or platform permits internal areas to show, the internal areas are where air goes that is used to cool the blade

      The erosion or burn on the airfoil or platform changes the shape of the airfoil, this does not include burns on the leading edge

      NOTE

      The trailing edge of the Stage 2 HPT blade can be blended per EM repair VRS3240. Blends on the trailing edge of the blade will be smooth and round bottomed and made in the shape of the initial contour. Blades that have been blended in accordance with VRS3240 are acceptable and can continue on in service.

      NOTE

      Manufacturer's holes are not included.

      NOTE

      Axial tip cracks may have the potential of releasing the blade tip, which may cause minor gaspath downstream damage.

      NOTE

      The most restrictive limits apply.

    6. SUBTASK 72-00-00-220-080 Examine the Blades for Cracks on the Airfoil of the Stage 2 HPT Blades

    1. Refer to Figure, Figure and Figure.

      Time/Cycle Limits Interval

      Area A

      Area B

      Area C

      Area D

      Area TE

      Area Platform

      600 Hours

      The crack is less than 0.080 inch (2.03 mm) long axially or less than 0.180 inch (4.57 mm) long radially

      The trailing edge crack is in Area C and is less than 0.300 inch (7.62 mm) long in any direction

      300 Hours

      The crack is less than 0.080 inch (2.03 mm) long axially or less than 0.140 inch (3.56 mm) long radially

      The crack is between 0.080 inch (2.03 mm) and 0.140 inch (3.56 mm) long axially or between 0.180 inch (4.57 mm) and 0.360 inch (9.14 mm) long radially

      The crack is between 0.080 inch (2.03 mm) and 0.610 inch (15.49 mm) long axially or between 0.180 inch (4.57 mm) and 0.360 inch (9.14 mm) long radially. The crack must be forward of the trailing edge slots. For these cracks, intersecting cracks are allowed if the intersection of the crack is within 0.200 inch (5.08 mm) of the blade tip. This does not include closed loop cracks or trailing edge slot cracks.

      150 Hours

      The crack is between 0.610 inch (15.49 mm) and 0.800 inch (20.32 mm) long axially and must be outside the trailing edge slots. The axial crack can have up to 0.450 inch (11.43 mm) in radial length. For these cracks, intersecting cracks are allowed if the intersection of the crack is within 0.200 inch (5.08 mm) of the blade tip. This does not include closed loop cracks or trailing edge slot cracks.

      There is a crack that is more than 0.800 inch (20.32 mm) long axially or more than 0.450 inch (11.43 mm) long radially

      Reject if

      The crack is more than 0.080 inch (2.03 mm) long axially or more than 0.140 inch (3.56 mm) long radially

      The crack is more than 0.140 inch (3.56 mm) long axially or more than 0.360 inch (9.14 mm) long radially

      There is a trailing edge crack in Area D

      There is a trailing edge crack in Area C and is more than 0.300 inch (7.62 mm) long in any direction

      Cracks on the airfoil go through or touch other cracks, trailing edge slot cracks or closed loop cracks (this does not include cracks at the tip as described above)

      Loss of blade tip material so that the internal cooling cavity shows

      Loss of trailing edge tip material above the last trailing edge cooling slot

      NOTE

      The trailing edge of the Stage 2 HPT blade can be blended per EM repair VRS3240. Blends on the trailing edge of the blade will be smooth and round bottomed and made in the shape of the initial contour. Blades that have been blended in accordance with VRS3240 are acceptable and can continue on in service.

      NOTE

      Manufacturer's holes are not included.

      NOTE

      Axial tip cracks may have the potential of releasing the blade tip, which may cause minor gaspath downstream damage.

      NOTE

      The most restrictive limits apply.

    7. SUBTASK 72-00-00-220-178 Examine the Blades for Airfoil Surface Imperfections (Areas of Raised Material) and Surface Imperfections with Cracks on the Stage 2 HPT Blade

    1. Refer to Figure, Figure, Figure.

      Time/Cycle Limits Interval

      Area A

      Area B

      Area C

      Area D

      Area TE

      Area Platform

      600 Hours

      There are surface imperfections (areas of raised material) on the airfoil surface

      A surface imperfection has a crack with a length that is less than 0.080 inch (2.03 mm) long axially or less than 0.180 inch (4.57 mm) long radially

      300 Hours

      A surface imperfection has a crack with a length that is less than 0.080 inch (2.03 mm) long axially or less than 0.140 inch (3.56 mm) long radially

      A surface imperfection has a crack with a length that is between 0.080 inch (2.03 mm) and 0.140 inch (3.56 mm) long axially or between 0.180 inch (4.57 mm) and 0.360 inch (9.14 mm) long radially

      A surface imperfection has a crack with a length that is between 0.080 inch (2.03 mm) and 0.200 inch (5.08 mm) long axially or between 0.180 inch (4.57 mm) and 0.360 inch (9.14 mm) long radially

      150 Hours

      Reject if

      A surface imperfection has a crack with a length more than 0.080 inch (2.03 mm) long axially or more than 0.140 inch (3.56 mm) long radially

      A surface imperfection has a crack with a length more than 0.140 inch (3.56 mm) long axially or more than 0.360 inch (9.14 mm) long radially

      A surface imperfection has a crack with a length more than 0.200 inch (5.08 mm) long axially or more than 0.360 inch (9.14 mm) long radially

      A surface imperfection has a crack

      Surface imperfections on the airfoil surface have cracks that go through other cracks

      NOTE

      The trailing edge of the Stage 2 HPT blade can be blended per EM repair VRS3240. Blends on the trailing edge of the blade will be smooth and round bottomed and made in the shape of the initial contour. Blades that have been blended in accordance with VRS3240 are acceptable and can continue on in service.

      NOTE

      Manufacturer's holes are not included.

      NOTE

      Axial tip cracks may have the potential of releasing the blade tip, which may cause minor gaspath downstream damage.

      NOTE

      The most restrictive limits apply.

    8. SUBTASK 72-00-00-220-081 Examine the Blades for Cracks on the Platform of the Stage 2 HPT Blades

    1. Refer to Figure.

      Time/Cycle Limits Interval

      Area A

      Area B

      Area C

      Area D

      Area TE

      Area Platform

      600 Hours

      Cracks that are longer than 0.125 inch (3.17 mm) that do not go through the platform to the airfoil fillet radius

      300 Hours

      150 Hours

      Reject if

      There is a crack which goes through the platform to airfoil fillet radius

      NOTE

      The trailing edge of the Stage 2 HPT blade can be blended per EM repair VRS3240. Blends on the trailing edge of the blade will be smooth and round bottomed and made in the shape of the initial contour. Blades that have been blended in accordance with VRS3240 are acceptable and can continue on in service.

      NOTE

      Manufacturer's holes are not included.

      NOTE

      Axial tip cracks may have the potential of releasing the blade tip, which may cause minor gaspath downstream damage.

      NOTE

      The most restrictive limits apply.

    9. SUBTASK 72-00-00-220-094 Examine for Burn Holes in the Stage 2 HPT Duct Segments

      NOTE

      When you do a borescope inspection of the Stage 2 HPT blades, some areas of the Stage 2 HPT duct segments will be seen. Locations 1 and 2 in the figure are important areas.

    1. Refer to Figure.

      2. Reject if:

        NOTE

        Quantity of cracks is not important and are acceptable without reduced inspection intervals.

      1. There is a burn hole that is longer than 0.500 in. (12.7 mm).

  10. SUBTASK 72-00-00-020-061 Remove the Borescope Equipment from the Borescope Inspection Ports

    11. SUBTASK 72-00-00-420-063 Close the Borescope Inspection Ports after Borescope Inspection is Completed

    1. Refer to Figure.

      2. For the T1/2L and T1/2R port, proceed as follows:

      1. Put the ENGINE-HP TURBINE ROTOR AND STATOR ASSEMBLY (72-45-00,01-120) gasket 1 off in the case recess.

      2. Replace the gasket if it is not above the case surface.

        NOTE

        It is permissible to correct minor thread damage to a threaded hole with a 0.250-28UNJF-3B tap.

      3. CAUTION

        USE CAUTION WHEN INSTALLING PLUG. IF THE PLUG BREAKS DURING INSTALLATION AND FALLS INTO 2ND STAGE VANE CAVITY, REMOVE PLUG PIECE PRIOR TO RETURNING ENGINE TO SERVICE. IF NECESSARY, ACCESS TO THE CAVITY CAN BE OBTAINED BY REMOVING THE TCA TUBE.

        Put the gasket on the plug ENGINE-HP TURBINE ROTOR AND STATOR ASSEMBLY (72-45-00, 01-140) and install the plug in the case.

        NOTE

        Make sure that the borescope plug is correctly installed and bolt holes are aligned prior to continuing to next step.

      4. Lubricate the plug threads with CoMat 10-129 ANTI-SEIZE PASTE or CoMat 10-094 ANTI-SEIZE COMPOUND, PURE Ni-SPECIAL. Wipe off excess paste.

      5. Install the bolts.

      6. Torque the bolts to 75 lbfin to 85 lbfin (8.48 Nm to 9.60 Nm).

      7. Safety the bolts with CoMat 02-141 LOCKWIRE.

      3. CAUTION

        MAKE SURE THAT THE SLEEVE FLANGED BUSHING DOES NOT FALL OUT. IF THE PART FALLS, IT WILL BE DAMAGED.

        For the T2/3L and the T2/3R port, proceed as follows.

        NOTE

        Do not change the spacer plates as they are adjusted to the related blanking plug.

      1. Install the sleeve flanged bushing.

      2. Install the blanking plug with the related spacer plates.

      3. Apply CoMat 10-129 ANTI-SEIZE PASTE to the bolts. Install the bolts.

      4. Torque the bolts to 62 lbfin to 72 lbfin (7.0 Nm to 8.1 Nm).

      5. Safety the bolts with CoMat 02-141 LOCKWIRE.

  12. SUBTASK 72-00-00-020-062 Remove the Foot-Operated Motor Drive Unit from the Gearbox Crank Pad

    13. Figure: Crank Pad Location

    Crank Pad Location

    Figure: HP Turbine Borescope Locations for Inspection of the Stage 2 HPT Blades (Left Side)

    HP Turbine Borescope Locations for Inspection of the Stage 2 HPT Blades (Left Side)

    Figure: HP Turbine Borescope Ports for Inspection of the Stage 2 HPT Blades (Right Side)

    HP Turbine Borescope Ports for Inspection of the Stage 2 HPT Blades (Right Side)

    Figure: Stage 2 HPT Blade Inspection Areas

    Stage 2 HPT Blade Inspection Areas

    Figure: Borescope Ports

    Borescope Ports

    Figure: HP and LP Turbine Ports for Inspection of the Stage 2 HPT Blades

    HP and LP Turbine Ports for Inspection of the Stage 2 HPT Blades

    Figure: Stage 2 HPT Blade Inspection Areas

    Stage 2 HPT Blade Inspection Areas

    Figure: Stage 2 HPT Duct Segment Inspection Location

    Stage 2 HPT Duct Segment Inspection Location

    Figure: Stage 2 HPT Blade Inspection with a Flexible Borescope

    Stage 2 HPT Blade Inspection with a Flexible Borescope

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Revised the procedure to add inspection criteria. (19VC339)

Link not Found
Manufacturer Code:0AM53
Enterprise Name:IAE INTERNATIONAL AERO ENGINES AG
BU Name:NULL
Building:SUITE 400
Street:628 HEBRON AVENUE
City:GLASTONBURY
State:CT
Zip Code:06033
Country:USA
Manufacturer Code:34568
Enterprise Name:TIODIZE CO., INC.
BU Name:TIODIZE CO., INC.
Street:5858 ENGINEER DRIVE
City:HUNTINGTON BEACH
State:CA
Zip Code:92649
Country:USA
Phone Number:1-714-898-4377
Fax Number:1-714-891-7467
Internet:www.tiodize.com
Manufacturer Code:K2147
Enterprise Name:BOSTIC FINDLEY
BU Name:BOSTIC FINDLEY
Street:COMMON ROAD
City:STAFFORD
Zip Code:ST16 3EH
Country:UNITED KINGDOM
Phone Number:44-1785-272727
Fax Number:44-1162-689283
Manufacturer Code:LOCAL
Enterprise Name:LOCALLY SUPPLIED
Manufacturer Code:X333X
Enterprise Name:REFER TO V2500 SB ENG-79-0108
Link not Found
Manufacturer Code:LOCAL
Supply Number:CoMat 02-141
Type:sp01
Supply Short Name:CoMat 02-141 LOCKWIRE
Supply Name:CoMat 02-141 LOCKWIRE
Specification Groups:
Doc NumberType
AS3214-02 (0.8 mm)AMS 5689
Suppliers:
ManufacturerRemarks
LOCAL
81343
IE508
58401
Manufacturer Code:X333X
Supply Number:CoMat 10-077
Type:sp01
Supply Short Name:CoMat 10-077 APPROVED ENGINE OILS
Supply Name:CoMat 10-077 APPROVED ENGINE OILS
Specification Groups:
Doc NumberType
For V2500-A1/A5/D5 models - Refer to V2500 Service Bulletin ENG-79-0108
For V2500-E5 model - Refer to Service Bulletin E5-79-0001
Suppliers:
ManufacturerRemarks
X333X
Manufacturer Code:K2147
Supply Number:CoMat 10-094
Type:sp01
Supply Short Name:CoMat 10-094 ANTI-SEIZE COMPOUND, PURE Ni-SPECIAL
Supply Name:CoMat 10-094 ANTI-SEIZE COMPOUND, PURE Ni-SPECIAL
Specification Groups:
Doc NumberType
BOSTIK NEVER-SEEZ PURE NICKEL SPECIAL
Suppliers:
ManufacturerRemarks
K2147
K6835
5W425
Manufacturer Code:34568
Supply Number:CoMat 10-129
Type:sp01
Supply Short Name:CoMat 10-129 ANTI-SEIZE PASTE
Supply Name:CoMat 10-129 ANTI-SEIZE PASTE
Specification Groups:
Doc NumberType
TIODIZE T8E PASTE
Suppliers:
ManufacturerRemarks
34568
Manufacturer Code:LOCAL
Tool Number:Cover (eye)
Tool Name:Cover (eye)
Manufacturer Code:LOCAL
Tool Number:Flexible Borescope
Tool Name:Flexible borescope (probe dia. 0.24 to 0.31 in. (6.0 to 8.0 mm) with view capability of 180 degrees up and down)
Manufacturer Code:0AM53
Tool Number:IAE 1P16184
Tool Name:IAE 1P16184 Puller
Manufacturer Code:LOCAL
Tool Number:Motor Drive Unit
Tool Name:Motor Drive Unit
Manufacturer Code:LOCAL
Tool Number:Rigid borescope
Tool Name:Rigid borescope
Manufacturer Code:LOCAL
Tool Number:Torque Wrench 96-900
Tool Name:Torque wrench, range 96 to 900 lbf.in (10 to 100 Nm)