TASK 72-00-31-300-005 LPC Fan Blade - Blend Repair Leading Edge Erosion, Repair-005 (VRS1051)

DMC:V2500-A0-72-00-3104-02A-649A-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 72-00-31-300-005 LPC Fan Blade - Blend Repair Leading Edge Erosion, Repair-005 (VRS1051)

Material of component

PART IDENT

SYMBOL

MATERIAL

LP Compressor rotor blade assembly

TFH or TJW

Titanium, Aluminum and Vanadium alloy

General

This repair must only be done when instructed to do so is given in 72-00-31 Inspection/Check.

This repair gives the procedure to repair erosion on the leading edge only, of the LP Compressor Rotor Blade, by material removal.

The maximum area of metal removal, for a given LP Compressor Rotor Blade set is equivalent of three blades dressed to the maximum limit. Exceeding this could result in engine vibration of unacceptable limits and/or increased SFC.

Fan Blade repaired to this scheme, must be glass bead peened when the blades are removed from the LP Fan Disk by 72-00-31, Inspection/Check. Glass bead peening instructions are specified in Repair, VRS1724 TASK 72-31-11-300-026 (REPAIR-026).

The practices and processes referred to in this procedure by TASK numbers are in the SPM.

NOTE

To identify the consumable materials, refer to the PCI.

NOTE

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

NOTE

Although erosion can be removed by full edge material removal, erosion will be more evident on the top half of the LP Compressor Rotor Blade.

Preliminary Requirements

Pre-Conditions

NONE

Support Equipment

NameManufacturerPart Number / IdentificationQuantityRemark
Chemical Cleaning EquipmentLOCALChemical Cleaning Equipment
Fluorescent Penetrant Inspection EquipmentLOCALFluorescent Penetrant Inspection Equipment
Portablegrinding equipmentLOCALPortable grinding equipment
ClothLOCALCloth
BrushLOCALBrush
Workshop Inspection EquipmentLOCALWorkshop Inspection Equipment
Vibrating Marking PencilLOCALVibrating Marking Pencil
IAE 3R19016 LE profile gage0AM53IAE 3R190161
IAE 3R19017 LE profile gage0AM53IAE 3R190171
IAE 3R19317 Template0AM53IAE 3R19317
IAE 3R19320 Template0AM53IAE 3R19320
IAE 3R19321 Mould0AM53IAE 3R19321
IAE 3R19323 Mould0AM53IAE 3R19323

Consumables, Materials and Expendables

NameManufacturerPart Number / IdentificationQuantityRemark
CoMat 02-050 HIGH TEMPERATURE GLASS CLOTH TAPE76381CoMat 02-050
CoMat 02-051 HIGH TEMPERATURE GLASS CLOTH TAPE0AM53CoMat 02-051
CoMat 02-052 HIGH TEMPERATURE GLASS CLOTH TAPE0AM53CoMat 02-052
CoMat 02-053 HIGH TEMPERATURE GLASS CLOTH TAPE0AM53CoMat 02-053
CoMat 03-398 METAL SPRAYING STOPPING-OFFCOMPOUNDLOCALCoMat 03-398
CoMat 05-019 WATERPROOF SILICON CARBIDELOCALCoMat 05-019
CoMat 05-020 WATERPROOF SILICON CARBIDELOCALCoMat 05-020
CoMat 05-021 WATERPROOF SILICON CARBIDE44197CoMat 05-021
CoMat 05-064 WATERPROOF SILICON CARBIDEK6835CoMat 05-064
CoMat 06-022 FLUORESCENT PENETRANT (POST-EMULSIFIED ULTRA HIGH SENSITIVITY)LOCALCoMat 06-022
CoMat 06-063 FLUORESCENT PENETRANT (POST-EMULSIFIED MEDIUM SENSITIVITY)LOCALCoMat 06-063
CoMat 06-064 FLUORESCENT PENETRANT (WATER WASHABLE MEDIUM SENSITIVITY)LOCALCoMat 06-064

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-00-31-230-059 Examine the LP Compressor Rotor Blade Assembly for Cracks

    2. SUBTASK 72-00-31-350-055 Seal the LP Compressor Rotor Blade Airfoil Surfaces

      1. CAUTION

        YOU MUST PROTECT THE AIRFOIL SURFACES OF THE BLADE AND BEFORE AND AFTER BLADES, WHEN YOU REMOVE EROSION FROM THE LEADING EDGE, AS PARTICLES OF TITANIUM CAN BOND TO THE BLADE AIRFOIL SURFACE.

        Seal the airfoil surfaces of the LP Compressor Rotor Blade.

    3. SUBTASK 72-00-31-350-056-A00 Remove Erosion from the LP Compressor Rotor Blade Assembly, Assembly A

      2. CAUTION

        TITANIUM COMPONENT - YOU MUST USE SILICON CARBIDE TYPE ABRASIVE WHEELS, STONES AND PAPERS TO DRESS, BLEND AND POLISH THIS COMPONENT.

        CAUTION

        TITANIUM COMPONENT - DO NOT USE FORCE WITH MECHANICAL CUTTERS OR THE MATERIAL WILL BECOME TOO HOT.

        CAUTION

        TITANIUM COMPONENT - IF THE MATERIAL SHOWS A CHANGE IN COLOR, TO DARKER THAN A LIGHT STRAW COLOR, THE COMPONENT IS TO BE REJECTED.

        CAUTION

        TITANIUM COMPONENT - MAXIMUM SPEED FOR MECHANICAL TOOLS MUST NOT EXCEED 1000 REVOLUTIONS PER MINUTE.

        CAUTION

        MAKE SURE THE LEADING EDGE PROFILE RADIUS IS POLISHED ALL ROUND THE NOSE. THE FINISHED PROFILE MUST GIVE A NOSE DOWN CONDITION FIG 72-00-31-990-082 (FIG 912).

        Re-profile the leading edge radii.

      1. Refer to Figure.

        The profiling of the leading edge must be done such that excess thickness is removed only from the suction surface of the airfoil and leading edge radii is recreated/blended smoothly into the original non-eroded blade profile.

        Only minimum amount of material removal is required to get a satisfactory leading edge profile.

        If you use mechanical tools, do not exceed 1000 rpm.

      3. NOTE

        Although erosion can be removed by full edge material removal, erosion will be more evident on the top half of the LP Compressor Rotor Blade.

        Make smooth and polish the repaired area(s).

      1. Make sure all the damage marks are completely removed and the area is made smooth into the adjacent material.

        Polish repaired area(s), to remove scratches and to give a surface finish the same as the adjacent material.

      4. NOTE

        The last polish is to be in a radial direction.

        Remove the stopping-off compound or masking tape.

      1. Do Step.

    4. SUBTASK 72-00-31-350-056-B00 Remove Erosion from the LP Compressor Rotor Blade Assembly, Assembly B

      2. CAUTION

        TITANIUM COMPONENT - YOU MUST USE SILICON CARBIDE TYPE ABRASIVE WHEELS, STONES AND PAPERS TO DRESS, BLEND AND POLISH THIS COMPONENT.

        CAUTION

        TITANIUM COMPONENT - DO NOT USE FORCE WITH MECHANICAL CUTTERS OR THE MATERIAL WILL BECOME TOO HOT.

        CAUTION

        TITANIUM COMPONENT - IF THE MATERIAL SHOWS A CHANGE IN COLOR, TO DARKER THAN A LIGHT STRAW COLOR, THE COMPONENT IS TO BE REJECTED.

        CAUTION

        TITANIUM COMPONENT - MAXIMUM SPEED FOR MECHANICAL TOOLS MUST NOT EXCEED 1000 REVOLUTIONS PER MINUTE.

        CAUTION

        MAKE SURE THE LEADING EDGE PROFILE RADIUS IS POLISHED ALL ROUND THE NOSE. THE FINISHED PROFILE MUST GIVE A NOSE DOWN CONDITION FIG.72-00-31-990-082 (FIG. 912).

        Re-profile the leading edge radii.

      1. Refer to Figure.

        The profiling of the leading edge must be done such that excess thickness is removed only from the suction surface of the airfoil and leading edge radii is recreated/blended smoothly into the original non-eroded blade profile.

        Only minimum amount of material removal is required to get a satisfactory leading edge profile.

        If you use mechanical tools, do not exceed 1000 rpm.

      3. NOTE

        Although erosion can be removed by full edge material removal, erosion will be more evident on the top half of the LP Compressor Rotor Blade.

        Make smooth and polish the repaired area(s).

      1. Make sure all the damage marks are completely removed and the area is made smooth into the adjacent material.

        Polish repaired area(s), to remove scratches and to give a surface finish the same as the adjacent material.

      4. NOTE

        The last polish is to be in a radial direction.

        Remove the stopping-off compound or masking tape.

      1. Do Step.

    5. SUBTASK 72-00-31-350-056-C00 Remove Erosion from the LP Compressor Rotor Blade Assembly, Assembly C

      2. CAUTION

        TITANIUM COMPONENT - YOU MUST USE SILICON CARBIDE TYPE ABRASIVE WHEELS, STONES AND PAPERS TO DRESS, BLEND AND POLISH THIS COMPONENT.

        CAUTION

        TITANIUM COMPONENT - DO NOT USE FORCE WITH MECHANICAL CUTTERS OR THE MATERIAL WILL BECOME TOO HOT.

        CAUTION

        TITANIUM COMPONENT - IF THE MATERIAL SHOWS A CHANGE IN COLOR, TO DARKER THAN A LIGHT STRAW COLOR, THE COMPONENT IS TO BE REJECTED.

        CAUTION

        TITANIUM COMPONENT - MAXIMUM SPEED FOR MECHANICAL TOOLS MUST NOT EXCEED 1000 REVOLUTIONS PER MINUTE.

        CAUTION

        MAKE SURE THE LEADING EDGE PROFILE RADIUS IS POLISHED ALL ROUND THE NOSE. THE FINISHED PROFILE MUST GIVE A NOSE DOWN CONDITION FIG 72-00-31-990-082 (FIG 912).

        Re-profile the leading edge radii.

      1. Refer to Figure.

        The profiling of the leading edge must be done such that excess thickness is removed only from the suction surface of the airfoil and leading edge radii is recreated/blended smoothly into the original non-eroded blade profile.

        Only minimum amount of material removal is required to get a satisfactory leading edge profile.

        If you use mechanical tools, do not exceed 1000 rpm.

        Use portable grinding equipment.

      3. NOTE

        Although erosion can be removed by full edge material removal, erosion will be more evident on the top half of the LP Compressor Rotor Blade.

        Make smooth and polish the repaired area(s).

      1. Make sure all the damage marks are completely removed and the area is made smooth into the adjacent material.

        Polish repaired area(s), to remove scratches and to give a surface finish the same as the adjacent material.

      4. NOTE

        The last polish is to be in a radial direction.

        Remove the stopping-off compound or masking tape.

      1. Do Step.

    6. SUBTASK 72-00-31-350-056-D00 Remove Erosion from the LP Compressor Rotor Blade Assembly, Assembly D

      2. CAUTION

        TITANIUM COMPONENT - YOU MUST USE SILICON CARBIDE TYPE ABRASIVE WHEELS, STONES AND PAPERS TO DRESS, BLEND AND POLISH THIS COMPONENT.

        CAUTION

        TITANIUM COMPONENT - DO NOT USE FORCE WITH MECHANICAL CUTTERS OR THE MATERIAL WILL BECOME TOO HOT.

        CAUTION

        TITANIUM COMPONENT - IF THE MATERIAL SHOWS A CHANGE IN COLOR, TO DARKER THAN A LIGHT STRAW COLOR, THE COMPONENT IS TO BE REJECTED.

        CAUTION

        TITANIUM COMPONENT - MAXIMUM SPEED FOR MECHANICAL TOOLS MUST NOT EXCEED 1000 REVOLUTIONS PER MINUTE.

        CAUTION

        MAKE SURE THE LEADING EDGE PROFILE RADIUS IS POLISHED ALL ROUND THE NOSE. THE FINISHED PROFILE MUST GIVE A NOSE DOWN CONDITION FIG 72-00-31-990-082 (FIG 912).

        Re-profile the leading edge radii.

      1. Refer to Figure.

        The profiling of the leading edge must be done such that excess thickness is removed only from the suction surface of the airfoil and leading edge radii is recreated/blended smoothly into the original non-eroded blade profile.

        Only minimum amount of material removal is required to get a satisfactory leading edge profile.

        If you use mechanical tools, do not exceed 1000 rpm.

      3. NOTE

        Although erosion can be removed by full edge material removal, erosion will be more evident on the top half of the LP Compressor Rotor Blade.

        Make smooth and polish the repaired area(s).

      1. Make sure all the damage marks are completely removed and the area is made smooth into the adjacent material.

        Polish repaired area(s), to remove scratches and to give a surface finish the same as the adjacent material.

      4. NOTE

        The last polish is to be in a radial direction.

        Remove the stopping-off compound or masking tape.

      1. Do Step.

    7. SUBTASK 72-00-31-110-056 Chemically Clean

    1. CAUTION

      IF CoMat 03-398 METAL SPRAYING STOPPING-OFFCOMPOUND IS USED, YOU MUST REMOVE THE STOPPING-OFF COMPOUND, WITH THE BLADES IN THE BOTTOM DEAD CENTER POSITION.

      Chemically clean the LP Compressor Rotor Blade Airfoil Surfaces.

      2. Remove the stopping-off compound.

      1. Use a cloth or brush soaked in clean cold water.

        Make sure the blades are in the bottom dead center position.

      3. Clean the blade.

      1. Refer to TASK 70-11-03-300-503, SUBTASK 70-11-03-300-002 or SUBTASK 70-11-03-300-003.

    8. SUBTASK 72-00-31-110-057 Do a Swab Etch

      1. Swab etch the repaired area(s).

      1. Refer to TASK 70-11-08-300-503, SUBTASK 70-11-08-300-001 and SUBTASK 70-11-08-300-002.

        Use chemical cleaning equipment.

    9. SUBTASK 72-00-31-230-060 Examine the LP Compressor Rotor Blade Assembly for Cracks

      1. Do a local penetrant crack test on the blades.

    10. SUBTASK 72-00-31-220-069-A00 Examine the LP Compressor Rotor Blade Assembly, Assembly A

    2. Visually examine and measure the dimensions of the repaired area(s).

      3. Visually examine the leading edge profile radius.

      1. Make sure there is a good large radius, with any change in camber, to be in a nose down condition.

    11. SUBTASK 72-00-31-220-069-B00 Examine the LP Compressor Rotor Blade Assembly, Assembly B

    2. Visually examine and measure the dimensions of the repaired area(s).

      3. Visually examine the leading edge profile radius.

      1. Make sure there is a good large radius, with any change in camber, to be in a nose down condition.

    12. SUBTASK 72-00-31-220-069-C00 Examine the LP Compressor Rotor Blade Assembly, Assembly C

    2. Visually examine and measure the dimensions of the repaired area(s).

      3. Visually examine the leading edge profile radius.

      1. Make sure there is a good large radius, with any change in camber, to be in a nose down condition.

    13. SUBTASK 72-00-31-220-069-D00 Examine the LP Compressor Rotor Blade Assembly, Assembly D

    1. Refer to Figure, Figure, Figure, Figure and Figure.

    2. Visually examine and measure the dimensions of the repaired area(s).

      3. Visually examine the leading edge profile radius.

      1. Make sure there is a good large radius, with any change in camber, to be in a nose down condition.

    14. SUBTASK 72-00-31-350-057 Identify the Repair

    1. CAUTION

      DO NOT VIBRO-ENGRAVE ON THE BLADE AIRFOIL OR LOCATION FACES.

      Record the location number of repaired fan blade and repair number, VRS1501 in the engine log book.

    2. NOTE

      Fan blades repaired to this scheme must be glass peened and marked "VRS1051" adjacent to the assembly number at the next shop visit. Refer to paragraph 2 General.

    15. Figure: Repair details and dimensions, Assembly A and Assembly B

    Repair details and dimensions, Assembly A and Assembly B

    Figure: Repair details and dimensions, Assembly A and Assembly B

    Repair details and dimensions, Assembly A and Assembly B

    Figure: Repair details and dimensions, Assembly A and Assembly B

    Repair details and dimensions, Assembly A and Assembly B

    Figure: Repair details and dimensions, Assembly A and Assembly B

    Repair details and dimensions, Assembly A and Assembly B

    Figure: Repair details and dimensions, Assembly A and Assembly B

    Repair details and dimensions, Assembly A and Assembly B

    Figure: Repair details and dimensions, Assembly C and Assembly D

    Repair details and dimensions, Assembly C and Assembly D

    Figure: Repair details and dimensions, Assembly C and Assembly D

    Repair details and dimensions, Assembly C and Assembly D

    Figure: Repair details and dimensions, Assembly C

    Repair details and dimensions, Assembly C

    Figure: Repair details and dimensions, Assembly D

    Repair details and dimensions, Assembly D

    Figure: Repair details and dimensions, Assembly C and Assembly D

    Repair details and dimensions, Assembly C and Assembly D

    Figure: Repair details and dimensions, Assembly C and Assembly D

    Repair details and dimensions, Assembly C and Assembly D

    Figure: Repair details and dimensions

    Repair details and dimensions

Requirements After Job Completion

Follow-On Conditions

NONE
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:44197
Enterprise Name:SAINT-GOBAIN INDUSTRIAL CERAMICS INC.
BU Name:SAINT-GOBAIN ABRASIVES, INC
Street:ONE NEW BOND STREET
P.O. Box:PO BOX 15008
City:WORCESTER
State:MA
Zip Code:01615-0008
Country:USA
Phone Number:1-508-795-5000
Fax Number:1-508-795-2828
Internet:www.saint-gobain-northamerica.com
Manufacturer Code:76381
Enterprise Name:3M COMPANY
BU Name:3M COMPANY
Department:3M CENTER
City:ST PAUL
State:MN
Zip Code:55144-1000
Country:USA
Phone Number:1-651-733-1110
Fax Number:1-651-733-9973
Internet:www.mmm.com
Manufacturer Code:K6835
Enterprise Name:MED-LAB LTD
BU Name:MED-LAB LTD
Street:COPELAND ST
City:DERBY
Zip Code:DE1 2PU
Country:GREAT BRITAIN
Phone Number:44-1332-349094
Fax Number:44-1332-371237
Email:sales@med-lab.co.uk
Internet:www.med-lab.co.uk
Manufacturer Code:LOCAL
Enterprise Name:LOCALLY SUPPLIED
Manufacturer Code:X222X
Supply Number:CoMat 02-050
Type:sp01
Supply Short Name:CoMat 02-050 HIGH TEMPERATURE GLASS CLOTH TAPE
Supply Name:CoMat 02-050 HIGH TEMPERATURE GLASS CLOTH TAPE
Suppliers:
ManufacturerRemarks
X222X
Manufacturer Code:X111X
Supply Number:CoMat 02-051
Type:sp01
Supply Short Name:CoMat 02-051 HIGH TEMPERATURE GLASS CLOTH TAPE
Supply Name:CoMat 02-051 HIGH TEMPERATURE GLASS CLOTH TAPE
Suppliers:
ManufacturerRemarks
X111X
Manufacturer Code:X111X
Supply Number:CoMat 02-052
Type:sp01
Supply Short Name:CoMat 02-052 HIGH TEMPERATURE GLASS CLOTH TAPE
Supply Name:CoMat 02-052 HIGH TEMPERATURE GLASS CLOTH TAPE
Suppliers:
ManufacturerRemarks
X111X
Manufacturer Code:X111X
Supply Number:CoMat 02-053
Type:sp01
Supply Short Name:CoMat 02-053 HIGH TEMPERATURE GLASS CLOTH TAPE
Supply Name:CoMat 02-053 HIGH TEMPERATURE GLASS CLOTH TAPE
Suppliers:
ManufacturerRemarks
X111X
Manufacturer Code:LOCAL
Supply Number:CoMat 03-398
Type:sp01
Supply Short Name:CoMat 03-398 METAL SPRAYING STOPPING-OFFCOMPOUND
Supply Name:CoMat 03-398 METAL SPRAYING STOPPING-OFFCOMPOUND
Specification Groups:
Doc NumberType
OMAT:3/37AMETCO ANTI-BOND
Suppliers:
ManufacturerRemarks
LOCAL
39918
IE103
IE195
K1030
K6835
IE200
Manufacturer Code:1E1X8
Supply Number:CoMat 05-019
Type:sp01
Supply Short Name:CoMat 05-019 WATERPROOF SILICON CARBIDE
Supply Name:CoMat 05-019 WATERPROOF SILICON CARBIDE
Specification Groups:
Doc NumberType
OMAT: 5/31 (RR REF)WATERPROOF SILICON CARBIDE ABRASIVE PAPER, CAMI GRIT DESIGNATION 400 (ANSI B74.18)
JCR-184 (JAEC REF)
Suppliers:
ManufacturerRemarks
1E1X8
LOCAL
K6835
Manufacturer Code:1E1X8
Supply Number:CoMat 05-020
Type:sp01
Supply Short Name:CoMat 05-020 WATERPROOF SILICON CARBIDE
Supply Name:CoMat 05-020 WATERPROOF SILICON CARBIDE
Specification Groups:
Doc NumberType
OMAT: 5/33 (RR REF)WATERPROOF SILICON CARBIDE ABRASIVE PAPER, CAMI GRIT DESIGNATION 320 (ANSI B74.18)
JCR-027 (JAEC REF)
JCR-186 (JAEC REF)
Suppliers:
ManufacturerRemarks
1E1X8
LOCAL
K6835
Manufacturer Code:1E1X8
Supply Number:CoMat 05-021
Type:sp01
Supply Short Name:CoMat 05-021 WATERPROOF SILICON CARBIDE
Supply Name:CoMat 05-021 WATERPROOF SILICON CARBIDE
Specification Groups:
Doc NumberType
OMAT: 5/35 (RR REF)WATERPROOF SILICON CARBIDE ABRASIVE PAPER, CAMI GRIT DESIGNATION 240 (ANSI B74.18 )
JCR-188 (JAEC REF)
Suppliers:
ManufacturerRemarks
1E1X8
K6835
LOCAL
Manufacturer Code:1E1X8
Supply Number:CoMat 05-064
Type:sp01
Supply Short Name:CoMat 05-064 WATERPROOF SILICON CARBIDE
Supply Name:CoMat 05-064 WATERPROOF SILICON CARBIDE
Specification Groups:
Doc NumberType
OMAT: 5/29 (RR REF)WATERPROOF SILICON CARBIDE ABRASIVE PAPER, CAMI GRIT DESIGNATION 600 (ANSI B74.18)
JCR-182 (JAEC REF)
Suppliers:
ManufacturerRemarks
1E1X8
K6835
LOCAL
Manufacturer Code:X222X
Supply Number:CoMat 06-022
Type:sp01
Supply Short Name:CoMat 06-022 FLUORESCENT PENETRANT (POST-EMULSIFIED ULTRA HIGH SENSITIVITY)
Supply Name:CoMat 06-022 FLUORESCENT PENETRANT (POST-EMULSIFIED ULTRA HIGH SENSITIVITY)
Specification Groups:
Doc NumberType
ARDROX 985-P14 OMAT: 652 (CHEMETALL OAKITE 985-P14)It is not permitted to mix the selected CoMat 06‐022 letter suffix material with other CoMat 06‐022 letter suffix materials. Where CoMat 06‐022 is specified with no suffix, use one of the CoMat 06‐ 022 letter suffix materials.
Suppliers:
ManufacturerRemarks
X222X
Manufacturer Code:X222X
Supply Number:CoMat 06-063
Type:sp01
Supply Short Name:CoMat 06-063 FLUORESCENT PENETRANT (POST-EMULSIFIED MEDIUM SENSITIVITY)
Supply Name:CoMat 06-063 FLUORESCENT PENETRANT (POST-EMULSIFIED MEDIUM SENSITIVITY)
Specification Groups:
Doc NumberType
It is not permitted to mix the selected CoMat 06‐063 letter suffix material with other CoMat 06‐063 letter suffix materials. Where CoMat 06‐063 is specified with no suffix, use one of the CoMat 06‐063 letter suffix materials.
Suppliers:
ManufacturerRemarks
X222X
Manufacturer Code:X222X
Supply Number:CoMat 06-064
Type:sp01
Supply Short Name:CoMat 06-064FLUORESCENT PENETRANT (WATER WASHABLE MEDIUM SENSITIVITY)
Supply Name:CoMat 06-064 FLUORESCENT PENETRANT (WATER WASHABLE MEDIUM SENSITIVITY)
Specification Groups:
Doc NumberType
It is not permitted to mix the selected CoMat 06‐064 letter suffix material with other CoMat 06‐064 letter suffix materials.Where CoMat 06‐064 is specified with no suffix, use one of the CoMat 06‐064 letter suffix materials.
Suppliers:
ManufacturerRemarks
X222X
Manufacturer Code:LOCAL
Tool Number:Brush
Tool Name:Brush
Link not Found
Manufacturer Code:LOCAL
Tool Number:Cloth
Tool Name:Cloth
Link not Found
Manufacturer Code:0AM53
Tool Number:IAE 3R19016
Tool Name:IAE 3R19016 LE profile gage
Manufacturer Code:0AM53
Tool Number:IAE 3R19017
Tool Name:IAE 3R19017 LE profile gage
Manufacturer Code:0AM53
Tool Number:IAE 3R19317
Tool Name:IAE 3R19317 Template
Manufacturer Code:0AM53
Tool Number:IAE 3R19320
Tool Name:IAE 3R19320 Template
Manufacturer Code:0AM53
Tool Number:IAE 3R19321
Tool Name:IAE 3R19321 Mould
Manufacturer Code:0AM53
Tool Number:IAE 3R19323
Tool Name:IAE 3R19323 Mould
Manufacturer Code:LOCAL
Tool Number:Portable grinding equipment
Tool Name:Portablegrinding equipment
Manufacturer Code:LOCAL
Tool Number:Vibrating Marking Pencil
Tool Name:Vibrating Marking Pencil
Link not Found