TASK 72-41-15-300-015 HPC Stage 7 Rotor Blade - Weld Repair The Airfoil, Repair-015 (VRS6053)

DMC:V2500-A0-72-41-1507-00A-627A-C|Issue No:003.00|Issue Date:2018-02-01

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 72-41-15-300-015 HPC Stage 7 Rotor Blade - Weld Repair The Airfoil, Repair-015 (VRS6053)

Effectivity

FIG/ITEM

PART NO.

ASSEMBLY

02-270

6A3246

A

02-270

6A4905

B

02-270

6A5588

A

02-270

6A6462

B

02-270

6A6493

A

02-270

6A8314

C

02-285

6A3247

A

02-285

6A4906

B

02-285

6A5589

A

02-285

6A6463

B

02-285

6A6494

A

02-285

6A8315

C

02-300

6A3245C01

A

02-300

6A4907C01

B

02-300

6A5584C01

A

02-300

6A6469C01

B

02-300

6A6492C01

A

02-300

6A8312

C

02-315

6A3245C01

A

02-315

6A4907C01

B

02-315

6A5584C01

A

02-315

6A6469C01

B

02-315

6A6492C01

A

02-315

6A8312

C

02-317

6A3245C02

A

02-317

6A4907C02

B

02-317

6A5584C02

A

02-317

6A6469C02

B

02-317

6A6492C02

A

02-317

6A8313

C

Material of component

PART IDENT

MATERIAL

HP compressor rotor blade - Stage 7

Titanium alloy

General

This repair must only be done when the instruction to do so is given in 72-41-15 Inspection.

This TASK gives the procedure to repair the HP compressor rotor blade, stage 7 tip length by welding.

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

To keep the HP compressor efficiency, rotor blades are repaired as near to the new blade condition as possible.

Rotor blades must be repaired as soon as damage or wear is monitored, to get back HP compressor efficiency and extend the rotor blade life.

This is a Source Demonstration Repair which can only be done by Authorized Repair Vendors.

This repair cannot be done if:

- The minimum airfoil dimensions as given in 72-41-15 Inspection cannot be achieved.

- The airfoil surface has been repaired three times, refer to Repair VRS6150, TASK 72-41-15-300-040 (REPAIR-040).

Discard blades, if during the weld procedure, arcing has occurred on any part of the blade.

TASKS identified by SPM TASK are in the Standard Practices and Processes manual (SPM).

Price and Availability

Refer to International Aero Engines

Related Repairs

HP Compressor Stage 7 and 8 Compressor Blade - The Replacement of the Flame Deposition Material. Refer to Repair VRS6153, TASK 72-41-15-300-034 (REPAIR-034).

HP Compressor - Stages 3 to 12 - Rotor blades - Restore airfoil surface condition. Refer to Repair VRS6150, TASK 72-41-15-300-040 (REPAIR-040).

HP Compressor Rotor blades - Stage 7 to 12 - Shot Peen Root of Blade to Restore Fatigue Strength. Refer to Repair VRS6152, TASK 72-41-15-300-043 (REPAIR-043).

NOTE

Equipment and materials necessary to do this repair are in the SPM TASKS given below:
SPM TASK 70-09-00-400-501
SPM TASK 70-11-01-300-503
SPM TASK 70-11-08-300-503
SPM TASK 70-12-01-120-501
SPM TASK 70-12-02-120-501
SPM TASK 70-23-04-230-501
SPM TASK 70-31-02-310-501-001

NOTE

  1. It is possible that some materials in the consumable materials chart cannot be used for some or all of the necessary applications. Before you use the materials, make sure the types, quantities and applications of the materials necessary are legally permitted in your location. All persons must obey all applicable federal, state, local and provincial laws and regulations when it is necessary to work with these materials.

  2. To identify the consumable materials, refer to the Overhaul Processes and Consumables Index (PCI).

  3. Other necessary consumable materials are referred to in the SPM TASKS.

Preliminary Requirements

Pre-Conditions

NONE

Support Equipment

NameManufacturerPart Number / IdentificationQuantityRemark
Chemical cleaning equipmentLOCALChemical cleaning equipment
Penetrant Crack Test EquipmentLOCALPenetrant crack test equipment
Abrasive blast equipmentLOCALAbrasive blast equipment
Welding equipmentLOCALWelding equipment

Argonarc

Heat treatment equipmentLOCALHeat treatment equipment
Hardness testerLOCALHardness tester
Grinding machineLOCALGrinding machine
Standard workshop equipmentLOCALStandard workshop equipment
Radiographic equipmentLOCALRadiographic equipment
Vibrating marking pencilLOCALVibrating marking pencil
Workshop inspection equipmentLOCALWorkshop inspection equipment

Consumables, Materials and Expendables

NameManufacturerPart Number / IdentificationQuantityRemark
CoMat 02-001 ADHESIVE TAPE (MASKING)LOCALCoMat 02-001
CoMat 03-285 TITANIUM WELD WIREIE306CoMat 03-285
CoMat 03-348 WELDING WIRELOCALCoMat 03-348
CoMat 05-002 ABRASIVE MEDIUM, ALUMINUM OXIDELOCALCoMat 05-002
CoMat 05-003 ABRASIVE MEDIUM ALUMINUM OXIDE, 120/220 GRADELOCALCoMat 05-003
CoMat 06-022 FLUORESCENT PENETRANT (POST-EMULSIFIED ULTRA HIGH SENSITIVITY)LOCALCoMat 06-022

Spares

NONE

Safety Requirements

NONE

Procedure

    1. Repair Facilities

      1. The Source Demonstration requirements of this repair means that any facility not authorized to accomplish this repair either, utilize the Authorized Repair Vendors listed below or contact the IAE Repair Services Group to determine if a qualification program can be initiated at their facility.

        IAE International Aero Engines AG

        400 Main Street

        M/S 121-10

        East Hartford CT 06118

        U.S.A.

        Attn: Manager Technical Services

      1. Authorized Repair Vendors for Repair VRS6053 of Assembly A, Assembly B and Assembly C parts are listed below:

        Airfoil Services Sdn Bhd

        No. 12 Jalan Teknologi

        Taman Sains Selangor 1

        Kota Damansara PJU5

        47810 Petailing Jaya

        Selangor Darul Ehsan

        MALAYSIA

        Turbine Overhaul Services Pte, Ltd. (TOS)

        5 Tuas Drive Two - Mail Stop 107-58

        Singapore 638639

        Tel: 65-6860-2260

        Fax: 65-6862-1068

        Rolls-Royce Inchinnan

        Inchinnan Drive

        Inchinnan Business Park

        Inchinnan, PA4 9AF

        Scotland

        2. Authorized Repair Vendors for Repair VRS6053 of Assembly A and Assembly B parts are listed below:

          Chromalloy Dallas

          14042 Distribution Way

          Dallas, TX 75234

          U.S.A.

          Rolls Royce

          Aero-Engine Services Ltd

          Component Refurbishment

          Mavor Avenue

          Nerston

          EAST KILBRIDE

          Glasgow

          G74 4PY

          SCOTLAND

          Ishikawajima-Harima Heavy Industries Co. Ltd.

          229 Tonogaya, Mizuho-Machi

          Nishitama-gun

          Tokyo 190-1297

          JAPAN

          Turbine Overhaul Services Pte, Ltd. (TOS)

          5 Tuas Drive Two - Mail Stop 107-58

          Singapore 638639

          Tel: 65-6860-2260

          Fax: 65-6862-1068

          Rolls-Royce Inchinnan

          Inchinnan Drive

          Inchinnan Business Park

          Inchinnan, PA4 9AF

          Scotland

        1. The designation by IAE of an Authorized Repair Vendor indicates that the Repair Vendor has demonstrated the necessary capability to enable it to carry out the listed repair work. However, IAE makes no warranties or representations concerning the qualifications or quality standards of the Repair Vendors to carry out the repair work and accepts no responsibility whatsoever for any work that may be carried out by a Repair Vendor other than when IAE is listed as the Repair Vendor. Authorized Repair Vendors do not act as agents or representatives of IAE.

    2. SUBTASK 72-41-15-110-100 Clean the Stage 7 Rotor Blades

      1. Chemically clean the blades.

      1. Refer to TASK 72-41-15-100-000 (CLEANING-000).

      2. Use chemical cleaning equipment.

    3. SUBTASK 72-41-15-120-060 Remove the Aluminum Oxide Coating, as necessary, Assembly A and Assembly B

    1. Refer to Figure.

      2. Mask the areas of the blade not to be blasted.

      1. Use CoMat 02-001 ADHESIVE TAPE (MASKING) or locally manufactured fixture.

      3. Remove the aluminum oxide coating from the blade tip, as necessary.

      1. Refer to the SPM TASK 70-12-02-120-501.

      2. Use CoMat 05-002 ABRASIVE MEDIUM, ALUMINUM OXIDE with abrasive blast equipment.

      3. Make sure that the minimum amount of blade material is removed.

    4. Remove the masks, when the blasting is completed.

    4. SUBTASK 72-41-15-220-219 Examine the Stage 7 Rotor Blades

      2. Examine the blades to make sure the blades can be repaired.

      1. Examine the blades if repair VRS6150 is done.

      2. If the blade is repaired by VRS6150 three times, reject the blade.

      3. The blades must be easily identified to let dimensions before and after repair to be checked.

      4. Record blade length before repair.

    5. SUBTASK 72-41-15-120-061 Vapor Blast the Stage 7 Rotor Blades

    1. Refer to Figure, Figure and Figure.

      2. Apply masking to the areas of the blade not to be welded.

      3. Vapor blast the areas of the blade to be welded.

      1. Refer to the SPM TASK 70-12-01-120-501.

    4. Remove the masking tape.

    6. SUBTASK 72-41-15-110-101 Clean the Stage 7 Rotor Blades

      1. NOTE

        The blades must be fully cleaned before you do Step or Step.

        Chemically clean the blades.

      1. Refer to the SPM TASK 70-11-08-300-503.

      2. Use chemical cleaning equipment.

    7. SUBTASK 72-41-15-310-055-A00 Weld the Stage 7 Rotor Blade Tips, Assembly A and Assembly B

    1. CAUTION

      YOU MUST PREVENT ARCING ON THE BLADE DURING THE WELD PROCEDURE.

      Refer to Figure, Figure and Figure.

      2. Build up the blade tip with weld to restore the length.

      1. Refer to the SPM TASK 70-31-02-310-501-001.

      2. Use CoMat 03-285 TITANIUM WELD WIRE with argon arc welding equipment.

      3. NOTE

        Weld Data.
        Refer to Authorized Repair Vendors in 4. Repair Facilities, Para B. and Para C. for weld parameters.
        An increase in blade length of not more than a maximum of 0.060 in. (1.52 mm) is permitted by this repair.

        Apply sufficient weld to get the necessary blade length to get final dimensions.

      1. Identify a sample stage 7 rotor blade and repair along with each repair batch.

    8. SUBTASK 72-41-15-310-055-B00 Weld the Stage 7 Rotor Blade Tips, Assembly C

    1. CAUTION

      YOU MUST PREVENT ARCING ON THE BLADE DURING THE WELD PROCEDURE.

      Refer to Figure and Figure.

      2. Build up the blade tip with weld to restore the length.

      1. Refer to the SPM TASK 70-31-02-310-501-001.

      2. Use CoMat 03-348 WELDING WIRE with argon arc welding equipment.

      3. NOTE

        Weld Data.
        Refer to Authorized Repair Vendors in 4. Repair Facilities, Para B. and Para C. for weld parameters.
        An increase in blade length of not more than a maximum of 0.060 in. (1.52 mm) is permitted by this repair.

        Apply sufficient weld to get the necessary blade length to get final dimensions.

      1. Identify a sample stage 7 rotor blade and repair along with each repair batch.

    9. SUBTASK 72-41-15-370-055-A00 Heat-Treat the Stage 7 Rotor Blades, Assembly A and Assembly B

      1. NOTE

        Heat-Treat Data.
        Heat to a temperature of 1157 deg F (625 deg C) for 2 hours in a vacuum or argon atmosphere.
        Cool down to room temperature in air.

        Heat-treat the blade in a vacuum or controlled atmosphere.

      1. Refer to the SPM TASK 70-31-02-310-501-001.

      2. Use heat treatment equipment.

    10. SUBTASK 72-41-15-370-055-B00 Heat-Treat the Stage 7 Rotor Blades, Assembly C

      1. NOTE

        Heat-Treat Data.
        Heat to a temperature of 1103 deg F (595 deg C) for 4 hours in a vacuum or argon atmosphere.
        Cool down to room temperature in air.

        Heat-treat the blade in a vacuum or controlled atmosphere.

      1. Refer to the SPM TASK 70-31-02-310-501-001.

      2. Use heat treatment equipment.

    11. SUBTASK 72-41-15-220-220-A00 Do a Hardness Check, Assembly A and Assembly B

      1. NOTE

        If the sample blade is outside of the hardness variation limits, additional blades must be sampled. If more than 10 percent have a variation in hardness greater than 30 HV, then the cause must be investigated.

        Do a hardness check on a longitudinal cross section of a sample blade.

      1. Use a sample blade.

      2. The hardness variation must be in less than 30 HV across the weld material, heat affected zone and parent material.

      3. This is a guide for quality control purposes and is not an absolute limit.

      4. Use a hardness tester.

    12. SUBTASK 72-41-15-220-220-B00 Do a Hardness Check, Assembly C

      1. NOTE

        If the sample blade is outside of the hardness variation limits, additional blades must be sampled. If more than 10 percent have a variation in hardness greater than with the approved data card, then the cause must be investigated.

        Do a hardness check on a longitudinal cross section of a sample blade.

      1. Use a sample blade.

      2. The hardness variation across the weld material, heat affected zone and parent material must be in the approved range. Refer to approved vendor test sample record.

      3. This is a guide for quality control purposes and is not an absolute limit.

      4. Use a hardness tester.

    13. SUBTASK 72-41-15-350-107 Put the Shape Back on the Stage 7 Rotor Blade Contour and Height

    1. CAUTION

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

      CAUTION

      TITANIUM COMPONENTS - MAXIMUM SPEED FOR MECHANICAL TOOLS MUST NOT BE MORE THAN 1000 REVOLUTIONS PER MINUTE.

      CAUTION

      TITANIUM COMPONENTS - YOU MUST MAKE SURE THAT WHEN YOU REMOVE MATERIAL, BLEND AND POLISH, TO MAKE SMOOTH THAT NO SPARKS ARE PRODUCED.

      CAUTION

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

      CAUTION

      TITANIUM COMPONENTS - GRIT BLASTING IS A PROCESS OF EROSION THAT CAN DAMAGE ENGINE PARTS. YOU MUST TAKE CARE NOT TO CAUSE DAMAGE TO THE ENGINE PARTS.

      2. Put the shape back on the blade contour.

      1. Refer to Authorized Repair Vendors in 4. Repair Facilities, Para B. and Para C., for special machines to make the blade contour or use standard workshop equipment.

      3. Grind the blade tip to the correct height.

      1. Use a grinding machine.

      4. Dress the blade tip to remove burrs.

      1. Use standard workshop equipment.

    14. SUBTASK 72-41-15-220-221 Examine the Stage 7 Rotor Blades

      2. Visually examine the blade for signs of electric arcing.

      1. If signs of arcing are found then discard.

      3. Visually examine the airfoil surface and the blade contour.

      1. Scratches or scores on the airfoil surfaces are not permitted.

      2. If scratches or scores are shown on the airfoil surface, do Step.

      4. Dimensionally examine the blade tip.

      1. Make sure the tip contour and thickness are in the given limits.

      5. Dimensionally examine the blade height.

      1. Compare before and after repair dimensions, refer to Step.

      2. Welded material must be in the given limits.

    15. SUBTASK 72-41-15-350-108 Polish the Stage 7 Rotor Blade Airfoil Surface and Contour

    1. CAUTION

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

      CAUTION

      TITANIUM COMPONENTS - MAXIMUM SPEED FOR MECHANICAL TOOLS MUST NOT BE MORE THAN 1000 REVOLUTIONS PER MINUTE.

      CAUTION

      TITANIUM COMPONENTS - YOU MUST MAKE SURE THAT WHEN YOU REMOVE MATERIAL, BLEND AND POLISH, TO MAKE SMOOTH THAT NO SPARKS ARE PRODUCED.

      CAUTION

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

      CAUTION

      TITANIUM COMPONENTS - GRIT BLASTING IS A PROCESS OF EROSION THAT CAN DAMAGE ENGINE PARTS. YOU MUST TAKE CARE NOT TO CAUSE DAMAGE TO THE ENGINE PARTS.

      Refer to Figure, Figure and Figure.

      2. Polish the blade airfoil surface and contour to remove scratches.

      1. Refer to Authorized Repair Vendors in 4. Repair Facilities, Para B. and Para C., for special machines to make the blade contour.

      2. Hand methods are permitted to polish the blade contour.

    16. SUBTASK 72-41-15-110-137 Do a Swab Etch

      1. Chemically clean.

      1. Refer to the SPM TASK 70-11-08-300-503, SUBTASK 70-11-08-300-001.

      2. Use chemical cleaning equipment.

      2. Swab etch the repaired area.

      1. Refer to the SPM TASK 70-11-08-300-503, SUBTASK 70-11-08-300-002.

      2. Use chemical cleaning equipment.

    17. SUBTASK 72-41-15-230-083 Do a Crack Test

      1. Do a penetrant crack test.

      1. Refer to the SPM TASK 70-23-04-230-501.

      3. Use penetrant crack test equipment.

      4. Discard any cracked blades.

    18. SUBTASK 72-41-15-260-076 Radiographically Examine the Stage 7 Rotor Blades

      1. NOTE

        Radiographic Data.
        Refer to Authorized Repair Vendors in 4. Repair Facilities, Para B. and Para C., for the appropriate data card and Radiographic Examination parameters.

        Radiographically examine the welded blade tip.

      1. Cracks or unwanted material are not permitted.

      2. Pores larger than 0.006 in. (0.15 mm) diameter are not permitted.

      3. Pores with a distance of less than 0.200 in. (5.10 mm) between them, are not permitted.

      4. Surfaces broken by pores are not permitted.

      5. Pores are not permitted less than 0.040 in. (1.00 mm) from the leading and trailing edges.

      6. Use radiographic equipment.

    19. SUBTASK 72-41-15-380-086 Restore Airfoil Surface Condition

      1. Restore airfoil surface condition.

      1. Refer to Repair VRS6150, TASK 72-41-15-300-040 (REPAIR-040).

    20. SUBTASK 72-41-15-380-111 Shot-Peen the Dovetail Root of the HP Compressor Stage 7 Rotor Blade

      1. Shot-peen the dovetail root of the HP Compressor stage 7 rotor blade.

      1. Refer to Repair VRS6152, TASK 72-41-15-300-043 (REPAIR-043).

    21. SUBTASK 72-41-15-340-054 Apply the Aluminum Oxide Coating, Assembly A and Assembly B

      1. NOTE

        Operators have the option to include the application of the Aluminum Oxide Coating as necessary. The operation to apply the aluminium oxide coating is not mandatory.

        Apply aluminum oxide coating to the blade tip.

      1. Refer to Repair VRS6153, TASK 72-41-15-300-034 (REPAIR-034).

    22. SUBTASK 72-41-15-350-053 Identify the Blades, Assembly A and Assembly B

      1. CAUTION

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

        If the aluminum oxide coating has not been reapplied, reidentify the blades.

      1. Refer to SBE 72-0252.

      2. Refer to the SPM TASK 70-09-00-400-501, SUBTASK 70-09-00-400-001.

      2. If the aluminum oxide has been reapplied do not change the part number.

      1. Refer to SBE 72-0252.

    23. Figure: Repair Details and Dimensions - Assembly A and Assembly B

    Sheet 1

    Legend
    Repair Details and Dimensions - Assembly A and Assembly B

    Sheet 1

    Close

    Figure: Repair Details and Dimensions

    Sheet 2

    Legend
    Repair Details and Dimensions

    Sheet 2

    Close

    Figure: Repair Details and Dimensions

    Sheet 1

    Legend
    Repair Details and Dimensions

    Sheet 1

    Close

    Figure: Repair Details and Dimensions

    Sheet 2

    Legend
    Repair Details and Dimensions

    Sheet 2

    Close

    Figure: Repair Details and Dimensions - Assembly A

    Sheet 1

    Legend
    Repair Details and Dimensions - Assembly A

    Sheet 1

    Close

    Figure: Repair Details and Dimensions - Assembly A

    Sheet 2

    Legend
    Repair Details and Dimensions - Assembly A

    Sheet 2

    Close

    Figure: Repair Details and Dimensions - Assembly B and Assembly C

    Sheet 1

    Legend
    Repair Details and Dimensions - Assembly B and Assembly C

    Sheet 1

    Close

    Figure: Repair Details and Dimensions - Assembly B and Assembly C

    Sheet 2

    Legend
    Repair Details and Dimensions - Assembly B and Assembly C

    Sheet 2

    Close

    Figure: Repair Details and Dimensions - Assembly A

    Sheet 3

    Legend
    Repair Details and Dimensions - Assembly A

    Sheet 3

    Close

    Figure: Repair Details and Dimensions - Assembly B and Assembly C

    Sheet 4

    Legend
    Repair Details and Dimensions - Assembly B and Assembly C

    Sheet 4

    Close

    Figure: Repair Details and Dimensions

    Repair Details and Dimensions

    Figure: Repair Details and Dimensions

    Repair Details and Dimensions

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Revised the repair facilities to update vendor addresses. (17VC206)

Manufacturer Code:IE306
Enterprise Name:DELETED. SEE CAGE CODE KB362
BU Name:VBC LTD
Manufacturer Code:LOCAL
Enterprise Name:LOCALLY SUPPLIED
Manufacturer Code:LOCAL
Supply Number:CoMat 02-001
Type:sp01
Supply Short Name:CoMat 02-001 ADHESIVE TAPE (MASKING)
Supply Name:CoMat 02-001 ADHESIVE TAPE (MASKING)
Specification Groups:
Doc NumberType
OMAT: 230 (RR REF)ZINC OXIDE AT142
JCR-197 (JAEC REF)ZINC OXIDE AT142
Suppliers:
ManufacturerRemarks
LOCAL
K6835
U0415
Manufacturer Code:1EW28
Supply Number:CoMat 03-285
Type:sp01
Supply Short Name:CoMat 03-285 TITANIUM WELD WIRE
Supply Name:CoMat 03-285 TITANIUM WELD WIRE
Specification Groups:
Doc NumberType
IMI 829 (Ti 5331S) WELD WIRE
Suppliers:
ManufacturerRemarks
1EW28
22994
K6835
KB362
U9025
Manufacturer Code:LOCAL
Supply Number:CoMat 03-348
Type:sp01
Supply Short Name:CoMat 03-348 WELDING WIRE
Supply Name:CoMat 03-348 WELDING WIRE
Specification Groups:
Doc NumberType
AMS 49526-2-4-2
Suppliers:
ManufacturerRemarks
LOCAL
2R602
3G172
58401
Manufacturer Code:X222X
Supply Number:CoMat 05-002
Type:sp01
Supply Short Name:CoMat 05-002 ABRASIVE MEDIUM, ALUMINUM OXIDE
Supply Name:CoMat 05-002 ABRASIVE MEDIUM, ALUMINUM OXIDE
Specification Groups:
Doc NumberType
Where CoMat 05-002 is specified with no letter suffix, use one of the CoMat 05-002 letter suffix alternatives.
Suppliers:
ManufacturerRemarks
X222X
Manufacturer Code:X222X
Supply Number:CoMat 05-003
Type:sp01
Supply Short Name:CoMat 05-003 ABRASIVE MEDIUM ALUMINUM OXIDE, 120/220 GRADE
Supply Name:CoMat 05-003 ABRASIVE MEDIUM ALUMINUM OXIDE, 120/220 GRADE
Specification Groups:
Doc NumberType
Use one of the CoMat 05-003 letter suffix alternatives.
Suppliers:
ManufacturerRemarks
X222X
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
Link not Found
Manufacturer Code:LOCAL
Tool Number:Chemical cleaning equipment
Tool Name:Chemical cleaning equipment
Link not Found
Link not Found
Link not Found
Manufacturer Code:LOCAL
Tool Number:Penetrant crack test equipment
Tool Name:Penetrant Crack Test Equipment
Link not Found
Link not Found
Link not Found
Manufacturer Code:LOCAL
Tool Number:Welding equipment
Tool Name:Welding equipment
Manufacturer Code:LOCAL
Tool Number:Workshop inspection equipment
Tool Name:Workshop inspection equipment