TASK 72-31-11-300-008 LPC Fan Blade - Repair The Airfoil Damage, Repair 008(VRS1003)

DMC:V2500-A0-72-31-1101-01A-649A-C|Issue No:002.00|Issue Date:2016-05-01

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 72-31-11-300-008 LPC Fan Blade - Repair The Airfoil Damage, Repair 008(VRS1003)

Effectivity

FIG/ITEM

PART NO.

01-300

6A3494

Assembly A

01-300

6A3971

Assembly A

01-300

6A5485

Assembly A

01-300

6A6519

Assembly B

01-300

6A4700

Assembly C

01-300

6A6521

Assembly D

01-300

6A7403

Assembly A

01-300

6A7656

Assembly A

01-300

6A7649

Assembly A

01-300

6A7650

Assembly A

01-300

6A7651

Assembly A

01-300

6A7653

Assembly A

01-300

6A7658

Assembly A

01-300

6A7613

Assembly B

01-300

6A7652

Assembly B

01-300

6A7654

Assembly C

01-300

6A7614

Assembly D

01-300

6A7655

Assembly D

General

This repair gives the procedure to glass bead peen (Ref to VRS1724) to restore the airfoil surface finish. The VRS1724 can only be carried out on a blade the maximum five times. If VRS1724/5 is engraved adjacent to the part number, the blade cannot be glass bead peened and must be discarded.

This repair must only be done when the instruction to do so is given in 72-31-11 Inspection/Check.

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

The maximum number of dressed blades for a given fan set is the equivalent of three blades dressed to the maximum limits. All the remaining blades must not be dressed. This maximum number of dressed blades must be obeyed to prevent a risk of blade vibration.

All airfoil damage must be removed prior to the glass bead peening operation, refer to VRS1002, TASK 72-31-11-300-007 (REPAIR-007).

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

A change in fan balance can occur when fan blades are dressed to this TASK.

This repair should only be used after the blades are removed from the disk.

Material of component

PART IDENT

IAE

SYMBOL

MATERIAL

LP Compressor rotor blade

assembly

TFH

Titanium, Aluminum and Vanadium alloy

Price and availability - Refer to International Aero Engines.

Related repairs

LP Compressor Rotor Blade - Restore Airfoil Surface Finish, Refer to VRS1724 TASK 72-31-11-300-026 (REPAIR-026).

NOTE

Two recommended meters are:
Nova 201 precision ultrasonic thickness gage, with the DIR probe. Automation Industries Inc., Sperry Products Division, Shelton Rock Road, Danbury, Connecticut 06810
Krautkramer caliper CL 204 or CL 304, with the CLf 4 probe. Wells-Krautkramer Ltd, Non-Destructive Testing, Blackhorse Road, Letchworth, Hertfordshire SG6 1HF

NOTE

To identify the consumable materials refer to the PCI.

NOTE

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

Preliminary Requirements

Pre-Conditions

NONE

Support Equipment

NameManufacturerPart Number / IdentificationQuantityRemark
Chemical cleaning equipmentLOCALChemical cleaning equipment
Penetrant Crack Test EquipmentLOCALPenetrant crack test equipment
Ultrasonic thickness meterLOCALUltrasonic thickness meter

(see Note)

Portablegrinding equipmentLOCALPortable grinding equipment
Transient accoustic propagation equipmentLOCALTransient accoustic propagation equipment
Workshop inspection equipmentLOCALWorkshop inspection equipment
Vibro-engraving equipmentLOCALVibro-engraving equipment
IAE 3R19397 Perspex template c/c Assembly A and B0AM53IAE 3R193971
IAE 3R19399 Perspex template c/c Assembly A and B0AM53IAE 3R193991
IAE 3R19401 Perspex template c/c Assembly C and D0AM53IAE 3R194011
IAE 3R19403 Perspex template c/c Assembly C and D0AM53IAE 3R194031
IAE 3R18011 Thickness calibration gage0AM53IAE 3R180111

Consumables, Materials and Expendables

NameManufacturerPart Number / IdentificationQuantityRemark
CoMat 05-075 WATERPROOF SILICON CARBIDEIE241CoMat 05-075
CoMat 05-076 WATERPROOF SILICON CARBIDEK3895CoMat 05-076
CoMat 05-077 WATERPROOF SILICON CARBIDEK6835CoMat 05-077
CoMat 05-079 WATERPROOF SILICON CARBIDEK3895CoMat 05-079
CoMat 05-082 WATERPROOF SILICON CARBIDE44197CoMat 05-082
CoMat 06-022 FLUORESCENT PENETRANT (POST-EMULSIFIED ULTRA HIGH SENSITIVITY)LOCALCoMat 06-022

Spares

NONE

Safety Requirements

CAUTION

TITANIUM COMPONENTS. SILICON CARBIDE TYPE WHEELS, STONES AND ABRASIVE PAPERS ARE TO BE USED FOR THIS REPAIR.

CAUTION

ALUMINUM OXIDE MUST NOT BE USED.

CAUTION

THE MATERIAL WILL OXIDIZE AND CRACK IF MECHANICAL CUTTERS ARE USED HEAVILY. THIS HAS OCCURED IF THE COMPONENT SHOWS DARK STRAW TO BLUE DISCOLORATION.

Procedure

    1. SUBTASK 72-31-11-110-076 Chemically Clean

      1. Chemically clean the LP Compressor Rotor Blade Assembly.

      1. Refer to TASK 72-31-11-100-000 (CLEANING-000).

        Use chemical cleaning equipment.

    2. SUBTASK 72-31-11-230-069 Do a Crack Test

      CAUTION

      DO NOT PUT THE PART FULLY INTO THE SOLUTION IF THE LP COMPRESSOR BLADE ASSEMBLY IS POST SB72-0375 OR POST SB72-0384. ENSURE THAT THE PENETRANT FLUIDS DO NOT MAKE CONTACT WITH THE BLADE ROOT DOVETAIL FACES.

      1. Do a penetrant crack test.

      1. Refer to TASK 72-31-11-200-000 (INSPECTION/CHECK-000).

        Use penetrant crack test equipment.

    3. SUBTASK 72-31-11-270-054-A00 Do an Ultrasonic Test on the LP Compressor Rotor Blade Airfoil, Assembly A and Assembly B

      2. Do a transient acoustic propagation check on the blade airfoil.

      1. Refer to TASK 72-31-11-200-000 (INSPECTION/CHECK-000).

      3. Find the honeycomb area on the blade airfoil.

      4. Measure the thickness of the material adjacent to the damage in the honeycomb area.

      1. Make sure there is sufficient material to allow for the damage to be removed.

        The minimum thickness after repair is indicated on the perspex templates.

        NOTE

          Calibration Procedure.

          Calibration is done by the use of IAE 3R18011 Thickness calibration gage 1 off. Put the ultrasonic thickness meter probe on the thickness calibration gage. Use the area nearest in thickness to that of the damaged area to be measured. Refer to the manufacturers instructions and adjust the meter to give the correct indication. Measure each side to make sure calibration range is correct, i.e. if the blade is 0.153 in. (3.90 mm) thick at the damaged area, calibrate on the 0.157 in. (4.00 mm) area and the 0.118 in. (3.00 mm) and 0.197 in. (5.00 mm) areas. If necessary, adjust the meter so that all three indications are correct.

        NOTE

          Thickness Calculation.

          If a damage mark does not fall directly on a checking station the inspector is required to carry out a pro-rata calculation between the station points to determine what the thickness should be.

          The required calculation is as follows:

          Minimum thickness at damage area X = A - ((A - B) x percent C).

          Where:

          A = Thickness at first station.

          B = Thickness at second station.

          C = percent of distance from first station.

          e.g. Damage is 40 percent from station A where:

          A = 0.0484 in. (1.23 mm) and B = 0.025 in. (0.64 mm).

          .

          .

          Therefore:

          Minimum thickness X = 0.0484 - ((0.0484 - 0.025) x 40/100) = 0.039 in.

          or.

          Minimum thickness X = 1,23 - ((1.23 - 0.64) x 40/100) = 0.99 mm.

    4. SUBTASK 72-31-11-270-054-B00 Do an Ultrasonic Test on the LP Compressor Rotor Blade Airfoil, Assembly C and Assembly D

      2. Do a transient acoustic propagation check on the blade airfoil.

      1. Refer to TASK 72-31-11-200-000 (INSPECTION/CHECK-000).

      3. Find the honeycomb area on the blade airfoil.

      4. Measure the thickness of the material adjacent to the damage in the honeycomb area.

      1. Make sure there is sufficient material to allow for the damage to be removed.

        The minimum thickness after repair is indicated on the perspex templates.

        NOTE

          Calibration Procedure.

          Calibration is done by the use of IAE 3R18011 Thickness calibration gage thickness calibration gage, 1 off. Put the ultrasonic thickness meter probe on the thickness calibration gage. Use the area nearest in thickness to that of the damaged area to be measured. Refer to the manufacturers instructions and adjust the meter to give the correct indication. Measure each side to make sure calibration range is correct, i.e. if the blade is 0.153 in. (3.90 mm) thick at the damaged area, calibrate on the 0.157 in. (4.00 mm) area and the 0.118 in. (3.00 mm) and 0.197 in. (5.00 mm) areas. If necessary, adjust the meter so that all three indications are correct.

        NOTE

          Thickness Calculation.

          If a damage mark does not fall directly on a checking station the inspector is required to carry out a pro-rata calculation between the station points to determine what the thickness should be.

          The required calculation is as follows:

          Minimum thickness at damage area X = A - ((A - B) x percent C).

          Where:

          A = Thickness at first station.

          B = Thickness at second station.

          C = percent of distance from first station.

          e.g. Damage is 40 percent from station A where:

          A = 0.0484 in. (1.23 mm) and B = 0.025 in. (0.64 mm).

          .

          .

          Therefore:

          Minimum thickness X = 0.0484 - ((0.0484 - 0.025) x 40/100) = 0.039 in.

          or.

          Minimum thickness X = 1.23 - ((1.23 - 0.64) x 40/100) = 0.99 mm.

    5. SUBTASK 72-31-11-350-054 Remove Damage from the LP Compressor Rotor Blade

      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.

      2. Remove damage on the airfoil surfaces by material removal.

      1. Use portable grinding equipment.

        Continue to remove material until all the damage is removed.

        Below the 2.5 in. (63.5 mm) line, material removal must not be more than 0.010 in. (0.25 mm) in depth.

        Do not cut away below the airfoil fillet radius, 0.866 in. (22.0 mm) measured from the root bottom surface.

        If you use mechanical tools do not exceed 1000 rpm.

      3. Make smooth the repaired area(s).

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

      4. Polish the repaired area(s).

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

        NOTE

        The last polish is to be in a radial direction.

    6. SUBTASK 72-31-11-110-077 Do a Swab Etch

      CAUTION

      ENSURE THAT THE SWAB ETCH CHEMICALS AND NEUTRALISING FLUIDS DO NOT MAKE CONTACT WITH THE BLADE ROOT DOVETAIL FACES IF THE LP COMPRESSOR BLADE ASSEMBLY IS POST SB72-0375 OR POST SB72-0384.

      1. Chemically clean.

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

        Use chemical cleaning equipment.

      2. Swab etch the repaired area(s).

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

        Use chemical cleaning equipment.

    7. SUBTASK 72-31-11-230-070 Do a Crack Test

      CAUTION

      ENSURE THAT THE PENETRANT FLUIDS DO NOT MAKE CONTACT WITH THE BLADE ROOT DOVETAIL FACES IF THE LP COMPRESSOR BLADE ASSEMBLY IS POST SB72-0375 OR POST SB72-0384.

      1. Do a local penetrant crack test on the repaired area(s).

      1. Refer to the SPM TASK 70-23-05-230-501.

        Cracks are not permitted.

    8. SUBTASK 72-31-11-270-055 Do an Ultrasonic Examination of the LP Compressor Rotor Blade Airfoil, Assembly A and Assembly B

      1. Do a transient acoustic propagation check on the blade airfoil.

      1. Refer to TASK 72-31-11-200-000 (INSPECTION/CHECK-000).

        Use transient acoustic propagation equipment.

      2. Measure the thickness of the material at the repaired area(s).

      1. Calibrate as specified in Step.

        Make sure that minimum material thickness is remaining.

        NOTE

          Thickness Calculation.

          If a repaired area(s) does not fall directly on a checking station the inspector is required to carry out a pro-rata calculation between the station points to determine what the thickness should be.

          The required calculation is as follows:

          Minimum thickness at damage area X = A - ((A - B) x percent C).

          Where:

          A = Thickness at first station.

          B = Thickness at second station.

          C = percent of distance from first station.

          e.g. Damage is 40 percent from station A where:

          A = 0.0484 in. (1.23 mm) and B = 0.025 in. (0.64 mm).

          .

          .

          Therefore:

          Minimum thickness X = 0.0484 - ((0.0484 - 0.025) x 40/100) = 0.039 in.

          or.

          Minimum thickness X = 1.23 - ((1.23 - 0.,64) x 40/100) = 0.99 mm.

        2. CAUTION

          YOU MUST REJECT AND MUTILATE THE FAN BLADE IF THE MEASURED THICKNESS IS BELOW THE MINIMUM THICKNESS. THIS WILL PREVENT REUSE OF UNSERVICEABLE PARTS.

          Thickness below the minimum thickness.

          1. Reject and mutilate the part.

          1. Refer to the SPM TASK 70-21-01-220-501, SUBTASK 70-21-01-220-008.

    9. SUBTASK 72-31-11-270-056 Do an Ultrasonic Examination of the LP Compressor Rotor Blade Airfoil, Assembly C and Assembly D

      1. Do a transient acoustic propagation check on the blade airfoil.

      1. Refer to TASK 72-31-11-200-000 (INSPECTION/CHECK-000).

        Use transient acoustic propagation equipment.

      2. Measure the thickness of the material at the repaired area(s).

      1. Calibrate as specified in Step.

        Make sure that minimum material thickness is remaining.

        NOTE

          Thickness Calculation.

          If a repaired area(s) does not fall directly on a checking station the inspector is required to carry out a pro-rata calculation between the station points to determine what the thickness should be.

          The required calculation is as follows:

          Minimum thickness at damage area X = A - ((A - B) x percent C).

          Where:

          A = Thickness at first station.

          B = Thickness at second station.

          C = percent of distance from first station.

          e.g. Damage is 40 percent from station A where:

          A = 0.0484 in. (1.23 mm) and B = 0.025 in. (0.64 mm).

          Therefore:

          Minimum thickness X = 0.0484 - ((0.0484 - 0.025) x 40/100) = 0.039 in.

          or.

          Minimum thickness X = 1.23 - ((1.23 - 0.64) x 40/100) = 0.99 mm.

        2. CAUTION

          YOU MUST REJECT AND MUTILATE THE FAN BLADE IF THE MEASURED THICKNESS IS BELOW THE MINIMUM THICKNESS. THIS WILL PREVENT REUSE OF UNSERVICEABLE PARTS.

          Thickness below the minimum thickness.

          1. Reject and mutilate the part.

          1. Refer to the SPM TASK 70-21-01-220-501, SUBTASK 70-21-01-220-008.

    10. SUBTASK 72-31-11-350-093 Identify the Repair

      1. Make a mark VRS1003 adjacent to the part number.

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

        Use vibro engraving equipment.

    11. SUBTASK 72-31-11-380-055 Restore the Airfoil Surface Finish

    1. Refer to Figure.

      2. Restore the airfoil surface finish.

      1. Refer to VRS1724, TASK 72-31-11-300-026 (REPAIR-026).

    12. Figure: Repair Details and Dimensions

    Sheet 1

    Legend
    Repair Details and Dimensions

    Sheet 1

    Close

    Figure: Repair Details and Dimensions for Assembly A and B

    Sheet 2

    Legend
    Repair Details and Dimensions for Assembly A and B

    Sheet 2

    Close

    Figure: Repair Details and Dimensions for Assembly C and D

    Sheet 3

    Legend
    Repair Details and Dimensions for Assembly C and D

    Sheet 3

    Close

    Figure: Repair Details and Dimensions

    Sheet 4

    Legend
    Repair Details and Dimensions

    Sheet 4

    Close

    Figure: Repair Details and Dimensions for Assembly A and B

    Sheet 5

    Legend
    Repair Details and Dimensions for Assembly A and B

    Sheet 5

    Close

    Figure: Repair Details and Dimensions for Assembly C and D

    Sheet 6

    Legend
    Repair Details and Dimensions for Assembly C and D

    Sheet 6

    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 procedure to add inspection criteria. (87VJ306I)

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:IE241
Enterprise Name:DELETED. Was ANGLO ABRASIVES.
Manufacturer Code:K3895
Enterprise Name:DELETED. REFER TO VENDOR CODE KC1D9.
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:1E1X8
Supply Number:CoMat 05-075
Type:sp01
Supply Short Name:CoMat 05-075 WATERPROOF SILICON CARBIDE
Supply Name:CoMat 05-075 WATERPROOF SILICON CARBIDE
Specification Groups:
Doc NumberType
OMAT: 5/28 (RR REF)WATERPROOF SILICON CARBIDE ABRASIVE PAPER, CAMI GRIT DESIGNATION 800
JCR-181 (JAEC REF)
Suppliers:
ManufacturerRemarks
1E1X8
K1905
K6835
LOCAL
Manufacturer Code:1E1X8
Supply Number:CoMat 05-076
Type:sp01
Supply Short Name:CoMat 05-076 WATERPROOF SILICON CARBIDE
Supply Name:CoMat 05-076 WATERPROOF SILICON CARBIDE
Specification Groups:
Doc NumberType
OMAT: 5/30 (RR REF)WATERPROOF SILICON CARBIDE ABRASIVE PAPER, CAMI GRIT DESIGNATION 500
JCR-183 (JAEC REF)
Suppliers:
ManufacturerRemarks
1E1X8
K6835
LOCAL
Manufacturer Code:1E1X8
Supply Number:CoMat 05-077
Type:sp01
Supply Short Name:CoMat 05-077 WATERPROOF SILICON CARBIDE
Supply Name:CoMat 05-077 WATERPROOF SILICON CARBIDE
Specification Groups:
Doc NumberType
OMAT: 5/32 (RR REF)WATERPROOF SILICON CARBIDE ABRASIVE PAPER, CAMI GRIT DESIGNATION 360
JCR-185 (JAEC REF)
Suppliers:
ManufacturerRemarks
1E1X8
K6835
LOCAL
Manufacturer Code:1E1X8
Supply Number:CoMat 05-079
Type:sp01
Supply Short Name:CoMat 05-079 WATERPROOF SILICON CARBIDE
Supply Name:CoMat 05-079 WATERPROOF SILICON CARBIDE
Specification Groups:
Doc NumberType
OMAT: 5/36 (RR REF)WATERPROOF SILICON CARBIDE ABRASIVE PAPER, CAMI GRIT DESIGNATION 220 (ANSI B74.18)
JCR-189 (JAEC REF)
Suppliers:
ManufacturerRemarks
1E1X8
K6835
LOCAL
Manufacturer Code:1E1X8
Supply Number:CoMat 05-082
Type:sp01
Supply Short Name:CoMat 05-082 WATERPROOF SILICON CARBIDE
Supply Name:CoMat 05-082 WATERPROOF SILICON CARBIDE
Specification Groups:
Doc NumberType
OMAT: 5/39 (RR REF)WATERPROOF SILICON CARBIDE ABRASIVE PAPER, CAMI GRIT DESIGNATION 120 (ANSI B74.18)
JCR-192 (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:LOCAL
Tool Number:Chemical cleaning equipment
Tool Name:Chemical cleaning equipment
Manufacturer Code:0AM53
Tool Number:IAE 3R18011
Tool Name:IAE 3R18011 Thickness calibration gage
Manufacturer Code:0AM53
Tool Number:IAE 3R19397
Tool Name:IAE 3R19397 Perspex template c/c Assembly A and B
Manufacturer Code:0AM53
Tool Number:IAE 3R19399
Tool Name:IAE 3R19399 Perspex template c/c Assembly A and B
Manufacturer Code:0AM53
Tool Number:IAE 3R19401
Tool Name:IAE 3R19401 Perspex template c/c Assembly C and D
Manufacturer Code:0AM53
Tool Number:IAE 3R19403
Tool Name:IAE 3R19403 Perspex template c/c Assembly C and D
Manufacturer Code:LOCAL
Tool Number:Penetrant crack test equipment
Tool Name:Penetrant Crack Test Equipment
Manufacturer Code:LOCAL
Tool Number:Portable grinding equipment
Tool Name:Portablegrinding equipment
Manufacturer Code:LOCAL
Tool Number:Transient accoustic propagation equipment
Tool Name:Transient accoustic propagation equipment
Manufacturer Code:LOCAL
Tool Number:Ultrasonic thickness meter
Tool Name:Ultrasonic thickness meter
Manufacturer Code:LOCAL
Tool Number:Vibro-engraving equipment
Tool Name:Vibro-engraving equipment
Manufacturer Code:LOCAL
Tool Number:Workshop inspection equipment
Tool Name:Workshop inspection equipment