TASK 72-44-20-200-001-A01 HPT Stage 1 Vane - Examine, Inspection-001

DMC:V2500-A0-72-44-2000-00A-310A-C|Issue No:003.00|Issue Date:2015-05-01

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 72-44-20-200-001-A01 HPT Stage 1 Vane - Examine, Inspection-001

Effectivity

FIG/ITEM

PART NO.

01-250

2A0091CL21

01-250

2A2591CL21

01-251

2A0091CL22

01-251

2A2591Cl22

01-252

2A0091CL23

01-252

2A2591CL23

01-253

2A0091CL24

01-253

2A2591CL24

01-254

2A0091CL25

01-254

2A2591CL25

01-255

2A0091CL26

01-255

2A2591CL26

01-256

2A0091CL27

01-256

2A2591CL27

01-257

2A0091CL28

01-257

2A2591CL28

01-258

2A0091CL29

01-258

2A2591CL29

01-259

2A0091CL30

01-259

2A2591CL30

01-260

2A0091CL31

01-260

2A2591CL31

01-261

2A0091CL32

01-261

2A2591CL32

01-262

2A0091CL33

01-262

2A2591CL33

01-263

2A0091CL34

01-263

2A2591CL34

01-264

2A0091CL35

01-264

2A2591CL35

01-265

2A0091CL36

01-265

2A2591CL36

01-266

2A0091CL37

01-266

2A2591CL37

01-267

2A0091CL38

01-267

2A2591CL38

01-268

2A0091CL39

01-268

2A2591CL39

01-269

2A0091CL40

01-269

2A2591CL40

01-270

2A0091CL41

01-270

2A2591CL41

01-271

2A0091CL42

01-271

2A2591CL42

01-272

2A0091CL43

01-272

2A2591CL43

01-273

2A0091CL44

01-273

2A2591CL44

01-274

2A0091CL45

01-274

2A2591CL45

01-275

2A0091CL46

01-275

2A2591CL46

01-276

2A0091CL47

01-276

2A2591CL47

01-277

2A0091CL48

01-277

2A2591CL48

01-278

2A0091CL48-5

01-279

2A0091CL49

01-279

2A2591CL49

01-280

2A0091CL49-5

01-284

2A2591CL50

01-286

2A2591CL51

General

This TASK gives the procedure for the inspection of the stage 1 HPT vane cluster assembly. For the other stage 1 HPT vane cluster assembly parts refer to TASK 72-44-20-200-000 (INSPECTION/CHECK-000).

Fig/item numbers in parentheses in the procedure agree with those used in the IPC.

The policy that is necessary for inspection is given in the SPM TASK 70-20-00-200-501.

All the parts must be cleaned before any part is examined. Refer to the SPM TASK 70-10-00-100-501.

All parts must be visually examined for damage, corrosion and wear. Any defects that are not identified in the procedure must be referred to IAE.

The procedure for those parts which must have a crack test is given in SUBTASK 72-44-20-230-051. Do the test before the part is visually examined.

Do not discard any part until you are sure there are no repairs available. Refer to the instructions in Repair before a discarded part is used again or oversize parts are installed.

Parts which should be discarded can be held although no repair available. The repair of a discarded part could be shown to be necessary at a later date.

All parts must be examined to make sure that all the repairs have been completed satisfactorily.

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

References

Refer to the SPM for data on these items.

Definition of Damages, SPM TASK 70-02-02-350-501

Moderate Cleaning, SPM TASK 70-11-03-300-503

Vapor Degrease, SPM TASK 70-11-01-300-503

Cleaning, SPM TASK 70-12-09-120-501

Air flow - Turbine Blades and Vanes, SPM TASK 70-72-01-720-501

Ultrasonic Clean all Metal (But not Magnesium), SPM TASK 70-13-01-100-501

Inspection of Parts, SPM TASK 70-20-00-200-501

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
OvenLOCALOven

(air furnace)

IAE 2P16342 Digital indicator0AM53IAE 2P163421
IAE 2P16343 Computer kit0AM53IAE 2P163431
IAE 2P16344 Computer program0AM53IAE 2P163441
IAE 2P16234 Gage0AM53IAE 2P162341
IAE 2P16235 Master0AM53IAE 2P162351
IAE 2P16081 Airflow fixture0AM53IAE 2P160811
IAE 2P16085 Airflow master0AM53IAE 2P160851
IAE 2P16156 Airflow insert set0AM53IAE 2P161561
IAE 2P16157 Airflow insert set (Optional)0AM53IAE 2P161571

Consumables, Materials and Expendables

NameManufacturerPart Number / IdentificationQuantityRemark
CoMat 02-029 MASKING TAPE (CLOTH BACKING)0AM53CoMat 02-029
CoMat 02-030 MASKING TAPE (CLOTH BACKING)IE479CoMat 02-030

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-44-20-230-051-002 Examine the Stage 1 HPT Vane Cluster Assembly (01-250 thru 01-286) for Cracks

    2. Clean the part. Refer to TASK 72-44-20-100-000 (CLEANING-000).

    3. Do the test for cracks on the part that is given below. Use the applicable penetrant inspection procedure.

      PART IDENT

      TASK/SUBTASK

      Stage 1 HPT vane cluster assembly

      (Spray)

      4. Examine the vane assembly airfoil surfaces (concave and convex sides) for axial and radial cracks, Figure.

        1. NOTE

          Example of a closed loop crack is shown at location 1 and a radial crack at location 2.

          Axial cracks that go through radial cracks when no closed loops are made or material lift-up occurs at location 3

        1. Accept

        2. Three radial cracks up to 1.200 in. (30.480 mm) in length.

        1. Accept

        3. NOTE

          Example of axial cracks are shown at locations 4 and 5.

          Any amount of axial cracks up to 1.200 in. (30.480 mm) in length between the cooling air holes at location 3.

        1. Accept

        4. Other than Step, Step and Step.

        1. Repair, VRS3141 TASK 72-44-20-300-001 (REPAIR-001).

      5. Examine the vane assembly trailing edge convex sides for cracks. Cracks are only permitted at locations 1 and 2, Figure.

        1. Cracks that extend in the convex fillet radii from the trailing edge to the rear cooling air holes or 0.500 in. (12.7 mm) maximum from the trailing edge fillets. The cracks must be tight and show no sign of burns.

        1. Accept

        2. Other than Step.

        1. Repair, VRS3141 TASK 72-44-20-300-001 (REPAIR-001).

      6. Examine the vane assembly leading edge for cracks at location 2, Figure.

        1. Cracks on each vane if each crack extends between two adjacent cooling air holes, no more than one crack on each hole and no closed loop cracks are made.

        1. Accept

        2. Other than Step.

        1. Repair, VRS3141 TASK 72-44-20-300-001 (REPAIR-001).

      7. Examine the vane assembly leading edge platform fillet area at location 1, Figure.

        1. Cracks on each vane up to 0.250 in. (6.37 mm) in length at the inner and outer platform fillets when the cracks do not go across each other, make a closed loop crack or run along the fillet parallel to the platform.

        1. Accept

        2. Other than Step.

        1. Repair, VRS3141 TASK 72-44-20-300-001 (REPAIR-001).

      8. Examine the vane assembly inner and outer platforms for cracks, Figure.

        1. No cracks at locations 1, 3 and 4.

        1. Accept

        2. NOTE

          Example of a crack is shown at location 4.

          Cracks on the vane assembly when the cracks start at the feather seal slot and extends on to the platform a maximum of 0.150 in. (3.81 mm) in length. The cracks must not go across each other, make a close loop crack and be tight with no sign of burn.

        1. Accept

        3. Other than Step or Step.

        1. Repair, VRS3141 TASK 72-44-20-300-001 (REPAIR-001).

      9. Examine the vane assembly inner and outer platform welds for cracks at locations 4 and 7, Figure.

        1. If the crack is less than one-half the weld joint and is contained in the welds.

        1. Accept

        2. Other than Step.

        1. Reject

      10. Examine the vane assembly insert and impingement covers for cracks at locations 1, 2, 3, 5, 6 and 8, Figure.

        1. Cracks

          1. Cracks

          1. Reject

          2. Cracks in the outer diameter platform insert weld if the cracks are only in the weld.

          1. Accept

          3. Other than Step and Step.

          1. Repair, VRS3152 TASK 72-44-20-300-005 (REPAIR-005).

      11. Examine the vane assembly for cracks in the feather seal slot plug welds at locations 1, 2 and 3, Figure.

        1. Cracks.

          1. Any amount when the cracks do not go out of the weld and make no closed loop cracks.

          1. Accept

          2. Other than Step.

          1. Repair, VRS3141 TASK 72-44-20-300-001 (REPAIR-001).

    2. SUBTASK 72-44-20-220-051 Examine the Stage 1 HPT Vane Cluster Assembly (01-250 thru 01-286) Airfoils and Platforms

    1. Refer to Figure.

      2. Examine the vane assembly at locations 3, 7 and 11 for burn-through or material that is not there on the airfoils and platforms.

        1. Burn-through and material that is not there.

        1. Reject

      3. Examine the vane assembly at location 11 for chipped coating on the airfoil.

        1. Chipped coating

        1. Repair, VRS3165 TASK 72-44-20-300-007 (REPAIR-007).

      4. Examine the vane assembly at locations 4, 10 and 11 for burns and erosion on the airfoil, leading and trailing edges.

        1. Burns and erosion.

          1. NOTE

            To find if the base metal is shown, use the heat tint inspection in Step.

            Base metal does not show.

          1. Accept

          2. Other than Step.

          1. Repair, VRS3154 TASK 72-44-20-300-011 (REPAIR-011).

      5. Examine the vane assembly at locations 3 and 7 for burns and erosion on the inner and outer platforms.

        1. Burns and erosion.

        1. Repair, VRS3154 TASK 72-44-20-300-011 (REPAIR-011).

      6. Examine the vane assembly for dents and nicks on the airfoils, platforms, leading and trailing edges.

        1. Nicks at locations 3, 4, 7, 10 and 11.

        1. Repair, VRS3154 TASK 72-44-20-300-011 (REPAIR-011).

        2. Dents

          1. NOTE

            To find if the base metal is shown, use the heat tint inspection in Step.

            Dents with a rounded bottom up to 0.010 in. (0.254 mm) in depth and no base metal is shown at locations 3, 4, 7, 10 and 11. The dent must not block a cooling air hole by more than 50 percent.

          1. Accept

          2. Other than Step.

          1. Repair, VRS3154 TASK 72-44-20-300-011 (REPAIR-011).

    3. SUBTASK 72-44-20-220-052 Examine the Stage 1 HPT Vane Cluster Assembly (01-250 thru 01-286) Airfoils and Platforms Cooling Air Holes/Slots for Plugging

    1. Refer to Figure.

      2. Examine the vane assembly airfoils at location 10 (each side, all around), cooling air holes and the trailing edge at location 1 cooling air slots for plugging.

        1. Plugging

        1. Repair, VRS3145 TASK 72-44-20-300-013 (REPAIR-013) and VRS3498 TASK 72-44-20-300-021 (REPAIR-021).

      3. Examine the vane assembly platforms cooling air holes for plugging at locations 6 and 9. Do not examine the holes at locations 2, 3, 4, 5, 7 and 8.

        1. Plugging.

          1. Each hole must be a minimum of 0.013 in. (0.33 mm) in diameter.

          1. Accept

          2. Other than Step.

          1. Repair, VRS3145 TASK 72-44-20-300-013 (REPAIR-013)

    4. SUBTASK 72-44-20-220-053 Examine the Stage 1 HPT Vane Cluster Assembly (01-250 thru 01-286) for Unwanted Material and Plugging on the Front and Rear Inserts and Platform Impingement Covers

    1. Refer to Figure.

      2. Examine the vane assembly for unwanted material and plugged cooling air holes on all the inserts and impingement covers at locations 1, 2, 3, 5, 6 and 8.

        1. Plugging and unwanted material.

        1. Repairs, VRS3152 TASK 72-44-20-300-005 (REPAIR-005) and VRS3153 TASK 72-44-20-300-014 (REPAIR-014).

    5. SUBTASK 72-44-20-220-054 Examine the Stage 1 HPT Vane Cluster Assembly (01-250 thru 01-286) for Chipped Coating on the Platforms

    1. Refer to Figure.

      2. Examine the vane assembly platforms for chipped coating.

        1. Chipped coating in areas A, B and C on the two inner and outer platforms.

        1. Accept

        2. Other than Step.

        1. Repairs, VRS3164 TASK 72-44-20-300-015 (REPAIR-015) and VRS3141 TASK 72-44-20-300-015 (REPAIR-001).

    6. SUBTASK 72-44-20-220-055 Examine the Stage 1 HPT Vane Cluster Assembly (01-250 thru 01-286) for Local Damage on the Trailing Edge

    1. Refer to Figure.

      2. Examine the vane assembly at location 4 for local damage on the trailing edge.

        1. Damage

          1. Bowed for three slots 0.300 in. (7.62 mm) in length at one position at location 3 and up to 0.020 in. (0.508 mm) out of plane at location 2 in a local area.

          1. Accept

          2. Other than Step

          1. Reject

    7. SUBTASK 72-44-20-220-056 Examine the Stage 1 HPT Vane Cluster Assembly (01-250 thru 01-286) for Wear and Chipped Plasma Spray Coat on the Rear Foot

    1. Refer to Figure.

      2. Examine the vane assembly at location 1 for wear and chipped plasma spray coat.

        1. Wear

          1. NOTE

            To find if the base metal is shown, use the heat tint inspection if Step.

            Base metal does not show.

          1. Accept

          2. Other than Step.

          1. Reject

        2. Chipped coat

        1. Reject

    8. SUBTASK 72-44-20-220-057 Examine the Stage 1 HPT Vane Cluster Assembly (01-250 thru 01-286) for the Outer Diameter Rear Foot Thickness

    1. Refer to Figure.

      2. Examine the vane assembly at location 2002 for thickness of the outer diameter rear foot.

        1. Thickness

          1. If the dimension is between 0.192 and 0.198 in. (4.877 and 5.029 mm).

          1. Accept

          2. Other than Step.

          1. Repair, VRS3158 TASK 72-44-20-300-018 (REPAIR-018).

    9. SUBTASK 72-44-20-220-058 Examine the Stage 1 HPT Vane Assembly (01-250 thru 01-286) for the Axial Dimension between the Inner Diameter Platform Leading Edge and the Front Edge of the Inner Diameter Rear Foot

    1. Refer to Figure.

      2. Examine the vane assembly at location 2004 for axial dimension.

        1. Axial dimension.

          1. If the dimension is between 0.837 and 0.857 in. (21.26 and 21.77 mm).

          1. Accept

          2. Other than Step.

          1. Reject

    10. SUBTASK 72-44-20-220-059 Examine the Stage 1 HPT Vane Assembly (01-250 thru 01-286) for the Wear on the Platform Front Faces and Two Sides on the Rear Inner Diameter Flange Surfaces

    1. Refer to Figure.

      2. Examine the vane assembly at locations 1 and 2 and two sides at location 3 for wear on the contact surface.

        1. Wear

          1. Fretting and rub up to 0.015 in. (0.381 mm) in depth.

          1. Accept

          2. Other than Step.

          1. Reject

    11. SUBTASK 72-44-20-220-060 Examine the Stage 1 HPT Vane Cluster Assembly (01-250 thru 01-286) for Burned Areas and Unwanted Material on all the Feather Seal Slots

    1. Refer to Figure.

      2. Examine the vane assembly at locations 4 and 5 (two ends) for burned areas and unwanted material in the feather seal slots.

        1. Burned areas and unwanted material.

        1. Reject

    12. SUBTASK 72-44-20-280-051 Examine the Stage 1 HPT Vane Cluster Assembly (01-250 thru 01-286) Vane Coat by Heat Tint

    1. Moderately clean the vane cluster by the SPM TASK 70-11-03-300-503 or vapor degrease the vane cluster by the SPM TASK 70-11-01-300-503.

    2. Mask the inner and outer platform ceramic coated areas. Use CoMat 02-029 MASKING TAPE (CLOTH BACKING) or CoMat 02-030 MASKING TAPE (CLOTH BACKING).

    3. CAUTION

      DO NOT DRY BLAST THE VANE CLUSTER COATED AREA TOO MUCH. THIS CAUSES THE COATING TO BE REMOVED.

      Clean the vane cluster airfoils by the SPM TASK 70-12-09-120-501.

    4. Remove the masking tape from the inner and outer platforms.

      5. WARNING

        WEAR PROTECTIVE CLOTHES. HEAT CAN CAUSE INJURY TO THE PERSON.

        CAUTION

        DO NOT PERMIT FINGERPRINTS OR CONTAMINATION OF ANY TYPE ON THE VANE CLUSTER. THIS WILL CAUSE AN INCORRECT HEAT TINT EXAMINATION.

        Put the vane cluster in an oven for the coating heat tint inspection.

      1. Heat tint the vane cluster in an oven (air furnace) for one hour between 1050 and 1100 deg F (566 and 593 deg C).

      2. Remove the vane cluster from the oven.

      6. Examine the vane cluster airfoils coating for heat tint.

        1. NOTE

          Heat tint does not show the thickness of the coating. The vane cluster can be repaired by Repair, VRS3141 TASK 72-44-20-300-001 (REPAIR-001) if the vane cluster will be installed in an engine for an extended length of time.

          Heat tint.

          1. Light gold color shows the vane has coating.

          1. Accept

          2. Dark gold color shows a diffusion area where the coating is thin.

          1. Accept

          3. Blue color that is not shiny shows the vane has no coating.

          1. Repair, VRS3141 TASK 72-44-20-300-001 (REPAIR-001).

    13. SUBTASK 72-44-20-280-052 Examine the Stage 1 HPT Vane Cluster Assembly (01-250 thru 01-286) by the Airflow Check

    1. NOTE

      Do all the inspections and repairs on the vane cluster before you do the airflow check.

      Refer to Figure and Figure.

    2. Do the airflow procedure for the stage 1 HPT vane cluster assembly by the procedures given in the SPM TASK 70-72-01-720-501.

    3. Refer to Figure or the specific tools and Figure or the airflow limits.

    14. SUBTASK 72-44-20-220-071 Examine the Stage 1 HPT Vane Cluster Assembly (01-250 thru 01-286) to Measure the Vane Class by the Area Method

      1. Measure the vane class by the area method. Use the IAE 2P16342 Digital indicator 1 off, IAE 2P16343 Computer kit 1 off, IAE 2P16344 Computer program 1 off, IAE 2P16234 Gage 1 off and IAE 2P16235 Master 1 off (tool instructions are included in each tool).

        1. If the numerical class average has increased 0.64 class or less.

        1. Accept

        2. If the numerical class average has increased more than 0.64 class, identify the vane to the next vane class number. Use the vibration peen method. Refer to the SPM TASK 70-09-00-400-501.

    15. Figure: Stage 1 HPT Vane Cluster Assembly Axial and Radial Cracks Inspection Locations

    Stage 1 HPT Vane Cluster Assembly Axial and Radial Cracks Inspection Locations

    Figure: Stage 1 HPT Vane Cluster Assembly Trailing Edge Cracks (Convex Side) Inspection Locations

    Stage 1 HPT Vane Cluster Assembly Trailing Edge Cracks (Convex Side) Inspection Locations

    Figure: Stage 1 HPT Vane Cluster Assembly Leading Edge Cracks Inspection Locations

    Stage 1 HPT Vane Cluster Assembly Leading Edge Cracks Inspection Locations

    Figure: Stage 1 HPT Vane Cluster Assembly Inner and Outer Platform Cracks Inspection Location

    Stage 1 HPT Vane Cluster Assembly Inner and Outer Platform Cracks Inspection Location

    Figure: Stage 1 HPT Vane Cluster Assembly Platforms, Inserts and Impingement Cover Cracks Inspection Location

    Stage 1 HPT Vane Cluster Assembly Platforms, Inserts and Impingement Cover Cracks Inspection Location

    Figure: Stage 1 HPT Vane Cluster Assembly Feather Seal Slot Plug Welds Inspection Location

    Stage 1 HPT Vane Cluster Assembly Feather Seal Slot Plug Welds Inspection Location

    Figure: Stage 1 HPT vVane Cluster Assembly Inspection Locations

    Stage 1 HPT vVane Cluster Assembly Inspection Locations

    Figure: Stage 1 HPT Vane Cluster Assembly Cooling Air Holes Inspection Locations

    Stage 1 HPT Vane Cluster Assembly Cooling Air Holes Inspection Locations

    Figure: Stage 1 HPT Vane Cluster Assembly Platform Coating Inspection Locations

    Stage 1 HPT Vane Cluster Assembly Platform Coating Inspection Locations

    Figure: Stage 1 HPT vane cluster assembly inspection locations

    Stage 1 HPT vane cluster assembly inspection locations

    Figure: Stage 1 HPT Vane Cluster Assembly Inspection Locations

    Stage 1 HPT Vane Cluster Assembly Inspection Locations

    Figure: Stage 1 HPT Vane Cluster Assembly Airflow Limits Table

    Sheet 1

    Legend
    Stage 1 HPT Vane Cluster Assembly Airflow Limits Table

    Sheet 1

    Close

    Figure: Stage 1 HPT Vane Cluster Assembly Airflow Limits Table

    Sheet 2

    Legend
    Stage 1 HPT Vane Cluster Assembly Airflow Limits Table

    Sheet 2

    Close

    Figure: Stage 1 HPT Vane Cluster Assembly Airflow Check Tools

    Stage 1 HPT Vane Cluster Assembly Airflow Check Tools

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Revised format. (editorial change)

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:IE479
Enterprise Name:DELETED,SEE CAGE CODE 4L0S0
BU Name:DELETED,SEE CAGE CODE 4L0S0
Manufacturer Code:LOCAL
Enterprise Name:LOCALLY SUPPLIED
Manufacturer Code:0AM53
Supply Number:CoMat 02-029
Type:sp01
Supply Short Name:CoMat 02-029 MASKING TAPE (CLOTH BACKING)
Supply Name:CoMat 02-029 MASKING TAPE (CLOTH BACKING)
Suppliers:
ManufacturerRemarks
0AM53
Manufacturer Code:IE479
Supply Number:CoMat 02-030
Type:sp01
Supply Short Name:CoMat 02-030 MASKING TAPE (CLOTH BACKING)
Supply Name:CoMat 02-030 MASKING TAPE (CLOTH BACKING)
Specification Groups:
Doc NumberType
PMC 4001SHURTAPE PC-622
Suppliers:
ManufacturerRemarks
IE479
Manufacturer Code:0AM53
Tool Number:IAE 2P16081
Tool Name:IAE 2P16081 Airflow fixture
Manufacturer Code:0AM53
Tool Number:IAE 2P16085
Tool Name:IAE 2P16085 Airflow master
Manufacturer Code:0AM53
Tool Number:IAE 2P16156
Tool Name:IAE 2P16156 Airflow insert set
Manufacturer Code:0AM53
Tool Number:IAE 2P16157
Tool Name:IAE 2P16157 Airflow insert set (Optional)
Manufacturer Code:0AM53
Tool Number:IAE 2P16234
Tool Name:IAE 2P16234 Gage
Manufacturer Code:0AM53
Tool Number:IAE 2P16235
Tool Name:IAE 2P16235 Master
Manufacturer Code:0AM53
Tool Number:IAE 2P16342
Tool Name:IAE 2P16342 Digital indicator
Manufacturer Code:0AM53
Tool Number:IAE 2P16343
Tool Name:IAE 2P16343 Computer kit
Manufacturer Code:0AM53
Tool Number:IAE 2P16344
Tool Name:IAE 2P16344 Computer program
Manufacturer Code:LOCAL
Tool Number:Oven
Tool Name:Oven