TASK 72-45-32-200-001-B00 HPT Stage 2 Blade - Examine, Inspection-001

DMC:V2500-A0-72-45-3201-00B-300A-C|Issue No:008.00|Issue Date:2021-08-01

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 72-45-32-200-001-B00 HPT Stage 2 Blade - Examine, Inspection-001

Effectivity

FIG/ITEM

PART NO.

01-010

2A2202

01-010

2A2202-001

01-010

2A2202-002

01-010

2A2202-003

01-010

2A2702

01-010

2A2702-001

01-010

2A8702

01-010

2A9002

01-010

2A4722

General

This TASK gives the procedure for the inspection of the stage 2 HPT blade assembly. For the other stage 2 HPT blade assembly parts, refer to TASK 72-45-32-200-000 (INSPECTION-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 SPM TASK 70-20-00-200-501.

All the parts must be cleaned before any part is examined. Refer to 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 72-45-32-230-053-001. Do the test for cracks only if the visual examination of the blade is unsatisfactory.

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 is 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 SPM.

References

Refer to SPM for data on these items.

Definitions of Damage, SPM TASK 70-02-02-350-501.

Metal Temperature Analysis (Nickel Base Alloys) SPM TASK 70-02-03-220-501.

Aqueous Cleaning, SPM TASK 70-11-03-300-503.

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

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

Fluorescent Penetrant Inspection, SPM TASK 70-23-08-230-501.

Shot peening, SPM TASK 70-38-13-380-501.

Airflow - Turbine Blades and Vanes, SPM TASK 70-72-01-720-501.

Inspection of Parts, SPM TASK 70-20-01-200-501.

Precipitation Heat Treatment of Nickel Castings, SPM TASK 70-37-27-370-501.

Magnetic Permeability Inspection, SPM TASK 70-22-06-220-501.

Some data on these items is contained in this TASK. For more data on these items refer to SPM.

Method of Testing for Crack Indications.

Chemical Processes.

Surface Protection.

NOTE

To identify consumable materials refer to 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
Magnetoscope(R) Meter, Model 1.069 or equivalent, Model 1.067, or 1.068LOCALMagnetoscop(R), Meter, Model 1.069 or equivalent, Model 1.067, or 1.068

Manufacturer: Institute Dr. Foerster GmbH und Co, KM Im Laisen 70, D-72766, Reutlingen, Germany

Permeability ProbeLOCAL1.069.01-3001
Adapter, ProbeLOCAL9064001

Reference Standard PN 1.067-101-12 Manufacturer: Foerster Instruments Inc., RIDC Park West, 140 Industry Drive, Pittsburgh, PA 15275 USA or equivalent

IAE 2P16101 Airflow base0AM53IAE 2P16101
IAE 2P16113 Airflow fixture0AM53IAE 2P16113
IAE 2P16119 Airflow insert0AM53IAE 2P16119
IAE 2P16359 Blade length gage0AM53IAE 2P16359
IAE 2P16411 Airflow master0AM53IAE 2P16411
IAE 2P16508 Reference card0AM53IAE 2P16508

Consumables, Materials and Expendables

NameManufacturerPart Number / IdentificationQuantityRemark
CoMat 02-081 PENCIL - METAL MARKING(HARD)86874CoMat 02-081
CoMat 03-010 ARGON GAS0B434CoMat 03-010
CoMat 05-029 CAST STEEL SHOT, S11055807CoMat 05-029
CoMat 05-032 CAST STEEL SHOT, S17055807CoMat 05-032
CoMat 05-138 SHOT, CAST STEEL, S11055807CoMat 05-138
CoMat 05-176 CAST STEEL SHOT, S17055807CoMat 05-176
CoMat 05-177 CUT WIRE SHOT,CW-140FUN2CoMat 05-177
CoMat 05-178 CUT WIRE SHOT, CW-200FUN2CoMat 05-178
CoMat 05-187 STAINLESS STEEL CUT WIRE SHOT, SCW-200FUN2CoMat 05-187
CoMat 05-188 STAINLESS STEEL CUT WIRE SHOT, SPECIAL CONDITIONED, SCW-200FUN2CoMat 05-188
CoMat 05-234 CAST STEEL SHOT, HIGH HARDNESS, S11055807CoMat 05-234
CoMat 06-120 METAL MARKING PENCIL (HARD)86874CoMat 06-120

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-45-32-220-110 Do a Permeability Inspection of the Stage 2 HPT blade Assembly Internal Airfoil Surfaces

      CAUTION

      DO NOT CLEAN THE INTERNAL CAVITIES OF THE ENGINE RUN BLADES BEFORE YOU DO THIS INSPECTION.

    1. Refer to Figure, Figure and Figure.

      NOTE

      It is permitted to clean the external blade surfaces by the SPM TASK 70-11-03-300-503 or SPM TASK 70-12-09-120-501 before you do this inspection.

    2. You can use this procedure on blades that are not installed in the rotor and are not cleaned internally.

      3. Do a permeability inspection by SPM TASK 70-22-06-220-501.

      1. Refer to Figure for blade inspection area and Figure for inspection path.

      2. Examine Area 1 with the permeability probe in a radial orientation. Refer to Figure.

      3. Examine Area 2 with the permeability probe in an axial orientation. Refer to Figure.

        4. If you use FOERSTER Magnetoscope Model 1.069:

          1. Accept blades with a permeability value of:

          1. 1.034 in. (26.264 mm) or less in Area 1.

          2. 1.024 in. (26.010 mm) or less in Area 2.

          2. Repair by Repair, VRS3440 TASK 72-45-32-300-013 (REPAIR-013), Repair, VRS3602 TASK 72-45-32-300-021 (REPAIR-021), or Repair, VRS3838 TASK 72-45-32-300-033 (REPAIR-033) as applicable, if blades have a permeability value of:

          1. More than 1.034 in. (26.264 mm) in Area 1.

          2. More than 1.024 in. (26.010 mm) in Area 2.

        5. If you use FOERSTER Magnetoscope Model 1.070:

          1. Accept blades with a permeability value of:

          1. 1.0170 in. (25.8318 mm) or less in Area 1.

          2. 1.0120 in. (25.7048 mm) or less in Area 2.

          2. Repair by Repair, VRS3440 TASK 72-45-32-300-013 (REPAIR-013), Repair, VRS3602 TASK 72-45-32-300-021 (REPAIR-021), or Repair, VRS3838 TASK 72-45-32-300-033 (REPAIR-033) as applicable, if blades have a permeability value of:

          1. More than 1.0170 in. (25.8318 mm) in Area 1.

          2. More than 1.0120 in. (25.7048 mm) in Area 2.

    2. SUBTASK 72-45-32-220-071 Examine the Stage 2 HPT Blade Assembly (01-010) Blade Platform Area

      NOTE

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

    1. Refer to Figure.

      2. Examine the blade platform area for corrosion and burned areas.

        1. If the base metal is not shown and there is no damage to the coating.

        1. Accept.

        2. Other than Step.

        1. Repairs, VRS3496 TASK 72-45-32-300-010 (REPAIR-010) or VRS3440 TASK 72-45-32-300-013 (REPAIR-013) or VRS3602 TASK 72-45-32-300-021 (REPAIR-021) or VRS3838 TASK 72-45-32-300-033 (REPAIR-033).

      3. Examine the blade platform area for cracks, nicks and chipped coating. Use a white light and 10X magnification to examine for cracks.

        1. Any amount of cracks, nicks and chipped coating all around location 3.

        1. Accept.

          NOTE

          The knife edge is not included in location 3.

        2. Cracks at the knife edge location 1.

        1. Repairs, VRS3496 TASK 72-45-32-300-010 (REPAIR-010) or VRS3440 TASK 72-45-32-300-013 (REPAIR-013) or VRS3602 TASK 72-45-32-300-021 (REPAIR-021) or VRS3838 TASK 72-45-32-300-033 (REPAIR-033).

        3. Cracks, nicks and chipped coating at location 2.

        1. Repairs, VRS3496 TASK 72-45-32-300-010 (REPAIR-010) or VRS3440 TASK 72-45-32-300-013 (REPAIR-013) or VRS3602 TASK 72-45-32-300-021 (REPAIR-021) or VRS3838 TASK 72-45-32-300-033 (REPAIR-033).

        4. Cracks in the airfoil/platform fillet.

        1. Reject.

      4. Examine the blade platform area for dents at locations 2 and 3.

        1. Two dents up to 0.150 in. (3.81 mm) in diameter and there is no base metal shown. There must be a minimum relation between length and depth of 10 to 1.

        1. Accept.

        2. Other than Step.

        1. Repairs, VRS3496 TASK 72-45-32-300-010 (REPAIR-010) or VRS3340 TASK 72-45-32-300-013 (REPAIR-013) or VRS3602 TASK 72-45-32-300-021 (REPAIR-021) or VRS3838 TASK 72-45-32-300-033 (REPAIR-033).

        3. Dents in the airfoil/platform radius.

        1. Reject.

      5. Examine the blade underplatform as follows:

        1. Meet the limits given in repair, VRS3517 TASK 72-45-32-300-015 (REPAIR-015) or VRS3837 TASK 72-45-32-300-032 (REPAIR-032).

        1. Repair, VRS3582 TASK 72-45-32-300-023 (REPAIR-023) or VRS3839 TASK 72-45-32-300-031 (REPAIR-031).

        2. Other than Step.

        1. Reject.

    3. SUBTASK 72-45-32-220-072 Examine the Stage 2 HPT Blade Assembly (01-010) Airfoil

    1. Refer to Figure and Figure.

      NOTE

      1. It is permitted to have not more than three casting holes for each side on the HPT Stage 2 blade airfoil (also referred to as chaplet holes). This is a maximum of six casting holes for each blade, if there were no more than three holes each side. These holes are typically located out near the tip on the concave and convex side of the airfoil and are less than 0.030 in. (0.76 mm) in diameter. The blade is required to have passed an airflow check and magnetoscope inspection.

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

      2. Examine the blade airfoil surfaces at locations 1 and 2, for burned areas, corrosion and erosion, Figure.

        1. If the base metal is not shown and there is no damage to the coating.

        1. Accept.

        2. Other than Step.

        1. Repairs, VRS3496 TASK 72-45-32-300-010 (REPAIR-010), VRS3440 TASK 72-45-32-300-013 (REPAIR-013) or VRS3602 TASK 72-45-32-300-021 (REPAIR-021) or VRS3838 TASK 72-45-32-300-033 (REPAIR-033).

      3. Examine the blade airfoil surfaces at locations 1 and 2, for chipped and nicked coating.

        1. Chipped and nicked coating.

        1. Repairs, VRS3496 TASK 72-45-32-300-010 (REPAIR-010), VRS3440 TASK 72-45-32-300-013 (REPAIR-013) or VRS3602 TASK 72-45-32-300-021 (REPAIR-021) or VRS3838 TASK 72-45-32-300-033 (REPAIR-033).

          NOTE

          Refer to Step for cracks on the trailing edge.

      4. Examine the blade airfoil surfaces at location 1, for cracks. Use a white light and 10X magnification.

        1. Cracks.

        1. Repairs, VRS3496 TASK 72-45-32-300-010 (REPAIR-010), VRS3440 TASK 72-45-32-300-013 (REPAIR-013) or VRS3602 TASK 72-45-32-300-021 (REPAIR-021) or VRS3838 TASK 72-45-32-300-033 (REPAIR-033).

      5. Examine the blade airfoil surfaces for dents and nicks, Figure.

        1. The acceptable limits for each dent on the blade are as follows unless otherwise stated in to Step to Step.

        1. Not more than a depth of 0.005 in. (0.13 mm).

        2. There is no base metal shown.

        3. There is a smooth bottom.

        4. There are no cracks or damage to the coating.

        5. The minimum relation between length and depth is 10 to 1.

        2. The acceptable dent limits at Location 2 (mid-chord) is as follows.

          1. Two dents on each side of the concave and convex airfoil surfaces.

          1. Accept.

        3. The acceptable dent limits at Location 3 (aft-chord) is as follows.

          1. For PN's 2A9002 and 2A4722 only.

            1. Two dents on the convex airfoil surfaces, but at a location that is not less than 0.400 in. (10.16 mm) from the blade's platform as noted by Index 5.

              1. Accept if the following conditions are met.

                1. Dents not more than a diameter of 0.100 in. (2.54 mm).

                1. Dents must be separated a minimum of 0.100 in. (2.54 mm).

            2. Five dents on the concave airfoil surfaces, but at a location that is not less than 0.400 in. (10.16 mm) from the blade's platform as noted by Index 5.

              1. Accept if the following conditions are met.

              1. Dents not more than a diameter of 0.100 in. (2.54 mm).

              2. Dents must be separated a minimum of 0.100 in. (2.54 mm).

          2. For all other PN's.

            1. Two dents on each side of the concave and convex airfoil surfaces.

            1. Accept.

        4. The acceptable dent limits at Location 1 (leading edge) is as follows.

          1. Any amount of dents on the leading edge, but at a location that is not less than 0.100 in. (2.54 mm) from the blade's platform as noted by Index 6.

          1. Accept.

        5. Other than Step to Step.

        1. Repairs, VRS3496 TASK 72-45-32-300-010 (REPAIR-010), VRS3440 TASK 72-45-32-300-013 (REPAIR-013) or VRS3602 TASK 72-45-32-300-021 (REPAIR-021) or VRS3838 TASK 72-45-32-300-033 (REPAIR-033).

    4. SUBTASK 72-45-32-220-073 Examine the Stage 2 HPT Blade Assembly (01-010) Abrasive Tip

    1. Refer to Figure.

      NOTE

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

      2. Examine the blade tip to see if the base metal is shown

        1. If there is base metal shown on the base metal/tip interface at location 2.

        1. Repairs, VRS3496 TASK 72-45-32-300-010 (REPAIR-010) or VRS3516 TASK 72-45-32-300-014 (REPAIR-014) or VRS3836 TASK 72-45-32-300-030 (REPAIR-030).

          NOTE

          The base metal/tip interface is shown at location 6.

        2. If there is base metal shown on the base metal/tip interface at locations 1 and 3.

        1. Accept

        3. One or more chips at Location 2 where the sum of all the chip widths is a maximum of 0.200 in. (5.08 mm) in width and there is no base metal shown on the base metal/tip interface at location 6.

        1. Accept

          NOTE

          Example of a chip is shown at location 5.

        4. Other than Step.

        1. Repairs, VRS3496 TASK 72-45-32-300-010 (REPAIR-010) or VRS3516 TASK 72-45-32-300-014 (REPAIR-014) or VRS3836 TASK 72-45-32-300-030 (REPAIR-030).

      3. Examine the blade abrasive tip for taper on the trailing edge at location 4.

        1. The trailing edge is tapered 0.200 in. (5.08 mm) radially by 0.020 in. (0.51 mm) axially

        1. Accept.

        2. Other than Step.

        1. Repairs, VRS3496 TASK 72-45-32-300-010 (REPAIR-010) or VRS3516 TASK 72-45-32-300-014 (REPAIR-014) or VRS3836 TASK 72-45-32-300-030 (REPAIR-030).

    5. SUBTASK 72-45-32-220-074 Examine the Stage 2 HPT Blade Assembly (01-010) Blade Length

      1. Examine the blade assembly for the blade length dimension.

      1. Install the blade assembly into the IAE 2P16359 Blade length gage 1 off.

      2. Position the three pins of the gage on the blade tip

      3. Zero the dial indicator against the end surface of the gage.

        4. Measure the dimension for the distance from the end surface of the gage to the surface of the middle pin.

          1. If the dimension is 0.010 in. (0.254 mm) or less

          1. Accept

          2. Other than Step.

          1. Repairs, VRS3496 TASK 72-45-32-300-010 (REPAIR-010) or VRS3516 TASK 72-45-32-300-014 (REPAIR-014) or VRS3836 TASK 72-45-32-300-030 (REPAIR-030).

            NOTE

            A suspect engine has a set of blades which has any blades with negative stretch readings (less than minus 0.005 in. (minus 0.127 mm) or positive stretch readings that are more than three times the average of the entire set.

      2. Examine the blades for incorrect marking.

      1. Do the procedure in Step below if you think a blade has incorrect markings.

    6. SUBTASK 72-45-32-220-092 Examine the Stage 2 HPT Blade Assembly (01-010) Blade Length

    1. Refer to Figure.

      2. Find the measured length of the blade by the procedure given in Step. Use Z-plane and the growth measurement hole.

      1. Make a note of airfoil thinning.

        2. Make a record of three-decimal place results as follows:

        1. 3.657 in. would be read 657.

      3. Subtract the initial marked length from the last three digits of the measured length values you found in the step above to calculate the growth of individual blades.

      4. Find which blades are suspect.

      3. Find the quantity of suspect readings.

        1. If fewer than 75 percent of the blades in the set are suspect, do the steps that follow:

        1. Calculate the average growth of the non-suspect blades only (a minimum of 10 parts). Do not include negative stretch readings into this average.

          2. If the number of non-suspect blades is 10 or less, do the steps that follow:

          1. Measure the dimension from the edge of the second trailing edge slot in from the tip to the edge of the second trailing edge slot in from the platform as shown in the figure.

          2. Use a locally fabricated blade master tool and dial caliper to check the calibrated standard reading marked on the master and find the correct measurement location within the trailing edge slots.

          3. Make a record of the three-digit number from the caliper to make a record of the measurement for all suspect blades.

          4. Find the average for the suspect blades only, in thousandths of an inch.

          5. Use the master blade every 10 measurements to check the measurement technique.

          6. Subtract 0.041 in. (1.04 mm) from the average dimension as calculated above to find the average growth of the set. Disregard average negative measured growth.

          3. If the number of non-suspect blades is more than 10, do the steps that follow:

          1. Subtract the calculated average growth of the set from the individual observed length of the suspect blades as measure in Step A.

        2. If 75 percent or more of the blades in the set are suspect, do the steps that follow:

        1. Measure the dimension from the edge of the second trailing edge slot in from the tip to the edge of the second trailing edge slot in from the platform as shown in the figure.

        2. Use a locally fabricated blade master tool and dial caliper to check the calibrated standard reading marked on the master and find the correct measurement location within the trailing edge slots.

        3. Make a record of the three-digit number from the caliper to make a record of the measurement for all suspect blades.

        4. Find the average for the suspect blades only, in thousandths of an inch.

        5. Use the master blade every 10 measurements to check the measurement technique.

        6. Subtract 0.041 in. (1.04 mm) from the average dimension as calculated above to find the average growth of the set. Disregard average negative measured growth.

      3. Make a mark on the suspect blades only, of the calculated length from the step above. Use the vibro-peen or dot-peen method. Refer to the SPM TASK 70-09-00-400-501. Make a mark in the same area as the initial mark.

    7. SUBTASK 72-45-32-220-075 Examine the Stage 2 HPT Blade Assembly (01-010) Trailing Edge

    1. Refer to Figure.

      2. Examine the blade trailing edge for cracks. Use a white light and a 10X magnification.

        1. Cracks at the trailing edge at location 3

        1. Repairs, VRS3496 TASK 72-45-32-300-010 (REPAIR-010) or VRS3602 TASK 72-45-32-300-021 (REPAIR-021) or VRS3838 TASK 72-45-32-300-033 (REPAIR-033).

          NOTE

          Example of a crack is shown at location 1.

        2. Cracks that extend from the concave surface of the cooling air slots at location 2

        1. Repair, VRS3496 TASK 72-45-32-300-010 (REPAIR-010) or Repair, VRS3602 TASK 72-45-32-300-021 (REPAIR-021) or VRS3838 TASK 72-45-32-300-033 (REPAIR-033).

          NOTE

          Example of a linear crack indication that is caused by the blade casting die separation line is shown at location 5. These are not cracks.

    3. Examine the blade trailing edge cooling air slots at location 3, for plugging.

    4. CAUTION

      WHEN YOU DO PENCIL GRIT BLAST, BE CAREFUL NOT TO ERODE THE TRAILING EDGE SLOT.

      NOTE

      Example of a cooling air slot is shown at location 4.

      Unplug with a wire probe and power flush or pencil grit blast and high pressure air blast or Repair, VRS3360 TASK 72-45-32-300-005 (REPAIR-005).

    8. SUBTASK 72-45-32-220-076 Examine the Stage 2 HPT Blade Assembly (01-010) Leading and Trailing Edge Platform

    1. Refer to Figure.

      2. Examine the trailing edge platform at location 2, for signs of rub with the LPT inner duct.

        1. Rub.

          1. Up to 25 percent of the local, total platform thickness at location 7, or up to 0.025 in. (0.635 mm) in depth, whichever is less

          1. Repair, VRS3409 TASK 72-45-32-300-006 (REPAIR-006)

            NOTE

            Rubbing must not go past the tapered area or into the fillet radius.

          2. Other than Step.

          1. Reject.

      3. Examine the blade trailing edge platform for curling at location 1.

        1. Curling.

        1. Reject.

          NOTE

          Curling on the blade platform is shown when the platform is bent in an out radial direction. It occurs when the temperature is sufficiently high to permit the platform to give under centrifugal force.

      4. Examine the blade leading edge knife edge seal for wear at location 4.

        1. Wear.

          1. Not less than 0.080 in. (2.032 mm) minimum dimension at location 4

          1. Accept.

          2. Not less than 0.050 in. (1.27 mm) minimum dimension at location 6

          1. Accept.

          3. Other than Step and Step.

          1. Reject.

    9. SUBTASK 72-45-32-220-077 Examine the Stage 2 HPT Blade Assembly (01-010) Damper Contact Area

    1. Refer to Figure.

      2. Examine the blade damper contact area for wear.

        1. Up to 0.005 in. (0.127 mm) in depth on the platform where the blade damper touches the blade at location 3

        1. Accept.

        2. Other than Step.

        1. Reject.

    10. SUBTASK 72-45-32-220-078 Examine the Stage 2 HPT Blade Assembly (01-010) Blade Root Attachment Area

    1. Refer to Figure.

      2. Examine the blade root attachment area for erosion and corrosion at Locations 1, 6, 7 and 11.

        1. Not more than 0.005 in. (0.13 mm) in depth when the surface is not rough and there are no cracks, crazing, ridges or depressions.

        1. Accept.

        2. Other than Step.

        1. Reject.

      3. Examine the blade root attachment area for erosion and corrosion at Locations 3, 4 and 10.

        1. Not more than 0.005 in. (0.13 mm) in depth when the surface is not rough and there are no cracks, crazing, ridges or depressions.

        1. Accept.

        2. Other than Step.

        1. Repairs, VRS3240 TASK 72-45-32-300-001 (REPAIR-001) or VRS3496 TASK 72-45-32-300-010 (REPAIR-010) or VRS3440 TASK 72-45-32-300-013 (REPAIR-013) or VRS3602 TASK 72-45-32-300-021 (REPAIR-021) or VRS3838 TASK 72-45-32-300-033 (REPAIR-033).

      4. Examine the blade root attachment area for fretting and galling at Locations 4, 6 and 7.

        1. Not more than 0.005 in. (0.13 mm) in depth on the load bearing tooth surface when there are no cracks or pitting.

        1. Accept.

        2. Other than (Step).

        1. Reject.

      5. Examine the blade root attachment area for pitting, nicks and cracks at Locations 1, 2, 5, 6, 7 and 11. Use a white light and a 10X magnification to examine for cracks.

        1. Nicks.

        1. Reject.

        2. Cracks at Locations 1, 2, 5, 7 and 11.

        1. Reject.

        3. Cracks at Location 6.

        1. Repair, VRS3517 TASK 72-45-32-300-015 (REPAIR-015) or VRS3837 TASK 72-45-32-300-032 (REPAIR-032).

        4. Pitting at Locations 2, 6, and 7.

        1. Not more than 0.003 in. (0.076 mm) in depth at Location 6 and 7.

        2. Not more than 0.010 in. (0.254 mm) in depth at Location 2.

          3. Other that Step and Step.

          1. Reject.

        5. Pitting at location 1.

        1. Repairs, VRS3517 TASK 72-45-32-300-015 (REPAIR-015) or VRS3837 TASK 72-45-32-300-032 (REPAIR-032).

          2. Pitting at Locations 5 and 11.

          1. Reject.

      6. Examine the blade root attachment area for contact wear that is not equal (tooth to tooth and side to side) at Locations 6 and 7.

        1. Contact wear on the blade root that is not equal along the root tooth not more than 0.005 in. (0.13 mm) in depth when there are no cracks or pitting.

        1. Accept.

        2. Other than (Step).

        1. Reject.

          NOTE

          Contact wear that is local and not equal along the blade root tooth can look like bright (bare) spots on the surface.

      7. Examine the blade root face for previous repair code markings.

        1. Previous repair code markings located less than 0.050 in. (1.27 mm) from edge of blade root face.

        1. Reject.

        2. Parts not rejected by Step, examine the blade root face for cracks. Fluorescent Penetrant Inspection (FPI) under black light, examine by white light with a minimum of 10X magnification to verify that there are no cracks.

          1. Any cracks found present.

          1. Reject.

          2. No cracks found.

          1. Accept.

    11. SUBTASK 72-45-32-220-079 Examine the Stage 2 HPT Blade Assembly (01-010) Root Area

    1. Refer to Figure and Figure.

      2. Examine the blade root area for nicks and cracks at Locations 3, 4 and 10. Use a white light and a 10X magnification to examine for cracks.

        1. Cracks or nicks.

        1. Repairs, VRS3240 TASK 72-45-32-300-001 (REPAIR-001) or VRS3496 TASK 72-45-32-300-010 (REPAIR-010) or VRS3440 TASK 72-45-32-300-013 (REPAIR-013) or VRS3602 TASK 72-45-32-300-021 (REPAIR-021) or VRS3838 TASK 72-45-32-300-033 (REPAIR-033).

        2. Cracks at the bottom root cooling slot.

        1. Do a fluorescent penetrant inspection, Step.

      3. Examine the blade root area for pitting at Locations 3, 4, 8, 9 and 10.

        1. Pitting at Locations 3 and 4.

          1. Not more than 0.005 in. (0.13 mm).

          1. Accept.

          2. Other than Step.

          1. Reject.

        2. Pitting at Location 10.

          1. Not more than 0.010 in. (0.25 mm).

          1. Accept.

          2. Other than Step.

          1. Reject.

        3. Pitting at Location 8.

          1. For all part numbers except 2A4722, not more than 0.010 in. (0.254 mm) at Location 8. Refer to Figure.

          1. Repair, VRS3582 TASK 72-45-32-300-023 (REPAIR-023).

          2. For part number 2A4722, not more than 0.005 in. (0.127 mm) at Location 8. Refer to Figure.

          1. Repair, VRS3839 TASK 72-45-32-300-031 (REPAIR-031).

        4. Pitting at Location 9.

          1. For PN 2A4722, not more than 0.003 in. (0.076 mm) at Location 9. Refer to Figure.

          1. Repair by TASK 72-45-32-300-031 (REPAIR-031).

      4. Examine the blade root area for blends and dents.

        1. Not more than 0.005 in. (0.13 mm) with rounded edges, corners and bottoms at Locations 1, 6 and 7. The dents have a minimum relation between length and depth of 10 to 1.

        1. Accept.

        2. Not more than 0.010 in. (0.25 mm) with rounded edges, corners and bottoms at Location 4. The dents have a minimum relation between length and depth of 10 to 1.

        1. Accept.

        3. Other than Step and Step.

        1. Repairs, VRS3240 TASK 72-45-32-300-001 (REPAIR-001) or VRS3496 TASK 72-45-32-300-010 (REPAIR-010) or VRS3440 TASK 72-45-32-300-013 (REPAIR-013) or VRS3602 TASK 72-45-32-300-021 (REPAIR-021) or VRS3838 TASK 72-45-32-300-033 (REPAIR-033).

        4. Blades which show depressed and/or raised casting imperfections on ends of seal support lug (damper pin).

        1. Accept.

    12. SUBTASK 72-45-32-220-080 Examine the Stage 2 HPT Blade Assembly (01-010) Root Metering Plate Welds

    1. Refer to Figure.

      2. Examine the blade root metering plate welds at Location 5 (four locations) for cracks.

        1. One crack on each blade.

        1. Accept.

        2. More than one crack on each blade.

        1. Repair, VRS3361 TASK 72-45-32-300-008 (REPAIR-008).

    13. SUBTASK 72-45-32-280-056 Examine the Stage 2 HPT Blade Assembly (01-010) for Overtemperature

      NOTE

      1. Blades that were at temperatures more than the limit of 2100 deg F (1149 deg C) for a short time will cause a change in the alloy microstructure of the blade.

      2. In the case of an EGT overtemperature, such that the AMM requires metallurgical analysis, the stage 2 HPT blades must be examined for overtemperature even if the stage 1 HPT blades are not rejected for overtemperature.

    1. Refer to Figure.

      2. Examine one blade assembly for overtemperature by metallurgical analysis if the engine was removed for EGT overlimit. Refer to SPM TASK 70-02-03-220-501.

        1. Cut the blade at location 1 to get the airfoil sample to be analyzed.

        1. Cut a small vee shaped groove on the airfoil sample on the cut surface at location 4.

          NOTE

          The small vee shaped groove will mark the blade airfoil sample surface to be analyzed.

        2. Cut the blade airfoil sample at Location 2.

      2. Cut out the blade root sample at Location 8.

      3. Discard the remaining blade pieces.

        4. Attach and polish the blade samples, refer to SPM TASK 70-02-03-220-501 as follows:

        1. The blade airfoil sample where the small vee groove is, shows the surface to be polished.

        2. The blade root sample where the longest cut is, shows the surfaces to be polished.

        5. Examine the microstructure of the blade samples. Refer to SPM TASK 70-02-03-220-501.

        1. Examine the blade airfoil samples for metal temperature at Locations 3, 5 and 6. The correct points to be examined under magnification must be 0.010 in. to 0.015 in. (0.254 mm to 0.381 mm) from the coating to the base metal interface.

        2. Examine the blade root sample for metal temperature at location 7. This location must be nearest to the inner diameter of the blade. the correct point to be examined under magnification must be 0.010 in. to 0.015 in. (0.254 mm to 0.381 mm) from the edge of the root sample.

        6. Reject all of the stage 2 HPT blade assemblies in the engine if the metal temperature is higher than 2050 deg F (1121 deg C) at any of the locations that follow.

          NOTE

          You can use this location to compare the hot areas of the airfoils.

        1. Leading edge analysis area at location 6.

        2. Midcord analysis area at location 5.

        3. Trailing edge analysis area at location 3.

      7. Do not examine any other area of the blade.

    3. Examine a stage 3 LPT blade from the same engine only if the stage 2 HPT blades are rejected for overtemperature.

    14. SUBTASK 72-45-32-220-052-001 Examine the Stage 2 HPT Blade (01-010) for Internal Stress Corrosion Cracks

    1. Refer to Figure.

    2. Remove the root cover plate. Refer to VRS3361 TASK 72-45-32-300-008 (REPAIR 008).

    3. Clean the internal cavities of the blade. Refer to VRS3360 TASK 72-45-32-300-005 (REPAIR 005).

      4. Do a boroscope inspection of the internal cavities of the blade per latest revision of NDIP-1147.

        1. Cracks.

        1. Reject blades and contact IAE Technical Services.

    5. Replace the root cover plate prior to completion of blade airflow inspection/check Step. Refer to VRS3361 TASK 72-45-32-300-008 (REPAIR 008).

    15. SUBTASK 72-45-32-230-053-001 Examine the Stage 2 HPT Blade (01-010) for Cracks

    1. Refer to Figure and Figure.

      NOTE

      Do this procedure only if the visual examination of the blade is unsatisfactory.

    2. Before you clean the blade, remove the root cover plate by grinding. When you remove the cover plate, make sure the grinding motion is from the concave to the convex side, or from the convex to the concave side. This will make grinding marks perpendicular to root bottom axial cracks (if they exist).

    3. Clean the part. Refer to TASK 72-45-32-100-003 (CLEANING-003, CONFIG-001).

      NOTE

      Removal of root cover plate and cleaning the blade may have been already performed per the previous step.

    4. WARNING

      IT IS THE RESPONSIBILITY OF THE OPERATOR TO OBTAIN AND OBSERVE THE MANUFACTURERS MATERIAL SAFETY DATA SHEETS FOR CONSUMABLE MATERIALS INFORMATION SUCH AS HAZARDOUS INGREDIENTS, PHYSICAL/CHEMICAL CHARACTERISTICS, FIRE, EXPLOSION, REACTIVITY, HEALTH HAZARD DATA, PRECAUTIONS FOR SAFE HANDLING, USE AND CONTROL MEASURES AND ALSO TO TAKE LOCAL REGULATION INTO CONSIDERATION.

      Heat treat the blade to open up cracks before inspection.

    5. Do the test for cracks on the part that is given below. Carefully examine the blade platform, leading edge, trailing edge and root area. Use the applicable penetrant procedure.

      PART IDENT

      TASK/SUBTASK

      Stage 2 HPT Blade

      6. Carefully examine the bottom root cooling slot. Refer to Figure.

        1. Cracks not more than 0.020 in. (0.51 mm).

        1. Accept.

        2. More than Step.

        1. Reject.

          NOTE

          Not more than two cracks are permitted for each rib, but not on the same side.

    7. If you find any crack indications, make a temporary mark on the indications with CoMat 02-081 PENCIL - METAL MARKING(HARD).

    8. Do the applicable visual and dimensional inspection procedures again on the crack indications with marks.

      9. Precipitation heat treat the blade assembly as follows:

      1. Refer to SPM TASK 70-37-27-370-501.

      2. Let the blade air cool.

    16. SUBTASK 72-45-32-280-057 Examine the Stage 2 HPT Blade Assembly (01-010) Coating by Heat Tint

    1. Moderately clean the blade assembly by SPM TASK 70-11-03-300-503.

    2. CAUTION

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

      Clean the blade assembly by SPM TASK 70-12-09-120-501.

      3. CAUTION

        DO NOT GET FINGERPRINTS OR CONTAMINATION OF ANY TYPE ON THE BLADE ASSEMBLY. THIS WILL CAUSE AN INCORRECT HEAT TINT EXAMINATION.

        Put the blade assembly in an oven for the coating heat tint inspection.

      1. Heat tint the blade assembly in an oven (air furnace) for one hour between 1050 deg F and 1100 deg F (566 deg C and 593 deg C) or for 20 to 75 minutes between 1275 deg F and 1325 deg F (691 deg C and 718 deg C).

      2. WARNING

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

        Remove the blade assembly from the oven.

      4. Examine the blade assembly coating for heat tint.

        1. Heat tint.

          1. Light gold color shows the blade has coating

          1. Accept

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

          1. Accept

            NOTE

            Heat tint does not show the thickness of the coating. The blade assembly can be repaired by the TASK listed below if the blade assembly will be installed in an engine for an extended length of time.

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

          1. Repairs, VRS3496 TASK 72-45-32-300-010 (REPAIR-010) or VRS3440 TASK 72-45-32-300-013 (REPAIR-013) or Repair, VRS3602 TASK 72-45-32-300-021 (REPAIR-021) or Repair, VRS3838 TASK 72-45-32-300-033 (REPAIR-033).

    17. SUBTASK 72-45-32-260-052 Examine the Stage 2 HPT Blade Assembly (01-010) for Internal Cracks and Unwanted Material by Radiographic Inspection)

    1. Refer to Figure, Figure and Figure.

      2. Examine the blade assembly for internal cracks and unwanted material by radiographic inspection.

      1. Do a radiographic inspection in Positions A and B by Figure and SPM TASK 70-26-01-260-501.

        NOTE

        The radiographic inspection in positions A and B may require different exposure and film speeds in order to provide adequate contrast to inspect for cracks, due to the thicker section at the root with respect to the airfoil (Refer to TASK 70-26-01-260-501, Section 7).

        NOTE

        Surface indication that are acceptable to the visual inspection are not cause to be rejected by radiographic inspection.

        2. Make an analysis on the radiographic indications.

          1. Cracks.

          1. Reject.

            NOTE

            The entire blade should be inspected for cracks with a focus inspection at the root area as shown in Figure.

          2. Unwanted material in the internal cavities.

          1. Power flush or Repair, VRS3360 TASK 72-45-32-300-005 (REPAIR-005).

            NOTE

            If there are any indications of shot peen and/or other forms of foreign material, e.g. metal chips or broken wire that are distinguishable by the their shape, form, or density, the parts must be rejected.

          2. After cleaning the internal cavities refer to VRS3360, TASK 72-45-32-300-005 (REPAIR-005), unwanted metal and material are acceptable if the size, density and location of the indication(s) have remained unchanged from Step. Refer to the limits in Figure and Figure, area (4).

          3. Unwanted material in the internal cavities at the blade tip area

          1. Power flush or Repair, VRS3360, TASK 72-45-32-300-005 (REPAIR-005)

          2. NOTE

            If there are any indications of shotpeen and/or other forms of foreign material, e.g., metal chips or broken wire that are distinguishable by their shape, form or density, the parts must be rejected.

            After cleaning the internal cavities, refer to VRS3360, TASK 72-45-32-300-005 (REPAIR-005). Unwanted metal and material are acceptable provided the size, density and location of the indication(s) have remained unchanged from Step. Refer to the limits in Figure and Table 801, area (4).

          4. Sudden changes in the wall thickness contours which are not continuous

          1. Reject

    18. SUBTASK 72-45-32-220-083 Examine the Stage 2 HPT Blade Assembly (01-010) for the Growth Measurement

      1. Examine the blade assembly for the growth measurement.

        NOTE

        The thinner airfoils can be identified when the internal shape of the blade design becomes visible. External surfaces between shapes will be damaged.

      1. Examine the blade assembly for a thinner airfoil because of radial growth.

      2. A blade assembly that shows signs of thinner airfoil must be rejected.

        3. Growth.

          1. Up to 0.010 in. (0.254 mm) in length.

          1. Accept.

          2. Other than (Step).

          1. Reject.

    19. SUBTASK 72-45-32-220-095 Examine the Stage 2 HPT Blade Assembly (01-010) for the Growth Measurement and Average Growth Calculation

    1. Refer to Figure.

      NOTE

      This procedure applies only to blades that have not previously been remarked for length.

        A blade set is considered suspect if either of the following applies:

        It is found to contain individual blades with negative measured stretch greater than minus 0.005 in. (minus 0.127 mm), (minus 0.006 in., minus 0.010 in. etc.), (minus 0.152 mm, minus 0.254 mm etc.).

        It is found to contain individual blades that are rejected by the blade stretch measurement technique presently contained in SUBTASK 72-45-32-220-083.

        Within a suspect set of blades, individual suspect blades are defined as:

        All blades within the set that are found with any negative stretch.

        All blades within the set that are found with positive stretch greater than 0.010 in. (0.254 mm).

        All blades within the set that are found with more than 3 times the average stretch of the non-suspect blades in the set.

    2. Determine measured length of individual blade by Step. Make note of airfoil thinning inspection. Record three-decimal place results as directed (example, 3.657 in. would read 657 (92.888 mm would read 888).

    3. Calculate the growth of individual blades by subtracting the original marked length from the last three digits of the measured length values found in Step.

      NOTE

      If all blades in a set display negative stretch 0.001 in. - 0.005 in. (0.0254 mm - 0.127 mm) remark the blade length as described in Step I.

    4. Measure entire set of blades by Step and Step. Determine if blade set is suspect. See applicability above.

    5. Determine which blades within the set are suspect. See applicability above. A statistical analysis must be done on this initial set of growth readings to determine which measurements will be considered suspect versus those that are non-suspect. Suspect blade measurements are not to be evaluated again to further reduce the quantity of suspect parts in the set.

    6. Determine quantity of suspect readings. If 75 percent of the set or more blades are suspect, skip to Step.

      7. If less than 75 percent of the blades in the set are suspect, do the following:

      1. Determine the average stretch for the non-suspect blades (see Step.). Define a lot of standard non-suspect blades (10 blades minimum).

      2. Measure the dimension from the top edge of the second trailing edge (T/E) slot from the tip to the bottom edge of the second T/E slot from the platform, as shown in Figure for the lot.

      3. Average the values measured in Step. Subtract the average stretch of the non-suspect blades, from Step. This is the T/E base dimension.

        Example: Non-suspect blade lot T/Es are measured and average 2.243 in. (56.972 mm). Average growth of these non-suspect blades was found to be 0.003 in. (0.0762 mm) at Step. T/E base dimension is set at 2.240 in. (56.897 mm).

      4. For each suspect blade, measure the dimension from the top edge of the second T/E slot from the tip to the bottom edge of the second T/E slot from the platform, as shown in Figure.

      5. Calculate the growth of each suspect blade by subtracting the T/E base dimension Step from the T/E dimension Step of each suspect blade.

        Example: Non-suspect blade lot shows average 0.003 in. (0.0762 mm) growth and T/E base dimension of 2.240 in. (56.897 mm). Suspect blade T/E measures 2.242 in. (56.947 mm), so calculated growth of the suspect blade is 0.002 in. (0.0508 mm) (0.001 in. (0.0254 mm) less than the average established by the non-suspect blades in the set).

      6. If the calculated growth Step is 0.010 in. (0.254 mm) or less, mark by Step and Step. Negative calculated growth should be considered zero growth.

      7. If the calculated growth Step is over 0.010 in. (0.254 mm) then scrap by Step.

      8. Do the following if the blade set meets one of the conditions that follow:

        If 75 percent or more of the blades in the set are suspect.

        The quantity of non-suspect blades is 15 or less.

        The blades are previously repaired and mismarking condition has not been identified.

      1. For each suspect blade, measure the dimension from the top edge of the second T/E slot from the tip to the bottom edge of the second T/E slot from the platform, as shown in Figure.

        NOTE

        A locally fabricated tool based on a sample part may be used to confirm the standard T/E base dimension during inspection.

      2. Calculate the growth of each suspect blade by subtracting the standard T/E base dimension of 2.240 in. (56.897 mm) from the suspect blade T/E dimension Step.

        Example: Base T/E dimension is 2.240 in. (56.897 mm). suspect blade T/E measures 2.244 in. (56.997 mm) so the calculated growth of the suspect blades 0.004 in. (0.1016 mm).

      3. If the calculated growth (Step) is 0.010 in. (0.254 mm) or less, mark by Step and Step. Negative calculated growth should be considered zero growth.

      4. If the calculated growth Step is over 0.010 in. (0.254 mm) then scrap by Step.

    9. The calculated OEM length of a suspect blade is determined by subtracting the calculated growth Step or Step from the measured length Step as follows:

      Example: Blade is found at Step A. to measure 3.657 in. (92.888 mm) but OEM length marked is 655 (3.655 in.) (837 (92.837 mm)). Calculated growth of blade is determined to be 0.002 in. (0.0508 mm), 3.657 in. minus 0.002 in. equals 3.655 in. Blade is identified as 655 (92.888 mm minus 0.0508 mm equals 92.837 mm. Blade is identified as 837).

    10. Mark only the suspect blades with the calculated length from Step. with vibro-peen or dot-peen technique by SPM TASK 70-09-00-400-501. Mark the last three digits of the measurements, rounded to the nearest 0.001 in. (0.0254 mm). Example, if the length is 2.449 in. (62.204 mm), mark 449 (204). Mark in the same area as the original marking. Cross out or line out the original marked length with vibro-peen or dot-peen technique by SPM TASK 70-09-00-400-501.

    11. Scrap all blades found with true growth greater than 0.010 in. (0.254 mm).

    20. SUBTASK 72-45-32-280-059 Examine the Stage 2 HPT Blade Assembly (01-010) for the Wall Thickness Dimension

      1. Examine the blade assembly for the wall thickness dimension only when the coating is removed and you can see erosion, or when airfoil blending has removed the coating locally.

      1. Wall thickness inspection details have been removed. Refer to Repairs, VRS3440 TASK 72-45-32-300-013 (REPAIR-013) or VRS3602 TASK 72-45-32-300-021 (REPAIR-021) or VRS3838 TASK 72-45-32-300-033 (REPAIR-033).

    21. SUBTASK 72-45-32-280-070 Examine the Stage 2 HPT Blade (01-010) by Airflow Check

      NOTE

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

    1. Do the airflow check for the stage 2 HPT blade by the procedure given in VRS3713 TASK 72-45-32-300-028 (REPAIR-028).

    22. SUBTASK 72-45-32-230-063 Examine the Stage 2 HPT Blade (01-010) For Casting Flow Lines and Imperfections

    1. Refer to Figure.

      2. Examine all cast non-machined surfaces for casting flow lines by fluorescent penetrant inspection. If a flow line is detected during fluorescent penetrant inspection under black light, examine by white light with a minimum of 10X magnification to verify that there are no cracks.

        1. Flow lines with no cracks.

        1. Accept.

        2. Flow lines with cracks.

        1. Reject.

          NOTE

          1. All other inspection criteria apply.

            A flow line is a slight depression which you can see without equipment.

            Do not examine casting flow lines in the root cooling slot. Refer to Figure. If the cracks are large enough to reject the blade, the cracks would be detected at SUBTASK 72-45-32-220-079 and SUBTASK 72-45-32-230-053-001.

      3. Examine the base of the underplatform damper pins for casting voids by visual inspection with a white light and a minimum of 3X magnification. These voids must be smooth, shallow in depth, and flat-bottomed. IAE 2P16508 Reference card 1 off shows an example of an acceptable casting void. These casting voids are a maximum of 0.030 in. (0.76 mm) in diameter. Any quantity of voids is permitted.

        1. Casting voids with no cracks.

        1. Accept.

        2. Casting voids with cracks.

        1. Reject.

          NOTE

          All other inspection criteria apply.

      4. Examine the base of the underplatform damper pins for anomalies by visual inspection with a white light and a minimum of 10X magnification. Acceptable anomalies have a length of 0.070 in. (1.78 mm) or less. Indications that go from the centerline of the damper pin radius to the blade root, are not acceptable. Indications on the blade root are not acceptable. Any quantity of linear anomalies is permitted. IAE 2P16508 Reference card 1 off shows examples of acceptable linear anomalies. Cracks inside or which start from linear anomalies are not permitted. Fluorescent penetrant inspect questionable indications. Acceptable linear anomalies will not retain fluorescent penetrant fluid.

        1. Linear anomalies with no cracks.

        1. Accept.

        2. Linear anomalies with cracks.

        1. Reject.

          NOTE

          All other inspection criteria apply.

          NOTE

          Linear anomalies are tight, shallow indications with an approximate width of 0.002 in. (0.05 mm) and depth of 0.001 in. (0.03 mm).

    23. SUBTASK 72-45-32-280-064 Examine the Stage 2 HPT Blade (01-010) For Porosity and Shrinkage

      NOTE

      Porosity is regular in shape with rounded bottoms and shallow depth. Pitting is irregular in shape, deeper, with a very irregular, sponge-like surface texture.

    1. Refer to Figure.

      2. Examine the blade root rails and fillet radii on both the concave and convex sides of the blade. Use white light and 3X magnification.

        1. One 0.030 inch (0.762 mm) maximum diameter indication (porosity or shrinkage) per rail in area "L".

        1. Accept.

        2. Porosity and shrinkage indications less than 0.020 inch (0.508 mm) diameter, not in linear alignment, in area "A".

        1. Accept.

        3. One cluster, 0.185 inch (4.699 mm) maximum diameter, in area "A".

        1. Accept.

          NOTE

          All other applicable overhaul inspection criteria apply.

      3. Examine the blade root rails and fillet radii on both the concave and convex sides of the blade by fluorescent penetrant ispection. See SPOP 82 (IAE 70-23-08).

        1. One 0.030 inch (0.762 mm) maximum diameter indication (porosity or shrinkage) per rail in area "L".

        1. Accept.

        2. Porosity and shrinkage indications less than 0.020 inch (0.508 mm) diameter, not in linear alignment, in area "A".

        1. Accept.

        3. One cluster, 0.185 inch (4.699 mm) maximum diameter, in area "A"

        1. Accept.

    24. SUBTASK 72-45-32-220-115 Examine the Stage 2 HPT Blade (01-010) for Blade Width Dimensions

    1. Refer to Figure.

      2. Do a dimensional inspection to examine the blade width dimension at Location 1.

        1. For PN 2A2202, 2A2202-001, 2A2202-002, 2A2202-003: If the dimension is between 1.154 in. and 1.158 in. (29.31 mm and 29.41 mm).

        1. Accept.

        2. For PN 2A2202, 2A2202-001, 2A2202-002, 2A2202-003: If the dimension is 1.152 in. (29.26 mm) or more, and less than (Step).

        1. Permitted for select fit only, if the fit limits at Location 1554 are in the limits.

        3. For all other part numbers: If the dimension is between 1.152 in. and 1.158 in. (29.26 mm and 29.41 mm).

        1. Accept.

        4. Other than Step, Step and Step.

        1. Reject.

    25. Figure: Stage 2 HPT Blade Permeability Inspection Areas

    Stage 2 HPT Blade Permeability Inspection Areas

    Figure: Stage 2 HPT Blade Permeability Inspection Path

    Stage 2 HPT Blade Permeability Inspection Path

    Figure: Stage 2 HPT Blade Probe Orientations

    Stage 2 HPT Blade Probe Orientations

    Figure: Stage 2 HPT Blade Assembly Platform Inspection Locations

    Stage 2 HPT Blade Assembly Platform Inspection Locations

    Figure: Stage 2 HPT Blade Assembly Airfoil Inspection Locations

    Stage 2 HPT Blade Assembly Airfoil Inspection Locations

    Figure: Stage 2 HPT Blade Assembly Airfoil Dents Inspection Locations

    Stage 2 HPT Blade Assembly Airfoil Dents Inspection Locations

    Figure: Stage 2 HPT Blade Assembly Abrasive Tip Inspection Locations

    Stage 2 HPT Blade Assembly Abrasive Tip Inspection Locations

    Figure: Stage 2 HPT Blade Assembly Blade Length

    Stage 2 HPT Blade Assembly Blade Length

    Figure: Stage 2 HPT Blade Assembly Trailing Edge Inspection Locations

    Stage 2 HPT Blade Assembly Trailing Edge Inspection Locations

    Figure: Stage 2 HPT Blade Assembly Platform Surfaces Inspection Locations

    Stage 2 HPT Blade Assembly Platform Surfaces Inspection Locations

    Figure: Stage 2 HPT Blade Root and Root Attachment Area Inspection Locations For Part Number 2A4722

    Stage 2 HPT Blade Root and Root Attachment Area Inspection Locations For All Part Numbers Except 2A4722

    HPT Blade Root and Root Attachment Area Inspection Locations For All Part Numbers Except 2A4722

    HPT Blade Root and Root Attachment Area Inspection Locations For Part Number 2A4722

    Stage 2 HPT Blade Root and Root Attachment Area Inspection Locations For Part Number 2A4722

    Stage 2 HPT Blade Root and Root Attachment Previous Repair Code Markings Acceptance Area

    Legend
    1

    Stage 2 HPT Blade Root and Root Attachment Area Inspection Locations For All Part Numbers Except 2A4722

    2

    HPT Blade Root and Root Attachment Area Inspection Locations For All Part Numbers Except 2A4722

    3

    HPT Blade Root and Root Attachment Area Inspection Locations For Part Number 2A4722

    4

    Stage 2 HPT Blade Root and Root Attachment Area Inspection Locations For Part Number 2A4722

    5

    Stage 2 HPT Blade Root and Root Attachment Previous Repair Code Markings Acceptance Area

    Close

    Figure: Stage 2 HPT Blade Metal Temperature Analysis Locations

    Stage 2 HPT Blade Metal Temperature Analysis Locations

    Figure: Stage 2 HPT Blade Assembly Shot Peen Locations

    Stage 2 HPT Blade Assembly Shot Peen Locations

    Figure: Excess Metal and Foreign Material Limits (After Cleaning)

    Excess Metal and Foreign Material Limits (After Cleaning)

    Figure: Stage 2 HPT Blade Assembly Radiographic Positions Inspection Locations

    Stage 2 HPT Blade Assembly Radiographic Positions Inspection Locations

    Figure: X-Ray Inspection Internal Cavity (After Cleaning)

    X-Ray Inspection Internal Cavity (After Cleaning)

    Figure: Stage 2 HPT Blade Assembly Casting Flow Line Inspection

    Stage 2 HPT Blade Assembly Casting Flow Line Inspection

    Figure: Stage 2 HPT Blade Assembly Inspection For Porosity and Shrinkage

    Stage 2 HPT Blade Assembly Inspection For Porosity and Shrinkage

    Figure: Stage 2 HPT Blade Assembly Blade Root Cooling Slot Inspection

    Stage 2 HPT Blade Assembly Blade Root Cooling Slot Inspection

    Figure: Stage 2 HPT Blade Assembly Growth Measurement

    Stage 2 HPT Blade Assembly Growth Measurement

    Figure: Stage 2 HPT Blade Assembly Dimensional Inspection for Blade Width

    Stage 2 HPT Blade Assembly Dimensional Inspection for Blade Width

    Figure: BSI Inspection of HPT Stage 2 Blade Through Port 3 of The Blade

    BSI Inspection of HPT Stage 2 Blade Through Port 3 of The Blade

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Revised the procedural steps and figures. (20VC475)

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:0B434
Enterprise Name:MATHESON TRI-GAS INC
BU Name:MATHESON TRI-GAS INC
Street:150 ALLEN RD STE 302
City:BASKING RIDGE
Zip Code:NJ 07920
Country:USA
Phone Number:1-800-828-43130
Fax Number:1-215-619-0458
Internet:www.mathesongas.com
Manufacturer Code:0FUN2
Enterprise Name:PREMIER SHOT CO INC
BU Name:PREMIER SHOT CO INC
Street:1203 W. 65TH ST
City:CLEVELAND
Zip Code:OH 44102
Country:USA
Phone Number:1-216-651-6758
Fax Number:1-216-651-6331
Internet:www.premiershot.com
Manufacturer Code:55807
Enterprise Name:ERVIN INDUSTRIES, INC
BU Name:ERVIN INDUSTRIES, INC
Street:3893 RESEARCH PARK DR
City:ANN ARBOR
State:MI
Zip Code:48108-8221
Country:USA
Phone Number:1-734-769-4600, 1-800-748-0055
Fax Number:1-734-663-0136
Internet:www.ervinindustries.com
Manufacturer Code:86874
Enterprise Name:SANFORD CORPORATION
BU Name:SANFORD CORPORATION
Street:2711 WASHINGTON BLVD
City:BELLWOOD
State:IL
Zip Code:60104
Country:USA
Phone Number:1-708-547-6650, 1-800-323-0749
Fax Number:1-708-547-6719, 1-800-457-9208
Internet:www.sanfordcorp.com
Manufacturer Code:LOCAL
Enterprise Name:LOCALLY SUPPLIED
Manufacturer Code:86874
Supply Number:CoMat 02-081
Type:sp01
Supply Short Name:CoMat 02-081 PENCIL - METAL MARKING (HARD)
Supply Name:CoMat 02-081 PENCIL - METAL MARKING(HARD)
Specification Groups:
Doc NumberType
PMC 4059-7PRISMACOLOR VERITHIN NO.753 or PRISMACOLOR THICK LEAD 949
Suppliers:
ManufacturerRemarks
86874
Manufacturer Code:0B434
Supply Number:CoMat 03-010
Type:sp01
Supply Short Name:CoMat 03-010 ARGON GAS
Supply Name:CoMat 03-010 ARGON GAS
Specification Groups:
Doc NumberType
ARGON GAS:MINIMUM PURITY 99.998% MOISTURE 6 PPM MAX. OXYGEN 5 PPM MAX. HYDROCARBONS + CO2 3 PPM MAX. NITROGEN 20 PPM MAX. HYDROGEN 1 PPM MAX. APPROXIMATE DEW POINT -84 degF
Suppliers:
ManufacturerRemarks
0B434
0KPC9
4YRR6
46AN7
649M0
Manufacturer Code:55807
Supply Number:CoMat 05-029
Type:sp01
Supply Short Name:CoMat 05-029 CAST STEEL SHOT, S110
Supply Name:CoMat 05-029 CAST STEEL SHOT, S110
Specification Groups:
Doc NumberType
AMS 2431/1 ASR 110
Suppliers:
ManufacturerRemarks
55807
Manufacturer Code:55807
Supply Number:CoMat 05-032
Type:sp01
Supply Short Name:CoMat 05-032 CAST STEEL SHOT, S170
Supply Name:CoMat 05-032 CAST STEEL SHOT, S170
Specification Groups:
Doc NumberType
AMS 2431/1 ASR 170
Suppliers:
ManufacturerRemarks
55807
Manufacturer Code:55807
Supply Number:CoMat 05-138
Type:sp01
Supply Short Name:CoMat 05-138 SHOT, CAST STEEL, S110
Supply Name:CoMat 05-138 SHOT, CAST STEEL, S110
Specification Groups:
Doc NumberType
AMS 2431/1 ASR 110, HARDNESS 45-55 HRC
Suppliers:
ManufacturerRemarks
55807
Manufacturer Code:55807
Supply Number:CoMat 05-176
Type:sp01
Supply Short Name:CoMat 05-176 CAST STEEL SHOT, S170
Supply Name:CoMat 05-176 CAST STEEL SHOT, S170
Specification Groups:
Doc NumberType
AMS 2431/1 ASR 170, HARDNESS 45-55 HRC
Suppliers:
ManufacturerRemarks
55807
Manufacturer Code:0FUN2
Supply Number:CoMat 05-177
Type:sp01
Supply Short Name:CoMat 05-177 CUT WIRE SHOT,CW-14
Supply Name:CoMat 05-177 CUT WIRE SHOT,CW-14
Specification Groups:
Doc NumberType
AMS 2431/3 AWCR 14 HARDNESS 45-55 HRC
Suppliers:
ManufacturerRemarks
0FUN2
29978
S5114
Manufacturer Code:0FUN2
Supply Number:CoMat 05-178
Type:sp01
Supply Short Name:CoMat 05-178 CUT WIRE SHOT, CW-20
Supply Name:CoMat 05-178 CUT WIRE SHOT, CW-20
Specification Groups:
Doc NumberType
AMS 2431/3 AWCR 20 HARDNESS 45-55 HRC
Suppliers:
ManufacturerRemarks
0FUN2
29978
S5114
Manufacturer Code:0FUN2
Supply Number:CoMat 05-187
Type:sp01
Supply Short Name:CoMat 05-187 STAINLESS STEEL CUT WIRE SHOT, SCW-20
Supply Name:CoMat 05-187 STAINLESS STEEL CUT WIRE SHOT, SCW-20
Specification Groups:
Doc NumberType
AMS 2431/4 AWS 20
Suppliers:
ManufacturerRemarks
0FUN2
29978
Manufacturer Code:0FUN2
Supply Number:CoMat 05-188
Type:sp01
Supply Short Name:CoMat 05-188 STAINLESSSTEEL CUT WIRE SHOT, SPECIAL CONDITIONED, SCW-20
Supply Name:CoMat 05-188 STAINLESS STEEL CUT WIRE SHOT, SPECIAL CONDITIONED, SCW-20
Specification Groups:
Doc NumberType
AMS 2431/4 AWS 20
Suppliers:
ManufacturerRemarks
0FUN2
29978
S5114
Manufacturer Code:55807
Supply Number:CoMat 05-234
Type:sp01
Supply Short Name:CoMat 05-234 CAST STEEL SHOT, HIGH HARDNESS, S110
Supply Name:CoMat 05-234 CAST STEEL SHOT, HIGH HARDNESS, S110
Specification Groups:
Doc NumberType
AMS 2431/2 ASH 110, HARDNESS 55-65 HRC
Suppliers:
ManufacturerRemarks
55807
Manufacturer Code:86874
Supply Number:CoMat 06-120
Type:sp01
Supply Short Name:CoMat 06-120 METAL MARKING PENCIL (HARD)
Supply Name:CoMat 06-120 METAL MARKING PENCIL (HARD)
Specification Groups:
Doc NumberType
PMC 4059-2COL-ERASE 1276 BLUE
Suppliers:
ManufacturerRemarks
86874
Manufacturer Code:LOCAL
Tool Number:1.069.01-3001
Tool Name:Permeability Probe
Manufacturer Code:LOCAL
Tool Number:9064001
Tool Name:Adapter, Probe
Manufacturer Code:0AM53
Tool Number:IAE 2P16101
Tool Name:IAE 2P16101 Airflow base
Manufacturer Code:0AM53
Tool Number:IAE 2P16113
Tool Name:IAE 2P16113 Airflow fixture
Manufacturer Code:0AM53
Tool Number:IAE 2P16119
Tool Name:IAE 2P16119 Airflow insert
Manufacturer Code:0AM53
Tool Number:IAE 2P16359
Tool Name:IAE 2P16359 Blade length gage
Manufacturer Code:0AM53
Tool Number:IAE 2P16411
Tool Name:IAE 2P16411 Airflow master
Manufacturer Code:0AM53
Tool Number:IAE 2P16508
Tool Name:IAE 2P16508 Reference card
Manufacturer Code:LOCAL
Tool Number:Magnetoscop(R), Meter, Model 1.069 or equivalent, Model 1.067, or 1.068
Tool Name:Magnetoscope(R) Meter, Model 1.069 or equivalent, Model 1.067, or 1.068
Manufacturer Code:LOCAL
Tool Number:Oven
Tool Name:Oven