TASK 72-45-14-200-001-A00 HPT Stage 1 Blade - Examine, Inspection-001

DMC:V2500-A0-72-45-1401-00A-300A-C|Issue No:001.00|Issue Date:2013-11-01

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 72-45-14-200-001-A00 HPT Stage 1 Blade - Examine, Inspection-001

Effectivity

FIG/ITEM PART NO.

01-010

2A1221

01-010

2A1221-001

01-010

2A1221-002

01-010

2A1721

01-010

2A1721-001

01-010

2A1721-002

01-010

2A2421

01-010

2A2421-001

01-010

2A3001

01-010

2A3001-001

01-010

2A3001-002

01-010

2A8601

01-010

2A8901

General

This TASK gives the procedure for the inspection of the stage 1 HPT blade. For the other part of the stage 1 HPT blade assembly, refer to TASK 72-45-14-200-000 (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 72-45-14-230-052. Do the test for cracks only if the visual examination of the blade is unsatisfactory.

A ** following repair referenced in this inspection indicates that the repair is not yet published in the current revision of the manual and the part must be rejected. Contact IAE for additional information concerning FAA approved repair date.

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 the SPM.

References

Refer to the 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

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

Procedure to Moderately Clean, 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

Shotpeening, SPM TASK 70-38-13-380-501

Radiograph Inspection Procedure, SPM TASK 70-26-01-260-501

Airflow - 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 70-20-01-200-501

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

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

Method of Testing for Crack Indications

Chemical Processes

Surface Protection

NOTE

To identify 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
OvenLOCALOven

(Air furnace)

IAE 2P16101 Airflow base0AM53IAE 2P161011
IAE 2P16113 Airflow fixture0AM53IAE 2P161131
IAE 2P16114 Airflow insert0AM53IAE 2P161141
IAE 2P16115 Airflowmaster0AM53IAE 2P161151
IAE 2P16116 Airflowmaster0AM53IAE 2P161161
IAE 2P16117 Airflowmaster0AM53IAE 2P161171
IAE 2P16118 Airflowmaster0AM53IAE 2P161181
IAE 2P16360 Airflowmaster0AM53IAE 2P163601
IAE 2P16361 Airflowmaster0AM53IAE 2P163611
IAE 2P16362 Airflowmaster0AM53IAE 2P163621
IAE 2P16371 Stage 1 HPT Blade Length Gage0AM53IAE 2P163711
IAE 2P16508 Reference card0AM53IAE 2P165081

Consumables, Materials and Expendables

NameManufacturerPart Number / IdentificationQuantityRemark
CoMat 03-010 ARGON GASLOCALCoMat 03-010
CoMat 03-117 ARGON GAS0AM53CoMat 03-117
CoMat 03-118 ARGON GAS0AM53CoMat 03-118
CoMat 05-029 CAST STEEL SHOT, S110LOCALCoMat 05-029
CoMat 05-030 CAST STEEL SHOT DELETED0AM53CoMat 05-030
CoMat 05-031 CAST STEEL SHOT DELETED0AM53CoMat 05-031
CoMat 05-032 CAST STEEL SHOT, S17042736CoMat 05-032
CoMat 05-033 CAST STEEL SHOT DELETED0AM53CoMat 05-033
CoMat 05-034 CAST STEEL SHOT DELETED0AM53CoMat 05-034
CoMat 05-138 SHOT, CAST STEEL, S11081349CoMat 05-138
CoMat 05-176 CAST STEEL SHOT, S17042736CoMat 05-176
CoMat 05-177 CUT WIRE SHOT,CW-14LOCALCoMat 05-177
CoMat 05-178 CUT WIRE SHOT, CW-20LOCALCoMat 05-178
CoMat 05-187 STAINLESS STEEL CUT WIRE SHOT, SCW-20LOCALCoMat 05-187
CoMat 05-188 STAINLESS STEEL CUT WIRE SHOT, SPECIAL CONDITIONED, SCW-20LOCALCoMat 05-188
CoMat 05-234 CAST STEEL SHOT, HIGH HARDNESS, S110LOCALCoMat 05-234

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-45-14-220-053 Examine the Stage 1 HPT Blade (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 (1)

        1. Repairs, VRS3202 TASK 72-45-14-300-001 (REPAIR-001), VRS3203 TASK 72-45-14-300-002 (REPAIR-002), VRS3204 TASK 72-45-14-300-003 (REPAIR-003), VRS3495 TASK 72-45-14-300-007 (REPAIR-007), or VRS3493 TASK 72-45-14-300-008 (REPAIR-008)

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

        1. Any amount of cracked, nicked or chipped coating at location 3 but none is permitted in the airfoil radius at location 1

        1. Accept

        2. Any amount of cracks up to 0.100 in. (2.54 mm) in length at locations 2 and 3. No cracks permitted in the airfoil radius at location 1

        1. Accept

        3. Any quantity of through cracks up to 0.100 in. (2.54 mm) in length at location 4. One through crack up to 0.120 in. (3.05 mm) in length at location 4 is permitted if the crack does not intersect the airfoil-to-platform fillet radius. No intersecting (closed loop) cracks are permitted

        1. Accept

        4. Other than (1), (2) and (3)

        1. Repairs, VRS3202 TASK 72-45-14-300-001 (REPAIR-001), VRS3203 TASK 72-45-14-300-002 (REPAIR-002), VRS3204 TASK 72-45-14-300-003 (REPAIR-003), VRS3495 TASK 72-45-14-300-007 (REPAIR-007), or VRS3493 TASK 72-45-14-300-008 (REPAIR-008)

      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. No dents are permitted in the airfoil radius

        1. Accept

        2. Other than (1)

        1. Repairs, VRS3202 TASK 72-45-14-300-001 (REPAIR-001), VRS3203 TASK 72-45-14-300-002 (REPAIR-002), VRS3204 TASK 72-45-14-300-003 (REPAIR-003), VRS3495 TASK 72-45-14-300-007 (REPAIR-007) or VRS3493 TASK 72-45-14-300-008 (REPAIR-008)

    2. SUBTASK 72-45-14-220-054 Examine the Stage 1 HPT Blade (01-010) Airfoil

      NOTE

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

    1. Refer to Figure and Figure.

      2. Examine the blade airfoil surfaces for burned areas, corrosion and erosion.

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

        1. Accept

        2. Other than (1)

        1. Repairs, VRS3202 TASK 72-45-14-300-001 (REPAIR-001), VRS3203 TASK 72-45-14-300-002 (REPAIR-002), VRS3204 TASK 72-45-14-300-003 (REPAIR-003), VRS3495 TASK 72-45-14-300-007 (REPAIR-007), or VRS3493 TASK 72-45-14-300-008 (REPAIR-008)

      3. Examine the blade airfoil surfaces for nicked and chipped coating.

        1. Nicked or chipped coating

        1. Repairs, VRS3202 TASK 72-45-14-300-001 (REPAIR-001), VRS3203 TASK 72-45-14-300-002 (REPAIR-002), VRS3204 TASK 72-45-14-300-003 (REPAIR-003), VRS3495 TASK 72-45-14-300-007 (REPAIR-007), or VRS3493 TASK 72-45-14-300-008 (REPAIR-008)

          NOTE

          Refer to Step for cracks on the trailing edge and Step for cracks on the blade tip.

      4. Examine the blade concave and convex surfaces and the leading edge cooling air holes for cracks. Use a white light and a 10X magnification, Figure.

        1. Cracks in Area A.

          1. One or more cracks if a crack does not go through more than two holes and the cracks are mostly in a radial direction

          1. Accept

          2. Other than (a)

          1. Remove the coating, VRS3204 TASK 72-45-14-300-003 (REPAIR-003)

        2. Cracks in Area B.

          1. One or more cracks if a crack does not go through more than two holes and the cracks are mostly in a radial direction

          1. Accept

          2. Other than (a)

          1. Remove the coating, VRS3204 TASK 72-45-14-300-003 (REPAIR-003)

      5. Examine the blade concave and convex surfaces for dents, Figure.

        1. The acceptable limits for each dent on the blade area as follows:

        1. A smooth bottom.

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

        3. A minimum relation between length and depth of 10 to 1.

        4. There is not base metal shown.

        5. At a location that does not block the cooling air holes.

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

        7. At a location that is not less than 0.100 in. (2.54 mm) from the blade platform at location 5.

        2. The acceptable quantity of dents on the blade is as follows:

          1. Three dents on each side of the concave and convex airfoil surfaces at location 1

          1. Accept

          2. Four dents on the leading edge at location 3

          1. Accept

          3. One or more dents on the convex and concave airfoil surfaces in 0.250in. (6.35 mm) of the blade tip at location 4

          1. Accept

        3. Other than (1) and (2), including nicks

        1. Repairs, VRS3202 TASK 72-45-14-300-001 VRS3203 TASK 72-45-14-300-002 (REPAIR-002), VRS3204 TASK 72-45-14-300-003 (REPAIR-003), VRS3495 TASK 72-45-14-300-007 (REPAIR-007) or VRS3493 TASK 72-45-14-300-008 (REPAIR-008)

    3. SUBTASK 72-45-14-220-055 Examine the Stage 1 HPT Blade (01-010) Abrasive Tip

    1. Refer to: Figure

      2. Examine the blade abrasive tip for base metal that shows.

        1. There is base metal that shows on the base metal/tip interface at location 2

        1. Repair, VRS3495 TASK 72-45-14-300-007 (REPAIR-007) VRS3493 TASK 72-45-14-300-008 (REPAIR-008) or VRS3204 TASK 72-45-14-300-003 (REPAIR-003)

          NOTE

          The base metal/tip interface is shown at location 5.

        2. There is base metal that shows on the base metal/tip interface at location 1 or 4

        1. Accept

        3. One or more chips at location 2 which have an equivalent total width of 0.200in. (5.08mm) (the sum of the individual widths of multiple chips must be less than or equal to 0.200in, (5.08 mm)) and there is no base metal shown on th airfoil base metal/tip interface at location 5

        1. Accept

          NOTE

          Example of a chip is shown at location 6.

        4. Other than (3)

        1. Repair, VRS3495 TASK 72-45-14-300-007 (REPAIR-007) or VRS3493 TASK 72-45-14-300-008 (REPAIR-008)

    4. SUBTASK 72-45-14-220-068 Examine the Stage 1 HPT Blade Assembly (01-010) Blade Length

      NOTE

      If the blades were repaired before, a repair code will be marked on the blade root area. These codes will have one, two, three or four characters. In some cases there will be a vendor-processing code before the repair code. The vendor-processing code will have ten or more digits and may be identified as (X-XXXXX-XX), or an approved supplier code (a heart inside a circle).
      These repair codes will indicate how the blade was repaired. More than one repair code can be shown on the blade root.
      Only the latest repair codes will not have a straight line through them.

      1. Examine the front and rear blade root surfaces for the repair code(s) that are marked on the blade.

      1. R.

      2. RR.

      3. T, RT.

      4. TR, RRT.

      5. TT.

      6. TTR, RTT, RRTT.

      2. REPAIR FACILITY CODE.

      1. K5 or c inside a circle 5.

      2. K10 or c inside a circle 10.

      3. L5 or +5.

      4. L10 or +10.

      5. M or +.

      6. M5 or +5.

      7. M10 or +10.

      3. Examine the blade assembly at location 1 for the blade length dimension.

        1. Install the blade assembly into the IAE 2P16371 Stage 1 HPT Blade Length Gage 1 off.

        1. Put the two gage dowel pins in the first blade root fir tree slots from the blade platform and clamp into position.

      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 distance from the end surface of the gage to the surface of the middle pin.

          1. If less than or equal to 0.005in. (0.127 mm) for repair codes M, R, RR + or No Code

          1. Accept

          2. If less than or equal to 0.008in. (0.203 mm) for repair codes T, RT, TR or RRT

          1. Accept

          3. If less than or equal to 0.010in. (0.254 mm) for repair codes TT, TTR, RTT, RRTT, K5, L5, M5, c in a circle 5 or +5

          1. Accept

          4. If less than or equal to 0.015in. (0.381 mm) for repair codes K10, L10, M10, c in a circle 10 or +10

          1. Accept

          5. Other than (a) thru (d)

          1. Repair, VRS3495 TASK 72-45-14-300-007 (REPAIR-007), VRS3493 TASK 72-45-14-300-008 (REPAIR-008) or VRS3204 TASK 72-45-14-300-003 (REPAIR-003)

        5. Measure the distance for the end surface of the gage to the surface of the trailing edge pin.

          1. If less than or equal to 0.005in. (0.127 mm) for repair codes M, R, RR, + or No Code

          1. Accept

          2. If less than or equal to 0.008in. (0.203 mm) for repair codes T, RT, TR or RRT

          1. Accept

          3. If less than or equal to 0.010in. (0.254 mm) for repair codes TT, TTR, RTT, RRTT, K5, L5, M5, c in a circle 5 or +5

          1. Accept

          4. If less than or equal to 0.015in. (0.381 mm) for repair codes K10, L10, M10, c in a circle 10 or +10

          1. Accept

          5. Other then (a) thru (d)

          1. Repair, VRS3495 TASK 72-45-14-300-007 (REPAIR-007), VRS3493 TASK 72-45-14-300-008 (REPAIR-008) or VRS3204 TASK 72-45-14-300-003 (REPAIR-003)

    5. SUBTASK 72-45-14-220-056 Examine the Stage 1 HPT Blade (01-010) Trailing Edge

    1. Refer to: Figure

      NOTE

      The tip of the trailing edge may have a blend no more than 0.060 in. (0.24 mm) deep, extending from the tip to the middle of the third trailing edge window. Reference VRS3685, TASK 72-45-14-300-021. This condition is acceptable.

      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, VRS3202 TASK 72-45-14-300-001 (REPAIR-001), VRS3203 TASK 72-45-14-300-002 VRS3204 TASK 72-45-14-300-003 72-45-14-300-007 (REPAIR-007) or VRS3493 TASK 72-45-14-300-008 (REPAIR-008) or VRS3685 TASK 72-45-14-300-021 (REPAIR-021)

          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. Reject

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

        1. Plugging

        1. Use a wire probe and power flush or pencil grit blast and high pressure air blast or Repair, VRS3357 TASK 72-45-14-300-005 (REPAIR-005)

          NOTE

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

    6. SUBTASK 72-45-14-220-057 Examine the Stage 1 HPT Blade (01-010) Leading Edge Platform

    1. Refer to: Figure

      2. Examine the blade surface at location 2, for signs of rub with the stage 1 HPT duct segment seal or the stage 1 HPT vane platform.

        1. Rub up to 0.005in. (0.127 mm)

        1. Accept

        2. Other than (1)

        1. Repair, VRS3408 TASK 72-45-14-300-006 (REPAIR-006)**

      3. Examine the blade leading edge platform for curling at location 3.

        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.

    7. SUBTASK 72-45-14-220-058 Examine the Stage 1 HPT Blade (01-010) Damper Contact Area

    1. Refer to: Figure

      2. Examine the blade damper contact area for wear at location 1.

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

        1. Accept

        2. Other than (1)

        1. Repair, VRS3594 TASK 72-45-14-300-019 (REPAIR-019)

    8. SUBTASK 72-45-14-220-059 Examine the Stage 1 HPT Blade (01-010) Root Attachment Area

    1. Refer to: Figure

      2. Examine the blade root attachment area for erosion and corrosion at location, 2, 3 and 7.

        1. Up to 0.005in. (0.127 mm) in depth when the surface is not rough and there are no cracks, crazing, ridges or depressions

        1. Accept

        2. Other than (1)

        1. Reject

      3. Examine the blade root attachment area for erosion and corrosion at locations 1, 5 and 6.

        1. Up to 0.005in. (0.127 mm) in depth when the surface is not rough and there are no cracks, crazing, ridges or depressions

        1. Accept

        2. Other than (1)

        1. Repair, VRS3203 TASK 72-45-14-300-002 (REPAIR-002) or Repair, VRS3594 TASK 72-45-14-300-019 (REPAIR 019)

      4. Examine the blade root attachment area for fretting and galling at location 3.

        1. Up to 0.005in. (0.127 mm) in depth on the load bearing tooth surfaces when there are no cracks or pitting

        1. Accept

        2. Other than (1)

        1. Repair, VRS3594 TASK 72-45-14-300-019 (REPAIR 019)

      5. Examine the blade root attachment area for contact wear that is not equal (tooth to tooth and side to side) at location 3.

        1. Contact wear on the blade root that is not equal along the root tooth up to 0.005in. (0.127 mm) in depth when there are no cracks or pitting

        1. Accept

        2. Other than (1)

        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.

      6. Examine the blade root attachment area for pitting, nicks and cracks at locations 2, 3 and 7. Use a white light and a 10X magnification to examine for cracks.

        1. Cracks, nicks or pitting

        1. Repair, VRS3594 TASK 72-45-14-300-019 (REPAIR-019)

    9. SUBTASK 72-45-14-220-060 Examine the Stage 1 HPT Blade (01-010) Root Area

    1. Refer to: Figure

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

        1. Cracks or nicks

        1. Repair, VRS3203 TASK 72-45-14-300-002 (REPAIR-002)

      3. Examine the blade root area for pitting.

        1. Up to 0.005in. (0.127 mm) at locations 1 and 6

        1. Accept

        2. Up to 010in. (0.254 mm) at location 5

        1. Accept

        3. Other than (1) or (2)

        1. Repair, VRS3594 TASK 72-45-14-300-019 (REPAIR-019)

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

        1. Up to 0.005in. (0.127 mm) with rounded edges, corners and bottoms at locations 1 and 6. The dents have a minimum relation between length and depth of 10 to 1

        1. Accept

        2. Up to 0.010in. (0.254 mm) with rounded edges, corners and bottoms at location 5. The dents have a minimum relation between length and depth of 10 to 1

        1. Accept

        3. Blades which show depressed and/or raised casting imperfections on ends of seal support lugs (see location 4)

        1. Accept

        4. Other than (1), (2) or (3)

        1. Repair, VRS3203 TASK 72-45-14-300-002 (REPAIR-002)

    10. SUBTASK 72-45-14-280-051 Examine the Stage 1 HPT Blade (01-010) for Overtemperature

    1. Refer to Figure.

      NOTE

      1. Blades that were at temperatures more than the limit of 2000 deg F (1093 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.

    2. Examine one blade for overtemperature by metallurgical analysis if the engine was removed because the temperature/time was higher than the limit.

      3. Cut the blade at location 1 to get the airfoil sample to be analyzed. Refer to the SPM TASK 70-02-03-220-501.

        NOTE

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

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

      2. Cut the blade airfoil sample at location 2.

    4. Cut out the blade root sample at location 8.

    5. Discard the remaining blade pieces.

      6. Attach and polish the blade samples by the 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 surface to be polished.

      7. Examine the microstructure of the blade samples, refer to the 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 to 0.015 in. (0.25 to 0.38 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 to 0.015 in. (0.25 to 0.38 mm) from the edge of the root sample.

        1. This location can be used to compare the hot areas of the airfoils.

      8. Reject all of the stage 1 HPT blades in the engine if the metal temperature is higher than 2050 deg F (1121 deg C) at any of the locations that follows:

      1. Leading edge analysis area at location 6.

      2. Midchord analysis area at location 5.

      3. Trailing edge analysis area at location 3.

    9. Do not examine any other areas of the blade.

    11. SUBTASK 72-45-14-230-052-001 Examine the Stage 1 HPT Blade (01-010) for Cracks

    1. Refer to Figure.

      NOTE

      Do this procedure only if the visual examination of the blade is unsatisfactory.
      If you cannot do this procedure, do the procedure given in SUBTASK 72-45-14-230-052-003.

    2. Clean the part. Refer to TASK 72-45-14-100-003 (CLEANING-003, CONFIG-001).

      3. WARNING

        IT IS THE RESPONSILIBILTY OF THE OPERATOR TO OBTAIN AND OBSERVE THE MANUFACTURERS MATERIAL SAFETY SHEETS FROM THE 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 REGULATIONS INTO CONSIDERATION.

        Stress relief the blade.

      1. CAUTION

        FAILURE TO STRESS RELIEVE THE BLADE BEFORE FLUORESCENT PENETRANT EXAMINATION CAN CAUSE DAMAGE TO THE BLADE.

        Heat the blade to between 1950 and 2000 deg F (1066 and 1093 deg C) in an oven and hold for 30 minutes minimum to four hours in a vacuum or argon protected atmosphere. Use CoMat 03-010 ARGON GAS, CoMat 03-117 ARGON GAS or CoMat 03-118 ARGON GAS. Refer to the SPM TASK 70-37-26-370-501.

      2. Cool the blade at a rate of 10 deg F (5.5 deg C) for each hour or faster.

    4. 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 1 HPT blade

    5. If you find any crack indications, make a temporary mark on the indications with one of the approved temporary markers in the SPM TASK 70-09-00-400-501.

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

      7. Precipitation heat treat (PHT) the blade assembly.

      1. Heat the blade assembly (PN 2A1221, 2A1721 and 2A2421) to between 1575 and 1625 deg F (857 to 885 deg C) in an oven and keep at this temperature for 32 hours. PHT is optional for these part numbers. Refer to the SPM TASK 70-37-27-370-501.

      2. Heat the blade assembly (PN 2A3001, 2A8601 and 2A8901) to between 1575 and 1625 deg F (857 and 885 deg C) in an oven and keep at this temperature for 8, 12 or 32 hours. Refer to the SPM TASK 70-37-27-370-501.

      3. Let the blade air cool.

    12. SUBTASK 72-45-14-230-052-002 Examine the Stage 1 HPT Blade (01-010) for Cracks

      NOTE

      Do this procedure only if the visual examination of the blade is unsatisfactory.
      If you cannot do Step do this procedure.

    1. CAUTION

      FAILURE TO STRESS RELIEVE THE BLADE BEFORE FLUORESCENT PENETRANT EXAMINATION CAN CAUSE DAMAGE TO THE BLADE.

      When you cannot stress relieve the blade, you must send the blade to one of the approved sources that follows:

      PRATT and WHITNEY AFTERMARKET SERVICES (PWAS)
      Connecticut Airfoil Repair Operations
      400 Main St., Well 11
      East Hartford, CT 06108-0969 USA
      Tel: (860) 565-3922
      Fax: (860) 557-8247

      Sequa Corp.,
      Chromalloy Research and Technology Div.
      108 Blaisdell Road
      Orangeburg, New York 10962 USA
      Tel: (845) 359-4700
      Fax: (845) 359-4409

    13. SUBTASK 72-45-14-280-052 Examine the Stage 1 HPT Blade (01-010) Coating by Heat Tint

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

    2. CAUTION

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

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

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

        1. CAUTION

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

          Heat tint the blade at one of the temperatures that follow:

        1. Heat tint the blade at 1050 to 1100 deg F (566 to 593 deg C) in an oven (air furnace) for 45 to 75 minutes.

        2. Heat tint the blade at 1275 to 1325 deg F (691 to 718 deg C) in an oven (air furnace) for 20 to 30 minutes.

      2. WARNING

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

        Remove the blade from the oven.

      4. Examine the blade coating for heat tint.

        1. Heat tint.

          1. Light gold color shows the blade has a 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 TASKS 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. Repair, VRS3203 TASK 72-45-14-300-002 (REPAIR-002), VRS3204 TASK 72-45-14-300-003 (REPAIR-003) VRS3495 TASK 72-45-14-300-007 (REPAIR-007) or VRS3493 TASK 72-45-14-300-008 (REPAIR-008)

    14. SUBTASK 72-45-14-260-051 Examine the Stage 1 HPT Blade (01-010) for Internal Cracks and Unwanted Material by Radiographic Inspection

    1. Refer to: Figure and Figure

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

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

        NOTE

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

        2. Make an analysis on the radiographic indications.

          1. Cracks

          1. Reject

          2. Unwanted material in the internal cavities

          1. Power flush or Repair, VRS3357 TASK 72-45-14-300-005 (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 there shape, form or density, the parts shall be rejected.

          2. After cleaning the internal cavities refer to VRS3357 TASK 72-45-14-300-005 (REPAIR-005), unwanted metal and materials are acceptable provided the size, density and location of the indication(s) has remained unchanged from step (2) (b). Refer to the limits in Figure and Table 801.

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

          1. Reject

    15. SUBTASK 72-45-14-280-066 Examine the Stage 1 HPT Blade Assembly (01-010) by Airflow Check

      NOTE

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

    1. Do the airflow procedure for the stage 1 HPT blade assembly by the procedure given in VRS3710 TASK 72-45-14-300-031 (PEPAIR-031).

    16. SUBTASK 72-45-14-280-070 Examine the Stage 1 HPT Blade Assembly (01-010) by Waterflow Check

    1. Refer to Figure.

      2. Do the waterflow check to examine the blade.

      1. Install the blade into the waterflow fixture.

      2. Flow filtered water into the blade.

        3. Examine the water flow from the blade cooling holes. There must be a clear stream of water from each cooling hole.

        1. If there are holes that are fully or partially blocked, you must clean the holes to remove the blockages.

      4. Do steps (1), (2) and (3) of the waterflow check again.

        NOTE

        Casting chaplet holes that are not mismatched or double drilled holes are acceptable. Chaplet holes may or may not exist. EDM toolmarks and/or double drilled holes are acceptable if they are not blocked and the blades meet airflow requirements. Refer to Figure for typical chaplet and double drilled holes.

      5. Dry the internal cavities of the blade with dry shop air.

    17. SUBTASK 72-45-14-230-057 Examine the Stage 1 HPT Blade (01-010) For Casting Flow Lines and Imperfections

    1. Refer to Figure.

      NOTE

      All other inspection criteria apply.

      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

      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. (0.762 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.

          NOTE

          Linear anomalies are tight, shallow indications with an approximate width of 0.002 in. (0.051 mm) and depth of 0.001 in. (0.025 mm).

      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. (1.778 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

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

    18. SUBTASK 72-45-14-230-058 Examine the Stage 1 HPT Blade (01-010) For Porosity and Shrinkage

    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 inspection. 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

          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.

    19. Figure: Stage 1 HPT Blade Platform Inspection Locations

    Stage 1 HPT Blade Platform Inspection Locations

    Figure: Stage 1 HPT Blade Cooling Air Holes Inspection Locations

    Stage 1 HPT Blade Cooling Air Holes Inspection Locations

    Figure: Stage 1 HPT Blade Airfoil Inspection Locations

    Stage 1 HPT Blade Airfoil Inspection Locations

    Figure: Stage 1 HPT Blade Abrasive Tip Inspection Locations

    Stage 1 HPT Blade Abrasive Tip Inspection Locations

    Figure: Stage 1 HPT Blade Trailing Edge Inspection Locations

    Stage 1 HPT Blade Trailing Edge Inspection Locations

    Figure: Stage 1 HPT Blade Platform Surfaces Inspection Locations

    Stage 1 HPT Blade Platform Surfaces Inspection Locations

    Figure: Stage 1 HPT Blade Root and Attachment Area Inspection Locations

    Stage 1 HPT Blade Root and Attachment Area Inspection Locations

    Figure: Stage 1 HPT Blade Metal Temperature Analysis Locations

    Stage 1 HPT Blade Metal Temperature Analysis Locations

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

    Excess Metal and Foreign Material Limits (After Cleaning)

    Figure: Stage 1 HPT Blade Radiographic Positions Inspection Locations

    Stage 1 HPT Blade Radiographic Positions Inspection Locations

    Figure: X-Ray Inspection Internal Cavity

    X-Ray Inspection Internal Cavity

    Figure: Stage 1 HPT Blade Assembly Shot Peen Locations

    Sheet 1

    Legend
    Stage 1 HPT Blade Assembly Shot Peen Locations

    Sheet 1

    Close

    Figure: Stage 1 HPT Blade Assembly Shot Peen Locations

    Sheet 2

    Legend
    Stage 1 HPT Blade Assembly Shot Peen Locations

    Sheet 2

    Close

    Figure: Stage 1 HPT Blade Assembly Airfoil Cooling Hole Inspection

    Sheet 3

    Legend
    Stage 1 HPT Blade Assembly Airfoil Cooling Hole Inspection

    Sheet 3

    Close

    Figure: Stage 1 HPT Blade Assembly Casting Flow Line Inspection

    Stage 1 HPT Blade Assembly Casting Flow Line Inspection

    Figure: Stage 1 HPT Blade Assembly Inspection for Porosity and Shrinkage

    Stage 1 HPT Blade Assembly Inspection for Porosity and Shrinkage

Requirements After Job Completion

Follow-On Conditions

NONE
Manufacturer Code:0AM53
Enterprise Name:IAE INTERNATIONAL AERO ENGINES AG
BU Name:NULL
Building:SUITE 400
Street:628 HEBRON AVENUE
City:GLASTONBURY
State:CT
Zip Code:06033
Country:USA
Manufacturer Code:42736
Enterprise Name:NATIONAL METAL ABRASIVE INC.
BU Name:NATIONAL METAL ABRASIVE INC.
Street:142 Auble Street
P.O. Box:150
City:Wadsworth
State:Ohio
Zip Code:44281
Country:USA
Phone Number:+1-330-334-1566
Fax Number:+1-330-334-1456
Manufacturer Code:81349
Enterprise Name:DELETED, SEE CAGE CODE 81348
Manufacturer Code:LOCAL
Enterprise Name:LOCALLY SUPPLIED
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:X111X
Supply Number:CoMat 03-117
Type:sp01
Supply Short Name:CoMat 03-117 ARGON GAS
Supply Name:CoMat 03-117 ARGON GAS
Specification Groups:
Doc NumberType
DELETED
Suppliers:
ManufacturerRemarks
X111X
Manufacturer Code:X111X
Supply Number:CoMat 03-118
Type:sp01
Supply Short Name:CoMat 03-118 ARGON GAS
Supply Name:CoMat 03-118 ARGON GAS
Specification Groups:
Doc NumberType
DELETED
Suppliers:
ManufacturerRemarks
X111X
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:0AM53
Supply Number:CoMat 05-030
Type:sp01
Supply Short Name:CoMat 05-030 CAST STEEL SHOT DELETED
Supply Name:CoMat 05-030 CAST STEEL SHOT DELETED
Specification Groups:
Doc NumberType
DELETED
Suppliers:
ManufacturerRemarks
0AM53
Manufacturer Code:0AM53
Supply Number:CoMat 05-031
Type:sp01
Supply Short Name:CoMat 05-031 CAST STEEL SHOT DELETED
Supply Name:CoMat 05-031 CAST STEEL SHOT DELETED
Specification Groups:
Doc NumberType
DELETED
Suppliers:
ManufacturerRemarks
0AM53
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:0AM53
Supply Number:CoMat 05-033
Type:sp01
Supply Short Name:CoMat 05-033 CAST STEEL SHOT DELETED
Supply Name:CoMat 05-033 CAST STEEL SHOT DELETED
Specification Groups:
Doc NumberType
DELETED
Suppliers:
ManufacturerRemarks
0AM53
Manufacturer Code:0AM53
Supply Number:CoMat 05-034
Type:sp01
Supply Short Name:CoMat 05-034 CAST STEEL SHOT DELETED
Supply Name:CoMat 05-034 CAST STEEL SHOT DELETED
Specification Groups:
Doc NumberType
DELETED
Suppliers:
ManufacturerRemarks
0AM53
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: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 2P16114
Tool Name:IAE 2P16114 Airflow insert
Manufacturer Code:0AM53
Tool Number:IAE 2P16115
Tool Name:IAE 2P16115 Airflowmaster
Manufacturer Code:0AM53
Tool Number:IAE 2P16116
Tool Name:IAE 2P16116 Airflowmaster
Manufacturer Code:0AM53
Tool Number:IAE 2P16117
Tool Name:IAE 2P16117 Airflowmaster
Manufacturer Code:0AM53
Tool Number:IAE 2P16118
Tool Name:IAE 2P16118 Airflowmaster
Manufacturer Code:0AM53
Tool Number:IAE 2P16360
Tool Name:IAE 2P16360 Airflowmaster
Manufacturer Code:0AM53
Tool Number:IAE 2P16361
Tool Name:IAE 2P16361 Airflowmaster
Manufacturer Code:0AM53
Tool Number:IAE 2P16362
Tool Name:IAE 2P16362 Airflowmaster
Manufacturer Code:0AM53
Tool Number:IAE 2P16371
Tool Name:IAE 2P16371 Stage 1 HPT Blade Length Gage
Manufacturer Code:0AM53
Tool Number:IAE 2P16508
Tool Name:IAE 2P16508 Reference card
Manufacturer Code:LOCAL
Tool Number:Oven
Tool Name:Oven