TASK 72-45-14-200-001-C00 HPT Stage 1 Blade - Examine, Inspection-001

DMC:V2500-A0-72-45-1401-00C-300A-C|Issue No:005.00|Issue Date:2019-08-01

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 72-45-14-200-001-C00 HPT Stage 1 Blade - Examine, Inspection-001

Effectivity

FIG/ITEM

PART NO.

01-010

2A9321

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-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.

Repair, VRS3702 TASK 72-45-14-300-030 (REPAIR-030), contains a special cleaning and inspection procedure for the under-platform stress corrosion. You must do this repair in conjunction with the inspection requirements in this task.

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 72-45-14-230-064. 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

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 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
OvenLOCAL
OvenLOCAL

(Air furnace)

IAE 2P16372 Stage 1 HPT Blade Length Gage0AM53IAE 2P163721
IAE 2P16508 Reference card0AM53IAE 2P165081

Consumables, Materials and Expendables

NameManufacturerPart Number / IdentificationQuantityRemark
CoMat 03-010 ARGON GASLOCALCoMat 03-010
CoMat 03-117 ARGON GASNEWCoMat 03-117
CoMat 03-118 ARGON GASLOCALCoMat 03-118
CoMat 05-029 CAST STEEL SHOT, S110LOCALCoMat 05-029
CoMat 05-030 CAST STEEL SHOT DELETEDLOCALCoMat 05-030
CoMat 05-031 CAST STEEL SHOT DELETEDLOCALCoMat 05-031
CoMat 05-032 CAST STEEL SHOT, S17055807CoMat 05-032
CoMat 05-033 CAST STEEL SHOT DELETEDLOCALCoMat 05-033
CoMat 05-034 CAST STEEL SHOT DELETEDLOCALCoMat 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 05-234 CAST STEEL SHOT, HIGH HARDNESS, S110LOCALCoMat 05-234

Spares

NONE

Safety Requirements

CAUTION

YOU MUST BE VERY CAREFUL DURING THE INSPECTION OR HANDLING OF THE PARTS. INCORRECT HANDLING, SUCH AS TOUCHING THE BLADES WITH DIRTY HANDS, OR DROPPING THE BLADES ON THE GROUND, CAN CAUSE CHIPPING OF THE THERMAL BARRIER COATING AND DISCOLORATION OF THE BLADES.

Procedure

    1. SUBTASK 72-45-14-220-080 Examine the Stage 1 HPT Blade (01-010) Blade Platform Area

    1. Refer to Figure.

      NOTE

      To find if the metallic base coat is present, use the heat tint examination in Step.

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

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

        1. Accept.

        2. Other than Step.

        1. Repair, VRS3816 TASK 72-45-14-300-041 (REPAIR-041) or Repair, VRS3824 TASK 72-45-14-300-043 (REPAIR-043).

      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 Locations 2 and 3 provided the metallic base coat is present.

        1. Accept.

        2. Any amount of cracks not more than 0.070 in. (1.78 mm) in length at Locations 2 and 3. No cracks permitted in the airfoil radius at Location 1.

        1. Accept.

        3. Other than Step.

        1. Remove the coating, Repair, VRS3816 TASK 72-45-14-300-041 (REPAIR-041) or Repair, VRS3824 TASK 72-45-14-300-043 (REPAIR-043) and examine the cracks again. Reject if Step is not satisfied.

        4. Other than Step.

        1. Repair, VRS3816 TASK 72-45-14-300-041 (REPAIR-041) or Repair, VRS3824 TASK 72-45-14-300-043 (REPAIR-043).

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

        1. Two dents not more than 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 Step.

        1. Repair, VRS3816 TASK 72-45-14-300-041 (REPAIR-041) or Repair, VRS3824 TASK 72-45-14-300-043 (REPAIR-043).

    2. SUBTASK 72-45-14-220-081 Examine the Stage 1 HPT Blade (01-010) Blade Airfoil

    1. Refer to Figure.

      NOTE

      To find if the metallic base coat is present, use the heat tint examination in Step.

      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 base metallic coating

        1. Accept.

        2. Other than Step.

        1. Repair, VRS3816 TASK 72-45-14-300-041 (REPAIR-041) or Repair, VRS3824 TASK 72-45-14-300-043 (REPAIR-043).

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

        1. Nicked or chipped ceramic coating, unlimited in Locations 2, 3 and 5. Metallic undercoat must be present.

        1. Accept.

        2. Nicked or chipped ceramic coating in Location 1, no more than three on each side 0.0225 sqin (14.516 sqmm) or smaller, separated by a minimum of 0.200 in. (5.08 mm). Metallic undercoat must be present.

        1. Accept.

        3. Nicked or chipped ceramic coating, unlimited in Location 4. Metallic undercoat can be chipped in no more than two places that are 0.050 in. (1.27 mm) in diameter or equivalent area 0.002 sqin (1.29 sqmm) separated by 0.500 in. (12.70 mm) minimum.

        1. Accept.

        4. Nicked or chipped airfoil cooling holes are permitted to have 0.030 in. (0.76 mm) all around the holes, in addition to the limits given above.

        1. Accept.

        5. Other than Step thru Step.

        1. Repair, VRS3816 TASK 72-45-14-300-041 (REPAIR-041) or Repair, VRS3824 TASK 72-45-14-300-043 (REPAIR-043).

        6. Nicked or chipped coating after Step and limits are not met.

        1. Repair, VRS3816 TASK 72-45-14-300-041 (REPAIR-041) or Repair, VRS3824 TASK 72-45-14-300-043 (REPAIR-043).

          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.

        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 Step.

          1. Remove the coating, Repair, VRS3816 TASK 72-45-14-300-041 (REPAIR-041) or Repair, VRS3824 TASK 72-45-14-300-043 (REPAIR-043) and examine for cracks again. Reject if Step is not satisfied.

          3. Other than Step and Step.

          1. Reject.

        2. Cracks in Area B.

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

          1. Accept.

          2. Other than Step.

          1. Remove the coating, Repair, VRS3816 TASK 72-45-14-300-041 (REPAIR-041) or Repair, VRS3824 TASK 72-45-14-300-043 (REPAIR-043) and examine for cracks again. Reject if Step is not satisfied.

          3. Other than Step and Step.

          1. Reject.

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

        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 0.250 in. (6.35 mm) of the blade tip at Location 4

          1. Accept

          4. Two dents on the trailing edge at Location 2. The dents must not extend more than 0.100 in. (2.54 mm) along the blade span. The dents must not block any of the cooling air slots by more than 50 per cent

          1. Accept

        3. Other than Step and Step.

        1. Repair, VRS3816 TASK 72-45-14-300-041 (REPAIR-041) or Repair, VRS3824 TASK 72-45-14-300-043 (REPAIR-043).

    3. SUBTASK 72-45-14-220-082 Examine the Stage 1 HPT Blade (01-010) Underplatform Area

    1. Refer to Figure.

      2. Examine the blade underplatform area for cracks and corrosion.

        1. If the underplatform area contains no corrosion or cracks.

        1. Accept.

        2. Other than Step.

        1. Repair, VRS3702 TASK 72-45-14-300-030 (REPAIR-030).

      3. Examine the blade underplatform area to confirm the presence of the protective coating in Area 1 using the heat tint examination in Step.

        1. Protective coating is present in Area A.

        1. Accept.

        2. Other than Step.

        1. VRS3816 TASK 72-45-14-300-041 (REPAIR-041), or Repair, VRS3824 TASK 72-45-14-300-043 (REPAIR-043).

    4. SUBTASK 72-45-14-220-083 Examine the Stage 1 HPT Blade (01-010) Abrasive Tip

    1. Refer to Figure.

      2. Examine the blade abrasive tip for chips that expose base metal.

        1. Three or fewer chips that expose the base metal/tip interface at Location 2. These chips must not extend more than one-half of the airfoil tip width at that location and must not exceed 0.100 in. (2.54 mm) in maximum dimension. Each chip must be separated by at least 0.250 in. (6.35 mm).

        1. Accept.

        2. Any chips that expose the base metal/tip interface at Locations 1 and 3.

        1. Accept.

        3. Other than Step.

        1. Repair, VRS3810 TASK 72-45-14-300-040 (REPAIR-040) or Repair, VRS3816 TASK 72-45-14-300-041 (REPAIR-041) or Repair, VRS3824 TASK 72-45-14-300-043 (REPAIR-043).

      3. Examine the blade abrasive tip for cracks.

        1. One radial crack not more than 0.062 in. (1.58 mm).

        1. Accept.

        2. Other than Step.

        1. Repair, VRS3810 TASK 72-45-14-300-040 (REPAIR-040) or Repair, VRS3816 TASK 72-45-14-300-041 (REPAIR-041), or Repair, VRS3824 TASK 72-45-14-300-043 (REPAIR-043).

      4. 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. Repair, VRS3810 TASK 72-45-14-300-040 (REPAIR-040) or Repair, VRS3816 TASK 72-45-14-300-041 (REPAIR-041), or Repair, VRS3824 TASK 72-45-14-300-043 (REPAIR-043).

    5. SUBTASK 72-45-14-220-084 Examine the Stage 1 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 2P16372 Stage 1 HPT 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. Use the dial indicator to measure the distance from the end surface of the gage to the surface of the trailing edge pin.

          1. If the dimension is more than 2.729 in. (69.32 mm).

          1. Accept.

          2. Other than Step.

          1. Repair, VRS3810 TASK 72-45-14-300-040 (REPAIR-040) or Repair, VRS3816 TASK 72-45-14-300-041 (REPAIR-041) or Repair, VRS3824 TASK 72-45-14-300-043 (REPAIR-043).

    6. SUBTASK 72-45-14-220-062 Examine the Stage 1 HPT Blade (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. Repair, VRS3816 TASK 72-45-14-300-041 (REPAIR-041) or Repair, VRS3824 TASK 72-45-14-300-043 (REPAIR-043).

          NOTE

          An example of a crack is 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 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).

    7. SUBTASK 72-45-14-220-085 Examine the Stage 1 HPT Blade (01-010) Leading Edge Platform

    1. Refer to Figure.

      2. Examine the blade surface at Locations 2 and 3, for signs of rub with the stage 1 HPT duct segment seal or the stage 1 HPT vane platform.

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

        1. Accept.

        2. Other than Step.

        1. Repair, VRS3816 TASK 72-45-14-300-041 (REPAIR-041) or Repair, VRS3824 TASK 72-45-14-300-043 (REPAIR-043).

      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.

    8. SUBTASK 72-45-14-220-086 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 0.005 in. (0.127 mm) in depth on the platform where the blade damper touches the blade.

        1. Accept.

        2. Other than Step.

        1. Reject.

    9. SUBTASK 72-45-14-220-087 Examine the Stage 1 HPT Blade (01-010) Root Attachment Area

    1. Refer to Figure, Figure and Figure.

      2. Examine the blade root attachment area for erosion, corrosion and pitting at Location 2.

        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 except as noted below.

        1. Accept.

        2. Other than Step.

        1. Reject.

      3. Examine the blade root attachment area for fretting and galling at Location 2.

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

        1. Accept.

          NOTE

          An example of a load bearing tooth surface is shown at Location 4.

        2. Other than Step.

        1. Reject.

      4. Examine the blade root attachment area for contact wear that is not equal (tooth to tooth and side to side) at Location 2.

        1. Contact wear on the blade root that is not equal along the root tooth up to 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.

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

        1. Cracks, nicks or pitting.

        1. Reject.

        2. Cracks on the top serration.

        1. Repair, VRS3042 TASK 72-45-14-300-030 (REPAIR-030).

        3. Other than Step.

        1. Reject.

      6. Examine the blade underplatform area for corrosion and pitting.

        1. Any corrosion or pitting in Areas 6 or 13. Area 6 includes fillet radius of three damper posts and buttresses

        1. Repair, VRS3702 TASK 72-45-14-300-030 (REPAIR-030).

        2. Any quantity of corrosion or pitting in Area 7 of 0.010 in. (0.25 mm) or less in depth.

        1. Accept.

        3. Other than Step.

        1. Repair, VRS3702 TASK 72-45-14-300-030 (REPAIR-030).

        4. Any quantity of corrosion or pitting in Area 8 of 0.010 (0.25 mm) or less in depth.

        1. Accept.

        5. Any quantity of corrosion or pitting in Area 9 of 0.005 in. (0.13 mm) or less in depth.

        1. Accept.

        6. Any quantity of corrosion or pitting in Area 10 of 0.010 in. (0.25 mm) or less in depth if there are no linear indications.

        1. Accept.

        7. Any quantity of corrosion or pitting in Area 11 of 0.003 in. (0.07 mm) or less in depth.

        1. Accept.

        8. Other than Step, Step, Step or Step.

        1. Reject.

        9. Any corrosion, pitting or linear indications in Area 12.

        1. Reject.

    10. SUBTASK 72-45-14-220-088 Examine the Stage 1 HPT Blade (01-010) Root Area

    1. Refer to Figure and Figure.

      2. Examine the blade root area for cracks at Location 1. Use a white light and a 10X magnification to examine for cracks.

        1. Cracks.

        1. Reject.

      3. Examine the blade root area for pitting at Location 1.

        1. Up to 0.005 in. (0.127 mm).

        1. Accept.

        2. Other than Step.

        1. Reject.

    11. SUBTASK 72-45-14-220-067 Examine the Stage 1 HPT Blade Root Area

    1. Refer to Figure.

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

        1. Blends and dents not more than 0.100 in. (2.54 mm) in diameter and 0.005 in. (0.13 mm) in depth except in Locations 1 and 2 both sides.

        1. Accept.

        2. Blends and dents not more than 0.100 in. (2.54 mm) in diameter and 0.010 in. (0.25 mm) in depth on the root bottom at Location 3 and the root bottom edges.

        1. Accept.

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

        1. Accept.

        4. Other than Step, Step or Step.

        1. Reject.

        5. Sharp nicks.

        1. Repair, VRS3202 TASK 72-45-14-300-001 (REPAIR-001), or Repair, VRS3816 TASK 72-45-14-300-041 (REPAIR-041) or Repair, VRS3824 TASK 72-45-14-300-043 (REPAIR-043).

    12. SUBTASK 72-45-14-280-061 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 2100 deg F (1148.9 deg C) at Location 3, all other locations have a limit of 2050 deg F (1121.1 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 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 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 SPM TASK 70-02-03-220-501 and SPM TASK 70-02-11-220-501.

      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. (0.25 mm 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 in. to 0.015 in. (0.25 mm 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 2100 deg F (1148.9 deg C) at Location 3 or 2050 deg F (1121.1 deg C) at any other location that follows:

      1. Leading edge analysis area at Location 6.

      2. Mid chord analysis area at Location 5.

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

    13. SUBTASK 72-45-14-230-064-001 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 this procedure, do the procedure given in SUBTASK 72-45-14-230-064-002.

    1. Refer to Figure.

      Clean the part. Refer to TASK 72-45-14-100-000 (CLEANING-000).

      2. WARNING

        IT IS THE RESPONSIBILITY 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 deg F and 2000 deg F (1086 deg C 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 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.

    3. 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

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

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

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

      1. Heat the blade to between 1575 deg F and 1625 deg F (857 deg C and 885 deg C) in an oven and keep at this temperature for 32 hours. Refer to SPM TASK 70-37-27-370-501.

      2. Let the blade air cool.

    14. SUBTASK 72-45-14-230-064-002 Examine the Stage 1 HPT Blade (01-010) for Cracks

    1. CAUTION

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

      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 72-45-14-230-064-001.

      When you cannot stress relieve the blade, you must send the blade to the approved source that follows:

      PRATT and WHITNEY AFTERMARKET SERVICES (PWAS)

      Connecticut Airfoil Repair Operations (CARO)

      400 Main St., Well 11

      East Hartford, CT 06108-0969 USA

      Tel: (860) 565-3922

      Fax: (860) 557-8247

    15. SUBTASK 72-45-14-280-062 Examine the Stage 1 HPT Blade (01-010) Coating by Heat Tint

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

    2. CAUTION

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

      Clean the blade by 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 deg F to 1100 deg F (566 deg C and 593 deg C) in an oven (Air furnace) for 45 to 75 minutes.

        2. Heat tint the blade at 1275 deg F to 1325 deg F (691 deg C and 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 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. Repair, VRS3816 TASK 72-45-14-300-041 (REPAIR-041) or Repair, VRS3824 TASK 72-45-14-300-043 (REPAIR-043).

    16. SUBTASK 72-45-14-260-054 Examine the Stage 1 HPT Blade (01-010) for Internal Cracks and Unwanted Material by Radiographic Inspection

    1. Refer to 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 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 their 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 material are acceptable provided the size, density and location of the indication(s) has remained unchanged from step (2)(b). Refer to the limits in Table 801.

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

          1. Reject.

    17. SUBTASK 72-45-14-280-068 Examine the Stage 1 HPT Blade Assembly (01-010) by the Airflow Check

      NOTE

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

    1. Do the airflow check by Repair, VRS3701 TASK 72-45-14-300-029 (REPAIR-029).

    18. SUBTASK 72-45-14-230-060 Examine the Stage 1 HPT Blade (01-010) for Casting Flow Lines and Imperfections

    1. Refer to Figure.

      NOTE

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

      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

          All other inspection criteria apply.

      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.

          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).

      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. (1.77 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.

    19. SUBTASK 72-45-14-220-102 Examine the Stage 1 HPT Blade (01-010) for Blade Width Dimensions

      CAUTION

      YOU MUST DO AN INSPECTION FOR ALL THE SIXTY FOUR (64) BLADES INDIVIDUALLY. IF THE INDIVIDUAL INSPECTION IS UNSATISFACTOY, IT CAN CAUSE FIT PROBLEMS DURING ASSEMBLY PROCEDURE.

    1. Refer to Figure.

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

        1. If the dimension is between 0.882 (22.40 mm) and 0.890 in. (22.61 mm).

        1. Accept.

        2. Other than Step.

        1. Reject.

    20. Figure: Stage 1 HPT Blade Platform Inspection Locations

    Stage 1 HPT Blade Platform Inspection Locations

    Figure: Stage 1 HPT Blade Airfoil Inspection Locations

    Stage 1 HPT Blade Airfoil Inspection Locations

    Figure: Stage 1 HPT Blade Underplatform Coating Inspection Locations

    Stage 1 HPT Blade Underplatform Coating 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

    Sheet 1

    Legend
    Stage 1 HPT Blade Root and Attachment Area Inspection Locations

    Sheet 1

    Close

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

    Sheet 2

    Legend
    Stage 1 HPT Blade Root and Attachment Area Inspection Locations

    Sheet 2

    Close

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

    Sheet 3

    Legend
    Stage 1 HPT Blade Root and Attachment Area Inspection Locations

    Sheet 3

    Close

    Figure: Stage 1 HPT Blade Metal Temperature Analysis Locations

    Stage 1 HPT Blade Metal Temperature Analysis Locations

    Figure: Stage 1 HPT Blade Assembly Shot Peen Locations

    Stage 1 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 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 Casting Flow Line Inspection

    Stage 1 HPT Blade Assembly Casting Flow Line Inspection

    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 Dimensional Inspection for Blade Width

    Stage 1 HPT Blade Dimensional Inspection for Blade Width

Requirements After Job Completion

Follow-On Conditions

NONE
Change Type:

Revised the procedure to update typographical error. (19VC189)

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: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:81349
Enterprise Name:DELETED, SEE CAGE CODE 81348
Manufacturer Code:LOCAL
Enterprise Name:LOCALLY SUPPLIED
Link not Found
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: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 2P16372
Tool Name:IAE 2P16372 Stage 1 HPT Blade Length Gage
Manufacturer Code:0AM53
Tool Number:IAE 2P16508
Tool Name:IAE 2P16508 Reference card
Link not Found