TASK 72-45-14-200-001-B00 HPT Stage 1 Blade - Examine, Inspection-001

DMC:V2500-A0-72-45-1401-00B-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-B00 HPT Stage 1 Blade - Examine, Inspection-001

Effectivity

FIG/ITEM PART NO.

01-010

2A8321-002

01-010

2A8321-003

01-010

2A8321-004

01-010

2A8521-002

01-010

2A8521-003

01-010

2A8521-004

01-010

2A8521-005

01-010

2A8701-001

01-010

2A8701-002

01-010

2A9001

01-010

2A9101

01-010

2A9201

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.

VRS3484 Repair-011, contains a special cleaning and inspection procedure for the under-platform stress corrosion. You must do this repair in conjuction 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 Step or Step. 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 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 2P16408 Airflow master0AM53IAE 2P164081
IAE 2P16409 Airflow master0AM53IAE 2P164091
IAE 2P16439 Airflow master0AM53IAE 2P164391
IAE 2P16440 Airflow master0AM53IAE 2P164401
IAE 2P16446 Airflow master0AM53IAE 2P16446
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 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 05-234 CAST STEEL SHOT, HIGH HARDNESS, S110LOCALCoMat 05-234

Spares

NONE

Safety Requirements

NONE

Procedure

    1. SUBTASK 72-45-14-220-070 Examine the Stage 1 HPT Blade (01-010) Blade Platform Area

    1. Refer to Figure, Figure and Figure.

      NOTE

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

      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. Repair VRS3042, TASK 72-45-14-300-009 (REPAIR-009) or VRS3645, TASK 72-45-14-300-024 (REPAIR-024)

      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 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 (2)

        1. Reject

        4. Other than (1)

        1. Repair VRS3042, TASK 72-45-14-300-009 (REPAIR-009) or VRS3645, TASK 72-45-14-300-024 (REPAIR-014)

      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 (1)

        1. Repair VRS3042, TASK 72-45-14-300-009 (REPAIR-009) or VRS3645, TASK 72-45-14-300-024 (REPAIR-024)

      5. Examine the underplatform of the blade for cracks, Figure.

        1. Cracks which come from cooling holes, that are a maximum of 0.040 in. (1.02 mm) in length

        1. Repair VRS3616, TASK 72-45-14-300-022 (REPAIR-022)

        2. Cracks which come from cooling holes, that are a maximum of 0.080 in. (2.03 mm) in length

        1. Repair VRS3686, TASK 72-45-14-300-023 (REPAIR-023)

        3. Other than (1) or (2)

        1. Reject

    2. SUBTASK 72-45-14-220-071 Examine the Stage 1 HPT Blade (01-010) Airfoil

    1. Refer to Figure and Figure.

      NOTE

      To find if the base metal is shown, 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 coating

        1. Accept

        2. Other than (1)

        1. Repair VRS3042, TASK 72-45-14-300-009 (REPAIR-009) or VRS3645, TASK 72-45-14-300-024 (REPAIR-024)

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

        1. Nicked or chipped coating

        1. Repair VRS3042, TASK 72-45-14-300-009 (REPAIR-009) or VRS3645, TASK 72-45-14-300-024 (REPAIR-024)

        2. Nicked or chipped coating after Repair VRS3042, TASK 72-45-14-300-009 (REPAIR-009) or VRS3645, TASK 72-45-14-300-024 (REPAIR-024) has been done

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

          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 (a)

          1. Remove the coating, Repair VRS3042, TASK 72-45-14-300-009 (REPAIR-009) or VRS3645, TASK 72-45-14-300-024 (REPAIR-024) and examine for cracks again

          3. Other than (a) and (b)

          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 (a)

          1. Remove the coating, Repair VRS3042, TASK 72-45-14-300-009 (REPAIR-009) or VRS3645, TASK 72-45-14-300-024 (REPAIR-024) and examine for crack again

          3. Other than (a) and (b)

          1. Reject

      5. Examine the blade airfoil surfaces for additional cooling holes, Figure.

        1. If one additional cooling hole is in the leading edge showerhead lacation, Area A in the figure

        1. Accept

        2. If there is more than one additional hole, or if the hole is in a location other than Area A

        1. Reject

      6. 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 0.250 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 percent

          1. Accept

        3. Other than (1) and (2)

        1. Repair VRS3042, TASK 72-45-14-300-009 (REPAIR-009) or VRS3645, TASK 72-45-14-300-024 (REPAIR-024)

    3. SUBTASK 72-45-14-220-072 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 VRS3042, TASK 72-45-14-300-009 (REPAIR-009) or VRS3645, TASK 72-45-14-300-024 (REPAIR-024)

          NOTE

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

        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 0.200 in. (5.08 mm) (the sum of the individual widths of multiple chips must be less than or equal to 0.200 in. (5.08 mm) and there is no base metal shown on the airfoil base metal/tip interface at location 6

        1. Accept

          NOTE

          Example of a chip is shown at location 7.

        4. Other than (2) or (3)

        1. Repair VRS3042, TASK 72-45-14-300-009 (REPAIR-009) or VRS3645, TASK 72-45-14-300-024 (REPAIR-024)

      3. Examine the blade abrasive tip for cracks at location 3.

        1. One radial crack up to 0.0620 in. (1.58 mm)

        1. Accept

        2. Other than (1)

        1. Repair VRS3042, TASK 72-45-14-300-009 (REPAIR-009) or VRS3645, TASK 72-45-14-300-024 (REPAIR-024)

      4. Examine the blade abrasive tip for taper on the trailing edge at location 5.

        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 (1)

        1. Repair VRS3042, TASK 72-45-14-300-009 (REPAIR-009) or VRS3645, TASK 72-45-14-300-024 (REPAIR-024)

    4. SUBTASK 72-45-14-220-073-B00 Examine the Stage 1 HPT Blade Assembly (01-010) (PN 2A8321-002, 2A8321-003, 2A8321-004, 2A8521-002, 2A8521-003, 2A8521-004, 2A8521-005, 2A8701-002, 2A9001, 2A9101 and 2A9201) 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 2.7260 in. (69.240 mm)

          1. Accept

          2. Other than (a)

          1. Repair VRS3042, TASK 72-45-14-300-009 (REPAIR-009) or VRS3645, TASK 72-45-14-300-024 (REPAIR-024)

    5. SUBTASK 72-45-14-220-074 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. Repairs VRS3042, TASK 72-45-14-300-009 (REPAIR-009) or VRS3645, TASK 72-45-14-300-024 (REPAIR-024)

          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 VRS3042, TASK 72-45-14-300-009 (REPAIR-009) or VRS3645, TASK 72-45-14-300-024 (REPAIR-024)

      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) or Repair VRS3042, TASK 72-45-14-300-009 (REPAIR-009)

          NOTE

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

    6. SUBTASK 72-45-14-220-075 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 0.0050 in. (0.127 mm)

        1. Accept

        2. Other than (1)

        1. Repair VRS3042, TASK 72-45-14-300-009 (REPAIR-009) or VRS3645, TASK 72-45-14-300-024 (REPAIR-024)

      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 72-45-14-220-076 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 0.0050 in. (0.127 mm) in depth on the platform where the blade damper touches the blade

        1. Accept

        2. Other than (1)

        1. Reject

    8. SUBTASK 72-45-14-220-077 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 0.0050 in. (0.127 mm) in depth when the surface is not rough and there are no cracks, crazing, ridges or depressions except as noted in Step 13.E.

        1. Accept

        2. Other than (1)

        1. Reject

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

        1. Not more than 0.0050 in. (0.127 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 5.

        2. Other than (1)

        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 4.

        1. Contact wear on the blade root that is not equal along the root tooth not more than 0.0050 in. (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.

      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. Nicks or pitting

        1. Reject

        2. Cracks on the top serration

        1. Repair VRS3484, TASK 72-45-14-300-011 (REPAIR-011)

        3. Other than (2)

        1. Reject

      6. Examine the blade underplatform area for corrosion and pitting by Figure and Figure by the following requirements:

        1. Any corrosion or pitting in Areas 6 and 13

        1. Repair VRS3484, TASK 72-45-14-300-011 (REPAIR-011)

        2. Any quantity of corrosion or pitting in Areas 7 of 0.0100 in. (0.254 mm) or less in depth

        1. Accept

        3. Other than (2)

        1. Repair VRS3484, TASK 72-45-14-300-011 (REPAIR-011)

        4. Any quantity of corrosion or pitting in Area 8 of 0.0100 in. (0.254 mm) or less in depth

        1. Accept

        5. Any quantity of corrosion or pitting in Area 9 of 0.0050 in. (0.127 mm) or less in depth

        1. Accept

        6. Any quantity of corrosion or pitting in Area 10 of 0.0100 in. (0.254 mm) or less in depth provided no linear indications are present

        1. Accept

        7. Any quantity of corrosion or pitting in Area 11 of 0.0030 in. (0.076 mm) or less in depth

        1. Accept

        8. Other than (4), (5), (6) or (7)

        1. Reject

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

        1. Reject

    9. SUBTASK 72-45-14-220-078 Examine the Stage 1 HPT Blade (01-010) Root Area

    1. Refer to Figure, Figure, 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 0.0050 in. (0.127 mm)

        1. Accept

        2. Other than (1)

        1. Reject

      4. Examine the bottom root cooling slots.

      1. Refer to Step for crack limits.

    10. SUBTASK 72-45-14-220-079 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 up to 0.1000 in. (2.54 mm) in diameter and 0.005 in. (0.127 mm) in depth except in locations 1 and 2 both sides

        1. Accept

        2. Blends and dents up to 0.100 in. (2.54 mm) in diameter and 0.0100 in. (0.254 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 (1), (2) or (3)

        1. Reject

        5. Sharp nicks

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

    11. SUBTASK 72-45-14-280-056 Examine the Stage 1 HPT Blade (01-010) for Overtemperature

      NOTE

      Blades that were at temperatures more than the limit of 2150 deg F (1176.7 deg C) for a short time will cause a change in the alloy microstructure of the blade.

      NOTE

      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 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 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 0.0100 to 0.0150 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 0.0100 to 0.0150 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 2150 deg F (1176.7 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.

    12. SUBTASK 72-45-14-230-053-001 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 Step.

    1. Refer to Figure.

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

      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-relieve the blade.

        1. CAUTION

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

          Heat the blade by one of the methods that follow:

        1. Heat the blade to between 1950 and 2000 deg F (1086 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 GASCoMat 03-117 ARGON GAS or CoMat 03-118 ARGON GAS. Refer to the SPM TASK 70-37-26-370-501.

        2. Heat the blade to between 1600 and 1975 deg F (871 and 1079 deg C) for 40 minutes with a minimum of seven minutes at 1950 and 2000 deg F (1066 and 1093 deg C).

      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. Examine the root cooling slots carefully. See Figure.

        1. Cracks in areas 1 and 2.

          1. There is a maximum of one crack with a maximum length of 0.020 in. (0.51 mm). The crack can start from a fillet radius or a cooling slot sidewall edge.

          1. Accept

          2. Back-to-back cracks

          1. Reject

        2. Cracks in areas 3 and 4.

          1. There is a maximum of two cracks of any combination with a maximum length of 0.020 in. (0.51 mm) for each crack. Cracks are separated by a minimum of 0.100 in. (2.54 mm). There is only one crack from each cooling slot fillet radius.

          1. Accept

          2. Other than (a)

          1. Reject

    6. If you find any crack indications that are more than the limits given above, make a temporary mark on the indications with one of the approved temporary markers in the SPM TASK 70-09-00-400-501.

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

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

      1. Heat the blade to between 1575 and 1625 deg F (857 and 885 deg C) in a vacuum or argon atmosphere and keep at this temperature for 32 hours. Refer to the SPM TASK 70-37-27-370-501 (IAE 1480).

      2. Let the blade air cool at a minimum temperature of 10 deg F (6 deg C)/ minute to 1200 deg F (649 deg C).

    13. SUBTASK 72-45-14-230-053-002 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 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

    14. SUBTASK 72-45-14-280-057 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 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 and 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 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 VRS3042, TASK 72-45-14-300-009 (REPAIR-009) or VRS3645, TASK 72-45-14-300-024 (REPAIR-024)

    15. SUBTASK 72-45-14-260-052 Examine the Stage 1 HPT Blade (01-010) for Internal Cracks and Unwanted Material by Radiographic Inspection

    1. Refer to Figure, 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 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 Figure and Figure.

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

          1. Reject

    16. SUBTASK 72-45-14-280-067 Examine the Stage 1 HPT Blade Assembly (01-010) by Airflow Check

      NOTE

      Do all the 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 VRS3712 TASK 72-45-14-300-033.

    17. SUBTASK 72-45-14-280-071 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.

    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

      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 0.0300 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 0.0020 in. (0.051 mm) and depth of 0.0010 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 0.0700 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.

    19. SUBTASK 72-45-14-220-101 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 0.883 (22.43 mm) and 0.889 in. (22.58 mm)

        1. Accept

        2. If the minimum dimension is 0.882 in. (22.40 mm) and maximum dimension is 0.890 in. (22.61 mm)

        1. Permitted for select fit only, if the fit limits at Location 1552 are in the limits

        3. Other than (1) or (2)

        1. Reject

    20. Figure: Stage 1 HPT Blade (For PN's see Table, CONFIG-002) Platform Inspection Locations

    Stage 1 HPT Blade (For PN's see Table, CONFIG-002) Platform Inspection Locations

    Figure: Stage 1 HPT Blade (2A8521-001 and 2A8801) Platform Inspection Locations

    Stage 1 HPT Blade (2A8521-001 and 2A8801) Platform Inspection Locations

    Figure: Stage 1 HPT Blade Crack Inspection

    Stage 1 HPT Blade Crack Inspection

    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

    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 Root Bottom Inspection Areas for Root Rip Cracks

    Sheet 4

    Legend
    Stage 1 HPT Blade Root Bottom Inspection Areas for Root Rip Cracks

    Sheet 4

    Close

    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: 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 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: Excess Metal and Foreign Material Limits (after Cleaning)

    Excess Metal and Foreign Material Limits (after Cleaning)

    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
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: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 2P16372
Tool Name:IAE 2P16372 Stage 1 HPT Blade Length Gage
Manufacturer Code:0AM53
Tool Number:IAE 2P16408
Tool Name:IAE 2P16408 Airflow master
Manufacturer Code:0AM53
Tool Number:IAE 2P16409
Tool Name:IAE 2P16409 Airflow master
Manufacturer Code:0AM53
Tool Number:IAE 2P16439
Tool Name:IAE 2P16439 Airflow master
Manufacturer Code:0AM53
Tool Number:IAE 2P16440
Tool Name:IAE 2P16440 Airflow master
Manufacturer Code:0AM53
Tool Number:IAE 2P16446
Tool Name:IAE 2P16446 Airflow master
Manufacturer Code:0AM53
Tool Number:IAE 2P16508
Tool Name:IAE 2P16508 Reference card
Manufacturer Code:LOCAL
Tool Number:Oven
Tool Name:Oven