Preliminary Requirements

Procedure

1. SUBTASK 72-45-32-220-112 Do a Permeability Inspection of the Stage 2 HPT blade Assembly Internal Airfoil Surfaces

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

   1. Refer to Figure, Figure and Figure.

      NOTE

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

   2. This permeability inspection is to find sulfidation distress on the internal airfoil surfaces for the HPT blades. This procedure can only be used on blades that are not installed in the rotor and have not been cleaned.

   3. Information on the Permeability Probes.

      1. PN 1.069-01-3001 permeability probe is used for this inspection procedure.

         NOTE

         1. It is recommended that you read the Magnetoscop 1.069 description and operation instruction manual before you do this inspection.

         2. If you use the older permeability probes to do this inspection, PN 1.005-1522 permeability probe provides a 1X sensitivity or PN 1.005-1532 permeability probe has a 10X sensitivity designed for the Magnetoscop 1.067 and 1.068 models, it will be necessary to use a PN 9064001 probe adapter with the Magnetoscop 1.069 model.

         1. Only remove the probe protective cap from the probe to calibrate and take the inspection measurements.

         2. PN 1.067-101-12 reference standard is located in the cover of the Magnetoscop. Do not use any other reference standard.

            1. This inspection uses the comparison method to find the presence of the internal sulfidation and requires the use of the reference standard with a permeability (Mu) between 1.4 and 1.5.

            2. Do not use any other reference standard.

         3. Use a CoMat 06-110 PENCIL or CoMat 06-111 PENCIL to mark the HPT blades. Refer to the SPM TASK 70-09-01-400-501 for the procedure to temporary mark the parts.

      2. Magnetoscop Calibration Procedure.

         1. 

            CAUTION

            DO NOT PERMIT THE PERMANENT MAGNET OF THE PROBE TO BECOME DEMAGNETIZED BY BEING EXPOSED TO MAGNETIC MATERIAL, PERMANENT MAGNETS OR STRONG ALTERNATING CURRENTS.

            

            CAUTION

            REMOVE THE PROTECTIVE CAP ON THE PROBE END ONLY DURING THE CALIBRATION PROCEDURE AND WHEN MEASUREMENTS ARE TO BE TAKEN DURING THE INSPECTION.

            NOTE

            The inspection area must be free from magnetic materials, permanent magnets and strong alternating current fields such as electric motors which will influence the meter needle deflection.

            Put the Magnetoscop on a suitable work bench with a non-magnetic work surface and remove the top cover.

         2. Connect the permeability probe to the Magnetoscop field intensity meter.

            NOTE

            The Magnetoscop will find what type of probe is being used. If one of the old Magnetoscop 1.067 or 1.068 probes is used, a 1.069 probe adapter PN 9064001 will be needed to connect the probe to the unit. A menu on the magnetoscop will give a list of probes. You can then select the applicable probe to use. If you use the new probe designed for the Magnetoscop 1.069 model, the probe will be detected automatically.

         3. Apply power to the Magnetoscop and permit the meter to warm up for ten minutes.

         4. Press the DC/AC/PERM (MODE) button until the instrument displays that it is in the Permeability Comparison mode.

         5. Press the RANGE button and set the range so that the Magnetoscop will display readings between 1.000 to 2.000 Mu.

         6. Press the MENU button and select Calibration from the main menu.

            NOTE

            The Magnetoscop will then adjust the offset of the system automatically. This can take up to one minute to complete. The calibration menu will permit you to make another selection once the offset has been completed.

         7. Select OFFSET ADJUST from the calibration menu.

         8. Select PERM PROBE ZERO ADJUST from the calibration menu.

            1. Adjust the thumb wheel adjustment or screw adjustment on the probe until the display is as close to zero as you can get.

            2. Exit the menu when completed.

         9. Select PERMEABILITY CALIBRATION from the calibration menu.

            1. Input the calibration value from the reference standard into the Magnetoscop display. Do not press the ENTER key.

         10. Put the PN 1.067-101-12 reference standard in an area away from any permeable materials or magnetic fields.

         11. Place the probe element on the center of the probe body perpendicular to the contact surface of the standard.

         12. Press the ENTER key on the Magnetoscop.

         13. The Magnetoscop will then calibrate to the value input from the reference standard.

         14. When completed, the display will return to the calibration menu.

         15. Exit from the calibration menu and the calibration is completed.

         16. When the Magnetoscop is removed from the standard, hold the Magnetoscop in the air.

             1. The reading on the Magnetoscop must be 1.000 +/- 0.005 Mu.

             2. If you do not get this reading, do the calibration procedure again.

         17. The permeability probe calibration must be checked at the start and end of each inspection sequence or if the inspection sequence has been interrupted.

      3. Permeability Inspection Procedure.

         1. 

            CAUTION

            PERMEABILITY LIMITS WERE ESTABLISHED FOR SERVICE RUN BLADE CONDITIONS BEFORE TASK 72-45-32-100-003, CLEANING-003 IS COMPLETED ON THE BLADES. DO NOT CLEAN THE BLADE AND THE BLADE INTERNAL CAVITIES BEFORE YOU DO THIS INSPECTION. CLEANING CAN REMOVE THE SULFIDATION PRODUCT AND REDUCE THE PERMEABILITY VALUE. THIS WILL CHANGE THE CALIBRATED REALTIONSHIP BETWEEN THE PERMEABILITY AND REMAINING BLADE WALL THICKNESS. THIS WILL RESULT IN BLADES WITH WALL THICKNESS THAT ARE NOT ACCEPTABLE TO CONTINUE-IN-SERVICE.

         2. Remove loose dirt and deposits from only the external surface of the blade which could cause the meter needle to deflect. Use a soft bristle brush.

         3. Keep the probe perpendicular to the airfoil surface. Traverse the permeability probe tip along the external surface to be examined and monitor the readings for permeability indications.

         4. At a constant speed of 0.250 to 0.500 in. (6.4 to 12.7 mm) per second, traverse the probe along each of the airfoil surfaces.

         5. If you find permeability indications, locate the area which has the maximum permeability.

         6. Record the maximum permeability at the corresponding location on the airfoil surface. Use only CoMat 06-110 PENCIL or CoMat 06-111 PENCIL to mark the blade airfoil.

            1. Blades with a permeability value of 1.04 or less.

               1. Accept

            2. Blades with a permeability value more than 1.04.

               1. Reject

2. SUBTASK 72-45-32-220-053 Examine the Stage 2 HPT Blade Assembly (01-010) Blade Platform Area

   NOTE

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

   1. Refer to Figure.

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

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

         1. Accept

      2. Other than (1)

         1. Repair, VRS3240 TASK 72-45-32-300-001 (REPAIR-001) or VRS3242 TASK 72-45-32-300-002 (REPAIR-002) or VRS3053 TASK 72-45-32-300-011 (REPAIR-011) or VRS3496 TASK 72-45-32-300-010 (REPAIR-010) or VRS3243 TASK 72-45-32-300-003 (REPAIR-003) or VRS3494 TASK 72-45-32-300-009 (REPAIR-009)

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

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

         1. Accept

            NOTE

            The knife edge is not included in location 3.

      2. Cracks at the knife edge location 1.

         1. Repair, VRS3240 TASK 72-45-32-300-001 (REPAIR-001) or VRS3242 TASK 72-45-32-300-002 (REPAIR-002) or VRS3053 TASK 72-45-32-300-011 (REPAIR-011) or VRS3496 TASK 72-45-32-300-010 (REPAIR-010) or VRS3243 TASK 72-45-32-300-003 (REPAIR-003) or VRS3494 TASK 72-45-32-300-009 (REPAIR-009)

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

         1. Repair, VRS3240 TASK 72-45-32-300-001 (REPAIR-001) or VRS3242 TASK 72-45-32-300-002 (REPAIR-002) or VRS3053 TASK 72-45-32-300-011 (REPAIR-011) or VRS3496 TASK 72-45-32-300-010 (REPAIR-010) or VRS3243 TASK 72-45-32-300-003 (REPAIR-003) or VRS3494 TASK 72-45-32-300-009 (REPAIR-009)

      4. Cracks in the airfoil/platform fillet.

         1. Reject

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

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

         1. Accept

      2. Other than Step.

         1. Repair, VRS3240 TASK 72-45-32-300-001 (REPAIR-001) or VRS3242 TASK 72-45-32-300-002 (REPAIR-002) or VRS3053 TASK 72-45-32-300-011 (REPAIR-011) or VRS3496 TASK 72-45-32-300-010 (REPAIR-010) or VRS3243 TASK 72-45-32-300-003 (REPAIR-003) or VRS3494 TASK 72-45-32-300-009 (REPAIR-009)

      3. Dent in the airfoil/platform radius.

         1. Reject

3. SUBTASK 72-45-32-220-054 Examine the Stage 2 HPT Blade Assembly (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 at locations 1 and 2, for burned areas, corrosion and erosion, Figure.

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

         1. Accept

      2. Other than Step.

         1. Repair, VRS3240 TASK 72-45-32-300-001 (REPAIR-001) or VRS3242 TASK 72-45-32-300-002 (REPAIR-002) or VRS3053 TASK 72-45-32-300-011 (REPAIR-011) or VRS3496 TASK 72-45-32-300-010 (REPAIR-010) or VRS3243 TASK 72-45-32-300-003 (REPAIR-003) or VRS3494 TASK 72-45-32-300-009 (REPAIR-009)

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

      1. Chipped and nicked coating.

         1. Repair, VRS3240 TASK 72-45-32-300-001 (REPAIR-001) or VRS3242 TASK 72-45-32-300-002 (REPAIR-002) or VRS3053 TASK 72-45-32-300-011 (REPAIR-011) or VRS3496 TASK 72-45-32-300-010 (REPAIR-010) or VRS3243 TASK 72-45-32-300-003 (REPAIR-003) or VRS3494 TASK 72-45-32-300-009 (REPAIR-009)

            NOTE

            Refer to Step for cracks on the trailing edge.

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

      1. Cracks

         1. Repair, VRS3240 TASK 72-45-32-300-001 (REPAIR-001) or VRS3242 TASK 72-45-32-300-002 (REPAIR-002) or VRS3053 TASK 72-45-32-300-011 (REPAIR-011) or VRS3496 TASK 72-45-32-300-010 (REPAIR-010) or VRS3243 TASK 72-45-32-300-003 (REPAIR-003) or VRS3494 TASK 72-45-32-300-009 (REPAIR-009)

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

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

         1. Up to a depth of 0.005in. (0.127 mm).

         2. There is no base metal shown.

         3. There is a smooth bottom.

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

         5. At a location that is not less than 0.100in. (2.54 mm) from the blade platform at location 1.

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

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

         1. Two dents on each side of the concave and convex airfoil surfaces at location 2.

            1. Accept

         2. Two dents on each side of the concave and convex airfoil surfaces at location 3.

            1. Accept

         3. Any amount of dents on the leading edge at location 5.

            1. Accept

      3. Other than Step or Step.

         1. Repair, VRS3240 TASK 72-45-32-300-001 (REPAIR-001) or VRS3242 TASK 72-45-32-300-002 (72-45-32, REPAIR 002 or VRS3053 TASK 72-45-32-300-011 (REPAIR-011) or VRS3496 TASK 72-45-32-300-010 (REPAIR-010) or VRS3243 TASK 72-45-32-300-003 (REPAIR-003) or VRS3494 TASK 72-45-32-300-009 (REPAIR-009)

4. SUBTASK 72-45-32-220-055 Examine the Stage 2 HPT Blade Assembly (01-010) Abrasive Tip

   NOTE

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

   1. Refer to: Figure.

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

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

         1. Repair, VRS3496 TASK 72-45-32-300-010 (REPAIR-010) or VRS3494 TASK 72-45-32-300-009 (REPAIR-009) or VRS3243 TASK 72-45-32-300-003 (REPAIR-003)

            NOTE

            The base metal/tip interface is shown at location 4.

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

         1. Accept

      3. One or more chips at location 2 where the sum of all the chip widths is a maximum of 0.200in. (5.08 mm) in width and there is no base metal shown on the base metal/tip interface at location 4.

         1. Accept

            NOTE

            Example of a chip is shown at location 5.

      4. Other than Step.

         1. Repair, VRS3496 TASK 72-45-32-300-010 (REPAIR-010) or VRS3494 TASK 72-45-32-300-009 (REPAIR-009) or VRS3243 TASK 72-45-32-300-003 (REPAIR-003)

5. SUBTASK 72-45-32-220-070 Examine the Stage 2 HPT Blade Assembly (01-010) Blade Length

   1. Refer to Figure.

      NOTE

      If the blades were repaired before, a repair code will be marked on the blade root area. Some code will have ten digits or more before the code.

      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.

   2. Examine the front and rear blade root surface at locations 2 and 3, for the repair code(s) that are marked on the blade.

      1. No code.

      2. R

      3. RR

      4. RT

      5. RTT

      6. T

      7. TT.

      8. TR

      9. TTR

      10. RRTT

      11. K5

      12. K10

      13. L5

      14. L10

      15. M

      16. M5

      17. M10

      18. N

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

      1. Install the blade assembly into the IAE 2P16358 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. Put the three pins of the gage on the blade tip.

      3. Set the dial indicator to zero while it is against the end surface of the gage.

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

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

            1. Accept

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

            1. Accept

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

            1. Accept

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

            1. Accept

         5. Other than (a) through (d).

            1. Repair, VRS3496 TASK 72-45-32-300-010 (REPAIR-010) or VRS3494 TASK 72-45-32-300-009 (REPAIR-009) or VRS3243 TASK 72-45-32-300-003 (REPAIR-003)

   4. Examine the blades that you suspect have incorrect marking.

      1. A blade set is suspect if:

         1. The set has any blades with negative stretch readings in excess of minus 0.005 in. (minus 0.127 mm) (minus 0.006 in. (minus 0.154 mm)), (minus 0.010 in. (minus 0.254 mm)) etc.

         2. There are blades which were rejected by the blade stretch measurement technique in TASK 72-45-32-200-001-A00.

      2. In a suspect set of blades, individual suspect blades are defined as:

         1. All blades in the set that have any negative stretch.

         2. All blades in the set that have positive stretch that is more than 0.010 in. (0.254 mm).

         3. All blades in the set that have more than three times the average stretch of the non-suspect blades in the set.

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

6. SUBTASK 72-45-32-220-091 Examine the Stage 2 HPT Blade Assembly (01-010) Blade Length

   NOTE

   This procedure applies only to first time repair blades.

   1. Refer to Figure.

   2. Find the measured length of the blade by the procedure given in this TASK.

      1. Make a note of airfoil thinning.

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

         1. 3.657 in. would be read 657.

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

      4. Measure the complete set of blades as directed in the three steps given above.

      5. Find which blades in the set are suspect.

         1. Do a statistical analysis on this initial set of growth readings to find which measurements will be considered suspect and those that are not suspect.

         2. Suspect blade measurements must not be evaluated again to reduce the quantity of suspect parts in the set.

   3. Find the quantity of suspect readings.

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

         1. Calculate the average stretch for the non-suspect blades.

         2. Define a lot of standard, non-suspect blades (a minimum of 15 parts). Measure the dimension from the top edge of the second trailing edge slot in from the tip to the bottom edge of the second trailing edge slot in from the platform as shown in Figure, for the lot.

         3. Find the average of the values you measured in the step above, subtract the average stretch of the non-suspect blades. This is the trailing edge base dimension.

            Example: A non-suspect blade lot trailing edges average 2.155 in. Average growth of the non-suspect blades is 0.003 in. The trailing edge base dimension is set at 2.152 in.

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

         5. Subtract the trailing edge base dimension from the trailing edge dimension of each suspect blade to calculate the growth of each suspect blade.

            Example: A non-suspect blade lot has an average growth of 0.003 in. (0.076 mm). The trailing edge base dimension is 2.152 in. The suspect blade trailing edge measures 2.154 in., so the calculated growth of the suspect blade is 0.002 in. (0.051 mm) (0.001 in. (0.025 mm)) less than the average established by the non-suspect blades in the set.

            If the calculated growth is 0.010 in. (0.254 mm) or less, do steps (3) and (4) below. Negative calculated growth must be considered zero growth.

            If the calculated growth is more than 0.010 in. (0.254 mm), scrap the part.

      2. If 75 per cent or more of the blades in the set are suspect, or if the set is very small (less than a total of 10 blades), do the steps that follow:

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

         2. Subtract the standard trailing edge base dimension of 2.149 in. from the trailing edge dimension of each suspect blade to calculate the growth of each suspect blade.

            Example: A second stage HPT blade has a base trailing edge dimension that is 2.149 in. The suspect blade trailing edge measures 2.152 in., so the calculated growth of the suspect blade is 0.003 in. (0.076 mm).

         3. Use a locally fabricated tool based on a sample part to confirm the standard trailing edge base dimension during inspection.

         4. If the calculated growth is 0.010 in. (0.254 mm) or less, do steps (3) and (4) below. Negative calculated growth must be considered zero growth.

         5. If the calculated growth is more than 0.010 in. (0.254 mm), scrap the part.

      3. Subtract the calculated growth from the measured length to find the Original Equipment Manufacturers (OEM) length of a suspect blade.

         Example: A blade measures 3.459 in., but the OEM length is marked 436 (3.436 in.). The calculated growth of the blade is determined to be 0.002 in. (0.051 mm). The initial blade marking should be 457.

      4. Make a mark on the suspect blades only, of the calculated length from the step above. Mark the last three digits of the measurements, rounded to the nearest 0.001 in. For example, if the length were 3.657 in., mark 657. Cross out the initial marked length. Use the vibro-peen or dot-peen method. Refer to the SPM TASK 70-09-00-400-501. Make a mark in the same area as the initial mark.

      5. Scrap all blades with true growth that is more than 0.010 in. (0.254 mm).

7. SUBTASK 72-45-32-220-056 Examine the Stage 2 HPT Blade Assembly (01-010) Trailing Edge

   1. Refer to: Figure

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

      1. Cracks at the trailing edge at location 3

         1. Repair, VRS3240 TASK 72-45-32-300-001 (REPAIR-001) or VRS3242 TASK 72-45-32-300-002 (REPAIR-002) or VRS3053 TASK 72-45-32-300-011 (REPAIR-011) or VRS3496 TASK 72-45-32-300-010 (REPAIR-010) or VRS3243 TASK 72-45-32-300-003 (REPAIR-003) or VRS3494 TASK 72-45-32-300-009 (REPAIR-009)

            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

            NOTE

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

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

   4. 

      CAUTION

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

      NOTE

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

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

8. SUBTASK 72-45-32-220-057 Examine the Stage 2 HPT Blade Assembly (01-010) Leading and Trailing Edge Platform

   1. Refer to: Figure

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

      1. Rub.

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

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

               NOTE

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

         2. Other than (a)

            1. Reject

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

      1. Curling

         1. Reject

            NOTE

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

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

      1. Wear.

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

            1. Accept

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

            1. Accept

         3. Other than (a) and (b)

            1. Reject

9. SUBTASK 72-45-32-220-058 Examine the Stage 2 HPT Blade Assembly (01-010) Damper Contact Area

   1. Refer to: Figure

   2. Examine the blade damper contact area for wear.

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

         1. Accept

      2. Other than (1)

         1. Reject

10. SUBTASK 72-45-32-220-059 Examine the Stage 2 HPT Blade Assembly (01-010) Blade Root Attachment Area

    1. Refer to: Figure and Figure

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

       1. Refer to locations and limits in referenced figures

          1. Accept. Refer to Figure and Figure

       2. Other than (1)

          1. Repair, VRS3595 TASK 72-45-32-200-022,(REPAIR-022)

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

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

          1. Accept

       2. Other than (1)

          1. Repair, VRS3595 TASK 72-45-32-200-022,(REPAIR-022)

    4. Examine the blade root attachment area for nicks and cracks at locations 2, 4 and 5. Use a white light and a 10X magnification to examine for cracks.

       1. Cracks or nicks

          1. Repair, VRS3240 TASK 72-45-32-300-001 (REPAIR-001) or Repair, VRS3595 TASK 72-45-32-300-022 (REPAIR-022)

    5. 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 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 area for blends and dents.

       1. Up to 0.005in. (0.127 mm) with rounded edges, corners and bottoms at locations 4 and 5. 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 6. 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 7)

          1. Accept

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

          1. Repair, VRS3240 TASK 72-45-32-200-001 (REPAIR-001)

11. SUBTASK 72-45-32-220-094 Examine the Stage 2 HPT Blade Assembly (01-010) Top Most Serration

    1. Refer to: Figure

    2. Do a visual inspection of the blade root top most serration with a white light and no magnification.

       1. 0.005 in. (0.127 mm) in depth linear wear indication extending across the length of the top most serration of the blade root, at the edge of the disk contact pattern, on the concave and/or convex side

          1. Acceptable if it does not continue into the break edge. Refer to Figure

    3. Do a visual inspection of the blade root top most serration with a white light and 10X magnification.

       1. Indications are limited to the wear groove of the top serration only on convex and/or concave sides

          1. Acceptable. Refer to Figure

       2. Tight hairline cracks which appear to be shallow in depth or linear indications (linked and/or unlinked) up to 0.500 in. (0.127 mm) total length of the serration on either the concave and/or convex sides

          1. Acceptable

          2. One or more indications:

             1. They do not continue into the break edge or onto the front or rear face of the attachment

                1. Acceptable

             2. They are not in the fillet radius

                1. Acceptable

    4. Do a fluorescent penetrant inspection of the serration on both the concave and convex side of the blade by the SPM TASK 70-23-02-230-501 (normal sensitivity) or SPM TASK 70-23-08-230-501.

       1. Indications are limited to the wear groove of the top serration only on convex and concave sides

          1. Acceptable. Refer to Figure

       2. Tight hairline cracks which appear to be shallow in depth or linear indications (linked and/or unlinked) up to 0.500 in. (0.127 mm) total length of the serration on either the concave and/or convex sides

          1. Acceptable

          2. One or more indications:

             1. They do not continue into the break edge or onto the front or rear face of the attachment

                1. Acceptable

             2. They are not in the fillet radius

                1. Acceptable

                   NOTE

                   All other applicable overhaul manual inspection criteria apply.

12. SUBTASK 72-45-32-220-068 Examine the Stage 2 HPT Blade Assembly (01-010) Root Metering Plate Welds

    1. Refer to: Figure

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

       1. One crack on each blade

          1. Accept

       2. More than one crack on each blade

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

13. SUBTASK 72-45-32-280-051 Examine the Stage 2 HPT Blade Assembly (01-010) for Overtemperature

    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.

    1. Refer to Figure.

    2. Examine one blade assembly for overtemperature by metallurgical analysis if the engine was removed for EGT overlimit.

    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 mark 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, refer to 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 surfaces 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 0.015in. (0.254 to 0.381 mm) from the coating to the base metal interface.

       2. Examine the blade root sample for metal temperature at location 7. This location must be nearest to the inner diameter of the blade. The correct point to be examined under magnification must be 0.010 to 0.015in. (0.254 to 0.381 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 2 HPT blade assemblies in the engine if the metal temperature is higher than 2050 deg F (1121 deg C) at any of the locations that follow.

       1. Leading edge analysis area at location 6.

       2. Mid-chord analysis area at location 5.

       3. Trailing edge analysis area at location 3.

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

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

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

    1. Refer to Figure.

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

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

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

       1. Cracks.

          1. Reject blades and contact IAE Technical Services.

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

15. SUBTASK 72-45-32-230-052-002 Examine the Stage 2 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 in Step.

    1. Clean the part. Refer to TASK 72-45-32-100-003 (CLEANING-003, CONFIG-01).

       NOTE

       Removal of root cover plate and cleaning the blade may have been already performed per the previous step.
    2. 
       WARNING
       IT IS THE RESPONSIBILITY OF THE OPERATOR TO OBTAIN AND OBSERVE THE MANUFACTURERS MATERIAL SAFETY DATA SHEETS FOR CONSUMABLE MATERIALS INFORMATION SUCH AS HAZARDOUS INGREDIENTS, PHYSICAL/CHEMICAL CHARACTERISTICS, FIRE, EXPLOSION, REACTIVITY, HEALTH HAZARD DATA, PRECAUTIONS FOR SAFE HANDLING, USE AND CONTROL MEASURES AND ALSO TO TAKE LOCAL REGULATIONS INTO CONSIDERATION.

       Stress relieve the blade (PN 2A0402 and 2A0402-001 only).

       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.

    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 2 HPT blade	SPM TASK 70-23-08-230-501

    4. 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.

    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 assembly to between (PN 2A0402 and 2A0402-001) 1575 and 1625 deg F (857 to 885 deg C) in an oven and hold for 32 hours. Refer to the SPM TASK 70-37-27-370-501. The PHT is optional for these part numbers.

       2. Heat the assembly (PN 2A1102, 2A8602 and 2A8902) to between 1575 and 1625 deg F (857 to 885 deg C) in an oven and hold for 8, 12 or 32 hours. Refer to the SPM TASK 70-37-27-370-501.

       3. Let the blade air cool.

    7. Shot peen the blade root area by the SPM TASK 70-38-13-380-501. Refer to Figure.

       1. Use CoMat 05-029 CAST STEEL SHOT, S110, CoMat 05-030 CAST STEEL SHOT DELETED, CoMat 05-031 CAST STEEL SHOT DELETED, CoMat 05-032 CAST STEEL SHOT, S170, CoMat 05-033 CAST STEEL SHOT DELETED, CoMat 05-034 CAST STEEL SHOT DELETED, CoMat 05-138 SHOT, CAST STEEL, S110, CoMat 05-176 CAST STEEL SHOT, S170, CoMat 05-234 CAST STEEL SHOT, HIGH HARDNESS, S110 or CoMat 05-177 CUT WIRE SHOT,CW-14, CoMat 05-178 CUT WIRE SHOT, CW-20 or CoMat 05-187 STAINLESS STEEL CUT WIRE SHOT, SCW-20, CoMat 05-188 STAINLESS STEEL CUT WIRE SHOT, SPECIAL CONDITIONED, SCW-20. Peen with an intensity of 6A. Refer to the SPM TASK 70-38-13-380-501, SUBTASK 70-38-13-380-006.

16. SUBTASK 72-45-32-230-052-003 Examine the Stage 2 HPT Blade Assembly (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 RELIEF THE BLADE BEFORE FLUORESCENT PENETRANT EXAMINATION CAN CAUSE DAMAGE TO THE BLADE (PN 2A0402 AND 2A0402-001).

       When you cannot stress relief 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 Street, Well 11

       East Hartford, CT 06108-0969 USA

       Tel: (860) 565 3922

       Fax: (860) 557 8247

       Sequa Corp.,

       Chromalloy Research and Technology Division

       108 Blaisdell Road

       Orangeburg, New York 10962 USA

       Tel: (845) 359-4700

       Fax: (845) 359-4409

17. SUBTASK 72-45-32-280-052 Examine the Stage 2 HPT Blade Assembly (01-010) Coating by Heat Tint

    1. Vapor degrease the blade assembly by the SPM TASK 70-11-01-300-503.

    2. 

       CAUTION

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

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

    3. 
       CAUTION
       DO NOT PERMIT FINGERPRINTS OR CONTAMINATION OF ANY TYPE ON THE BLADE ASSEMBLY. THIS WILL CAUSE AN INCORRECT HEAT TINT EXAMINATION.

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

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

       2. 

          WARNING

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

          Remove the blade assembly from the oven.

    4. Examine the blade assembly coating for heat tint.

       1. Heat tint.

          1. Light gold color shows the blade has coating

             1. Accept

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

             1. Accept

                NOTE

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

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

             1. Repair, VRS3242 TASK 72-45-32-300-002 (REPAIR-002) or VRS3053 TASK 72-45-32-300-011 (REPAIR-011) or VRS3496 TASK 72-45-32-300-010 (REPAIR-010) or VRS3243 TASK 72-45-32-300-003 (REPAIR-003) or VRS3494 TASK 72-45-32-300-009 (REPAIR-009)

18. SUBTASK 72-45-32-260-051 Examine the Stage 2 HPT Blade Assembly (01-010) for Internal Cracks and Unwanted Material by Radiographic Inspection

    1. Refer to: Figure and Figure

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

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

          NOTE

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

          NOTE

          Surface 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

                NOTE

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

          2. Unwanted material in the internal cavities

             1. Power flush or Repair, VRS3360 TASK 72-45-32-300-005 (REPAIR-005). After you clean the internal cavities refer to VRS3360, TASK 72-45-32-300-005 (REPAIR-005). Unwanted metal and material are acceptable if the size, density and location of the indication(s) has remained unchanged from step (2) (b). Refer to the limits in Figure and Table 801

                NOTE

                If there are any indications of shot peen and/or other forms of foreign material, such as metal chips or broken wire, reject the parts.

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

             1. Reject

19. SUBTASK 72-45-32-280-053 Examine the Stage 2 HPT Blade Assembly (01-010) for the Growth Measurement

    1. Refer to: Figure and Figure

    2. Examine the blade assembly for the growth measurement.

       NOTE

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

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

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

       3. Use IAE 2P16207 Stages 1 and 2 HPT Blade Length Optical Gage 1 off, IAE 2P16211 Stage 2 HPT Turbine Blade Holder 1 off, IAE 2P16212 Stage 2 HPT Turbine Blade Gage - Master 1 off and IAE 2P16213 Stage 2 HPT Turbine Blade Reticle 1 off to measure the blade growth as follows:

          1. Center the optical gage adjustable work table with the three hand knobs refer to Figure.

          2. Loosen the two knurled head screws in the front rail on the adjustable work table.

          3. Install the blade holder between the front and rear rails on the work table and tighten the two screws.

          4. Install the gage master into the blade holder with the notch in the master located on the holder dowel pin. The other end of the master will locate on the second dowel pin at the dial indicator end of the holder.

          5. Loosen the thumb screw in the upper holder on the optical gage.

          6. Install the reticle into the upper holder and tighten the thumb screw.

          7. Look through the reticle and adjust the three hand knobs to center the target hole of the blade master inside the center circle of the reticle.

          8. Adjust the dial indicator on the blade holder to read the actual dimension marked on the gage master. Hand tighten the dial indicator to the blade holder with the detail nut.

          9. Remove the blade master.

             NOTE

             When the blade assembly is manufactured, the blade length is measured to the nearest 0.001in. (0.026 mm) at location 1. The last two numbers for PN 2A0402 or 2A0402-001 or the last three numbers for PN 2A1102 or 2A8602 of this dimension are roll-marked on the trailing edge root shank surface at location 2. Refer Figure.

          10. Record the two numbers for PN 2A0402 or 2A0402-001 or three numbers for PN 2A1102 or 2A8602 located on the blade assembly root shank surface.

              EXAMPLE: If the measured length at the time of manufacture was 3.504in. (89.002 mm), the PN 2A0402 or 2A0402-100 blade is marked at location 2 with the numbers 04 and the PN 2A1102 or 2A8602 blade is marked at location 2 with the numbers 504. This is the reference number from which the blade growth is found.

          11. Install the blade root slot at location 4 into the blade holder over the dowel pin.

          12. Look through the reticle and adjust the three hand knobs to center the blade measurement hole at location 3 inside the center circle of the reticle.

          13. Look at the dial indicator and record the dimension.

          14. Subtract the recorded blade dimension from the dial indicator dimension. The difference between the two dimensions is the amount of the blade growth.

          15. Remove the blade assembly.

       4. Growth.

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

             1. Accept

          2. Other than (a)

             1. Reject

20. SUBTASK 72-45-32-280-054 Examine the Stage 2 HPT Blade Assembly (01-010) for the Wall Thickness Dimension

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

       1. Wall thickness inspection details have been removed. Refer to Repair, VRS3552 TASK 72-45-32-300-016 (REPAIR-016) for inspection details.

21. SUBTASK 72-45-32-280-069 Examine the Stage 2 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 2 HPT blade assembly by the procedure given in VRS3711 TASK 72-45-32-300-027 (REPAIR-027).

22. SUBTASK 72-45-32-230-061 Examine the Stage 2 HPT Blade (01-010) for Casting Flow Lines and Imperfections

    1. Refer to Figure.

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

    3. Flow lines with no cracks

       1. Accept

    4. Flow lines with cracks

       1. Reject

          NOTE

          All other inspection criteria apply.

    5. 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

             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).

    6. 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.

             NOTE

             All other inspection criteria apply.

23. SUBTASK 72-45-32-280-062 Examine the Stage 2 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

    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.

             NOTE

             All other applicable overhaul inspection criteria apply.

Figure: Stage 2 HPT Blade Assembly Platform Inspection Locations

Stage 2 HPT Blade Assembly Platform Inspection Locations



Figure: Stage 2 HPT Blade Assembly Airfoil Inspection Locations

Stage 2 HPT Blade Assembly Airfoil Inspection Locations



Figure: Stage 2 HPT Blade Assembly Airfoil Dents Inspection Loations

Stage 2 HPT Blade Assembly Airfoil Dents Inspection Loations



Figure: Stage 2 HPT Blade Assembly Abrasive Tip Inspection Locations

Stage 2 HPT Blade Assembly Abrasive Tip Inspection Locations



Figure: Stage 2 HPT Blade Assembly Trailing Edge Inspection Locations

Stage 2 HPT Blade Assembly Trailing Edge Inspection Locations



Figure: Stage 2 HPT Blade Assembly Platform Surfaces Inspection Locations

Stage 2 HPT Blade Assembly Platform Surfaces Inspection Locations



Figure: Stage 2 HPT Blade Root and Root Attachment Area Inspection Locations and Limits

Sheet 1



Legend

Stage 2 HPT Blade Root and Root Attachment Area Inspection Locations and Limits

Sheet 1

Close

Figure: Stage 2 HPT Blade Root and Root Attachment Area Inspection Locations and Limits

Sheet 2



Legend

Stage 2 HPT Blade Root and Root Attachment Area Inspection Locations and Limits

Sheet 2

Close

Figure: Stage 2 HPT Blade Assembly Top Most Serration Inspection Locations

Stage 2 HPT Blade Assembly Top Most Serration Inspection Locations



Figure: Stage 2 HPT Blade Metal Temperature Analysis Locations

Stage 2 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 2 HPT Blade Assembly Radiographic Positions Inspection Locations

Stage 2 HPT Blade Assembly Radiographic Positions Inspection Locations



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

X-Ray Inspection Internal Cavity (After Cleaning)



Figure: Stage 2 HPT Blade Assembly Growth Tools

Stage 2 HPT Blade Assembly Growth Tools



Figure: Stage 2 HPT Blade Assembly Growth Measurement Inspection Locations

Stage 2 HPT Blade Assembly Growth Measurement Inspection Locations



Figure: Stage 2 HPT Blade Assembly Shot Peen Locations

Stage 2 HPT Blade Assembly Shot Peen Locations



Figure: Stage 2 HPT Blade Assembly Blade Length Locations

Stage 2 HPT Blade Assembly Blade Length Locations



Figure: Stage 2 HPT Blade Assembly Blade Length

Stage 2 HPT Blade Assembly Blade Length



Figure: Stage 2 HPT Blade Assembly Casting Flow Line Inspection

Stage 2 HPT Blade Assembly Casting Flow Line Inspection



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

Stage 2 HPT Blade Assembly Inspection for Porosity and Shrinkage



Figure: Stage 2 HPT Blade Permeability Tools

Sheet 1



Legend

Stage 2 HPT Blade Permeability Tools

Sheet 1

Close

Figure: Stage 2 HPT Blade Permeability Tools

Sheet 2



Legend

Stage 2 HPT Blade Permeability Tools

Sheet 2

Close

Figure: Stage 2 HPT Blade Permeability Inspection Areas

Stage 2 HPT Blade Permeability Inspection Areas



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

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