Preliminary Requirements

Safety Requirements

WARNING

THE ENGINE IS HOT IMMEDIATELY AFTER SHUTDOWN AND CAN CAUSE BURNS AND DAMAGE TO THE BORESCOPE EQUIPMENT. WAIT 2 TO 3 HOURS AFTER SHUTDOWN BEFORE YOU DO A BORESCOPE INSPECTION.

CAUTION

THE LIMITS WHICH FOLLOW ARE APPLICABLE ON A CONTINUE IN SERVICE BASIS ONLY. EACH LIMIT IS BASED ON WHAT THE STRUCTURE OF THE BLADE MUST BE AND DOES NOT INDICATE THAT THERE WILL NOT BE A DETERIORATION OF THE ENGINE PERFORMANCE, STABILITY, OPERATING LIMITS OR PART REPAIRABILITY.

Procedure

1. SUBTASK 72-00-00-420-079 Install the Foot-Operated Motor Drive Unit to the Gearbox Crank Pad

   1. Refer to Figure.

2. SUBTASK 72-00-00-420-080 Install the Guide Tube and the Flexible Borescope into the IP1 Borescope Port to Examine the Stage 1 HPT Blades,thru

   1. Refer to Figure and Figure.

   2. Remove the igniter plug.

   3. Do not remove the igniter insert.

   4. Put the flexible borescope into the IAE 2P16204 Guide Tube 1 off until the end of the borescope is even with the end of the tube. This will be a limit mark on the borescope so you will not insert the borescope too far and cause damage to the borescope.

   5. Put a piece of CoMat 02-024 MASKING TAPE (CREPE PAPERBACKING) on the borescope fiber bundle 3.250in. (82.55 mm) from the other end of the guide tube.

   6. Put the end of the tube nearest the tape mark in the down position and the plane of the tube at a right angle to the engine axis.

   7. Install the tube into the IP1 port.

      1. As the tube is put in, turn it clockwise carefully and connect the fitting to the igniter insert.

      2. Push the guide tube in until it touches the stop.

         NOTE

         1. In this position, the slot will be up.

         2. A cover for the eye which is not used will decrease eye tension.

         3. If you use an adjustable clamp to hold the borescope, you will be able to easily move the borescope dial and the fiber bundle.

         4. Some borescope units have closed-circuit television adapters. We highly recommend this unit.

      3. Turn the guide tube clockwise until it stops. Hold the tube in this position and tighten the locking wheel to secure the guide tube.

      4. Slowly push in the borescope through the guide tube while looking through the eye piece.

         NOTE

         At this point, the borescope is between two Stage 1 HPT vanes and at a location to see the concave side of the Stage 1 HPT blades.

      5. Move the borescope end slightly, while pushing in, and find the stage 1 HPT blades. Turn the borescope fiber bundle to help you locate the stage 1 HPT blades. Do not push the borescope past the tape mark.

   8. 

      CAUTION

      MAKE SURE THAT THE BORESCOPE TIP IS NOT IN THE PATH OF THE STAGE 1 HPT BLADES BEFORE YOU TURN THE ENGINE.

      Examine the blades for damage.

3. SUBTASK 72-00-00-020-071 Install a Rigid Borescope to Examine the Stage 1 HPT Blades through the B3 or B4 and T1/2L or T1/2R Ports,thru

   NOTE

   1. For a close up inspection, do the procedure in the paragraph above.

   2. An eye cover for the eye which is not used will decrease eye tension.

   3. Removal of the plugs at both of the locations will permit you to examine both leading and trailing edges.

   1. Refer to Figure and Figure.

   2. Get access to the stage 1 HPT blades through the B3 or B4 port, Figure.

      1. Remove the lockwire from the plug.

      2. Loosen and remove the plug and the gasket from the B3 or B4 port, Figure.

   3. 
      WARNING
      MAKE SURE THAT THE BLANKING PLUG IS COOL BEFORE YOU REMOVE IT. THE PLUG STAYS HOT FOR A SHORT TIME AFTER THE ENGINE IS SHUTDOWN.

      Get access to the stage 1 HPT blades through the T1/2L and the T1/2R ports, Figure.

      1. Remove the lockwire and the bolts which hold the plugs.

      2. Put the IAE 1P16184 Puller 1 off in to the center hole of the plug (use if required).

      3. Remove the plug from the port with the puller.

      4. Remove the gasket from the plug.

      5. Remove the plug from the puller.

      6. Do Step to Step for the other plug.

   4. Put a rigid borescope through the B3 or B4 port, Figure.

   5. Examine the blades for damage.

   6. Put a rigid borescope through the T1/2L or T1/2R port, Figure.

   7. Examine the blades for damage.

4. SUBTASK 72-00-00-220-119 Examine the Stage 1 HPT Blades for Nicks or Dents on the Airfoil

   1. Refer to Figure, Figure and Figure.

   2. Accept with an inspection each 750 hours if:

      1. There is a nick or dent with cracks on the leading edge outer 50 percent span which has a total radial or axial length of up to 0.20 in. (5.08 mm).

   3. Accept with an inspection each 600 hours if:

      1. The nick or dent is in Area A or B and is larger than 0.200 in. (5.08 mm).

      2. Provided the nick or dent does not show the following conditions:

         1. The nick or dent is in Area A or Area B (not to include the blade trailing edge tip) and shows signs of torn metal or cracks.

         2. The nick or dent causes internal areas to show. These are areas where the air that is used to cool the blade goes.

   4. Accept with an inspection each 300 hours if:

      1. There is a nick or dent with cracks on the leading edge outer 50 percent span which has a total axial length up to 0.27 in. (6.8 mm) and a total radial length of greater than 0.20 in. (5.08 mm) and up to a total radial length of 0.50 in. (12.7 mm).

5. SUBTASK 72-00-00-220-120 Examine the Stage 1 HPT Blades for Cracks on the Airfoil

   1. Refer to Figure, Figure, Figure, Figure and Figure.

      NOTE

      1. There will be unwanted material on the airfoil because of the casting procedure. Refer to Figure. During borescope inspection, this material will look like small bumps on the concave and convex surfaces of the airfoil. These bumps are usually round or oval, are between 0.100 to 0.200 in. (2.54 to 5.08 mm) wide and are 0.005 in. (0.13 mm) high. These bumps are acceptable. No action is necessary.

      2. Tip zone - lower edge of upper tip cooling holes to tip. In this zone a crack going through another crack is permitted.

   2. Accept with an inspection each 600 hours if:

      1. The crack in Area A or Area B is longer than 0.070 in. (1.78 mm).

      2. The crack in Area A (this does not include the inner 25 percent of the leading or trailing edge span) or Area B extends from a burned area and the combination of a burn and a crack is longer than 0.120 in. (3.05 mm) in one direction.

      3. The crack in the inner 25 percent of the leading or trailing edge span in Area A extends from a burned area and the combination of the burn plus the crack is longer than 0.070 in. (1.78 mm).

      4. The crack in Area C is longer than 0.10 in. (2.5 mm).

      5. The crack in Area C extends from a burned area and a combination of the burn plus a crack is longer than 0.100 in. (2.54 mm).

      6. A radial crack on the airfoil starts at the blade tip and is longer than 0.200 in. (5.08 mm) but not more than 0.35 in. (8.9 mm). The number of cracks is not important.

      7. Axial crack is more than 0.14 in. (3.6 mm) but not more than 0.30 in. (7.6 mm) in the tip zone.

      8. There is missing material which extends more than 0.050 in. (1.27 mm) radially from the tip.

   3. Accept with an inspection each 300 hours if:

      1. Axial crack is more than 0.20 in. (5.1 mm) in the tip zone.

      2. If there is missing material that extends more than 0.080 in. (2.03 mm) radially from the tip.

      3. If there is missing material which extends more than 0.60 in. (1.52 mm) radially and is also more than 0.120 in. (3.05 mm) axially.

      4. The crack on the leading edge (in the outer 50 percent span) extends from a burned area or burn-through and the combination of a burn or burn through plus a crack is more than or equal to 0.20 in. (5.05 mm) in the radial direction.

   4. Accept with an inspection each 150 hours if:

      1. Axial crack is more than 0.24 in. (6.1 mm) in the tip zone.

      2. If there is missing material which extends more than 0.10 in. (2.5 mm) radially from the tip.

      3. If there is missing material which extends more than 0.080 in. (2.03 mm) radially and is also more than 0.18 in. (4.6 mm) in the tip zone.

      4. The crack on the leading edge (in the outer 50 percent span) extends from a burned area or burn-through and the combination of a burn or burn-through plus a crack is more than or equal to 0.20 in. (5.08 mm) in the radial direction and the crack is less than 0.45 in. (3.81 mm) in the radial direction.

   5. Reject if:

      1. The crack on the leading edge in the outer 50 percent span extends from a burned area or burn through and the combination of burn or burn through plus a crack is longer than 0.70 in. (17.78 mm) in the radial direction.

      2. The crack in Area A (other than a radial crack that starts at the blade tip) is more than or equal to 0.15 in. (3.81 mm).

      3. The crack in Area A (this does not include the inner 25 percent of the leading or trailing edge span, or a radial crack or burn through on the outer 50 percent span of the leading edge) extends from a burned area and the combination of a burn plus a crack is longer than 0.22 in. (5.59 mm).

      4. The crack in the inner 25 percent of the trailing edge span in Area A extends from a burned area and the combination of the burn plus the crack is longer than 0.130 in. (3.30 mm).

      5. The crack in Area B is longer than 0.15 in. (3.81 mm).

      6. The crack in Area B extends from a burned area and the combination of the burn plus a crack is longer than 0.15 in. (3.81 mm).

      7. The crack in Area C is longer than 0.20 in. (5.08 mm).

      8. The crack in Area C extends from a burned area and the combination of the burn plus a crack is longer than 0.20 in. (5.08 mm).

      9. A radial crack on the airfoil starts at the blade tip and is longer than 0.35 in. (8.89 mm).

      10. The cracks form closed loops between cooling holes except in the tip zone.

      11. The crack goes through other cracks except in the tip zone.

      12. The internal cooling passages can be seen at the blade tip.

      13. There is missing material which extends more than 0.09 in. (2.29 mm) radially and 0.28 in. (7.11 mm) axially in the tip zone.

      14. There is an axial crack that has a length more than 0.30 in. (7.62 mm) in the tip zone.

      15. In the airfoil fillet radius there is a crack combination of a burn and a crack.

6. SUBTASK 72-00-00-220-121 Examine the Stage 1 HPT Blades for Cracks on the Platform

   1. Refer to Figure.

      NOTE

      It is acceptable to have small pieces of the Stage 1 HPT seal HPT Stage 1 Blade And Related Parts (72-45-14,01-060) out between the rear platform of the Stage 1 HPT blade HPT Stage 1 Blade And Related Parts (72-45-14,01-010) and the Stage 1 HPT air seal ENGINE-STAGE 1 AIR SEAL (REAR) (72-45-15,01-020).

   2. Accept with an inspection each 600 hours if:

      1. The crack is longer than 0.150 in. (3.81 mm) and does not go up to the platform-to-airfoil fillet radius. The number of cracks is not important.

   3. Accept with an inspection each 300 hours if:

      1. The crack goes into the platform-to-airfoil fillet radius, and the crack does not go through the platform to the platform radius.

      2. The crack is longer than 0.20 in. (5.1 mm) and does not go into the platform to the airfoil radius.

   4. Reject if:

      1. The crack goes through the platform to airfoil fillet radius.

      2. The crack is longer than 0.25 in. (6.35 mm) and does not go into the platform to airfoil fillet radius.

         NOTE

         Crack is not permitted in airfoil fillet radius.

7. SUBTASK 72-00-00-220-122 Examine the Stage 1 HPT Blades for Erosion or Burns on the Airfoil or Platform

   1. Refer to Figure, Figure, Figure, Figure and Figure.

      NOTE

      The newest standard of Stage 1 HPT blades has an outer ceramic coating and protective coatings underneath the ceramic coating. Erosion or chipping of the ceramic outer coating is acceptable. A reduced inspection interval or engine removal is not necessary until burning or erosion of the base material of the blade occurs as specified below. Thus, it is not necessary to remove the engine or reduce the inspection interval because of coating loss.

   2. Accept with an inspection each 1500 hours if:

      1. The leading edge hole beyond the 75 percent span is less than 0.10 in. (2.54 mm) axially and 0.15 in. (3.81 mm) radially.

   3. Accept with an inspection each 750 hours if:

      1. The leading edge hole beyond the 50 percent span is less than 0.10 in. (2.54 mm) axially and less than 0.20 in. (5.08 mm) radially.

   4. Accept with an inspection each 600 hours if:

      1. The erosion or burn on the leading edge is more than one quarter of the airfoil radial length.

      2. The erosion or burns on the leading edge have changed the airfoil shape.

      3. The erosion or burns on the airfoil or platform have gone through the coating. This does not include burns on the airfoil leading edge, trailing edge or tip.

      4. The erosion or burns on the trailing edge in the inner 25 percent are more than 0.070 in. (1.78 mm) and less than 0.11 in. (2.79 mm) axially.

      5. The erosion or burns on the trailing edge beyond the inner 25 percent span are more than 0.120 in. (3.05 mm) and less than 0.20 in. (5.08 mm) axially. This does not include the blade tip.

      6. The burning at the blade tip in Zone 1 is at the bottom of the lower tip cooling row holes.

      7. The burning at the remainder of the tip (but no including the trailing edge tip) is more than 0.060 in. (1.52 mm) radially and above the top edge of the upper cooling holes.

      8. There is material that is burned away or missing on the blade trailing edge tip that is more than 0.070 in. (1.78 mm) axially from the trailing edge.

         NOTE

         The blade trailing edge tip is 0.150 in. (3.81 mm) radially from the tip and 0.100 in. (2.54 mm) from the trailing edge and burning or erosion is permitted in this area.

   5. Accept with an inspection each 300 hours if:

      1. The erosion or burns on the trailing edge of the inner 25 percent span are more than or equal to 0.110 in. (2.79 mm) axially and less than 0.15 in. (3.81 mm) axially.

      2. The erosion or burns on the trailing edge beyond the inner 25 percent span are equal to or more than 0.20 in. (5.08 mm) and less than 0.30 in. (7.62 mm) axially. This does not include the blade tip.

      3. The leading edge hole on the outer 50 percent span is equal to or greater than 0.10 in. (2.54 mm) and less than 0.20 in. (5.08 mm) in the axial direction and is equal to or greater than 0.20 (5.08 mm) and less than 0.50 in. (12.70 mm) in the radial direction.

      4. There is visible platform material missing due to erosion or burning.

      5. The burning at the tip (except in Zone 1 and the trailing edge tip) is below the upper edge of the upper tip cooling row but above the upper edge of the lower tip cooling row.

      6. There is material that is burned away or missing on the blade trailing edge tip that is more than 0.090 in. (2.29 mm) axially from the trailing edge.

   6. Accept with an inspection each 150 hours if:

      1. The leading edge hole on the outer 50 percent span is less than 0.200 in. (5.08 mm) in the axial direction and in the radial direction is between 0.50 in. (12.70 mm) and 0.70 in. (17.78 mm) and the burning at the tip does not extend beyond the first row of cooling holes.

      2. The trailing edge tip has missing or burned-away material that is less than or equal to 0.50 in. (12.70 mm) in the axial direction and less than or equal to 0.15 in. (3.81 mm) in the radial direction.

   7. Reject if:

      1. The leading edge hole on the outer 50 percent span is more than or equal to 0.20 in. (5.08 mm) in the axial direction more than or equal to 0.70 in. (17.78 mm) in the radial direction, and the burning at the tip does not extend beyond the first row of cooling holes.

      2. The erosion or burn (in a location other than the outer 50 percent span) lets internal areas and walls show. The internal areas are where the air that is used to cool the blade goes.

      3. The burn on the platform increases the gap to the adjacent platform to more than 0.05 in. (1.27 mm) or a crack has increased to more than 0.05 in. (1.27 mm) wide. This does not include the trailing edge platform corner burning.

      4. The burn on the trailing edge platform corner is more than 0.40 in. (10.16 mm) axially or 0.60 in. (15.24 mm) circumferentially.

      5. The erosion or burns on the trailing edge in the inner 25 percent span are more than or equal to 0.15 in. (3.81 mm) axially.

      6. The erosion or burns on the trailing edge beyond the inner 25 percent span are more than or equal to 0.30 in. (7.62 mm) axially. This does not include the blade tip.

      7. The burning at the tip has extended to completely include the lower tip cooling row holes or burn through at the tip has occurred.

      8. The leading edge hole on the outer 50 percent span is more than or equal to 0.20 in. (5.08 mm) in the axial direction, and the burning at the tip extends beyond the first row of cooling holes.

      9. The leading edge hole on the outer 50 percent span is more than or equal to 0.50 in. (12.70 mm) in the radial direction, and the burning at the tip extends beyond the first row of cooling holes.

      10. The inner wall (as you can see through the burn-through hole in the outer 50 percent span of the leading edge) has burns or has been breached.

          NOTE

          The trailing edge and the inner row of blade tip holes is 0.15 in. (3.81 mm) radially.

      11. The trailing edge tip has missing or burned-away material more than or equal to 0.5 in. (12.70 mm) in the axial direction and more than or equal to 0.15 in. (3.81 mm) in the radial direction.

8. SUBTASK 72-00-00-220-123 Examine the Stage 1 HPT Duct Segments

   1. Refer to Figure, Figure, Figure, Figure, Figure, Figure, Figure and Figure.

   2. If an engine is in the shop for maintenance other than the HPT, you must do a 360-degree inspection of the stage 1 HPT duct segments.

      1. Damage in columns A and B will need reduced on-wing inspections of either 300 hours or 125 hours if you do not replace the damaged duct segments. It is recommended that, because of the reduced inspection intervals, you review the timing of the next maintenance interval for the HPT and find out if you must replace the duct segments before you return the engine to service.

      2. Damage in Column C means you must replace the duct segments before you return the engine to service.

         NOTE

         The HPT Stage 1 BOAS has a protective coating underneath the ceramic coating. Chipping and spalling of the ceramic coating is acceptable without a decrease in borescope inspection interval. The smearing of blade tip material on the HPT Stage 1 BOAS is acceptable without a decrease in the borescope inspection interval.

         CONDITION		A. 300-HR. INSPECTION		B. 125-HR. INSPECTION		C. REPLACE THE DUCT SEGMENT
         Axial cracks		One crack is longer than 0.250 in. (6.35 mm) and shorter than 0.500 in. (12.70 mm)		One crack is longer than or equal to 0.500 in. (12.70 mm) but shorter than 1.20 in. (30.50 mm)		One crack is longer than or equal to 1.20 in. (30.5 mm)
         Circumferential cracks		One crack is longer than 0.375 in. (9.53 mm) and is shorter than 0.500 in. (12.70 mm)		One crack is longer than or equal to 0.500 in. (12.70 mm) but shorter than 1.50 in. (38.10 mm)		One crack is longer than or equal to 1.50 in. (38.10 mm)
         Intersecting cracks		A combined crack that is longer than 0.250 in. (6.35 mm) and shorter than 0.500 in. (12.70 mm) axially or longer than 0.375 in. (9.53 mm) and shorter than 0.500 in. (12.70 mm) circumferentially.		A combined crack that is longer than or equal to 0.500 in. (12.70 mm) and shorter than 1.20 in. (30.48 mm) axially or longer than or equal to 0.500 in. (12.70 mm) and shorter than 1.500 in. (38.10 mm) circumferentially.		A combined crack that is longer than or equal to 1.20 in. (30.48 mm) axially or 1.500 in. (38.10 mm) circumferentially.
         Closed loop of cracks		Does not apply		Maximum length in X or Y direction that is less than 0.500 in. (12.70 mm).		Maximum length in X or Y direction that is more than or equal to 0.500 in. (12.70 mm)
         Burning or erosion of the base metal at Area 1 (no burn-through)		One amount that is greater than two connecting cooling holes		Does not apply		Does not apply
         Burning or erosion of the base metal at Area 2 (no burn-through)		Shiplap burning more than the first row of cooling holes and not more than the second row of cooling holes		Shiplap burning goes through the second row of cooling holes		Does not apply
         Burn-through in Areas 1 and 2		Does not apply		Less than 0.500 in. (12.70 mm) of continuous burn-through in Area 1, Area 2 or Areas 1 and 2 together		More than or equal to 0.500 in. (12.70 mm) continuous burn-through in Area 1, Area 2 or Areas 1 and 2 together
         Burn-through with adjoining cracks in the axial direction		Does not apply		Combined length of X¹+X²+Z is less than 1.20 in. (30.48 mm) and Z is less than 0.500 in. (12.70 mm) in Area 1, Area 2 or Areas 1 and 2 together		Combined length of X¹+X²+Z is more than or equal to 1.20 in. (30.48 mm) or Z is more than or equal to 0.500 in. (12.70 mm)
         Burn-through with adjoining cracks in the circumferential direction		Does not apply		Combined length of Y¹+Y²+Z is less than 1.50 in. (38.10 mm) and Z is less than 0.500 in. (12.70 mm) in Area 1, Area 2 or Areas 1 and 2 together		Combined length of Y¹+Y²+Z is more than or equal to 1.50 in. (38.10 mm) or Z is more than or equal to 0.500 in. (12.70 mm)
         Burn-through the impingement plate		Does not apply		Does not apply		Any amount
         Material on the Leading Edge is lifted up		Does not apply		Does not apply		Seal edge is lifted
         Loss of Leading Edge Material (parent material loss)		Less than 0.300 in. (7.62 mm)		More than or equal to 0.300 in. (7.62 mm) but less than 0.500 in. (12.70 mm)		More than or equal to 0.500 in. (12.70 mm)

9. SUBTASK 72-00-00-020-072 Remove the Borescope Equipment from the Borescope Inspection Ports

10. SUBTASK 72-00-00-420-081 Close the Borescope Inspection Ports after the Borescope Inspection is Completed

    1. Refer to Figure and Figure.

    2. For the IP1 igniter port, install the igniter plug.

    3. For the B3 or B4 port proceed as follows:

       NOTE

       It is permissible to correct minor thread damage to the threaded hole with a 0.5625-18UNF-3B die.

       1. Lubricate the plug threads with CoMat 10-129 ANTI-SEIZE PASTE or CoMat 10-094 ANTI-SEIZE COMPOUND, PURE Ni-SPECIAL. Wipe off excess paste.

       2. Install the plug Diffuser Case Assembly And Fittings (72-42-10,01-020) and the Diffuser Case Assembly And Fittings (72-42-10, 01-010) gasket 1 off, Figure.

       3. Torque the plug to 70 lbfin to 80 lbfin (7.91 Nm to 9.04 Nm).

       4. Safety the plug with CoMat 02-141 LOCKWIRE.

    4. For the T1/T2 and T1/2R port proceed as follows:

       1. Put the HP Turbine (HPT) Rotor And Stator Assembly (72-45-00, 01-120) gasket 1 off in the case recess, Figure.

       2. Replace the gasket if the seal is not above the case surface.

       3. 

          CAUTION

          USE CAUTION WHEN INSTALLING PLUG. IF THE PLUG BREAKS DURING INSTALLATION AND FALLS INTO 2ND STAGE VANE CAVITY, REMOVE PLUG PIECE PRIOR TO RETURNING ENGINE TO SERVICE. IF NECESSARY, ACCESS TO THE CAVITY CAN BE OBTAINED BY REMOVING THE TCA TUBE.

          Put the gasket on the plug (2) HP Turbine (HPT) Rotor And Stator Assembly (72-45-00, 01-140) and install it in the case.

          NOTE

          It is permissible to correct minor thread damage to the threaded hole with a 0.5625-18UNF-3B die.

       4. Lubricate the bolt threads with CoMat 10-129 ANTI-SEIZE PASTE or CoMat 10-094 ANTI-SEIZE COMPOUND, PURE Ni-SPECIAL. Wipe off excess paste.

          NOTE

          Make sure that the borescope plug is correctly installed and bolt holes are aligned prior to continuing to next step.

       5. Install the bolts (72-45-00, 10-160).

       6. Torque the bolts to 75 lbfin to 85 lbfin (8.48 Nm to 9.60 Nm).

       7. Safety the bolts with CoMat 02-141 LOCKWIRE.

11. SUBTASK 72-00-00-020-073 Remove the Foot-Operated Motor Drive Unit from the Gearbox Crank Pad

Figure: Crank Pad Location

Crank Pad Location



Figure: HP Turbine Borescope Locations for Inspection of the Stage 1 HPT Blades (Left Side)

HP Turbine Borescope Locations for Inspection of the Stage 1 HPT Blades (Left Side)



Figure: HP Turbine Borescope Ports for Inspection of the Stage 1 HPT blades (Right Side)

HP Turbine Borescope Ports for Inspection of the Stage 1 HPT blades (Right Side)



Figure: HP Turbine Ports for Inspection of the Stage 1 HPT Blades

HP Turbine Ports for Inspection of the Stage 1 HPT Blades



Figure: Borescope Equipment

Borescope Equipment



Figure: Borescope Ports

Borescope Ports



Figure: Borescope Ports

Borescope Ports



Figure: Stage 1 HPT Blade Inspection Areas

Stage 1 HPT Blade Inspection Areas



Figure: Stage 1 HPT Blade Inspection Areas

Stage 1 HPT Blade Inspection Areas



Figure: Stage 1 HPT Blade Inspection Areas

Stage 1 HPT Blade Inspection Areas



Figure: Stage 1 HPT Blade Inspection Areas

Stage 1 HPT Blade Inspection Areas



Figure: Stage 1 HPT Duct Segment Inspection Locations

Stage 1 HPT Duct Segment Inspection Locations



Figure: Stage 1 HPT Duct Segment Inspection Locations

Stage 1 HPT Duct Segment Inspection Locations



Figure: Stage 1 HPT Blade Inspection Areas

Stage 1 HPT Blade Inspection Areas



Figure: HPT Stage 1 Duct Segment Intersecting Cracks

HPT Stage 1 Duct Segment Intersecting Cracks



Figure: HPT Stage 1 Duct Segment Intersecting Cracks

HPT Stage 1 Duct Segment Intersecting Cracks



Figure: HPT Stage 1 Duct Segment Intersecting Cracks

HPT Stage 1 Duct Segment Intersecting Cracks



Figure: Burn Through with Adjoining Cracks in Axial Direction

Burn Through with Adjoining Cracks in Axial Direction



Figure: Burn Through with Adjoining Cracks in Cirumferential Direction

Burn Through with Adjoining Cracks in Cirumferential Direction



Figure: Closed Loop of Cracks

Closed Loop of Cracks