Preliminary Requirements

Safety Requirements

CAUTION

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

Procedure

1. SUBTASK 72-00-00-020-055-A00 Get Access to the Combustion Chamber and the Stage 1 Turbine Vanes through the B1 to B5 and IP1 and IP2 Ports

   PRE SBE 72-0221

   1. Refer to Figure, Figure and Figure.

   2. For the B1 to B5 ports, remove the 5 plugs and gaskets at the locations shown.

   3. For the IP1 and IP2 ports, remove the igniter plugs.

      NOTE

      Do not remove the igniter insert.

2. SUBTASK 72-00-00-020-055-B00 Get Access to the Combustion Chamber and the Stage 1 Turbine Vanes through the B1 to B6 and IP1 and IP2 Ports (SBE 72-0221)

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

   2. For B1 to B6 ports, remove the 6 plugs and gaskets at locations shown.

   3. For IP1 and IP2 ports, remove the igniter plugs.

      NOTE

      Do not remove the igniter insert.

3. SUBTASK 72-00-00-220-054- A00 Examine the Combustion Chamber and the Stage 1 HPT Vanes for Damage (Pre SBE 72- 0221)

   1. Refer to Figure.

   2. 

      CAUTION

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

      Put the borescope into the ports and examine the combustion chamber and the Stage 1 HPT vanes for damage.

      NOTE

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

   3. If the damage seen is not listed, contact your IAE representative.

4. SUBTASK 72-00-00-220-054- B00 Examine the Combustion Chamber and the Stage 1 HPT Vanes for Damage (SBE 72- 0221)

   1. Refer to Figure.

   2. 

      CAUTION

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

      Put the Rigid boroscope (6 or 8 mm) into the ports and examine the combustion chamber and the stage 1 HPT vanes for damage.

      NOTE

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

   3. If the damage seen is not listed, contact your IAE representative.

5. SUBTASK 72-00-00-220-055 Convex and Concave Surface Cracks/Burns

   NOTE

   All cracks or sections of cracks burned to a width of more than 0.050 in. (1.270 mm) are burn holes. Use the applicable burn limits.

   NOTE

   If a convex or a concave burn extends to the leading edge, you must use leading edge criteria.

   1. Refer to Figure and Figure.

   2. Accept with an inspection each 600 hours if:

      1. There is more than one axial crack three-quarters of a chord length long or longer. Axial and radial cracks can go through each other.

      2. There are many radial cracks that are more than 1.500 in. (38.100 mm) in length. Axial cracks can go through radial cracks.

      3. There is a burn that has caused a burn-through that is between 0.050 and 0.100 in. (1.270 and 2.540 mm) at is shortest dimension.

   3. Accept with an inspection each 300 hours if:

      1. There is a burn that has caused a burn-through that is between 0.100 and 0.300 in. (2.540 and 7.620 mm) at its shortest dimension.

   4. Reject if:

      1. There is axial or radial crack lift up of more than 0.050 in. (12.7 mm).

      2. There are connected loop cracks that show a piece of vane metal that is calculated to be more than 0.500 in. (12.7 mm) in length.

      3. There Is a crack that is three-quarters of a cord length long or longer that also goes into a leading edge or a convex surface burn-through.

      4. There is a burn that has caused a burn-through that is more than 0.300 in. (7.620 mm) at its shortest dimension.

6. SUBTASK 72-00-00-220-056 Leading Edge Cracks and Leading Edge Burns

   NOTE

   There is no limit to the number of leading edge tight cracks permitted without decreased inspection times.

   1. Refer to Figure.

   2. Accept with an inspection each 600 hours if:

      1. There are leading edge and/or convex surface cracks, or burns that have caused a burn-through that is less than 0.850 in. (21.59 mm) in length radially.

   3. Accept with an inspection each 300 hours if:

      1. There is leading edge burn-through that is located less than 0.200 in. (5.08 mm) beyond the first row of leading edge cooling holes and the total length of the burn-through is less than 0.650 in. (16.51 mm) axially and 0.850 in. (21.59 mm) radially.

   4. Accept with an inspection each 75 hours if:

      1. There is leading edge burn-through that is less than 0.250 in. (6.35 mm) beyond the first row of cooling holes and the total length of the burn-through is less than 0.650 in. (16.51 mm) axially and 0.850 ln. (21.59 mm) radically.

   5. Reject if:

      1. There is leading edge burn-through that extends more than 0.250 in. (6.35 mm) beyond the first row of cooling holes on either the convex or concave surfaces.

      2. Radial leading edge burning extends beyond 0.850 in. (21.59 mm).

      3. Axial leading edge burning extends beyond 0.650 in. (16.51 mm).

      4. On any vane, the total length of bum-through from the leading edge plus a crack and/or bum-through from the trailing edge is more than three-quarters of the chord length.

      5. There is baffle bum-through.

      6. There is baffle cracking.

7. SUBTASK 72-00-00-220-057 Trailing Edge Burns, .nd

   1. Refer to Figure and Figure.

   2. Accept with an inspection each 600 hours if:

      1. NOTE

         0.500 in. (12.700 mm) is equal to five trailing edge cooling air slots.

         There is a burn-through that goes between one quarter and one half on the chord length from the trailing edge and is more than 0.500 in. (12.700 mm) in width at the trailing edge.

   3. Accept with an inspection each 300 hours if:

      1. NOTE

         0.500 in. (12.700 mm) is equal to five trailing edge cooling air slots.

         There is a burn-through that goes between one half and three quarters of the chord length from the trailing edge and is more than 0.500 in. (12.700 mm) in width at the trailing edge.

   4. Reject if:

      1. There is a bum-through that goes more than three quarters of a chord length from the trailing edge and is more than 0.500 in. (12.7 mm) in width at the trailing edge.

         NOTE

         0.500 in. (12.70 mm) is equal to five trailing edge cooling air slots.

      2. There is a trailing edge burn-through inboard of the first two trailing edge cooling slots.

8. SUBTASK 72-00-00-220-058 Cracks on the Inner and Outer Platform

   1. Refer to Figure.

   2. Accept with an inspection each 600 hours if:

      1. There is a crack that is more than 0.500 in. (12.700 mm) in length.

   3. Accept with an inspection each 300 hours if:

      1. There is a crack that is more than 1.000 in. (25.400 mm) in length.

   4. Reject if:

      1. There is a crack that Is parallel to the airfoil fillet radius, that goes around the airfoil leading edge and that is more than 1.500 in. (38.1 mm) in length.

9. SUBTASK 72-00-00-220- 059 Cracks on the Inner and Outer Platform Airfoil Fillet Radii

   1. Refer to Figure.

   2. Accept with an inspection each 600 hours if:

      1. There is a fillet crack that is more than 1.000 in. (25.400 mm) in length and that goes from the fillet on to the airfoil.

   3. Reject if:

      1. There is a crack that Is more than 1.000 in. (25.4 mm) in length and part of the length is eroded to a width of more than 0.030 in. (0.76 mm).

      2. There is a crack in the fillet radius that Is more than 1.500 in. (38.1 mm) in length and that goes around to the airfoil leading edge.

10. SUBTASK 72-00-00-220-060 Burns on the Inner and Outer Platform

    1. Refer to Figure.

    2. Accept with an inspection each 600 hours if:

       1. There are burns that go from the edge of the platform to the platform airfoil fillet.

    3. Accept with an inspection each 300 hours if:

       1. There are burns that have caused a burn hole that is less than 0.250 in. (6.350 mm) in length.

    4. Reject if:

       1. There are burns that have caused a burn-through that is more than 0.250 in. (6.35 mm) in length.

11. SUBTASK 72-00-00-220-061 Burner Liner Segment Cracks

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

    2. Accept burner liner segments that have combustion holes without a decreased borescope inspection time if:

       1. There are two cracks completely through a segment in the axial direction and each crack goes through combustion holes that are separated by a combustion holes without a crack.

       2. There are two cracks completely through a segment in the axial direction and one of the cracks goes through a combustion hole and the other crack is separated by a combustion hole and is not less than 0.700 in. (17.78 mm) from a circumferential edge.

    3. Accept burner liner segments that do not have combustion holes without a decreased borescope inspection time if:

       1. There is one crack completely through axially that is more than 0.700 in. (17.780 mm) from a circumferential edge.

    4. Accept burner liner segments that have combustion holes with an inspection each 600 hours if:

       1. There are two or more cracks downstream of a combustion hole, one of the cracks goes from the combustion hole to the trailing edge. No other crack goes more than half the distance to the same combustion hole or trailing edge.

    5. Accept burner liner segments that do not have combustion holes with an inspection each 600 hours if:

       1. There are two or more axial cracks, one crack is completely through the segment and is more than 0.700 in. (17.780 mm) from a circumferential edge. No other crack is more than half the axial length of the segment or nearer than 0.700 in. (17.780 mm) to a circumferential edge.

    6. Accept burner liner segment that have combustion holes with an inspection each 300 hours if:

       NOTE

       You must also do a borescope Inspection of the Stage 1 HPT Blades TASK 72-00-00-200-004-A00 (Inspection-004) each 300 hours of liner segments are on a 300 hour repeat borescope inspection for segment cracking.

       1. There are 2, 3 or 4 cracks completely through axially and the following requirements are met:

          1. Each crack goes through a combustion hole.

          2. At least two cracks go through adjacent combustion holes.

       2. There are two or more cracks downstream of a combustion hole and the following conditions are met:

          1. One crack goes from a combustion hole to the trailing edge.

          2. No other crack goes more than two thirds of the distance to the same combustion hole or trailing edge.

       3. There are cracks that can cause a piece of segment material not more than 0.25 in.2 (161.29 mm2 ) in area to break off.

    7. Accept burner liner segments that do not have combustion holes with an inspection each 300 hours if:

       NOTE

       You must also do a borescope inspection of the Stage 1 HPT Blades TASK 72-00-00-200-004-A00 (Inspection-004) each 300 hours of liner segments are on a 300 hour repeat borescope inspection for segment cracking.

       1. There are two or more axial cracks and the following requirements are met:

          1. One crack is completely through the segment and is more than 0.700 in. (17.780 mm) from a circumferential edge.

          2. No other crack is more than two thirds the axial length of the segment or nearer than 0.700 in. (17.780 mm) to a circumferential edge.

       2. There are cracks that can cause a piece of segment material not more than 0.25 in.2 (161.29 mm2 ) in area to break off.

    8. Reject if:

       1. There are cracks that can cause a piece of segment material more than 0.25 in.2 (161.29 mm2 ) in area to break off.

12. SUBTASK 72-00-00-220-062 Segment Edge Burnback

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

    2. Accept burner liner segments without a decreased borescope inspection if:

       1. There is trailing edge burnback less than 0.70 in (17.78 mm) and the following conditions are met:

          1. There is no liner shell damage (burn-through or cracks).

          2. There is damage to the rails around the igniter holes on the Row 1 igniter segment less than 135 degrees.

          3. You must not be able to see an attachment post.

    3. Accept burner liner segments with an inspection 600 hours if:

       1. The trailing edge burnback is between 0.70 in. (17.78 mm) and 0.90 in. (22.86 mm) and the following conditions are met:

          1. There is no liner shell damage (burn-through or cracks).

          2. There is damage to the rails around the igniter holes on the row 1 igniter segment less than 135 degrees.

          3. You must not be able to see an attachment post.

    4. Accept burner liner segments with an inspection each 300 hours if:

       1. The trailing edge burnback is more than 0.90 in. (22.86 mm) and the following conditions are met:

          1. Liner shell damage (burn-through or cracks) must not have an area of more than 0.50 in.2 (322.58 mm2).

          2. There is damage to the rails around the igniter holes on the row 1 igniter segment less than 135 degrees.

          3. You must not be able to see an attachment post.

             NOTE

             A maximum of three liner shell damage locations for each burner assembly is allowed.

    5. Reject if:

       1. There is complete edge burnback on one segment and another area of edge burnback more than 1.00 in. (25.4 mm) on the same segment.

       2. There are two or more segments with complete edge burnback. Refer to Figure.

       3. There is damage to the rails around the Igniter holes on the Row 1 igniter segment more than 135 degrees.

       4. There is trailing edge burnback that shows an attachment post or an attachment post is missing.

       5. There is liner shell damage (burn-through or cracks) that is more than 0.500 in.2 (322.58 mm2 ) in area or there are more than three locations of liner shell damage less than 0.500 in.2 (322.58 mm2 ) in all the burner assembly.

13. SUBTASK 72-00-00-220- 063 Surface Burns and Burn-Through Holes in Liner Segments

    1. Refer to Figure and Figure.

    2. Accept segments (with or without combustion holes) without a decreased borescope inspection time if:

       1. As much as all the surface is burned.

       2. There are segment burn-through holes that are less 0.350 in. (8.890 mm) in length and the following conditions are met:

          1. There must be no liner shell damage (burn-through or cracks).

          2. There is damage to the rails around the Igniter holes on the row 1 igniter segment less than 135 degrees.

          3. You must not be able to see an attachment post.

    3. Accept segments (with or without combustion holes) with an inspection each 600 hours if:

       1. There is a segment burn-through hole that is between 0.350 and 0.650in. (8.890 and 16.510 mm) in length and the following conditions are met:

          1. There must be no liner shell damage (burn-through or cracks).

          2. There is damage to the rails around the Igniter holes on the row 1 igniter segment less than 135 degrees.

          3. You must not be able to see an attachment post.

    4. Accept segments (with or without combustion holes) with an inspection each 300 hours if:

       1. There is a segment burn-through hole that is between 0.650 and 1.000in. (16.51 0 and 25.400 mm) in length and the following conditions are met:

          1. Liner shell damage (burn-through or cracks) must not have an area of more than 0.50 in.2 (322.58 mm2).

          2. Liner shell damage (burn-through or cracks) must not occur in more than three locations.

          3. There is damage to the rails around the igniter holes on the row 1 igniter segment less than 135 degrees.

          4. You must not be able to see an attachment post.

       2. There are segment burns or cracks that can cause a piece of segment material more than 0.50 in. (12.70 mm) In length to break off.

    5. Reject if:

       1. There is a segment burn-through hole that is more than 1.00 in. (25.4 mm) in length.

       2. There is damage to the rails around the igniter holes on the row 1 igniter segment more than 135 degrees.

       3. There are segment burn-through holes that show an attachment post.

       4. There is liner shell damage (burn-through or cracks) that is more than 0.500 in.2 (322.58 mm2) in area or occurs in more than three locations that are less than 0.500 in.2 (322.58 mm2) in area.

14. SUBTASK 72-00-00-220-064 Bulkhead Segment Cracks

    1. Refer to Figure.

    2. Accept all bulkhead segments without a decreased inspection time if:

       1. There is no more than one crack on each side of the bulkhead segment. There is no limit to the length of the crack.

       2. There are two or more cracks on the same side of the bulkhead segment, as long as only one crack exceeds the 0.375 in. (9.52 mm) and the remaining cracks are less than 0.375 in. (9.52 mm).

    3. Accept all bulkhead segments with a 600 hour repeat borescope inspection if:

       1. There are two or more cracks more than 0.375 in. (9.53 mm) on the same side of one or more bulkhead segments.

    4. Accept all bulkhead segments with a 300 hour repeat borescope inspection if:

       NOTE

       You must also do a borescope inspection of the Stage 1 HPT Blades TASK 72-00-00-200-004-A00 (Inspection-004) each 300 hours if the combustor is on a 300 hour repeat borescope inspection for bulkhead segment cracking.

       1. There are cracks that may liberate a piece of material equal to or less than 0.25 in. 2 (161.29 mm2).

       2. There are two or more cracks on the same side of one or more bulkhead segments. At least two cracks of each bulkhead segment extend from the edge of the bulkhead segment under the fuel nozzle guide. These cracks must be separated by less than 0.50 in. (12.70 mm).

    5. Reject if:

       1. There are cracks that may liberate a piece of material more than 0.25 in.2 (161.29 mm2 ).

       2. There are two or more cracks on the same side of a bulkhead segment. At least one crack extends from the edge of the bulkhead segment under the fuel nozzle guide. These cracks are separated by more than 0.50 inch (12.70 mm).

15. SUBTASK 72-00-00-220- 065 Bulkhead Segment Burns and Burn-Through Holes

    1. Refer to Figure and Figure.

    2. Accept all bulkhead segments without a decreased borescope inspection time if:

       1. As much as all the surface is burned.

       2. There is one bulkhead segment burn-through hole less than 2.00 in. (50.8 mm) in length and the following conditions are met:

          1. There must be no damage to the bulkhead liner below.

          2. A bulkhead segment attachment post must not be visible.

       3. There are multiple bulkhead segment burn-through holes less than 1.00 in. (25.4 mm) in length and the following conditions are met:

          1. There must be no damage to the bulkhead liner below.

          2. A bulkhead segment attachment post must not be visible.

    3. Accept all bulkhead segments with an inspection each 600 hours if:

       1. There is one bulkhead segment bum-through hole more than 2.00 in. (25.4 mm) but less than 3.00 in. in length and the following conditions are met:

          1. There must be no damage to the bulkhead liner below.

          2. A bulkhead segment attachment post must not be visible.

       2. There are multiple bulkhead segment burn-through holes more than 1.00 in. (25.40 mm) but less than 1.50 in. (38.10 mm) in length and the following conditions are met:

          1. There must be no damage to the bulkhead liner below.

          2. A bulkhead segment attachment post must not be visible.

    4. Reject if:

       1. There is one bulkhead segment burn-through hole that is more than 3.00 in. (76.20 mm) in length.

       2. There are multiple bulkhead segment burn-through holes that are more than 1.50 in. (38.10 m) in length.

       3. There Is a bulkhead liner burn-through hole that is more than 0.50 in.2 (322.58 mm2) in area.

       4. There is a bulkhead liner segment attachment post visible.

16. SUBTASK 72-00-00-220-066 Bulkhead Deflector Cracks

    1. Accept all bulkhead deflectors, Figure and Figure without a decreased borescope inspection time if:

       1. There are cracks that are not circumferential.

       2. There are circumferential cracks that can cause less than 0.500 in. (12.7 mm) in length of break off.

    2. Reject if:

       1. There is a circumferential crack that can cause material more than 0.500 in. (12.7 mm) in length to break off.

17. SUBTASK 72-00-00-220-067 Bulkhead Deflector Burns

    1. Refer to Figure, Figure and Figure.

    2. Accept all bulkhead deflectors without decreased borescope time if:

       1. There are surface burns or base material burns that are less than the full deflector thickness.

       2. There are full material thickness burns that are a minimum of 0.280 in. (7.11 mm) from the combustion holes.

    3. Accept all bulkhead deflectors with an inspection each 1000 hours if:

       1. There are full material thickness burns between 0.230 and 0.280 in. (5.84 and 7.11 mm) from the combustion air holes.

    4. Accept all bulkhead deflectors with an inspection each 600 hours if:

       1. There are full material thickness burns between 0.180 and 0.230 in. (4.57 and 5.84 mm) from the combustion air holes.

    5. Accept all bulkhead deflectors with an inspection each 300 hours if:

       1. There are full material thickness burns between 0.130 and 0.180 in. (3.30 and 4.57 mm) from the combustion air holes.

       2. There is localized burning in a "V" notch pattern, with the point of the "V" directed toward and on a radial line with the combustion air holes on the deflector radially inward to within 0.080 in. (2.03 mm) of the combustion holes.

       3. There are full material thickness burns that are less than 0.130 in. (3.30 mm) from the combustion air holes but do not break into the combustion air holes. This burning can extend for a maximum of 180 degrees around the circumference of the deflector. This is acceptable at a maximum of four locations around the circumference of the combustor. Deflectors with this condition must be separated by a minimum of three deflectors with full material thickness burns that are more than 0.130 in. (3.30 mm) from the combustion air holes. It is not acceptable at the igniter locations or the locations adjacent to the igniters.

    6. Reject if:

       1. There are burns that are more than the limits in Step thru Step.

18. SUBTASK 72-00-00-220-068 End Cap Heatshield Damage on the Fuel Nozzles

    1. Refer to Figure, Figure and Figure.

    2. Accept the nozzle if:

       1. The clearance between the end cap and the nozzle is fully closed.

       2. There is no limit to the number of radial circumferential cracks in the end cap heatshield.

       3. Some or all of the end cap segments are broken away.

    3. Replace the fuel nozzle if:

       1. There are cracks, distortion, erosion or other damage on the areas adjacent to the end cap heatshleld.

19. SUBTASK 72-00-00-020- 056 Remove the Borescope Equipment from the Borescope Inspection Ports

20. SUBTASK 72-00-00-420-056- A00 Close the Borescope Inspection Ports, after the Borescope Inspection is Completed, as follows: (Pre SBE 72- 0221)

    1. For the B1 through B5 ports:

       1. Lubricate the plug ENGINE-DIFFUSER CASE ASSEMBLY AND FITTINGS (72-42 -10, 01-020) threads with CoMat 10-129 ANTI-SEIZE PASTE or CoMat 10-094 ANTI-SEIZE COMPOUND, PURE Ni-SPECIAL.

          NOTE

          It is permissible to correct minor thread damage to a threaded hole with a Tap 0.5625-18 UNJF-3B.

       2. Install the plugs and the ENGINE-DIFFUSER CASE ASSEMBLY AND FITTINGS (72-42-10, 01-010) gaskets 5 off, Figure. Wipe off excess paste.

       3. Torque the plugs to 70 to 80 lbf.in (7.91 to 9.04 Nm).

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

    2. For the IP1 and IP2 ports:

       1. Install the igniter plugs, and torque to 300 to 360 * lbf.in (33.895 to 40.675 Nm).

21. SUBTASK 72-00-00-420-056- B00 Close the Borescope Inspection Ports after the Borescope Inspection is Completed, as follows: (SBE 72- 0221)

    1. SBE 72- 0221: Introduce a new diffuser case

    2. For the B1 to B6 ports:

       1. Lubricate the plug ENGINE-DIFFUSER CASE ASSEMBLY AND FITTINGS (72-42 -10, 01-020) threads with CoMat 10-129 ANTI-SEIZE PASTE or CoMat 10-094 ANTI-SEIZE COMPOUND, PURE Ni-SPECIAL.

          NOTE

          It is permissible to correct minor thread damage to a threaded hole with a tap 0.5625 - 18 UNJF-3B.

       2. Install the plugs and the ENGINE-DIFFUSER CASE ASSEMBLY AND FITTINGS (72-42-10, 01-010) gaskets 6 off, Figure. Wipe off excess paste.

       3. Torque the plugs to 70 to 80 lbf.in (7.91 to 9.04 Nm).

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

    3. For the IP1 and IP2 ports:

       1. Install the igniter plugs, and torque to 300 to 360 lbf.in (33.895 to 40.675 Nm).

Figure: Pre SBE 72-0721: Borescope Ports for Inspection of the Combustion Chamber Liners and the Stage 1 HPT Vanes (Left Side)

Pre SBE 72-0721: Borescope Ports for Inspection of the Combustion Chamber Liners and the Stage 1 HPT Vanes (Left Side)



Figure: SBE 72-0221: Borescope Ports for the Inspection of the Combustion Chamber Liners and First Stage Vanes (Left Side)

SBE 72-0221: Borescope Ports for the Inspection of the Combustion Chamber Liners and First Stage Vanes (Left Side)



Figure: Pre SBE 72-0221: Borescope Ports for Inspection of the Combustion Chamber Liners and the Stage 1 HPT Vanes (Right Side)

Pre SBE 72-0221: Borescope Ports for Inspection of the Combustion Chamber Liners and the Stage 1 HPT Vanes (Right Side)



Figure: SBE 72-0221: Borescope Ports for Inspection of the Combustion Chamber Liners and first Stage Vanes (Right Side)

SBE 72-0221: Borescope Ports for Inspection of the Combustion Chamber Liners and first Stage Vanes (Right Side)



Figure: Stage 1 HPT Vane Area Names and Dimensional References

Stage 1 HPT Vane Area Names and Dimensional References



Figure: Stage 1 HPT Vane Area Names

Stage 1 HPT Vane Area Names



Figure: Stage 1 HPT Vane Area Names and Dimensional References

Stage 1 HPT Vane Area Names and Dimensional References



Figure: Stage 1 HPT Vane Area Names and Types of Damage

Stage 1 HPT Vane Area Names and Types of Damage



Figure: Stage 1 HPT Vane Area Names and Types of Damage

Stage 1 HPT Vane Area Names and Types of Damage



Figure: Stage 1 HPT Vane Area Names and Dimensional References

Stage 1 HPT Vane Area Names and Dimensional References



Figure: Stage 1 HPT Vane Area Names and Types of Damage

Stage 1 HPT Vane Area Names and Types of Damage



Figure: Combustion Chamber Area Names

Combustion Chamber Area Names



Figure: Inner Combustion Chamber Liner Dimensions References

Inner Combustion Chamber Liner Dimensions References



Figure: Outer Combustion Chamber Liner Dimensions References

Outer Combustion Chamber Liner Dimensions References



Figure: Pre SBE 72-0221: Borescope Parts

Pre SBE 72-0221: Borescope Parts



Figure: SBE 72-0221: Borescope Parts

SBE 72-0221: Borescope Parts



Figure: Pre SBE 72-0221: Borescope Inspection Ports for the Stage 1 HPT Vanes and the Combustion Chamber Liner

Pre SBE 72-0221: Borescope Inspection Ports for the Stage 1 HPT Vanes and the Combustion Chamber Liner



Figure: SBE 72-0221: Borescope Inspection Ports for the First Stage Vanes and the Combustion Chamber Liner

SBE 72-0221: Borescope Inspection Ports for the First Stage Vanes and the Combustion Chamber Liner



Figure: Combustion Chamber Liner Segments Borescope Inspection Guide Lines

Combustion Chamber Liner Segments Borescope Inspection Guide Lines



Figure: Combustion Chamber Liner Segment Burn Limits

Combustion Chamber Liner Segment Burn Limits



Combustion Chamber Liner Segment Burn Limits



Figure: Liner (Bulkhead) Segment Inspection Areas and Cracks

Liner (Bulkhead) Segment Inspection Areas and Cracks



Figure: Combustion Chamber Bulkhead Segment Burn-Through Hole

Combustion Chamber Bulkhead Segment Burn-Through Hole



Figure: Combustion Chamber Bulkhead Deflector Cracks and Burnback

Combustion Chamber Bulkhead Deflector Cracks and Burnback



Figure: Burnback limits for combustion chamber rejection

Burnback limits for combustion chamber rejection



Figure: Burnback Limits for 300 Hour Inspection

Burnback Limits for 300 Hour Inspection



Figure: Combustion Chamber Outer Liner Row 1 (with Igniter Holes)

Combustion Chamber Outer Liner Row 1 (with Igniter Holes)



Figure: Combustion Chamber Outer Liner Row 2

Combustion Chamber Outer Liner Row 2



Figure: Combustion Chamber Outer Liner Row 3

Combustion Chamber Outer Liner Row 3



Figure: Combustion Chamber Outer Liner Row 4

Combustion Chamber Outer Liner Row 4



Figure: Combustion Chamber Inner Liner Row 2

Combustion Chamber Inner Liner Row 2



Figure: Combustion Chamber Inner Liner Row 3

Combustion Chamber Inner Liner Row 3



Figure: Combustion Chamber Inner Liner Row 4

Combustion Chamber Inner Liner Row 4



Figure: Fuel Nozzle Types of Damage

Fuel Nozzle Types of Damage



Figure: Fuel Nozzle End Cap Inspection area

Fuel Nozzle End Cap Inspection area



Figure: Fuel Nozzle End Cap Inspection Area

Fuel Nozzle End Cap Inspection Area



Figure: Combustion Chamber Bulkhead Deflector Burns

Combustion Chamber Bulkhead Deflector Burns