Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes [IAE]

TASK 72-00-00-200-013-B
Borescope Inspection of inside of Combustion Chamber and HP turbine stage 1 Vanes

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 DETERIORATION OF THE ENGINE PERFORMANCE, STABILITY, OPERATING LIMITS OR PART REPAIRABILITY.

ZONE: 400
FIN: 1000EM1 ** ON A/C NOT FOR ALL
FIN: 1000EM2 ** ON A/C NOT FOR ALL

1. Reason for the Job
Refer to the MPD TASK: 724000-I1
BORESCOPE INSPECTION OF INSIDE OF COMBUSTION CHAMBER AND HP TURBINE STAGE 1 VANES.
This task gives the procedure for the borescope inspection of the combustion chamber and the HPT first stage vanes.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	AR	BORESCOPE - FLEXIBLE
No specific	AR	BORESCOPE - RIGHT ANGLE, FLEXSCOPE
No specific	AR	COVER - EYE
No specific	AR	WARNING NOTICE(S)
No specific	Torque wrench: range to between 80 and 70 lbf.in (0.90 and 0.79 m.daN )

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.V02-141)	corrosion resistant steel lockwire
(Material No.V10-094)	anti-seize compound
(Material No.V10-129)	anti-seize paste

C. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
400	POWER PLANT, NACELLES AND PYLONS
FOR [1000EM1] (ENGINE-1)
437AL, 438AR, 451AL, 452AR
FOR [1000EM2] (ENGINE-2)
447AL, 448AR, 461AL, 462AR

D. Expendable Parts

FIG.ITEM	DESIGNATION	IPC-CSN
1	GASKET, OPTION	AIPC 72-42-10-81-010

E. Referenced Information

REFERENCE	DESIGNATION
TASK 70-23-11-911-013-A	General Torque Tightening Techniques
TASK 71-13-00-010-010-A	Opening of the Fan Cowls 437AL(447AL),438AR(448AR)
TASK 71-13-00-410-010-A	Closing of the Fan Cowls 437AL(447AL),438AR(448AR)
TASK 72-00-00-200-014-B	Borescope Inspection of the Stage 1 High Pressure Turbine (HPT) Blades and Duct Segments
TASK 72-00-00-200-014-B-01	Borescope Inspection of the Stage 1 High Pressure Turbine (HPT) Blades and Duct Segments
TASK 74-21-41-000-010-A	Removal of the Igniter Plug
TASK 74-21-41-400-010-A	Installation of the Igniter Plug
TASK 78-30-00-040-012-A	Deactivation of the Thrust Reverser Hydraulic Control Unit (HCU) for Ground Maintenance
TASK 78-30-00-440-012-A	Re-activation of the Thrust Reverser Hydraulic Control Unit (HCU) after Ground Maintenance
TASK 78-32-00-010-010-A	Opening of the Thrust Reverser Halves
TASK 78-32-00-410-010-A	Closing of the Thrust Reverser Halves
Borescope Ports for Inspection of the Combustion Chamber Liners and the First Stage Vanes (Left Side)
Borescope Ports for Inspection of the Combustion Chamber Liners and the First Stage Vanes (Right Side)
Borescope Inspection Ports for the First Stage Vanes and the Combustion Chamber Liner
HPT 1st Stage Vane Area Names and Dimensional References
HPT 1ST Stage Vane Area Names and Dimensional References
HPT 1st Stage Vane Area Names and Dimensional References
HPT 1st Stage vane Area Names and Dimensional References
HPT 1st Stage Vane Area Names and Types of Damage
HPT 1st Stage Vane Area Names and Types of Damage
Combustion Chamber Area Names
Inner Combustion Chamber Liner Dimensions References
Outer Combustion Chamber Liner Segments Dimensions References
Combustion Chamber Liner Segments Borescope Inspection Guidelines
Borescope Ports
HPT 1st Stage Area Names and Dimensional References
Combustion Chamber Damage Form
Combustion Chamber Damage Form
Combustion Chamber Damage Form
Combustion Chamber Damage Form
Combustion Chamber Damage Form
Combustion Chamber Damage Form
Combustion Chamber Damage Form
Combustion Chamber Damage Form
Combustion Chamber Damage Form
Combustion Chamber Damage Form
Combustion Chamber Damage Form
Burnback limits for 300 hour inspection
Burnback Limits for Engine Removal in Less than 30 cycles
Combustion Chamber Outer Liner Row 1
Combustion Chamber Outer Liner Row 2
Combustion Chamber Outer Liner Row 3
Combustion Chamber Outer Liner Row 4
Combustion Chamber Inner Liner Row 2
Combustion Chamber Inner Liner Row 3
Combustion Chamber Inner Liner Row 4
Combustion Chamber Liner Segment Crack Limits
Combustion Chamber Liner Segment Burn Limits
Combustion Chamber Liner Segment Attachment Post Visibility
Liner (Bulkhead) Segment Inspection Areas and Cracks
Combustion Chamber Bulkhead Segment Burn Hole
Bulkhead Deflector Burnback
Combustion Chamber Bulkhead Segment Attachment Post Visibility
Combustion Chamber Bulkhead Deflector Cracks and Burnback
Fuel Nozzle End Cap Inspection Areas
Fuel Nozzle End Cap Inspection Areas
Fuel Nozzle Types of Damage

3. Job Set-up
Subtask 72-00-00-941-089-A ** ON A/C NOT FOR ALL

A. Safety Precautions
(1) On the center pedestal, on the ENG panel 115VU:
(a) Put a WARNING NOTICE(S) to tell persons not to start the engine.
(2) Make sure that the engine 1(2) shutdown occurred not less than 5 minutes before you do this procedure.
(3) On the overhead maintenance panel 50VU:
(a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
(b) Put a WARNING NOTICE(S) to tell persons not to energize the FADEC 1(2).

Subtask 72-00-00-010-123-A ** ON A/C NOT FOR ALL

B. Get Access
(1) Open the fan cowls (Ref. AMM TASK 71-13-00-010-010):
(a) FOR [1000EM1] (ENGINE-1)
437AL, 438AR
(b) FOR [1000EM2] (ENGINE-2)
447AL, 448AR.

Subtask 72-00-00-040-076-A ** ON A/C NOT FOR ALL

C. Deactivate the Thrust Reverser

WARNING: MAKE SURE THAT THE THRUST REVERSER HYDRAULIC CONTROL UNIT (HCU) IS DEACTIVATED BEFORE YOU DO WORK ON OR AROUND THE THRUST REVERSER. IF THE HCU IS NOT DEACTIVATED, THERE IS A RISK OF UNWANTED THRUST REVERSER OPERATION WHICH CAN CAUSE INJURY TO PERSONS AND/OR DAMAGE TO EQUIPMENT.

(1) Deactivate the thrust reverser Hydraulic Control Unit (HCU) (Ref. AMM TASK 78-30-00-040-012).

Subtask 72-00-00-010-117-A ** ON A/C NOT FOR ALL

D. Get Access
(1) Open the thrust reverser halves (Ref. AMM TASK 78-32-00-010-010):
(a) FOR [1000EM1] (ENGINE-1)
451AL, 452AR
(b) FOR [1000EM2] (ENGINE-2)
461AL, 462AR.

4. Procedure
Subtask 72-00-00-290-072-A ** ON A/C NOT FOR ALL

A. General

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

(1) There are six borescope ports and two igniter ports to give access to the combustion chamber and the HPT 1st stage vanes.

Borescope Ports for Inspection of the Combustion Chamber Liners and the First Stage Vanes (Left Side) ** ON A/C NOT FOR ALL

Borescope Ports for Inspection of the Combustion Chamber Liners and the First Stage Vanes (Right Side) ** ON A/C NOT FOR ALL

Borescope Inspection Ports for the First Stage Vanes and the Combustion Chamber Liner ** ON A/C NOT FOR ALL

(2) The names of different parts and dimensional references of the combustion chamber and the HPT 1st stage vanes are shown.

HPT 1st Stage Vane Area Names and Dimensional References ** ON A/C NOT FOR ALL

HPT 1ST Stage Vane Area Names and Dimensional References ** ON A/C NOT FOR ALL

HPT 1st Stage Vane Area Names and Dimensional References ** ON A/C NOT FOR ALL

HPT 1st Stage vane Area Names and Dimensional References ** ON A/C NOT FOR ALL

HPT 1st Stage Vane Area Names and Types of Damage ** ON A/C NOT FOR ALL

Combustion Chamber Area Names ** ON A/C NOT FOR ALL

Inner Combustion Chamber Liner Dimensions References ** ON A/C NOT FOR ALL

Outer Combustion Chamber Liner Segments Dimensions References ** ON A/C NOT FOR ALL

Use these names when identifying borescope inspection limits.
(3) Use these terms when you identify a combustion chamber condition seen during borescope inspection:
(a) BURN: A local area of burner liner segment, bulkhead segment, or deflector surface that has changed colour, has a rough surface texture or shows thinner material because of high temperatures. Burns can be located all around but more are found downstream of combustion holes in the burner liner segments.
(b) BURN - THROUGH HOLE: A local burn area that has continued through the base material, and does not extend to the leading or trailing edge of the segment.

Combustion Chamber Liner Segments Borescope Inspection Guidelines ** ON A/C NOT FOR ALL

(c) EDGE BURNBACK: Full thickness liner segment burns that start at an edge, occur more at the segment trailing edge location but have also occurred at the leading edge. Burnback is segment material that is missing. Complete edge burnback is when segment material is missing from the trailing edge to the leading edge.

Combustion Chamber Liner Segments Borescope Inspection Guidelines ** ON A/C NOT FOR ALL

(d) RADIAL BURNBACK: Full thickness burning on deflector edge continuing radially inward toward fuel nozzle.
(e) THROUGH CRACK: A crack on the surface of the segment material that has penetrated beyond the surface into and past the parent material. Typically the crack will be black in color and liner segment separation will be visible at the crack location.
(f) NON-THROUGH CRACK: An indication / crack on the segment material which does not extend beyond segment material. Non-through cracks are acceptable as-is and should not be added to the measurement of the through crack.
(4) General inspection guidelines:
(a) Give the results of decreased time inspections to your IAE representative.
(b) If a piece of combustion chamber materials breaks off between inspection times, a borescope inspection of the high pressure turbine is necessary. If the high pressure turbine is not damaged after the material breaks off you can continue the combustion chamber borescope inspections at the times given by other limits.
(c) All spalled ceramic coating on the combustor segments, the bulkhead segments or the bulkhead deflectors is acceptable without a decreased borescope inspection time.
(d) Bulkhead and liner segments: Any coating loss on the bulkhead/liner segment due to cracks is not considered as material liberation or break off. Material liberation or break off is defined as the coating loss along with the bulkhead/liner segment parent material missing.
(5) Use these terms when you identify an HPT 1st stage vane condition seen during borescope inspection:
(a) BURNS: A local area of 1st stage vane surface that has changed colour, has a rough surface texture or shows thinner material because of high temperatures. Burns can be located all around.
(b) BURN THROUGH: A local burn area that has continued through the airfoil surface. Cracks that have burned to more than 0.050 in. (1.27 mm) separation are also burn through.
(c) TRAILING EDGE BURNS: Burns or burn through that start at the airfoil trailing edge and continue forward to the airfoil leading edge.
(d) LIFT UP: An area where the surface on one side of a crack is higher than the surface on the other side of the crack.
(e) COATING DAMAGE: Chips, spalling, flakes, blisters, peeling or oxidation that is confined to the coating.
(f) CONNECTED LOOP CRACK: A crack or a group of cracks that show an isolated area of vane metal.
(g) LEADING EDGE: The area from the first row of cooling holes on the concave side of the vane to the first row of cooling holes on the convex side of the vane.
(6) General inspection guidelines:
(a) Give the results of decreased time inspections to your IAE representative.
(b) All ceramic coating damage is acceptable without a decreased borescope inspection time. Extended operation with a large quantity of ceramic coating not there can possibly cause the vane to be out of limits and cannot be repaired at overhaul.

Subtask 72-00-00-010-106-A ** ON A/C NOT FOR ALL

B. Get access to the combustion chamber and the HPT 1st stage vanes through the B1 to B6 and IP1 and IP2 ports as follows:
(1) For the B1 to B6 ports, remove the 6 plugs and gaskets at the locations shown.

Borescope Ports ** ON A/C NOT FOR ALL

(2) For the IP1 and IP2 ports, remove the igniter plugs (Ref. AMM TASK 74-21-41-000-010).

Borescope Ports ** ON A/C NOT FOR ALL

NOTE: Do not remove the igniter insert.

Subtask 72-00-00-290-073-A ** ON A/C NOT FOR ALL

C. Examine the combustion chamber, fuel injectors and the first stage vanes for damage

(1) Put the BORESCOPE - RIGHT ANGLE, FLEXSCOPE or BORESCOPE - FLEXIBLE in to the ports and examine the combustion chamber, fuel injectors and the first stage vanes for damage.

Borescope Ports ** ON A/C NOT FOR ALL

NOTE: An COVER - EYE is recommended for the eye that is not used, to decrease eye tension.

(2) If damage seen is not listed, contact your IAE representative.

Subtask 72-00-00-220-077-A ** ON A/C NOT FOR ALL

D. Convex and Concave Surface Cracks/Burns

HPT 1st Stage Vane Area Names and Dimensional References ** ON A/C NOT FOR ALL

HPT 1st Stage Vane Area Names and Types of Damage ** ON A/C NOT FOR ALL

HPT 1st Stage Area Names and Dimensional References ** ON A/C NOT FOR ALL

NOTE: All cracks or sections of cracks burned to a width of more than 0.05 in. (1.27 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 the leading edge criteria.

(1) Accept with an inspection each 600 hours if:
(a) There is more than one axial crack 3/4 chord length or longer. Axial and radial cracks can go through each other.
(b) There are many radial cracks that are more than 1.50 in. (38.10 mm) in length. Axial cracks can go through radial cracks.
(c) There is a burn that has caused a burn-through that is between 0.05 in. (1.27 mm) and 0.10 in. (2.54 mm) at its shortest dimension.
(2) Accept with an inspection each 300 hours if:
(a) There is a burn that has caused a burn-through that is between 0.10 in. (2.54 mm) and 0.30 in. (7.62 mm) at its shortest dimension.
(3) Remove the engine in less than 10 cycles and tell your IAE representative if:
(a) There is axial or radial crack lift-up of more than 0.05 in. (1.27 mm).
(b) There are connected loop cracks that show a piece of vane metal that is calculated to be more than 0.50 in. (12.70 mm) in length.
(c) There is a crack that is three-quarters of a chord length long or longer that also goes into a leading edge or a convex surface burn-through.
(d) There is a burn that has caused a burn-through that is more than 0.30 in. (7.62 mm) at its shortest dimension.

Subtask 72-00-00-220-078-A ** ON A/C NOT FOR ALL

E. Leading Edge Cracks and Leading Edge Burns

HPT 1st Stage vane Area Names and Dimensional References ** ON A/C NOT FOR ALL

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

(1) Accept with an inspection each 600 hours if:
(a) There are leading edge cracks and burns that have caused base vane material burn through within the leading edge cooling holes and it measures less than 0.85 in. (21.59 mm) in length radially.
(2) Accept with an inspection each 300 hours if:
(a) There is leading edge base vane material burn through that extends less than 0.20 in. (5.08 mm) beyond the first row of leading edge cooling air holes and it measures less than 0.65 in. (16.51 mm) axially and 0.85 in. (21.59 mm) radially.
(3) Accept with an inspection each 75 hours if:
(a) There is leading edge base vane material burn through that extends less than 0.25 in. (6.35 mm) beyond the first row of leading edge cooling holes and it measures less than 0.65 in. (16.51 mm) axially and 0.85 in. (21.59 mm) radially.
(4) Remove the engine in less than 10 cycles and tell your IAE representative if:
(a) There is leading edge base vane material burn through that extends more than 0.25 in. (6.35 mm) beyond the leading edge cooling air holes.
(b) There is leading edge base vane material burn through of more than 0.85 in. (21.59 mm) radially.
(c) There is leading edge base vane material burn through of more than 0.65 in. (16.51 mm) axially.
(d) There is leading edge axial burn-through, plus an axial crack and/or burn through from the trailing edge that total three quarters of the chord in length.
(e) There is axial leading edge base vane material burn through plus a crack that measures three quarters of the cord length.
(f) There is baffle burn-through.
(g) There is baffle cracking.

Subtask 72-00-00-220-109-A ** ON A/C NOT FOR ALL

F. Trailing Edge Burns

HPT 1st Stage vane Area Names and Dimensional References ** ON A/C NOT FOR ALL

(1) Accept with an inspection each 600 hours if:
(a) There is a burn through that goes between one quarter and one half of the chord length from the trailing edge and is more than 0.50 in. (12.70 mm) in width at the trailing edge.

NOTE: 0.50 in. (12.70 mm) is equal to five trailing edge cooling air slots.

NOTE: One-quarter chord is equal to the second row of cooling holes from the trailing edge or 0.50 in. (12.70 mm).
One half-chord is equal to the fifth row of cooling holes from the trailing edge or 1.00 in. (25.40 mm).
Three-quarter chord is equal to 1.50 in. (38.10 mm).

(2) Accept with an inspection each 300 hours if:
(a) 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 0.50 in. (12.70 mm) in width at the trailing edge.

NOTE: 0.50 in. (12.70 mm) is equal to five trailing edge cooling air slots.

(3) Remove the engine in less than 10 cycles and tell your IAE representative if:
(a) There is a burn-through that goes more than three quarters of the chord length from the trailing edge and is more than 0.50 in. (12.70 mm) in width at the trailing edge.

NOTE: 0.50 in. (12.70 mm) is equal to five trailing edge cooling air slots.

(b) There are signs of burning on the inner platform within 0.50 in. (12.70 mm) of the trailing edge and trailing edge burning inside the first cooling slots at the inner diameter.

HPT 1st Stage Vane Area Names and Types of Damage ** ON A/C NOT FOR ALL

Subtask 72-00-00-220-110-A ** ON A/C NOT FOR ALL

G. Cracks on the Inner and Outer Platforms

HPT 1st Stage Vane Area Names and Types of Damage ** ON A/C NOT FOR ALL

(1) Accept with an inspection each 600 hours if:
(a) There is a crack that is more than 0.50 in. (12.70 mm) in length.
(2) Accept with an inspection each 300 hours if:
(a) There is a crack that is more than 1.00 in. (25.40 mm) in length.
(3) Remove the engine in less than 10 cycles and tell your IAE representative if:
(a) There is a crack that is parallel to the airfoil fillet radius, that goes around the airfoil leading edge and that is more than 1.50 in. (38.10 mm) in length.

Subtask 72-00-00-220-111-A ** ON A/C NOT FOR ALL

H. Cracks on the Inner and Outer Platform Airfoil Fillet Radii

HPT 1st Stage Vane Area Names and Types of Damage ** ON A/C NOT FOR ALL

(1) Accept with an inspection each 600 hours if:
(a) There is a filler crack that is more than 1.00 in. (25.40 mm) in length and that goes from the fillet on to the airfoil.
(2) Remove the engine in less than 10 cycles and tell your IAE representative if:
(a) There is a crack that is more than 1.00 in. (25.40 mm) in length and a part of the length is eroded to a width of more than 0.03 in. (0.76 mm).
(b) There is a crack in the fillet radius that is more than 1.50 in. (38.10 mm) in length and that goes around the airfoil leading edge.

Subtask 72-00-00-220-133-A ** ON A/C NOT FOR ALL

I. Burns on the Inner and Outer Platform

HPT 1st Stage Vane Area Names and Types of Damage ** ON A/C NOT FOR ALL

(1) Accept with an inspection each 600 hours if:
(a) There are burns that go from the edge of the platform to the platform airfoil fillet.
(2) Accept with an inspection each 300 hours if:
(a) There are burns that have caused a burn through that is less than 0.25 in. (6.35 mm) in length.
(3) Remove the engine in less than 10 cycles and tell your IAE representative if:
(a) There are burns that have caused a burn through that is more than 0.25 in. (6.35 mm) in length.

Subtask 72-00-00-220-112-A ** ON A/C NOT FOR ALL

J. Make a record of the damage that you find when you do a borescope inspection of the combustion chamber
(1) Use the Combustion Chamber Damage Forms to record the damage.

Combustion Chamber Damage Form ** ON A/C NOT FOR ALL

Subtask 72-00-00-220-113-A ** ON A/C NOT FOR ALL

K. Segment Cracks
(1) Accept segments that have combustion holes without a decreased borescope inspection time if:
(a) 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 hole without a crack.
(b) 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 0.70 in. (17.78 mm) from a circumferential edge.
(2) Accept segments that do not have combustion holes without a decreased borescope inspection time if:
(a) There is one crack completely through axially and that is more than 0.70 in. (17.78 mm) from a circumferential edge.
(3) Accept segments that have combustion holes with an inspection each 750 hours if:
(a) There are two or more cracks downstream of a combustion hole and one of the cracks goes from the combustion hole to the trailing edge and no other crack goes more than half the distance to the same combustion hole or trailing edge.
(4) Accept segments that do not have combustion holes with an inspection each 750 hours if:
(a) There are two or more axial cracks, one crack is completely through the segment and is more than 0.70 in. (17.78 mm) from a circumferential edge. No other crack is more than half the axial length of the segment or nearer than 0.70 in. (17.78 mm) to a circumferential edge.
(5) Accept segments 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 (Ref. AMM TASK 72-00-00-200-014) each 300 hours if the liner segments are on a 300-hour repeat borescope inspection for segment cracking.

(a) There are 2, 3 or 4 cracks completely through axially and each crack goes through a combustion hole and at least two cracks go through adjacent combustion holes.
(b) There are two or more cracks downstream of a combustion hole, one crack goes from a combustion hole to the trailing edge and no other crack goes more than two thirds of the distance to the same combustion hole or trailing edge
(c) There are cracks that can cause a piece of segment material up to 0.25 in.2 (161.29 mm2) in area to break off.

NOTE: Material break off is defined as the coating loss along with the liner segment parent material missing.

(6) Accept segments that do not have combustion holes with an inspection each 300 hours if:

(a) There are two or more axial cracks, one crack is completely through the segment and is more than 0.70 in. (17.78 mm) from a circumferential edge. No other crack is more than two thirds the axial length of the segment or nearer than 0.70 in. (17.78 mm) to a circumferential edge.
(b) There are cracks that can cause a piece of segment material up to 0.25 in.2 (161.29 mm2) in area to break off.

NOTE: Material break off is defined as the coating loss along with the liner segment parent material missing.

(7) All segments, remove the engine in less than 30 cycles and tell your IAE representative if:
(a) There are cracks that can cause a piece of segment material that is more than 0.25 in.2 (161.29 mm2) in area to break off.

NOTE: Material break off is defined as the coating loss along with the liner segment parent material missing.

Subtask 72-00-00-220-114-A ** ON A/C NOT FOR ALL

L. Segment Edge Burnback

Burnback limits for 300 hour inspection ** ON A/C NOT FOR ALL

Burnback Limits for Engine Removal in Less than 30 cycles ** ON A/C NOT FOR ALL

Combustion Chamber Outer Liner Row 1 ** ON A/C NOT FOR ALL

Combustion Chamber Outer Liner Row 2 ** ON A/C NOT FOR ALL

Combustion Chamber Outer Liner Row 3 ** ON A/C NOT FOR ALL

Combustion Chamber Outer Liner Row 4 ** ON A/C NOT FOR ALL

Combustion Chamber Inner Liner Row 2 ** ON A/C NOT FOR ALL

Combustion Chamber Inner Liner Row 3 ** ON A/C NOT FOR ALL

Combustion Chamber Inner Liner Row 4 ** ON A/C NOT FOR ALL

(1) Accept segments without a decreased borescope inspection if:
(a) There is 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 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.
(2) Accept segments with an inspection each 750 hours if:
(a) The edge burnback is between 0.70 in. (17.78 mm) and 0.90 in. (22.86 mm) and the following conditions are met:

Combustion Chamber Liner Segment Crack Limits ** ON A/C NOT FOR ALL

1 There is no liner shell damage (burn-through or cracks).
2 There is damage to 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 the segments with an inspection each 300 hours if:
(a) The edge burnback is more than 0.90 in. (22.86 mm) and the conditions that follow are met:

Burnback limits for 300 hour inspection ** ON A/C NOT FOR ALL

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 One attachment post is visible up to 50 percent in one or more liner segments.

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

(b) The inner burner assembly has two each segments with complete edge burnback.

NOTE: The inner and outer segments having complete edge burnback must not be opposite of each other.

(4) If the edge burnback is more than 1.00 in. (25.40 mm) you must do a borescope inspection of the Stage 1 HPT Blades (Ref. AMM TASK 72-00-00-200-014) each 300 hours.
(5) Remove the engine in less than 30 cycles and tell your IAE representative if:
(a) There is one area of complete edge burnback on one segment and another area of edge burnback is more than 1.00 in. (25.40 mm) on the same segment.
(b) There are more than two segments with complete edge burnback. Refer to

Burnback Limits for Engine Removal in Less than 30 cycles ** ON A/C NOT FOR ALL

for burnback inspection limits which need engine removal in less than 30 cycles.
(c) There is damage to the rails around the igniter holes on the row 1 igniter segment more than 135 degrees.
(d) There is edge burnback that shows an attachment post more than 50 percent or an attachment post is missing.
(e) There is combined inner and outer liner shell damage (burn-through or cracks) that is more than 0.50 in.2 (322.58 mm2) in area.
(f) The total damage locations on the inner combustion chamber liner shell exceeds 3.
(g) The total damage locations on the outer combustion chamber liner shell exceeds 3.
(h) The inner burner assembly has three or more segments with complete edge burnback.
(i) The outer burner assembly has three or more segments with complete edge burnback.

Subtask 72-00-00-220-115-A ** ON A/C NOT FOR ALL

M. Surface Burns and Burn-Through Holes in Liner Segments
(1) Accept segments (with or without combustion holes)

Combustion Chamber Liner Segment Burn Limits ** ON A/C NOT FOR ALL

without a decreased borescope inspection time if:
(a) As much as all the surface is burned.
(b) There are segment burn-through holes that are less 0.35 in. (8.89 mm) in length and the following conditions are met:
1 There must be no liner shell damage (burns, burn-through, 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.
(2) Accept segments (with or without combustion holes)

Combustion Chamber Liner Segment Burn Limits ** ON A/C NOT FOR ALL

with an inspection each 600 hours if:
(a) There is a segment burn-through hole that is between 0.35 in. (8.89 mm) and 0.65 in. (16.51 mm) in length and the following conditions are met:
1 There must be no liner shell damage (burns, burn-through, 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)

Combustion Chamber Liner Segment Burn Limits ** ON A/C NOT FOR ALL

Combustion Chamber Liner Segment Attachment Post Visibility ** ON A/C NOT FOR ALL

with an inspection each 300 hours if:
(a) There is a segment burn-through hole that is between 0.65 in. (16.51 mm) and 1.00 in. (25.40 mm) in length and the following conditions are met:
1 Liner shell damage (burns, burn-through, cracks) must not have an area of more than 0.50 in.2 (322.58 mm2).
2 Liner shell damage (burns, burn-through, cracks) must not occur in more than three locations.
3 There is damage to the rails around the igniter holes in the igniter segment less than 135 degrees.
4 One attachment post is visible up to 50 percent in one or more liner segments.
(b) 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.
(4) Segments (with or without combustion holes),

Combustion Chamber Liner Segment Crack Limits ** ON A/C NOT FOR ALL

Combustion Chamber Liner Segment Burn Limits ** ON A/C NOT FOR ALL

Combustion Chamber Liner Segment Attachment Post Visibility ** ON A/C NOT FOR ALL

remove the engine in less than 30 cycles and tell your IAE representative if:
(a) There is a segment burn-through hole that is more than 1.00 in. (25.40 mm) in length.
(b) There are segment burn-through holes that go in to the rail around the igniter holes in the igniter segment more than the limit.

Combustion Chamber Liner Segment Crack Limits ** ON A/C NOT FOR ALL

(c) One attachment post is visible more than 50 percent in one or more liner segments.
(d) More than one attachment post is visible on one or more liner segment.
(e) There is combined inner and outer liner shell damage (burn-through or cracks) that is more than 0.50 in.2 (322.58 mm2) in area.
(f) The total damage locations on the inner combustion chamber liner shell exceeds 3.
(g) The total damage locations on the outer combustion chamber liner shell exceeds 3.

Subtask 72-00-00-220-116-A ** ON A/C NOT FOR ALL

N. Bulkhead Segment Cracks
(1) Accept all bulkhead segments without a reduced inspection if:

Liner (Bulkhead) Segment Inspection Areas and Cracks ** ON A/C NOT FOR ALL

(a) There is no more than one crack on any side of the bulkhead segment. There is no limit to the length of the crack.
(b) 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).
(2) Accept all bulkhead segments with a 750-hour repeat borescope inspection if:

Liner (Bulkhead) Segment Inspection Areas and Cracks ** ON A/C NOT FOR ALL

(a) There are two or more cracks more than 0.375 in. (9.52 mm) on the same side of any bulkhead segment.
(3) Accept all bulkhead segments with a 300-hour repeat borescope inspection if:

Liner (Bulkhead) Segment Inspection Areas and Cracks ** ON A/C NOT FOR ALL

NOTE: You must also do a borescope inspection of the stage 1 HPT blades (Ref. AMM TASK 72-00-00-200-014) each 300 hours if the combustor is on a 300-hour repeat borescope inspection for bulkhead segment cracking.

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

NOTE: Material liberation is defined as the coating loss along with the segment parent material missing.

(b) There are two or more cracks on the same side of any bulkhead segment. At least two cracks extend from the edge of the bulkhead segment under the fuel nozzle guide or to the inner rim of the bulkhead segment and another is at least 0.375 in. (9.52 mm). These cracks must be separated by more than 0.50 in. (12.70 mm).
(4) Remove the engine in less than 30 cycles if:

Liner (Bulkhead) Segment Inspection Areas and Cracks ** ON A/C NOT FOR ALL

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

NOTE: Material liberation is defined as the coating loss along with the segment parent material missing.

Subtask 72-00-00-220-117-A ** ON A/C NOT FOR ALL

O. Bulkhead Segment Burns and Burn-Through Holes
(1) Accept all bulkhead segments

Liner (Bulkhead) Segment Inspection Areas and Cracks ** ON A/C NOT FOR ALL

Combustion Chamber Bulkhead Segment Burn Hole ** ON A/C NOT FOR ALL

Bulkhead Deflector Burnback ** ON A/C NOT FOR ALL

without a decreased borescope inspection time if:
(a) As much as all the surface is burned.
(b) There is one bulkhead segment burn-through hole less than 2.00 in. (50.80 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.
(c) There are multiple bulkhead segment burn-through holes less than 1.00 in. (25.40 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.
(2) Accept all bulkhead segments

Liner (Bulkhead) Segment Inspection Areas and Cracks ** ON A/C NOT FOR ALL

Combustion Chamber Bulkhead Segment Burn Hole ** ON A/C NOT FOR ALL

Bulkhead Deflector Burnback ** ON A/C NOT FOR ALL

with an inspection each 750 hours if:
(a) There is one bulkhead segment burn-back or burn-through hole more than 2.00 in. (50.80 mm) but less than 2.75 in. (69.85 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.
(b) 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.
(3) Accept all bulkhead segments with an inspection each 300 hours if:

Combustion Chamber Bulkhead Segment Attachment Post Visibility ** ON A/C NOT FOR ALL

Liner (Bulkhead) Segment Inspection Areas and Cracks ** ON A/C NOT FOR ALL

Combustion Chamber Bulkhead Segment Burn Hole ** ON A/C NOT FOR ALL

(a) There is one bulkhead segment burn-back or burn-through hole more than 2.75 in. (69.85 mm) but less than 3.00 in. (76.20 mm) in length and the following conditions are met:
1 There must be no cracking or burn through to the bulkhead liner below.
(b) One attachment post is visible up to 50 percent in one or more bulkhead segments.
1 There must be no cracking or burn through to the bulkhead liner shell adjacent to the attachment post hole.
(4) Accept all bulkhead segments with an inspection of 200 hours if:

Combustion Chamber Bulkhead Segment Attachment Post Visibility ** ON A/C NOT FOR ALL

(a) One attachment post is visible up to 75 percent in one or more bulkhead segments.
1 There must be no cracking or burn through to the bulkhead liner shell adjacent to the attachment post hole.
(5) Reject all bulkhead segments,

Liner (Bulkhead) Segment Inspection Areas and Cracks ** ON A/C NOT FOR ALL

Combustion Chamber Bulkhead Segment Burn Hole ** ON A/C NOT FOR ALL

Combustion Chamber Bulkhead Segment Attachment Post Visibility ** ON A/C NOT FOR ALL

Bulkhead Deflector Burnback ** ON A/C NOT FOR ALL

remove the engine in less than 30 cycles and tell your IAE representative if:
(a) There is one bulkhead segment burn-through hole that is more than 3.00 in. (76.20 mm) in length.
(b) There are multiple bulkhead segment burn-through holes that are more than 1.50 in. (38.10 mm) in length.
(c) There is a bulkhead liner burn-through hole that is more than 0.50 in.2 (322.58 mm2) in area.
(d) There is a bulkhead liner segment attachment post visible. One attachment post is visible more than 75 percent in one or more bulkhead segments.
(e) More than one attachment post is visible on one or more bulkhead segment.

Subtask 72-00-00-220-118-A ** ON A/C NOT FOR ALL

P. Bulkhead Deflector Cracks
(1) Accept all bulkhead deflectors

Liner (Bulkhead) Segment Inspection Areas and Cracks ** ON A/C NOT FOR ALL

Combustion Chamber Bulkhead Deflector Cracks and Burnback ** ON A/C NOT FOR ALL

without a decreased borescope inspection time if:
(a) There are cracks that are not circumferential.
(b) There are circumferential cracks that can cause material less than 0.50 in. (12.70 mm) in length to break off.
(2) All bulkhead deflectors,

Liner (Bulkhead) Segment Inspection Areas and Cracks ** ON A/C NOT FOR ALL

Combustion Chamber Bulkhead Deflector Cracks and Burnback ** ON A/C NOT FOR ALL

remove the engine in less than 30 cycles and tell your IAE representative if:
(a) There is a circumferential crack that can cause material more than 0.50 in. (12.70 mm) in length to break off.

Subtask 72-00-00-220-134-A ** ON A/C NOT FOR ALL

Q. Bulkhead Deflector Burns
(1) Accept all bulkhead deflectors without a decreased borescope time if:

Liner (Bulkhead) Segment Inspection Areas and Cracks ** ON A/C NOT FOR ALL

Combustion Chamber Bulkhead Deflector Cracks and Burnback ** ON A/C NOT FOR ALL

Bulkhead Deflector Burnback ** ON A/C NOT FOR ALL

(a) There are surface burns or base material burns that are less than the full deflector thickness.
(b) There is full material thickness edge burnback that extends circumferentially to the outer diameter of a total of eight combustion air holes.
1 Burnback can extend radially back to combustion air holes. Cracks which connect full material thickness burnback to combustion air holes are permitted. Cracks can break into combustion air holes.
2 There must be sufficient bulkhead deflector material over the bulkhead segment for correct retention.
(2) Accept all bulkhead deflectors with an inspection each 750 hours if:

Liner (Bulkhead) Segment Inspection Areas and Cracks ** ON A/C NOT FOR ALL

Combustion Chamber Bulkhead Deflector Cracks and Burnback ** ON A/C NOT FOR ALL

Bulkhead Deflector Burnback ** ON A/C NOT FOR ALL

(a) There is full material thickness edge burnback that extends circumferentially to the outer diameter of more than eight and less than 10 total combustion air holes.
1 Burnback can extend radially back to combustion air holes. Cracks which connect full material thickness burnback to combustion air holes are permitted. Cracks can break into combustion air holes.
2 The remaining material must be on opposite sides of the deflector.
3 There must be sufficient bulkhead deflector material over the bulkhead segment for proper retention.
4 Surface burns are unlimited circumferentially.
(3) Accept all bulkhead deflectors.

Liner (Bulkhead) Segment Inspection Areas and Cracks ** ON A/C NOT FOR ALL

Combustion Chamber Bulkhead Deflector Cracks and Burnback ** ON A/C NOT FOR ALL

Bulkhead Deflector Burnback ** ON A/C NOT FOR ALL

with an inspection each 300 hours if:
(a) There is full material thickness edge burnback that extends circumferentially to the outer diameter of 10 and less than 11 total combustion air holes. Surface burns are unlimited circumferentially.
1 Burnback can extend radially back to combustion air holes. Full material burnback can break into one combustion air hole but must not be more than 25% of the combustion air hole circumference.
2 Remaining material must be on opposite sides of the deflector.
3 There must be sufficient bulkhead deflector material over the bulkhead segment for proper retention.
(4) Reject all bulkhead deflectors.

Liner (Bulkhead) Segment Inspection Areas and Cracks ** ON A/C NOT FOR ALL

Combustion Chamber Bulkhead Deflector Cracks and Burnback ** ON A/C NOT FOR ALL

Bulkhead Deflector Burnback ** ON A/C NOT FOR ALL

Remove the engine in less than 30 cycles and tell your IAE representative if:
(a) There is full material thickness edge burnback that extends radially back to combustion air holes and extends circumferentially along the outer diameter of 11 or more total combustion air holes. Surface burns are unlimited circumferentially.
(b) There is full material thickness edge burnback that extends into one combustion air hole and is more that 25% of the combustion air hole circumference.
(c) There is full material thickness edge burnback that extends through the outer diameter of more than one combustion air hole for each bulkhead deflector.
(d) Remaining material is not located on the opposite sides of the deflector.
(e) Sufficient bulkhead deflector material does not exist over the bulkhead segment for correct retention.

Subtask 72-00-00-220-128-A ** ON A/C NOT FOR ALL

R. End cap damage on the fuel nozzles

Fuel Nozzle End Cap Inspection Areas ** ON A/C NOT FOR ALL

Fuel Nozzle Types of Damage ** ON A/C NOT FOR ALL

(1) Accept the fuel nozzle if:
(a) The clearance between the end cap and the nozzle is fully closed.
(b) There is no limit to the number of radial and circumferential cracks in the end cap.
(c) Some or all of the end cap segments are broken away.
(2) Replace the fuel nozzle if:
(a) there are cracks, distortion, erosion or other damage on the areas adjacent to the end cap.

5. Close-up
Subtask 72-00-00-410-105-A ** ON A/C NOT FOR ALL

A. Close the Borescope Inspection Ports, after the Borescope Inspection is completed, as follows

Borescope Ports ** ON A/C NOT FOR ALL

(1) For the B1 thru B6 ports:
(a) Lubricate the plug (2) threads using anti-seize paste (Material No.V10-129) or anti-seize compound (Material No.V10-094) . Wipe off excess paste. !

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

(b) Install the plugs and the 72421081-010GASKET, OPTION1.
(c) TORQUE the plugs to between 80 and 70 lbf.in (0.90 and 0.79 m.daN )

(Ref. AMM TASK 70-23-11-911-013).
(d) Safety the plugs with corrosion resistant steel lockwire (Material No.V02-141) .
(2) For the IP1 and IP2 ports:
(a) Install the igniter plugs (Ref. AMM TASK 74-21-41-400-010).

Subtask 72-00-00-410-106-A ** ON A/C NOT FOR ALL

B. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Close the thrust reverser halves (Ref. AMM TASK 78-32-00-410-010):
(a) FOR [1000EM1] (ENGINE-1)
451AL, 452AR
(b) FOR [1000EM2] (ENGINE-2)
461AL, 462AR.

Subtask 72-00-00-440-078-A ** ON A/C NOT FOR ALL

C. Activate the thrust reverser HCU (Ref. AMM TASK 78-30-00-440-012).

Subtask 72-00-00-410-119-A ** ON A/C NOT FOR ALL

D. Close Access
(1) Close the fan cowls (Ref. AMM TASK 71-13-00-410-010):
(a) FOR [1000EM1] (ENGINE-1)
437AL, 438AR
(b) FOR [1000EM2] (ENGINE-2)
447AL, 448AR.
(2) Remove the WARNING NOTICE(S).

[Rev.10 from 2021] 2026.04.01 02:44:11 UTC