DOC AIRBUS | AMM A320FBorescope Inspection of the Stage 1 High Pressure Turbine (HPT) Blades and Duct Segments [IAE]
TASK 72-00-00-200-014-B
Borescope Inspection of the Stage 1 High Pressure Turbine (HPT) Blades and Duct Segments
This task is for A5 basic (non SelectOne) engines, which have not incorporated SBE 72-0562 (SelectOne Production or Retrofit Standard).
This task gives the procedure for the borescope inspection of the stage 1 HPT blades and duct segments. This task recommends the use of a flexible borescope. You can use a rigid borescope to inspect for general damage to the blades and duct segments but a rigid borescope will not permit you to see sufficient detail to inspect the blades and duct segments to the limits in this task.
A. Fixtures, Tools, Test and Support Equipment
B. Consumable Materials
C. Work Zones and Access Panels
D. Expendable Parts
E. Referenced Information
3. Job Set-up
Subtask 72-00-00-941-090-A ** ON A/C NOT FOR ALL
Subtask 72-00-00-290-077-A ** ON A/C NOT FOR ALL
Subtask 72-00-00-410-110-A ** ON A/C NOT FOR ALL
[Rev.10 from 2021]
2026.04.01 02:44:12 UTC
Borescope Inspection of the Stage 1 High Pressure Turbine (HPT) Blades and Duct Segments
WARNING:
BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
WARNING:
BE CAREFUL WHEN YOU DO WORK ON THE ENGINE PARTS AFTER THE ENGINE SHUTDOWN. USE APPLICABLE THERMAL GLOVES. THE ENGINE PARTS CAN STAY HOT FOR ONE HOUR AFTER SHUTDOWN AND CAN BURN YOU.
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.
1. Reason for the JobThis task is for A5 basic (non SelectOne) engines, which have not incorporated SBE 72-0562 (SelectOne Production or Retrofit Standard).
This task gives the procedure for the borescope inspection of the stage 1 HPT blades and duct segments. This task recommends the use of a flexible borescope. You can use a rigid borescope to inspect for general damage to the blades and duct segments but a rigid borescope will not permit you to see sufficient detail to inspect the blades and duct segments to the limits in this task.
NOTE: If damage is not listed contact your IAE representative.
2. Job Set-up InformationA. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | 1 | BORESCOPE - RIGHT ANGLE, FLEXSCOPE |
| No specific | 1 | BORESCOPE - RIGID |
| No specific | AR | COVER - EYE |
| No specific | 1 | GAGE - THREAD (0.5625 IN - 18 THD/IN) |
| 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 )  | |
| No specific | Torque wrench: range to between 85 and 75 lbf.in (0.96 and 0.85 m.daN ) | |
| IAE1P16184 | 1 | PULLER, KNOCKER |
| IAE2P16204 | 1 | TUBE-BORESCOPE GUIDE |
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.V02-024) | tape |
| (Material No.V02-141) | corrosion resistant steel lockwire |
| (Material No.V10-094) | anti-seize compound |
| (Material No.V10-129) | anti-seize paste |
| 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 | |
| FIG.ITEM | DESIGNATION | IPC-CSN |
|---|---|---|
| 1 | GASKET, OPTION | AIPC 72-42-10-81-010 |
| 1 | GASKET, OPTION | AIPC 72-45-00-80-040 |
| 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 72-00-00-080-010-A | Removal of the Rotator Kit for Borescope Inspection |
| TASK 72-00-00-480-010-A | Installation of the Rotator Kit for Borescope Inspection |
| TASK 72-00-00-860-010-A | Rotation of the HP Compressor with the Hand Turning Tool |
| 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 |
Subtask 72-00-00-941-090-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 72-00-00-010-118-A ** ON A/C NOT FOR ALL (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).
B. Get Access
(1) Open the fan cowls (Ref. AMM TASK 71-13-00-010-010):
(2) FOR [1000EM1] (ENGINE-1)
437AL 438AR.
(3) FOR [1000EM2] (ENGINE-2)
447AL 448AR.
Subtask 72-00-00-040-077-A ** ON A/C NOT FOR ALL (1) Open the fan cowls (Ref. AMM TASK 71-13-00-010-010):
(2) FOR [1000EM1] (ENGINE-1)
437AL 438AR.
(3) FOR [1000EM2] (ENGINE-2)
447AL 448AR.
C. Deactivate the thrust reverser.
Subtask 72-00-00-010-124-A ** ON A/C NOT FOR ALL 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). D. Open the thrust reverser halves (Ref. AMM TASK 78-32-00-010-010):
(1) FOR [1000EM1] (ENGINE-1)
451AL 452AR.
(2) FOR [1000EM2] (ENGINE-2)
461AL 462AR.
Subtask 72-00-00-480-064-A ** ON A/C NOT FOR ALL (1) FOR [1000EM1] (ENGINE-1)
451AL 452AR.
(2) FOR [1000EM2] (ENGINE-2)
461AL 462AR.
E. Install the foot operated motor drive unit to the gearbox crank pad (1) (Ref. AMM TASK 72-00-00-480-010).
4. ProcedureNOTE: With this unit the rotor can be turned 360 degrees to permit complete inspection.
(1) If the foot-operated motor drive is unavailable for use, rotate the HP compressor with the hand turning tool (Ref. AMM TASK 72-00-00-860-010). Subtask 72-00-00-290-077-A ** ON A/C NOT FOR ALL
A. General
HP Turbine Borescope Location for Inspection of the Stage 1 HPT Blades (Left Side) ** ON A/C NOT FOR ALL
HP Turbine Borescope Ports for Inspection of the Stage 1 HPT Blades (Right Side) ** ON A/C NOT FOR ALL
(2) The names of the different parts, areas and dimentional references of the Stage 1 HPT blades are shown.
(3) Use the names which follow when you identify a blade condition seen at borescope inspection:
(a) Erosion : A local area where material has been removed by causes other than heat distress.
(b) Leading Edge Hole : A hole in the leading edge open to the cooling air passage (can be caused by impact or burning).
(c) Burns : A local area where material has been removed because of heat distress.
(d) Coating damage : Chipping, flaking, blistering, peeling or oxidation of blade confined to the coating.
(e) Trailing edge metal loss: A burn through the convex trailing edge wall that causes a shorter airfoil chord length.
(f) Nick : A small surface imperfection having sharp edges, corners, or bottom, caused by the impact of some object.
(g) Dent : A surface depression normally having rounded edges, corners and bottom, caused by the impact of some object.
(4) Use the names which follow when you identify a duct segment condition seen at borescope inspection:
(a) Cracks: A linear opening that can easily be seen and which can cause the material to break.
(b) Closed loop of cracks: Adjoining cracks that close in on themselves.
(d) Burns: A local area where material has been removed because of heat distress.
(e) Burn-through: A hole in the duct segment gas path side which is open to the cavity behind it.
(g) Leading edge lifting: When the duct segment leading edge has become loose and can move radially inward.
(h) Impingement plate: The wall that seals the internal cavity from the backside of the duct segment.
(i) Shiplap: Location where adjoining duct segments overlap.
Subtask 72-00-00-290-078-A ** ON A/C NOT FOR ALL 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) Borescope ports are identified. HP Turbine Borescope Location for Inspection of the Stage 1 HPT Blades (Left Side) ** ON A/C NOT FOR ALL HP Turbine Borescope Ports for Inspection of the Stage 1 HPT Blades (Right Side) ** ON A/C NOT FOR ALL (3) Use the names which follow when you identify a blade condition seen at borescope inspection:
(a) Erosion : A local area where material has been removed by causes other than heat distress.
(b) Leading Edge Hole : A hole in the leading edge open to the cooling air passage (can be caused by impact or burning).
(c) Burns : A local area where material has been removed because of heat distress.
(d) Coating damage : Chipping, flaking, blistering, peeling or oxidation of blade confined to the coating.
(e) Trailing edge metal loss: A burn through the convex trailing edge wall that causes a shorter airfoil chord length.
(f) Nick : A small surface imperfection having sharp edges, corners, or bottom, caused by the impact of some object.
(g) Dent : A surface depression normally having rounded edges, corners and bottom, caused by the impact of some object.
(4) Use the names which follow when you identify a duct segment condition seen at borescope inspection:
(a) Cracks: A linear opening that can easily be seen and which can cause the material to break.
(b) Closed loop of cracks: Adjoining cracks that close in on themselves.
NOTE: Individual crack limits still apply to a closed loop of cracks.
(c) Intersecting cracks: One or more axial or circumferential cracks that go through each other. (d) Burns: A local area where material has been removed because of heat distress.
(e) Burn-through: A hole in the duct segment gas path side which is open to the cavity behind it.
NOTE: A crack that is wider than 0.05 in. (1.27 mm) over the cooling pocket is considered a burn-through.
(f) Erosion: A local area where material has been removed by causes other than heat distress. (g) Leading edge lifting: When the duct segment leading edge has become loose and can move radially inward.
(h) Impingement plate: The wall that seals the internal cavity from the backside of the duct segment.
(i) Shiplap: Location where adjoining duct segments overlap.
B. Do a close up borescope inspection of the Stage 1 HPT blades
(a) Remove the igniter plug (Ref. AMM TASK 74-21-41-000-010).
(3) Put a piece of tape (Material No.V02-024) on the borescope fiber bundle 3.25 in. (82.55 mm) from the other end of the guide 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.
(4) Put the end of the tube which is close to the tape mark in the down position and the plane of the tube at a right angle to the engine axis.
(5) Install the tube in to the IP1 igniter port
(a) As the tube is put in, turn it clockwise carefully and connect the fitting to the igniter bushing.
(b) Push the guide tube in until it touches the stop.
(c) Turn the guide tube clockwise until it stops. Hold the tube in this position and tighten the locking wheel to secure the guide tube.
(e) 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 in more than the tape mark.
Subtask 72-00-00-290-074-A ** ON A/C NOT FOR ALL NOTE: For a general inspection do the procedure in the next paragraph.
(1) Get access to the Stage 1 HPT blades through the IP1 igniter port (a) Remove the igniter plug (Ref. AMM TASK 74-21-41-000-010).
NOTE: Do not remove the igniter insert.
NOTE: Do not remove the igniter bushing.
(2) Put the flexible borescope in to the guide tube IAE2P16204 TUBE-BORESCOPE GUIDE until the end of the borescope is level with the end of the tube. (3) Put a piece of tape (Material No.V02-024) on the borescope fiber bundle 3.25 in. (82.55 mm) from the other end of the guide 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.
(4) Put the end of the tube which is close to the tape mark in the down position and the plane of the tube at a right angle to the engine axis.
(5) Install the tube in to the IP1 igniter port
(a) As the tube is put in, turn it clockwise carefully and connect the fitting to the igniter bushing.
(b) Push the guide tube in until it touches the stop.
(c) Turn the guide tube clockwise until it stops. Hold the tube in this position and tighten the locking wheel to secure the guide tube.
NOTE: In this position, the slot in the stop will be up.
NOTE: An COVER - EYE for the eye which is not used will decrease eye tension.
NOTE: An adjustable clamp to support the borescope will free the hands to move the borescope dials and fiber bundle.
NOTE: Some borescope units have closed circuit television adapters. We highly recommend this unit.
(d) Slowly push in the borescope through the guide tube while you look through the eye piece. (e) 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 in more than the tape mark.
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.
(6) Examination of the blades: CAUTION:
MAKE SURE THAT THE BORESCOPE TIP IS NOT IN THE PATH OF THE STAGE 1 HPT BLADES BEFORE YOU TURN THE ENGINE.
(a) Examine the blades for damage. C. You can use the BORESCOPE - RIGHT ANGLE, FLEXSCOPE to do a General Borescope Inspection of the Stage 1 HPT Blades
HP Turbine Borescope Location for Inspection of the Stage 1 HPT Blades (Left Side) ** ON A/C NOT FOR ALL
1 Remove and discard the lockwire from the plug.
(b) Loosen and remove the plug and the gasket from the B3 or B4 port.
(2) Get access to the Stage 1 HPT blades through the T1/2L or T1/2R ports.
HP Turbine Borescope Location for Inspection of the Stage 1 HPT Blades (Left Side) ** ON A/C NOT FOR ALL
HP Turbine Borescope Ports for Inspection of the Stage 1 HPT Blades (Right Side) ** ON A/C NOT FOR ALL
1 Remove the lockwire and the bolts which hold the plugs.
(b) Put the IAE1P16184 PULLER, KNOCKER in to the center hole of the plug (use if required).
(c) Use the puller to remove the plug from the port.
(d) Remove the gasket from the plug.
(e) Remove the plug from the puller.
(3) Put the BORESCOPE - RIGID through the B3 or B4 port.
(4) Examine the blades for damage.
(5) Put the BORESCOPE - RIGID through the T1/2L or T1/2R port.
(6) Examine the blades for damage.
Subtask 72-00-00-220-192-A ** ON A/C NOT FOR ALL NOTE: For a close up inspection do the procedure in the paragraph above.
NOTE: An eye cover for the eye which is not used will decrease eye tension.
NOTE: Removal of the plugs at both of the locations will permit you to examine both leading and trailing edges.
NOTE: The borescope inspection of the Stage 1 HPT blades and duct segments shows areas of the Stage 2 nozzle guide vane. If you find damage on the Stage 2 nozzle guide vanes, contact your IAE representative.
(1) Get access to the Stage 1 HPT blades through the B3 or B4 ports. HP Turbine Borescope Location for Inspection of the Stage 1 HPT Blades (Left Side) ** ON A/C NOT FOR ALL WARNING:
USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.
(a) 1 Remove and discard the lockwire from the plug.
(b) Loosen and remove the plug and the gasket from the B3 or B4 port.
(2) Get access to the Stage 1 HPT blades through the T1/2L or T1/2R ports.
HP Turbine Borescope Location for Inspection of the Stage 1 HPT Blades (Left Side) ** ON A/C NOT FOR ALL HP Turbine Borescope Ports for Inspection of the Stage 1 HPT Blades (Right Side) ** ON A/C NOT FOR ALL WARNING:
MAKE SURE THAT THE BLANKING PLUG IS SUFFICIENTLY COOL BEFORE REMOVAL.
THE TEMPERATURE STAYS HIGH FOR A SHORT TIME AFTER ENGINE SHUTDOWN.
WARNING:
USE PROTECTIVE GOGGLES AND GLOVES WHEN YOU REMOVE OR INSTALL LOCKWIRE. EACH TIME YOU CUT LOCKWIRE, REMOVE AND DISCARD IT IMMEDIATELY. LOOSE LOCKWIRE CAN CUT YOU OR MAKE YOU BLIND, AND/OR CAN CAUSE DAMAGE.
(a) 1 Remove the lockwire and the bolts which hold the plugs.
(b) Put the IAE1P16184 PULLER, KNOCKER in to the center hole of the plug (use if required).
(c) Use the puller to remove the plug from the port.
(d) Remove the gasket from the plug.
(e) Remove the plug from the puller.
(3) Put the BORESCOPE - RIGID through the B3 or B4 port.
(4) Examine the blades for damage.
(5) Put the BORESCOPE - RIGID through the T1/2L or T1/2R port.
(6) Examine the blades for damage.
D. Examine the Stage 2 Nozzle Guide-Vane
(1) The table below applies to the stage 2 nozzle guide-vane condition observed when doing a stage 1 HPT borescope inspection.
Subtask 72-00-00-220-094-A ** ON A/C NOT FOR ALL (1) The table below applies to the stage 2 nozzle guide-vane condition observed when doing a stage 1 HPT borescope inspection.
| CONDITION | AMOUNT | DISPOSITION |
|---|---|---|
| 1. Cracks and chipped coating | Any amount. | Acceptable. |
| 2. Inner or outer platform burn-through holes | Burn-through hole 0.25 in. (6.35 mm) by 0.050 in. (1.27 mm) – 3 locations maximum. | Acceptable. |
| Burn-through hole greater than 0.25 in. (6.35 mm) by 0.050 in. (1.27 mm). | Remove the engine in less than 30 cycles. | |
| 3. Leading-edge burn-through holes | Less than 0.050 in. (1.27 mm) radially. | Acceptable. |
| Between 0.050 in. (1.27 mm) and 0.300 in. (7.62 mm) radially, no impingement rib damage permitted. | Do the inspection again at 300 flight hour intervals. | |
| Greater than 0.300 in. (7.62 mm) radially, no impingement rib damage permitted. | Remove the engine in less than 10 cycles. | |
| 4. Conditions other than 1, 2 or 3 above | Any. | Contact IAE. |
E. Nicks or dents on the airfoil of the stage 1 HPT blades
(1) Accept with an inspection each 750 hours if:
(a) 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).
(2) Accept with an inspection each 600 hours if:
(a) The nick or dent is in area A or area B and is larger than 0.2 in. (5.08 mm).
(3) Accept with an inspection each 300 hours if:
(a) 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. (6.86 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. (12.70 mm).
(4) Remove in less than 30 cycles if:
(a) There is a nick or dent with cracks on the leading edge outer 50 percent span which has a total axial length greater than 0.27 in. (6.86 mm) and a total radial length of greater than 0.50 in. (12.70 mm).
(5) Remove the engine in less than 10 cycles if:
(a) The nick or dent is in area A or area B (not including the blade trailing edge tip or leading edge outer 50 percent) and shows signs of torn metal or cracks.
(b) The nick or dent (not including leading edge outer 50 percent span) causes internal areas to show. These are areas where the air that is used to cool the blade goes.
Subtask 72-00-00-220-095-A ** ON A/C NOT FOR ALL (1) Accept with an inspection each 750 hours if:
(a) 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).
(2) Accept with an inspection each 600 hours if:
(a) The nick or dent is in area A or area B and is larger than 0.2 in. (5.08 mm).
(3) Accept with an inspection each 300 hours if:
(a) 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. (6.86 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. (12.70 mm).
(4) Remove in less than 30 cycles if:
(a) There is a nick or dent with cracks on the leading edge outer 50 percent span which has a total axial length greater than 0.27 in. (6.86 mm) and a total radial length of greater than 0.50 in. (12.70 mm).
(5) Remove the engine in less than 10 cycles if:
(a) The nick or dent is in area A or area B (not including the blade trailing edge tip or leading edge outer 50 percent) and shows signs of torn metal or cracks.
(b) The nick or dent (not including leading edge outer 50 percent span) causes internal areas to show. These are areas where the air that is used to cool the blade goes.
F. Cracks on the Airfoil of the Stage 1 HPT Blades
(a) The crack in area A or area B is longer than 0.07 in. (1.78 mm).
(b) 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 0.12 in. (3.05 mm) in any direction.
(c) 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 0.07 in. (1.78 mm).
(d) The crack in area C is longer than 0.10 in. (2.54 mm) and does not extend radially to the blade tip.
(e) The crack in area C extends from a burned area and the combination of the burn plus a crack is longer than 0.10 in. (2.54 mm).
(f) A radial crack on the airfoil starts at the blade tip and is longer than 0.20 in. (5.08 mm). The number of cracks is not important.
(g) Axial crack is greater than 0.14 in. (3.56 mm) in the tip zone.
(h) There is missing material which extends greater than 0.05 in. (1.27 mm) radially from the tip.
(2) Accept with an inspection each 300 hours if:
(a) Axial crack is greater than 0.20 in. (5.08 mm) in the tip zone.
(b) There is missing material which extends greater than 0.08 in. (2.03 mm) radially from the tip.
(c) There is missing material which extends greater than 0.06 in. (1.52 mm) radially and is also greater than 0.12 in. (3.05 mm) axial.
(d) 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 equal to or greater than 0.20 in. (5.08 mm) in the radial direction and the crack is less than 0.15 in. (3.81 mm) in the radial direction.
(3) Accept with an inspection each 150 hours if:
(a) Axial crack is greater than 0.24 in. (6.10 mm) in the tip zone.
(b) There is missing material which extends greater than 0.10 in. (2.54 mm) radially from the tip.
(c) There is missing material which extends greater than 0.08 in. (2.03 mm) radially and is also greater than 0.18 in. (4.57 mm) axially in the tip zone.
(d) 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 equal to or greater than 0.50 in. (12.70 mm) in the radial direction and the crack is less than 0.15 in. (3.81 mm) in the radial direction.
(4) Remove the engine in less than 30 cycles if:
(a) 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 a burn-through plus a crack is longer than 0.70 in. (17.78 mm) in the radial direction.
(b) The crack in area A (other than a radial crack that starts at the blade tip) is equal to or greater than 0.15 in. (3.81 mm).
(c) The crack in area A (this does not include the inner 25 percent of the leading or trailing edge span or a radial crack and burn 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).
(d) The crack in area B is longer than 0.15 in. (3.81 mm).
(e) 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).
(f) The crack in area C is longer than 0.20 in. (5.08 mm) and does not extend radially to the blade tip.
(g) 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).
(h) A radial crack on the airfoil starts at the blade tip and is longer than 0.35 in. (8.89 mm).
(i) The cracks form closed loops between cooling holes except in the tip zone.
(j) The crack goes through other cracks except in the tip zone.
(k) The internal cooling passages can be seen at the blade tip.
(l) There is missing material which extends greater than 0.09 in. (2.29 mm) radially and 0.28 in. (7.11 mm) axially in the tip zone.
(m) There is an axial crack that has a length greater than 0.30 in. (7.62 mm) in the tip zone.
(5) Remove the engine in less than 10 cycles if:
(a) 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 0.13 in. (3.30 mm).
(b) In the airfoil fillet radius there is a crack or combination of a burn and a crack.
Subtask 72-00-00-220-098-A ** ON A/C NOT FOR ALL NOTE: There will be unwanted material on the airfoil because of the casting procedure 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 0.1 in. (2.54 mm) to 0.2 in. (5.08 mm) wide and are 0.005 in. (0.13 mm) high. These bumps are acceptable. No action is necessary.
NOTE: Tip Zone - Lower edge of upper tip cooling holes to tip. In this zone a crack going through another crack is permitted.
(1) Accept with an inspection each 600 hours if: (a) The crack in area A or area B is longer than 0.07 in. (1.78 mm).
(b) 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 0.12 in. (3.05 mm) in any direction.
(c) 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 0.07 in. (1.78 mm).
(d) The crack in area C is longer than 0.10 in. (2.54 mm) and does not extend radially to the blade tip.
(e) The crack in area C extends from a burned area and the combination of the burn plus a crack is longer than 0.10 in. (2.54 mm).
(f) A radial crack on the airfoil starts at the blade tip and is longer than 0.20 in. (5.08 mm). The number of cracks is not important.
(g) Axial crack is greater than 0.14 in. (3.56 mm) in the tip zone.
(h) There is missing material which extends greater than 0.05 in. (1.27 mm) radially from the tip.
(2) Accept with an inspection each 300 hours if:
(a) Axial crack is greater than 0.20 in. (5.08 mm) in the tip zone.
(b) There is missing material which extends greater than 0.08 in. (2.03 mm) radially from the tip.
(c) There is missing material which extends greater than 0.06 in. (1.52 mm) radially and is also greater than 0.12 in. (3.05 mm) axial.
(d) 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 equal to or greater than 0.20 in. (5.08 mm) in the radial direction and the crack is less than 0.15 in. (3.81 mm) in the radial direction.
(3) Accept with an inspection each 150 hours if:
(a) Axial crack is greater than 0.24 in. (6.10 mm) in the tip zone.
(b) There is missing material which extends greater than 0.10 in. (2.54 mm) radially from the tip.
(c) There is missing material which extends greater than 0.08 in. (2.03 mm) radially and is also greater than 0.18 in. (4.57 mm) axially in the tip zone.
(d) 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 equal to or greater than 0.50 in. (12.70 mm) in the radial direction and the crack is less than 0.15 in. (3.81 mm) in the radial direction.
(4) Remove the engine in less than 30 cycles if:
(a) 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 a burn-through plus a crack is longer than 0.70 in. (17.78 mm) in the radial direction.
(b) The crack in area A (other than a radial crack that starts at the blade tip) is equal to or greater than 0.15 in. (3.81 mm).
(c) The crack in area A (this does not include the inner 25 percent of the leading or trailing edge span or a radial crack and burn 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).
(d) The crack in area B is longer than 0.15 in. (3.81 mm).
(e) 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).
(f) The crack in area C is longer than 0.20 in. (5.08 mm) and does not extend radially to the blade tip.
(g) 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).
(h) A radial crack on the airfoil starts at the blade tip and is longer than 0.35 in. (8.89 mm).
(i) The cracks form closed loops between cooling holes except in the tip zone.
(j) The crack goes through other cracks except in the tip zone.
(k) The internal cooling passages can be seen at the blade tip.
(l) There is missing material which extends greater than 0.09 in. (2.29 mm) radially and 0.28 in. (7.11 mm) axially in the tip zone.
(m) There is an axial crack that has a length greater than 0.30 in. (7.62 mm) in the tip zone.
(5) Remove the engine in less than 10 cycles if:
(a) 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 0.13 in. (3.30 mm).
(b) In the airfoil fillet radius there is a crack or combination of a burn and a crack.
G. Cracks on the platform of the stage 1 HPT blade
(a) The crack is longer than 0.15 in. (3.81 mm) and does not go up to the platform to airfoil fillet radius. The number of cracks is not important.
(2) Accept with an inspection each 300 hours if:
(a) The crack goes in to the platform to airfoil fillet radius. The crack is longer than 0.20 in. (5.08 mm) and does not go into the platform to airfoil fillet radius.
(3) Remove the engine in less than 10 cycles if:
(a) The crack goes through the platform to airfoil fillet radius. The crack is longer than 0.25 in. (6.35 mm) and does not go into the platform to airfoil fillet radius.
Subtask 72-00-00-220-099-A ** ON A/C NOT FOR ALL NOTE: It is acceptable to have small pieces of the Stage 1 HPT seal out between the rear platform of the Stage 1 HPT blade and the Stage 1 HPT air seal.
(1) Accept with an inspection each 600 hours if: (a) The crack is longer than 0.15 in. (3.81 mm) and does not go up to the platform to airfoil fillet radius. The number of cracks is not important.
(2) Accept with an inspection each 300 hours if:
(a) The crack goes in to the platform to airfoil fillet radius. The crack is longer than 0.20 in. (5.08 mm) and does not go into the platform to airfoil fillet radius.
(3) Remove the engine in less than 10 cycles if:
(a) The crack goes through the platform to airfoil fillet radius. The crack is longer than 0.25 in. (6.35 mm) and does not go into the platform to airfoil fillet radius.
NOTE: Cracks are not acceptable in the airfoil fillet radius.
H. Erosion or Burns on the Airfoil or Platform
(a) 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.
(2) Accept with an inspection each 750 hours if:
(a) The leading edge hole beyond the 50 percent span is less than 0.10 in. (2.54 mm) axially and less 0.20 in. (5.08 mm) radially.
(3) Accept with an inspection each 600 hours if:
(a) The erosion or burns on the leading edge is more than one quarter of the airfoil radial length.
(b) 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.
(c) The erosion or burns on the trailing edge in the inner 25 percent span are more than 0.07 in. (1.78 mm) and less than 0.11 in. (2.79 mm) axially.
(d) The erosion or burns on the trailing edge beyond the inner 25 percent span are more than 0.12 in. (3.05 mm) and less than 0.20 in. (5.08 mm) axially. This does not include the blade tip.
(e) The burning at the blade tip in zone 1 is at the bottom of the lower tip cooling row holes.
(f) The burning at the remainder of the tip (but not including the trailing edge tip) is more than 0.06 in. (1.52 mm) radially and above the top edge of the upper cooling holes.
(g) There is material that is burned away or missing on the blade trailing edge tip that is more than 0.07 in. (1.78 mm) axially from the trailing edge.
(a) The erosion or burns on the trailing edge in the inner 25 percent span are equal to or greater than 0.11 in. (2.79 mm) and less than 0.15 in. (3.81 mm) axially.
(b) The erosion or burns on the trailing edge beyond the inner 25 percent span are equal to or greater than 0.20 in. (5.08 mm) and less than 0.30 in. (7.62 mm) axially. This does not include the blade tip.
(c) The burns on the trailing edge platform corner is more than 0.25 in. (6.35 mm) axially or 0.45 in. (11.43 mm) tangentially.
(d) 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 in. (5.08 mm) and less than 0.50 in. (12.70 mm) in the radial direction.
(e) There is visible platform material missing due to erosion or burning.
(f) 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.
(g) There is material that is burned away or missing on the blade trailing edge tip that is more than 0.09 in. (2.29 mm) axially from the trailing edge.
(5) Do an inspection each 150 hours if:
(a) The leading edge hole on the outer 50 percent span is less than 0.20 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.
(b) At the trailing edge tip:
(6) Do an inspection each 75 hours if:
(a) The burning of base material is at the airfoil leading edge is on the inner 25 percent span.
(7) Remove the engine in less than 30 cycles if:
(a) The leading edge hole on the outer 50 percent span is equal to or greater than 0.20 in. (5.08 mm) in the axial direction or equal to or greater than 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.
(8) Remove the engine in less than 10 cycles if:
(a) The erosion or burn (in any location other than the leading edge outer 50 percent span) which lets internal areas and inner walls show. The internal areas are where the air that is used to cool the blade goes.
(b) 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.
(c) The burn on the trailing edge platform corner is more than 0.04 in. (1.02 mm) axially or 0.60 in. (15.24 mm) circumferentially.
(d) The erosion or burns on the trailing edge in the inner 25 percent span are equal to or more than 0.15 in. (3.81 mm) axially.
(e) The erosion or burns on the trailing edge beyond the inner 25 percent span are equal to or more than 0.30 in. (7.62 mm) axially. This does not include the blade tip.
(f) The burning at the tip has extended to completely include the lower tip cooling row holes or burn-through at the tip has occurred.
(g) The leading edge hole on the outer 50 percent span is equal to or more than 0.20 in. (5.08 mm) in the axial direction and the burning at the tip extends beyond the first row of cooling holes.
(h) The leading edge hole on the outer 50 percent span is equal to or more than 0.50 in. (12.70 mm) in the radial direction, and the burning at the tip extends beyond the first row of cooling holes.
(i) 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.
(j) At the trailing edge tip:
(l) There is burning of base material at the airfoil leading edge-platform fillet radius.
Subtask 72-00-00-220-100-A ** ON A/C NOT FOR ALL NOTE: The newest standard of the 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.
NOTE: Chaplet holes may or may not exist. They are a byproduct of the casting process. Casting chaplet holes are small holes typically 0.025 in. (0.6350 mm) in diameter, that are circular in nature and may appear in the airfoil. Chaplet holes are acceptable.
(1) Accept with an inspection each 1500 hours if: (a) 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.
(2) Accept with an inspection each 750 hours if:
(a) The leading edge hole beyond the 50 percent span is less than 0.10 in. (2.54 mm) axially and less 0.20 in. (5.08 mm) radially.
(3) Accept with an inspection each 600 hours if:
(a) The erosion or burns on the leading edge is more than one quarter of the airfoil radial length.
(b) 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.
(c) The erosion or burns on the trailing edge in the inner 25 percent span are more than 0.07 in. (1.78 mm) and less than 0.11 in. (2.79 mm) axially.
(d) The erosion or burns on the trailing edge beyond the inner 25 percent span are more than 0.12 in. (3.05 mm) and less than 0.20 in. (5.08 mm) axially. This does not include the blade tip.
(e) The burning at the blade tip in zone 1 is at the bottom of the lower tip cooling row holes.
(f) The burning at the remainder of the tip (but not including the trailing edge tip) is more than 0.06 in. (1.52 mm) radially and above the top edge of the upper cooling holes.
(g) There is material that is burned away or missing on the blade trailing edge tip that is more than 0.07 in. (1.78 mm) axially from the trailing edge.
NOTE: The blade trailing edge tip is 0.15 in. (3.81 mm) radially from the tip and 0.10 in. (2.54 mm) from the trailing edge and burning or erosion is permitted in this area.
(4) Accept with an inspection each 300 hours if: (a) The erosion or burns on the trailing edge in the inner 25 percent span are equal to or greater than 0.11 in. (2.79 mm) and less than 0.15 in. (3.81 mm) axially.
(b) The erosion or burns on the trailing edge beyond the inner 25 percent span are equal to or greater than 0.20 in. (5.08 mm) and less than 0.30 in. (7.62 mm) axially. This does not include the blade tip.
(c) The burns on the trailing edge platform corner is more than 0.25 in. (6.35 mm) axially or 0.45 in. (11.43 mm) tangentially.
(d) 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 in. (5.08 mm) and less than 0.50 in. (12.70 mm) in the radial direction.
(e) There is visible platform material missing due to erosion or burning.
(f) 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.
(g) There is material that is burned away or missing on the blade trailing edge tip that is more than 0.09 in. (2.29 mm) axially from the trailing edge.
(5) Do an inspection each 150 hours if:
(a) The leading edge hole on the outer 50 percent span is less than 0.20 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.
(b) At the trailing edge tip:
- If there is missing or burned-away material that is 0.5 in. (12.70 mm) or less in the axial direction and 0.15 in. (3.81 mm) or less in the radial direction.
(6) Do an inspection each 75 hours if:
(a) The burning of base material is at the airfoil leading edge is on the inner 25 percent span.
(7) Remove the engine in less than 30 cycles if:
(a) The leading edge hole on the outer 50 percent span is equal to or greater than 0.20 in. (5.08 mm) in the axial direction or equal to or greater than 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.
(8) Remove the engine in less than 10 cycles if:
(a) The erosion or burn (in any location other than the leading edge outer 50 percent span) which lets internal areas and inner walls show. The internal areas are where the air that is used to cool the blade goes.
(b) 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.
(c) The burn on the trailing edge platform corner is more than 0.04 in. (1.02 mm) axially or 0.60 in. (15.24 mm) circumferentially.
(d) The erosion or burns on the trailing edge in the inner 25 percent span are equal to or more than 0.15 in. (3.81 mm) axially.
(e) The erosion or burns on the trailing edge beyond the inner 25 percent span are equal to or more than 0.30 in. (7.62 mm) axially. This does not include the blade tip.
(f) The burning at the tip has extended to completely include the lower tip cooling row holes or burn-through at the tip has occurred.
(g) The leading edge hole on the outer 50 percent span is equal to or more than 0.20 in. (5.08 mm) in the axial direction and the burning at the tip extends beyond the first row of cooling holes.
(h) The leading edge hole on the outer 50 percent span is equal to or more than 0.50 in. (12.70 mm) in the radial direction, and the burning at the tip extends beyond the first row of cooling holes.
(i) 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.
(j) At the trailing edge tip:
- If there is missing or burned-away material equal to or more than 0.50 in. (12.70 mm) in the axial direction and equal to or more than 0.15 in. (3.81 mm) in the radial direction.
NOTE: The trailing edge and the inner row of blade tip holes is 0.15 in. (3.81 mm) radially.
(k) There is burning of base material with cracks at the airfoil leading edge is on the inner 50 percent span. (l) There is burning of base material at the airfoil leading edge-platform fillet radius.
I. Examine the Stage 1 HPT Duct Segments
5. Close-upNOTE: At the subsequent inspection, you must do a 360 degrees borescope inspection to identify the worst duct segment condition. Subsequent inspections of any duct segment distress must use these findings.
NOTE: The HTP stage 1 BOAS has a protective coating underneath the ceramic coating. Chipping and spalling of the ceramic coating is acceptable without a decrease in the borescope inspection interval. The smearing of blade tip material on the HTP stage 1 BOAS is acceptable without a decrease in the borescope inspection interval.
| CONDITION | 300 HR. INSPECTION | 125 HR. INSPECTION | REMOVE THE ENGINE IN 10 CYCLES |
|---|---|---|---|
| | | | |
| Axial cracks | One or more cracks that are longer than 0.25 in. (6.35 mm) and shorter than 0.50 in. (12.70 mm) | One or more cracks that are longer than or equal to 0.50 in. (12.70 mm) but shorter than 1.20 in. (30.48 mm) | One or more cracks that are longer than or equal to 1.20 in. (30.48 mm) |
| Circumferential cracks | One or more cracks that are longer than 0.38 in. (9.53 mm) and shorter than 0.50 in. (12.70 mm) | One or more cracks that are longer than or equal to 0.50 in. (12.70 mm) but shorter than 1.50 in. (38.10 mm) | One or more cracks are longer than or equal to 1.50 in. (38.10 mm) |
| Intersecting cracks | Any combined crack that is longer than 0.25 in. (6.35 mm) and shorter than 0.50 in. (12.70 mm) axially or longer than 0.375 in. (9.52 mm) and shorter than 0.50 in. (12.70 mm) circumferentially. | Any combined crack that is longer than or equal to 0.50 in. (12.70 mm) and shorter than 1.20 in. (30.48 mm) axially or longer than or equal to 0.50 in. (12.70 mm) and shorter than 1.50 in. (38.10 mm) circumferentially. | Any combined crack that is longer than or equal to 1.20 in. (30.48 mm) axially or longer than or equal to 1.50 in. (38.10 mm) circumferentially. |
| Closed loop of cracks | Does not apply | Maximum length in X or Y direction less than 0.50 in. (12.70 mm) | Maximum length in X or Y direction more than or equal to 0.50 in. (12.70 mm) |
| Burning or erosion of the base metal at area 1 with no burn-through | Any amount greater than two connecting cooling holes | Does not apply | Does not apply |
| Burning or erosion of the base metal at area 2 with no burn-through | Shiplap burning that goes past the first row of cooling holes and goes up to 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 0.50 in. (12.70 mm) of continuous burn-through in area 1, area 2, or areas 1 and 2 together | 0.50 in. (12.70 mm) or more of 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 0.50 in. (12.70 mm) in area 1, area 2, or areas 1 and 2 together | Combined length of X1 + X2 + Z is greater than or equal to 1.20 in. (30.48 mm) or Z is greater than or equal to 0.50 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 0.50 in. (12.70 mm) in area 1, area 2, or areas 1 and 2 together | Combined length of Y1 + Y2 + Z is greater than or equal to 1.50 in. (38.10 mm) or Z is greater than or equal to 0.50 in. (12.70 mm) |
| Burn-through of the impingement plate | Does not apply | Does not apply | One or more |
| Lifting of leading edge material | Does not apply | Does not apply | Lifting of seal edge |
| Loss of leading edge material (parent material loss) | Less than 0.30 in. (7.62 mm) | 0.30 in. (7.62 mm) or more, but less than 0.50 in. (12.70 mm) | 0.50 in. (12.70 mm) or more |
Subtask 72-00-00-410-110-A ** ON A/C NOT FOR ALL
A. Close the borescope inspection ports after the borescope inspection is completed as follows:
(1) For the IP1 igniter port, install the igniter plug (Ref. AMM TASK 74-21-41-400-010).
(2) For the B3 or B4 port, proceed as follows:
(a) Lubricate the plug threads with anti-seize paste (Material No.V10-129) or anti-seize compound (Material No.V10-094) . Wipe off excess paste.
72421081-010 GASKET, OPTION 1
(c) TORQUE the plug 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 plug with corrosion resistant steel lockwire (Material No.V02-141)
(3) For the T1/2L or T1/2R port, proceed as follows:
(a) Put the72450080-040 GASKET, OPTION 1
(b) Replace the gasket if the seal is not above the case surface.
(c) Installation of the plug
(d) Lubricate the bolt threads with anti-seize paste (Material No.V10-129) or anti-seize compound (Material No.V10-094) . Wipe off excess paste.
1 Make sure that the borescope plug is correctly installed and bolt holes are aligned prior to continuing to next step.
(f) TORQUE the bolts to between 85 and 75 lbf.in (0.96 and 0.85 m.daN ) (Ref. AMM TASK 70-23-11-911-013).
(g) Safety the bolts with corrosion resistant steel lockwire (Material No.V02-141) .
Subtask 72-00-00-080-059-A ** ON A/C NOT FOR ALL (1) For the IP1 igniter port, install the igniter plug (Ref. AMM TASK 74-21-41-400-010).
(2) For the B3 or B4 port, proceed as follows:
(a) Lubricate the plug threads with anti-seize paste (Material No.V10-129) or anti-seize compound (Material No.V10-094) . Wipe off excess paste.
NOTE: You can correct minor thread damage to the threaded hole which a GAGE - THREAD (0.5625 IN - 18 THD/IN).
(b) Install the plug (2) and the (c) TORQUE the plug 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 plug with corrosion resistant steel lockwire (Material No.V02-141)
(3) For the T1/2L or T1/2R port, proceed as follows:
(a) Put the
(b) Replace the gasket if the seal is not above the case surface.
(c) Installation of the plug
CAUTION:
BE CAREFUL WHEN YOU INSTALL THE PLUG. IF THE PLUG BREAKS DURING THE INSTALLATION AND A PLUG PIECE FALLS INTO THE SECOND-STAGE VANE CAVITY, REMOVE THIS PIECE BEFORE YOU PUT THE ENGINE BACK INTO SERVICE. IF NECESSARY, REMOVE THE TURBINE COOLING-AIR TUBE TO GET ACCESS TO THE SECOND-STAGE VANE CAVITY. IF YOU DO NOT REMOVE THE PLUG PIECE FROM THE VANE CAVITY, DAMAGE TO THE ENGINE CAN OCCUR.
1 Put the gasket on the plug (2) and install it in the case. (d) Lubricate the bolt threads with anti-seize paste (Material No.V10-129) or anti-seize compound (Material No.V10-094) . Wipe off excess paste.
1 Make sure that the borescope plug is correctly installed and bolt holes are aligned prior to continuing to next step.
NOTE: You can correct minor thread damage to the threaded hole with a 0.250-28UNJF-3B Tap.
(e) Install the bolts. (f) TORQUE the bolts to between 85 and 75 lbf.in (0.96 and 0.85 m.daN )
(Ref. AMM TASK 70-23-11-911-013). (g) Safety the bolts with corrosion resistant steel lockwire (Material No.V02-141) .
B. Remove the foot operated motor drive unit from the gearbox crank pad (Ref. AMM TASK 72-00-00-080-010).
Subtask 72-00-00-410-111-A ** ON A/C NOT FOR ALL C. 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 72-00-00-440-075-A ** ON A/C NOT FOR ALL Subtask 72-00-00-410-120-A ** ON A/C NOT FOR ALL (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.