DMC:V2500-A1-72-00-0000-06A-312A-B|Issue No:004|Issue Date:2018-02-01

Export Control

EAR Export Classification: Not subject to the EAR per 15 C.F.R. Chapter 1, Part 734.3(b)(3), except for the following Service Bulletins which are currently published as EAR Export Classification 9E991: SBE70-0992, SBE72-0483, SBE72-0580, SBE72-0588, SBE72-0640, SBE73-0209, SBE80-0024 and SBE80-0025.

Copyright

© IAE International Aero Engines AG (2001, 2014 - 2021) The information contained in this document is the property of © IAE International Aero Engines AG and may not be copied or used for any purpose other than that for which it is supplied without the express written authority of © IAE International Aero Engines AG. (This does not preclude use by engine and aircraft operators for normal instructional, maintenance or overhaul purposes.).

Applicability

V2500-A1

Common Information

TASK 72-00-00-200-004-A00 Engine General - Examine (Borescope) The HPT Stage 1 Blades, Inspection-004

General

All Fig/item numbers in the procedure agree with those used in the IPC. Only the primary Fig/item numbers are used. For the service bulletin alpha variants refer to the IPC.

For all parts identified in a different Chapter/Section/Subject, the applicable Chapter/Section/Subject comes before the Fig/item number.

For standard torque data and procedures refer to the SPM TASK 70-41-00-400-501, SPM TASK 70-41-00-400-501 and SPM TASK 70-41-01-400-501.

Special torque data is identified with the symbol * after the torque value.

Assembly tolerances are included in this procedure.

Lubricate all threads and abutment faces of nuts and bolts with CoMat 10-077 APPROVED ENGINE OILS, unless other lubricants are referred to in the procedure.

The number for each radial location must be identified in a clockwise direction. These start at the engine top position when you look from the rear of the engine, unless stated differently in the procedure.

Definitions and General Information

This TASK is for inspection of A1 engines only. 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, but a rigid borescope will not permit you to see sufficient detail to inspect the blades or duct segments to the limits in this TASK.

Pre SBE 72-0221: Borescope ports are identified in Figure, Figure and Figure.

SBE 72-0221: Borescope ports are identified in Figure, Figure and Figure.

The names of the different parts and areas of the Stage 1 HPT blades are shown Figure.

Use the names which follow when you identify a blade condition seen at borescope inspection:

Erosion: A local area where material has been removed by causes other than heat distress.

Leading Edge Burn-Through: A hole in the leading edge open to the cooling air passage.

Burns: A local area where material has been removed because of heat distress.

Coating damage: Chipping, flaking, blistering, peeling or oxidation of blade confined to coating.

Trailing edge metal loss: A burn through the convex trailing edge wall that causes a shorter airfoil chord length

Use the names which follow when you identify a duct segment condition seen at borescope inspection:

Cracks: A linear opening that can easily be seen and which can cause the material to break.

Closed loop of cracks: Adjoining cracks that close in on themselves.

Intersecting cracks: One or more axial or circumferential cracks that go through each other.

Burns: A local area where material was removed because of heat distress.

Burn-Through: A hole in the duct segment gas path side which is open to the cavity behind it.

Erosion: A local area where material was removed by causes other than heat distress.

Leading edge (LE) lifting: When the duct segment leading edge has become loose and can move radially inward.

Impingement plate: The wall that seals the internal cavity from the backside of the duct segment.

Shiplap: Location where adjoining duct segments overlap.

NOTE

To identify the consumable materials refer to the PCI.

NOTE

Special tools are identified in the procedure by the tool primary number.

NOTE

If damage is not listed contact your IAE representative.

NOTE

Individual crack limits still apply to a closed loop of cracks.

NOTE

A crack that is wider than 0.050 in. (1.27 mm) over the cooling pocket is considered a burn-through.

Preliminary Requirements

Pre-Conditions

NONE

Support Equipment

Name	Manufacturer	Part Number / Identification	Quantity
Torque wrench, range 0 to 250 lbfin (0 to 20 Nm)	LOCAL	Torque Wrench 0-250
Flexible borescope	LOCAL	Flexible borescope
Rigid borescope	LOCAL	Rigid borescope
Cover (eye)	LOCAL	Cover (eye)
Motor drive unit	LOCAL	Motor drive unit
IAE 1P16184 Puller	0AM53	IAE 1P16184	1
IAE 2P16204 Guide Tube	0AM53	IAE 2P16204	1

Consumables, Materials and Expendables

Name	Manufacturer	Part Number / Identification
CoMat 02-024 MASKING TAPE (CREPE PAPERBACKING)	0AM53	CoMat 02-024
CoMat 02-141 LOCKWIRE	LOCAL	CoMat 02-141
CoMat 10-029 CORROSION PREVENTIVESLUSHING OIL	0AM53	CoMat 10-029
CoMat 10-077 APPROVED ENGINE OILS	LOCAL	CoMat 10-077
CoMat 10-094 ANTI-SEIZE COMPOUND, PURE Ni-SPECIAL	LOCAL	CoMat 10-094
CoMat 10-129 ANTI-SEIZE PASTE	34568	CoMat 10-129

Spares

Name	Manufacturer	Part Number / Identification	Quantity	Remark
Gasket			2
Gasket			2

Safety Requirements

WARNING

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

CAUTION

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

Procedure

1. Refer to: Figure
2. Install the foot-operated motor drive unit to the gearbox crank pad.
1. Refer to: Figure and Figure
2. Remove the igniter plug.
3. Do not remove the igniter insert.
4. Put the flexible borescope into the IAE 2P16204 Guide Tube 1 off until the end of the borescope is even with the end of the tube. This will be a limit mark on the borescope so you will not insert the borescope too far and cause damage to the borescope.
5. Put a piece of CoMat 02-024 MASKING TAPE (CREPE PAPERBACKING) on the borescope fiber bundle 3.250in. (82.55 mm) from the other end of the guide tube.
6. Put the end of the tube nearest the tape mark in the down position and the plane of the tube at a right angle to the engine axis.
7. 1. As the tube is put in, turn it clockwise carefully and connect the fitting to the igniter insert.
  2. Push the guide tube in until it touches the stop.
    NOTE
    In this position, the slot in the stop will be up.
    A cover for the eye which is not used will decrease eye tension.
    If you use an adjustable clamp to hold the borescope, you will be able to easily move the borescope dial and the fiber bundle.
    Some borescope units have closed-circuit television adapters. We highly recommend this unit.
  3. Turn the guide tube clockwise until it stops. Hold the tube in this position and tighten the locking wheel to secure the guide tube.
  4. Slowly push in the borescope through the guide tube while looking through the eye piece.
  5. CAUTION
    MAKE SURE THAT THE BORESCOPE TIP IS NOT IN THE PATH OF THE STAGE 1 HPT BLADES BEFORE YOU TURN THE ENGINE.
    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.
    Move the borescope end slightly, while pushing in, and find the Stage 1 HPT blades. Turn the borescope fiber bundle to help you locate the stage 1 HPT blades. Do not push the borescope past the tape mark.
8. Examine the blades for damage.
1. Refer to: Figure, Figure, Figure and Figure
2. SBE 72-0221: Introduce a new diffuser case
3. Remove the igniter plug.
4. Do not remove the igniter insert.
5. Put the flexible borescope into the IAE 2P16204 Guide Tube 1 off until the end of the borescope is even with the end of the tube. This will be a limit mark on the borescope so you will not insert the borescope too far and cause damage to the borescope.
6. Put a piece of CoMat 02-024 MASKING TAPE (CREPE PAPERBACKING) on the borescope fiber bundle 3.250 in. (82.55 mm) from the other end of the guide tube.
7. Put the end of the tube nearest the top mark in the down position and the plane of the tube at a right angle to the engine axis.
8. 1. As the tube is put in, turn it clockwise carefully and connect the fitting to the igniter insert.
  2. Push the guide tube in until it touches the stop.
    NOTE
    In this position, the slot in the stop will be up.
    A cover for the eye which is not used will decrease eye tension.
    If you use an adjustable clamp to hold the borescope, you will be able to easily move the borescope dial and the fiber bundle.
    Some borescope units have closed-circuit television adapters. We highly recommend this unit.
  3. Turn the guide tube clockwise until it stops. Hold the tube in this position and tighten the locking wheel to secure the guide tube.
  4. Slowly push in the borescope through the guide tube while looking through the eye piece.
  5. CAUTION
    MAKE SURE THAT THE BORESCOPE TIP IS NOT IN THE PATH OF THE STAGE 1 HPT BLADES BEFORE YOU TURN THE ENGINE.
    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.
    Move the borescope end slightly, while pushing in, and find the stage 1 HPT blades. Turn the borescope fiber bundle to help you locate the stage 1 HPT blades. Do not push the borescope past the tape mark.
9. Examine the blades for damage.
1. Refer to Figure and Figure.
2. 1. Remove the lockwire from the plug.
  2. Loosen and remove the plug and the gasket from the B2 or B3 port, Figure.
3. 1. WARNING
    MAKE SURE THAT THE BLANKING PLUG IS COOL BEFORE YOU REMOVE IT. THE PLUG STAYS HOT FOR A SHORT TIME AFTER THE ENGINE IS SHUTDOWN.
    Remove the lockwire and the bolts which hold the plugs.
  2. Put the IAE 1P16184 Puller 1 off in to the center hole of the plug (use if required).
  3. Remove the plug from the port with the puller.
  4. Remove the gasket from the plug.
  5. Remove the plug from the puller.
  6. Do Step to Step for the other plug.
4. Put a rigid borescope through the B2 or B3 port, Figure.
5. Examine the blades for damage.
6. Put a rigid borescope through the T1/2L or T1/2R port, Figure.
7. Examine the blades for damage.
1. Refer to: Figure, Figure, Figure, Figure, Figure and Figure
2. SBE 72-0221: Introduce a new diffuser case
3. 1. Remove the lockwire from the plug.
  2. Loosen and remove the plug and the gasket from the B3 or B4 port, Figure.
4. 1. Remove the lockwire and the bolts which hold the plugs.
  2. Put the IAE 1P16184 Puller 1 off into the centre hole of the plug (use if required).
  3. Remove the plug from the port with the puller.
  4. Remove the gasket from the plug.
  5. Remove the plug from the puller.
  6. Do Step throughStep for the other plug.
5. Put a rigid borescope through the B3 or B4 port, Figure.
6. Examine the blades for damage.
7. Put a rigid borescope through the T1/2L or T1/2R port, Figure.
8. Examine the blades for damage.
1. Refer to Figure, Figure and Figure.
2. 1. The nick or dent is in Area A or B and is larger than 0.200 in. (5.08 mm).
  2. Provided the nick or dent does not show the conditions that follow:
    The nick or dent is in Area A or Area B (not to include the blade trailing edge tip) and shows signs of torn metal or cracks.
    The nick or dent causes internal areas to show. These are areas where the air that is used to cool the blade goes.
1. Refer to Figure, Figure, Figure, Figure and Figure.
  NOTE
  There will be unwanted material on the airfoil because of the casting procedure. Refer to Figure. During borescope inspection, this material will look like small bumps on the concave and convex surfaces of the airfoil. These bumps are usually round or oval, are between 0.100 to 0.200 in. (2.54 to 5.08 mm) wide and are 0.005 in. (0.13 mm) high. These bumps are acceptable. No action is necessary.
  Tip Zone - The lower edge of the upper tip cooling holes to tip. In this zone a crack going through another crack is permitted.
2. 1. The crack in Area A or Area B is longer than 0.070 in. (1.78 mm) but not more than 0.15 in. (3.8 mm) for Area B and not more than 0.12 in. (3.0 mm) for Area A.
  2. The crack in Area A (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 the burn plus a crack is longer than 0.120 in. (3.05 mm). Maximum crack length is 0.070 in. (1.78 mm). Also, the combination of the burn plus the crack in Area A is not more than 0.220 in. (5.59 mm) and in Area B is not more than 0.15 in. (3.8 mm).
  3. The crack in the inner 25 percent of the leading or trailing edge span in Area A extends from a burned area and the combination of the burn plus the crack is longer than 0.070 in. (1.78 mm). Also, the combination of the burn plus the crack is not more than 0.130 in. (3.30 mm).
  4. The crack in Area C is longer than 0.100 in. (2.54 mm) but not more than 0.20 in. (5.1 mm).
  5. 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. (2.5 mm) but not more than 0.20 in. (5.1 mm).
  6. A radial crack on the airfoil starts at the blade tip and is longer than 0.20 in. (5.1 mm) but not more than 0.35 in. (8.9 mm). The number of cracks is not important.
  7. Axial crack is more than 0.14 in. (3.6 mm) but not more than 0.30 in. (7.6 mm) in the tip zone.
  8. There is missing material which extends more than 0.50 in. (12.7 mm) radially from the tip.
3. 1. Axial crack is more than 0.20 in. (5.1 mm) in the tip zone.
  2. There is missing material which extends more than 0.080 in. (2.03 mm) radially from the tip.
  3. There is missing material which extends more than 0.060 in. (1.52 mm) radially and is also more than 0.120 in. (3.05 mm) axially in the tip zone.
4. 1. Axial crack is more than 0.24 in. (6.1 mm) in the tip zone but not more than 0.30 in. (7.6 mm).
  2. There is missing material which extends more than 0.10 in. (2.5 mm) radially from the tip.
  3. There is missing material which extends more than 0.080 in. (2.03 mm) radially and is also more than 0.18 in. (4.6 mm) axially in the tip zone, but less than 0.09 in. (2.3 mm) radially and 0.280 in. (7.11 mm) axially in the tip zone.
  4. Provided the airfoil does not show the following:
    The cracks do not form closed loops between cooling holes (outside tip zone).
    The cracks do not go through other cracks (outside the tip zone).
    In the airfoil fillet radius there is a crack in the airfoil fillet radius or combination of a burn and crack.
    The internal cooling passages can be seen at the blade tip.
1. Refer to Figure.
  NOTE
  It is acceptable to have small pieces of the Stage 1 HPT seal (72-45-14,01-060) out between the rear platform of the Stage 1 HPT blade HPT Stage 1 Blade And Related Parts (72-45-14,01-010) and the Stage 1 HPT air seal ENGINE-STAGE 1 AIR SEAL (REAR) (72-45-15,01-020).
2. 1. The crack is longer than 0.150 in. (3.81 mm) and does not go up to the platform-to-airfoil fillet radius. The number of cracks is not important.
3. 1. The crack goes into the platform-to-airfoil fillet radius, but the crack does not go through the platform to the platform radius.
    NOTE
    Crack is not acceptable in airfoil fillet radius.
  2. The crack is longer than 0.20 in. (5.1 mm) and not more than 0.25 in. (6.4 mm) and does not go into the platform to the airfoil radius.
1. Refer to Figure, Figure, Figure, Figure and Figure.
2. 1. The erosion or burns on the trailing edge in the inner 25 percent of Area A are more than 0.070 in. (1.78 mm) long axially.
  2. The erosion or burns on the leading edge are more than one-quarter of the radial length of the airfoil.
  3. The erosion or burns on the leading edge have changed the airfoil shape.
  4. The erosion or burns on the airfoil or platform have gone through the coating. This does not include the burns on the leading edge, trailing edge or tip.
  5. The burns on the trailing in the outer 75 percent of Area A are more than 0.120 in. (3.05 mm) axially, except for the tip.
  6. The erosion or burns on the blade tip are more than 0.060 in. (1.52 mm) radially. (For reference, the concave side tip cooling holes (OD) are 0.080 in. (2.03 mm) from the tip).
    NOTE
    The blade trailing edge tip is 0.15 in. (3.81 mm) radially from the tip and 0.100 in. (2.54 mm) from the trailing edge and burning or erosion is permitted within this area.
  7. There is burned away or missing material on the blade trailing edge tip that is more than 0.07 in. (1.8 mm) axially from the trailing edge.
3. 1. The burns on the trailing edge of the inner 25 percent of the airfoil length of Area A are more than 0.110 in. (2.79 mm) axially and not more than 0.15 in. (3.8 mm).
  2. The burns on the trailing edge of the outer 75 percent of the airfoil length of Area A are more than 0.20 in. (5.1 mm) axially and not more than 0.30 in. (7.6 mm) axially. This does not include the blade tip.
  3. The burns on the trailing edge platform corner are more than 0.250 in. (6.35 mm) axially and not more than 0.40 in. (10.2 mm) axially; or more than 0.450 in. (11.43 mm) tangentially and not more than 0.60 in. (15.2 mm) tangentially.
    NOTE
    It is not permitted to have internal cavity exposed at tip.
  4. The erosion or burns on the blade tip extend more than 0.120 in. (3.05 mm) radially and not more than 0.180 in. (4.57 mm) radially.
  5. The leading edge burn-through on the outer 50 percent span in Area A is less than 0.20 in. (5.1 mm) in any direction. Note that the internal wall as seen through the burn-through hole is breached or has burns.
    NOTE
    Burns on the platform cannot increase the gap to the adjacent platform to more than 0.05 in. (1.3 mm).
  6. There is burned away or missing material on the blade trailing edge tip that is more than 0.09 in. (2.3 mm) axially from the trailing edge.

SUBTASK 72-00-00-220-093 Examine the Stage 1 HPT Duct Segments

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

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

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

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

NOTE

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

CONDITION	A 300-HR. INSPECTION	B 125-HR. INSPECTION	C REPLACE THE DUCT SEGMENT
Axial cracks	Any crack is longer than 0.250 in. (6.35 mm) and shorter than 0.500 in. (12.70 mm)	Any crack is longer than or equal to 0.500 in. (12.70 mm) but shorter than 1.20 in. (30.48 mm)	Any crack is longer than or equal to 1.20 in. (30.48 mm)
Circumferential cracks	Any crack is longer than 0.375 in. (9.53 mm) and shorter than 0.500 in. (12.70 mm)	Any crack is longer than or equal to 0.500 in. (12.70 mm) but shorter than 1.50 in. (38.1 mm)	Any crack is longer than or equal to 1.50 in. (31.38 mm)
Intersecting cracks	A combined crack that is longer than 0.250 in. (6.35 mm) and shorter than 0.500 in. (12.70 mm) axially or longer than 0.375 in. (9.53 mm) and shorter than 0.500 in. (12.70 mm) circumferentially	A combined crack that is longer than or equal to 0.500 in. (12.70 mm) and shorter than 1.20 in. (30.48 mm) axially or longer than or equal to 0.500 in. (12.70 mm) and shorter than 1.500 in. (38.10 mm) circumferentially	A combined crack that is longer than or equal to 1.20 in. (30.48 mm) axially or 1.500 in. (38.10 mm) circumferentially
Closed loop of cracks	Does not apply	Maximum length in X or Y direction that is less than 0.500 in. (12.70 mm)	Maximum length in X or Y direction that is more than or equal to 0.500 in. (12.70 mm)
Burning or erosion of the base metal at Area 1 (no burn-through)	Any amount more than two connecting holes	Does not apply	Does not apply
Burning or erosion of the base metal at Area 2 (no burn-through)	Shiplap burning more than the first row of cooling holes and not more than the second row of cooling holes	Shiplap burning goes through the second row of cooling holes	Does not apply
Burn-through in Areas 1 and 2	Does not apply	Less than 0.500 in. (12.7 mm) of continuous burn-through in Area 1, Area 2 or Areas 1 and 2 together	More than or equal to 0.500 in. (12.70 mm) continuous burn-through in Area 1, Area 2 or Areas 1 and 2 together
Burn-through with adjoining cracks in the axial direction	Does not apply	Combined length of X¹+X²+Z is less than 1.20 in. (30.48 mm) and Z is less than 0.500 in. (12.70 mm) in Area 1, Area 2 or Areas 1 and 2 together	Combined length of X¹+X²+Z is more than or equal to 1.20 in. (30.48 mm) or Z is more than or equal to 0.500 in. (12.70 mm)
Burn-through with adjoining cracks in the circumferential direction	Does not apply	Combined length of Y¹+Y²+Z is less than 1.50 in. (38.10 mm) and Z is less than 0.500 in. (12.70 mm) in Area 1, Area 2 or Areas 1 and 2 together	Combined length of Y¹+Y²+Z is more than or equal to 1.50 in. (38.10 mm) or Z is more than or equal to 0.500 in. (12.70 mm)
Burn-through the impingement plate	Does not apply	Does not apply	Any amount
Material on the Leading Edge is lifted up	Does not apply	Does not apply	Seal edge is lifted
Loss of Leading Edge material (parent material loss)	Less than 0.300 in. (7.62 mm)	More than or equal to 0.300 in. (7.62 mm) but less than 0.500 in. (12.70 mm)	More than or equal to 0.500 in. (12.70 mm)

1. Remove the borescope equipment from the borescope inspection ports.
1. For the IP1 igniter port, install the igniter plug.
2. 1. Lubricate the plug threads with CoMat 10-129 ANTI-SEIZE PASTE or CoMat 10-094 ANTI-SEIZE COMPOUND, PURE Ni-SPECIAL. Wipe off excess paste.
  2. Install the plug ENGINE-DIFFUSER CASE ASSEMBLY AND FITTINGS (72-42-10,01-020) and the ENGINE-DIFFUSER CASE ASSEMBLY AND FITTINGS (72-42-10,01-010) gasket 1 off, Figure.
  3. Torque the plug to 70 to 80 lbfin (7.91 to 9.04 Nm).
  4. Safety the plug with CoMat 02-141 LOCKWIRE.
3. 1. Put the ENGINE-HP TURBINE ROTOR AND STATOR ASSEMBLY (72-45-00,01-120) gasket 1 off in the case recess, Figure.
  2. Replace the gasket if the seal is not above the case surface.
  3. Put the gasket on the plug (2) ENGINE-HP TURBINE ROTOR AND STATOR ASSEMBLY (72-45-00,01-140) and install it in the case.
    NOTE
    It is permissible to correct minor thread damage to the threaded hole with a 0.5625-18UNF-3B die.
  4. Lubricate the bolt threads with CoMat 10-029 CORROSION PREVENTIVESLUSHING OIL anti-seize paste or CoMat 10-094 ANTI-SEIZE COMPOUND, PURE Ni-SPECIAL. Wipe off excess paste.
  5. Install the bolts (72-45-00,10-160).
  6. Torque the bolts to 75 to 85 lbfin (8.48 to 9.60 Nm).
  7. Safety the bolts with CoMat 02-141 LOCKWIRE.
1. For the IP1 igniter port, install the igniter plug.
2. 1. Lubricate the plug threads with CoMat 10-129 ANTI-SEIZE PASTE or CoMat 10-094 ANTI-SEIZE COMPOUND, PURE Ni-SPECIAL. Wipe off excess paste.
  2. Install the plug ENGINE-DIFFUSER CASE ASSEMBLY AND FITTINGS (72-42-10, 01-020) and the ENGINE-DIFFUSER CASE ASSEMBLY AND FITTINGS (72-42-10, 01-010) gasket 1 off, Figure.
  3. Torque the plug 70 lbfin to 80 lbfin (7.91 Nm to 9.05 Nm).
  4. Safety the plug with CoMat 02-141 LOCKWIRE.
3. 1. Put the ENGINE-HP TURBINE ROTOR AND STATOR ASSEMBLY (72-45-00, 01-120) gasket 1 off in the case recess, Figure.
  2. Replace the gasket if the seal is not above the case surface.
  3. CAUTION
    USE CAUTION WHEN INSTALLING PLUG. IF THE PLUG BREAKS DURING INSTALLATION AND FALLS INTO 2ND STAGE VANE CAVITY, REMOVE PLUG PIECE PRIOR TO RETURNING ENGINE TO SERVICE. IF NECESSARY, ACCESS TO THE CAVITY CAN BE OBTAINED BY REMOVING THE TCA TUBE.
    Put the gasket on the plug ENGINE-HP TURBINE ROTOR AND STATOR ASSEMBLY (72-45-00, 01-140) and install it in the case.
    NOTE
    It is permissible to correct minor thread damage to the threaded hole with a 0.5625-18UNF-3B die.
  4. Lubricate the bolt threads with CoMat 10-129 ANTI-SEIZE PASTE or CoMat 10-094 ANTI-SEIZE COMPOUND, PURE Ni-SPECIAL. Wipe off excess paste.
    NOTE
    Make sure that the borescope plug is correctly installed and bolt holes are aligned prior to continuing to next step.
  5. Install the bolts ENGINE-HP TURBINE ROTOR AND STATOR ASSEMBLY (72-45-00, 01-160).
  6. Torque the bolts to 75 lbfin to 85 lbfin (8.48 Nm to 9.60 Nm).
  7. Safety the bolts with CoMat 02-141 LOCKWIRE.
1. Remove the foot-operated motor drive unit from the gearbox crank pad.

Crank Pad Location

Pre SBE 72-0221: HP Turbine Borescope Locations for Inspection of the Stage 1 HPT Blades (Left Side)

SBE 72-0221: HP Turbine Borescope Locations for Inspection of the Stage 1 HPT Blades (Left Side)

Pre SBE 72-0221: HP Turbine Borescope Ports for Inspection of the Stage 1 HPT Blades (Right Side)

SBE 72-0221: HP Turbine Borescope Ports for Inspection of the Stage 1 HPT bBades (Right Side)

Pre SBE 72-0221: HP Turbine Ports for Inspection of the Stage 1 HPT Blades

SBE 72-0221: HP Turbine Ports for Inspection of the Stage 1 HPT Blades

Borescope Equipment

Pre SBE 72-0221: Borescope Ports

SBE 72-0221: Borescope Ports

Borescope Ports

Stage 1 HPT Blade Inspection Areas

Stage 1 HPT Blade Inspection Aeas

Sheet 1

Sheet 2

Stage 1 HPT Blade Inspection Areas

HPT Stage 1 HPT Segment Intersecting Cracks

Burn through with Adjoining Cracks in Axial Direction

Burn through with Adjoining Cracks in Circumferential Direction

Closed Loop of Cracks

Requirements After Job Completion

Follow-On Conditions

NONE

Manufacturer Code:	0AM53
Enterprise Name:	IAE INTERNATIONAL AERO ENGINES AG
BU Name:	NULL
Building:	SUITE 400
Street:	628 HEBRON AVENUE
City:	GLASTONBURY
State:	CT
Zip Code:	06033
Country:	USA

Manufacturer Code:	34568
Enterprise Name:	TIODIZE CO., INC.
BU Name:	TIODIZE CO., INC.
Street:	5858 ENGINEER DRIVE
City:	HUNTINGTON BEACH
State:	CA
Zip Code:	92649
Country:	USA
Phone Number:	1-714-898-4377
Fax Number:	1-714-891-7467
Internet:	www.tiodize.com

Manufacturer Code:	LOCAL
Enterprise Name:	LOCALLY SUPPLIED

Manufacturer Code:	LOCAL
Tool Number:	Cover (eye)
Tool Name:	Cover (eye)

TASK 72-00-00-200-004-A00 Engine General - Examine (Borescope) The HPT Stage 1 Blades, Inspection-004

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Common Information

TASK 72-00-00-200-004-A00 Engine General - Examine (Borescope) The HPT Stage 1 Blades, Inspection-004

General

Definitions and General Information

NOTE

NOTE

NOTE

NOTE

NOTE

Preliminary Requirements

Pre-Conditions

Support Equipment

Consumables, Materials and Expendables

Spares

Safety Requirements

WARNING

CAUTION

Procedure

SUBTASK 72-00-00-420-057 Install the Foot-Operated Motor Drive Unit to the Gearbox Crank Pad

SUBTASK 72-00-00-420-058-A00 Install the Guide Tube and the Flexible Borescope into the IP1 Borescope Port to Examine the Stage 1 Blades, thru (Pre SBE 72-0221)

NOTE

CAUTION

NOTE

SUBTASK 72-00-00-420-058-B00 Install the Guide Tube and the Flexible Borescope into the IP1 Borescope Port to Examine the Stage 1 HPT Blades (SBE 72-0221)

NOTE

CAUTION

NOTE

SUBTASK 72-00-00-020-057-A00 Install a Rigid Borescope to Examine the Stage 1 HPT Blades through the B2 or B3 and T1/2L or T1/2R Ports,thru (Pre SBE 72-0221)

NOTE

WARNING

SUBTASK 72-00-00-020-057-B00 Install a Rigid Borescope to Examine the Stage 1 HPT Blades through the B3 or B4 and T1/2L or T1/2R Ports (SBE 72-0221)

NOTE

WARNING

SUBTASK 72-00-00-220-074 Examine the Stage 1 HPT Blades for Nicks or Dents on the Airfoil

SUBTASK 72-00-00-220-075 Examine the Stage 1 HPT Blades for Cracks on the Airfoil

NOTE

SUBTASK 72-00-00-220-076 Examine the Stage 1 HPT Blades for Cracks on the Platform

NOTE

NOTE

SUBTASK 72-00-00-220-077 Examine the Stage 1 HPT Blades for Erosion or Burns on the Airfoil or Platform

NOTE

NOTE

NOTE

SUBTASK 72-00-00-220-093 Examine the Stage 1 HPT Duct Segments

NOTE

SUBTASK 72-00-00-020-058 Remove the Borescope Equipment from the Borescope Inspection Ports

SUBTASK 72-00-00-420-060-A00 Close the Borescope Inspection Ports after the Borescope Inspection is Completed (Pre SBE 72-0221)

NOTE

NOTE

SUBTASK 72-00-00-420-060-B00 Close the Borescope Inspection Ports after the Borescope Inspection is Completed (SBE 72-0221)

NOTE

CAUTION

NOTE

NOTE

SUBTASK 72-00-00-020-059 Remove the Foot-Operated Motor Drive Unit from the Gearbox Crank Pad

Figure: Crank Pad Location

Crank Pad Location

Figure: Pre SBE 72-0221: HP Turbine Borescope Locations for Inspection of the Stage 1 HPT Blades (Left Side)

Pre SBE 72-0221: HP Turbine Borescope Locations for Inspection of the Stage 1 HPT Blades (Left Side)

Figure: SBE 72-0221: HP Turbine Borescope Locations for Inspection of the Stage 1 HPT Blades (Left Side)

SBE 72-0221: HP Turbine Borescope Locations for Inspection of the Stage 1 HPT Blades (Left Side)

Figure: Pre SBE 72-0221: HP Turbine Borescope Ports for Inspection of the Stage 1 HPT Blades (Right Side)

Pre SBE 72-0221: HP Turbine Borescope Ports for Inspection of the Stage 1 HPT Blades (Right Side)

Figure: SBE 72-0221: HP Turbine Borescope Ports for Inspection of the Stage 1 HPT bBades (Right Side)

SBE 72-0221: HP Turbine Borescope Ports for Inspection of the Stage 1 HPT bBades (Right Side)

Figure: Pre SBE 72-0221: HP Turbine Ports for Inspection of the Stage 1 HPT Blades

Pre SBE 72-0221: HP Turbine Ports for Inspection of the Stage 1 HPT Blades

Figure: SBE 72-0221: HP Turbine Ports for Inspection of the Stage 1 HPT Blades

SBE 72-0221: HP Turbine Ports for Inspection of the Stage 1 HPT Blades

Figure: Borescope Equipment

Borescope Equipment

Figure: Pre SBE 72-0221: Borescope Ports

Pre SBE 72-0221: Borescope Ports

Figure: SBE 72-0221: Borescope Ports

SBE 72-0221: Borescope Ports

Figure: Borescope Ports