W DOC AIRBUS | AMM A320F

Inspection of the HP Compressor [IAE]

TASK 72-00-00-200-016-B
Inspection of the HP Compressor

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.
ZONE: 400
FIN: 1000EM1 ** ON A/C NOT FOR ALL
FIN: 1000EM2 ** ON A/C NOT FOR ALL
1. Reason for the Job
This task is for A5 basic (non SelectOne) engines, which have not SBE 72-0560 or SBE 72-0561 incorporated (SelectOne Retrofit Standard or SelectOne Production Standard).
This task gives the procedure for the inspection of the HP compressor. A description of the types of damage that may be seen is given in 70-52-11, Definition of Damage.
2. Job Set-up Information
 A. Fixtures, Tools, Test and Support Equipment
REFERENCE
QTY
DESIGNATION
No specific
AR
BRUSH - BRISTLED, STIFF
No specific
AR
SCRAPER - NON METALLIC
No specific
AR
SCREWDRIVER TORQ BIT SET 212-1/4-ACR
No specific
AR
WARNING NOTICE(S)
No specific
Torque wrench: range to between 105 and 85 lbf.in (1.19 and 0.96 m.daN ) T
IAE6F10408
1
EQUIPMENT-BORESCOPE
 B. Consumable Materials
REFERENCE
DESIGNATION
(Material No.V04-004)
jointing compound
(Material No.V10-070)
anti-seize compound
(Material No.V10-072)
anti-seize compound
(Material No.14SBA1)
Textile-Lint free Cotton -
 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
2
GASKET
AIPC 72-41-00-80-030
1
GASKET
AIPC 72-41-23-80-060
 E. Referenced Information
REFERENCE
DESIGNATION
TASK 70-11-50-100-802-A
Local Swab or Wipe Cleaning with Solvent
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 72-00-00-210-012-A
Inspection of the HP Compressor Stage 3 Rotor Clapper
TASK 72-00-00-300-802-A
Dressing of Damaged Leading or Trailing Edges on the HP Compressor Blades through the Borescope Ports, Repair - VRS9653
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 75-23-51-000-010-B
Removal of the Stage 10 to HPT Air Control Valve
TASK 75-23-51-400-010-B
Installation of the Stage 10 to HPT Air Control Valve
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
F HP Compressor Borescope Access Ports (Underside)
F Stage 3 Borescope Access Port
F Stage 5 Borescope Access Port
F HP Compressor Blades
F HP Compressor Blade
F Blade Tip Rub
F HP Compressor Blades
F HP Compressor Blades
F Typical Leading Edge Nicks and Dents in Zone C (For Stage 8 and 10 Rotor Blades only)
F Stage 6 to 11 Stator Path Liner Loss Inspection
F Stage 6 Rotor Path Lining
F Stage 6, 7 and 8 Front and Rear Damper Wires
3. Job Set-up
Subtask 72-00-00-941-084-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 72-00-00-010-100-A ** ON A/C NOT FOR ALL
B. Open the fan cowls (Ref. AMM TASK 71-13-00-010-010):
   (1) FOR [1000EM1] (ENGINE-1)
437AL 438AR.
   (2) FOR [1000EM2] (ENGINE-2)
447AL 448AR.
Subtask 72-00-00-040-075-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 72-00-00-010-111-A ** ON A/C NOT FOR ALL
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 72-00-00-010-099-A ** ON A/C NOT FOR ALL
E. Remove the borescope access port covers
F HP Compressor Borescope Access Ports (Underside) ** ON A/C NOT FOR ALL
NOTE: The borescope access ports give access to these stages of the compressor:
  • Port A gives access to the leading edge of stage 3. It is located 40 degrees below the engine horizontal on the left side.
  • Port B gives access to the trailing edge of stage 3 and the leading edge of stage 4. It is located 34 degrees below the engine horizontal on the right side.
  • Port C gives access to the trailing edge of stage 5 and the leading edge of stage 6. It is located 61 degrees below the engine horizontal on the left side.
  • Port D gives access to the trailing edge of stage 7 and the leading edge of stage 8. It is located 61 degrees below the engine horizontal on the right side.
  • Port E gives access to the trailing edge of stage 8 and the leading edge of stage 9. It is located 74 degrees below the engine horizontal on the right side.
  • Port F gives access to the trailing edge of stage 9 and the leading edge of stage 10. It is located 61 degrees below the engine horizontal on the right side.
  • Port G gives access to the trailing edge of stage 11 and the leading edge of stage 12. It is located 55 degrees below the engine horizontal on the right side.
NOTE: Unless specified elsewhere, it is sufficient to inspect stage 3 and 12 HP compressor blades with the engine on wing, in order to determine the general condition of the HP compressor.
   (1) Remove the borescope access port covers A or B
F Stage 3 Borescope Access Port ** ON A/C NOT FOR ALL
     (a) Remove the bolts which attach the access port cover.
     (b) Remove the access port cover.
   (2) Remove the borescope access port covers D, E, F or G
     (a) Remove the bolts which attach the access port cover.
     (b) Remove the access port cover and discard the gasket.
   (3) Remove the access port cover C
F Stage 5 Borescope Access Port ** ON A/C NOT FOR ALL
     (a) Remove the nuts (1) from the two stage 5 levers (2) which are adjacent to the borescope access port cover.
     (b) Remove the levers (2) and the adjusting spacers. Keep the adjusting spacers (3) with the applicable lever.
     (c) Remove the two screws (4). Use the SCREWDRIVER TORQ BIT SET 212-1/4-ACR.
     (d) Remove the borescope port cover (5).
Subtask 72-00-00-010-103-A ** ON A/C NOT FOR ALL
F. Remove the stage 10 to HP Turbine Air Valve
   (1) Remove the stage 10 to HP Turbine Air Valve (Ref. AMM TASK 75-23-51-000-010).
Subtask 72-00-00-110-067-A ** ON A/C NOT FOR ALL
G. Remove the old jointing
CAUTION: MAKE SURE THAT NONE OF THE OLD JOINTING COMPOUND GOES IN TO THE ENGINE THROUGH THE ACCESS PORTS.
   (1) Remove the old jointing compound from around the access ports and the access port covers.
     (a) Use a SCRAPER - NON METALLIC and a clean Textile-Lint free Cotton - (Material No.14SBA1) made moist with a solvent from (Ref. AMM TASK 70-11-50-100-802) to remove all traces of old jointing compound (Ref. AMM TASK 70-11-50-100-802).
Subtask 72-00-00-480-062-A ** ON A/C NOT FOR ALL
H. Install the tool to turn the HP system (Ref. AMM TASK 72-00-00-480-010) or (Ref. AMM TASK 72-00-00-860-010).
Subtask 72-00-00-941-085-A ** ON A/C NOT FOR ALL
I. Prepare the borescope for use
   (1) Prepare the IAE6F10408 EQUIPMENT-BORESCOPE for use as given in the maker's instructions.
4. Procedure
Subtask 72-00-00-480-063-A ** ON A/C NOT FOR ALL
A. Install the borescope probe
   (1) Carefully put the borescope probe into the access port of the stage of the compressor you want to examine.
NOTE: Use an 8 mm borescope probe for ports A, B and C and a 5.5 mm borescope probe for ports D, E, F and G and a flexible borescope for the inspection of the heatshield assemblies.
Subtask 72-00-00-290-066-A ** ON A/C NOT FOR ALL
B. Inspection of the Heatshield Retaining Assemblies at their five (5) locations
NOTE: For the inspection of the heatshield assemblies you must remove the stage 10 to HP turbine air valve.
   (1) Examine the boltspacer and washer assembly at 2 fixed locations
     (a) Frettage, wear or loss
  • Reject
   (2) Examine the spacers or washers at the eight (8) floating locations
     (a) Frettage, wear or loss
  • Accept, provided the fifth retaining location (mid-span of heatshield) is secure with no frettage or wear.
Subtask 72-00-00-290-058-A ** ON A/C NOT FOR ALL
C. Inspection of the HP Compressor Blades
F HP Compressor Blades ** ON A/C NOT FOR ALL
F HP Compressor Blade ** ON A/C NOT FOR ALL
F Blade Tip Rub ** ON A/C NOT FOR ALL
   (1) Examine each compressor blade in turn for:
     (a) Nicks or tears.
     (b) Cracks.
     (c) Dents.
     (d) Tip damage and discoloration.
NOTE: Use the compressor turning tool attached to the gearbox crank pad to turn the compressor. This permits inspection of each blade.
NOTE: Surface contamination from airborne abradable deposits is acceptable without limit.
Subtask 72-00-00-220-072-A ** ON A/C NOT FOR ALL
D. Examine the stage 3 blades:
   (1) Damage in zone A:
F HP Compressor Blade ** ON A/C NOT FOR ALL
     (a) Nicks and tears:
       1 One nick or tear per airfoil not more than 0.125 in. (3.17 mm) in the axial length
  • Accept
       2 More than one nick or tear per airfoil but with a cumulative axial length of not more than 0.125 in. (3.17 mm)
  • Accept
       3 Nicks or tears with an axial length more than Para 4.D.(1).(a).2_ but not more than 0.200 in. (5.08 mm) per airfoil
       4 More than Para 4.D.(1).(a).3_
  • Reject
     (b) Cracks:
       1 Radial cracks from the blade tip not more than 0.250 in. (6.35 mm) in length
  • Accept
       2 More than Para 4.D.(1).(b).1_ or axial cracks
  • Reject
     (c) Dents:
       1 Dents not related to cracks, nicks or tears
  • Accept
       2 Dents related to cracks, nicks or tears
  • Reject
   (2) Damage in zone B:
F HP Compressor Blade ** ON A/C NOT FOR ALL
F HP Compressor Blades ** ON A/C NOT FOR ALL
F HP Compressor Blades ** ON A/C NOT FOR ALL
     (a) Nicks and tears:
       1 Nicks that are 0.005 in. (0.127 mm) deep or less
  • Accept
       2 Other than Para 4.D.(2).(a).1_
  • Reject
     (b) Cracks:
  • Reject
     (c) Dents:
       1 Dents not related to cracks, nicks or tears
  • Accept
       2 Dents related to cracks, nicks or tears
  • Reject
     (d) Clapper misalignment:
       1 No sign of clapper overlap
  • Accept
       2 No signs of bent or misaligned clappers
  • Accept
       3 Less than 50 percent clapper misalignment
  • Accept
       4 More than Para 4.D.(2).(d).3_
  • Reject
       5 Signs of bent clappers or clapper overlap (shingling)
  • Reject
     (e) Clapper wear:
   (3) Damage in zone C:
F HP Compressor Blade ** ON A/C NOT FOR ALL
     (a) Nicks and Tears:
       1 One nick or tear per airfoil not more than 0.060 in. (1.52 mm) in the axial length
  • Accept
       2 More than one nick or tear per airfoil but with a cumulative axial length not more than 0.060 in. (1.52 mm)
  • Accept
       3 Nicks or tears with an axial length more than Para 4.D.(3).(a).2_ but not more than 0.200 in. (5.08 mm) per airfoil
       4 More than Para 4.D.(3).(a).3_
  • Reject
     (b) Cracks:
  • Reject
     (c) Dents:
       1 Dents not related to cracks, nicks or tears
  • Accept
       2 Dents related to cracks, nicks or tears
  • Reject
   (4) Damage in zone D:
F HP Compressor Blade ** ON A/C NOT FOR ALL
     (a) Tears:
  • Reject
     (b) Nicks:
       1 Nicks that are 0.005 in. (0.127 mm) or less in depth
  • Accept, without limit to number
       2 More than in Para 4.D.(4).(b).1_ but not more than 0.050 in. (1.270 mm) in depth, located on either the leading edge or the trailing edge. A minimum distance of 0.205 in. (5.207 mm) from the top (Outer Diameter) of the blade platform, measured from the corner that is the closest to the leading edge and the trailing edge, must be kept. Keep out of the fillet area.
       3 More than Step 4.D.(4).(b).2_
  • Reject
     (c) Cracks:
  • Reject
     (d) Dents (not related to cracks, nicks or tears):
       1 Dents that are 0.005 in. (0.127 mm) deep or less
  • Accept, without limit to number
       2 More than in Para 4.D.(4).(d).1_ but not more than 0.050 in. (1.270 mm) in depth, located on either the leading edge or the trailing edge. A minimum distance of 0.205 in. (5.207 mm) from the top (Outer Diameter) of the blade platform, measured from the corner that is the closest to the leading edge and the trailing edge, must be kept. Keep out of the fillet area.
       3 More than Step 4.D.(4).(d).2_
  • Reject
   (5) Tip damage and discoloration:
F HP Compressor Blades ** ON A/C NOT FOR ALL
     (a) Discoloration:
       1 Heat discoloration related to blade tip rub
  • Accept
       2 Heat discoloration not related to blade tip rub
  • Reject
     (b) Bend or curl:
       1 The length of the bend or the curl is not more than 5 percent of dimension X and the width of the bend or the curl is not more than 5 percent of dimension Y
  • Accept
       2 More than Para 4.D.(5).(b).1_
  • Reject
       3 Bends or curls related to cracks or tears
  • Reject
     (c) Piece of blade tip missing:
       1 The axial length of the piece is not more than 25 percent of the blade chord and the radial length of the piece is not more than the axial length
  • Accept when the blades of all the stages that follow are examined and acceptable
       2 More than Para 4.D.(5).(c).1_
  • Reject
     (d) Blade tip rub:
       1 Not more than 0.005 in. (0.127 mm) in depth
  • Accept
       2 More than Para 4.D.(5).(d).1_
  • Reject
Subtask 72-00-00-220-073-A ** ON A/C NOT FOR ALL
E. Examine the stage 4 and 5 blades:
   (1) Damage in zone A:
F HP Compressor Blade ** ON A/C NOT FOR ALL
     (a) Nicks and tears:
       1 One nick or tear per airfoil not more than 0.125 in. (3.17 mm) in the axial length
  • Accept
       2 More than one nick or tear per airfoil but with a cumulative axial length of not more than 0.125 in. (3.17 mm)
  • Accept
       3 Nicks or tears with an axial length more than Para 4.E.(1).(a).2_ but not more than 0.180 in. (4.57 mm) per airfoil
       4 More than Para 4.E.(1).(a).3_
  • Reject
     (b) Cracks:
       1 Radial cracks from the blade tip not more than 0.250 in. (6.35 mm) in length
  • Accept
       2 More than Para 4.E.(1).(b).1_ or axial cracks
  • Reject
     (c) Dents:
       1 Dents not related to cracks, nicks or tears
  • Accept
       2 Dents related to cracks, nicks or tears
  • Reject
   (2) Damage in zone B:
F HP Compressor Blade ** ON A/C NOT FOR ALL
     (a) Nicks and tears:
       1 One nick or tear per airfoil not more than 0.060 in. (1.52 mm) in the axial length
  • Accept
       2 More than one nick or tear per airfoil but with a cumulative axial length of not more than 0.060 in. (1.52 mm)
  • Accept
       3 Nicks or tears with an axial length more than Para 4.E.(2).(a).2_ but not more than 0.180 in. (4.57 mm) per airfoil
       4 More than Para 4.E.(2).(a).3_
  • Reject
     (b) Cracks:
  • Reject
     (c) Dents:
       1 Dents not related to cracks, nicks or tears
  • Accept
       2 Dents related to cracks, nicks or tears
  • Reject
   (3) Damage in zone C:
F HP Compressor Blade ** ON A/C NOT FOR ALL
     (a) Tears:
  • Reject
     (b) Nicks:
       1 Nicks that are 0.005 in. (0.127 mm) or less in depth
  • Accept, without limit to number
       2 Stage 4 blades: More than in Para 4.E.(3).(b).1_ but not more than 0.050 in. (1.27 mm) in depth, located on the leading edge. A minimum distance of 0.220 in. (5.588 mm) from the top (Outer Diameter) of the blade platform, measured from the corner that is the closest to the leading edge, must be kept. Keep out of the fillet area.
       3 Stage 5 blades: More than in Para 4.E.(3).(b).1_ but not more than 0.050 in. (1.27 mm) in depth, located on the trailing edge. A minimum distance of 0.220 in. (5.588 mm) from the top (Outer Diameter) of the blade platform, measured from the corner that is the closest to trailing edge, must be kept. Keep out of the fillet area.
       4 More than Para 4.E.(3).(b).2_ or Para 4.E.(3).(b).3_
  • Reject
     (c) Cracks:
  • Reject
     (d) Dents (not related to cracks, nicks or tears):
       1 Dents that are 0.005 in. (0.127 mm) or less in depth
  • Accept, without limit to number
       2 Stage 4 blades: More than in Para 4.E.(3).(d).1_ but not more than 0.050 in. (1.27 mm) in depth, located on the leading edge. A minimum distance of 0.220 in. (5.588 mm) from the top (Outer Diameter) of the blade platform, measured from the corner that is the closest to the leading edge, must be kept. Keep out of the fillet area.
       3 Stage 5 blades: More than in Para 4.E.(3).(d).1_ but not more than 0.050 in. (1.27 mm) in depth, located on the trailing edge. A minimum distance of 0.220 in. (5.588 mm) from the top (Outer Diameter) of the blade platform, measured from the corner that is the closest to the trailing edge, must be kept. Keep out of the fillet area.
       4 Other than Para 4.E.(3).(d).2_ or Para 4.E.(3).(d).3_
  • Reject
   (4) Tip damage and discoloration:
F HP Compressor Blades ** ON A/C NOT FOR ALL
     (a) Discoloration:
       1 Heat discoloration related to blade tip rub
  • Accept
       2 Heat discoloration not related to blade tip rub
  • Reject
     (b) Bend or curl:
       1 The length of the bend or the curl is not more than 5 percent of dimension X and the width of the bend or the curl is not more than 5 percent of dimension Y
  • Accept
       2 More than Para 4.E.(4).(b).1_
  • Reject
       3 Bends or curls related to cracks or tears
  • Reject
     (c) Piece of blade tip missing:
       1 The axial length of the piece is not more than 25 percent of the blade chord and the radial length of the piece is not more than the axial length
  • Accept when the blades of all the stages that follow are examined and acceptable
       2 More than Para 4.E.(4).(c).1_
  • Reject
     (d) Blade tip rub:
       1 Blade tip rub not more than 0.005 in. (0.127 mm) in depth
  • Accept
       2 More than Para 4.E.(4).(d).1_
  • Reject
Subtask 72-00-00-220-135-A ** ON A/C NOT FOR ALL
F. Examine the stage 6 blades:
   (1) Damage in zone A:
F HP Compressor Blade ** ON A/C NOT FOR ALL
     (a) Nicks and tears:
       1 One nick or tear per airfoil not more than 0.125 in. (3.17 mm) in the axial length
  • Accept
       2 More than one nick or tear per airfoil but with a cumulative axial length of not more than 0.125 in. (3.17 mm)
  • Accept
       3 More than Para 4.F.(1).(a).2_
  • Reject
     (b) Cracks:
       1 Radial cracks from the blade tip not more than 0.250 in. (6.35 mm) in length
  • Accept
       2 More than Para 4.F.(1).(b).1_ or axial cracks
  • Reject
     (c) Dents:
       1 Dents not related to cracks, nicks or tears
  • Accept
       2 Dents related to cracks, nicks or tears
  • Reject
   (2) Damage in zone B:
F HP Compressor Blade ** ON A/C NOT FOR ALL
     (a) Nicks and tears:
       1 One nick or tear per airfoil not more than 0.060 in. (1.52 mm) in the axial length
  • Accept
       2 More than one nick or tear per airfoil but with a cumulative axial length of not more than 0.060 in. (1.52 mm)
  • Accept
       3 More than Para 4.F.(2).(a).2_
  • Reject
     (b) Cracks:
  • Reject
     (c) Dents:
       1 Dents not related to cracks, nicks or tears
  • Accept
       2 Dents related to cracks, nicks or tears
  • Reject
   (3) Damage in zone C:
F HP Compressor Blade ** ON A/C NOT FOR ALL
     (a) Tears:
  • Reject
     (b) Nicks:
       1 Nicks that are 0.005 in. (0.127 mm) or less in depth
  • Accept, without limit to number
       2 Other than Para 4.F.(3).(b).1_
  • Reject
     (c) Cracks:
  • Reject
     (d) Dents (not related to cracks, nicks or tears):
       1 Dents that are 0.005 in. (0.127 mm) or less in depth
  • Accept, without limit to number
       2 More than Para 4.F.(3).(d).1_
  • Reject
   (4) Tip damage and discoloration:
F HP Compressor Blades ** ON A/C NOT FOR ALL
NOTE: Engines with any damage more than 10 percent of dimension X or dimension Y require a one-off inspection at 750 flight cycles.
NOTE: All the tip curls must be free from cracks, tears, nicks and creases.
     (a) Discoloration:
       1 Heat discoloration related to blade tip rub
  • Accept
       2 Heat discoloration not related to blade tip rub
  • Reject
     (b) Bend or curl:
       1 The length of the bend or the tip curl is not more than 5 percent of dimension X or dimension Y (whichever is the greater)
  • Accept
       2 The length of the bend or the tip curl is between 5 and 10 percent of dimension X or dimension Y (whichever is the greater)
  • Accept for ten blades
       3 The length of the bend or the tip curl is between 10 and 15 percent of dimension X or dimension Y (whichever is the greater)
  • Accept for five blades
       4 The length of the bend or the tip curl is between 15 and 20 percent of dimension X or dimension Y (whichever is the greater)
  • Accept for one blade
       5 The length of the bend or the tip curl is more than Para 4.F.(4).(b).4_ or more blades are bent or curled than accepted in Para 4.F.(4).(b).2_ thru Para 4.F.(4).(b).4_
  • Reject
NOTE: If the damage is more than the limits specified during the scheduled inspection, reject the engine in less than 10 flight cycles.
NOTE: If the damage is more than the limits specified during the unscheduled inspection, reject the engine immediately.
     (c) Piece of blade tip missing:
       1 The axial length of the piece is not more than 25 percent of the blade chord and the radial length of the piece is not more than the axial length
  • Accept when the blades of all the stages that follow are examined and acceptable
       2 More than Para 4.F.(4).(c).1_
  • Reject
     (d) Blade tip rub:
       1 Blade tip rub not more than 0.005 in. (0.13 mm) in depth
  • Accept
       2 More than Para 4.F.(4).(d).1_
  • Reject
Subtask 72-00-00-220-136-A ** ON A/C NOT FOR ALL
G. Examine the stage 7 blades:
   (1) Damage in zone A:
F HP Compressor Blade ** ON A/C NOT FOR ALL
     (a) Nicks and tears:
       1 One nick or tear per airfoil not more than 0.030 in. (0.76 mm) in the axial length
  • Accept
       2 More than one nick or tear per airfoil but with a cumulative axial length of not more than 0.030 in. (0.76 mm)
  • Accept
       3 Nicks and tears with an axial length more than Para 4.G.(1).(a).2_ but not more than 0.075 in. (1.90 mm) per airfoil
       4 More than Para 4.G.(1).(a).3_
  • Reject
     (b) Cracks:
       1 Radial cracks from the blade tip not more than 0.250 in. (6.35 mm) in length
  • Accept
       2 More than Para 4.G.(1).(b).1_
  • Reject
     (c) Dents:
       1 Dents not related to cracks, nicks or tears
  • Accept
       2 Dents related to cracks, nicks or tears
  • Reject
   (2) Damage in zone B:
F HP Compressor Blade ** ON A/C NOT FOR ALL
     (a) Nicks and tears:
       1 One nick or tear per airfoil not more than 0.030 in. (0.7620 mm) in the axial length
  • Accept
       2 More than one nick or tear per airfoil but with a cumulative axial length of not more than 0.030 in. (0.76 mm)
  • Accept
       3 Nicks and tears with an axial length more than Para 4.G.(2).(a).2_ but not more than 0.075 in. (1.90 mm) per airfoil
       4 More than Para 4.G.(2).(a).3_
  • Reject
     (b) Cracks:
  • Reject
     (c) Dents:
       1 Dents not related to cracks, nicks or tears
  • Accept
       2 Dents related to cracks, nicks or tears
  • Reject
   (3) Damage in zone C:
F HP Compressor Blade ** ON A/C NOT FOR ALL
     (a) Tears:
  • Reject
     (b) Nicks:
       1 Nicks that are 0.005 in. (0.127 mm) or less in depth
  • Accept, without limit to number
       2 More than in Para 4.G.(3).(b).1_ but not more than 0.026 in. (0.660 mm) in depth, located on the trailing edge. A minimum distance of 0.095 in. (2.413 mm) from the top (Outer Diameter) of the blade platform, measured from the corner that is the closest to trailing edge, must be kept. Keep out of the fillet area.
       3 More than Step 4.G.(3).(b).2_
  • Reject
     (c) Cracks:
  • Reject
     (d) Dents (not related to cracks, nicks or tears):
       1 Dents that are 0.005 in. (0.127 mm) or less in depth
  • Accept, without limit to number
       2 More than in Para 4.G.(3).(d).1_ but not more than 0.026 in. (0.660 mm) in depth, located on the trailing edge. A minimum distance of 0.095 in. (2.413 mm) from the top (Outer Diameter) of the blade platform, measured from the corner that is the closest to the trailing edge, must be kept. Keep out of the fillet area.
       3 More than Step 4.G.(3).(d).2_
  • Reject
   (4) Tip damage and discoloration:
F HP Compressor Blades ** ON A/C NOT FOR ALL
     (a) Discoloration:
       1 Heat discoloration related to blade tip rub
  • Accept
       2 Heat discoloration not related to blade tip rub
  • Reject
     (b) Bend or curl:
       1 The length of the bend or the curl is not more than 5 percent of dimension X and the width of the bend or the curl is not more than 5 percent of dimension Y
  • Accept
       2 More than Para 4.G.(4).(b).1_
  • Reject
       3 Bends or curls related to cracks or tears
  • Reject
     (c) Piece of blade tip missing:
       1 The axial length of the piece is not more than 25 percent of the blade chord and the radial length of the piece is not more than the axial length
  • Accept when the blades of all the stages that follow are examined and acceptable
       2 More than Para 4.G.(4).(c).1_
  • Reject
     (d) Blade tip rub:
       1 Blade tip rub not more than 0.005 in. (0.13 mm) in depth
  • Accept
       2 More than Para 4.G.(4).(d).1_
  • Reject
Subtask 72-00-00-220-137-A ** ON A/C NOT FOR ALL
H. Examine the stage 8 blades:
   (1) Damage in zone A:
F HP Compressor Blade ** ON A/C NOT FOR ALL
     (a) Nicks and tears:
       1 One nick or tear per airfoil not more than 0.030 in. (0.76 mm) in the axial length
  • Accept
       2 More than one nick or tear per airfoil but with a cumulative axial length of not more than 0.030 in. (0.76 mm)
  • Accept
       3 Nicks or tears with an axial length more than Para 4.H.(1).(a).2_ but not more than 0.067 in. (1.70 mm) per airfoil
       4 More than Para 4.H.(1).(a).3_
  • Reject
     (b) Cracks:
       1 Radial cracks from the blade tip not more than 0.250 in. (6.35 mm) in length
  • Accept
       2 More than Para 4.H.(1).(b).1_ or axial cracks
  • Reject
     (c) Dents:
       1 Dents not related to cracks, nicks or tears
  • Accept
       2 Dents related to cracks, nicks or tears
  • Reject
   (2) Damage in zone B:
F HP Compressor Blade ** ON A/C NOT FOR ALL
     (a) Nicks and tears:
       1 One nick or tear per airfoil not more than 0.030 in. (0.76 mm) in the axial length
  • Accept
       2 More than one nick or tear per airfoil but with a cumulative axial length of not more than 0.030 in. (0.76 mm)
  • Accept
       3 Nicks and tears with an axial length more than Para H.(2).(a).2_ but not more than 0.067 in. (1.70 mm) per airfoil
       4 More than Para 4.H.(2).(a).3_
  • Reject
     (b) Cracks:
  • Reject
     (c) Dents:
       1 Dents not related to cracks, nicks or tears
  • Accept
       2 Dents related to cracks, nicks or tears
  • Reject
   (3) Damage in zone C:
F HP Compressor Blade ** ON A/C NOT FOR ALL
     (a) Tears:
  • Reject
     (b) Nicks:
       1 Nicks that are 0.005 in. (0.127 mm) or less in depth
  • Accept, without limit to number
       2 Nicks more than in Para 4.H.(3).(b).1_ but not more than 0.012 in. (0.305 mm) in depth
  • Accept, as long as the following criteria are met:
         a A single nick per blade in zone C, located on the leading edge or contained in less than 0.020 in. (0.508 mm) from the leading edge.
F Typical Leading Edge Nicks and Dents in Zone C (For Stage 8 and 10 Rotor Blades only) ** ON A/C NOT FOR ALL
         b Not more than three nicks per stage.
NOTE: Alternative option to perform the repair prior to the next flight, (Ref. AMM TASK 72-00-00-300-802) for damage that meets criteria of Para 4.H.(3).(b).2_.
       3 More than in Para 4.H.(3).(b).2_ but not more than 0.028 in. (0.711 mm) in depth, located on the leading edge. A minimum distance of 0.075 in. (1.905 mm) from the top (Outer Diameter) of the blade platform, measured from the corner that is the closest to the leading edge, must be kept. Keep out of the fillet area.
       4 More than in Para 4.H.(3).(b).3_
  • Reject
     (c) Cracks:
  • Reject
     (d) Dents (not related to cracks, nicks or tears):
       1 Dents that are 0.005 in. (0.127 mm) or less in depth
  • Accept, without limit to number
       2 More than in Para 4.H.(3).(d).1_ but not more than 0.012 in. (0.305 mm) in depth
  • Accept as long as the following criteria are met:
         a A single dent per blade in zone C, located on the leading edge or contained in less than 0.020 in. (0.508 mm) from the leading edge.
         b Not more than three dents per stage.
NOTE: Alternative option to perform the repair prior to the next flight, (Ref. AMM TASK 72-00-00-300-802) for damage that meets criteria of Para 4.H.(3).(d).2_.
       3 More than in Para 4.H.(3).(d).2_ but not more than 0.028 in. (0.711 mm) in depth, located on the leading edge. A minimum distance of 0.075 in. (1.905 mm) from the top (Outer Diameter) of the blade platform, measured from the corner that is the closest to the leading edge, must be kept. Keep out of the fillet area.
       4 More than in Para 4.H.(3).(d).3_
  • Reject
   (4) Tip damage and discoloration:
F HP Compressor Blades ** ON A/C NOT FOR ALL
     (a) Discoloration:
       1 Heat discoloration related to blade tip rub
  • Accept
       2 Heat discoloration not related to blade tip rub
  • Reject
     (b) Bend or curl:
       1 The length of the bend or the curl is not more than 5 percent of dimension X and the width of the bend or the curl is not more than 5 percent of dimension Y
  • Accept
       2 More than Para 4.H.(4).(b).1_
  • Reject
       3 Bends or curls related to cracks or tears
  • Reject
     (c) Piece of blade tip missing:
       1 The axial length of the piece is not more than 25 percent of the blade chord and the radial length of the piece is not more than the axial length
  • Accept when the blades of all the stages that follow are examined and acceptable
       2 More than Para 4.H.(4).(c).1_
  • Reject
     (d) Blade tip rub:
       1 Blade tip rub not more than 0.005 in. (0.127 mm) in depth
  • Accept
       2 More than Para 4.H.(4).(d).1_
  • Reject
Subtask 72-00-00-220-149-A ** ON A/C NOT FOR ALL
I. Examine the stage 9 blades:
   (1) Damage in zone A:
F HP Compressor Blade ** ON A/C NOT FOR ALL
     (a) Nicks and tears:
       1 One nick or tear per airfoil not more than 0.030 in. (0.76 mm) in the axial length
  • Accept
       2 More than one nick or tear per airfoil but with a cumulative axial length of not more than 0.030 in. (0.76 mm)
  • Accept
       3 Nicks and tears with an axial length more than Para 4.J.(1).(a).2_ but not more than 0.060 in. (1.52 mm) per airfoil
       4 More than Para 4.J.(1).(a).3_
  • Reject
     (b) Cracks:
       1 Radial cracks from the blade tip not more than 0.250 in. (6.35 mm) in length
  • Accept
       2 More than Para 4.J.(1).(b).1_ or axial cracks
  • Reject
     (c) Dents:
       1 Dents not related to cracks, nicks or tears
  • Accept
       2 Dents related to cracks, nicks or tears
  • Reject
   (2) Damage in zone B:
F HP Compressor Blade ** ON A/C NOT FOR ALL
     (a) Nicks and tears:
       1 One nick or tear per airfoil not more than 0.030 in. (0.76 mm) in the axial length
  • Accept
       2 More than one nick or tear per airfoil but with a cumulative axial length of not more than 0.030 in. (0.76 mm)
  • Accept
       3 Nicks and tears with an axial length more than Para 4.J.(2).(a).2_ but not more than 0.060 in. (1.52 mm) per airfoil
       4 More than Para 4.J.(2).(a).3_
  • Reject
     (b) Cracks:
  • Reject
     (c) Dents:
       1 Dents not related to cracks, nicks or tears
  • Accept
       2 Dents related to cracks, nicks or tears
  • Reject
   (3) Damage in zone C:
F HP Compressor Blade ** ON A/C NOT FOR ALL
     (a) Tears:
  • Reject
     (b) Nicks:
       1 Nicks that are 0.005 in. (0.127 mm) or less in depth
  • Accept, without limit to number
       2 More than in Para 4.J.(3).(b).1_ but not more than 0.030 in. (0.762 mm) in depth, located on either the leading edge or the trailing edge. A minimum distance of 0.075 in. (1.905 mm) from the top (Outer Diameter) of the blade platform, measured from the corner that is the closest to the leading edge and the trailing edge, must be kept. Keep out of the fillet area.
       3 More than Para 4.J.(3).(b).2_
  • Reject
     (c) Cracks:
  • Reject
     (d) Dents (not related to cracks, nicks or tears):
       1 Dents that are 0.005 in. (0.127 mm) deep or less
  • Accept, without limit to number
       2 More than in Para 4.J.(3).(d).1_ but not more than 0.030 in. (0.762 mm) in depth, located on either the leading edge or the trailing edge. A minimum distance of 0.075 in. (1.905 mm) from the top (Outer Diameter) of the blade platform, measured from the corner that is the closest to the leading edge and trailing edge, must be kept. Keep out of the fillet area.
       3 More than Para 4.J.(3).(d).2_
  • Reject
   (4) Tip damage and discoloration:
F HP Compressor Blades ** ON A/C NOT FOR ALL
     (a) Discoloration:
       1 Heat discoloration related to blade tip rub
  • Accept
       2 Heat discoloration not related to blade tip rub
  • Reject
     (b) Bend or curl:
       1 The length of the bend or the curl is not more than 5 percent of dimension X and the width of the bend or the curl is not more than 5 percent of dimension Y
  • Accept
       2 More than Para 4.J.(4).(b).1_
  • Reject
       3 Bends or curls related to cracks or tears
  • Reject
     (c) Piece of blade tip missing:
       1 The axial length of the piece is not more than 25 percent of the blade chord and the radial length of the piece is not more than the axial length
  • Accept when the blades of all the stages that follow are examined and acceptable
       2 More than Para 4.J.(4).(c).1_
  • Reject
     (d) Blade tip rub:
       1 Tip rub which agrees with the rotor path wear
  • Accept
       2 Tip rub which does not agree with the rotor path wear
  • Reject
Subtask 72-00-00-220-143-A ** ON A/C NOT FOR ALL
J. Examine the stage 10-12 blades:
   (1) Damage in zone A:
F HP Compressor Blade ** ON A/C NOT FOR ALL
     (a) Nicks and tears:
       1 One nick or tear per airfoil not more than 0.030 in. (0.76 mm) in the axial length
  • Accept
       2 More than one nick or tear per airfoil but with a cumulative axial length of not more than 0.030 in. (0.76 mm)
  • Accept
       3 Nicks and tears with an axial length more than Para 4.J.(1).(a).2_ but not more than 0.050 in. (1.27 mm) per airfoil
       4 More than Para 4.K.(1).(a).3_
  • Reject
     (b) Cracks:
       1 Radial cracks from the blade tip not more than 0.250 in. (6.35 mm) in length
  • Accept
       2 More than Para 4.K.(1).(b).1_ or axial cracks
  • Reject
     (c) Dents:
       1 Dents not related to cracks, nicks or tears
  • Accept
       2 Dents related to cracks, nicks or tears
  • Reject
   (2) Damage in zone B:
F HP Compressor Blade ** ON A/C NOT FOR ALL
     (a) Nicks and tears:
       1 One nick or tear per airfoil not more than 0.030 in. (0.76 mm) in the axial length
  • Accept
       2 More than one nick or tear per airfoil but with a cumulative axial length of not more than 0.030 in. (0.76 mm)
  • Accept
       3 Nicks and tears with an axial length more than Para 4.K.(2).(a).2_ but not more than 0.050 in. (1.27 mm) per airfoil
       4 More than Para 4.K.(2).(a).3_
  • Reject
     (b) Cracks:
  • Reject
     (c) Dents:
       1 Dents not related to cracks, nicks or tears
  • Accept
       2 Dents related to cracks, nicks or tears
  • Reject
   (3) Damage in zone C:
F HP Compressor Blade ** ON A/C NOT FOR ALL
     (a) Tears:
  • Reject
     (b) Cracks:
  • Reject
     (c) Nicks:
       1 Nicks that are 0.005 in. (0.127 mm) or less in depth
  • Accept, without limit to number
       2 Stage 10 blades: More than in Para 4.K.(3).(c).1_ but not more than 0.018 in. (0.457 mm) in depth
  • Accept as long as the following criteria are met:
         a A single nick per blade in zone C, located on the leading edge or contained in less than 0.040 in. (1.016 mm) from the leading edge.
F Typical Leading Edge Nicks and Dents in Zone C (For Stage 8 and 10 Rotor Blades only) ** ON A/C NOT FOR ALL
         b Not more than three nicks per stage.
NOTE: Alternative option to perform the repair prior to the next flight, (Ref. AMM TASK 72-00-00-300-802) for damage that meets criteria of Para 4.K.(3).(c).2_.
       3 Stage 10 blades: More than in Para 4.K.(3).(c).2_ but not more than 0.030 in. (0.762 mm) in depth, located on the leading edge. A minimum distance of 0.075 in. (1.905 mm) from the top (Outer Diameter) of the blade platform, measured from the corner that is the closest to the leading edge, must be kept. Keep out of the fillet area.
       4 Stage 11 blades: More than in Para 4.K.(3).(c).1_ but not more than 0.030 in. (0.762 mm) in depth, located on the trailing edge. A minimum distance of 0.077 in. (1.956 mm) from the top (Outer Diameter) of the blade platform, measured from the corner that is the closest to the trailing edge, must be kept. Keep out of the fillet area.
       5 Stage 12 blades: More than in Para 4.K.(3).(c).1_ but not more than 0.030 in. (0.762 mm) in depth, located on the leading edge. A minimum distance of 0.075 in. (1.905 mm) from the top (Outer Diameter) of the blade platform, measured from the corner that is the closest to the leading edge, must be kept. Keep out of the fillet area.
       6 Other than Para 4.K.(3).(c).3_ or Para 4.K.(3).(c).4_ or Para 4.K.(3).(c).5_
  • Reject
     (d) Dents (not related to cracks, nicks or tears):
       1 Dents that are 0.005 in. (0.127 mm) or less in depth
  • Accept, without limit to number
       2 Stage 10 blades: More than in Para 4.K.(3).(d).1_ but not more than 0.018 in. (0.457 mm) in depth
  • Accept as long as the following criteria are met:
         a A single dent per blade in zone C, located on the leading edge or contained in less than 0.040 in. (1.016 mm) from the leading edge.
         b Not more than three dents per stage.
NOTE: Alternative option to perform the repair prior to the next flight, (Ref. AMM TASK 72-00-00-300-802) for damage that meets criteria of Para 4.K.(3).(d).2_
       3 Stage 10 blades: More than in Para 4.K.(3).(d).2_ but not more than 0.030 in. (0.762 mm) in depth, located on the leading edge. A minimum distance of 0.075 in. (1.905 mm) from the top (Outer Diameter) of the blade platform, measured from the corner that is the closest to the leading edge, must be kept. Keep out of the fillet area.
       4 Stage 11 blades: More than in Para 4.K.(3).(d).1_ but not more than 0.030 in. (0.762 mm) in depth, located on the trailing edge. A minimum distance of 0.077 in. (1.956 mm) from the top (Outer Diameter) of the blade platform, measured from the corner that is the closest to the trailing edge, must be kept. Keep out of the fillet area.
       5 Stage 12 blades: More than in Para 4.K.(3).(d).1_ but not more than 0.030 in. (0.762 mm) in depth, located on the leading edge. A minimum distance of 0.075 in. (1.905 mm) from the top (Outer Diameter) of the blade platform, measured from the corner that is the closest to the leading edge, must be kept. Keep out of the fillet area.
       6 Other than Para 4.K.(3).(d).3_ or Para 4.K.(3).(d).4_ or Para 4.K.(3).(d).5_
  • Reject
     (e) Stage 12 rotor locking blade platforms:
       1 Cracks in the blade platform
  • Accept
       2 Piece of platform missing
  • Accept, if the blades of stage 12 and other downstream hardware are acceptable
       3 More than Para 4.K.(3).(d).2_
  • Reject
   (4) Tip damage and discoloration:
F HP Compressor Blades ** ON A/C NOT FOR ALL
     (a) Discoloration:
       1 Heat discoloration related to blade tip rub
  • Accept
       2 Heat discoloration not related to blade tip rub
  • Reject
     (b) Bend or curl:
       1 The length of the bend or the curl is not more than 5 percent of dimension X and the width of the bend or the curl is not more than 5 percent of dimension Y
  • Accept
       2 More than Para 4.K.(4).(b).1_
  • Reject
       3 Bends or curls related to cracks or tears
  • Reject
     (c) Piece of blade tip missing:
       1 The axial length of the piece is not more than 25 percent of the blade chord and the radial length of the piece is not more than the axial length
  • Accept when the blades of all the stages that follow are examined and acceptable
       2 More than Para 4.K.(4).(c).1_
  • Reject
     (d) Blade tip rub:
       1 Tip rub which agrees with the rotor path wear
  • Accept
       2 Tip rub which does not agree with the rotor path wear
  • Reject
Subtask 72-00-00-220-145-A ** ON A/C NOT FOR ALL
K. Stator Path Liner
F Stage 6 to 11 Stator Path Liner Loss Inspection ** ON A/C NOT FOR ALL
NOTE: The stator path detachment is calculated as an average percentage loss across the circumference.
NOTE: In the inspection that follows, each stator path equals 100 percent.

PRE SBE 72-0273

   (1) Stator path Liner Detachment.
     (a) Stage 6.
       1 Not more than 40 percent of the ceramic coating and not more than 25 percent of the bond coating missing:
  • Accept.
       2 More than Para 4.L.(1).(a).1_ but with no vibration level increase:
  • Reject in less than 10 flight cycles.
       3 More than Para 4.L.(1).(a).1_ and with vibration level increase:
  • Reject.
     (b) Stage 7
       1 Not more than 40 percent of the ceramic coating and not more than 25 percent of the bond coating missing:
  • Accept.
       2 More than Para 4.L.(1).(b).1_ but to a maximum of 100 percent of the ceramic coating and not more than 25 percent of the bond coating missing, provided the criteria at Para 4.L.(1).(d).1_ apply and there is no vibration level increase:
  • Accept.
       3 More than Para 4.L.(1).(b).2_ but with no vibration level increase:
  • Reject in less than 10 flight cycles.
       4 More than Para 4.L.(1).(b).2_ and with vibration level increase:
  • Reject.
     (c) Stage 8
       1 Not more than 40 percent of the ceramic coating and not more than 25 percent of the bond coating missing:
  • Accept.
       2 More than Para L.(1).(c).1_ but with no vibration level increase:
  • Reject in less than 10 flight cycles.
       3 More than Para L.(1).(c).1_ and with vibration level increase:
  • Reject
     (d) Stages 9 to 11 cumulative
       1 Not more than 140 percent of the ceramic coating cumulative and not more than 25 percent of the bond coating per stage missing:
  • Accept.
       2 More than Para 4.L.(1).(d).1_ but not more than 200 percent of the ceramic coating cumulative and not more than 25 percent of the bond coating per stage missing, provided the reference criteria at Para 4.L.(1).(b).1_ are met:
  • Accept.
       3 More than Para 4.L.(1).(d).2_ but with no vibration level increase:
  • Reject in less than 10 flight cycles.
       4 More than Para 4.L.(1).(d).2_ and with vibration level increase:
  • Reject
     (e) Stages 6 to 11 cumulative
       1 Not more than 240 percent of the ceramic coating cumulative and not more than 25 percent of the bond coating per stage missing:
  • Accept.
       2 More than Para 4.L.(1).(e).1_ but with no vibration level increase:
  • Reject in less than 10 flight cycles.
       3 More than Para 4.L.(1).(e).1_ and with vibration level increase:
  • Reject.

    END of PRE SBE 72-0273

    POST SBE 72-0273

   (2) Stator Path Liner Detachment
     (a) Stages 6
       1 Not more than 40 percent of the ceramic coating and not more than 25 percent of the bond coating missing:
  • Accept.
       2 More than Para 4.L.(2).(a).1_ but with no vibration level increase:
  • Reject in less than 10 flight cycles.
       3 More than Para 4.L.(2).(a).1_ and with vibration level increase:
  • Reject.
     (b) Stages 7
       1 Not more than 40 percent of the ceramic coating and not more than 25 percent of the bond coating missing:
  • Accept.
       2 More than Para 4.L.(2).(b).1_ but to a maximum of 100 percent of the ceramic coating and not more than 25 percent of the bond coating missing, provided the criteria at Para 4.L.(2).(d).1_ apply and there is no vibration level increase:
  • Accept.
       3 More than Para 4.L.(2).(b).2_ but with no vibration level increase:
  • Reject in less than 10 flight cycles.
       4 More than Para 4.L.(2).(b).2_ and with vibration level increase:
  • Reject.
     (c) Stage 8
       1 Not more than 40 percent of the ceramic coating and not more than 25 percent of the bond coating missing:
  • Accept.
       2 More than Para 4.L.(2).(c).1_ but with no vibration level increase:
  • Reject in less than 10 flight cycles.
       3 More than Para 4.L.(2).(c).1_ and with vibration level increase:
  • Reject.
     (d) Stages 6 to 11 cumulative
       1 Not more than 340 percent of the ceramic coating cumulative and not more than 25 percent of the bond coating per stage missing:
  • Accept.
       2 More than Para 4.L.(2).(d).1_ but with no vibration level increase:
  • Reject in less than 10 flight cycles.
       3 More than Para 4.L.(2).(d).1_ and with vibration level increase:
  • Reject.

    END of POST SBE 72-0273

Subtask 72-00-00-220-165-A ** ON A/C NOT FOR ALL
L. Inspection of the HP compressor Stage 6 Rotor Path Coating
F Stage 6 Rotor Path Lining ** ON A/C NOT FOR ALL
   (1) Rotor path detachment
NOTE: The minimum view of the inspection area is specified by rotor path lining segment 3 and 4.
     (a) Not more than ten percent liner loss
  • Accept
     (b) More than Para 4.M.(1).(a) but not more than 40 percent liner coating detachment
  • Accept and do the inspection again at intervals of 750 flight cycles
     (c) More than Para 4.M.(1).(b)
  • Reject in less than 50 flight cycles
Subtask 72-00-00-220-169-A ** ON A/C NOT FOR ALL
M. Stages 6,7 and 8 Front and Rear Damper Wires
F Stage 6, 7 and 8 Front and Rear Damper Wires ** ON A/C NOT FOR ALL
NOTE: The limits below are applicable for each individual stage 6, 7 and 8 front or rear damper wires.
   (1) Wear of individual damper wire
     (a) Damper wire visible between the blade platform and the wire slot wall, if it does not extend out into the gas path and is not released
  • Accept and do the inspection again at intervals of 150 flight cycles
     (b) Damper wire extending out not more than 0.800 in. (20.32 mm) into the gas path
  • Accept and do the inspection again at intervals of 50 flight cycles
     (c) Damper wire extending out more than Para 4.N.(1).(b) or an individual damper wire which is released into gas path
  • Reject in less than 10 flight cycles
5. Close-up
Subtask 72-00-00-080-057-A ** ON A/C NOT FOR ALL
A. Remove the support equipment
   (1) Remove the borescope probe from the engine.
   (2) Remove the tool used to turn the HP system (Ref. AMM TASK 72-00-00-080-010).
Subtask 72-00-00-410-102-A ** ON A/C NOT FOR ALL
B. Install the borescope access port covers
F HP Compressor Borescope Access Ports (Underside) ** ON A/C NOT FOR ALL
   (1) Access ports A and B
F Stage 3 Borescope Access Port ** ON A/C NOT FOR ALL
     (a) Apply a thin layer of jointing compound (Material No.V04-004) to the mating faces of the access ports and the access port covers using a BRUSH - BRISTLED, STIFF. Do not apply jointing compound nearer than 0.12 to 0.16 in. (3 to 4 mm) to the access port.
     (b) Let the jointing compound dry for at least 10 minutes.
     (c) Apply anti-seize compound (Material No.V10-070) or anti-seize compound (Material No.V10-072) to the screws which attach the access port cover.
     (d) Install the access port cover and attach with the bolts.
     (e) TORQUE the bolts to between 105 and 85 lbf.in (1.19 and 0.96 m.daN ) T (Ref. AMM TASK 70-23-11-911-013).
     (f) After at least two minutes, TORQUE the bolts again to between 105 and 85 lbf.in (1.19 and 0.96 m.daN ) T (Ref. AMM TASK 70-23-11-911-013).
     (g) Remove unwanted jointing compound from around the access port.
   (2) Access port C
F Stage 5 Borescope Access Port ** ON A/C NOT FOR ALL
     (a) Apply a thin layer of jointing compound (Material No.V04-004) to the mating faces of the access port and access port cover using a stiff bristle brush. Do not apply jointing compound nearer than 0.12 to 0.16 in. (2 to 4 mm) to the access port.
     (b) Let the jointing compound dry for at least 10 minutes.
     (c) Apply anti-seize compound (Material No.V10-070) or anti-seize compound (Material No.V10-072) to the screws which attach the access port cover.
     (d) Install the access port cover (5) and attach with the screws (4).
     (e) TORQUE the screws with ACR Torq-Set bit (212-1/4-ACR) to between 105 and 85 lbf.in (1.19 and 0.96 m.daN ) T (Ref. AMM TASK 70-23-11-911-013).
     (f) After at least two minutes, TORQUE the bolts again to between 105 and 85 lbf.in (1.19 and 0.96 m.daN ) T (Ref. AMM TASK 70-23-11-911-013).
     (g) Remove unwanted jointing compound from around the access port.
     (h) Install the levers:
CAUTION: MAKE SURE THAT THE VSV LEVERS ARE CORRECTLY INSTALLED. DAMAGE CAN OCCUR TO THE HP COMPRESSOR BLADES IF THE LEVERS ARE NOT INSTALLED CORRECTLY.
       1 Install the two levers (2) with their applicable adjusting spacers (3) and the nuts (1).
       2 TORQUE the nuts (1) to between 105 and 85 lbf.in (1.19 and 0.96 m.daN ) T (Ref. AMM TASK 70-23-11-911-013).
   (3) Access ports D, E, F and G
CAUTION: WHEN YOU INSTALL THE ACCESS PORT COVERS, MAKE SURE THAT THE PLUG ORIENTATION IS CORRECT, SPECIALLY AT PORT F. IF YOU DO NOT INSTALL THE ACCESS PORT COVERS CORRECTLY, THE PLUGS CAN BECOME BENT AND/OR THE HPC CASE DAMAGED.
     (a) Apply anti-seize compound (Material No.V10-070) or anti-seize compound (Material No.V10-072) to the screws which attach the access port cover.
     (b) Install the access port cover with the new AIPC 72-41-23-80-060 GASKET (1) and the new AIPC 72-41-00-80-030 GASKET (2) and attach with the bolts.
     (c) TORQUE the bolts to between 105 and 85 lbf.in (1.19 and 0.96 m.daN ) T (Ref. AMM TASK 70-23-11-911-013).
Subtask 72-00-00-410-104-A ** ON A/C NOT FOR ALL
C. Install the Stage 10 to HP Turbine Air Valve
   (1) Install the Stage 10 to HP turbine air valve (Ref. AMM TASK 75-23-51-400-010).
Subtask 72-00-00-410-103-A ** ON A/C NOT FOR ALL
D. 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 72-00-00-440-079-A ** ON A/C NOT FOR ALL
E. Activate the thrust reverser HCU (Ref. AMM TASK 78-30-00-440-012).
Subtask 72-00-00-410-109-A ** ON A/C NOT FOR ALL
F. 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 02:44:07 UTC
"Aviabrain" 2025