Inspection of the LP Compressor [IAE]

TASK 72-00-00-200-017-B
Inspection of the LP Compressor

WARNING: BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.

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

1. Reason for the Job
This task gives the procedure for the inspection of the stage 1.5 thru 2.5 Low Pressure (LP) compressor blades. A description of the 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	ACCESS PLATFORM 1M(3 FT)
No specific	AR	MAT - WORK
No specific	AR	WARNING NOTICE(S)
No specific	Torque wrench: range to between 111 and 102 lbf.in (1.25 and 1.15 m.daN )
IAE2J12030	1	GUIDE-TUBE
IAE6F10408	1	EQUIPMENT-BORESCOPE

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.V06-069)	marker

C. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
FOR [1000EM1] (ENGINE-1)
437AL, 438AR, 452AR
FOR [1000EM2] (ENGINE-2)
447AL, 448AR, 462AR

D. Expendable Parts

FIG.ITEM	DESIGNATION	IPC-CSN
1	KEY WASHER	AIPC 72-32-83-80-020

E. Referenced Information

REFERENCE	DESIGNATION
TASK 70-23-11-911-013-A	General Torque Tightening Techniques
TASK 70-40-11-911-014-A	Locking Devices General Information
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 72-00-00-300-020-A	Repair the Damage on the LP Compressor Stage 1.5 Blades - VRS1130
TASK 72-31-11-000-010-B	Removal of the LP Compressor Fan Blades
TASK 72-31-11-400-010-C	Installation of the LP Compressor Fan Blades
TASK 72-32-88-000-010-B	Removal of the Fan Exit Guide Vanes (FEGVs)
TASK 72-32-88-400-010-B	Installation of the Fan Exit Guide Vanes (FEGVs)
TASK 72-38-11-000-010-A	Removal of the Inlet Cone
TASK 72-38-11-400-010-A	Installation of the Inlet Cone
TASK 78-30-00-040-012-A	Deactivation of the Thrust Reverser Hydraulic Control Unit (HCU) for Ground Maintenance
TASK 78-30-00-440-012-A	Re-activation of the Thrust Reverser Hydraulic Control Unit (HCU) after Ground Maintenance
TASK 78-32-00-010-010-A	Opening of the Thrust Reverser Halves
TASK 78-32-00-410-010-A	Closing of the Thrust Reverser Halves
Borescope Inspection Equipment
LP Compressor Stage 1.5 Blades
LP Compressor Stage 1.5 Blades - Maximum Serviceable Limits
FEGV Location and Key Washer
LP Compressor Stage 2.0 and 2.3 Blades - Maximum Serviceable Limits
LP Compressor Stage 2.0 Blades - Maximum Serviceable Limits
LP Compressor Stage 2.3 Blades - Maximum Serviceable Limits
LP Compressor Stage 2.5 Blades
LP Compressor Stage 2.5 Blades - Maximum Serviceable Limits

3. Job Set-up
Subtask 72-00-00-941-093-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 72-00-00-010-121-A ** ON A/C NOT FOR ALL

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
(4) Put the ACCESS PLATFORM 1M(3 FT) in position to gain access to the air intake cowl.

Subtask 72-00-00-040-079-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 72-00-00-010-128-A ** ON A/C NOT FOR ALL

D. Open the right thrust reverser half (Ref. AMM TASK 78-32-00-010-010):
(1) FOR [1000EM1] (ENGINE-1)
452AR
(2) FOR [1000EM2] (ENGINE-2)
462AR

Subtask 72-00-00-480-066-A ** ON A/C NOT FOR ALL

E. Prepare the support equipment
(1) Prepare the IAE6F10408 EQUIPMENT-BORESCOPE for use as given in the makers instructions.

Borescope Inspection Equipment ** ON A/C NOT FOR ALL

(2) Put the MAT - WORK in the air intake cowl.

4. Procedure
Subtask 72-00-00-480-067-A ** ON A/C NOT FOR ALL

A. Put the IAE2J12030 GUIDE-TUBE and borescope probe in position to examine the stage 1.5 LP compressor blades

CAUTION: BE CAREFUL DURING INSTALLATION AND REMOVAL OF THE GUIDE TUBE NOT TO CAUSE DAMAGE TO THE OUTER OR INNER OUTLET GUIDE VANES.

(1) Put the IAE2J12030 GUIDE-TUBE in position through the fan frame strut, LP compressor Fan Exit Guide Vanes (FEGV) and the LP compressor inlet guide vane at approximately the 3 o'clock position.

LP Compressor Stage 1.5 Blades ** ON A/C NOT FOR ALL

(2) Put the borescope probe in to the guide tube until the stage 1.5 compressor blades can be examined.

LP Compressor Stage 1.5 Blades - Maximum Serviceable Limits ** ON A/C NOT FOR ALL

Subtask 72-00-00-290-079-A ** ON A/C NOT FOR ALL

B. Examine the stage 1.5 LP compressor blades

NOTE: Do this operation with two persons:
One person in the air intake cowl to adjust the position of the guide tube and to turn the stage 1 fan blades.
The other person at the right side of the engine to examine the compressor blades.

(1) Make a mark on a fan blade and the adjacent fan case using marker (Material No.V06-069) to identify the start position of the inspection.
(a) As an alternative to the marker (Material No.V06-069) , it is permitted to use a marker that is specified in IAE V2500 Standard Practices Manual (SPP-V2500-1IA) 70-09-01-400-501 - Procedure To Make Temporary Marks On Components And Assemblies.
(2) Examine the surface of each stage 1.5 LP compressor blade for:
(a) Cracks
(b) Tears.
(c) Nicks and scratches.
(d) Dents.
(e) Blade tip damage, bends and curls.

Subtask 72-00-00-220-108-A ** ON A/C NOT FOR ALL

C. Damage in Zone A

LP Compressor Stage 1.5 Blades - Maximum Serviceable Limits ** ON A/C NOT FOR ALL

(1) Leading edge
(a) Dents, nicks and scratches
1 If they have damages which have no raised metal, up to 0.0078 in. (0,20 mm) in depth, accept them.
2 If they have damages which have no raised metal, up to 0.015 in. (0,40 mm) in depth, accept them with inspection at intervals of 50 flight hours or 25 flight cycles, or repair them per VRS1130 (Ref. AMM TASK 72-00-00-300-020) within 50 flight hours or 25 flight cycles.

NOTE: If they are repaired, no repeat inspection is needed.

3 If they have damages beyond limits in the step C.(1).(A).2_ and within the repair limits of VRS1130, repair them per VRS1130 (Ref. AMM TASK 72-00-00-300-020) within 50 flight hours or 25 flight cycles.
4 If they have damages beyond the repair limits of VRS1130 (Ref. AMM TASK 72-00-00-300-020), reject them.
(b) Cracks or tears
1 If they have cracks or tears, reject them.
(2) Trailing edge and other surfaces
(a) Dents, nicks and scratches
1 If they have damages up to 0.0078 in. (0,20 mm) in depth, accept them.
2 If they have damages beyond limits in the step C.(2).(a).1_, reject them.
(b) Cracks or tears
1 If they have cracks or tears, reject them.

Subtask 72-00-00-220-119-A ** ON A/C NOT FOR ALL

D. Damage in Zone B

LP Compressor Stage 1.5 Blades - Maximum Serviceable Limits ** ON A/C NOT FOR ALL

(1) Leading edge
(a) Dents, nicks and scratches
1 If they have damages up to 0.031 in. (0,79 mm) in depth, accept them.
2 If they have damages up to 0.045 in. (1.14 mm) in depth, accept them with inspection at intervals of 50 flight hours or 25 flight cycles, or repair them per VRS1130 (Ref. AMM TASK 72-00-00-300-020) within 50 flight hours or 25 flight cycles.

NOTE: If they are repaired, no repeat inspection is needed.

3 If they have damages beyond limits in the step D.(1).(a).2_ and within the repair limits of VRS1130, repair them per VRS1130 (Ref. AMM TASK 72-00-00-300-020) within 10 flight hours or 5 flight cycles.
4 If they have damages beyond the repair limits of VRS1130 (Ref. AMM TASK 72-00-00-300-020), reject them.
(b) Cracks or tears
1 If they have cracks or tears, reject them.
(2) Trailing edge
(a) Dents, nicks and scratches
1 If they have damages up to 0.031 in. (0,79 mm) in depth, accept them.
2 If they have damages up to 0.045 in. (1,14 mm) in depth, accept them with inspection at intervals of 50 flight hours or 25 flight cycles.
3 If they have damages beyond limits in the step D.(2).(a).2_, reject them.
(b) Cracks or tears
1 If they have cracks or tears, reject them.
(3) Other surfaces
(a) Dents, nicks and scratches
1 If they have damages up to 0.007 in. (0,17 mm) in depth, accept them.
2 If they have damages beyond limits in the step D.(3).(a).1_, reject them.
(b) Cracks or tears
1 If they have cracks or tears, reject them.

Subtask 72-00-00-220-120-A ** ON A/C NOT FOR ALL

E. Damage in Zone C

LP Compressor Stage 1.5 Blades - Maximum Serviceable Limits ** ON A/C NOT FOR ALL

(1) Leading edge
(a) Dents, nicks and scratches
1 If they have damages up to 0.051 in. (1,30 mm) in depth accept them.
2 If they have damages up to 0.075 in. (1,91 mm) in depth, accept them with inspection at intervals of 50 flight hours or 25 flight cycles, or repair them per VRS1130 (Ref. AMM TASK 72-00-00-300-020) within 50 flight hours or 25 flight cycles.

NOTE: If they are repaired, no repeat inspection is needed.

3 If they have damages beyond limits in the step E.(1).(a).2_ and within the repair limits of VRS1130, repair them per VRS1130 (Ref. AMM TASK 72-00-00-300-020) within 10 flight hours or 5 flight cycles.
4 If they have damages beyond the repair limits of VRS1130 (Ref. AMM TASK 72-00-00-300-020), reject them.
(b) Tip bend or curl
1 If they have tip bend or curl which is not related to cracks or tears and less than 10 percent of the chord length, accept them.
2 If they have tip bend or curl which is not related to cracks or tears and less than 15 percent of the chord length, accept them with inspection at intervals of 50 flight hours or 25 flight cycles, or repair them per VRS1130 (Ref. AMM TASK 72-00-00-300-020) within 50 flight hours or 25 flight cycles under the following conditions:

Up to 13 blades to be repaired.

NOTE: If they are repaired, no repeat inspection is needed.

3 If they have tip bend or curl beyond limits in the step E.(1).(b).2_ reject them.
(c) Missing tip corner
1 If they have missing tip corner which is without sharp corners, less than 0.079 in. (2,00 mm) in axial length and 0.079 in. (2,00 mm) in radial length, accept them.
2 If they have missing tip corner beyond limits in the step E.(1).(c).1_ and within the repair limits of VRS1130, repair them per VRS1130 (Ref. AMM TASK 72-00-00-300-020) within 50 flight hours or 25 flight cycles under the following conditions:

Loose piece due to crack or tear is removed.
Do repeat inspection at intervals of 10 flight hours or 5 flight cycles.
Up to 13 blades to be repaired.

3 If they have missing tip corner beyond the repair limits of VRS1130, reject them.
(d) Cracks or tears
1 If they have cracks or tears on the tip corner, repair them per VRS1130 (Ref. AMM TASK 72-00-00-300-020) within 10 flight hours or 5 flight cycles under the following conditions:

Loose piece due to crack or tear is removed.
Up to 13 blades to be repaired.

2 If they have cracks or tears on other surfaces, reject them.
(2) Trailing edge
(a) Dents, nicks and scratches
1 If they have damages up to 0.051 in. (1,30 mm) in depth, accept them.
2 If they have damages up to 0.075 in. (1,91 mm) in depth, accept them with inspection at intervals of 50 flight hours or 25 flight cycles.
3 If they have damages beyond limits in the step E.(2).(a).2_, reject them.
(b) Tip bend or curl
1 If they have tip bend or curl which is not related to cracks or tears and less than 10 percent of the chord length, accept them.
2 If they have tip bend or curl which is not related to cracks or tears and less than 15 percent of the chord length, accept them with inspection at intervals of 50 flight hours or 25 flight cycles.
3 If they have tip bend or curl beyond limits in the step E.(2).(b).2_, reject them.
(c) Missing tip corner
1 If they have missing tip corner which is without sharp corners, less than 0.079 in. (2,00 mm) in axial length and 0.079 in. (2,00 mm) in radial length, accept them.
2 If they have missing tip corner beyond limits in the step E.(2).(c).1_, reject them.
(d) Cracks or tears
1 If they have cracks or tears, reject them.
(3) Other surfaces
(a) Dents, nicks and scratches
1 If they have damages up to 0.015 in. (0,40mm) in depth, accept them.
2 If they have damages beyond limits in the step E.(3).(a).1_, reject them.
(b) Cracks or tears
1 If they have cracks or tears, reject them.

Subtask 72-00-00-220-170-A ** ON A/C NOT FOR ALL

F. Examine the Abradable Rubber Seal of the LPC Front Case

LP Compressor Stage 1.5 Blades ** ON A/C NOT FOR ALL

(1) Erosion
(a) If the metal surface is not fully exposed from front end to rear end of the seal, accept it.
(b) More than in (a), reject it.

Subtask 72-00-00-080-061-A ** ON A/C NOT FOR ALL

G. Remove the borescope probe and guide tube
(1) Remove the borescope probe from the guide tube.
(2) Remove the guide tube from the fan case.

Subtask 72-00-00-480-068-A ** ON A/C NOT FOR ALL

H. Remove the inlet cone, the fan blades and the fan exit guide vanes to get access to the plug
(1) Remove the inlet cone (Ref. AMM TASK 72-38-11-000-010).
(2) Remove the 22 fan blades (Ref. AMM TASK 72-31-11-000-010).
(3) Remove the fan exit guide vanes (Ref. AMM TASK 72-32-88-000-010).
(a) Remove the two segments at the approximately 5 o'clock position.

FEGV Location and Key Washer ** ON A/C NOT FOR ALL

Subtask 72-00-00-290-080-A ** ON A/C NOT FOR ALL

I. Remove the plug from the LP compressor rear case

FEGV Location and Key Washer ** ON A/C NOT FOR ALL

(1) Bend back and flatten the tab of the key washer.
(2) Remove the plug and the key washer from the LP compressor rear case. Discard the key washer.

Subtask 72-00-00-220-121-A ** ON A/C NOT FOR ALL

J. Put the borescope probe in position to examine the stages 2.0 and 2.3 LP compressor blades
(1) Put the borescope probe in position through the borescope inspection hole at approximately the 5 o'clock position.

LP Compressor Stage 2.0 and 2.3 Blades - Maximum Serviceable Limits ** ON A/C NOT FOR ALL

(2) Put the borescope probe in until the stage 2.0 and 2.3 LP compressor blades can be examined.

LP Compressor Stage 2.0 Blades - Maximum Serviceable Limits ** ON A/C NOT FOR ALL

LP Compressor Stage 2.3 Blades - Maximum Serviceable Limits ** ON A/C NOT FOR ALL

Subtask 72-00-00-220-122-A ** ON A/C NOT FOR ALL

K. Examine the stage 2.0 LP compressor blades

NOTE: Do this operation with two persons:
One person in the air intake cowl to turn the LP rotor.
The other person at the rear of the engine to examine the compressor blades.

(1) Make a mark on a fan blade and the adjacent fan case using marker (Material No.V06-069) to identify the start position of the inspection.
(a) As an alternative to the marker (Material No.V06-069) , it is permitted to use a marker that is specified in IAE V2500 Standard Practices Manual (SPP-V2500-1IA) 70-09-01-400-501 - Procedure To Make Temporary Marks On Components And Assemblies.
(2) Examine the surfaces of each stage 2.0 LP compressor blade for:
(a) Cracks
(b) Tears.
(c) Nicks and scratches.
(d) Dents.
(e) Blade tip damage, bends and curls.

Subtask 72-00-00-220-123-A ** ON A/C NOT FOR ALL

L. Damage in Zone A

LP Compressor Stage 2.0 Blades - Maximum Serviceable Limits ** ON A/C NOT FOR ALL

(1) Accept blades if:
(a) Dents, nicks or scratches on the fillet root are less than 0.002 in. (0.05 mm) in depth.
(2) Accept with an inspection each 25 flight hours or 12 flight cycles if:
(a) Dents on all the surfaces are less than 0.004 in. (0.10 mm) in depth and the diameter or length is less than 0.03 in. (0.76 mm).
(b) Nicks and scratches on all the surfaces are less than 0.004 in. (0.10 mm) in depth and the length is less than 0.03 in. (0.76 mm).
(c) Cracks or tears on all the surfaces are not permitted.
(3) Damage more than (2), reject it.

Subtask 72-00-00-220-124-A ** ON A/C NOT FOR ALL

M. Damage in Zone B

LP Compressor Stage 2.0 Blades - Maximum Serviceable Limits ** ON A/C NOT FOR ALL

(1) Accept blades if:
(a) Dents on the leading or trailing edges are less than 0.031in. (0.79mm) in axial length.
(b) Nicks on the leading or trailing edges are less than 0.031in. (0.79mm) in axial length.
(c) Dents or nicks on the other surfaces are less than 0.007in. (0.17mm) in depth and the length or diameter is less than 0.156in. (3.96mm).
(d) Scratches on the other surfaces are less than 0.007in. (0.17mm) in depth and the length or diameter is less than 0.156in. (3.96mm).
(e) Cracks or tears are not permitted.
(2) Accept with an inspection each 50 flight hours or 25 flight cycles if:
(a) Dents on the leading or trailing edges are less than 0.045in. (1.14mm) in axial length.
(b) Nicks and scratches on the leading or trailing edges are less than 0.045in. (1.14mm) in axial length.
(c) Dents or nicks on the other surfaces are less than 0.007in. (0.17mm) in depth and the length or diameter is less than 0.234in.(5.94mm).
(d) Scratches on the other surfaces are less than 0.007in. (0.17mm) in depth and the length or diameter is less than 0.234in. (5.94mm).
(e) Cracks or tears are not permitted.
(3) Damage more than (2), reject it.

Subtask 72-00-00-220-125-A ** ON A/C NOT FOR ALL

N. Damage in Zone C

LP Compressor Stage 2.0 Blades - Maximum Serviceable Limits ** ON A/C NOT FOR ALL

(1) Accept blade if:
(a) Dents on the leading or trailing edges are less than 0.051in. (1.30mm) in axial length.
(b) Nicks on the leading or trailing edges are less than 0.051in. (1.30mm) in axial length.
(c) Dents or nicks on the other surfaces are less than 0.007in. (0.17mm) in depth and the length or diameter is less than 0.250in. (6.35mm).
(d) Scratches on the other surfaces are less than 0.007in. (0.17mm) in depth and the length or diameter is less than 0.250in. (6.35mm).
(e) Tip bend or curl (not related to cracks or tears) is less than 10 percent of the chord length.
(f) Cracks or tears are not permitted.
(2) Accept with an inspection each 50 flight hours or 25 flight cycles if:
(a) Dents on the leading or trailing edges are less than 0.076in. (1.95mm) in axial length.
(b) Nicks on the leading or trailing edges are less than 0.076in. (1.95mm) in axial length.
(c) Dents or nicks on the other surfaces are less than 0.007in. (0.17mm) in depth and the length or diameter is less than 0.380in. (9.65mm).
(d) Scratches on the other surfaces are less than 0.007in. (0.17mm) in depth and the length or diameter is less than 0.380in. (9.65mm).
(e) Tip bend or curl (not related to cracks or tears) is less than 15 percent of the chord length.
(f) Cracks or tears are not permitted
(3) Damage more than (2), reject it.

Subtask 72-00-00-290-081-A ** ON A/C NOT FOR ALL

O. Examine the stage 2.3 LP compressor blades

NOTE: Do this operation with two persons:
One person in the air intake cowl to turn the LP rotor.
The other person at the right side of the engine to examine the compressor blades.

(1) Examine the surfaces of each stage 2.3 LP compressor blade for:
(a) Cracks.
(b) Tears.
(c) Nicks and scratches.
(d) Dents.
(e) Blade tip damage, bends and curls.

Subtask 72-00-00-220-126-A ** ON A/C NOT FOR ALL

P. Damage in Zone A

LP Compressor Stage 2.3 Blades - Maximum Serviceable Limits ** ON A/C NOT FOR ALL

(1) Accept blades if:
(a) Dents on the leading edge, which must have smoothly rounded bottom and no raised metal, are less than 0.006 in. (0.15 mm) in depth.
(b) Dents on the fillet root except the leading edge are less than 0.002 in. (0.05 mm) in depth.
(c) Nicks or scratches on the fillet root are less than 0.002 in. (0.05 mm) in depth.
(2) Accept with an inspection each 25 flight hours or 12 flight cycles if:
(a) Dents on the leading edge more than (1),(a).
(b) Dents on all the surfaces, except the leading edge are less than 0.004 in. (0.10 mm) in depth and the diameter or length is less than 0.020 in. (0.51 mm).
(c) Nicks and scratches on all the surfaces are less than 0.004 in. (0.10 mm) in depth and the length is less than 0.020 in. (0.51 mm).
(d) Cracks or tears on all the surfaces are not permitted.
(3) Damage more than (2), reject it.

Subtask 72-00-00-220-127-A ** ON A/C NOT FOR ALL

Q. Damage in Zone B

LP Compressor Stage 2.3 Blades - Maximum Serviceable Limits ** ON A/C NOT FOR ALL

(1) Accept blades if:
(a) Dents on the leading or trailing edges are less than 0.031in. (0.79mm) in axial length.
(b) Nicks on the leading or trailing edges are less than 0.031in. (0.79mm) in axial length.
(c) Dents or nicks on the other surfaces are less than 0.007in. (0.17mm) in depth and the length or diameter is less than 0.45in. (1.14mm).
(d) Scratches on the other surfaces are less than 0.007in. (0.17mm) in depth and the length or diameter is less than 0.45in. (1.14mm).
(e) Cracks or tears are not permitted.
(2) Accept with an inspection each 50hours or 25 flights if:
(a) Dents, nicks or scratches on the leading or trailing edges are not more than in step R. (1).
(b) Dents or nicks on the other surfaces are less than 0.007in. (0.17mm) in depth and the length or diameter is less than 0.068in. (1.73mm).
(c) Scratches on the other surfaces are less than 0.007in. (0.17mm) in depth and the length or diameter is less than 0.068in. (1.73mm).
(d) Cracks or tears are not permitted.
(3) Damage more than (2), reject it.

Subtask 72-00-00-220-129-A ** ON A/C NOT FOR ALL

R. Damage in Zone C

LP Compressor Stage 2.3 Blades - Maximum Serviceable Limits ** ON A/C NOT FOR ALL

(1) Accept blades if:
(a) Dents on the leading or trailing edges are less than 0.051in. (1.30mm) in axial length.
(b) Nicks on the leading or trailing edges are less than 0.051in. (1.30mm) in axial length.
(c) Dents or nicks on the other surfaces are less than 0.007in. (0.17mm) in depth and the length or diameter is less than 0.100in. (2.54mm).
(d) Scratches on the other surfaces are less than 0.007in. (0.17mm) in depth and the length or diameter is less than 0.100in. (2.54mm).
(e) Tip bend or curl (not related to cracks or tears) is less than 10 percent of the chord length.
(f) Cracks or tears are not permitted.
(2) Accept with an inspection each 50 flight hours or 25 flight cycles if:
(a) Dents on the leading or trailing edges are less than 0.063in. (1.60mm) in axial length.
(b) Nicks on the leading or trailing edges are less than 0.063in. (1.60mm) in axial length.
(c) Dents or nicks on the other surfaces are less than 0.007in. (0.17mm) in depth and the length or diameter is less than 0.150in. (0.17mm) in depth and the length or diameter is less than 0.150in. (3.81mm).
(d) Scratches on the other surfaces are less than 0.007in. (0.17mm) in depth and the length or diameter is less than 0.150in. (3.81mm).
(e) Tip bend or curl (not related to cracks or tears) is less than 15 percent of the chord length.
(f) Cracks or tears are not permitted.
(3) Damage more than (2), reject it.

Subtask 72-00-00-080-062-A ** ON A/C NOT FOR ALL

S. Remove the borescope probe from the rear case.

Subtask 72-00-00-480-069-A ** ON A/C NOT FOR ALL

T. Put the Borescope Probe in Position to Examine the Stage 2.5 LP Compressor Blades
(1) Put the borescope probe in position through the outlet port of the booster stage bleed valve at approximately the 6 o'clock position

LP Compressor Stage 2.5 Blades ** ON A/C NOT FOR ALL

(2) Put the borescope probe in to the bleed duct until the stage 2.5 LP compressor blades can be examined

LP Compressor Stage 2.5 Blades - Maximum Serviceable Limits ** ON A/C NOT FOR ALL

Subtask 72-00-00-290-082-A ** ON A/C NOT FOR ALL

U. Examine the Stage 2.5 LP Compressor Blades

NOTE: Do this operation with two persons:
One person in the air intake cowl to turn the LP rotor.
The other person at the rear of the engine to examine the compressor blades.

(1) Make a mark on the LP rotor and the adjacent fan case using the marker (Material No.V06-069) to identify the start position of the inspection.
(a) As an alternative to the marker (Material No.V06-069) , it is permitted to use a marker that is specified in IAE V2500 Standard Practices Manual (SPP-V2500-1IA) 70-09-01-400-501 - Procedure To Make Temporary Marks On Components And Assemblies.
(2) Examine the surface of each stage 2.5 LP compressor blade for:
(a) Cracks.
(b) Tears.
(c) Nicks and scratches.
(d) Dents.
(e) Blade tip damage, bends and curls.

Subtask 72-00-00-220-130-A ** ON A/C NOT FOR ALL

V. Damage in Zone A

LP Compressor Stage 2.5 Blades - Maximum Serviceable Limits ** ON A/C NOT FOR ALL

(1) Accept blades if:
(a) Dents, nicks or scratches on the fillet root are less than 0.002 in. (0.05 mm) in depth.
(2) Accept with an inspection each 25 flight hours or 12 flight cycles if:
(a) Dents on all the surfaces are less than 0.004 in. (0.10 mm) in depth and less the diameter or length is less than 0.03 in. (0.76 mm).
(b) Nicks and scratches on all the surfaces are less than 0.004 in. (0.10 mm) in depth and the length is less than 0.03 in. (0.76 mm).
(c) Cracks or tears on all the surfaces are not permitted.
(d) Damage more than (2), reject it.

Subtask 72-00-00-220-131-A ** ON A/C NOT FOR ALL

W. Damage in Zone B

LP Compressor Stage 2.5 Blades - Maximum Serviceable Limits ** ON A/C NOT FOR ALL

Subtask 72-00-00-220-132-A ** ON A/C NOT FOR ALL

X. Damage in Zone C

LP Compressor Stage 2.5 Blades - Maximum Serviceable Limits ** ON A/C NOT FOR ALL

(1) Accept blades if:
(a) Dents on the leading or trailing edges are less than 0.051in. (1.30mm) in axial length.
(b) Nicks on the leading or trailing edges are less than 0.051in. (1.30mm) in axial length.
(c) Dents or nicks on the other surfaces are less than 0.007in. (0.17mm) in depth and the length or diameter is less than 0.250in. (6.35mm).
(d) Scratches on the other surfaces are less than 0.007in. (0.17mm) in depth and the length or diameter is less than 0.250in. (6.35mm)
(e) Tip bend or curl (not related to cracks or tears) is less than 10 percent of the chord length.
(f) Cracks or tears are not permitted.
(2) Accept with an inspection each 50 flight hours or 25 flight cycles if:
(a) Dents on the leading or trailing edges are less than 0.076in. (1.95mm) in axial length.
(b) Nicks on the leading or trailing edges are less than 0.076in. (1.95mm) in axial length.
(c) Dents or nicks on the other surfaces are less than 0.007in. (0.17mm) in depth and the length or diameter is less than 0.380in. (9.65mm).
(d) Scratches on the other surfaces are less than 0.007in. (0.17mm) in depth and the length or diameter is less than 0.380in. (9.65mm).
(e) Tip bend or curl (not related to cracks or tears) is less than 15 percent of the chord length.
(f) Cracks or tears are not permitted.
(3) Damage more than (2), reject it.

Subtask 72-00-00-080-063-A ** ON A/C NOT FOR ALL

Y. Remove the borescope probe from the bleed duct.

Subtask 72-00-00-420-062-A ** ON A/C NOT FOR ALL

Z. Install the Plug in to the Rear Case
(1) Install the plug, with a new AIPC 72-32-83-80-020 KEY WASHER (1), in to the inspection hole for the stage 2.0 and 2.3 LP compressor blades.
(2) TORQUE the plug to between 111 and 102 lbf.in (1.25 and 1.15 m.daN )

(Ref. AMM TASK 70-23-11-911-013).
(3) Safety the plug with the tab of the key washer (Ref. AMM TASK 70-40-11-911-014).
(4) Install the fan exit guide vane segments (Ref. AMM TASK 72-32-88-400-010).
(5) Install the fan blades (Ref. AMM TASK 72-31-11-400-010).
(6) Install the inlet cone (Ref. AMM TASK 72-38-11-400-010).

5. Close-up
Subtask 72-00-00-410-114-A ** ON A/C NOT FOR ALL

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

Subtask 72-00-00-440-065-A ** ON A/C NOT FOR ALL

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

Subtask 72-00-00-410-116-A ** ON A/C NOT FOR ALL

C. 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

Subtask 72-00-00-942-057-A ** ON A/C NOT FOR ALL

D. Remove the support equipment:
(1) Remove the workmat from the air intake cowl.
(2) Remove the access platform(s).
(3) Remove the WARNING NOTICE(S).

[Rev.10 from 2021] 2026.04.01 03:59:20 UTC