Repair Leading Edge Erosion on the LP Compressor Rotor Blades by Material Removal - VRS1065 [IAE]

TASK 72-31-11-300-021-B
Repair Leading Edge Erosion on the LP Compressor Rotor Blades by Material Removal - VRS1065

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

WARNING: BE CAREFUL WHEN YOU DO WORK ON THE ENGINE PARTS AFTER THE ENGINE SHUTDOWN. USE APPLICABLE THERMAL GLOVES. THE ENGINE PARTS CAN STAY HOT FOR ONE HOUR AFTER SHUTDOWN AND CAN BURN YOU.

CAUTION: TITANIUM COMPONENT- YOU MUST USE SILICON CARBIDE TYPE ABRASIVE WHEELS STONES AND PAPERS TO DRESS, BLEND AND POLISH THIS COMPONENT.

CAUTION: TITANIUM COMPONENT - AVOID BUILD UP OF HEAT BY APPLYING ONLY GENTLE PRESSURE AND KEEPING THE TOOL SPEED AS LOW AS POSSIBLE.

CAUTION: TITANIUM COMPONENT - YOU MUST MAKE SURE THAT WHEN YOU REMOVE MATERIAL, BLEND AND POLISH, TO MAKE SMOOTH, THAT NO SPARKS ARE PRODUCED.

CAUTION: TITANIUM COMPONENT- IF THE MATERIAL SHOWS A CHANGE IN COLOR TO DARKER THAN A LIGHT STRAW COLOR, THE COMPONENT IS TO BE REJECTED.

CAUTION: YOU MUST PROTECT THE AIRFOIL SURFACES OF THE BLADE AND THE BEFORE AND AFTER BLADES, WHEN YOU REMOVE EROSION FROM THE LEADING EDGE, AS PARTICLES OF TITANIUM CAN BOND TO THE BLADE AIRFOIL SURFACE.

CAUTION: FOR FAN BLADES THAT ARE INSTALLED ONLY, IF V03-398 METAL SPRAYING STOPPING-OFF COMPOUND IS USED, YOU MUST REMOVE THE STOPPING-OFF COMPOUND WITH THE BLADES IN THE BOTTOM DEAD CENTER POSITION TO PREVENT FOREIGN OBJECTS GOING INTO THE BLADE ROOT.

ZONE: 400

1. Reason for the Job
This task is for the V2500-A5 engines.
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	BRUSH - BRISTLED
No specific	AR	MAT - WORK
No specific	AR	VIBRO ENGRAVER
No specific	AR	WARNING NOTICE(S)
IAE2R19427	1	TEST KIT
IAE3R19320	1	TEMPLATE
IAE3R19469	1	CUTTER PROFILE
IAE3R19574	1	GAUGE PROFILE

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.V02-050)	High temperature glass cloth tape
(Material No.V02-051)	High temperature glass cloth tape
(Material No.V02-052)	High temperature glass cloth tape
(Material No.V02-053)	High temperature glass cloth tape
(Material No.V02-121)	marker pen
(Material No.V03-398)	Metal spray stopping-off compound
(Material No.V05-019)	Waterproof silicon carbide abrasive paper
(Material No.V05-020)	waterproof silicon carbide
(Material No.V05-021)	Waterproof silicon carbide abrasive paper
(Material No.V05-064)	Waterproof silicon carbide abrasive paper
(Material No.14SBA1)	Textile-Lint free Cotton -

C. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
400	POWER PLANT, NACELLES AND PYLONS

D. Referenced Information

REFERENCE	DESIGNATION
TASK 70-11-50-100-802-A	Local Swab or Wipe Cleaning with Solvent
TASK 72-00-00-200-023-B	Eddy Current Inspection of the LP Compressor Fan Blades Leading Edge
TASK 72-31-11-000-010-B	Removal of the LP Compressor Fan Blades
Repair Details and Dimensions - Assemblies A and B
Repair Details and Dimensions - Assembly A
Repair Details and Dimensions

3. Job Set-up
Subtask 72-31-11-941-074-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 1(2).
(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).
(4) Put the ground support equipment in position.
(a) Put the ACCESS PLATFORM 1M(3 FT) in position to give access to the engine.
(b) Put the MAT - WORK in position in the air intake cowl.

NOTE: Make sure that the red warning pennants of the workmat can be seen external to the aircraft.

NOTE: Make sure that the workmat has sufficient dimensions to give full protection to the lower half of the air intake cowl.

4. Procedure
Subtask 72-31-11-869-057-A ** ON A/C NOT FOR ALL

A. General

NOTE: This repair can only be done at a facility that has eddy current test equipment.

NOTE: This repair must only be done when instruction to do so is given in 72-31-11 Inspection/Check.

NOTE: Removal of material may affect the moment weight of the fan blade. The correct moment weight should be measured prior to redistribution using IAE software IAE1J12312. An incorrect moment weight may lead to a false distribution and can result in high vibration.

NOTE: This repair gives the procedure to repair erosion on the leading edge only, of the LP Compressor Rotor Blades, by material removal.

NOTE: This repair may be performed with the fan blade installed or removed. If the fan blades to be repaired are installed, you must ensure that the fan blades are sufficiently secured prior to dressing. If the fan blades are removed, you must follow the procedure given in (Ref. AMM TASK 72-31-11-000-010).

NOTE: Although erosion can be removed by full edge material removal, erosion will be more evident on the top half of the LP compressor rotor blade.

NOTE: This repair gives two alternative methods to remove erosion from the leading edge. Method 1 is using mechanical tools and method 2 is using hand tools only.

NOTE: This repair gives two alternative methods to examine the repaired area(s).

NOTE: If a IAE3R19469 CUTTER PROFILE is being used, you must ensure that it is in a good condition and clean before using it on the fan blade.

NOTE: Fan blades repaired to this scheme, must be glass bead peened, in accordance with VRS1724, at the next shop visit.

NOTE: A log book entry is necessary, when you complete this repair.

Subtask 72-31-11-350-081-A ** ON A/C NOT FOR ALL

B. Method 1: Remove erosion from the LP compressor fan blade leading edge using mechanical tools.

Repair Details and Dimensions - Assemblies A and B ** ON A/C NOT FOR ALL

Repair Details and Dimensions - Assembly A ** ON A/C NOT FOR ALL

Repair Details and Dimensions ** ON A/C NOT FOR ALL

NOTE: Subtask 72-31-11-350-081 and subtask 72-31-11-350-074 are alternatives.

Subtask 72-31-11-390-052-A ** ON A/C NOT FOR ALL

C. Seal the airfoil surface of the LP compressor rotor blade:

(1) Use the Metal spray stopping-off compound (Material No.V03-398) or High temperature glass cloth tape (Material No.V02-050) , High temperature glass cloth tape (Material No.V02-051) , High temperature glass cloth tape (Material No.V02-052) or High temperature glass cloth tape (Material No.V02-053) .
(2) Remove erosion and re-profile the leading edge radius:
(a) The profiling of the leading edge must be done such that excess thickness is removed only from the suction surface of the airfoil and the leading edge radius is re-created/blended smoothly into the original non-eroded fan blade profile. Only the minimum amount of material removal is required to get a satisfactory leading edge profile. Use the portable grinding equipment.

NOTE: Although erosion can be removed by full edge material removal, erosion will be more evident on the top half of the LP compressor fan blade.

(3) Make smooth and polish the repaired area(s):
(a) Use the Waterproof silicon carbide abrasive paper (Material No.V05-021) , waterproof silicon carbide (Material No.V05-020) , Waterproof silicon carbide abrasive paper (Material No.V05-019) and/or Waterproof silicon carbide abrasive paper (Material No.V05-064) .
(b) Make sure that all erosion is completely removed and the area is made smooth into the adjacent material.

NOTE: The last polish is to be in a radial direction.

(4) Make sure that the leading edge profile radius is polished all around the nose. The finished profile must give a full radius or a nose down condition.

Repair Details and Dimensions ** ON A/C NOT FOR ALL

(5) Remove the stopping-off compound or the masking tape.

Subtask 72-31-11-350-074-A ** ON A/C NOT FOR ALL

CAUTION: TITANIUM COMPONENT- YOU MUST USE SILICON CARBIDE TYPE ABRASIVE WHEELS STONES AND PAPERS TO DRESS, BLEND AND POLISH THIS COMPONENT.

D. Method 2: Remove erosion from the LP compressor fan blade using hand tools only.

Repair Details and Dimensions - Assemblies A and B ** ON A/C NOT FOR ALL

Repair Details and Dimensions - Assembly A ** ON A/C NOT FOR ALL

Repair Details and Dimensions ** ON A/C NOT FOR ALL

NOTE: Subtask 72-31-11-350-074 and subtask 72-31-11-350-081 are alternatives.

NOTE: Do not use mechanical tools for this Method 2 procedure.

(1) Remove erosion and re-profile the leading edge radius:
(a) The profiling of the leading edge must be done such that excess thickness is removed only from the suction surface of the airfoil and the leading edge radius is recreated/blended smoothly into the original non-eroded blade profile. Only the minimum amount of material removal is required to get a satisfactory leading edge profile. Use the IAE3R19469 CUTTER PROFILE, 1 off and hand tools only.

NOTE: Although erosion can be removed by full edge material removal, erosion will be more evident on the top half of the LP compressor rotor blade.

(2) Make smooth and polish the repaired area(s):
(a) Use the Waterproof silicon carbide abrasive paper (Material No.V05-021) , waterproof silicon carbide (Material No.V05-020) , Waterproof silicon carbide abrasive paper (Material No.V05-019) and/or Waterproof silicon carbide abrasive paper (Material No.V05-064) . Make sure that all the erosion is completely removed and the area is made smooth into the adjacent material. Polish the repaired area(s) to remove the scratches and to give the same surface finish as that of the adjacent material.

NOTE: The last polish is to be in a radial direction.

(3) Make sure that the leading edge profile radius is polished all around the nose. The finished profile must give a full radius or a nose down condition.

Repair Details and Dimensions ** ON A/C NOT FOR ALL

Subtask 72-31-11-110-062-A ** ON A/C NOT FOR ALL

E. Clean the LP compressor rotor blade airfoil surfaces.

(1) If there is the stopping-off compound, remove it.
(a) Use the Textile-Lint free Cotton - (Material No.14SBA1) or the BRUSH - BRISTLED soaked in clean cold water.
(b) If the fan blades are still installed, make sure that the blades are in the bottom dead center position.
(2) Clean the blade.
(a) If the fan blades are still installed, make sure that the blades are in the bottom dead center position.
(b) Use the chemical cleaning equipment (Ref. AMM TASK 70-11-50-100-802).

Subtask 72-31-11-230-063-A ** ON A/C NOT FOR ALL

F. Do an Eddy Current Crack Test on the repaired area(s).
(1) Do an eddy current Crack Test on the repaired area(s).
(a) Use IAE2R19427 TEST KIT. Cracks are not permitted (Ref. AMM TASK 72-00-00-200-023).
(b) If a crack is found, contact IAE Technical Services immediately.

NOTE: Any such cracked blades must be returned to IAE Technical Services.

Subtask 72-31-11-210-076-A ** ON A/C NOT FOR ALL

G. Method 1: Examine the LP Compressor Fan Blade.

Repair Details and Dimensions - Assemblies A and B ** ON A/C NOT FOR ALL

Repair Details and Dimensions - Assembly A ** ON A/C NOT FOR ALL

Repair Details and Dimensions ** ON A/C NOT FOR ALL

NOTE: This SUBTASK 72-31-11-210-076 and SUBTASK 72-31-11-210-077 are alternatives.

(1) Visually and dimensionally measure the dimensions of the repaired area(s).
(a) Use marker pen (Material No.V02-121) , IAE3R19574 GAUGE PROFILE, 1 off, and standard workshop inspection equipment. Make sure there is a good large radius, with any change in camber to be in a full radius or a nose down condition.

Repair Details and Dimensions ** ON A/C NOT FOR ALL

(b) Measure Dimension BJ.
1 Mark out the section to be measured. Measure dimension BA and BC true down the leading and trailing edge. Make a mark using marker pen (Material No.V02-121) .
2 Use standard workshop inspection equipment. Measure across the fan blade at the points marked.
(c) If the fan blade chordal width is below the minimum dimension BJ, reject it.

Subtask 72-31-11-210-077-A ** ON A/C NOT FOR ALL

H. Method 2: Examine the LP Compressor Fan Blade.

Repair Details and Dimensions - Assemblies A and B ** ON A/C NOT FOR ALL

Repair Details and Dimensions - Assembly A ** ON A/C NOT FOR ALL

Repair Details and Dimensions ** ON A/C NOT FOR ALL

NOTE: This SUBTASK 72-31-11-210-076 and SUBTASK 72-31-11-210-077 are alternatives.

(1) Visually and dimensionally measure the dimensions of the repaired area(s).
(a) Use IAE3R19320 TEMPLATE, 1 off, marker pen (Material No.V02-121) , IAE3R19574 GAUGE PROFILE, 1 off, and standard workshop inspection equipment. Make sure there is a good large radius, with any change in camber to be in a full radius or a nose down condition.

Repair Details and Dimensions ** ON A/C NOT FOR ALL

(b) Measure dimension BJ.
1 Mark out the area to be measured. Use IAE3R19320 TEMPLATE , 1 off and marker pen (Material No.V02-121) . Make a mark through the holes in the template.
2 Use standard workshop inspection equipment. Measure across the fan blade at the points marked.
(c) If the fan blade chordal width is below the minimum dimension BJ, reject it.

Subtask 72-31-11-930-051-A ** ON A/C NOT FOR ALL

I. Identify the repair.

CAUTION: DO NOT VIBRO-ENGRAVE ON THE FAN BLADE AIRFOIL OR CONTACT SURFACES, OR ANY OTHER PARTS, E.G. DOVETAIL PRESSURE SURFACES, DOVETAIL FRONT AND REAR SURFACES.

(1) A log entry is necessary when you have completed this repair. Write VRS1065 in the engine log book.
(2) At the next shop visit, moment weight the LP Compressor Rotor Blade Assembly and make a mark of the moment weight accordance with the Engine Manual.
(3) At the next shop visit make a mark VRS1065 adjacent to the assembly number. Use VIBRO ENGRAVER.
(4) Fan blades repaired to this scheme, must be glass bead peened at the next shop visit, to the instructions specified in VRS1724.

5. Close-up
Subtask 72-31-11-942-071-A ** ON A/C NOT FOR ALL

A. Remove the support equipment
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Remove the workmat from the air intake cowl.
(3) Remove the access platform(s).
(4) Remove the WARNING NOTICE(S).

[Rev.10 from 2021] 2026.04.01 13:01:00 UTC