Repair Damage on the Low Pressure Compressor (LPC) Fan Blades by Local Material Removal - VRS1506 [IAE]

TASK 72-31-11-300-016-A
Repair Damage on the Low Pressure Compressor (LPC) Fan Blades by Local Material Removal - VRS1506

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

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. USE TECHNIQUES WHICH ALLOW FOR PROGRESSIVE WEAR OF THE DRESSING MEDIA TO PRESENT A CONTINUALLY FRESH CUTTING SURFACE TO THE WORK PIECE.

CAUTION: DO NOT DWELL ON ONE AREA OF THE COMPONENT.

CAUTION: DRESS, WHERE POSSIBLE, IN A CIRCULAR MOTION, TAKING LIGHT CUTS TO AVOID OVERHEATING.

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

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

ZONE: 400

1. Reason for the Job
Self explanatory
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	CONTAINER - POLYTHENE, APPLICABLE CAPACITY
No specific	AR	LIGHT SOURCE - WHITE
No specific	AR	MACHINE - GRINDING, PORTABLE
No specific	AR	MAGNIFYING GLASS POWER 10X
No specific	AR	MAT - WORK
No specific	2	TWEEZER
No specific	1	VIBRO ENGRAVER
No specific	AR	WARNING NOTICE(S)
IAE2R19427	1	TEST KIT
IAE3R19016	AR	GAGE PROFILE
IAE3R19017	AR	GAGE PROFILE

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.V01-025)	nitric acid HNO3
(Material No.V01-027)	hydrofluoric acid
(Material No.V01-027A)	hydrofluoric acid
(Material No.V01-030)	sodium carbonate Na2CO3
(Material No.V01-031)	Acetone, Technical grade
(Material No.V01-300)	alkali cleaner
(Material No.V01-339)	alkali cleaner
(Material No.V01-422)	alkali cleaner
(Material No.V02-099)	lint free cloth
(Material No.V02-151)	tape
(Material No.V02-174)	cotton wool swab
(Material No.V05-019)	waterproof silicon carbide abrasive paper
(Material No.V05-020)	waterproof silicon carbide abrasive paper
(Material No.V05-021)	waterproof silicon carbide abrasive paper
(Material No.V05-064)	waterproof silicon carbide abrasive paper
(Material No.V06-022)	fluorescent penetrant
(Material No.V12-002)	polyethylene sheet

C. Work Zones and Access Panels

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

D. Referenced Information

REFERENCE	DESIGNATION
TASK 70-11-50-100-010-A	Remove Grease from the External Surfaces of the Engine
TASK 70-23-05-230-010-A	Local Application of Fluorescent Penetrant Inspection
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
TASK 72-31-11-200-010-B	Inspection of the Low Pressure (LP) Compressor Fan Blades
TASK 72-31-11-400-010-C	Installation of the LP Compressor Fan Blades
EM 723111300025
EM 723111300026
LP Compressor Fan Blades

3. Job Set-up
Subtask 72-31-11-941-065-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).
(4) Put the support equipment in to 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.

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

CAUTION: THE MAXIMUM NUMBER OF DRESSED BLADES FOR A GIVEN LP COMPRESSOR FAN BLADES SET IS THE EQUIVALENT OF THREE BLADES DRESSED TO THE MAXIMUM LIMIT. ALL THE REMAINING BLADES MUST NOT BE DRESSED.

Subtask 72-31-11-020-076-A ** ON A/C NOT FOR ALL

A. Removal of the LP Compressor Fan-Blades
(1) Remove the LP compressor fan-blades, if necessary (Ref. AMM TASK 72-31-11-000-010).

NOTE: The alternative local penetrant crack test or visual magnification inspection X10 techniques are done without a swab-etch. The components that are not inspected for cracks on the leading edge by eddy current inspection must be swab-etch and inspected as specified in the EM 723111300025 (VRS1026) and glass-bead peened after the fly-back limits are achieved, to the instructions specified in the EM 723111300026 (VRS1724).

NOTE:

LP Compressor Fan Blades ** ON A/C NOT FOR ALL

Subtask 72-31-11-110-057-A ** ON A/C NOT FOR ALL

B. Chemical Cleaning of the Blades

NOTE: Make sure that the part is at ambient temperature.

(1) Use the alkali cleaner (Material No.V01-300) , alkali cleaner (Material No.V01-339) or alkali cleaner (Material No.V01-422) and prepare the solution (Ref. AMM TASK 70-11-50-100-010).
(2) Wash the repaired area with a lint free cloth (Material No.V02-099) soaked in the solution.
(3) Use a lint free cloth (Material No.V02-099) soaked in clean cold water until the area is fully clean.
(4) If necessary, repeat Steps (2) and (3).
(5) Wipe the area with a clean dry cloth.

Subtask 72-31-11-380-050-A ** ON A/C NOT FOR ALL

WARNING: ALWAYS KEEP THE ETCHING SOLUTION AWAY FROM YOUR EYES AND BARE SKIN. WEAR PROTECTIVE CLOTHING, WHICH INCLUDES RUBBER GLOVES AND EYE PROTECTION. ALWAYS EXAMINE RUBBER GLOVES FOR PIN HOLES AND REPLACE GLOVES AS NECESSARY.

WARNING: FOR ALL BURNS, TELL THE MEDICAL PERSONNEL WHICH ETCH SOLUTION CAUSED THE BURN, ESPECIALLY WHEN AN HYDROFLUORIC ACID IS A CONSTITUENT.

WARNING: PUT SAFETY PLACARDS IN LOCATIONS WHERE YOU CAN EASILY SEE THEM. IF YOU DO NOT OBEY THIS INSTRUCTION, INJURY TO PERSONNEL CAN OCCUR.

WARNING: PUT THE EYE-WASH BOTTLES AND THE HF JELLY AS NEAR AS POSSIBLE TO THE WORK AREA. IF YOU DO NOT OBEY THIS INSTRUCTION, INJURY TO PERSONNEL CAN OCCUR.

CAUTION: USE THE SOLUTIONS AT AMBIENT TEMPERATURE (BETWEEN 64 AND 73 DEG F (18 TO 23 DEG)) OR, IF YOU USE THEM AT A HIGHER TEMPERATURE, DECREASE THE ETCHING TIME. IF YOU DO NOT OBEY THESE INSTRUCTIONS, DAMAGE TO THE EQUIPMENT CAN OCCUR.

C. Swab-Etch the Damaged Blade(s)

NOTE: If the SWAB-ETCH EQUIPMENT ( cotton wool swab (Material No.V02-174) and the TWEEZER) are not available, go to Step 4.D.

NOTE: This step is done to prepare the following inspection method in Step 4.D. It should not be carried out if the blade is going to be inspected per Step 4.E.

NOTE: This step can be performed only if the blade has been removed from the engine.

(1) Make the hydrofluoric acid (Material No.V01-027) and nitric acid HNO3 (Material No.V01-025) solution:
(a) Use the components that follow:

The nitric acid HNO3 (Material No.V01-025) 27 oz/gal (200g/l)
The hydrofluoric acid (Material No.V01-027) 6.6 oz/gal (50 g/l).

(b) Use the following proportions to make 13.2 USgal (50 l) of the solution (this quantity is given as an example):
1 Put approximately 6.6 USgal (25 l) of water into the CONTAINER - POLYTHENE, APPLICABLE CAPACITY or a suitable material tank of over 13.2 USgal (50 l) capacity.
2 Add slowly and carefully 2.6 USgal (10 l) of the nitric acid HNO3 (Material No.V01-025) (SG 1.42) and stir to mix.
3 Add the necessary amount of the hydrofluoric acid (Material No.V01-027) as follows:
a If the hydrofluoric acid (Material No.V01-027) 30 per cent HF weight/weight is used:

Add slowly and carefully, 2.0 USgal (7.6 l) of the hydrofluoric acid (Material No.V01-027) 30 per cent weight/weight.

b If the hydrofluoric acid (Material No.V01-027A) 40 per cent weight/weight is used:

Add slowly and carefully, 1.45 USgal (5.5 l) of the hydrofluoric acid (Material No.V01-027A) 40 per cent weight/weight.

4 Stir to mix.
5 Add water slowly and carefully, up to the level to make 13.2 USgal (50 l) of the solution.
(2)

LP Compressor Fan Blades ** ON A/C NOT FOR ALL

Use the SWAB-ETCH EQUIPMENT ( cotton wool swab (Material No.V02-174) and the TWEEZER). Use the hydrofluoric acid (Material No.V01-027) and nitric acid HNO3 (Material No.V01-025) solution:

NOTE: Put sufficient acid into the applicable open CONTAINER - POLYTHENE, APPLICABLE CAPACITY. Discard the acid after use and fully clean the container in clean, cold water.

(a) Hold the cotton wool swab (Material No.V02-174) in chemical resistant tongs or tweezers. Dip the cotton wool swab (Material No.V02-174) into the hydrofluoric acid (Material No.V01-027) and nitric acid HNO3 (Material No.V01-025) solution. Push the swab lightly against the container side to remove the unwanted solution.
(b) Swab the necessary area of the part with the cotton wool swab (Material No.V02-174) . Do not permit the solution to go on the other areas. Keep a layer of the solution on the surface for approximately 20 to 30 seconds until you can see a gray surface.
(c) Immediately swab fully the part with clean, cold water.
(d) Neutralize the remaining acid as follows:
1 Swab the surface with a solution of 9.4 oz/gal (70g/l) of sodium carbonate Na2CO3 (Material No.V01-030) in water to neutralize the acid.
2 Rinse the part with clean, cold water.
3 Swab the surface again with a solution of 9.4 oz/gal (70 g/l) of sodium carbonate Na2CO3 (Material No.V01-030) in water.
(e) Immediately swab-wash the part with clean, cold water to remove all the remaining neutralizing solution.
(f) Swab-wash the part with the V01-031Acetone, Technical grade to remove the water, then permit the part to dry.

NOTE: Step 4.C. combined with Step 4.D. is the preferred inspection method to be performed. If Step 4.C. combined with Step 4.D. cannot be performed, then Step 4.E. would be the next alternative. If Step 4.E. cannot be performed, then Step 4.F. would be the next alternative. If Step 4.C. combined with Step 4.D., Step 4.E. or Step 4.F. cannot be performed, it is mandatory to perform Step 4.G.

Subtask 72-31-11-230-066-A ** ON A/C NOT FOR ALL

D. Do a Local Penetrant Crack-Test on the Damaged Blades

NOTE: This step is only to be performed if Step 4.C was performed.

(1)

LP Compressor Fan Blades ** ON A/C NOT FOR ALL

(a) If a blade is cracked, reject it.
(b) If there are no cracked blades, do Step 4.H. or Step 4.J.
(2) If the local penetrant inspection equipment is not available, go to Para 4.E.

NOTE: If you find a crack during the penetrant inspection, inform IAE immediately. You must return cracked blades to IAE for inspection.

Subtask 72-31-11-250-050-A ** ON A/C NOT FOR ALL

E. Do an Eddy Current Crack-Test on the Leading Edge of the Damaged Blades

NOTE: If the eddy current inspection-equipment is not available, go to Step 4.F.

(1)

LP Compressor Fan Blades ** ON A/C NOT FOR ALL

Use the IAE2R19427 TEST KIT (Ref. AMM TASK 72-00-00-200-023):
(a) If a blade is cracked, reject it.
(b) If there are no cracked blades, do Step 4.H. or Step 4.J.
(2) If the eddy current inspection-equipment is not available or the damaged area is not on the leading edge, go to Step 4.F.

NOTE: If you find a crack during the eddy current inspection, inform IAE immediately. You must return cracked blades to IAE for inspection.

Subtask 72-31-11-230-056-A ** ON A/C NOT FOR ALL

F. Do a Local Penetrant Crack-Test on the Damaged Blades

NOTE: If the local penetrant inspection is not performed, go to Step 4.G.

LP Compressor Fan Blades ** ON A/C NOT FOR ALL

(1)

LP Compressor Fan Blades ** ON A/C NOT FOR ALL

(a) If a blade is cracked, reject it.
(b) If there are no cracked blades, do Step 4.H. or Step 4.J.
(2) If the local penetrant inspection equipment is not available, go to Para. 4.G.

NOTE: If you find a crack during the penetrant inspection, inform IAE immediately. You must return cracked blades to IAE for inspection.

Subtask 72-31-11-210-062-A ** ON A/C NOT FOR ALL

G. Visual Inspection - X10-time Magnification
(1) Use the MAGNIFYING GLASS POWER 10X and the LIGHT SOURCE - WHITE to do this inspection:
(a) If a blade is cracked, reject it.
(b) If there are no cracked blades, do Step 4.H. or Step 4.J.

NOTE: If you find a crack during the visual inspection, inform IAE immediately. You must return cracked blades to IAE for inspection.

Subtask 72-31-11-350-064-A ** ON A/C NOT FOR ALL

H. Remove Local Damage on the Leading Edge, Trailing Edge and Airfoil Surface

LP Compressor Fan Blades ** ON A/C NOT FOR ALL

CAUTION: DO NOT USE FORCE WITH MECHANICAL CUTTERS, OR THE MATERIAL WILL BECOME TOO HOT.

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

(1)

LP Compressor Fan Blades ** ON A/C NOT FOR ALL

Use the MACHINE - GRINDING, PORTABLE.

NOTE:

LP Compressor Fan Blades ** ON A/C NOT FOR ALL

(2)

LP Compressor Fan Blades ** ON A/C NOT FOR ALL

(3) Make the repaired area(s) smooth. Make sure that all the damaged marks are completely removed. Use the waterproof silicon carbide abrasive paper (Material No.V05-021) , waterproof silicon carbide abrasive paper (Material No.V05-020) and/or waterproof silicon carbide abrasive paper (Material No.V05-064) .
(4) Polish the repaired area(s) to remove scratches and make the surface finish the same as the adjacent material. The polish marks must be in a radial direction from root to tip. Use waterproof silicon carbide abrasive paper (Material No.V05-021) , waterproof silicon carbide abrasive paper (Material No.V05-020) and/or waterproof silicon carbide abrasive paper (Material No.V05-064) .
(5) Repair the blade leading edge radius. Use the waterproof silicon carbide abrasive paper (Material No.V05-021) , waterproof silicon carbide abrasive paper (Material No.V05-020) , waterproof silicon carbide abrasive paper (Material No.V05-019) , waterproof silicon carbide abrasive paper (Material No.V05-064) and the IAE3R19016 GAGE PROFILE and IAE3R19017 GAGE PROFILE to remove the minimum quantity of material to give the correct radius.
(6) Repair the blade shape from the leading edge radius to the airfoil. Use the waterproof silicon carbide abrasive paper (Material No.V05-021) , waterproof silicon carbide abrasive paper (Material No.V05-020) , waterproof silicon carbide abrasive paper (Material No.V05-019) and/or waterproof silicon carbide abrasive paper (Material No.V05-064) and lightly polish the blade until the shape is correct. The polish marks must be in a radial direction from root to tip of the blade. The surface finish must be the same as that of the adjacent area.

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

Subtask 72-31-11-350-096-A ** ON A/C NOT FOR ALL

I. Remove Local Damage by Tip Cropping and Blending

LP Compressor Fan Blades ** ON A/C NOT FOR ALL

(1) Protect the attrition liner from damage by sealing off the area surrounding the fan blade to be repaired, using a locally-manufactured mask of polyethylene sheet (Material No.V12-002) secured with tape (Material No.V02-151) . To prevent damage to the attrition liner, ensure that the tape (Material No.V02-151) securing the mask is fixed to the fan case but not to the attrition lining.
(2) Cut away material using the MACHINE - GRINDING, PORTABLE until all the damage is removed.
(3) Polish out scores remaining after the MACHINE - GRINDING, PORTABLE was used. Use 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) . the polish marks must be in a radial direction from root to tip of the blade.
(4) Repair the blade leading edge radius. Use 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) , Waterproof silicon carbide abrasive paper (Material No.V05-064) , the IAE3R19016 GAGE PROFILE and the IAE3R19017 GAGE PROFILE to remove the minimum quantity of material to give the correct radius.
(5) Repair the blade shape from the leading edge radius to the airfoil. Use 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) and lightly polish the blade until the shape is correct. The polish marks must be in a radial direction from root to tip of the blade. The surface finish must be the same as that of the adjacent area.
(6) Remove the mask.

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

Subtask 72-31-11-220-052-A ** ON A/C NOT FOR ALL

J. Examine the LP Compressor Fan-Blades

LP Compressor Fan Blades ** ON A/C NOT FOR ALL

(1) Do a visual and dimensional check of the blade. Visually examine and measure the dimensions of the scallop on the leading edge, the trailing edge and the airfoil surface. Make sure that the maximum depth of the repair on the airfoil surfaces is not more than 0.024 in. (0.6096 mm). Make sure that the damage is removed and the surface finish of the dressed area is the same as the adjacent material. Discard the blades if they are not in the limits specified. Use workshop inspection equipment.
(a) If the blade is not in the limits given in (Ref. AMM TASK 72-31-11-200-010), reject it.
(b) If the blade is in the limits given in (Ref. AMM TASK 72-31-11-200-010), go to Step 4.L.

Subtask 72-31-11-380-051-A ** ON A/C NOT FOR ALL

WARNING: FOR ALL BURNS, TELL THE MEDICAL PERSONNEL WHICH ETCH SOLUTION CAUSED THE BURN, ESPECIALLY WHEN AN HYDROFLUORIC ACID IS A CONSTITUENT.

WARNING: PUT SAFETY PLACARDS IN LOCATIONS WHERE YOU CAN EASILY SEE THEM. IF YOU DO NOT OBEY THIS INSTRUCTION, INJURY TO PERSONNEL CAN OCCUR.

WARNING: PUT THE EYE-WASH BOTTLES AND THE HF JELLY AS NEAR AS POSSIBLE TO THE WORK AREA. IF YOU DO NOT OBEY THIS INSTRUCTION, INJURY TO PERSONNEL CAN OCCUR.

K. Swab-Etch the Damaged Blade(s)

NOTE: If the SWAB-ETCH EQUIPMENT ( cotton wool swab (Material No.V02-174) and the TWEEZER) are not available, go to Step 4.N.

NOTE: This step is done to prepare the following inspection method in Step 4.M. It should not be carried out if the blade is going to be inspected per Step 4.N.

NOTE: This step can be performed only if the blade has been removed from the engine.

(1) Make the hydrofluoric acid (Material No.V01-027) and nitric acid HNO3 (Material No.V01-025) solution:
(a) Use the components that follow:

The nitric acid HNO3 (Material No.V01-025) 27 oz/gal (200g/l)
The hydrofluoric acid (Material No.V01-027) 6.6 oz/gal (50 g/l).

Add slowly and carefully, 2.0 USgal (7.6 l) of the hydrofluoric acid (Material No.V01-027) 30 per cent weight/weight.

b If the hydrofluoric acid (Material No.V01-027A) 40 per cent weight/weight is used:

Add slowly and carefully, 1.45 USgal (5.5 l) of the hydrofluoric acid (Material No.V01-027A) 40 per cent weight/weight.

4 Stir to mix.
5 Add water slowly and carefully up to the level to make 13.2 USgal (50 l) of the solution.
(2)

LP Compressor Fan Blades ** ON A/C NOT FOR ALL

Use the SWAB-ETCH EQUIPMENT ( cotton wool swab (Material No.V02-174) and the TWEEZER). Use the hydrofluoric acid (Material No.V01-027) and nitric acid HNO3 (Material No.V01-025) solution:

NOTE: Put sufficient acid into the applicable open CONTAINER - POLYTHENE, APPLICABLE CAPACITY. Discard the acid after use and fully clean the container in clean, cold water.

NOTE: Step 4.L. combined with Step 4.M. is the preferred inspection method to be performed. If Step 4.L. combined with Step 4.M. cannot be performed, then Step 4.N. would be the next alternative. If Step 4.N. cannot be performed, then Step 4.P. would be the next alternative. If Step 4.L. combined with Step 4.M., Step 4.N. or Step 4.P. cannot be performed, it is mandatory to perform Step 4.Q.

Subtask 72-31-11-230-067-A ** ON A/C NOT FOR ALL

L. Do a Local Penetrant Crack-Test on the Repaired Blades

NOTE: This step is only to be performed if Step 4.L. was performed.

(1) Use the fluorescent penetrant (Material No.V06-022) and do a penetrant inspection of the repaired area (Ref. AMM TASK 70-23-05-230-010).
Cracks are not permitted:
(a) If a blade is cracked, reject it.
(b) If the blade is not cracked, inspect as per (Ref. AMM TASK 72-31-11-200-010).
(c) If the blade is within the limits given in (Ref. AMM TASK 72-31-11-200-010), go to Step 4.R.

Subtask 72-31-11-250-051-A ** ON A/C NOT FOR ALL

M. Do an Eddy Current Crack-Test on the Leading Edge of the Repaired Blades

NOTE: If the eddy current inspection-equipment is not available, go to Step 4.P.

LP Compressor Fan Blades ** ON A/C NOT FOR ALL

(1)

LP Compressor Fan Blades ** ON A/C NOT FOR ALL

(a) If the blade is cracked, reject it.
(b) If the blade is not cracked, inspect it as per (Ref. AMM TASK 72-31-11-200-010).
(c) If the blade is within the limits given in (Ref. AMM TASK 72-31-11-200-010), proceed to Step 4.R.

NOTE: If you find a crack during the eddy current inspection, inform IAE immediately. You must return the cracked blades to IAE for inspection and the fly-back limits given in Step 4.N. and Step 4.P. can no longer be applied to those blades.

Subtask 72-31-11-230-057-A ** ON A/C NOT FOR ALL

N. Do a Local Penetrant Crack-Test on the Repaired Blades

NOTE: If the local penetrant inspection is not performed, go to Step 4.Q.

(1) Use the fluorescent penetrant (Material No.V06-022) and do a penetrant inspection of the repaired area (Ref. AMM TASK 70-23-05-230-010).
Cracks are not permitted:
(a) If the blade is cracked, reject it.
(b) If the blade is not cracked, inspect as per (Ref. AMM TASK 72-31-11-200-010).
(c) If the blade is within the limits given in (Ref. AMM TASK 72-31-11-200-010), go to Step 4.R.

NOTE: If you find a crack during the penetrant inspection, inform IAE immediately. You must return cracked blades to IAE for inspection.

Subtask 72-31-11-210-073-A ** ON A/C NOT FOR ALL

O. Visual Inspection of the Repaired Blades - X10 Magnification
(1) Use the MAGNIFYING GLASS POWER 10X and the LIGHT SOURCE - WHITE to do this inspection.
If no crack is found, apply the fly-back limits as follows:
(a) If the blade is cracked, reject it.
(b) If the blade is not cracked, inspect as per (Ref. AMM TASK 72-31-11-200-010).
(c) If the blade is within the limits given in (Ref. AMM TASK 72-31-11-200-010), go to Step 4.R.

NOTE: If you find a crack during the visual inspection, inform IAE immediately. You must return cracked blades to IAE for inspection.

Subtask 72-31-11-350-065-A ** ON A/C NOT FOR ALL

P. Identify the Repair

LP Compressor Fan Blades ** ON A/C NOT FOR ALL

NOTE: A log book entry is necessary when you have completed this repair. Depending on the procedure used to inspect the repair area, write the associated maximum fly-on limits in the engine log book.

(1) Make the following log book entries:
(a) Write "VRS1506" in the engine log book.
(b) If Step 4.P. or Step 4.Q. has been carried out fly-on limits have to be considered:
1 If Zone AA or AB has been repaired, then write the following fly-on limits "Maximum 10 flight hours or 5 flight cycles" in the engine log book and continue with Step 4.R.(2).
2 If Zone AC or AD has been repaired, then write the following fly-on limits "Maximum 50 flight hours or 25 flight cycles" in the engine log book and continue with Step 4.R.(2).
(c) If Step 4.L. combined with Step 4.M. or Step 4.N. has been carried out, no maximum fly-on limits apply. Continue with Step 4.R.(2).
(2) Identify the repair on the repaired blade:
(a) If the blade was removed from the engine, vibropeen VRS1506 adjacent to the part number.
(b) If the blade is installed in the engine, vibropeen VRS1506 adjacent to the part number at the next shop visit.
(c) Use the VIBRO ENGRAVER.

NOTE: If Step 4.P. or Step 4.Q. has been carried out, VRS1506 can be repeated again after the fly-on limits have been exhausted. In this case, repeat VRS1506 from Step 4.L. onwards.

NOTE: If the preferred inspection method swab-etch Step 4.L. combined with FPI Step 4.M. has been performed, do the glass-bead peen as specified in the EM 723111300026 (VRS1724) to the repaired blades at the next shop visit.

NOTE: If one of all other inspection methods Step 4.N., Step 4.P. or Step 4.Q. has been performed, do the swab-etch and FPI as specified in the EM 723111300025 (VRS1026) and glass-bead peen as specified in the EM 723111300026 (VRS1724) to the repaired blades at the next shop visit.

Subtask 72-31-11-420-140-A ** ON A/C NOT FOR ALL

Q. Installation of the LP Compressor Fan-Blades
(1) Install the LP compressor fan-blades, if removed (Ref. AMM TASK 72-31-11-400-010).

5. Close-up
Subtask 72-31-11-942-063-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 engine air intake.
(3) Remove the access platform(s).
(4) Remove the WARNING NOTICE(S).

[Rev.10 from 2021] 2026.04.01 13:00:58 UTC