DOC AIRBUS | AMM A320FBlend Repair of the Fan Blade Leading Edge (LE) [PW11]
TASK 72-11-03-320-801-A
Blend Repair of the Fan Blade Leading Edge (LE)
Use this procedure to locally blend repair scallops on the LE of the fan blade assembly.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Consumable Materials
C. Work Zones and Access Panels
D. Referenced Information
3. Job Set-up
Subtask 72-11-03-941-063-A ** ON A/C NOT FOR ALL
Subtask 72-11-03-860-055-A ** ON A/C NOT FOR ALL
[Rev.10 from 2021]
2026.04.01 13:02:16 UTC
Blend Repair of the Fan Blade Leading Edge (LE)
WARNING:
BE CAREFUL WHEN YOU DO WORK ON THE ENGINE AFTER SHUTDOWN. THE ENGINE CAN STAY HOT FOR A LONG TIME. IF YOU DO NOT OBEY THIS INSTRUCTION, INJURY CAN OCCUR.
WARNING:
MAKE SURE THAT THE ENGINE SHUTDOWN OCCURRED NOT LESS THAN FIVE MINUTES BEFORE YOU DO THIS PROCEDURE. IF YOU DO NOT OBEY THIS INSTRUCTION, INJURY CAN OCCUR.
WARNING:
BE CAREFUL WHEN YOU USE CONSUMABLE MATERIALS. OBEY THE MATERIAL MANUFACTURER'S INSTRUCTIONS AND YOUR LOCAL REGULATIONS.
WARNING:
USE PROTECTIVE GLOVES TO PREVENT POSSIBLE INJURY TO THE HANDS WHEN YOU TOUCH OR HOLD THE FAN BLADES. THE BLADE EDGES ARE SHARP AND CAN CUT THE HANDS.
CAUTION:
BE VERY CAREFUL WHEN YOU USE ELECTRICAL EQUIPMENT NEAR THE AREA OF THE BLADE. THE ELECTRICAL SOURCE MUST NOT SEND ELECTRICAL CURRENT TO THE BLADE SURFACE. IF IT DOES, IT CAN CAUSE AN ARC BURN WHICH CAN START A CRACK. IF YOU DO NOT OBEY THIS CAUTION, DAMAGE TO ENGINE PARTS CAN OCCUR.
ZONE: 400
1. Reason for the JobUse this procedure to locally blend repair scallops on the LE of the fan blade assembly.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| No specific | 1 | MAT - PROTECTIVE |
| REFERENCE | DESIGNATION |
|---|---|
| (Material No.P05-145) | tape, masking polyester film (mylar) |
| (Material No.P05-437) | tape, pressure sensitive polyester |
| cloth, emery | |
| (Material No.P11-014) | alcohol, isopropyl |
| (Material No.P11-078) | alcohol, isopropyl |
| ZONE/ACCESS | ZONE DESCRIPTION |
|---|---|
| 400 | POWER PLANT, NACELLES AND PYLONS |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 70-25-00-910-801-A | SPOP 70 - Fluorescent Penetrant Inspection (FPI) - Local Application |
| TASK 70-27-00-910-804-A | SPOP 208 - Degreasing of Parts by Solvent Wiping |
| TASK 70-28-00-910-801-A | SPOP 532 - Blending and Buffing of Titanium Parts |
| TASK 71-00-00-860-833-A | Procedure to Prevent Engine Motoring |
| TASK 72-11-03-000-801-A | Removal of the Fan Blades |
| TASK 72-11-03-400-801-A | Installation of the Fan Blades |
Fan Blade LE - Repair AreasSubtask 72-11-03-941-063-A ** ON A/C NOT FOR ALL
A. Safety Precautions
(1) Do the procedure to prevent engine motoring
(Ref. AMM TASK 71-00-00-860-833).
(2) Put the MAT - PROTECTIVE onto the inlet cowl and fan case to prevent damage to the inner surfaces.
4. Procedure(1) Do the procedure to prevent engine motoring
(Ref. AMM TASK 71-00-00-860-833).
(2) Put the MAT - PROTECTIVE onto the inlet cowl and fan case to prevent damage to the inner surfaces.
CAUTION:
WIPE CLEAN ALL PARTS AND TOOLS AS NECESSARY TO REMOVE UNWANTED DEBRIS AND PREVENT DAMAGE TO THE ENGINE.
Subtask 72-11-03-320-052-A ** ON A/C NOT FOR ALL A. Blend Repair of the Fan Blade LE
(1) Do a fluorescent penetrant inspection of the full LE area for cracks by SPOP 70 with ultra high sensitivity (Ref. AMM TASK 70-25-00-910-801).
(2) If necessary, you can remove the blade from the engine for this blend repair procedure. Make a record of the blade location on the hub (Ref. AMM TASK 72-11-03-000-801).
(3) Blend the LE repair areas to remove nicks, dents and scratches by SPOP 532 for general instructions, but do the specified procedures that follow (Ref. AMM TASK 70-28-00-910-801):
(a) Blend to remove the damage to the LE sheath on areas B, C and D.
(b) No blend repair permitted on area A. See the sheet 1 of the figure:
(c) Blend length−to−depth ratio for the blend repair is 20 to 1. Measure the blend length and depth on the LE as follows. See the sheet 2 of the figure:
1 Measure the length of the blend area.
2 Put a straight edge across the blend area.
3 Measure the distance between the straight edge and the lowest point of the blend area.
4 The blend length must be more than 20 times the blend depth.
(d) Blend the repair area to 0.002 in. (0.051 mm) - 0.003 in. (0.076 mm) more than the initial damage. Do not blend the repair area more than the maximum depth limit.
(e) Blend with hand tools only.
(f) Do a check for heat build-up with your bare hand. Clean the fan blade by SPOP 208 withP11-078 alcohol, isopropyl P11-014 alcohol, isopropyl
(g) The maximum cumulative length of all blends along the LE must be less than 3.20 in. (81.28 mm).
(h) No more than two blends of maximum depth are permitted for each blade.
(i) Blend depth limits are based on the initial edge contour. Total depth of LE blends is cumulative.
(k) Do the straight blend on the corners of the LE as an alternative to the scallop bend.
(l) Make sure blends are correctly rounded to the initial edge contour as follows:
1 Blend area must be smooth and continuous with no raised material.
2 Sharp edges are not permitted.
3 Break edges where blended areas come together with adjacent concave and convex faces to make a smooth change from blended area to blade concave and convex airfoil surface.
4 Blend no more than 0.090 in. (2.286 mm) aft from the blended area into concave and convex faces.
(m) The criteria that follow are applicable to blades with Trailing Edge (TE) blend repairs that were done before. See the sheet 2 of the figure:
1 Chord-wise depths of blends directly opposite on the LE and the TE are cumulative.
2 Isolate blends that are not directly opposite from each other by a distance of no less than the mean chord−wise width of the blades.
(4) Polish the blend areas by SPOP 532 withP05−104 cloth, emery
(a) Remove all tool and file marks. Polish along the length of the blade only. Do not polish across the chord width of the blade.
(b) Surface finish of the repair area must be the same as the adjacent area.
(5) Do the fluorescent penetrant inspection of the repaired areas for cracks by SPOP 70 with ultra high sensitivity. Crack indications are not permitted (Ref. AMM TASK 70-25-00-910-801):
(a) Fluorescent penetrant inspection only permitted on the LE detail. ApplyP05-145 tape, masking polyester film (mylar) P05-437 tape, pressure sensitive polyester
(6) Clean the repair area by SPOP 208 (Ref. AMM TASK 70-27-00-910-804).
(7) Do a dimensional inspection of the LE. Dimension V and LE radius is based on dimension A or W at blend locations only. Refer to table 1:
(a) Section B−B dimensions are applicable to Dimension W 25.089 in. (0.637 m) - 27.217 in. (0.691 m).
(b) Section C−C dimensions are applicable to Dimension W 3.934 in. (99.923 mm) -25.088 in. (0.637 m).
(c) Section D−D dimensions are applicable to Dimension W 0.00 in. (0 mm) - 3.933 in. (99.898 mm).
5. Close-up(1) Do a fluorescent penetrant inspection of the full LE area for cracks by SPOP 70 with ultra high sensitivity (Ref. AMM TASK 70-25-00-910-801).
(2) If necessary, you can remove the blade from the engine for this blend repair procedure. Make a record of the blade location on the hub (Ref. AMM TASK 72-11-03-000-801).
(3) Blend the LE repair areas to remove nicks, dents and scratches by SPOP 532 for general instructions, but do the specified procedures that follow (Ref. AMM TASK 70-28-00-910-801):
(a) Blend to remove the damage to the LE sheath on areas B, C and D.
(b) No blend repair permitted on area A. See the sheet 1 of the figure:
(c) Blend length−to−depth ratio for the blend repair is 20 to 1. Measure the blend length and depth on the LE as follows. See the sheet 2 of the figure:
1 Measure the length of the blend area.
2 Put a straight edge across the blend area.
3 Measure the distance between the straight edge and the lowest point of the blend area.
4 The blend length must be more than 20 times the blend depth.
(d) Blend the repair area to 0.002 in. (0.051 mm) - 0.003 in. (0.076 mm) more than the initial damage. Do not blend the repair area more than the maximum depth limit.
(e) Blend with hand tools only.
(f) Do a check for heat build-up with your bare hand. Clean the fan blade by SPOP 208 with
(g) The maximum cumulative length of all blends along the LE must be less than 3.20 in. (81.28 mm).
(h) No more than two blends of maximum depth are permitted for each blade.
(i) Blend depth limits are based on the initial edge contour. Total depth of LE blends is cumulative.
NOTE: EXAMPLE: Blend depth limit is 0.060 in. (1.524 mm). If a 0.010 in. (0.2540 mm) blend was made before, no more blend (or sum of blends) will be permitted to more than 0.050 in. (1.270 mm) depth.
(j) Blend the distress in the "normal to LE" direction. Round up the edges. (k) Do the straight blend on the corners of the LE as an alternative to the scallop bend.
(l) Make sure blends are correctly rounded to the initial edge contour as follows:
1 Blend area must be smooth and continuous with no raised material.
2 Sharp edges are not permitted.
3 Break edges where blended areas come together with adjacent concave and convex faces to make a smooth change from blended area to blade concave and convex airfoil surface.
4 Blend no more than 0.090 in. (2.286 mm) aft from the blended area into concave and convex faces.
(m) The criteria that follow are applicable to blades with Trailing Edge (TE) blend repairs that were done before. See the sheet 2 of the figure:
1 Chord-wise depths of blends directly opposite on the LE and the TE are cumulative.
2 Isolate blends that are not directly opposite from each other by a distance of no less than the mean chord−wise width of the blades.
(4) Polish the blend areas by SPOP 532 with
(a) Remove all tool and file marks. Polish along the length of the blade only. Do not polish across the chord width of the blade.
(b) Surface finish of the repair area must be the same as the adjacent area.
(5) Do the fluorescent penetrant inspection of the repaired areas for cracks by SPOP 70 with ultra high sensitivity. Crack indications are not permitted (Ref. AMM TASK 70-25-00-910-801):
(a) Fluorescent penetrant inspection only permitted on the LE detail. Apply
(6) Clean the repair area by SPOP 208 (Ref. AMM TASK 70-27-00-910-804).
(7) Do a dimensional inspection of the LE. Dimension V and LE radius is based on dimension A or W at blend locations only. Refer to table 1:
(a) Section B−B dimensions are applicable to Dimension W 25.089 in. (0.637 m) - 27.217 in. (0.691 m).
(b) Section C−C dimensions are applicable to Dimension W 3.934 in. (99.923 mm) -25.088 in. (0.637 m).
(c) Section D−D dimensions are applicable to Dimension W 0.00 in. (0 mm) - 3.933 in. (99.898 mm).
| Dimension A (Distance From Plane Z) | Minimum Dimension V | Angle B Reference | Section Reference | Dimension W (Straight Line Dimension) |
| 3.592 in. (91.237 mm) - 3.739 in. (94.970 mm) | 0.119 in. (3.023 mm) | - | J−J | - |
| 3.740 in. (94.996 mm) - 4.424 in. (112.369 mm) | 0.117 in. (2.9718 mm) | 11.203 degrees | K−K | 26.98 in. (0.685 m) - 26.10 in. (0.663 m) |
| 4.425 in. (112.3948 mm) - 5.095 in. (129.413 mm) | 0.112 in. (2.845 mm) | 8.402 degrees | L−L | 26.10 in. (0.663 m) - 25.22 in. (0.641 m) |
| 5.096 in. (129.438 mm) - 5.757 in. (146.228 mm) | 0.104 in. (2.642 mm) | 5.601 degrees | M−M | 25.22 in. (0.641 m) - 24.34 in. (0.618 m) |
| 5.756 in. (146.202 mm) - 6.413 in. (162.890 mm) | 0.095 in. (2.413 mm) | 2.801 degrees | N−N | 24.34 in. (0.618 m) - 23.44 in. (0.595 m) |
| 6.414 in. (162.915 mm) - 7.065 in. (179.451 mm) | 0.089 in. (2.261 mm) | 0 degrees | P-P | 23.44 in. (0.595 m) - 22.50 in. (0.571 m) |
| 7.066 in. (179.476 mm) - 8.065 in. (204.851 mm) | 0.085 in. (2.159 mm) | 0 degrees | R-R | 22.50 in. (0.571 m) - 21.57 in. (0.548 m) |
| 8.066 in. (204.876 mm) - 9.065 in. (230.251 mm) | 0.081 in. (2.057 mm) | 0 degrees | S-S | 21.57 in. (0.548 m) - 20.64 in. (0.524 m) |
| 9.066 in. (230.276 mm) - 10.065 in. (255.651 mm) | 0.079 in. (2.007 mm) | 0 degrees | T-T | 20.64 in. (0.524 m) - 19.71 in. (0.501 m) |
| 10.066 in. (255.676 mm) - 11.065 in. (281.051 mm) | 0.077 in. (1.956 mm) | 0 degrees | U-U | 19.71 in. (0.501 m) - 18.76 in. (0.477 m) |
| 11.066 in. (281.0759 mm) - 12.065 in. (306.450 mm) | 0.075 in. (1.905 mm) | 0 degrees | V-V | 18.76 in. (0.477 m) - 17.81 in. (0.452 m) |
| 12.066 in. (306.476 mm) - 13.065 in. (331.850 mm) | 0.074 in. (1.880 mm) | 0 degrees | W-W | 17.81 in. (0.452 m) - 16.84 in. (0.428 m) |
| 13.066 in. (331.876 mm) - 14.065 in. (0.357 m) | 0.075 in. (1.905 mm) | 0 degrees | X-X | 16.84 in. (0.428 m) - 15.86 in. (0.403 m) |
| 14.066 in. (0.357 m) - 15.065 in. (0.383 m) | 0.075 in. (1.905 mm) | 0 degrees | Y-Y | 15.86 in. (0.403 m) - 14.86 in. (0.377 m) |
| 15.066 in. (0.383 m) - 16.065 in. (0.408 m) | 0.075 in. (1.905 mm) | 0 degrees | Z-Z | 14.86 in. (0.377 m) - 13.85 in. (0.352 m) |
| 16.066 in. (0.408 m) - 17.065 in. (0.433 m) | 0.075 in. (1.905 mm) | 0 degrees | AA-AA | 13.85 in. (0.352 m) - 12.82 in. (325.63 mm) |
| 17.066 in. (0.433 m) - 18.065 in. (0.459 m) | 0.075 in. (1.905 mm) | 0 degrees | AB-AB | 12.82 in. (325.63 mm) - 11.79 in. (299.47 mm) |
| 18.066 in. (0.459 m) - 19.065 in. (0.484 m) | 0.074 in. (1.880 mm) | 0 degrees | AC-AC | 11.79 in. (299.47 mm) - 10.74 in. (272.80 mm) |
| 19.066 in. (0.484 m) - 20.065 in. (0.510 m) | 0.073 in. (1.854 mm) | 0 degrees | AD-AD | 10.74 in. (272.80 mm) - 9.69 in. (246.13 mm) |
| 20.066 in. (0.510 m) - 21.065 in. (0.535 m) | 0.073 in. (1.854 mm) | 0 degrees | AE-AE | 9.69 in. (246.13 mm) - 8.64 in. (219.46 mm) |
| 21.066 in. (0.535 m) - 22.065 in. (0.560 m) | 0.073 in. (1.854 mm) | 0 degrees | AF-AF | 8.64 in. (219.46 mm) - 7.57 in. (192.28 mm) |
| 22.066 in. (0.560 m) - 23.065 in. (0.586 m) | 0.073 in. (1.854 mm) | 0 degrees | AG-AG | 7.57 in. (192.28 mm) - 6.50 in. (165.10 mm) |
| 23.066 in. (0.586 m) - 24.065 in. (0.611 m) | 0.073 in. (1.854 mm) | 0 degrees | AH-AH | 6.50 in. (165.10 mm) - 5.39 in. (136.91 mm) |
| 24.066 in. (0.611 m) - 25.065 in. (0.637 m) | 0.078 in. (1.981 mm) | 0 degrees | AJ-AJ | 5.39 in. (136.91 mm) - 4.31 in. (109.47 mm) |
| 25.066 in. (0.637 m) - 26.065 in. (0.662 m) | 0.077 in. (1.956 mm) | 0 degrees | AK-AK | 4.31 in. (109.47 mm) - 3.41 in. (86.61 mm) |
| 26.066 in. (0.662 m) - 26.858 in. (0.682 m) | 0.078 in. (1.981 mm) | −0.91 degrees | AL-AL | 3.41 in. (86.61 mm) - 2.54 in. (64.52 mm) |
| 26.859 in. (0.682 m) - 27.651 in. (0.702 m) | 0.082 in. (2.083 mm) | −1.821 degrees | AM-AM | 2.54 in. (64.52 mm) - 1.67 in. (42.42 mm) |
| 27.652 in. (0.702 m) - 28.445 in. (0.723 m) | 0.083 in. (2.108 mm) | −2.731 degrees | AN-AN | 1.67 in. (42.42 mm) - 0.81 in. (20.57 mm) |
| 28.446 in. (0.723 m) - 29.241 in. (0.743 m) | 0.083 in. (2.108 mm) | −3.641 degrees | AP-AP | 0.81 in. (20.57 mm) - 0.00 in. (0 mm) |
Table - LE minimum V thickness
(8) If the blade(s) was(were) removed from the engine for this blend repair procedure, install the blade(s) in their initial location (Ref. AMM TASK 72-11-03-400-801). Subtask 72-11-03-860-055-A ** ON A/C NOT FOR ALL
A. Put the aircraft back to its initial configuration.
(1) Remove the MAT - PROTECTIVE from the inlet cowl.
(2) Examine the assembly for foreign objects, damage and correct assembly.
(3) Make sure that the work area is clean and clear of tools and other items.
(4) Remove the WARNING NOTICE(S).
(1) Remove the MAT - PROTECTIVE from the inlet cowl.
(2) Examine the assembly for foreign objects, damage and correct assembly.
(3) Make sure that the work area is clean and clear of tools and other items.
(4) Remove the WARNING NOTICE(S).