Visual Inspection of the Fan Blades Surface [PW11]

TASK 72-11-03-220-802-A
Visual Inspection of the Fan Blades Surface

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: 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 Job
Use this procedure to visually examine the flow path surface of the fan blades.
Do this procedure when you think there is Foreign Object Damage (FOD).
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	1	GLOVES - PROTECTIVE
No specific	1	LIGHT SOURCE - WHITE
No specific	1	MAGNIFYING GLASS POWER 03X
No specific	AR	MAT - PROTECTIVE
No specific	1	MIRROR - INSPECTION, FLEXIBLE
636-1100-3GSE	2	INLET COWL PROTECT COVER

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.P05-005)	wipe, lint-free

C. Work Zones and Access Panels

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

D. Referenced Information

REFERENCE	DESIGNATION
TASK 70-28-00-910-803-A	SPOP 42 - Chromate Conversion Coating of Aluminum
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 72-11-03-210-801-A	Visual Examination of the Fan Blade Root
TASK 72-11-03-210-802-A	Detailed Inspection of Fan Blades
TASK 72-11-03-210-803-A	Visual Examination of the Fan Blade Galvanic Isolation
TASK 72-11-03-220-805-A	Visual Inspection of the Fan Blade Polyurethane-Coat
TASK 72-11-03-230-801-A	Fluorescent Penetrant Inspection of the Fan Blade Airfoil
TASK 72-11-03-320-801-A	Blend Repair of the Fan Blade Leading Edge (LE)
TASK 72-11-03-400-801-A	Installation of the Fan Blades
Fan Blade Surface
Fan Blade Cover
Fan Blade Cover Bulge

3. Job Set-up
Subtask 72-11-03-941-054-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).

4. Procedure

CAUTION: WIPE CLEAN ALL PARTS AND TOOLS AS NECESSARY TO REMOVE UNWANTED DEBRIS AND PREVENT DAMAGE TO THE ENGINE.

Subtask 72-11-03-210-052-A ** ON A/C NOT FOR ALL

A. Do a visual inspection of the protective coat and Leading Edge (LE) for erosion (Ref. AMM TASK 72-11-03-210-802).

Subtask 72-11-03-220-051-A ** ON A/C NOT FOR ALL

B. Visual Inspection of the Fan Blade Airfoil Leading and Trailing Edges (TE) and the Airfoil Surfaces for Local Damage and other Damage

Fan Blade Surface ** ON A/C NOT FOR ALL

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: USE MAXIMUM CAUTION WITH ANY ELECTRICAL EQUIPMENT IN THE AREA OF THE BLADE. CONTACT WITH ANY ELECTRICAL SOURCE THAT CAN PASS CURRENT TO THE BLADE SURFACE CAN CAUSE AN ARC BURN. AN ARC BURN CAN CAUSE LOCAL DEGRADATION OF MATERIAL PROPERTIES AND BEGIN A CRACK.

(1) Put the MAT - PROTECTIVE or the 636-1100-3GSE INLET COWL PROTECT COVER inside the engine air intake cowl.
(2) Put the GLOVES - PROTECTIVE when you touch the blades.
(3) Use the inspection procedures that follow to find local damage:
(a) Use the LIGHT SOURCE - WHITE and the MIRROR - INSPECTION, FLEXIBLE.
(b) Lightly rub the blade edge with the GLOVES - PROTECTIVE or P05-005wipe, lint-free to help find damage.
(c) Use fingernails and fingertips to help identify the size and condition of the damage, for example to know if the damage has a V-shape or round bottom. Use your fingernail to help identify a local sharp nick or dent from erosion.
(4) Look for the different types of local damage that follows:
(a) Nicks and dents with lifted edges and compressed material with small radii or rough edges must be blend repaired.
(b) Carefully examine nicks and damage on the LE at the inner half of the airfoil. Damage is very important the nearer it is to the blade root.
(c) You must do a blend repair of small cracks to the permitted limits. You cannot repair large cracks that are more than the permitted repair limits.
(d) You cannot repair arc burns.

NOTE: An arc burn is shown by a small circular or semicircular heat damaged area on the blade surface that can have shallow pits, cracks and burned or melted areas.

(5) The purpose of this examination is to find local damage which is different from erosion. Erosion is a smooth or constant wear down of material along the surface. It is identified by many, very small dents or depressions with the texture of sand paper. It is permitted for blades with erosion in the limits provided to continue-in-service (Ref. AMM TASK 72-11-03-210-802).

Subtask 72-11-03-220-058-A ** ON A/C NOT FOR ALL

C. Visual Inspection of the Fan Blade Polyurethane Coat
(1) Do a visual inspection of the fan blade polyurethane coat (Ref. AMM TASK 72-11-03-220-805).

Subtask 72-11-03-220-053-A ** ON A/C NOT FOR ALL

D. Visual Inspection of the Fan Blade Flow Path Surface

Fan Blade Surface ** ON A/C NOT FOR ALL

NOTE: All areas below the inner diameter flow path line will not be in view at the LE unless the fan spinner is removed, and at the TE unless the fan blade is removed.

NOTE: You can possibly repair and put back into service blades that were removed from service because of surface damage.

NOTE: Area N extends 0.5 in. (12.70 mm) from the top of the platform along the blade and 0.5 in. (12.70 mm) from the side of the blade along the platform, each side of the blade for full chord width.

Fan blade surface - visual inspection

EXAMINE	DAMAGE	DISPOSITION
Fan blade (1) surface for:
Area F for:
Blade tip coat and damage.	All damage to tip coat that does not show base metal.	Permitted.
	All brown or black discoloration or discontinuities in tip coat surface.	Permitted.
	Missing tip coat that shows base metal, maximum two locations, not more than 0.875 in. (22.225 mm) in length total.	Not permitted. If no missing tip coat in 2.0 in. (50.8 mm) of LE sheath: repair or replace the blade by 2600 cycles. If missing tip coat in 2.0 in. (50.8 mm) of LE sheath: repair or replace blade by 50 cycles if not galvanic isolated or not checked, or by 1100 cycles if galvanic isolated. Do a check for galvanic isolation (Ref. AMM TASK 72-11-03-210-803). Anodize bare metal area by SPOP 42 (Ref. AMM TASK 70-28-00-910-803).
	Missing tip coat that shows base metal in more than two locations or more than 0.875 in. (22.225 mm) in total length.	Not permitted. If no missing tip coat in 2.0 in. (50.8 mm) of LE sheath: repair or replace the blade by 2600 cycles. If missing tip coat is in 2.0 in. (50.8 mm) of LE sheath: repair or replace blade by 50 cycles if not galvanic isolated or not checked, or 1100 cycles if galvanic isolated. Do a check for galvanic isolation (Ref. AMM TASK 72-11-03-210-803). Contact P&W for repair.
	All damage that shows base metal and not more than 0.020 in. (0.508 mm) depth in base metal.	Not permitted. If not in 2.0 in. (50.8 mm) of LE sheath: replace the blade by 2600 cycles. If in 2.0 in. (50.8 mm) of LE sheath: replace blade by 50 cycles if not galvanic isolated or not checked, or 1100 cycles if galvanic isolated. Do a check for galvanic isolation (Ref. AMM TASK 72-11-03-210-803).
NOTE: Tip coat is gray and porous when you see it with the MAGNIFYING GLASS POWER 03X. Exposed base metal on the tip is shiny and smooth.
Airfoil tip surfaces for cracks, tears or damage.	All cracks or tears.	Not permitted. Remove the blade from service by five cycles.
Area G for:
TE for nicks, dents and damage.	All damage to base metal not more than 0.020 in. (0.508 mm) in depth.	Permitted.
	All damage to base metal 0.020 in. (0.508 mm) in depth to not more than 0.060 in. (1.524 mm) in depth.	Not permitted. Replace the blade by five cycles.
	All damage to base metal more than 0.060 in. (1.524 mm) in depth.	Not permitted. Remove the blade from service immediately.
TE for cracks or tears.	All cracks or tears.	Not permitted. Remove the blade from service immediately.
Area H for:
LE for nicks, dents and damage.	All damage not more than 0.007 in. (0.178 mm) in depth.	Permitted.
	All damage 0.007 in. (0.178 mm) to 0.060 in. (1.524 mm) in depth.	Not permitted. Replace the blade by five cycles or do a blend repair (Ref. AMM TASK 72-11-03-320-801).
	All damage more than 0.060 in. (1.524 mm) in depth.	Not permitted. Remove the blade from service by five cycles.
Airfoil LE for cracks or tears.	All cracks or tears not more than 0.060 in. (1.524 mm) in depth.	Not permitted. Replace the blade by five cycles or do a blend repair. If the blade is blend repaired, do a fluorescent penetrant inspection (Ref. AMM TASK 72-11-03-230-801).
	All cracks or tears more than 0.060 in. (1.524 mm) in depth.	Not permitted. Remove the blade from service by five cycles.
Area J for:
LE for nicks, dents and damage.	All damage to base metal not more than 0.007 in. (0.178 mm).	Permitted.
	All damage 0.007 in. (0.178 mm) to 0.030 in. (0.762 mm) in depth.	Not permitted. Repair or replace the blade by five cycles or blend repair (Ref. AMM TASK 72-11-03-320-801).
	All damage more than 0.030 in. (0.762 mm) in depth.	Not permitted. Replace the blade by five cycles.
Airfoil LE for cracks or tears.	All cracks or tears not more than 0.030 in. (0.762 mm) in depth.	Not permitted. Replace the blade by five cycles or do a blend repair. If the blade is blend repaired, do a fluorescent penetrant inspection (Ref. AMM TASK 72-11-03-230-801).
	All cracks or tears more than 0.030 in. (0.762 mm) in depth.	Not permitted. Remove the blade from service by five cycles.
Areas H and J for:
LE for color change.	All color changes (for example: light blue, purple mix) of LE sheath.	Permitted.
Area L for:
Cover damage.	All scratched or gouged base metal more than 0.006 in. (0.152 mm) in depth.	Not permitted. Remove the blade from service by five cycles.
	Dents, smooth and continuous with no missing material not more than 0.100 in. (2.540 mm) in depth.	Permitted. Not more than five dents on each blade, each dent separated by 1.0 in. (25.4 mm) minimum.
	Dents, smooth and continuous with no missing material 0.100 in. (2.540 mm) to 0.250 in. (6.350 mm) in depth.	Not Permitted. Replace blade by 50 cycles.
	Dents more than 0.250 in. (6.350 mm) in depth.	Not permitted. Remove blade from service immediately.
	All cracks or tears.	Not permitted. Remove the blade from service by five cycles.
Cover transition areas (edges) for indications of loss of bond.	Adhesive cracks or spaces, or easily deflected surfaces in cover, all sizes.	Not permitted. Remove the blade from service immediately.
Cover transition areas (edges) for bulges.	Bulges are permitted in the cover transition area if the coat does not have cracks or spaces and the bulge does not move with light pressure.	Permitted.
Area M for:
Blade to platform fillet.	All damage to base metal.	Not permitted. Replace the blade by five cycles .
Area N for:
Sheath transition areas (edges) for indications of loss of bond.	Bulging, adhesive cracks or spaces, or easily moved surfaces in sheath, all sizes.	Not permitted. Remove the blade from service by five cycles.
Areas K and P for:
Blade surfaces.	All damage to base metal not more than 0.020 in. (0.508 mm) in depth.	Permitted.
	All scratched or gouged base metal more than 0.020 in. (0.508 mm) in depth.	Not permitted. Remove the blade from service by five cycles.
	Dents, smooth and continuous, with no missing material not more than 0.100 in. (2.540 mm) in depth.	Permitted. No more than five dents on a blade, each separated by at least 1.0 in. (25.4 mm).
	Dents, smooth and continuous, with no missing material between 0.100 in. (2.540 mm) to 0.250 in. (6.350 mm) in depth.	Not Permitted. Replace the blade by 50 cycles.
	Dents more than 0.250 in. (6.350 mm) in depth.	Not permitted. Remove the blade from service immediately.
	All cracks or tears.	Not permitted. Remove the blade from service immediately.
Area Q for:
Platform, flow path surface.	All damage to base metal not more than 0.020 in. (0.508 mm) in depth.	Permitted.
	All damage to base metal more than 0.020 in. (0.508 mm) in depth.	Not permitted. Remove the blade from service by five cycles.
	Cracks or tears.	Not permitted. Remove the blade from service immediately.
Area R for:
Sealant between sheath and ground tab.	Damaged sealant with bottom that you can see, all quantities, no base metal in view.	Permitted.
	Damaged sealant with no bottom that you can see, all quantities.	Not permitted. Replace blade or repair by five cycles.
All areas for:
All airfoil surfaces.	All arc burn.	Not Permitted. Remove blade from service by five cycles.

Subtask 72-11-03-220-057-A ** ON A/C NOT FOR ALL

E. Visual Inspection of the Fan Blade Root
(1) Do a visual inspection of the fan blade root for all root area, ground tab and platform seal requirements (Ref. AMM TASK 72-11-03-210-801).

Subtask 72-11-03-220-054-A ** ON A/C NOT FOR ALL

F. Visual Inspection of the Fan Blade Cover for Bulges
(1) Do a visual inspection of the fan blade cover for bulges.

Fan Blade Cover ** ON A/C NOT FOR ALL

Fan Blade Cover Bulge ** ON A/C NOT FOR ALL

NOTE: Bulge width is the largest bulge dimension along the blade surface.

NOTE: Bulge height is the distance between the highest point above the initial blade contour to the dent with the most depth adjacent to the bulge.

NOTE: The bulged area can show with or look like dents or ripples.

Fan blade cover - visual inspection

Bulge Height	Bulge Width	Distance From Cover Edge	Disposition
0.020 in. (0.508 mm) maximum	0.5 in. (12.7 mm) maximum	1.0 in. (25.4 mm) minimum	Permitted.
One bulge more than 0.020 in. (0.508 mm) and not more than 0.5 in. (12.7 mm)	1.0 in. (25.4 mm) maximum	1.0 in. (25.4 mm) minimum	Replace blade by ten cycles (Ref. AMM TASK 72-11-03-000-801) and (Ref. AMM TASK 72-11-03-400-801).
Multiple bulges more than 0.020 in. (0.508 mm)	All	All	Replace blade immediately (Ref. AMM TASK 72-11-03-000-801) and (Ref. AMM TASK 72-11-03-400-801).
More than 0.020 in. (0.508 mm) and not more than 0.050 in. (1.270 mm)	More than 1.0 in. (25.4 mm)	All	Replace blade immediately (Ref. AMM TASK 72-11-03-000-801) and (Ref. AMM TASK 72-11-03-400-801).
More than 0.020 in. (0.508 mm) and not more than 0.050 in. (1.270 mm)	All	In 1.0 in. (25.4 mm)	Replace blade immediately (Ref. AMM TASK 72-11-03-000-801) and (Ref. AMM TASK 72-11-03-400-801).
More than 0.050 in. (1.270 mm)	All	All	Replace blade immediately (Ref. AMM TASK 72-11-03-000-801) and (Ref. AMM TASK 72-11-03-400-801).

(2) Examine the assembly for foreign objects, damage and correct assembly.

5. Close-up
Subtask 72-11-03-860-053-A ** ON A/C NOT FOR ALL

A. Put the aircraft back to its initial configuration.
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Remove the 636-1100-3GSE INLET COWL PROTECT COVER or the MAT - PROTECTIVE from the inlet cowl.
(3) Remove the access platform(s).
(4) Remove the WARNING NOTICE(S).

[Rev.10 from 2021] 2026.04.01 02:47:54 UTC