Detailed Visual Inspection of the Fan Blades [PW11]

TASK 72-11-03-220-803-A
Detailed Visual Inspection of the Fan Blades

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.

ZONE: 400

1. Reason for the Job
Use this procedure to do a detailed visual inspection of the fan blades for damage and provide continue-in-service limits.
2. Job Set-up Information
A. Work Zones and Access Panels

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

B. Referenced Information

REFERENCE	DESIGNATION
TASK 71-00-00-860-833-A	Procedure to Prevent Engine Motoring
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 72-11-03-220-801-A	Visual Examination of the Fan Blade for Bends and Curls
TASK 72-11-03-220-802-A	Visual Inspection of the Fan Blades Surface
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 72-31-00-290-802-A	Borescope Inspection of the Low Pressure Compressor (LPC) Assembly
Detailed Visual Inspection of the Fan Blades

3. Job Set-up
Subtask 72-11-03-941-056-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
Subtask 72-11-03-220-052-A ** ON A/C NOT FOR ALL

A. Detailed Visual Inspection of the Fan Blades

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

(1) Find the fan blades on the front of the engine attached to the fan hub.
(2) General instructions for the inspection of the fan blades:
(a) The general steps which follow are standard inspection data that are applicable during the inspection tasks:

1 The use of a large number of blades repaired to or near maximum limits, or the use of blades which have many repaired areas can decrease compressor efficiency and thus decrease engine performance. Refer to the repair limits on the quantity and size of repaired areas.
2 All blade surfaces must be smooth. All signs of leading and trailing edge repairs must be smooth and rounded. Refer to the repair for the minimum edge thickness limits.
3 Measure from the initial edge contour (the edge contour when the blade was manufactured) to determine the depth of a nick, blend or other damage at the leading or trailing edge.
a To find the initial edge contour, use a straight edge. Do not measure from a raised material surface.
4 Examine the engine for Foreign Object Damage (FOD) if there is damage on the fan blade adjacent to the core inlet. Do a borescope inspection of the Low Pressure Compressor (LPC) (Ref. AMM TASK 72-31-00-290-802).
(b) Do only the following inspections if the fan blades are installed in the fan hub:
1 Do a visual examination of the fan blade for bends and curls (Ref. AMM TASK 72-11-03-220-801).
2 Do a visual inspection of the fan blade surface (Ref. AMM TASK 72-11-03-220-802).
3 Do a visual inspection of the fan blade polyurethane coat (Ref. AMM TASK 72-11-03-220-805).
4 Do a visual inspection of the fan blade for erosion (Ref. AMM TASK 72-11-03-210-802).
(c) Do a visual examination of the fan blade root if the fan blade is removed from the hub (Ref. AMM TASK 72-11-03-210-801).
(3) Examine the repaired areas with fluorescent penetrant if a fan blade is blend repaired (Ref. AMM TASK 72-11-03-230-801).
(4) Examine the assembly for foreign objects, damage and correct assembly.

5. Close-up
Subtask 72-11-03-942-051-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 WARNING NOTICE(S).

[Rev.10 from 2021] 2026.04.01 02:47:57 UTC