DOC AIRBUS | AMM A320FFluorescent Penetrant Inspection of the Fan Blade Airfoil [PW11]
TASK 72-11-03-230-801-A
Fluorescent Penetrant Inspection of the Fan Blade Airfoil
Use this inspection procedure to examine the fan blade airfoil for damage or cracks on the leading edge sheath.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
B. Referenced Information
3. Job Set-up
Subtask 72-11-03-941-051-A ** ON A/C NOT FOR ALL
Subtask 72-11-03-230-050-A ** ON A/C NOT FOR ALL
Subtask 72-11-03-860-051-A ** ON A/C NOT FOR ALL
[Rev.10 from 2021]
2026.04.01 02:47:53 UTC
Fluorescent Penetrant Inspection of the Fan Blade Airfoil
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.
1. Reason for the JobUse this inspection procedure to examine the fan blade airfoil for damage or cracks on the leading edge sheath.
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment
| REFERENCE | QTY | DESIGNATION |
|---|---|---|
| 636-1100-3GSE | 1 | INLET COWL PROTECT COVER |
| REFERENCE | DESIGNATION |
|---|---|
| TASK 70-25-00-910-801-A | SPOP 70 - Fluorescent Penetrant Inspection (FPI) - Local Application |
| TASK 71-00-00-860-833-A | Procedure to Prevent Engine Motoring |
| TASK 72-11-03-220-801-A | Visual Examination of the Fan Blade for Bends and Curls |
Fluorescent Penetrant Inspection of the Fan Blade AirfoilSubtask 72-11-03-941-051-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(1) Do the procedure to prevent engine motoring
(Ref. AMM TASK 71-00-00-860-833)
Subtask 72-11-03-230-050-A ** ON A/C NOT FOR ALL
A. Fluorescent Penetrant Inspection of the Fan Blade Airfoil
(a) Put an 636-1100-3GSE INLET COWL PROTECT COVER or equivalent in the inlet cowl.
(b) Use the SPOP 70, fluorescent penetrant inspection, (local application) ultra high sensitivity method.
(c) Examine the damaged areas of the fan blade airfoil leading edge sheath for cracks by SPOP 70 (Ref. AMM TASK 70-25-00-910-801).
(d) Cracks are not permitted. If a crack is found (Ref. AMM TASK 72-11-03-220-801) for required action.
(2) Remove the 636-1100-3GSE INLET COWL PROTECT COVER from the inlet cowl.
5. Close-upCAUTION:
WIPE CLEAN ALL PARTS AND TOOLS AS NECESSARY TO REMOVE UNWANTED DEBRIS AND PREVENT DAMAGE TO THE ENGINE.
(1) Do a fluorescent penetrant inspection of the fan blade airfoil leading edge sheath as follows: (a) Put an 636-1100-3GSE INLET COWL PROTECT COVER or equivalent in the inlet cowl.
(b) Use the SPOP 70, fluorescent penetrant inspection, (local application) ultra high sensitivity method.
(c) Examine the damaged areas of the fan blade airfoil leading edge sheath for cracks by SPOP 70 (Ref. AMM TASK 70-25-00-910-801).
(d) Cracks are not permitted. If a crack is found (Ref. AMM TASK 72-11-03-220-801) for required action.
(2) Remove the 636-1100-3GSE INLET COWL PROTECT COVER from the inlet cowl.
Subtask 72-11-03-860-051-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).
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Remove the WARNING NOTICE(S).