Detailed Visual Inspection (DVI) of the Fan Exit Stator [PW11]

TASK 72-21-07-220-801-A
Detailed Visual Inspection (DVI) of the Fan Exit Stator

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: DO NOT DO THIS INSPECTION DURING WINDY CONDITIONS. THE FIRST STAGE LPC ROTOR (FAN ROTOR) CAN TURN BY THE WIND AND CAUSE INJURY TO YOUR HANDS.

1. Reason for the Job
Self explanatory
2. Job Set-up Information
A. Fixtures, Tools, Test and Support Equipment

REFERENCE	QTY	DESIGNATION
No specific	1	FLASHLIGHT
No specific	AR	MAT - PROTECTIVE
636-1100-3GSE	1	INLET COWL PROTECT COVER

B. 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 72-21-07-000-801-A	Removal of the Fan Exit Stator
TASK 72-21-07-300-801-A	Blend The Surface Damage Of The Fan Exit Stator
TASK 72-21-07-400-801-A	Installation of the Fan Exit Stator
TASK 72-31-00-290-802-A	Borescope Inspection of the Low Pressure Compressor (LPC) Assembly
Fan Exit Stator

3. Job Set-up
Subtask 72-21-07-941-052-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 72-21-07-200-050-A ** ON A/C NOT FOR ALL

A. Visual Examination of the Fan Exit Stator
(1) Put MAT - PROTECTIVE or 636-1100-3GSE INLET COWL PROTECT COVER inside the air inlet cowl.
(2) Do a visual examination of the fan exit stator for damage by looking between the fan blades. See Table 601.
(a) Examine all of the vanes with a FLASHLIGHT.
(3) If the fan exit stator vanes are damaged, it is necessary to do a borescope inspection of the Low Pressure Compressor (LPC) variable inlet guide vanes and LPC 1st stage rotor (Ref. AMM TASK 72-31-00-290-802).

Fan Exit Stator Inspection

Table 601

EXAMINE	DAMAGE	DISPOSITION
Area A:
Vane leading edge for nicks, scratches and dents.	Any quantity up to 0.025 in. (0.63 mm) in depth 0.500 in. (12.70 mm) or more separation between each damage.	Permitted. Apply chromate conversion coating touch-up to the unprotected aluminum surfaces by SPOP 42 (Ref. AMM TASK 70-28-00-910-803).
	A maximum of three locations up to 0.030 in. (0.762 mm) in depth. 0.500 in. (12.70 mm) or more separation between each damage. Blend is permitted on only one vane per stator.	Not permitted. Repair the fan exit stator (Ref. AMM TASK 72-21-07-300-801), or replace the fan exit stator. (Ref. AMM TASK 72-21-07-000-801) and (Ref. AMM TASK 72-21-07-400-801), or remove the engine from service before the next flight.
	Any quantity more than 0.030 in. (0.762 mm) in depth or less than 0.500 in. (12.70 mm) separation between each damage or blended damage on more than one vane per stator.	Not permitted. Replace the fan exit stator (Ref. AMM TASK 72-21-07-000-801) and (Ref. AMM TASK 72-21-07-400-801), or remove the engine from service before the next flight.
Area A:
Vane leading and edge areas for tears and cracks.	Any quantity.	Not permitted. Replace the fan exit stator (Ref. AMM TASK 72-21-07-000-801) and (Ref. AMM TASK 72-21-07-400-801), or remove the engine from service within 5 flight cycles.
Area B:
ID and OD shroud areas for nicks, scratches and dents.	Any quantity up to 0.015 in. (0.38 mm) maximum depth.	Permitted.
	Any quantity over 0.015 in. (0.38 mm) up to 0.030 in. (0.76 mm) maximum depth.	Not permitted. Replace the fan exit stator (Ref. AMM TASK 72-21-07-000-801) and (Ref. AMM TASK 72-21-07-400-801), or remove the engine from service within 5 flight cycles.
	Any quantity over 0.030 in. (0.76 mm) depth.	Not permitted. Replace the fan exit stator (Ref. AMM TASK 72-21-07-000-801) and (Ref. AMM TASK 72-21-07-400-801), or remove the engine from service before the next flight.
Area B:
ID and OD shroud areas for cracks	Any quantity.	Not permitted. Replace the fan exit stator (Ref. AMM TASK 72-21-07-000-801) and (Ref. AMM TASK 72-21-07-400-801), or remove the engine from service before the next flight.
Area C:
Concave and convex vane surfaces for nicks, scratches and dents	Any quantity up to 0.010 in. (0.25 mm) depth maximum.	Permitted.
	Any quantity more than 0.010 in. (0.25 mm) depth up to 0.015 in. (0.38 mm) depth maximum must be 0.500 in. (12.70 mm) apart from other nicks or dents.	Permitted.
	Nicks and dents between 0.010 in. (0.25 mm) and 0.015 in. (0.38 mm) and less than 0.500 in. (12.70 mm) apart from other nicks or dents, or more than 0.015 in. (0.38 mm) depth.	Not permitted. Replace the fan exit stator (Ref. AMM TASK 72-21-07-000-801) and (Ref. AMM TASK 72-21-07-400-801), or remove the engine from service before the next flight.
Area C:
Concave and convex vane surfaces for cracks	Any quantity.	Not permitted. Replace the fan exit stator (Ref. AMM TASK 72-21-07-000-801) and (Ref. AMM TASK 72-21-07-400-801), or remove the engine from service before the next flight.
Area D:
Vane-to-shroud rubber sealing joint for loose or missing material.	Any amount up to 20 percent of vane sealing area, per vane.	Permitted.
	Any amount up to 40 percent of vane sealing area, per vane, for a maximum of 10 vanes.	Not permitted. Repair the fan exit stator, or replace the fan exit stator within 50 flight hours (Ref. AMM TASK 72-21-07-300-801), or (Ref. AMM TASK 72-21-07-000-801) and (Ref. AMM TASK 72-21-07-400-801).
	Over 40 percent of vane sealing area, per vane, or more than 10 vanes with loose or missing seal material.	Not permitted. Replace the fan exit stator (Ref. AMM TASK 72-21-07-000-801) and (Ref. AMM TASK 72-21-07-400-801), or remove the engine from service within 5 flight cycles.
All vane areas:
Pitting from corrosion	Any quantity up to 0.005 in. (0.13 mm) maximum depth.	Permitted.
	Any quantity over 0.005 in. (0.13 mm) maximum depth.	Not permitted. Replace the fan exit stator (Ref. AMM TASK 72-21-07-000-801) and (Ref. AMM TASK 72-21-07-400-801), or remove the engine from service before the next flight.

5. Close-up
Subtask 72-21-07-942-050-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 protective mat from the inlet cowl.
(3) Remove the WARNING NOTICE(S).

[Rev.10 from 2021] 2026.04.01 02:48:54 UTC