Visual Inspection of the Fan Frame Assembly [CFMB]

TASK 72-23-00-210-004-A
Visual Inspection of the Fan Frame Assembly

WARNING: BE CAREFUL WHEN YOU DO WORK ON THE ENGINE PARTS AFTER THE ENGINE SHUTDOWN. USE APPLICABLE THERMAL GLOVES. THE ENGINE PARTS CAN STAY HOT FOR ONE HOUR AFTER SHUTDOWN AND CAN BURN YOU.

CAUTION: TITANIUM PARTS REQUIRE THE USE OF NON-HALOGENATED SOLVENTS.

ZONE: 400
FIN: 1000EM1 ** ON A/C NOT FOR ALL
FIN: 1000EM2 ** ON A/C NOT FOR ALL

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

REFERENCE	QTY	DESIGNATION
No specific	AR	WARNING NOTICE(S)
No specific	Torque wrench: range to between 95 and 85 lbf.in (1.07 and 0.96 m.daN )

B. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
400	POWER PLANT, NACELLES AND PYLONS
FOR [1000EM1] (ENGINE-1)
437AL, 438AR, 451AL, 452AR
FOR [1000EM2] (ENGINE-2)
447AL, 448AR, 461AL, 462AR

C. Referenced Information

REFERENCE	DESIGNATION
TASK 71-00-00-000-042-A	Removal of the Power Plant
TASK 71-00-00-000-042-A-01	Removal of the Power Plant with the Engine Positioner TWW 75E (MIAG)
TASK 71-00-00-000-042-A-03	Removal of the Power Plant with Jacxson Tool
TASK 71-00-00-400-042-A	Installation of the Power Plant
TASK 71-00-00-400-042-A-01	Installation of the Power Plant with the Engine Positioner TWW 75E (MIAG)
TASK 71-00-00-400-042-A-03	Installation of the Power Plant with Jacxson Tool
TASK 71-13-00-010-040-B	Opening of the Fan Cowl Doors
TASK 71-13-00-410-040-B	Closing of the Fan Cowl Doors
TASK 72-00-00-200-025-A	Over-Serviceable-Limit Extensions
TASK 72-00-00-200-025-A-01	Over-Serviceable-Limit Extensions
TASK 72-23-00-000-027-A	Removal of the Fan Duct Panels
TASK 72-23-00-000-028-A	Removal of the Splitter Fairing
TASK 72-23-00-210-802-A	Visual Inspection of the Fan Frame Strut 7 Oil Leakage
TASK 72-23-00-280-005-A	Inspection of Forward Acoustical Panels
TASK 72-23-00-280-006-A	Inspection of Mid Acoustical Panels
TASK 72-23-00-280-007-A	Inspection of Aft Acoustical Panels
TASK 72-23-00-300-042-A	Repair of Fan Duct Panel
TASK 72-23-00-350-002-A	Removal of Rust from the Fan Frame Casing
TASK 72-23-00-400-027-A	Installation of the Fan Duct Panels
TASK 72-23-00-400-028-A	Installation of the Splitter Fairing
TASK 78-30-00-081-041-B	Make the Thrust Reverser Serviceable after Maintenance
TASK 78-30-00-481-041-B	Make the Thrust Reverser Unserviceable for Maintenance
TASK 78-36-00-010-040-B	Opening of the Thrust Reverser Doors
TASK 78-36-00-410-040-B	Closing of the Thrust Reverser Doors
Fan Frame Casing, Fan Inlet Case and Abradable Cartridge - Inspection/Check
Fan Duct Panels
Fan Inlet Case on B1 upstream bracket location
Wear on B1 Flange Radius

3. Job Set-up
Subtask 72-23-00-941-077-A ** ON A/C NOT FOR ALL

A. Safety Precautions
(1) On the center pedestal, on ENG panel 115VU:
(a) Put a WARNING NOTICE(S) in position to tell persons not to start the engine.
(2) Make sure that the engine 1(2) shutdown occurred not less than five minutes before you do this procedure.
(3) On the overhead maintenance panel 50VU:
(a) Make sure that the ON legend of the ENG/FADEC GND PWR/1(2) pushbutton switch is off.
(b) Put a WARNING NOTICE(S) in position to tell persons not to energize FADEC 1(2).

Subtask 72-23-00-010-088-A ** ON A/C NOT FOR ALL

B. Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-040):
(1) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(2) FOR [1000EM2] (ENGINE-2)
447AL 448AR

Subtask 72-23-00-040-066-A ** ON A/C NOT FOR ALL

C. Make the thrust reverser unserviceable (Ref. AMM TASK 78-30-00-481-041).

Subtask 72-23-00-010-101-A ** ON A/C NOT FOR ALL

D. Open the thrust reverser doors (Ref. AMM TASK 78-36-00-010-040):
(1) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(2) FOR [1000EM2] (ENGINE-2)
461AL 462AR

4. Procedure
Subtask 72-23-00-210-057-A ** ON A/C NOT FOR ALL

A. Visual inspection of the Fan Frame Assembly

INSPECT/CHECK	MAXIMUM SERVICEABLE LIMITS	REMARKS
1.Fan frame casing for: Fan Frame Casing, Fan Inlet Case and Abradable Cartridge - Inspection/Check ** ON A/C NOT FOR ALL
A.Cracks	No limits in quantity if 0.08 in. (2.03 mm) max. length and min. of 1 in. (25.40 mm) apart.
B.Dents or nicks on struts	No limits in quantity if, 0.08 in. (2.03 mm) max. depth
C.Corrosion (discoloration)	No limits in quantity	At the first opportunity remove rust (Ref. AMM TASK 72-23-00-350-002)
D.Scaling or pitting	Not serviceable
E.Traces of oil around the strut seven vent hole
a. Moisture	If 1.18 in. (29.97 mm) max. height and 3.62 in. (91.95 mm) max. length	For traces out of criterion 5-cycle serviceable extension is allowed (Ref. AMM TASK 72-23-00-210-802).
b. Droplet	Not serviceable	5-cycle serviceable extension is allowed (Ref. AMM TASK 72-23-00-210-802).
c. Black traces	If 1.18 in. (29.97 mm) max. height and 3.62 in. (91.95 mm) max. length.	For traces out of criterion 5-cycle serviceable extension is allowed (Ref. AMM TASK 72-23-00-210-802).
F.Water drain tube of the fan case and boss
a. Water drain boss detached	Not serviceable	Remove water drain tube of the fan case and boss NOTE: The water drain boss and water drain tube installation must be done is shop.
b. Water drain tube and/or water drain boss missing	No limits in quantity
2.Inlet case on the B1 and B3 upstream bracket location for: Fan Frame Casing, Fan Inlet Case and Abradable Cartridge - Inspection/Check ** ON A/C NOT FOR ALL
A.Wear of flange holes 66 and 67 oversized on the B1 flange only NOTE: Flange holes are counted clockwise, viewed from the aft looking forward. The No. 1 flange hole is located at the 12 o'clock position.	One or both holes expanded are permitted if: Each expanded hole is not more than 0.315 IN. (8 MM) width and not more than 0.6 IN. (15 MM) in length where length is the maximum dimension of wear and width is perpendicular to length. Minimum of five non-damaged holes on both sides of the expanded holes. Minimum distance between the expanded hole and flange edge is 0.2 IN. (5 MM).	Replace the inlet case, which makes the removal of the engine from the aircraft necessary (Ref. AMM TASK 71-00-00-000-042) and (Ref. AMM TASK 71-00-00-400-042). NOTE: Non-damaged holes have no wear of any kind.
	Or
	Each expanded hole is not more than 0.335 in. (8.5 mm) diameter.	Replace the inlet case, which makes the removal of the engine from the aircraft necessary (Ref. AMM TASK 71-00-00-000-042) and (Ref. AMM TASK 71-00-00-400-042).
B.Wear of all other flange holes oversized on B1 and B3 flanges	Two expanded adjacent holes are permitted if: Each expanded hole is not more than 0.315 IN. (8 MM) width and not more than 0.6 IN. (15 MM) in length where length is the maximum dimension of wear and width in perpendicular to length. Minimum of five non-damaged holes on both sides of the expanded holes. Minimum distance between the expanded hole and flange edge is 0.2 IN. (5 MM).	Repair. Refer to CFM56-5B SB 72-0892. NOTE: CFM56-5B SB 72-0892 is applicable to B1 flange bolt-hole locations 30, 31, 79 and 80 only. NOTE: Flange holes are counted clockwise, viewed from the aft looking forward. The No. 1 flange hole is located at the 12 o'clock position. NOTE: Non-damaged holes have no wear of any kind.
	Or Each expanded hole is not more than 0.315 IN. (8 MM) width and not more than 0.39 IN. (10 MM) in length where length is the maximum dimension of wear and width is perpendicular to the length. Minimum distance between the expanded hole and flange edge is 0.2 IN. (5 MM).
C.Wear, fretting, chafing of flange faces	If 0.008 in. (0.20 mm) max. depth or If 0.02 in. (0.5 mm) max. depth and 0.155/sq.in. (100 sq.mm) max. surface.	10-cycle serviceable extension is allowed, then replace the inlet case, which makes the removal of the engine from the aircraft necessary (Ref. AMM TASK 71-00-00-000-042) and (Ref. AMM TASK 71-00-00-400-042).
D.Wear, fretting, chafing on the top of flange holes	If 0.02 in. (0.5 mm) max. width and 0.8 in. (20 mm) max. length.	10-cycle serviceable extension is allowed, then replace the inlet case, which makes the removal of the engine from the aircraft necessary (Ref. AMM TASK 71-00-00-000-042) and (Ref. AMM TASK 71-00-00-400-042).
E.Washer impression around flange holes	If 0.032 in. (0.81 mm) max. depth and 0.60 in. (15.24 mm) max. diameter.	Do the blending according to SPM 70-41-11-350-009. 10-cycle serviceable extension is allowed, then replace the inlet case, which makes the removal of the engine from the aircraft necessary (Ref. AMM TASK 71-00-00-000-042) and (Ref. AMM TASK 71-00-00-400-042).
3.Fan inlet case on B1 upstream bracket location Fan Inlet Case on B1 upstream bracket location ** ON A/C NOT FOR ALL
A.Wear on the B1 flange radius. Wear on B1 Flange Radius ** ON A/C NOT FOR ALL	For damage that measures (X) from the B1 flange, a maximum depth of wear (A) is permitted.	Replace the inlet case, which makes the removal of the engine from the aircraft necessary (Ref. AMM TASK 71-00-00-000-042) and (Ref. AMM TASK 71-00-00-400-042).
4.Inlet case on the B4 upstream fan case:
A.Expanded holes	Two expanded adjacent holes are permitted if: Each expanded hole is not more than 0.315 in. (8 mm) width and not more than 0.39 in. (10 mm) long. Minimum of five non-damaged holes on both sides of the expanded holes.	NOTE: Non-damaged holes have no wear of any kind.
B.Wear, fretting, chafing around flange holes	If 0.031 in. (0.8 mm) max. depth and 0.155 sq.in. (100 sq.mm) max. surface.	10-cycle serviceable extension is permitted.
5.Inlet case on the B4 downstream fan case:
A.Expanded holes	Two expanded adjacent holes are permitted if: Each expanded hole is not more than 0.315 in. (8 mm) width and not more than 0.39 in. (10 mm) long. Minimum of five non-damaged holes on both sides of the expanded holes.	NOTE: Non-damaged holes have no wear of any kind.
B.Wear, fretting, chafing around flange holes	If 0.024 in. (0.6 mm) max. depth and 0.155 sq.in. (100 sq.mm) max. surface.	10-cycle serviceable extension is permitted.
6.Fan FWD acoustical panel (Ref. AMM TASK 72-23-00-280-005)
7.Fan MID acoustical panel (Ref. AMM TASK 72-23-00-280-006)
8.Fan aft acoustical panels (Ref. AMM TASK 72-23-00-280-007)
9.Splitter fairing for
A.Cracks	Not serviceable	Replace the fairing (Ref. AMM TASK 72-23-00-000-028) and (Ref. AMM TASK 72-23-00-400-028)
B.Damaged protective coating	No limits in quantity
C.Erosion	No limits in quantity
10.Fan duct panels for: Fan Duct Panels ** ON A/C NOT FOR ALL
A.Missing louver	One missing louver permitted per panel if no more than four panels have this damage	Replace the panel (Ref. AMM TASK 72-23-00-000-027) and (Ref. AMM TASK 72-23-00-400-027).
B.Nicks, dents or scratches	No limits
C.Loose bolts	Not serviceable	Make sure that the washers are installed and torque the bolts to between 95 and 85 lbf.in (1.07 and 0.96 m.daN )
D.Cracks in the screw hole area	One for each screw hole max. length 0.25 in. (6.35 mm)	Replace the panel (Ref. AMM TASK 72-23-00-000-027) and (Ref. AMM TASK 72-23-00-400-027)
E.Cracks in the flanged edges	Not serviceable	Repair the panel (Ref. AMM TASK 72-23-00-300-042)
F.Cracks on the louver and the area adjacent to the louver	2 cracks permitted on the same panel	Repair the panel (Ref. AMM TASK 72-23-00-300-042)
G.Fan duct panel missing	Not serviceable	Install the fan duct panel(s) (Ref. AMM TASK 72-23-00-400-027)
		Refer to over serviceable limit extension (Ref. AMM TASK 72-00-00-200-025)

5. Close-up
Subtask 72-23-00-410-082-A ** ON A/C NOT FOR ALL

A. Close Access
(1) Make sure that the work area is clean and clear of tools and other items.
(2) Close the thrust reverser doors (Ref. AMM TASK 78-36-00-410-040):
(a) FOR [1000EM1] (ENGINE-1)
451AL 452AR
(b) FOR [1000EM2] (ENGINE-2)
461AL 462AR

Subtask 72-23-00-440-061-A ** ON A/C NOT FOR ALL

B. Make the thrust reverser serviceable (Ref. AMM TASK 78-30-00-081-041).

Subtask 72-23-00-410-093-A ** ON A/C NOT FOR ALL

C. Close Access
(1) Close the fan cowl doors (Ref. AMM TASK 71-13-00-410-040):
(a) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(b) FOR [1000EM2] (ENGINE-2)
447AL 448AR
(2) Remove the WARNING NOTICE(S).

[Rev.10 from 2021] 2026.04.01 02:41:49 UTC