Visual Inspection of the Air Intake Cowl [CFMI]

TASK 71-11-00-210-040-A
Visual Inspection of the Air Intake Cowl

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	ACCESS PLATFORM 1M(3 FT)
No specific	AR	WARNING NOTICE(S)
No specific	Torque wrench: range to between 27 and 24 lbf.in (0.31 and 0.27 m.daN )

B. Consumable Materials

REFERENCE	DESIGNATION
(Material No.CP2517)	aerodynamic tape

C. Work Zones and Access Panels

ZONE/ACCESS	ZONE DESCRIPTION
FOR [1000EM1] (ENGINE-1)
437AL, 438AR
FOR [1000EM2] (ENGINE-2)
447AL, 448AR

D. Referenced Information

REFERENCE	DESIGNATION
TASK 71-13-00-010-040-A	Opening of the Fan Cowl Doors
TASK 71-13-00-410-040-A	Closing of the Fan Cowl Doors
TASK 71-13-11-210-040-A	Detailed Visual Inspection of the Fan Cowl Doors to Check for Mismatch at the Air Intake Cowl.
NSRM 541000
SRM 541000
CMM 711107
Intake Cowl Forward and Aft Bulkeads
Intake Cowl Outer Barrel
Intake Cowl Inner Barrel
Intake Cowl Lip
Intake Cowl Inner Barrel Acoustic Panel

3. Job Set-up
Subtask 71-11-00-941-057-A ** ON A/C NOT FOR ALL

A. Safety Precautions
(1) On the center pedestal, on the ENG panel 115VU:
(a) Put a WARNING NOTICE(S) to tell persons not to start the engine.
(2) Make sure that the engine 1(2) shutdown occurred not less than 5 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) to tell persons not to energize the FADEC 1(2).

Subtask 71-11-00-010-056-B ** ON A/C NOT FOR ALL

B. Get Access
(1) Open the fan cowl doors (Ref. AMM TASK 71-13-00-010-040):
(a) FOR [1000EM1] (ENGINE-1)
437AL 438AR
(b) FOR [1000EM2] (ENGINE-2)
447AL 448AR
(2) Put the ACCESS PLATFORM 1M(3 FT) in position.
(3) Removal of the anti-ice vent panel (30)

Intake Cowl Forward and Aft Bulkeads ** ON A/C NOT FOR ALL

(a) Remove the bolts (22) and washers (27) that attach the access covers (7, 12, 17) to the aft bulkhead.
(b) Remove the access covers (7, 12, 17).
(c) Remove the screws (35) that attach the anti-ice vent panel (30) to the inlet cowl outer barrel.
(d) Remove the anti-ice vent panel (30).

4. Procedure
Subtask 71-11-00-210-055-A ** ON A/C NOT FOR ALL

A. Do a Visual Inspection of the Intake Cowl Outer Barrel

Intake Cowl Outer Barrel ** ON A/C NOT FOR ALL

INSPECT/CHECK	MAXIMUM SERVICEABLE LIMITS	REMARKS
1.Inspect outer barrel access panel and vent frames, forward and aft lands, and upper and lower barrel half lands in splice areas for:
A.Crack	Terminated between two adjacent fasteners in joint of ten or more fasteners. 5 in. (127 mm) minimum from stiffener termination points. 10 in. (254 mm) minimum separation	Seal with aerodynamic tape (Material No.CP2517) .
		Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest).
		Permanent repair at 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest) recommended NSRM 541000.
B.Loose or missing fasteners, forward and aft lands	One loose or missing fastener with a minimum of five good fasteners on each side No loose or missing fasteners allowed a minimum of five fasteners above and below the splice No loose or missing fasteners allowed 12 inches (304.8 mm) from the anti-ice inlet duct	Apply aerodynamic tape (Material No. CP2517) over loose or missing fasteners. Replace loose or missing fasteners no later than 25 flight cycles NSRM 541000.
C.Loose or missing fasteners, splice areas	A maximum of seven out of twenty-nine fasteners can be loose or missing above or below each splice with a minimum of two good fasteners between each loose or missing fastener No loose or missing fasteners allowed in the two forward and two aft fastener rows No loose or missing fasteners allowed in the adjacent fasteners above and below the splice Loose or missing fasteners allowed in the adjacent fasteners above and below the splice if offset by at least one fastener	Apply aerodynamic tape (Material No. CP2517) over loose or missing fasteners. Replace loose or missing fasteners no later than 25 flight cycles NSRM 541000.
2.Inspect outer barrel skin for:
A.Crack	3 in. (76.2 mm) maximum length. 1 in. (25.4 mm) minimum from reinforced area. 10 in. (254 mm) minimum separation from cracks, holes, and delaminations. Maximum five each barrel half. Regard as hole if more than 0.1 in. (2.54 mm) wide or more than 0.01 in. (0.25 mm) deep	Seal with aerodynamic tape (Material No.CP2517) .
		Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest).
		Permanent repair at 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest) recommended NSRM 541000.
3.Inspect entire intake cowl outer barrel for:
A.Abrasion	No carbon fiber damage allowed	Repair carbon fiber damage before flight.
		Seal surface damage (paint and surface resin only) with aerodynamic tape (Material No.CP2517) .
		Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest).
		Permanent repair at 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest) recommended NSRM 541000.
B.Nick	0.01 in. (0.25 mm) maximum depth. Maximum width 0.1 in. (2.54 mm). Fourteen maximum	OK for flight if within limits.
C.Scratch	10 in. (254 mm) maximum length. 10 in. (254 mm) minimum separation. Ten maximum	Seal with aerodynamic tape (Material No.CP2517) .
		Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest).
		Permanent repair at 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest) recommended NSRM 541000.
D.Delamination	3 in. (76.2 mm) maximum diameter	Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest).
		Permanent repair at 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest) recommended NSRM 541000.
	1 in. (25.4 mm) minimum from reinforced area	Permanent repair at 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest) recommended.
	10 in. (254 mm) minimum separation from cracks, holes and delaminations
	0.25 in. (6.35 mm) minimum from edge of panel
	1 in. (25.4 mm) maximum length parallel to edge of panel
	Five maximum each panel
E.Hole	3 in. (76.2 mm) maximum diameter	Seal with aerodynamic tape (Material No.CP2517) .
		Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest).
		Permanent repair at 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest) recommended NSRM 541000.
	1 in. (25.4 mm) minimum from reinforced area
	10 in. (254 mm) minimum separation from cracks, holes and delaminations
	0.25 in. (6.35 mm) minimum from edge of panel
	1 in. (25.4 mm) maximum length parallel to edge of panel
	Five maximum for each barrel half
F.Gouge	0.01 in. (0.25 mm) maximum depth in 10 in. (254 mm) length	Seal with aerodynamic tape (Material No.CP2517) .
		Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest).
		Permanent repair at 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest) recommended NSRM 541000.
	10 in. (254 mm) minimum separation from gouges, scratches and cracks
	Ten maximum each barrel half
4.Examine the outer barrel to fan cowl door for mismatch.
A.Outer barrel to fan cowl	Positive 0.040 inch (1 mm) Negative 0.060 (1.5 mm)	These are the preferred measurements.
		If the mismatch is more than acceptable limits do a detailed visual inspection of the area (Ref. AMM TASK 71-13-11-210-040).
5.Examine the interphone jack assembly for:
A.Loose or missing fasteners	None allowed	Replace loose or missing fasteners CMM 711107.
B.Loose or missing pieces	None allowed	Replace loose or missing pieces CMM 711107.

Subtask 71-11-00-210-056-C ** ON A/C NOT FOR ALL

B. Do a Visual Inspection of the Intake Cowl Inner Barrel

Intake Cowl Inner Barrel ** ON A/C NOT FOR ALL

Intake Cowl Inner Barrel Acoustic Panel ** ON A/C NOT FOR ALL

INSPECT/CHECK	MAXIMUM SERVICEABLE LIMITS	REMARKS
1.Inspect perforated inner face sheet and nonperforated outer face sheet for:
A.Delamination	Not permitted opposite void or delamination on other face sheet. 1.5 in. (38.1 mm) maximum length	Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest).
		Permanent repair at 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest) check recommended NSRM 541000.
	Minimum separation from a void or other delamination is four times the maximum dimension of the delamination
	2 in. (50.8 mm) minimum from reinforced area or edge of honeycomb
	Maximum of two for each 929 cm2 (144 in.2)
B.Dent	0.05 in. (1.27 mm) maximum depth. 2.0 in. (50.8 mm) maximum length. 1.0 in. (25.4 mm) minimum from reinforced area or edge of honeycomb. 3.0 in. (76.2 mm) minimum separation from other dents.	Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest).
		Permanent repair at 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest) check recommended NSRM 541000.
C.Gouge	3 in. (76.2 mm) minimum from reinforced area, gouge or edge of honeycomb	Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest).
		Permanent repair at 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest) check recommended NSRM 541000.
	1 in. (25.4 mm) maximum length
D.Nick	2 in. (50.8 mm) minimum separation	Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest).
		Permanent repair at 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest) check recommended NSRM 541000.
	0.75 in. (19.05 mm) maximum length
	0.1 in. (2.54 mm) maximum depth
E.Scratch	2 in. (50.8 mm) minimum separation	Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest).
		Permanent repair at 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest) check recommended NSRM 541000.
	1.5 in. (38.1 mm) maximum length
	0.005 in. (0.13 mm) maximum depth
2.Inspect honeycomb core for:
A.Delamination	Not permitted opposite void or delamination on other face sheet. 1.5 in. (38.1 mm) maximum length	Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest).
		Permanent repair at 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest) check recommended NSRM 541000.
	Minimum separation from a void or other delamination is four times the maximum dimension of the delamination
	2 in. (50.8 mm) minimum from reinforced area or edge of honeycomb
	Maximum of two for each 929 cm2 (144 in.2)
3.Inspect thermal blanket for:
A.Missing aluminized covering	Aluminized covering may be fully worn or not there.	Permanent repair at 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest) check recommended NSRM 541000.
4.Inspect fire shield aluminized covering:
A.Gouge	10.0 in. (254 mm) maximum length and 0.25 in. (6.4 mm) maximum width.	Apply sealant. NSRM 541000, Repair 32.
		Permanent repair at 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest) check recommended NSRM 541000.
B.Nick	10.0 in. (254 mm) maximum length and 0.25 in. (6.4 mm) maximum width.	Apply sealant. NSRM 541000, Repair 32.
		Permanent repair at 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest) check recommended NSRM 541000.
C.Scratch	10.0 in. (254 mm) maximum length and 0.25 in. (6.4 mm) maximum width.	Apply sealant. NSRM 541000, Repair 32.
		Permanent repair at 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest) check recommended NSRM 541000.
5.Inspect riveted joint for:
A.Delamination	1 in. (25.4 mm) minimum from reinforced area or edge of honeycomb	Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest).
		Permanent repair at 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest) check recommended NSRM 541000.
	Maximum twenty-five percent of total area in two adjacent fasteners

Subtask 71-11-00-210-057-A ** ON A/C NOT FOR ALL

C. Do a Visual Inspection of the Intake Cowl Lip Structure

Intake Cowl Lip ** ON A/C NOT FOR ALL

INSPECT/CHECK	MAXIMUM SERVICEABLE LIMITS	REMARKS
1.Inspect lip segment splice fastener areas and fastener areas of lip skin to intake cowl forward bulkhead attachment.
A.Crack	Terminated between two adjacent fasteners in joint of ten or more fasteners	Do not stop drill.
	10 in. (254 mm) minimum separation	Do not install aerodynamic sealing tape.
B.Loose or missing outboard fasteners	Three missing fasteners are permitted with three intact fasteners on either side	Seal with two layers of aerodynamic tape (Material No.CP2517) .
	Six missing fasteners maximum per lip skin segment.	Inspect every 5 flight cycles.
	All fasteners must be present in splice and three intact fasteners on either side.	Install fasteners no later than 5 days SRM 541000.
C.Loose or missing inboard fasteners	Three missing fasteners are permitted with three intact fasteners on either side.	Inspect every 5 flight cycles.
	Six missing fasteners maximum per lip skin segment.	Install fasteners no later than 5 days SRM 541000.
	All fasteners must be present in splice and three intact fasteners on either side.
2.Inspect lip skin for:
A.Crack	2.99 in. (75.95 mm)	Do not stop drill.
	10 in. (254 mm) minimum separation	Do not install aerodynamic sealing tape.
		Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest).
		Permanent repair at 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest) check recommended NSRM 541000.
B.Scratch, Gouge, Abrasion	0.02 in. (0.51 mm) maximum depth	Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest).
		Permanent repair at 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest) check recommended NSRM 541000.
	Regard as crack if depth is more than 0.02 in. (0.51 mm) deep
C.Buckle	1.6 in. (40.64 mm) minimum from edge of panel	Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest).
		Permanent repair at 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest) check recommended NSRM 541000.
	5 in. (127 mm) maximum width
	Minimum width ten times depth. 0.5 in. (12 .7 mm) maximum depth
	10 in. (254 mm) minimum separation
D.Dent	1.6 in. (40.64 mm) minimum from edge of panel	Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest).
		Permanent repair at 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest) check recommended NSRM 541000.
	5 in. (127 mm) maximum width
	0.5 in. (12.7 mm) maximum depth
	Minimum width ten times depth
	10 in. (254 mm) minimum separation

Subtask 71-11-00-210-058-A ** ON A/C NOT FOR ALL

D. Do a Visual Inspection of the Intake Cowl Forward and Aft Bulkheads

Intake Cowl Forward and Aft Bulkeads ** ON A/C NOT FOR ALL

INSPECT/CHECK	MAXIMUM SERVICEABLE LIMITS	REMARKS
1.Inspect the forward and aft bulkhead fastener joints and doublers for:
A.Crack	Terminated between two adjacent fasteners	Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest).
		Permanent repair at 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest) check recommended NSRM 541000.
	10 in. (254 mm) minimum separation
2.Inspect the forward and aft bulkheads for:
A.Crack	0.99 in. (25.15 mm) maximum length	Stop-drill before flight.
	10 in. (254 mm) minimum separation	Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest).
		Permanent repair at 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest) check recommended NSRM 541000.
B.Gouge	10 in. (254 mm) maximum length	Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest).
		Permanent repair at 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest) check recommended NSRM 541000.
	10 in. (254 mm) minimum separation
	Regard as crack if depth is more than twenty-five percent of material thickness
C.Dent of buckle	Minimum twenty times sheet thickness from bulkhead edge	Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest).
		Permanent repair at 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest) check recommended NSRM 541000.
	Minimum width ten times depth
	5 in. (127 mm) maximum width
	0.05 in. (1.27 mm) maximum depth
	10 in. (254 mm) minimum separation
D.Hole	None allowed	Repair before flight.
E.Nick	0.1 in. (2.54 mm) maximum width	Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest).
		Permanent repair at 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest) check recommended NSRM 541000.
	Maximum depth twenty-five percent of material thickness
F.Scratch	10 in. (254 mm) maximum length	Monitor at 750 Flight Hours / 750 Flight Cycles / 4 calendar months (whichever the earliest).
		Permanent repair at 7500 Flight Hours / 5000 Flight Cycles / 24 calendar months (whichever the earliest) check recommended NSRM 541000.
	10 in. (254 mm) minimum separation
	Regard as crack if depth is more than twenty-five percent of material thickness

5. Close-up
Subtask 71-11-00-410-056-B ** 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) Installation of the anti-ice vent panel (30)

Intake Cowl Forward and Aft Bulkeads ** ON A/C NOT FOR ALL

(a) Install the bolts (22) and washers (27) that attach the access covers (7, 12, 17) to the aft bulkhead.
(b) TORQUE the bolts (22) to between 27 and 24 lbf.in (0.31 and 0.27 m.daN )

.
(c) Install the screws (35) that attach the anti-ice vent panel (30) to the inlet cowl outer barrel.
(3) 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
(4) Remove the access platform(s).
(5) Remove the WARNING NOTICE(S).

[Rev.10 from 2021] 2026.04.01 02:21:58 UTC