(4910-13-V)

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR ParI 39

IDoc~et No. FAA-2009-0655; Directorate Identifier 2008-NM-i92-ADj Amendment 39-

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RIN 2120-AA64

Ain"orthiness Directives; Boeing Model 747-200F, 747-200C, 747-400, 747-400D, and

747-400F Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of Transportation (DOT),

ACTION: Final rule.

SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which

applies to all Boeing Model 747-200F, 747-200C, 747-400, 747-400D, and 747-400F series

airplanes. That AD cun-ently requires repetitive inspections for cracking of certain fuselage

internal structure (i.e., Sections 42 and 46 fuselage frames, upper deck floor beams,

electronic bay access door cutout, nose wheel well, and main entry doors and door cutouts),

and repair if necessary. This new AD reqLLiresadditional repetitive 1Jlspections for cracking

of certain fuselage structure (i.e., Section 41 fuselage frames where they connect to upper

deck floor beams, and section 41 fuselage frames between stringer (S-8 and S-12), and

related investigative/corrective actions if necessary. This AD also reduces the inspection

threshold and repetitive inspection intervals for certain airplanes. This AD results from

fatigue tests and analysis by Boeing that identifIed additional areas of the fuselage where

fatigue cracks can occur. We aTeissuing this AD to prevent the loss of structural integrity of

the fuselage, which could result in rapid depressurization of the airplane.

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Federal Aviation Administration

14 CFR Part 39

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IDocket No. FAA-2009-0655; Directorate Identifier 2008-NM-192-ADj Amendment D.Pw ., (

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Airworthiness Directives; Boeing Model 747~200F, 747-200C, 747-400, 747-4000, an rm.r:s1li '

747-400F Series Airplanes '9:25 - 0 'i

AGENCY: Federal Aviation Administration (FAA), Department of Transportation

(DOT).

ACTION: Final rule.

SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which

applies to all Boeing Model 747-200F, 747-200C, 747-400, 747-400D, and 747-400F

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series airplanes. That AD currently requires repetitive inspections for cracking of certai m

fuselage internal structure (i.e., Sections 42 and 46 fuselage frames, upper deck floor

beams, electronic bay access door cutout, nose wheel well, and main entry doors and

door cutouts), and repair if necessary. This new AD requires additional repetitive

inspections for cracking of certain fuselage structure (i.e., Section 41 fuselage frames

where they connect to upper deck floor beams, and section 41 fuselage frames behveen

stringer (S-8 and S-12), and related investigative/corrective actions if necessary. This A

also reduces the inspection threshold and repetitive inspection intervals for certain

airplanes. This AD results fTomfatigue tests and analysis by Boeing that identified

additional areas of the fuselage where fatigue cracks can occur. We are issuing this AD

to prevent the loss of structural integrity of the fuselage, wh.ich could result in rapid

depressurization of the airplane.

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14910-13-UI

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

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(Docket No. FA..t\.-2009-0655; Directorate Identifier 2008-NM-192-AD; Amendment l';L r:..

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Ainvorthiness Directives; Boeing Model 747-200F, 747~200C. 747-400. 747-4000, an 'Nll~L'_.;--J"

747-400F Series Airplanes "0£ 9-2~- C"

AGENCY: Federal Aviation Administration (FAA). Depanment of Transportation

(DOT).

ACTION: Final rule.

SUMMARY: The F.A...A is superseding an existing airworthiness directive (AD). which

applies to all Boeing Model 747-200F, 747-200C, 747-400, 747-4000, and 747-400F

series airplanes. That AD cun-enily requires repetitive inspections for cracking of certai

fuselage internal structure (i.e., Sections 42 and 46 fuselage frames, upper deck floor

beams, electronic bay access door cutout, nose wheel well. and main entry doors and

door cutOUI's),and repair if necessary. This new AD requires additional repetitive

inspections for cracking of certain fuselage structure (i.e., Section 41 fuselage frames

where they connect to upper deck floor beams, and section 41 fuselage frames between

stringer (S-8 and S-12), and related investigative/corrective actions if necessary. This A

also reduces the inspection threshold and repetitive inspection intervals for certain

airplanes. This AD results from fatigue tests and analysis by Boeing that identified

additional areas of the fuselage where fatigue cracks can occur. We arc issuing this AD

to prevent the loss of structural integrity of the fuselage. which could result in rapid

depressurization of the airplane.

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