[4910-13-P]

DEPARTMENT OF TRANSPORT AnON

Federal Aviation Administration _DNCURJ\ENCES

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14 CFR Part 39 111-)(\)-1I'j

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[Docket No. FAA-2010-0132; Directorate Identifier 2009-NM-096-AD; Amendment '7 '

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39-*'; AD *(J.r- J.O I0-1 Lj _ \ 0 ,m

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RlN 2120-AA64

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

applies to certain Model 747-1 00, 747-200~, and -200F series airplanes, That AD '~:'_",.,_

currently requires inspections to detect cracking in the upper row of fasteners holes of th N~~~SI'f1t:: G,

skin lap joints in the fuselage lower lobe, and repair if necessary. This new AD reduces ~G

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t e maXtnlUm mtcrva ate post-ruo t lcatlOn mspectlOns. lS resu ts Tom report

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of fatigue cracking on modified airplanes. We afe issuing this AD to detect and correct Ji1Jm-lDif.J

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

Airworthiness Directives; The Boeing Company Model 747-100, -200B, and ~200F

Series Airplanes

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fatigue cracking in the longitudinal lap joints of the fuselage lower lobe, which could Ie

to the rapid decompression of the airplane and the inability of the structure to carry

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DATES, This AD is effective [INSERT DATE 135DAYS AFTER DATE OF C·~ I

PUBLICATION IN THE FEDERAL REGISTER].

fail-safe loads.

PUBLICATION IN TI-IE FEDERAL REGISTER].

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The Director 'OOATIi ;'1\)",',J of the Federal Register approved the incorporation by reference of tvl \i / LJI

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certain publication listed in the AD as of[INSERT DATE 35 DA YS AFTER DATE OF ,
14910-13-P]

DEPARTMENT OF TRANSPORT AnON

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Ainvorthiness Directives; The Boeing Company Model 747-100, -200B, and -200F

R1N 2120-AA64

Series Airplanes

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[Docket No. FAA-2010-0132; DIrectorate Identifier 2009-NM-096-AD; Amendment '7 .

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A,T~ 39-**; AD **j

14 CFR Part 39

Federal Aviation Administration

AGENCY: Federal Aviation Administration (I;AA), DOT. OVTlNG SVMlIOL

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ACTION: Final rule.

currently requires inspections to detect cracking in the upper row of fasteners holes ofth "SfR ";;J

skin lap joints in the fuselage lower lobe, and repair if necessary. This new AD reduces

the maximum interval oftbe post-modification inspections. This AD results from report

of fatigue cracking on modified airplanes. We Jre issuing this AD to detect and correct

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fatigue cracking in the longitudinal lap joints of the fuselage [ower lobe, which could lea

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to the rapid decompression of the airplane and the inability of the structure to carry

applies to certain Model 747-100,747-2008, and -200F series airplanes. That AD

SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which 0411;

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fail-safe loads.

DATES: This AD is effective [INSERT DATE 35 DAYS AFTER DATE OF

PUBLICATION IN THE FEDERAL REGISTER].

The Director of the Federal Register approved the incorporation by reference of . IJ i\ifl-I u J

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certam publicatIon hsted m the AD as of [INSERT DATE 3) DAYS AFTER DATE OF ,

PUBLICATION IN THE FEDERAL REGISTER]. '"

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