14910-I3-U]

DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 

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## O(p3fL, [Dock~t N,lt,FAA ~004 19175; Directorate Identifier 2009-NM-031-AD; Amendment 

### \(P15~ 39-**:AD**) 

## ;2010- 

## Ol-D2- RIN 212o-AA64 Airwortbiness Directive,: Boeing Model 747-1OOBSUD, -200B, -300, -400, and -4ooD Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department ofTransportation (DOT). ACTION: Final rule. SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747-looB SUD, -2ooB, -300, -400, and -4ooD series airplanes. That AD currently requires repetitive inspections for cracking in fuselage

configuration. This AD results from findings ofcracking in fuselage stringers SL, SR, tOL, and lORatbody stations 460, 480, and 500 frame locations. We are issuing this AD to detect and correct fatigue cracking incertain fuselage stringers. which, ifleft undetected, could result infuselage skin cracking thatreduces the structural integrity ofthe skin panel, and consequent rapid depressurization ofthe airplane. DATES: This AD becomes effective [insert date 35 days after date ofpublication inthe FEDERAL REGISTER]. OUTING SYMIIOL 

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DEPARTMENT OF TRANSPORTATION Fedewal Aviation Administration ONCUAAl'NCES OUTING S¥MlIOI.

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this AD to detect and correct fatigue cracking in certain fuselage stringers, which, ifleft 8L, 8R, 10L, and lORatbody stations 460, 480, and 500 frame locations. We are issui repair 

### ifnecessary. This new AD requires revising the applicability to include an additional airplane, and reduces compliance times for the initial inspection and repetitiv intervals forModel 747-400 series airplanes that have been converted to the large cargo freighter configuration. This AD results from findings ofcracking infuselage stringers stringers 8L, 8R, IOL, and lOR atbody stations 460, 480, and 500 frame locations; and SUl\1MARY: The FAA is superseding an existing airworthiness directive (AD), which ltbn~Symbol airplanes. That AD currently requires repetitive inspections for cracking infuselage applies to certain Boeing Model 747-100B 

### sun, -200B, -300, -400, and -400D series ACTION: Final rule. AGENCY: Federal Aviation Administration (FAA), Department ofTransportation Series Airplanes Airworthiness Directives; Boeing Model 747-100B SUD, -200B, -300, -400, and -400
(DOT). [Docket No. FAA-200 I 19175; Directorate Identifier 2009-NM-631-AD;
RIN 2120-AA64 14CFR Part 39

:Amendment 39-**; AD H)

undetected, could result infuselage skin cracking that reduces the structural integrity of the skin panel, and consequent rapid depressurization ofthe airplane. DATES: This AD becomes effective [i&sertdate 35 days after date ofpublication inth tlmAI.S/S1G

FEDERAL REGISTER].[4910-I3-U]

DEPARTMENT OF TRANSPORTATION 

### Federal AviationAdministration 14CFR Part 39 [Docket No. FAA l004 191'79\Directorate Identifier2009-NM-031-AD; 

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# .~ D RIN 2120-AA64
Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department ofTransportation 

## /JlJm1Z!b I f'lrn.o.LS,IS1G Airworthiness Directives; Boeing Model 747-100B SUD, -200B, -300, -400, and -400 1 

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## f1IJn'~5 ;Amendment 39-**; AD **]



### (DOl). ACTION: Final rule. 

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# 'if. SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which '- applies to certain Boeing Model 747-1OOBSUD, -200B, -300, -400, and -400D series airplanes. That AD currently requires repetitive inspections for cracking in fuselage stringers 8L, 8R, IOL,and lORatbody stations 460, 480, and 500 frame I"""tions; and repair ifnecessary ..This new AD requires revising the applicability to include an additional airplane, and reduces compliance times forthe 

### inltial inspection and repetitiv intervals forModel 747-400 series airplanes that have been converted to the large cargo OU11!'lG $'iHilOL l..C freighter configuration. lbis AD results from fmdings ofcracking in fuselage stringers 8L,8R, 10L, and lORatbody stations 460, 480, and 500 frame locations. We are iss . m this AD to detect and correct fatigue cracking incertain fuselage stringers, which, ifleft undetected, could result infuselage skin cracking that reduces the structural integrity of . the skin panel, and consequent rapid depressurization ofthe airplane. DATES: This AD becomes effective [J.sert date 35 days after date ofpublication inth FEDERAL REGISTER].