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747-400F, and 747SR Series Airplanes AGENCY: Federal Aviation Administration (FAA), Department ofTransportation ACTION: Final rule. 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, Airworthiness Directives; The Boeing Company Model 747-100, 747-1 OOB, RlN 2120-AA64

(DOT). Federal Aviation Administration DEPARTMENT OF TRANSPORTATION 14 CFR Part 39 {Dacke,tNo. FAA-2009-1069; Directorate Identifier 2009-NM-036-AD; Amendment 

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SUMMARY; The FAA is superseding an existing airworthiness directive (AD), which -, ---- Nm.<L..Y.;>G~ru"~ applies to all Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, ----- 'o.o.r[ 747-200F, 747-300, 747-400, 747-400D, 747-400F, and 747SR series airplanes. That """rUNV',n,8O!- AD currently requires repetitive inspections to find cracking ofthe web, strap, inner chords, and inner chord angle ofthe forward edge frame ofthe number 5main entry dool'~----- 

### ~" cutouts, and repair, ifnecessary. This new AD requires expanding the inspection areas tc~

_ Yoi6uTl>IG SY"!lO~ include the frame segment between stringers 16 and 23. This AD reinstates the repetlti>:.i'l;;;;;;;;;;';;;;;;;- 

### r IG~ATUR€ inspections specified above far certain airplanes. This AD alsa requires r~petitive inspections for cracking afrepairs. This AD results from additional reports ofcracks tha!b.~=" .. ==- ~~,t~<';~Y"OO~ have been found in the strap and inner chord afthe forward edge frame ofthe number 5 

# >--~=- l~lf1.&lYS>cMATUR£ main entry door cutouts, between stringers 16 and 23. We are issuing this AD to detect 

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I DEPARTMENT OF TRANSPORTATION Federal Aviation Administration QNCURREr~CES RDUnNG SYMBOL 14CFR Part 39 2.<>tA (Docket No. FAA-2Of&:.1069jDirectorate Identifier 2009-NM-036-AD; Amendmen 39-**; AD **1 RIN 2120-AA64 Airworthiness Directives; The Boeing Company Model 747~I00, 747~JDOB, Apm-j (q [VIM [NlnALSI51G

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747-200F, 747-300, 747-400, 747-400D, 747-400F, and 747SR series airplanes. That AD currently requires repetitive inspections to find cracking ofthe web, strap, inner NmAlSISIG I -£, r)J chords, and inner chord angle ofthe forward edge frame ofthe number 5 main entry do 'tv cutouts, and repair, ifnecessary. 111isnew AD requires exyanding the inspectio.n areas 

## J AT ~ ..; I O\JT1NG sY"''>OL include the frame segment between stringers 16 and 23. This AD reinstates the repetitiv

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# 7 (1) AGENCY: Federal Aviation Administration (FAA), Department ofTransportation 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, and 747SR Series Airplanes (DOT). ACTION: Final rule. ./ SUMMARY TI FAA' d' ... h' d' . (AD) h' h ~\\ 

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: Ie IS superse mg an eXIstmg aIrwort mess' lrectJve ,W Ie ;; 5 lG applies to all Boeing Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, '" "~'" b/\f) OUtING S'/MIIOl 

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~OUTING SY"'"Ol have been found in the strap and inner chord ofthe forward edge frame of the number 5 N1T1AL.5,'$IG main entry door cutouts, between stringers 16 and 23. We ar} issuing this AD to detect ATE and correct such cracks. This condition; ifnot corrected, could cause damage to the adjacent body structure, which could result in depressurization ofthe airplane in flight. OUTING SYMBOL NmAlSiSIG[4910-13-P)

DEPARTMENT OF TRANSPORTATION

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747-400F, and 747SR Series AiIplanes Ainvorthiness Directives; The Boeing Company 'Model 747-100, 747-1008,
AGENCY: Federal Aviation Administration (FAA), Department ofTransportation (DOT). ACTION: Final rule. ./ ~li SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which 

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747-200F, 747-300, 747-400, 747-4000, 747-400F, and 747SR series airplanes. That AD currently requires repetitive inspections to find cracking ofthe web, strap, irmcr

inspections specified above for certain airplanes. This AD also requires repetitive inspections for cracking ofrepairs. This AD results from additional reports ofcracks tha have been found in the strap and inner chord ofthe forward edge frame ofthe number 5 main entry door cutouts, between stringers 16and 23. We ar~ issuing this AD to detect and correct such cracks. This condition,' ifnot corrected, could cause damage to the adjacent body structure, which could result in depressurization ofthe airplane in flight.

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