[4910-13-P]

DEPARTMENT OF TRANSPORT AnON Federal Aviation Administration _DNCURJ\ENCES ~C1unNC;

SYM~QL 14 CFR Part 39 111-)(\)-1I'j INIllM..5lStG [Docket No. FAA-2010-0132; Directorate Identifier 2009-NM-096-AD; Amendment '7 ' 

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# L; 5 DATE RlN 2120-AA64

SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Model 747-100, 747-200~, and -200F series airplanes, That AD '~:' _",.,_ currently requires inspections to detect cracking inthe upper row of fasteners holes ofth N~~~SI'f1t:: G, skin lapjoints in the fuselage lower lobe, and repair ifnecessary. This new AD reduces ~G h ' , I f h d'fi'..' Th' AD I j' 

# 7frritC " t emaXtnlUmmtcrva ate post-ruo t lcatlOnmspectlOns. lS resu ts Tomreport ROlJTlNG SYMBOL offatigue 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

'N LSI IG fatigue cracking inthe longitudinal lapjoints ofthe fuselage lower lobe, which could Ie to the rapid decompression ofthe airplane and the inability ofthe structure to carry

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

# I PUBLICATION IN THE FEDERAL REGISTER]. fail-safe loads.

PUBLICATION INTI-IEFEDERAL REGISTER]. 

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# ;'1\)",',J The Director ofthe Federal Register approved the incorporation by reference of tvl \i / LJI ) TNI certain publication listed inthe AD as of[INSERT DATE 35 DAYS AFTER DATE OF 

### ,14910-13-P]

DEPARTMENT OF TRANSPORT AnON



## ADiYHZlD1 L INJTlALS/SlG 

## 1.L: J OLlnNG SYMBOL 

### $-21-/0 Ainvorthiness Directives; The Boeing Company Model 747-100, -200B, and -200F R1N 2120-AA64 Series Airplanes JhjIYHIt.j

. ~mA~~ [Docket No. FAA-2010-0132; DIrectorate Identifier 2009-NM-096-AD; Amendment '7 . -ulchl;" A,T~ 39-**; AD **j 14 CFR Part 39 Federal Aviation Administration

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

NGSYI'!llOL

~ INmALSIS1G ACTION: Final rule. currently requires inspections to detect cracking inthe upper row of fasteners holes ofth 

### "SfR ";;J skin lapjoints inthe fuselage lower lobe, and repair ifnecessary. This new AD reduces the maximum interval oftbe post-modification inspections. This AD results from report offatigue cracking on modified airplanes. We Jre issuing this AD to detect and correct I fatigue cracking inthe longitudinal lapjoints ofthe fuselage [ower lobe, which could lea I AT~ to the rapid decompression ofthe 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;

n"G SYHllOL fail-safe loads. DATES: This AD is effective [INSERT DATE 35 DAYS AFTER DATE OF PUBLICATION INTHE FEDERAL REGISTER]. The Director ofthe Federal Register approved the incorporation by reference of . 

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_ NmAl.SlSIG certam publicatIon hsted mthe AD as of [INSERT DATE 3) DAYS AFTER DATE OF 

### , PUBLICATION INTHE FEDERAL REGISTER]. 

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