[4910-13-P]

DEPARTMENT OF TRANSPORTATION 

### Federal Aviation Administration 14CFR Part 39 [Docket No. FAA-2009-0718; Directorate Identifier 2009-NM-025-AD; Amendmen 

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## 05-0:' RIN 2120-AA64 Ainvorthiness Directives; The Boeing Company Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-400D, 747-400F, 747SR, and 747SP Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: We are adopting anew airworthiness directive (AD) for allModel 

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rNTTlAl.S'SIG 747-100, 747-l00B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-40 747-400D, 747-400F, 747SR, and 747SP series airplanes. This AD requires one-time ~OlJrINGSYMaOL

NmALSiSIG detailed and high frequency eddy current inspections for cracks inthe wing and horizontal stabilizer side-of-body joints and the fuselage skin circumferential splices, an ~"TE repair ifnecessary. This AD also requires, for certain airplanes, repetitive detailed inspections for cracks ofthe fuselage skin circumferential splices, and repair ifnecess This AD results from Boeing analysis indicating that the wing andhorizontal stabilizer side-of-body joints, andthe fuselage skin circumferential splices, are susceptible to fatigue cracking dueto high cyclic loads on the airplane. We are issuing this AD to dete and correct fatigue cracking atmultiple adjacent locations in the subject areas, which could connect to form large cracks and result inreduced structural integrity leading to rapid decompression and consequent loss ofcontrol ofthe airplane. DATES: This AD iseffective [insert date 35 days after date ofpublication inthe FEDERAL REGISTER]. O\Tfrno ~YMllOL

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DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 IDocket No. FAA-Z009-0718; Directorate Identifier Z009-NM-llZ5-AD; Amendment 

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## , R1NZIZO-AA64 Airworthiness Directives; The Boeing Company Model 747-100, 747-100B, 747-100B SOD, 747-Z00B, 747-Z00C, 747-Z00F, 747-300, 747-400, 747-400D, j1pn-I~ II--

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## \2-~-O~ 747-400F, 747SR, and 747SP Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: We are adopting anew airworthiness directive (AD) forall Model 747-100, 747-100B, 747-100B SUD, 747-200B, 747-200C, 747-200F, 747-300, 747-40 m.«5;" 747-400D, 747-400F, 747SR, and 747SP series airplanes. This AD requires one-time detailed andhigh frequency eddy current inspections for cracks inthe wing and horizontal stabilizer side-of-body joints and the fuselage skin circumferential splices, an

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### =~~ and correct fatigue cracking atmultiple adjacent locations inthe subject areas, which could connect to form large cracks andresult inreduced structural integrity leading to rapid decompression and consequent loS'sofcontrol ofthe airplane. DATES: This AD iseffective [insert date 35 days after date ofpublication inthe 

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FEDERAL REGISTER].(4910-13-P)

DEPARTMENT OF TRANSPORT AnON Federal Aviation Administration 

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## """""'~ (Docket No, FAA-Z009-0718; Directorate Identifier Z009-NM-oZS-AD; Amendment 

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## "J /a.J.1l'I RlN Z120-AA64 Airworthiness Directives; The Boeing Company Model 747-100, 747-100B, 747-100B SUO, 747-200B, 747-200C, 747-200F, 747-300, 747-400, 747-4000, 747-400F, 747SR, and 747SP Series Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: We are adopting anew am.vorthiness directive (AD) forall Model 747-100, 747-100B, 747-100B SUO, 747-200B, 747-200C, 747-200F, 747-300, 747-40 747-400D, 747-400F, 747SR, and 747SP series airplanes. This AD requires one-time detailed and high frequency eddy current inspections for cracks inthe wing and horizontal stabilizer side-of-body joints and the fuselage skin circumferential splices, an repair ifnecessary. This AD also requires, forcertain airplanes, repetitive detailed inspections for cracks ofthe fuselage skin circumferential splices, and repair ifnecess This AD results from Boeing analysis indicating that the wing andhorizontal stabilizer side-of-body joints, and the fuselage skin circumferential splices are susceptible to 

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Nm.o.t.S/SIG fatigue cracking due to high cyclic loads on the airplane. We are issuing this AD to dete t and correct fatigue cracking atmultiple adjacent locations in the subject areas, which could connect to form large cracks and result inreduced structural integrity leading to rapid decompression and consequent lois ofcontrol ofthe airplane. DATES: This AD iseffective [insert date 35 days after date ofpublication inthe
NfTWSISIG FEDERAL REGISTER). 

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