[4910-13-P]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0718; Directorate Identifier 2009-NM-025-AD; Amendmen

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39-**; AD **] 2.0I 0 ~ 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 a new airworthiness directive (AD) for all Model

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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

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detailed and high frequency eddy current inspections for cracks in the wing and

horizontal stabilizer side-of-body joints and the fuselage skin circumferential splices, an ~"TE

repair if necessary. This AD also requires, for certain airplanes, repetitive detailed

inspections for cracks ofthe fuselage skin circumferential splices, and repair if necess

This AD results from Boeing analysis indicating that the wing and horizontal stabilizer

side-of-body joints, and the fuselage skin circumferential splices, are susceptible to

fatigue cracking due to high cyclic loads on the airplane. We are issuing this AD to dete

and correct fatigue cracking at multiple adjacent locations in the subject areas, which

could connect to form large cracks and result in reduced structural integrity leading to

rapid decompression and consequent loss of control of the airplane.

DATES: This AD is effective [insert date 35 days after date of publication in the

FEDERAL REGISTER].

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[4910-13-PJ

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

IDocket No. FAA-Z009-0718; Directorate Identifier Z009-NM-llZ5-AD; Amendment .J:Hvi\~

:.39-**·,AD **)

R1N ZIZO-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,

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747-400F, 747SR, and 747SP Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: We are adopting a new airworthiness directive (AD) for all 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 and high frequency eddy current inspections for cracks in the wing and

horizontal stabilizer side-of-body joints and the fuselage skin circumferential splices, an Nm~f!!

repair if necessary. This AD also requires, for certain airplanes, repetitive detailed

inspections for cracks of the fuselage skin circumferential splices, and repair if necess

This AD results from Boeing analysis indicating that the wing and horizontal stabilizer

side-of~body joints, and the fuselage skin circumferential splices are susceptible to

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fatigue cracking due to high cyclic loads on the airplane. We are issuing this AD to dete t JI,1, 0

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and correct fatigue cracking at multiple adjacent locations in the subject areas, which

could connect to form large cracks and result in reduced structural integrity leading to

rapid decompression and consequent loS'sof control of the airplane.

DATES: This AD is effective [insert date 35 days after date of publication in the

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FEDERAL REGISTER].
(4910-13-P)

DEPARTMENT OF TRANSPORT AnON

Federal Aviation Administration ,~~

14 CFR Part 39 A:xM141Di()

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(Docket No, FAA-Z009-0718; Directorate Identifier Z009-NM-oZS-AD; Amendment d:1.iVill$fJ

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: 39-*'; AD "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 a new am.vorthiness directive (AD) for all 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 in the wing and

horizontal stabilizer side-of-body joints and the fuselage skin circumferential splices, an

repair if necessary. This AD also requires, for certain airplanes, repetitive detailed

inspections for cracks of the fuselage skin circumferential splices, and repair if necess

This AD results from Boeing analysis indicating that the wing and horizontal stabilizer

side-of-body joints, and the fuselage skin circumferential splices are susceptible to

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fatigue cracking due to high cyclic loads on the airplane. We are issuing this AD to dete t

and correct fatigue cracking at multiple adjacent locations in the subject areas, which

could connect to form large cracks and result in reduced structural integrity leading to

rapid decompression and consequent lois of control of the airplane.

DATES: This AD is effective [insert date 35 days after date of publication in the

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FEDERAL REGISTER).

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