14910-I3-U]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39 '2.00';- O(p3 fL,

[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 747-1 OOBSUD, -200B, -300, -400, and -4ooD

Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of Transportation (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 of cracking in fuselage stringers SL, SR, tOL,

and lOR at body stations 460, 480, and 500 frame locations. We are issuing this AD to

detect and correct fatigue cracking in certain fuselage stringers. which, ifleft undetected,

could result in fuselage skin cracking that reduces the structural integrity of the skin panel,

and consequent rapid depressurization of the airplane.

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

FEDERAL REGISTER].

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[4910-I3-U)

DEPARTMENT OF TRANSPORTATION

Fedewal Aviation Administration ONCUAAl'NCES

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this AD to detect and correct fatigue cracking in certain fuselage stringers, which, if left

8L, 8R, 10L, and lOR at body stations 460, 480, and 500 frame locations. We are issui

repair if necessary. This new AD requires revising the applicability to include an

additional airplane, and reduces compliance times for the initial inspection and repetitiv

intervals for Model 747-400 series airplanes that have been converted to the large cargo

freighter configuration. This AD results from findings of cracking in fuselage stringers

stringers 8L, 8R, IOL, and lOR at body 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 in fuselage

applies to certain Boeing Model 747-100B sun, -200B, -300, -400, and -400D series

ACTION: Final rule.

AGENCY: Federal Aviation Administration (FAA), Department of Transportation

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

14 CFR Part 39

:Amendment 39-**; AD H)

undetected, could result in fuselage skin cracking that reduces the structural integrity of

the skin panel, and consequent rapid depressurization of the airplane.

DATES: This AD becomes effective [i&sert date 35 days after date of publication in th

tlmAI.S/S1G

FEDERAL REGISTER].
[4910-I3-U]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA l004 191'79\ Directorate Identifier2009-NM-031-AD;

fltJl'Ylil .

.~

D

RIN 2120-AA64

Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of Transportation

/JlJm1Z!b I

f'lrn.o.LS,IS1G

Airworthiness Directives; Boeing Model 747-100B SUD, -200B, -300, -400, and -400 1 L'

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;Amendment 39-**; AD **]

(DOl).

ACTION: Final rule. ';n 'if.

SUMMARY: The FAA is superseding an existing airworthiness directive (AD), which '-

applies to certain Boeing Model 747-1 OOBSUD, -200B, -300, -400, and -400D series

airplanes. That AD currently requires repetitive inspections for cracking in fuselage

stringers 8L, 8R, IOL, and lOR at body stations 460, 480, and 500 frame I"""tions; and

repair if necessary .. This new AD requires revising the applicability to include an

additional airplane, and reduces compliance times for the inltial inspection and repetitiv

intervals for Model 747-400 series airplanes that have been converted to the large cargo

OU11!'lG $'iHilOL

l..C

freighter configuration. lbis AD results from fmdings of cracking in fuselage stringers

8L,8R, 10L, and lOR at body stations 460, 480, and 500 frame locations. We are iss .

m

this AD to detect and correct fatigue cracking in certain fuselage stringers, which, if left

undetected, could result in fuselage skin cracking that reduces the structural integrity of .

the skin panel, and consequent rapid depressurization of the airplane.

DATES: This AD becomes effective [J.sert date 35 days after date of publication in th

FEDERAL REGISTER].