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## ,~ PUBLICATION INTHE FEDERAL REGISTER]. DATES: This AD is effective [INSERT DATE 35 DAYS AFTER DATE OF accelerate skin crack growth and could result inrapid decompression ofthe fuselage. This reduced structural integrity can increase loading in the fuselage skin, which will night cycle stresses from bothpressurization and maneuver loads. We are issuing this A to detect and correct fatigue cracking ofcertain fuselage frames and stub beams and possible severed frames, which could result inreduced structural integrity ofthe frame-s and corrective actions ifnecessary. This AD results from repOits ofthe detection of requires repetitive inspections for cracking ofcertain fuselage frames and stub beams, repetitive inspections. For aiIplanes on which acertain repair is done, this AD also necessary. 1l1isAD also provides foran optional repair, which would terminate the DEPARTMENT OF TRANSPORTATION

fatigue cracks at c,ertainframe sections, inaddilion to stub beam cracking, caused by hig 737-200, ·300, -400, and -500 series airplanes. This AD requires repetitive inspections for cracking ofcertain fuselage frames and stub beams, and corrective actions if Federal Aviation Administration

AGENCY: Federal Aviation Administration (FAA), DOT. RIN 2120-AA64

SUMMARY: We are adopting anew aif\vorthiness directive (AD) 

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Ain,"ol-thincss Directives; The Boeing Company Model 737-200, -300, -400, and -500 Series Airplanes

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### This reduced structural integrity can increase loading inthe fuselage skin, which will accelerate skin crack growth and could result inrapid decompression ofthe fuselage. DATES: This AD iseffective [INSERT DATE 35 DAYS AFTER DATE OF PUBLICATION INTHE FEDERAL REGISTEh{49JO-I3-Pj DEPARTMENT OF TRANSPORT AnON Federal Aviation Administration 14CFR Par) 39 INIIlAlS/S'" rDocket No. FAA-2010-0437; Directorate Ideo ifier2009-NM-130-AD; Amendmc 

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### ovn"".........."". eFT-. requires repetitive inspections for cracking of certain fuselage frames and stub beams, 'mnAlS/S AGENCY: Federal Aviation Administration (FN.I\), DOT. ACTION: Final rule.

and corrective actions ifnecessary. This AD results from reports ofthe detection of fatigue cracks at certain frame sectiolls, inadditiln to stub beam cracking, caused by flight cycle Slresses from both pressurization

# animaneuver loads. We are issuing this to detect and correct fatigue cracking of certain sciage frames and stub beams and SUMMARY: We are adopting anew ainvorthiness directive (AD) for certain Model 737-200, -300, ADO,and -500 series airplanes. This AD requires repetitive inspection I for cracking ofcertain fuselage frames and stub ~eams, and corrective actions 

### if necessary. This AD also provides for an optional repair, which would tem1inate the

possible severed frames, which could result in reduced structural integrity ofthe fram This reduced structural integrity can increase loa1ing inthe fuselage skin, which will accelerate skin crack growth and could result inrapid decompression ofthe fuselage. 

# , DATES: This .W is effective [INSERT DATE 35 DAYS AFTER DATE OF PUBLICATION IN THE FEDERAL REGISTER]. 

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## 1491O-13-PI DEPARTMENT OF TRANSPORT ATlON Federal Aviation Administration 14CFR Part 39 'Nrn••• s/S'G IDocket No. FAA-2010-0437; Directorate Idenrifier 2009-NM-130·ADj Amcndmc 

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llGSW,OOl fatigue cracks at certain frame sections, in addition to stub beam cracking, caused by I. and corrective actions ifnecessary. This AD results from reports ofthe detection of requires repetitive inspections for cracking of certain fuselage frames and stub beams, INln necessary. This AD also provides for an optional repair, which would terminate the repetitive inspections. For airplanes on which acertain repair is done, this AD also for cracking of certain fuselage frames and shlb beams, and corrective actions if ovr.'G 5'. w, RIN 2120-AA64 

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# 1.0 AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. SUMMARY: We are adopting a new ainvorthiness directive (AD) for certain Model 737-200, ··]00, -400, and -500 series airplanes. This AD requires repetitive inspection

flight cycle stresses from both pressurization and maneuver loads. We are issuing this, -D'S/5!l> to detect and correct fatigue cracking ofcertain fuselage frames and stub beams and possible severed frames, which could result inreduced structural integrity ofthc fram This reduced struchual integrity can inc'rease loading inthe fuselage skin, which will J~J "AC<!SJG accelemte skin crack growth and could result in rapid decompression orthe fuselage. AlE DATES: This AD is effective [INSERT DATE 35 DAYS APTER DATE OF PUBLICATION IN THE FEDERAL REGISTER].