# Proposed AD FAA-2007-0184: Boeing Model 737-100, -200, -200C, - 300, -400, and -500 Series Airplanes

- Type: Proposed airworthiness directive (not in force)
- Status: Became AD 2008-13-12
- Products: Boeing
- Product type: Aircraft
- Action: Notice of proposed rulemaking (NPRM).
- Published: November 13, 2007, 72 FR 63831
- Comments due: December 28, 2007
- Became: [AD 2008-13-12](https://openairdocs.org/ad/2008-13-12)
- Docket: FAA-2007-0184 (https://www.regulations.gov/docket/FAA-2007-0184, where comments are filed)
- Project: 2007-NM-140-AD
- FR document: E7-22104
- Official PDF: https://openairdocs.org/files/sha256/cf/a8/cfa8ad47d8977b317e391971999a120a5ca0c34171fae4511b3cb0419e055ecf (from https://www.govinfo.gov/content/pkg/FR-2007-11-13/pdf/E7-22104.pdf)
- Federal Register: https://www.federalregister.gov/documents/2007/11/13/E7-22104/airworthiness-directives-boeing-model-737-100--200--200c--300--400-and--500-series-airplanes
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/14EC9336EAA616B5862573920060D0C8.0001
- Page: https://openairdocs.org/proposed/FAA-2007-0184

## Summary

The FAA proposes to adopt a new airworthiness directive (AD) for certain Boeing Model 737-100, -200, -200C, -300, -400, and -500 series airplanes. This proposed AD would require various repetitive inspections for cracking of the upper frame to side frame splice of the fuselage, and other specified and corrective actions if necessary. This proposed AD also provides for an optional preventive modification, which would terminate the repetitive inspections. This proposed AD results from a report that the upper frame of the fuselage was severed between stringers S-13L and S-14L at station 747, and the adjacent frame at station 767 had a 1.3-inch-long crack at the same stringer location. We are proposing this AD to detect and correct fatigue cracking of the upper frame to side frame splice of the fuselage, which could result in reduced structural integrity of the frame and adjacent lap joint. This reduced structural integrity can increase loading in the fuselage skin, which will accelerate skin crack growth and result in decompression of the airplane.

## Notices in this docket

- Nov 13, 2007: Notice of proposed rulemaking (NPRM). (first notice), FR document E7-22104, comments due Dec 28, 2007 (https://www.federalregister.gov/documents/2007/11/13/E7-22104/airworthiness-directives-boeing-model-737-100--200--200c--300--400-and--500-series-airplanes)

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