AD 2005-07-19 Airworthiness Directives; Boeing Model 737-100, -200C, -300, -400, and -500 Series Airplanes

Models named: 737-100, -200, -200C, -300, -400, -500 series. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to all Model 737-100, -200, -200C, -300, -400, and -500 series airplanes; certified in any category.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Initial and Repetitive Inspections/Corrective Action (f) Do the applicable detailed, general visual, and low-, mid-, and high-frequency eddy current inspections for cracks in the fuselage skin, doubler, bearstrap, and frames surrounding the main, forward, and aft cargo doors, and for cracks in existing repairs, as specified in Tables 1, 2, and 3, as applicable, of paragraph 1.E., “Compliance,” of Boeing Alert Service Bulletin 737-53A1228, dated July 10, 2003. Do the inspections at the initial compliance times listed in Tables 1, 2, and 3, as applicable, of paragraph 1.E., “Compliance,” of the service bulletin; except, where the service bulletin specifies a compliance time after the service bulletin date, this AD requires compliance within the specified compliance time after the effective date of this AD. Do the inspections in accordance with the Accomplishment Instructions of the service bulletin. Repeat the inspections within the repetitive inspection intervals listed in Tables 1, 2, 3 of paragraph 1.E., “Compliance,” of the service bulletin. Accomplishing the requirements in this paragraph ends the requirements in AD 93-14-10, amendment 39-8634 (58 FR 43547. August 17, 1993). Note 1: At existing repairs around the forward and aft cargo door cutouts: The location for the specified detailed or mid-frequency eddy current inspections for cracking of the skin or bearstrap is at the outer row of fasteners common to the repair, as illustrated in Figures 8, 9, and 10 of Boeing Alert Service Bulletin 737-53A1228, dated July 10, 2003. (g) If any crack is found during any inspection: Repair before further flight in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-53A1228, dated July 10, 2003. Where the service bulletin specifies contacting the manufacturer for disposition of certain repair conditions, repair before further flight in accordance with a method approved by the Manager, Seattle Aircraft Certification Office (ACO), FAA; or an Authorized Representative for the Boeing Delegation Option Authorization (DOA) Organization who has been authorized by the Manager, Seattle ACO, to make such findings. For a repair method to be approved, the approval must specifically refer to this AD. No Reporting Required (h) Although the service bulletin referenced in this AD recommends reporting any discrepancies to the manufacturer, this AD does not include that requirement. Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, Seattle ACO, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by an Authorized Representative for the Boeing DOA Organization who has been authorized by the Manager, Seattle ACO, to make those findings. Material Incorporated by Reference (j) You must use Boeing Alert Service Bulletin 737-53A1228, dated July 10, 2003, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approves the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. For copies of the service information, contact Boeing Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124-2207. For information on the availability of this material at the National Archives and Records Administration (NARA), call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. You may view the AD docket at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street, SW., room PL-401, Nassif Building, Washington, DC. Issued in Renton, Washington, on March 30, 2005. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-6763 Filed 4-6-05; 8:45 am] BILLING CODE 4910-13-M

This AD was prompted by reports of multiple fatigue cracks in the fuselage skin and bonded skin doubler, bearstrap, and doorway frames surrounding the forward and aft cargo doors. We are issuing this AD to find and fix fatigue cracking in the fuselage skin, doubler, bearstrap, and frames, which could result in reduced structural integrity of the frames, possible loss of a cargo door, and consequent rapid decompression of the fuselage.