2009-02-06: Fuselage frame and frame reinforcement

2009-02-06 Boeing: Amendment 39-15796. Docket No. FAA-2008-0671; Directorate Identifier 2008-NM-017-AD. \n\nEffective Date \n\n\t(a) This airworthiness directive (AD) is effective April 15, 2009. \n\nAffected ADs \n\n\t(b) None. \n\nApplicability \n\n\t(c) This AD applies to Boeing Model 737-300, -400, and -500 series airplanes, certificated in any category; as identified in Boeing Alert Service Bulletin 737-53A1279, dated December 18, 2007. \n\nUnsafe Condition \n\n\t(d) This AD results from reports of cracking in the frame, or in the frame and frame reinforcement, common to the 1.04-inch nominal diameter wire penetration hole intended for wire routing. We are issuing this AD to detect and correct cracking in the fuselage frames and frame reinforcements, which could reduce the structural capability of the frames to sustain limit loads, and result in cracking in the fuselage skin and subsequent rapid depressurization of the airplane. \n\nCompliance \n\n\t(e) Comply with this AD within thecompliance times specified, unless already done. \n\nService Bulletin Reference Paragraph \n\n\t(f) The term "service bulletin,'' as used in this AD, means the Accomplishment Instructions of Boeing Alert Service Bulletin 737- 53A1279, dated December 18, 2007. \n\t(1) The "condition'' column of paragraph 1.E. of Boeing Alert Service Bulletin 737-53A1279, dated December 18, 2007, refers to total flight cycles "at the date given on this service bulletin.'' This AD applies to the airplanes with the specified total flight cycles as of the effective date of this AD. \n\t(2) Where the service bulletin specifies to contact Boeing for instructions for removing damage and repairing cracking: Before further flight, remove the damage or repair the cracking using a method approved in accordance with the procedures specified in paragraph (i) of this AD. \n\t(3) Although the service bulletin referenced in this AD specifies to submit information to the manufacturer, this AD does not include that requirement. \n\nInspections, Related Investigative and Corrective Actions \n\n\t(g) At the applicable time specified in paragraph 1.E., "Compliance,'' of the service bulletin, except as specified by paragraph (f)(1) of this AD: Do a high frequency eddy current (HFEC) surface inspection or an HFEC hole/edge inspection for cracking of the 1.04-inch nominal diameter wire penetration hole in the frame and frame reinforcement, between stringer S-20 and S-21; and do all applicable related investigative and corrective actions; by accomplishing all the actions specified in the Accomplishment Instructions of the service bulletin, except as specified by paragraphs (f)(2) and (f)(3) of this AD. Do all applicable related investigative and corrective actions before further flight. Thereafter, repeat the inspections at the applicable intervals specified in paragraph 1.E. of the service bulletin. \n\nTerminating Action \n\n\t(h) Doing the repair in Part 3 or the preventative modification in Part 5 of the service bulletin terminates the repetitive inspection requirements of this AD. \n\nAlternative Methods of Compliance (AMOCs) \n\n\t(i)(1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, ATTN: Wayne Lockett, Aerospace Engineer, Airframe Branch, ANM- 120S, 1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 917-6447; fax (425) 917-6590; has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. \n\t(2) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Before using any approved AMOC on any airplane to which the AMOC applies, notify your appropriate principal inspector (PI) in the FAA Flight Standards District Office (FSDO), or lacking a PI, your local FSDO. \n\t(3) 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 Commercial Airplanes Delegation Option Authorization Organization who has been authorized by the Manager, Seattle ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. \n\nMaterial Incorporated by Reference \n\n\t(j) You must use Boeing Alert Service Bulletin 737-53A1279, dated December 18, 2007, to do the actions required by this AD, unless the AD specifies otherwise. \n\t(1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. \n\t(2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, Washington 98124-2207; telephone 206-544-5000, extension 1, fax 206-766-5680; e-mail [email protected]; Internet https://www.myboeingfleet.com. \n\t(3) You may review copies of the service information incorporated by reference at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call 425-227-1221 or 425-227-1152. \n\t(4) You may also review copies of the service information at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_ regulations/ibr_locations.html.