AD 2011-17-11 Airworthiness Directives; The Boeing Company Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 Airplanes

This AD applies to The Boeing Company Model DC-9-81 (MD-81), DC-9-82 (MD-82), DC-9-83 (MD-83), DC-9-87 (MD-87), and MD-88 airplanes, certificated in any category; as identified in Boeing Alert Service Bulletin MD80-57A242, Revision 1, dated January 7, 2011.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Repetitive Inspections and Related Investigative and Corrective Actions (g) At the applicable times specified in paragraph 1.E. of Boeing Alert Service Bulletin MD80-57A242, Revision 1, dated January 7, 2011, do the actions required by paragraphs (g)(1) and (g)(2) of this AD, except as required by paragraph (i) of this AD. The actions specified in paragraphs (g)(1) and (g)(2) of this AD are not required for Group 1, Configuration 1 airplanes, as identified in Boeing Alert Service Bulletin MD80-57A242, Revision 1, dated January 7, 2011. (1) Do initial and repetitive eddy current testing high frequency (ETHF) inspections for cracking of the lower rear spar caps of the wings, and do all applicable related investigative and corrective actions, by doing all the applicable actions specified in the Accomplishment Instructions of Boeing Alert Service Bulletin MD80-57A242, Revision 1, dated January 7, 2011; or in accordance with the procedures specified in paragraph (k) of this AD. (2) Do initial and repetitive ETHF inspections for cracking of any doubler repairs, and do all applicable related investigative and corrective actions, by doing all the applicable actions specified in the Accomplishment Instructions of Boeing Alert Service Bulletin MD80-57A242, Revision 1, dated January 7, 2011; except as required by paragraph (j) of this AD. Credit for Actions Accomplished in Accordance With Previous Service Information (h) Actions done before the effective date of this AD in accordance with Boeing Alert Service Bulletin MD80-57A242, dated May 8, 2009, are acceptable for compliance with the corresponding requirements of this AD. Exceptions to Service Bulletin Specifications (i) Where Boeing Alert Service Bulletin MD80-57A242, Revision 1, dated January 7, 2011, specifies a compliance time after the date of that service bulletin, this AD requires compliance within the specified compliance time after the effective date of this AD. (j) If any crack is found during any inspection of a doubler repair, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (k) of this AD. Alternative Methods of Compliance (AMOCs) (k)(1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. (2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/certificate holding district office. (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 the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Los Angeles ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane. Related Information (l) For more information about this AD, contact Roger Durbin, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712-4137; phone: (562) 627-5233; fax: (562) 627-5210; e-mail: roger.durbin@faa.gov . Material Incorporated by Reference (m) You must use Boeing Alert Service Bulletin MD80-57A242, Revision 1, dated January 7, 2011; to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of the service information contained in this AD under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, Boeing Commercial Airplanes, Attention: Data & Services Management, 3855 Lakewood Boulevard, MC D800-0019, Long Beach, California 90846-0001; telephone 206-544-5000, extension 2; fax 206-766-5683; e-mail dse.boecom@boeing.com; Internet https://www.myboeingfleet.com . (3) You may review copies of the service information 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. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at an NARA facility, call 202-741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Issued in Renton, Washington, on August 8, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011-20672 Filed 8-19-11; 8:45 am] BILLING CODE 4910-13-P

This AD was prompted by reports of cracking of the wing rear spar lower cap at the outboard flap and inboard drive hinge at station Xrs=164.000; the cracking is due to material fatigue from normal flap operating loads. We are issuing this AD to detect and correct fatigue cracking, which could result in fuel leaks, damage to the wing skin or other structure, and consequent reduced structural integrity of the wing.