AD 2004-23-11 Airworthiness Directives; McDonnell Douglas Model DC-9-14 and DC-9-15 Airplanes; and Model DC-9-20, DC-9-30, DC-9-40, and DC-9-50 Series Airplanes

This AD applies to certain McDonnell Douglas Model DC-9-14, DC-9-15, DC-9-21, DC-9-31, DC-9-32, DC-9-32 (VC-9C), DC-9-32F, DC-9-33F, DC-9-34, DC-9-34F, DC-9-32F (C-9A, C-9B), DC-9-41, and DC-9-51 airplanes, certificated in any category; as listed in Boeing Service Bulletin DC9-57-223, dated July 21, 2003.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Inspection (f) At the later of the times specified in paragraph (f)(1) or (f)(2) of this AD: Do a high frequency eddy current inspection to detect cracks in the vertical radius of the upper cap of the center wing rear spar, in accordance with the Accomplishment Instructions of Boeing Service Bulletin DC9-57-223, dated July 21, 2003. (1) Before the accumulation of 25,000 total flight cycles. (2) Within 15,000 flight cycles or 5 years after the effective date of this AD, whichever occurs first. Corrective Action (g)(1) If no crack is found, then repeat the inspection thereafter at intervals not to exceed 15,000 flight cycles or 5 years, whichever occurs first. (2) If any crack is found, before further flight, repair per a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA. For a repair method to be approved by the Manager, Los Angeles ACO, as required by this paragraph, the Manager's approval letter must specifically refer to this AD. Alternative Methods of Compliance (AMOCs) (h) The Manager, Los Angeles ACO, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. Material Incorporated by Reference (i) You must use Boeing Service Bulletin DC9-57-223, dated July 21, 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, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. CI-L5A (D800-0024). 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 November 1, 2004. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-24934 Filed 11-12-04; 8:45 am] BILLING CODE 4910-13-M

This AD was prompted by reports of cracks in the upper cap of the center wing rear spar that resulted from stress corrosion. We are issuing this AD to detect and correct cracking of the left or right upper cap of the center rear spar, which could cause a possible fuel leak and structural failure of the upper cap, and result in reduced structural integrity of the airplane.