AD 2007-10-04 Airworthiness Directives; McDonnell Douglas 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 all McDonnell Douglas 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.

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 (f) Do eddy current inspections to detect cracks in the horizontal stabilizer, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin MD80-55A065, dated April 25, 2007. (1) Do the initial inspections before the accumulation of 20,000 total flight cycles, or within 854 flight cycles after the effective date of this AD, whichever occurs later. (2) Except as required by paragraphs (g) and (h) of this AD: Do all applicable repetitive inspections and related investigative and corrective actions in accordance with, and at the times specified in, the service bulletin. Exceptions to Service Bulletin Specifications (g) Where Boeing Alert Service Bulletin MD80-55A065, dated April 25, 2007, specifies inspecting any skin panel splice or cap splice installed as part of a crack repair option: This AD requires the initial inspection within the compliance time specified in the service bulletin, but the inspection type, method, and repetitive interval must be done with FAA approval in accordance with the procedures specified in paragraph (i) of this AD. (h) For airplanes on which any detected crack meets the Condition 2 criteria specified in Table 1 or Table 3 in paragraph 1.E. of Boeing Alert Service Bulletin MD80-55A065, dated April 25, 2007: If Option 1 or 2 is selected as the corrective action, either install a horizontal stabilizer aft skin panel splice or remove and replace the horizontal stabilizer aft skin panel within 4,000 flight cycles after accomplishing Option 1 or 2, in accordance with Option 3 or 4 of the applicable table, and repeat the inspection thereafter at the time specified in Option 3 or 4, as applicable. Alternative Methods of Compliance (AMOCs) (i)(1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (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. (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, Los Angeles ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane and 14 CFR 25.571, Amendment 45, and the approval must specifically refer to this AD. Material Incorporated by Reference (j) You must use Boeing Alert Service Bulletin MD80-55A065, dated April 25, 2007, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of this document in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1-L5A (D800-0024), for a copy of this service information. You may review copies at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 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/cfr/ibr-locations.html. Issued in Renton, Washington, on May 1, 2007. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-8768 Filed 5-7-07; 8:45 am] BILLING CODE 4910-13-P

This AD results from reports of cracks found in the horizontal stabilizer—in the upper and lower aft skin panels at the aft inboard corner at station XH = 8.2, and in the rear spar upper caps adjacent to the aft skin panel at station XH = 10.0. We are issuing this AD to detect and correct cracks in the upper and lower aft skin panels and rear spar upper caps, which, if not corrected, could lead to the loss of overall structural integrity of the horizontal stabilizer.