AD 2007-25-16 Airworthiness Directives; McDonnell Douglas Model DC-9-81 (MD-81) and DC-9-82 (MD-82) Airplanes

This AD applies to McDonnell Douglas Model DC-9-81 (MD-81) and DC-9-82 (MD-82) airplanes; certificated in any category; as identified in Boeing Alert Service Bulletin MD80-53A298, dated August 1, 2006.

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 Corrective Actions for Configuration 1, 2, and 3 Airplanes (f) For airplanes identified as Configuration 1, 2, or 3 in Boeing Alert Service Bulletin MD80-53A298, dated August 1, 2006: At the applicable times specified in paragraph 1.E., “Compliance,” of the alert service bulletin, do a low-frequency eddy current (LFEC) or high-frequency eddy current (HFEC) inspection, as applicable, for cracking of the fuselage skin at the upper corners of the forward passenger doorjamb; and do all applicable corrective actions (repetitive inspections, installation of doublers, replacements, and repairs), except as provided by paragraph (g) of this AD. Do the actions in accordance with the Accomplishment Instructions of the alert service bulletin. Where the alert service bulletin specifies a compliance time after the date on the service bulletin, this AD requires compliance within the specified compliance time after the effective date of this AD. Repair of Certain Conditions (g) If any crack is found during any inspection required by paragraph (f) of this AD and Boeing Alert Service Bulletin MD80-53A298, dated August 1, 2006, specifies to contact Boeing for repair instructions: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (i) of this AD. Corrective Action for Configuration 4 Airplanes (h) For airplanes identified as Configuration 4 in Boeing Alert Service Bulletin MD80-53A298, dated August 1, 2006: Within 90 days after the effective date of this AD, repair using a method approved in accordance with the procedures specified in paragraph (i) of this AD. 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 the Accomplishment Instructions of Boeing Alert Service Bulletin MD80-53A298, dated August 1, 2006, 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 this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1-L5A (D800-0024). (3) You may review copies of the service information incorporated by reference 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/code_of_federal_regulations/ibr_locations.html . Issued in Renton, Washington, on November 29, 2007. Stephen P. Boyd, Assistant Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E7-23687 Filed 12-7-07; 8:45 am] BILLING CODE 4910-13-P

This AD results from a report of fatigue cracking in the fuselage skin at the upper corners of the forward passenger doorjamb. We are issuing this AD to prevent cracking of the fuselage skin at the upper corners of the forward passenger doorjamb, which could lead to loss of overall structural integrity of the airplane.