AD 2006-07-08 Airworthiness Directives; McDonnell Douglas Model DC-9-10, DC-9-20, DC-9-30, DC-9-40, and DC-9-50 Series Airplanes

This AD applies to McDonnell Douglas Model DC-9-11, DC-9-12, DC-9-13, DC-9-14, DC-9-15, DC-9-15F, 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 identified in McDonnell Douglas DC-9 Service Bulletin 53-168, dated November 17, 1983.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Service Bulletin Reference (f) The term “service bulletin,” as used in this AD, means the Accomplishment Instructions of McDonnell Douglas DC-9 Service Bulletin 53-168, dated November 17, 1983, including McDonnell Douglas Service Sketch 3529, dated August 23, 1983. Repetitive Inspections and Corrective Actions (g) Prior to the accumulation of 15,000 total flight hours, or within 3,400 flight hours after the effective date of this AD, whichever occurs later: Do a detailed inspection, eddy current inspection, or ultrasonic inspection for stress corrosion cracks of the main fuselage frame in accordance with the service bulletin. Except as provided by paragraph (h) of this AD, repeat the inspection thereafter at intervals not to exceed 8,000 flight hours until the replacement in paragraph (i) of this AD is accomplished. Note 1: For the purposes of this AD, a detailed inspection is: “An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.” Corrective Actions (h) If any crack is found during any inspection required by this AD, do the applicable action in paragraph (h)(1), (h)(2), or (h)(3) of this AD. (1) If the crack is in the pocket area and the crack is within the crack limits specified in McDonnell Douglas Service Sketch 3529, dated August 23, 1983: Repeat the inspection specified in paragraph (g) of this AD at intervals not to exceed 3,400 flight hours until the action in paragraph (i) of this AD is accomplished. (2) If the crack is in the pocket area and the crack exceeds the crack limits specified in McDonnell Douglas Service Sketch 3529, dated August 23, 1983, before further flight: Do the action in paragraph (i) of this AD. (3) If the crack is in the web, before further flight: Do the action in paragraph (i) of this AD. Optional Terminating Action (i) Replacing the frame with a new or serviceable frame made of 7075-T73 aluminum material in accordance with the service bulletin terminates the repetitive inspection requirements of this AD for that frame only. No Reporting Required (j) Although the service bulletin referenced in this AD specifies to submit certain information to the manufacturer, this AD does not include that requirement. Parts Installation (k) After the effective date of this AD, no person may install on any airplane a main fuselage frame made of 7075-T6 aluminum material. Alternative Methods of Compliance (AMOCs) (l)(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) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Material Incorporated by Reference (m) You must use McDonnell Douglas DC-9 Service Bulletin 53-168, dated November 17, 1983, including McDonnell Douglas Service Sketch 3529, dated August 23, 1983, to perform the actions that are required by this AD, unless the AD specifies otherwise. (The issue date of the service sketch is shown only on the first sheet of that document.) The Director of the Federal Register approved the incorporation by reference of these documents 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 Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., Room PL-401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov ; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the 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 March 22, 2006. Michael Zielinski, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 06-3061 Filed 3-30-06; 8:45 am] BILLING CODE 4910-13-P

This AD results from several reports of cracking of the main fuselage frame. We are issuing this AD to detect and correct stress corrosion cracking of the main fuselage frame, which could result in extensive damage to adjacent structure, and reduced structural integrity of the airplane.