AD 2005-07-03 Airworthiness Directives; McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 Series Airplanes; and Model DC-9-81 (MD-81) and DC-9-82 (MD-82) Airplanes

Models named: DC-9-11, DC-9-12, DC-9-13, DC-9-14, DC-9-15, DC-9-15F, DC-9-21, DC-9-41, DC-9-51. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to the models listed in Table 1 of this AD, certificated in any category; as listed in McDonnell Douglas DC-9 Service Bulletin 57-179, Revision 1, dated December 21, 1994. Table 1.—Applicable Models   Model DC-9-11, DC-9-12, DC-9-13, DC-9-14, DC-9-15, and DC-9-15F, airplanes Model DC-9-21 airplanes Model DC-9-31, DC-9-32, DC-9-32, (VC-9C), DC-9-32F, DC-9-33F, DC-9-34, and DC-9-34F, DC-9-32F (C-9A, C-9B) airplanes Model DC-9-41 airplanes Model DC-9-51 airplanes Model DC-9-81 (MD-81), and DC-9-82 (MD-82) airplanes

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) Unless otherwise stated, the term “service bulletin”, as used in this Ad, means McDonnell Douglas DC-9 Service Bulletin 57-179, Revision 1, dated December 21, 1994. Inspection of the Upper and Lower Caps of the Rear Spar (g) At the time specified in paragraph (g)(1) or (g)(2) of this Ad, as applicable, do a detailed inspection of the upper and lower caps of the rear spar of the left and right wings at station Xrs = 267.000 for cracks in accordance with the Accomplishment Instructions of the service bulletin. (1) For Group 1 airplanes identified in paragraph 1.A.(1) of the service bulletin: Inspect prior to the accumulation of 50,000 total landings, or within 3,000 landings after the effective date of this AD, whichever occurs later. (2) For Group 2 airplanes identified in paragraph 1.A.(1) of the service bulletin: Inspect prior to the accumulation of 20,000 total landings, or within 3,000 landings after the effective date of this AD, whichever occurs later. Note 1: For the purposes of this AD, a detailed inspection is “An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.” No Crack Detected: Repetitive Inspections (h) If no crack is detected during any detailed inspection required by paragraph (g) of this AD, repeat the inspection thereafter at intervals not to exceed 3,000 landings until the crack preventative modification specified in paragraph (m) of this AD is done. Any Crack Detected: Corrective Actions (i) If any crack is detected during any detailed inspection required by paragraph (g) of this AD, before further flight, do the actions specified in paragraph (j) of this AD, except as provided by paragraph (k) of this AD. Permanent Repair Modification (j) If required by paragraph (i) of this AD, do the permanent repair modification for any cracked rear spar cap; and at the times specified in paragraph (j)(1) or (j)(2) of this AD, as applicable, do the detailed inspection specified in paragraph (g) of this AD. Do the actions in accordance with the Accomplishment Instructions of the service bulletin. (1) For Group 1 airplanes identified in paragraph 1.A.(1) of the service bulletin: Within 53,000 landings after accomplishing the permanent repair modification, do the detailed inspection. Repeat the detailed inspection thereafter at intervals not to exceed 3,000 landings until the crack preventative modification specified in paragraph (m) of this AD is done. (2) For Group 2 airplanes identified in paragraph 1.A.(1) of the service bulletin: Within 33,000 landings after accomplishing the permanent repair modification, do the detailed inspection. Repeat the detailed inspection thereafter at intervals not to exceed 3,000 landings until the crack preventative modification specified in paragraph (m) of this AD is done. Optional Temporary Repair Modification for Certain Cracking (k) In lieu of the actions specified in paragraph (j) of this AD, for any crack that does not exceed the limits specified in the Accomplishment Instructions of the service bulletin: Before further flight, do the temporary repair modification for any cracked rear spar cap; and at the times specified in paragraphs (k)(1) and (k)(2) of this AD, do the detailed inspections specified in paragraphs (k)(1) and (k)(2) of this AD. Do the actions in accordance with the Accomplishment Instructions of the service bulletin. (1) Within 1,500 landings after accomplishing the temporary repair modification, do a detailed inspection of the temporary repair for any new crack or crack progression and repeat the inspection thereafter at intervals not to exceed 1,500 landings until the permanent repair modification specified in paragraph (j) of this AD is done. (2) Within 3,000 landings after accomplishing the temporary repair modification, do detailed, eddy current, and ultrasonic inspections of the temporary repair for any new crack or crack progression and repeat the inspections thereafter at intervals not to exceed 3,000 landings until the permanent repair modification specified in paragraph (j) of this AD is done. (l) If any crack progression or new crack is detected during any inspection required by paragraph (k)(1) or (k)(2) of this AD, 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. Optional Terminating Crack Preventative Modification (m) Except as provided by paragraph (n) of this AD, accomplishment of the crack preventative modification in accordance with the applicable service bulletin listed in Table 2 of this AD ends the repetitive inspections required by this AD. If the applicable service bulletin specifies to contact the manufacturer for specific modification information: Repair per a method approved by the Manager, Los Angeles 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. Table 2.—Service Bulletins for Crack Preventative Modification For airplane model— Use McDonnell Douglas service bulletin— Model DC-9-10, -20, -30, -40, and -50 series airplanes; and Model DC-9-81 (MD-81) and DC-9-82 (MD-82) airplanes DC-9 Service Bulletin 57-160, dated December 7, 1987. Model DC-9-81 (MD-81), DC-9-82 (MD-82), and DC-9-83 (MD-83) airplanes MD-80 Service Bulletin 57-177, Revision 1, dated June 12, 1989. Model DC-9-82 (MD-82) airplanes MD-80 Service Bulletin 57-178, Revision 1, dated June 12, 1990. (n) For airplanes on which the temporary repair modification specified in paragraph (k) of this AD has been done: If accomplishing the crack preventative modification specified in paragraph (m) of this AD, before or concurrently with the crack preventative modification, do the permanent repair modification specified in paragraph (j) of this AD. Alternative Methods of Compliance (AMOCs) (o) 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 (p) You must use McDonnell Douglas DC-9 Service Bulletin 57-179, Revision 1, dated December 21, 1994, including McDonnell Douglas Service Sketch 3268D, approved February 20, 1984, 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. C1-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 March 21, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-6109 Filed 3-29-05; 8:45 am] BILLING CODE 4910-13-P

This AD was prompted by reports of fatigue cracks in the upper and lower caps of the wing spar. We are issuing this AD to detect and correct fatigue cracking in the upper and lower caps of the rear spar of the left and right wings, which could result in structural failure of the wings.