AD 95-13-11 Airworthiness Directives; McDonnell Douglas Model DC-10-10 Airplanes

Models named: DC-10-10. Read the applicability below — it usually turns on serial or part numbers too.

Model DC-10-10 airplanes, as listed in McDonnell Douglas DC-10 Service Bulletin 57-129, dated August 12, 1994; certificated in any category. Note 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must use the authority provided in paragraph (e) of this AD to request approval from the FAA. This approval may address either no action, if the current configuration eliminates the unsafe condition; or different actions necessary to address the unsafe condition described in this AD. Such a request should include an assessment of the effect of the changed configuration on the unsafe condition addressed by this AD. In no case does the presence of any modification, alteration, or repair remove any airplane from the applicability of this AD.

Required as indicated, unless accomplished previously. To prevent reduced structural integrity of the wing front spar and damage to adjacent structures due to fatigue cracking in the upper cap of the front spar of the wing, accomplish the following: (a) Prior to the accumulation of 10,000 total landings, or within 1,800 landings after the effective date of this AD, whichever occurs later, perform an initial eddy current test high frequency (ETHF) surface inspection to detect cracks in the upper cap of the front spar of the left and right wing at stations Xos 667.678 and Xos 789.645, in accordance with McDonnell Douglas DC-10 Service Bulletin 57-129, dated August 12, 1994. Repeat this inspection thereafter at the intervals specified in paragraph (b) or (c) of this AD, as applicable. (b) For airplanes on which no crack is found: Repeat the inspection required by paragraph (a) of this AD thereafter at intervals not to exceed 10,000 landings, or accomplish the crack preventative modification in accordance with McDonnell Douglas DC-10 Service Bulletin 57-129, dated August 12, 1994. Accomplishment of that preventative modification constitutes terminating action for the requirements of this paragraph. (c) For airplanes on which any crack is found that is identified as ``Condition II'' in McDonnell Douglas DC-10 Service Bulletin 57- 129, dated August 12, 1994: Accomplish paragraphs (c)(1) and (c)(2) of this AD in accordance with that service bulletin. (1) Prior to further flight, perform the permanent repair for cracks in accordance with the service bulletin; and (2) Within 12,500 landings after the installation of the permanent repair specified in paragraph (c)(1) of this AD, perform an ETHF surface inspection for cracks, in accordance with the service bulletin. Repeat this inspection thereafter at intervals not to exceed 7,000 landings. (d) For airplanes on which any crack is found that is identified as ``Condition III'' in McDonnell Douglas DC-10 Service Bulletin 57- 129, dated August 12, 1994: Prior to further flight, repair the cracking in accordance with a method approved by the Manager, Los Angeles Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. (e) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, Los Angeles ACO. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, Los Angeles ACO. Note 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO. (f) Special flight permits may be issued in accordance with sections 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished. (g) The inspections, modification, and permanent repair shall be done in accordance with McDonnell Douglas DC-10 Service Bulletin 57- 129, dated August 12, 1994. This incorporation by reference was approved previously by the Director of the Federal Register, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51 as of August 7, 1995 (60 FR 35326, July 7, 1995). Copies may be obtained from McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Technical Publications Business Administration, Department C1-L51 (2-60). Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Transport Airplane Directorate, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. (g) This amendment is effective on August 7, 1995. Issued in Renton, Washington, on January 22, 1996. Darrell M. Pederson, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 96-1569 Filed 1-29-96; 8:45 am] BILLING CODE 4910-13-U