95-04-07: Lockwires on Engine Mount Bolts

95-04-07 MCDONNELL DOUGLAS: Amendment 39-9159. Docket 94-NM-253-AD.\n\n\tApplicability: Model DC-10-30 airplanes on which bolt retainers have not been installed on the engine mount in accordance with McDonnell Douglas DC-10 Service Bulletin 71-133, Revision 6, dated June 30, 1992; Model DC-10-10 and -15 airplanes; and KC-10A (military) airplanes; certificated in any category.\n\n\tNOTE 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 (c) 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 conditiondescribed 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.\n\n\tCompliance: Required as indicated, unless accomplished previously.\n\n\tTo prevent broken lockwires, which could result in loosening of the engine mount bolts and subsequent separation of the engine from the airplane, accomplish the following:\n\n\t(a)\tWithin 120 days after the effective date of this AD, unless accomplished previously within the last 750 flight hours prior to the effective date of this AD, perform a visual inspection to detect broken lockwires on the forward engine mount bolts on engines 1, 2, and 3, in accordance with McDonnell Douglas Alert Service Bulletin DC10-71A159, Revision 1, dated January 31, 1995.\n\n\t\t(1)\tIf no lockwire is found broken, repeat the inspection thereafter at intervals not to exceed 750 flight hours.\n\n\t\t(2)\tIf any lockwire is found broken, prior to further flight, check the torque of the bolt, install a new lockwire, and install a torque stripe on the bolt, in accordance with the alert service bulletin. Thereafter at intervals not to exceed 750 flight hours, perform a visual inspection to detect misalignment of the torque stripes, and repeat the inspection to detect broken lockwires, in accordance with the alert service bulletin.\n\n\t(b)\tSubmit a report of findings of broken lockwires and/or misaligned torque stripes found during the inspections required by paragraph (a) of this AD to the Manager, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Boulevard, Lakewood, California 90712; or fax to (310) 627-5210, at the times specified in either paragraph (b)(1) or (b)(2) of this AD, as applicable. The report must include the manufacturer's fuselage number of the airplane, number of cycles on the airplane, torque value of the bolt, and condition of the lockwire (i.e, broken or intact). Information collection requirements contained in this regulation have been approved by the Office of Management and Budget (OMB) under the provisions of the Paperwork Reduction Act of 1980 (44 U.S.C. 3501 et seq.) and have been assigned OMB Control Number 2120-0056.\n\n\t\t(1)\tFor airplanes on which the inspections are accomplished after the effective date of this AD: Submit reports within 30 days after finding any discrepancy.\n\n\t\t(2)\tFor airplanes on which the inspections have been accomplished prior to the effective date of this AD: Submit the initial report within 30 days after the effective date of this AD, and subsequent reports within 30 days after finding any discrepancy.\n\n\t(c)\tFor Model DC-10-30 airplanes and KC-10A (military) airplanes only: Installation of retainers on the engine mount bolts in accordance with Figure 6 of Revision 6 of McDonnell Douglas DC-10 Service Bulletin 71-133, dated June 30, 1992, constitutes terminating action for the requirements of this AD.\n\n\t(d)\tAn 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 Aircraft Certification Office (ACO), FAA, Transport Airplane Directorate. 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.\n\n\tNOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO.\n\n\t(e)\tSpecial 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.\n\n\t(f)\tThe inspections shall be done in accordance with McDonnell Douglas Alert Service Bulletin DC10-71A159, Revision 1, dated January 31, 1995. The installation shall be done in accordance with McDonnell Douglas DC-10 Service Bulletin 71-133, Revision 6, dated June 30, 1992. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from McDonnell Douglas Corporation, P.O. Box 1771, Long Beach, California 90801-1771, Attention: Business Unit Manager, Technical Administrative Support, Department L51, M.C. 2-98. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at 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.\n\n\t(g)\tThis amendment becomes effective on March 17, 1995.