AD 95-04-07 R1 SUPERSEDED

This amendment clarifies information in an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10 series airplanes and KC-10A (military) airplanes, that currently requires inspections to determine the condition of the lockwires on the forward engine mount bolts and correction of any discrepancies found. That amendment also provides for termination of the inspections for some airplanes by installing retainers on the bolts. The actions specified in that AD are intended to prevent broken lockwires, which could result in loosening of the engine mount bolts, and subsequent separation of the engine from the airplane. This amendment clarifies the procedures for accomplishing the optional terminating action on engines 1, 2, and 3. This amendment is prompted by communications received from affected operators indicating that those procedures were unclear.\n\n\tThe incorporation by reference of certain publications listed in the regulations was approved previously by the Director of the Federal Register as of March 17, 1995 (60 FR 11617, March 2, 1995).

Final rule; correction.

95-04-07 R1 MCDONNELL DOUGLAS: Amendment 39-9317. Docket 94-NM-253-AD. Revises AD 95-04-07, Amendment 39-9159.\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 (d) 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.\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 of engines 1, 2, or 3 in accordancewith the procedures depicted in 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 for that engine.\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. The incorporation by reference of these documents was approved by the Director of the Federal Register, in accordance with 5 U.S.C. 552(a)and 1 CFR part 51, as of March 17, 1995 (60 FR 11617, March 2, 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, Los Angeles Aircraft Certification Office, Transport Airplane Directorate, 3960 Paramount Boulevard, Lakewood, California; or at the Office of theFederal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.\n\n\t(g)\tThis amendment is effective on March 17, 1995.

On February 16, 1995, the FAA issued AD 95-04-07, amendment 39-9159 (60 FR 11617, March 2, 1995), which is applicable to certain McDonnell Douglas Model DC-10-10, -15, and -30 airplanes, and KC-10A (military) airplanes. That AD requires visual inspections to determine the condition of the lockwires on the forward engine mount bolts on engines 1, 2, and 3, and correction of discrepancies found. That AD also requires that operators report the results of the visual inspections to the FAA. Additionally, that AD provides for the termination of the visual inspections by installing retainers on the engine mount bolts on Model DC-10-30 airplanes and KC-10A airplanes in accordance with Revision 6 of McDonnell Douglas DC-10 Service Bulletin 71-133, dated June 30, 1992. That action was prompted by reports indicating that the lockwires on the forward engine mount bolts were stretched or broken. The actions required by that AD are intended to prevent broken lockwires, which could result in loosening of the engine mount bolts, and subsequent separation of the engine from the airplane.\n\n\tSince the issuance of that AD, the FAA has received communication from affected operators indicating that the procedures for accomplishing the optional terminating action on engines 1, 2, and 3 are unclear. These operators have indicated that the service information contained in McDonnell Douglas DC-10 Service Bulletin 71-133, Revision 6, dated June 30, 1992 (which is referenced in the AD as the appropriate source of service information) does not describe procedures to accomplish the optional terminating action for engine 2. These operators have requested that the FAA clarify AD 95-04-07 to indicate exactly how to accomplish the optional terminating action for engine 2.\n\n\tIn considering this request, and upon further review of the procedures contained in that service bulletin, the FAA concurs that clarification is necessary.\n\n\tIt was the FAA's intent to include all engines in the provision for the optional terminating action. As such, the intent of paragraph (c) was to allow termination of the inspection for any engine on which retainers on the engine mount bolts had been installed. The FAA finds that although Figure 6 of the service bulletin does not describe procedures for installing retainers on the forward engine mount bolts on engine 2, the method for installing the retainers on engine 2 does not differ from the method for installing the retainers on engines 1 and 3, which is described in Figure 6 of the service bulletin. Therefore, the FAA has determined that paragraph (c) must be revised to reference Figure 6 of McDonnell Douglas DC-10 Service Bulletin 71-133, Revision 6, dated June 30, 1992, as the appropriate source of service information to accomplish the optional terminating action on engine 2, as well as engines 1 and 3.\n\n\tAction is taken herein to clarify AD 95-04-07 and to correctly add the AD as an amendment to section 39.13 of the Federal Aviation Regulations (14 CFR 39.13).\n\n\tThe final rule is being reprinted in its entirety for the convenience of affected operators. The effective date of the rule remains March 17, 1995.\n\n\tSince this action only clarifies the procedures for accomplishing an optional action contained in a final rule, it has no adverse economic impact and imposes no additional burden on any person. Therefore, notice and public procedures hereon are unnecessary.\n\nList of Subjects in 14 CFR Part 39\n\tAir transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.\n\nAdoption of the Amendment\n\tAccordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:\n\nPART 39 - AIRWORTHINESS DIRECTIVES\n\t1.\tThe authority citation for part 39 continues to read as follows:\nAuthority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C. 106(g);and 14 CFR 11.89.\n\n§ 39.13 - (Amended)\n\t2.\tSection 39.13 is amended by removing amendment 39-9159 (60 FR 11617, March 2, 1995), and by adding a new airworthiness directive (AD), amendment 39-9317, to read as follows:

The service information referenced in this AD may be obtained from McDonnell Douglas Corporation, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Technical Publications Business Administration, Department C1-L51 (2-60). This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, Los Angeles Aircraft Certification Office, Transport Airplane Directorate, 3960 Paramount Boulevard, Lakewood, California; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.

Maureen Moreland, Aerospace Engineer, Airframe Branch, ANM-120L, FAA, Transport Airplane Directorate, Los Angeles Aircraft Certification Office, 3960 Paramount Boulevard, Lakewood, California 90712; telephone (310) 627-5238; fax (310) 627-5210.