AD 95-04-07

This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-10 series airplanes and KC-10A (military) airplanes. This action requires inspections to determine the condition of the lockwires on the forward engine mount bolts and correction of any discrepancies found. This action also provides for termination of the inspections for some airplanes by installing retainers on the bolts. This amendment is prompted by reports of stretched or broken lockwires on the forward engine mount bolts. The actions specified in this 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\tComments for inclusion in the Rules Docket must be received on or before May 1, 1995.

Final rule; request for comments.

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.

On October 10, 1985, the FAA issued AD 85-22-01, amendment 39-5157, (50 FR 42153, October 18, 1985) applicable to certain McDonnell Douglas Model DC-10-10, -15, -30, and -40 airplanes, and KC-10A (military) airplanes. That AD requires repetitive inspections of the engine-to-pylon forward and aft mount and the engine mount bolts; and replacement of the bolts and nuts, torque check of the bolts, and installation of a torque stripe on the bolts, if necessary. That AD provided for termination of the inspections by replacing the engine mount bolts with bolts having a lockwire hole in the bolt head, installing tabs with a lockwire hole, and installing lockwires.\n\n\tSince the issuance of that AD, the FAA has received reports of broken or stretched lockwires on the forward engine mount bolts on several Model DC-10-30 airplanes on which the terminating actions described in AD 85-22-01 had been accomplished. Investigation has revealed that these lockwires may havestretched and eventually broken because the forward engine mount bolts had loosened. McDonnell Douglas has developed a bolt retainer that will prevent these bolts from loosening from the engines of Model DC-10-30 airplanes and KC-10A (military) airplanes.\n\n\tAdditionally, the FAA has received reports of loose bolts on the engine mounts of Model DC-10-10 airplane engines. However, McDonnell Douglas has not yet developed a bolt retainer for Model DC-10-10 or -15 airplanes, or KC-10A airplanes.\n\n\tBroken lockwires, if not corrected, could result in loosening of the engine mount bolts and subsequent separation of the engine from the airplane.\n\n\tThe lockwires on the forward engine mount bolts of Model DC-10-30 airplanes are similar to those installed on Model DC-10-10 and -15 airplanes, and KC-10A airplanes. Therefore, the FAA finds that Model DC-10-10 and -15 airplanes, and KC-10A airplanes are also subject to the same unsafe condition.\n\n\tThe FAA has reviewed and approved McDonnell Douglas Alert Service Bulletin DC10-71A159, Revision 1, dated January 31, 1995, which describes procedures for repetitive visual inspections to detect broken lockwires on the forward engine mount bolts on engines 1, 2, and 3. If any broken lockwire is found, the service bulletin describes procedures to check the torque of the bolt, to install a new lockwire, and to install a torque stripe on the bolt. This service bulletin also describes procedures for subsequent visual inspections to detect misalignment of the torque stripe.\n\n\tSince an unsafe condition has been identified that is likely to exist or develop on other airplanes of the same type design, this AD is being issued to prevent broken lockwires, which could result in loosening of the engine mount bolts and subsequent separation of the engine from the airplane. This 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. The actions are required to be accomplished in accordance with the alert service bulletin described previously.\n\n\tThe required compliance time of 120 days is usually sufficient to allow for a brief comment period before adoption of a final rule. In this AD, however, that compliance time was selected because of the degree of urgency associated with addressing the subject unsafe condition and the practical aspects of performing the inspection within a maximum interval of time allowable for all affected airplanes to continue to operate without compromising safety. Further, the FAA took into account the 6-month compliance time recommended by the manufacturer, as well as the number of days required for the rulemaking process; in consideration of these factors, the FAA finds that 120 days after the effective date of this rule will fall approximately at the same time as that recommended by the manufacturer.\n\n\tThis AD also requires that operators report the results of thevisual inspections to the FAA. The intent of these reports is to enable the FAA to determine how widespread the problem of broken lockwires may be in the affected fleet. Based on the results of these reports, further corrective action may be warranted.\n\n\tSince retainers have been developed only for Model DC-10-30 airplanes and KC-10A airplanes, this AD also 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.\n\n\tAs a result of recent communications with the Air Transport Association (ATA) of America, the FAA has learned that, in general, some operators may misunderstand the legal effect of AD's on airplanes that are identified in the applicability provision of the AD, but that have been altered or repaired in the area addressed by the AD. The FAA points out that all airplanes identified in the applicability provision of an AD are legally subject to the AD. If an airplane has been altered or repaired in the affected area in such a way as to affect compliance with the AD, the owner or operator is required to obtain FAA approval for an alternative method of compliance with the AD, in accordance with the paragraph of each AD that provides for such approvals. A note has been included in this rule to clarify this long-standing requirement.\n\n\tSince a situation exists that requires the immediate adoption of this regulation, it is found that notice and opportunity for prior public comment hereon are impracticable, and that good cause exists for making this amendment effective in less than 30 days.\n\nComments Invited\n\tAlthough this action is in the form of a final rule that involves requirements affecting flight safety and, thus, was not preceded by notice and an opportunity for public comment, comments are invited on this rule. Interested persons are invited tocomment on this rule by submitting such written data, views, or arguments as they may desire. Communications shall identify the Rules Docket number and be submitted in triplicate to the address specified under the caption "ADDRESSES." All communications received on or before the closing date for comments will be considered, and this rule may be amended in light of the comments received. Factual information that supports the commenter's ideas and suggestions is extremely helpful in evaluating the effectiveness of the AD action and determining whether additional rulemaking action would be needed.\n\n\tComments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify the rule. All comments submitted will be available, both before and after the closing date for comments, in the Rules Docket for examination by interested persons. A report that summarizes each FAA-public contact concerned with the substance of this AD will be filed in the Rules Docket.\n\n\tCommenters wishing the FAA to acknowledge receipt of their comments submitted in response to this rule must submit a self-addressed, stamped postcard on which the following statement is made: "Comments to Docket Number 94-NM-253-AD." The postcard will be date stamped and returned to the commenter.\n\n\tThe regulations adopted herein will not have substantial direct effects on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, in accordance with Executive Order 12612, it is determined that this final rule does not have sufficient federalism implications to warrant the preparation of a Federalism Assessment.\n\n\tThe FAA has determined that this regulation is an emergency regulation that must be issued immediately to correct an unsafe condition in aircraft, and that it is not a "significant regulatoryaction" under Executive Order 12866. It has been determined further that this action involves an emergency regulation under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979). If it is determined that this emergency regulation otherwise would be significant under DOT Regulatory Policies and Procedures, a final regulatory evaluation will be prepared and placed in the Rules Docket. A copy of it, if filed, may be obtained from the Rules Docket at the location provided under the caption "ADDRESSES."\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 adding the following new airworthiness directive: