AD 96-02-05

This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9 and Model DC-9-80 series airplanes; Model MD-88 airplanes; and C-9 (military) series airplanes, that currently requires visual and eddy current inspections to detect cracking of the rudder pedals adjuster hub assembly, and replacement of the assembly, if necessary. That amendment was prompted by several occurrences of failure of the rudder pedals adjuster hub assembly due to broken detent lugs. This amendment provides an optional terminating action for the required inspections, and expands the applicability of the existing AD to include additional airplanes. The actions specified by this AD are intended to prevent loss of rudder pedals control and reduction of braking capability.

Final rule.

96-02-05 MCDONNELL DOUGLAS: Amendment 39-9493. Docket 95-NM-20-AD. Supersedes AD 92-27-07, Amendment 39-8441. \n\n\tApplicability: Model DC-9-10, -20, -30, -40, and -50 series airplanes; Model DC-9-81 (MD-81), -82 (MD-82), -83 (MD-83), and -87 (MD-87) series airplanes; Model MD-88 airplanes; and Model C-9 (military) series airplanes; as listed in McDonnell Douglas DC-9 Alert Service Bulletin A27-325, Revision 2, dated January 27, 1995; 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 loss of rudder pedals control and reduction of braking capability, accomplish the following: \n\n\t(a)\tFor airplanes listed in McDonnell Douglas Alert Service Bulletin A27-325, Revision 1, dated February 3, 1992: Prior to the accumulation of 15,000 landings or within 270 days after January 22, 1993 (the effective date of AD 92-27-07, amendment 39-8441), whichever occurs later, conduct a visual and eddy current inspection to detect cracks of the rudder pedals adjuster hub assembly, part number 4616066, in accordance with McDonnell Douglas DC-9 Alert Service Bulletin A27-325, Revision 1, dated February 3, 1992, or Revision 2, dated January 27, 1995. \n\n\t\t(1)\tIf no cracks are detected as a result of the inspections required by this paragraph, repeat the inspections at intervals not to exceed 3,500 landings. \n\n\t\t(2)\tIf cracks are detected as a result of the inspections required by this paragraph, prior to further flight, replace the rudder pedals adjuster hub assembly, part number 4616066, with a new assembly having the same part number, in accordance with McDonnell Douglas DC-9 Alert Service Bulletin A27-325, Revision 2, dated January 27, 1995. Thereafter, conduct visual and eddy current inspections of the replacement rudder pedals adjuster hub assembly in accordance with this paragraph. \n\n\t(b)\tFor airplanes listed in McDonnell Douglas DC-9 Alert Service Bulletin A27-325, Revision 2, dated January 27, 1995, and not subject to paragraph (a) of this AD: Prior to the accumulation of 15,000 landings or within 270 days after the effective date of this AD, whichever occurs later, conduct a visual and eddy current inspection to detect cracks of the rudder pedals adjuster hub assembly, part number 4616066, in accordance with McDonnell Douglas DC-9 Alert Service Bulletin A27-325, Revision 1, dated February 3, 1992, or Revision 2, dated January 27, 1995. \n\n\t\t(1)\tIf no cracks are detected as a result of the inspections required by this paragraph, repeat the inspections at intervals not to exceed 3,500 landings. \n\n\t\t(2)\tIf cracks are detected as a result of the inspections required by this paragraph, prior to further flight, replace the rudder pedals adjuster hub assembly, part number 4616066, with a new assembly having the same part number, in accordance with McDonnell Douglas DC-9 Alert Service Bulletin A27-325, Revision 2, dated January 27, 1995. Thereafter, conduct visual and eddy current inspections of the replacement rudder pedals adjuster hub assembly in accordance with this paragraph. \n\n\t(c)\tInstallation of the aluminum rudder pedal adjustment hub assembly in the rudder pedal mechanism between stations X=69 and X=120.000 in the flight compartment, in accordance with McDonnell Douglas DC-9 Service Bulletin 27-325, Revision 1, dated November 30, 1994, 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. Alternative methods of compliance previously granted for AD 92-27-07, Amendment 39-8441, continue to be considered as acceptable alternative methods of compliance with this amendment. \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 actions shall be done in accordance with McDonnell Douglas DC-9 Alert Service Bulletin A27-325, Revision 2, dated January 27, 1995; McDonnell Douglas DC-9 Service Bulletin 27-325, Revision 1, dated November 30, 1994; and McDonnell Douglas DC-9 Alert Service Bulletin A27-325, Revision 1, dated February 3, 1992. Revision 2 of McDonnell Douglas DC-9 Alert Service Bulletin A27-325 contains the following list of effective pages: \n\n\nPage Number\nRevision Level\nShown on Page\nDate\nShown on Page \n1-22\n2\nJanuary 27, 1995 \n23-30\n1\nFebruary 3, 1992 \n\nRevision 1 of McDonnell Douglas DC-9 Service Bulletin 27-325 contains the following list of effective pages: \n\n\nPage Number\nRevision Level\nShown on Page\nDate\nShown on Page \n1-22\n1\nNovember 30, 1994 \n23-28\nOriginal\nSeptember 13, 1993 \n\t\nThe incorporation by reference of McDonnell Douglas DC-9 Alert Service Bulletin A27-325, Revision 1, dated February 3, 1992, 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 January 22, 1993 (57 FR 60116, December 18, 1992). The incorporation by reference of the remainder of service documents is 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, 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. \n\n\t(g)\tThis amendment becomes effective on March 25, 1996.

A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) by superseding AD 92-27-07, amendment 39-8441 (57 FR 60116, December 18, 1992), which is applicable to certain McDonnell Douglas Model DC-9 and Model DC-9-80 series airplanes; Model MD-88 airplanes; and C-9 (military) series airplanes, was published in the Federal Register on April 6, 1995 (60 FR 17489). The action proposed to continue to require visual and eddy current inspections to detect cracking of the rudder pedals adjuster hub assembly, and replacement of the assembly, if necessary. The action also proposed to expand the applicability of the existing AD to include additional airplanes. \n\n\tInterested persons have been afforded an opportunity to participate in the making of this amendment. Due consideration has been given to the comments received. \n\n\tTwo commenters support the proposed rule. \n\n\tTwo other commenters also support the proposed rule, but request that the FAA allow the replacement of the magnesium casting rudder pedal adjuster hub assembly with an aluminum assembly, as described in McDonnell Douglas DC-9 Service Bulletin 27-325, as terminating action for the requirements of this AD. \n\n\tThe FAA concurs. The FAA has reviewed and approved McDonnell Douglas DC-9 Service Bulletin 27-325, Revision 1, dated November 30, 1994, which describes procedures for replacement of the rudder pedal adjustment hub assembly in the rudder pedal mechanism. The FAA has determined that replacement of the existing magnesium casting with a new aluminum part, as specified in the service bulletin, provides optional terminating action for the repetitive inspections required by this AD. Accordingly, the FAA has revised the final rule to add a new paragraph (c) to specify this optional terminating action. \n\n\tMcDonnell Douglas Alert Service Bulletin number "A27-325," Revision 1, was inadvertently omitted in paragraph (a) of the proposed rule and a typographical error in the date of that alert service bulletin also appeared in paragraph (a) of the proposed rule. Additionally, McDonnell Douglas DC-9 Alert Service Bulletin number "A27-325," Revision 2, dated January 27, 1995, was inadvertently omitted in paragraph (b) of the proposed rule. The FAA has revised the final rule to correct these typographical errors. \n\n\tAfter careful review of the available data, including the comments noted above, the FAA has determined that air safety and the public interest require the adoption of the rule with the changes previously described. The FAA has determined that these changes will neither increase the economic burden on any operator nor increase the scope of the AD. \n\n\tThere are approximately 909 Model DC-9 and Model DC-9-80 series airplanes; Model MD-88 airplanes; and C-9 (military) series airplanes of the affected design in the worldwide fleet. The FAA estimates that 561 airplanes of U.S. registry will be affected by this AD, that it wouldtake approximately 3 work hours per airplane to accomplish the required actions, and that the average labor rate is $60 per work hour. Based on these figures the cost impact of this AD on U.S. operators is estimated to be $180 per airplane. \n\n\tThe actions specified in this AD previously were required by AD 92-27-07, which was applicable to approximately 373 airplanes. Based on the figures discussed above, the cost impact of the current requirements of that AD on U.S. operators is estimated to be $67,140. In consideration of the compliance time and effective date of AD 92-27-07, the FAA assumes that operators of the 373 airplanes subject to that AD have already initiated the required actions. This AD action adds no new costs associated with those airplanes. \n\n\tThis AD action is applicable to approximately 188 additional airplanes. Based on the figures discussed above, the new costs to U.S. operators that are imposed by this AD are estimated to be $33,840. This figure is basedon assumptions that no operator of these additional airplanes has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. \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\tFor the reasons discussed above, I certify that this action (1) is not a "significant regulatory action" under Executive Order 12866; (2) is not a "significant rule" under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on asubstantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it 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\n\tAir transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. \n\nAdoption of the Amendment \n\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\n\t1. The authority citation for part 39 continues to read as follows: \n\nAuthority: 49 USC 106(g), 40113, 44701. \n\n§ 39.13 - (Amended) \n\n\t2. Section 39.13 is amended by removing amendment 39-8441 (57 FR 60116, December 18, 1992), and by adding a new airworthiness directive (AD), amendment 39-9493, toread as follows: