AD 2001-24-27 Airworthiness Directives; McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 Series Airplanes; Model DC-9-81, -82, -83, and -87 Series Airplanes; Model MD-88 Airplanes; and C-9 Airplanes

Models named: DC-9-10, -20, -30, -40, -50 series, DC-9-81, -82, -83, -87 series, MD-88. Read the applicability below — it usually turns on serial or part numbers too.

Model DC-9-10, -20, -30, -40, and -50 series airplanes; Model DC-9-81, -82, -83, and -87 series airplanes; Model MD-88 airplanes; and C-9 series airplanes; as listed in McDonnell Douglas Service Bulletin DC9-27-325R02, Revision 02, dated December 12, 1995; 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 request approval for an alternative method of compliance in accordance with paragraph (d) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.

Required as indicated, unless accomplished previously. To prevent loss of rudder pedals control and reduction of braking capability, accomplish the following: Restatement of Requirements of AD 96-02-05 Repetitive Inspections and Replacement, If Necessary (a) For airplanes listed in McDonnell Douglas DC-9 Alert Service Bulletin A27-325R02, 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 A27-325R02, Revision 1, dated February 3, 1992, or Revision 2, dated January 27, 1995. (1) If 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. (2) If cracks are detected as a result of the inspections required by this paragraph, prior to further flight, replace the rudder pedal 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 A27-325R02, 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. (b) For airplanes listed in McDonnell Douglas DC-9 Alert Service Bulletin A27-325R02, 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 March 25, 1996 (the effective date of AD 96-02-05, amendment 39-9493), 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 A27-325R02, Revision 1, dated February 3, 1992, or Revision 2, dated January 27, 1995. (1) If 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. (2) If 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 A27-325R02, 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. New Actions Required By This AD Replacement and Reidentification (c) Prior to the accumulation of 15,000 total landings, or within 18 months after the effective date of this AD, whichever occurs later, do the actions specified in paragraphs (c)(1) and (c)(2) of this AD in accordance with the Accomplishment Instructions of McDonnell Douglas Service Bulletin DC9-27-325R02, Revision 02, dated December 12, 1995. Accomplishment of the these actions constitutes terminating action for the requirements of this AD. (1) Replace the existing magnesium casting hub assembly of the rudder pedal adjuster, part number (P/N) 4616066-3, and bearing, P/N AN201KP4A, in the rudder pedal mechanism between stations X=69.000 and X=120.000 in the flight compartment with a new aluminum assembly, part number (P/N) 5965435-3, and new bearing, P/N MS27641-4; and (2) Reidentify rudder pedal adjuster, P/N 5641294-501 or -503, as P/N 5641294-507. Note 2: Installation of the aluminum rudder pedal adjuster hub assembly per McDonnell Douglas Service Bulletin DC9-27-325R02, Revision 1, dated November 30, 1994, before the effective date of this AD, is considered acceptable for the requirements of paragraph (c) of this AD. Alternative Methods of Compliance (d) 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 Aircraft Certification Office (ACO), FAA. 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 3: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the Los Angeles ACO. Special Flight Permits (e) 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. Incorporation by Reference (f) The actions shall be done in accordance with McDonnell Douglas DC-9 Alert Service Bulletin A27-325R02, Revision 1, dated February 3, 1992; McDonnell Douglas DC-9 Alert Service Bulletin A27-325R, Revision 2, dated January 27, 1995; or McDonnell Douglas Service Bulletin DC9-27-325R02, Revision 02, dated December 12, 1995; as applicable. (1) The incorporation by reference of McDonnell Douglas Service Bulletin DC9-27-325R02, Revision 02, dated December 12, 1995, is approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) The incorporation by reference of McDonnell Douglas DC-9 Alert Service Bulletin A27-325R02, Revision 2, dated January 27, 1995, was approved previously by the Director of the Federal Register as of March 25, 1996 (61 FR 6922, February 23, 1996). (3) The incorporation by reference of McDonnell Douglas DC-9 Alert Service Bulletin A27-325R02, Revision 1, dated February 3, 1992, was approved previously by the Director of the Federal Register as of January 22, 1993 (57 FR 60116, December 18, 1992). (4) Copies may be obtained from Boeing Commercial Aircraft Group, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1-L5A (D800-0024). Copies may be inspected at the FAA, 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. Effective Date (g) This amendment becomes effective on January 16, 2002. Issued in Renton, Washington, on November 28, 2001. Vi L. Lipski, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 01-30203 Filed 12-11-01; 8:45 am] BILLING CODE 4910-13-P