AD 2001-24-28 Airworthiness Directives; McDonnell Douglas Model DC-8 Series Airplanes

Models named: DC-8 series. Read the applicability below — it usually turns on serial or part numbers too.

Model DC-8 series airplanes, serial numbers 45646 and 45928, and as listed in McDonnell Douglas DC-8 Alert Service Bulletin A27-275, Revision 1, dated February 3, 1992; 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 (g) 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: Inspection (a) For airplanes listed in McDonnell Douglas DC-8 Alert Service Bulletin A27-275, 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 92-27-06, amendment 39-8440), whichever occurs later, conduct a visual and eddy current inspection to detect cracks of the rudder pedals adjuster hub assembly, part number (P/N) 4616066, in accordance with McDonnell Douglas DC-8 Alert Service Bulletin A27-275, Revision 1, dated February 3, 1992, or Revision 2, dated August 5, 1992; or McDonnell Douglas Alert Service Bulletin DC8-27A275R03, Revision 03, dated April 5, 1996. As of the effective date of this AD only McDonnell Douglas Alert Service Bulletin DC8-27A275R03, Revision 03, dated April 5, 1996, shall be used. (b) For airplanes having serial numbers 45646 and 45928: Prior to the accumulation of 15,000 total 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, P/N 4616066, in accordance with McDonnell Douglas DC-8 Alert Service Bulletin A27-275, Revision 1, dated February 3, 1992, or Revision 2, dated August 5, 1992; or McDonnell Douglas Alert Service Bulletin DC8-27A275R03, Revision 03, dated April 5, 1996. As of the effective date of this AD, only McDonnell Douglas Alert Service Bulletin DC8-27A275R03, Revision 03, dated April 5, 1996, shall be used. No Crack Found During Inspection Required by Paragraph (a) or (b) of This AD: Repetitive Inspections (c) If no crack is detected as a result of the inspections required by paragraph (a) or (b) of this AD, repeat the inspections at intervals not to exceed 3,500 landings. Any Crack Found: Replacement and Repetitive Inspections (d) If any crack is detected as a result of the inspections required by paragraph (a), (b), or (c) of this AD, prior to further flight, replace the rudder pedals adjuster hub assembly, P/N 4616066, with a new assembly, P/N 5965435-1, in accordance with McDonnell Douglas Alert Service Bulletin DC8-27A275R03, Revision 03, dated April 5, 1996. Accomplishment of the replacement constitutes terminating action for the repetitive inspection requirements of this AD. Terminating Action (e) Prior to the accumulation of 15,000 total landings, or within 3,500 landings after the effective date of this AD, whichever occurs later, replace the existing adjuster hub assembly with a new assembly, P/N 5965435-1, per McDonnell Douglas Alert Service Bulletin DC8-27A275R03, Revision 03, dated April 5, 1996. Accomplishment of the replacement constitutes terminating action for the requirements of this AD. Spares (f) As of the effective date of this AD, no person shall install an adjuster hub assembly, P/N 4616066, on any airplane. Alternative Methods of Compliance (g) 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 2: 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 (h) 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 (i) The actions shall be done in accordance with McDonnell Douglas DC-8 Alert Service Bulletin A27-275, Revision 1, dated February 3, 1992; McDonnell Douglas DC-8 Alert Service Bulletin A27-275, Revision 2, dated August 5, 1992; or McDonnell Douglas Alert Service Bulletin DC8-27A275R03, Revision 03, dated April 5, 1996; as applicable. (1) The incorporation by reference of McDonnell Douglas DC-8 Alert Service Bulletin A27-275, Revision 1, dated February 3, 1992, was approved previously by the Director of the Federal Register as of January 22, 1993 (57 FR 60115, December 18, 1992). (2) The incorporation by reference of the remaining 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. (3) 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, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the FAA, 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 (j) 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. 01-30204 Filed 12-11-01; 8:45 am] BILLING CODE 4910-13-P