AD 2005-20-15 Airworthiness Directives; McDonnell Douglas Model DC-10-10 and DC-10-10F Airplanes; Model DC-10-15 Airplanes; Model DC-10-30 and DC-10-30F (KC-10A and KDC-10) Airplanes; Model DC-10-40 and DC-10-40F Airplanes; Model MD-10-10F and MD-10-30F Airplanes; and Model MD-11 and MD-11F Airplanes

Models named: DC-10-10, DC-10-10F, DC-10-15, DC-10-40, DC-10-40F, MD-10-10F, MD-10-30F, MD-11, MD-11F. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to the airplanes identified in Table 1 of this AD; certificated in any category. Table 1.—Applicability McDonnell Douglas— As identified in— Model DC-10-10 and DC-10-10F airplanes; Model DC-10-15 airplanes; Model DC-10-30 and DC-10-30F (KC-10A and KDC-10) airplanes; Model DC-10-40 and DC-10-40F airplanes; and Model MD-10-10F and MD-10-30F airplanes Boeing Alert Service Bulletin DC10-27A236, dated February 17, 2005. Model MD-11 and MD-11F airplanes Boeing Alert Service Bulletin MD11-27A083, dated February 17, 2005.

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Eddy Current Inspection and Replacement if Necessary (f) Within 6 months after the effective date of this AD, do a special detailed eddy current inspection of the rudder pedal torque tube assembly for cracks, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin DC10-27A236, dated February 17, 2005; or Boeing Alert Service Bulletin MD11-27A083, dated February 17, 2005; as applicable. If any crack is found, before further flight, replace the rudder pedal torque tube with a new or serviceable rudder pedal torque tube, in accordance with the applicable service bulletin. Ultrasonic Inspection and Replacement, if Necessary (g) If no cracking is found during the special detailed eddy current inspection required by paragraph (f) of this AD, before further flight, do a special detailed ultrasonic inspection of the rudder pedal torque tube assembly to determine the wall thickness of the rudder pedal torque tube, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin DC10-27A236, dated February 17, 2005; or Boeing Alert Service Bulletin MD11-27A083, dated February 17, 2005; as applicable. (1) If the wall thickness of the torque tube is within the limits identified as area C in Appendix B of the applicable service bulletin, no further action is required by this AD. (2) If the wall thickness of the torque tube is within the limits identified as area B in Appendix B of the applicable service bulletin, within 6,000 flight hours after doing the special detailed ultrasonic inspection, replace the torque tube with a new or serviceable torque tube, in accordance with the applicable service bulletin. (3) If the wall thickness of the torque tube is below the minimum limits, which are identified as area A in Appendix B of the applicable service bulletin, before further flight, replace the torque tube with a new or serviceable torque tube, in accordance with the applicable service bulletin. Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, Los Angeles Aircraft Certification Office (ACO), FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD, if it is approved by an Authorized Representative for the Boeing Commercial Airplanes Delegation Option Authorization Organization who has been authorized by the Manager, Los Angeles ACO, to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (3) Before using any AMOC approved in accordance with 14 CFR 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. Material Incorporated by Reference (i) You must use Boeing Alert Service Bulletin DC10-27A236, dated February 17, 2005; or Boeing Alert Service Bulletin MD11-27A083, dated February 17, 2005, as applicable, to perform the actions that are required by this AD, unless the AD specifies otherwise. The Director of the Federal Register approved the incorporation by reference of these documents in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Contact Boeing Commercial Airplanes, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data and Service Management, Dept. C1-L5A (D800-0024), for a copy of this service information. You may review copies at the Docket Management Facility, U.S. Department of Transportation, 400 Seventh Street SW., room PL-401, Nassif Building, Washington, DC; on the Internet at http://dms.dot.gov; or at the National Archives and Records Administration (NARA). For information on the availability of this material at the NARA, call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html. Issued in Renton, Washington, on September 26, 2005. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 05-19869 Filed 10-5-05; 8:45 am] BILLING CODE 4910-13-P

This AD results from a report of a broken rudder pedal torque tube. We are issuing this AD to prevent failure of a rudder pedal torque tube, which could result in loss of rudder control and nose wheel steering controlled by the rudder pedal, and consequent reduced controllability of the airplane.