AD 2006-22-02 Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model A300 C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes)

Models named: A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, C4-605R Variant F. Read the applicability below — it usually turns on serial or part numbers too.

This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes; certificated in any category; equipped with a Hamilton Sundstrand Ram Air Turbine (RAT).

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. Restatement of the Requirements of AD 2005-15-05 With Compliance Times for New Airplanes Inspection and Related Investigative/Corrective Actions (f) At the applicable time specified in paragraph (f)(1) or (f)(2) of this AD: Do a one-time detailed inspection for evidence of chafing between the hydraulic flexible hose and the RAT hub, and any applicable related investigative and corrective actions, by accomplishing all of the applicable actions specified in the Accomplishment Instructions of Airbus Service Bulletin A300-29-6054, Revision 01, excluding Appendix 01, dated November 4, 2004; or Revision 02, excluding Appendix 01, dated January 12, 2006. After the effective date of this AD, only Revision 02 of the service bulletin may be used. Any applicable corrective actions must be accomplished before further flight. Where the service bulletins specify to submit certain information to the manufacturer, and to submit damaged RATs to the vendor or a repair station, this AD does not include those requirements. (1) For airplanes having serial numbers (S/Ns) 0812, 0813, 0815 through 0818 inclusive, 0821 through 0828 inclusive, and 0836 through 0838 inclusive: Within 2,500 flight hours after August 26, 2005 (the effective date of AD 2005-15-05). (2) For airplanes not identified in paragraph (f)(1) of this AD: Within 2,500 flight hours after the effective date of this AD. Note 1: For the purposes of this AD, a detailed inspection is: “An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required.” Actions Accomplished Previously (g) Actions accomplished before the effective date of this AD, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-29-6054, excluding Appendix 01, dated June 8, 2004, are acceptable for compliance with the corresponding actions specified in this AD. Alternative Methods of Compliance (AMOCs) (h)(1) The Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested in accordance with the procedures found in 14 CFR 39.19. (2) Before using any AMOC approved in accordance with § 39.19 on any airplane to which the AMOC applies, notify the appropriate principal inspector in the FAA Flight Standards Certificate Holding District Office. (3) AMOCs approved previously in accordance with AD 2005-15-05 are approved as AMOCs for the corresponding provisions of this AD. Related Information (i) French airworthiness directive F-2006-035, dated February 1, 2006, also addresses the subject of this AD. Material Incorporated by Reference (j) You must use Airbus Service Bulletin A300-29-6054, Revision 01, excluding Appendix 01, dated November 4, 2004; or Airbus Service Bulletin A300-29-6054, Revision 02, excluding Appendix 01, dated January 12, 2006; to perform the actions that are required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A300-29-6054, Revision 02, excluding Appendix 01, dated January 12, 2006, in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. (2) On August 26, 2005 (70 FR 42267, July 22, 2005), the Director of the Federal Register approved the incorporation by reference of Airbus Service Bulletin A300-29-6054, Revision 01, excluding Appendix 01, dated November 4, 2004. (3) Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France, 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 October 11, 2006. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. E6-17657 Filed 10-26-06; 8:45 am] BILLING CODE 4910-13-P

This AD results from reports of holes in the ram air turbine (RAT) hub cover. We are issuing this AD to prevent a hole in the RAT hub cover. A hole in the RAT hub cover could allow water to enter the RAT governing mechanism, freeze during flight, and jam the governing mechanism. In addition, the metal particles that result from chafing between the hydraulic flexible hose and the RAT could mix with the lubricant grease and degrade the governing mechanism. In an emergency, a jammed or degraded RAT could result in its failure to deploy, loss of hydraulic pressure or electrical power to the airplane, and consequent reduced controllability of the airplane.