AD 2007-03-09

To prevent failure of the ram air turbine (RAT) yoke fitting, which could result in the loss of RAT function and possible loss of critical flight control in the event of certain emergency situations, accomplish the following:

(a) For Model A300-600 series airplanes, and Model A310 airplanes: Within 1,300 flight hours or 6 months after the effective date of this AD, whichever occurs first, do a detailed inspection for breaks of the bottom flange fitting of the yoke fitting for the RAT swivel coupling in accordance with the applicable all operators telex (AOT) in paragraph (a)(1) or (a)(2) of this AD. If the flange fitting is broken, before further flight, replace the flange fitting with a new flange fitting in accordance with the applicable AOT. For airplanes equipped with Hamilton Sundstrand RATs, verify the adjustment of the ejection jack, and correct the adjustment as applicable.

(1) For Model A300-600 series airplanes: Airbus A300-600 AOT 57A6096, Revision 01, dated April 11, 2005.

(2) For Model A310 airplanes: Airbus A310 AOT 57A2085, Revision 01, dated April 11, 2005.

Note 1: For the purposes of this AD, a detailed inspection is defined as: “An intensive visual examination of a specific structural area, system, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at intensity deemed appropriate by the inspector. Inspection aids such as mirror, magnifying lenses, etc., may be used. Surface cleaning and elaborate access procedures may be required.”

(b) For Model A300 airplanes, Model A300-600 series airplanes, and Model A310 airplanes equipped with Dowty Rotol RATs, except airplanes on which Airbus Modification 12986 has been done: Within 12 months after the effective date of this AD, replace the RAT swivel coupling fork fitting with a new steel fitting, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A300-57-0244, dated March 4, 2005 (for Model A300 airplanes); A300-57-6099, dated February 23, 2005 (for Model A300-600 series airplanes); or A310-57-2086, dated March 1, 2005 (for Model A310 airplanes); as applicable.

(c) For all airplanes: Within 3 months after the effective date of this AD: Incorporate the information in the applicable aircraft maintenance manual (AMM) specified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, into the FAA-approved maintenance program to specify an inspection for breaks of the bottom flange of the RAT swivel coupling yoke fitting after each RAT retraction; and replacement of the RAT swivel coupling yoke fitting with a new aluminum or steel part as applicable; in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the Direction Générale de l'Aviation Civile (or its delegated agent); or European Aviation Safety Agency (or its delegated agent). The page blocks specified in paragraphs (c)(1), (c)(2), and (c)(3) of this AD, as applicable, are one approved method for the actions required by paragraph (c) of this AD. Thereafter, except as provided by paragraph (d) of this AD, no alternative inspection intervals may be approved for the bottom flange of the RAT swivel coupling yoke fitting.

(1) Airbus A300-600 AMM, Chapter 29-25-00, Page Block 301, dated June 1, 2005.

(2) Airbus A310 AMM, Chapter 29-25-00, Page Block 301, dated June 1, 2005.

(3) Airbus A300 AMM Chapter 29-25-00, Page Block 301, dated March 1, 2006.

Note 2: After revising the maintenance program to include the required periodic inspections according to this paragraph, operators do not need to make a maintenance log entry to show compliance with this AD every time those inspections are accomplished thereafter.

Note 3: This AD requires revisions to certain operator maintenance documents to include new inspections. Compliance with these inspections is required by 14 CFR 91.403(c). For airplanes that have been previously modified, altered, or repaired in the areas addressed by these inspections, the operator may not be able to accomplish the inspections described in the revisions. In this situation, to comply with 14 CFR 91.403(c), the operator must request approval for an alternative method of compliance according to paragraph (d) of this AD. The request should include a description of changes to the required inspections that will ensure the continued damage tolerance of the affected structure. The FAA has provided guidance for this determination in Advisory Circular (AC) 25-1529-1.

(d)(1) In accordance with 14 CFR 39.19, the Manager, International Branch, ANM-116, is authorized to approve alternative methods of compliance for this AD.

(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.

Note 4: The subject of this AD is addressed in French airworthiness directives F-2005-089, dated June 8, 2005; and F-2005-090 R1, dated July 6, 2005.

(e) Unless otherwise specified in this AD, the actions must be done in accordance with the applicable service information specified in Table 1 of this AD. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. To get copies of this service information, contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. To inspect copies of this service information, go to the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or to 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.