2000-23-07: Autotrim Function

2000-23-07 AIRBUS INDUSTRIE: Amendment 39-11977. Docket 2000-NM-104-AD. Supersedes AD 2000-02-04, Amendment 39-11522. Applicability: This AD applies to the airplanes listed in Table 1. of this AD, certificated in any category: Table 1. Applicability Airbus Model Description A300 B2-203 airplanes and A300-B4-203 airplanes. In a forward facing cockpit version, as listed in Airbus Service Bulletin A300-22A0115, Revision 02, dated March 7, 2000. A310 series airplanes. All. A300-600 series airplanes. On which Airbus Modification 12277 has not been accomplished during production. NOTE 1: This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been otherwise 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 (c) 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. Compliance: Required as indicated, unless accomplished previously. To prevent a sudden change in pitch due to an out-of-trim condition combined with an autopilot disconnect, which could result in reduced controllability of the airplane, accomplish the following: Repetitive Inspections (a) At the applicable time specified by paragraph (a)(1) or (a)(2) of this AD: Perform an inspection of the autotrim function by testing the flight control computer (FCC)/flight augmentation computer (FAC) integrity in logic activation of the autotrim, in accordance with Airbus Service Bulletin A300-22A6042, Revision 01 (for Model A300-600 series airplanes); A300-22A0115, Revision 02 (for Model A300 series airplanes); or A310-22A2053, Revision 01 (for Model A310 series airplanes); all dated March 7, 2000; as applicable. If any discrepancy is found, prior to further flight, perform all applicable corrective actions (including trouble-shooting, replacing the FCC and/or FAC, retesting, checking the wires between certain FCC and FAC pins, and repairing damaged wires) in accordance with the applicable service bulletin. Repeat the inspection thereafter at intervals not to exceed 500 flight hours. (1) For airplanes on which the pitch trim system test has been performed in accordance with the requirements of AD 2000-02-04, amendment 39-11522: Inspect within 500 flight hours after accomplishment of the test required by that AD, or within 20 days after the effective date of this AD, whichever occurs later. (2) For all other airplanes: Inspect within 20 days after the effective date of this AD. ReportingRequirement (b) For all inspections required by paragraph (a) of this AD: At the applicable time specified by paragraph (b)(1) or (b)(2) of this AD, submit a report of the inspection results (both positive and negative findings) to AI/SE-D32 Technical Data and Documentation Services, Airbus Industrie Customer Services Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex France; fax (+33) 5 61 93 28 06. (1) For inspections accomplished after the effective date of this AD: Submit the report within 30 days after performing the inspection. (2) For inspections accomplished prior to the effective date of this AD: Submit the report within 30 days after the effective date of this AD. Alternative Methods of Compliance (c) 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, International Branch, ANM-116, FAA, Transport Airplane Directorate. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM-116. NOTE 2: Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116. Special Flight Permits (d) 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 (e) The actions shall be done in accordance with Airbus Service Bulletin A300-22A6042, Revision 01, including Appendix 01, dated March 7, 2000; Airbus Service Bulletin A300-22A0115, Revision 02, including Appendix 01, dated March 7, 2000; or Airbus Service Bulletin A310-22A2053, Revision 01, including Appendix 01, dated March 7, 2000; as applicable. 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. Copies may be obtained from Airbus Industrie, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC. NOTE 3: The subject of this AD is addressed in French airworthiness directive 2000-115-304(B) R2, dated July 12, 2000, as revised by Erratum, dated August 9, 2000. (f) This amendment becomes effective on December 20, 2000.