2000-02-04: Autopilot Disconnect, Out-Of-Trim Condition

2000-02-04 AIRBUS INDUSTRIE: Amendment 39-11522. Docket 2000-NM-09-AD. Applicability: Airbus Model A300 series airplanes, having manufacturer s serial number 159, 168, 188, 202, 205, 213, 299, or 302; and all Model A300-600 and A310 series airplanes; 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 (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: Pitch Trim System Test (a) Within 20 days after the effective date of this AD: Perform a pitch trim system test to detect any continuity defect in the autotrim function, in accordance with All Operators Telex (AOT) A300-22A0115 (for Model A300 series airplanes), A300-600-22A6042 (for Model A300-600 series airplanes), or A310-22A2053 (for Model A310 series airplanes), all dated December 23, 1999, as applicable. (1) If no continuity defect is found, no further action is required by this paragraph. Corrective Actions (2) If any continuity defect is found, prior to further flight, accomplish the actions required by paragraphs (a)(2)(i) and (a)(2)(ii) of this AD, in accordance with the applicable AOT. (i) Repair any discrepant wiring found in the pitch trim system. (ii) Repeat the initial pitch trim system test required by paragraph (a) of this AD. NOTE 2: All Operators Telexes (AOT) A300-22A0115, A300-600-22A6042, and A310-22A2053, all dated December 23, 1999, reference Aircraft Schematic Manual (ASM) 22-27-00 as an additional source of service information to accomplish the repair. Reporting Requirement (b) Within 10 days after accomplishing the pitch trim system test required by this AD, or within 10 days after the effective date of this AD, whichever occurs later: Submit a report of the inspection results (both positive and negative findings) to Airbus Customer Services, Engineering and Technical Support, Attention Mr. Vincent Frayssinet, AI/SE-E43; phonenumber 33 (0)5.62.11.04.96; Sita Code TLSBQ7X. 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 3: 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 All Operators Telex A300-22A0115, dated December 23, 1999; Airbus All Operators Telex A300-600-22A6042, dated December 23, 1999; or Airbus All Operators Telex A310-22A2053, dated December 23, 1999; 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 4: The subject of this AD is addressed in French airworthiness directive T2000-007-301(B), dated January 4, 2000. (f) This amendment becomes effective on February 9, 2000.