AD 2004-04-10 Airworthiness Directives; Airbus Model A300 B2 and A300 B4 Series Airplanes; A300 B4-600, B4-600R, C4-605R Variant F, and F4-600R (Collectively Called A300-600); and A310 Series Airplanes

Models named: A300 B2, A300 B4 series. Read the applicability below — it usually turns on serial or part numbers too.

All Airbus Model A300 B2 and A300 B4 series airplanes; A300 B4-600, B4-600R, C4-605R Variant F, and F4-600R (collectively called A300-600); and A310 series airplanes; certificated in any category.

Required as indicated, unless accomplished previously. To prevent failure of the landing gear selector valves, which could result in residual pressure on the retraction chamber side of the electro-hydraulic selector, and consequent uncommanded retraction of the landing gear when the airplane is on the ground, accomplish the following: Part Number Identification (a) For Model A300 B2 and A300 B4 series airplanes: Before the accumulation of 32,000 total flight cycles on the landing gear selector valves, or within 600 flight hours after the effective date of this AD, whichever occurs later, do the actions required by paragraphs (a)(1) and (a)(2) of this AD. (1) Inspect to determine whether any selector valve having part number (P/N) A25199-0-2 is installed. (2) Replace any selector valve having P/N A25199-0-2 with a new selector valve having P/N A25199-0-3, in accordance with Airbus Service Bulletin A300-32-0438, Revision 01, dated November 20, 2001. Operational Test (b) For airplanes installed with selector valves having P/N A25199-0-3 only: Before the accumulation of 32,000 total flight cycles on the landing gear selector valves, or within 600 flight hours after the effective date of this AD, whichever occurs later, perform an operational test of the selector valves. Do the test in accordance with the Accomplishment Instructions of Airbus Service Bulletins A300-32-0438 (for Model A300 B2 and A300 B4 series airplanes), A300-32-6082 (for Model A300-600 series airplanes and Model A300 C4-605R Variant F airplanes), and A310-32-2118 (for Model A310 series airplanes); all Revision 01, dated November 20, 2001; as applicable. Before further flight, replace any valve that fails the operational test with a new valve having P/N A25199-0-3, in accordance with the applicable service bulletin. Follow-on and Corrective Actions (c) For Model A300 B2 and A300 B4 series airplanes that have not been modified in accordance with Airbus Modification 3083 (Airbus Service Bulletin A300-32-0269): Within 3,000 flight hours after the accumulation of 32,000 total flight cycles on the valve, or within 3,000 flight hours after performing the operational test required by paragraph (b) of this AD, whichever occurs later, do task 323112-0503-2 of the Airbus A300 Maintenance Planning Document (MPD). Repeat the MPD task thereafter at intervals not to exceed 3,000 flight hours. (d) For Model A300 B2 and A300 B4 series airplanes that have been modified in accordance with Airbus Modification 3083 (Airbus Service Bulletin A300-32-0269), and for Model A300-600 and A310 series airplanes and Model A300 C4-605R Variant F airplanes: Repeat the operational test specified in paragraph (b) of this AD at the later of the times specified by paragraphs (d)(1) and (d)(2) of this AD. Thereafter, repeat the test at intervals not to exceed 18 months or 2,800 flight cycles, whichever occurs first. (1) Within 18 months or 2,800 flight cycles, whichever occurs first, after the accumulation of 32,000 total flight cycles on the valve. (2) Within 18 months or 2,800 flight cycles, whichever occurs first, after performing the initial operational test required by paragraph (b) of this AD. Alternative Methods of Compliance (e) In accordance with 14 CFR 39.19, the Manager, International Branch, ANM-116, FAA, is authorized to approve alternative methods of compliance for this AD. Incorporation by Reference (f) Unless otherwise specified in this AD, the actions must be done in accordance with Airbus Service Bulletin A300-32-0438, Revision 01, including Appendix 01, dated November 20, 2001; Airbus Service Bulletin A300-32-6082, Revision 01, including Appendix 01, dated November 20, 2001; and Airbus Service Bulletin A310-32-2118, Revision 01, including Appendix 01, dated November 20, 2001; 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, 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 1: The subject of this AD is addressed in French airworthiness directive 2001-603(B), dated December 12, 2001. Effective Date (g) This amendment becomes effective on April 13, 2004. Issued in Renton, Washington, on February 27, 2004. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 04-4921 Filed 3-8-04; 8:45 am] BILLING CODE 4910-13-P