2000-12-06: Piston Rod Of The Elevator Servo-Controls

2000-12-06 AIRBUS INDUSTRIE: Amendment 39-11784. Docket 2000-NM-64-AD. Applicability: A330 and A340 series airplanes, certificated in any category, equipped with any "SAMM" elevator servo-control having any part number SC4800-2 through SC4800-8 inclusive airplanes. 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 (b) 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 actionsto address it. Compliance: Required as indicated, unless accomplished previously. To detect and correct excessive play of the eye-end of the piston rod of the elevator servo-controls, which could result in failure of the elevator servo-control, accomplish the following: (a) Within 30 months since date of manufacture of the airplane, or within 500 flight hours after the effective date of this AD, whichever occurs later, perform an inspection to check the play of the piston rod eye-ends of the elevator servo-controls, in accordance with Airbus Service Bulletin A330-27-3062 (for Model A330 series airplanes) or A340-27-4072 (for Model A340 series airplanes), both Revision 01, both dated July 21, 1999. Thereafter, repeat the inspection at intervals not to exceed 15 months. (1) If any play that is 0.0059 inch (0.15 mm) or greater and less than 0.0118 inch (0.30 mm) is detected: Prior to further flight, replace the rod eye-end with a new SARMA or NMB rod eye-end, in accordance with the applicable service bulletin. (2) If any play that is 0.0118 inch (0.30 mm) or greater is detected: Prior to further flight, perform a dye penetrant inspection to detect cracking of the servo-control, in accordance with the applicable service bulletin. (i) If no crack is detected: Prior to further flight, replace the rod eye-end with a new SARMA or NMB rod eye-end, in accordance with the applicable service bulletin. (ii) If any crack is detected: Prior to further flight, replace the servo-control with a new servo-control, in accordance with the applicable service bulletin. NOTE 2: Accomplishment of an inspection in accordance with Airbus Service Bulletin A330-27-3062 (for Model A330 series airplanes) or A340-27-4072 (for Model A340 series airplanes), both dated February 5, 1999; is considered acceptable for compliance with the initial inspection requirements of paragraph (a) of this AD. NOTE 3: The Airbus service bulletins reference SAMM Service Bulletin SC4800-27-34-06, dated January 2, 1999, as an additional source of service information for accomplishment of the dye penetrant inspection specified by paragraph (a)(2) of this AD. Alternative Methods of Compliance (b) 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 4: 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 (c) 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 (d) The actions shall be done in accordance with Airbus Service Bulletin A330-27-3062, Revision 01, dated July 21, 1999; or Airbus Service Bulletin A340-27-4072, Revision 01, dated July 21, 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 5: The subject of this AD is addressed in French airworthiness directives 2000-025-109(B) R1 and 2000-024-135(B) R1, both dated March 8, 2000. (e) This amendment becomes effective on July 20, 2000.