2005-10-12: Lateral control trim actuator assembly

2005-10-12 Schweizer Aircraft Corporation: Amendment 39-14089. Docket No. FAA-2005-21217; Directorate Identifier 2005-SW-06-AD. Applicability: Model 269C, serial number (S/N) 1865 through 1874 with a prefix of S; Model 269C-1, S/N 0169 through 0191; and Model 269D, Configuration A, S/N 0044 through 0050 with an A suffix, helicopters, with a lateral control trim actuator assembly, part number (P/N) 269A7316-13, installed, except for an actuator assembly containing a 30 drilled hole in the lateral trim control housing through the wall of the inner spring tube socket, certificated in any category. Compliance: Required as indicated, unless accomplished previously. To prevent separation of the inner spring tube from the lateral trim control housing, the associated loss of trim control, increased local resistance to right cyclic stick movement, and subsequent emergency landing or loss of control of the helicopter, accomplish the following: (a) For Model 269C, S/N 1865 through 1874, with a prefix of S, and Model 269C-1, S/N 0169 through 0191, before further flight, inspect the lateral control trim actuator assembly for a scuffmark, indentation, or outer spring guide tube deformation. Inspect for security of the inner spring tube in the socket of the lateral trim control housing by rotating and pulling on the inner spring tube. Examine the resin bead around the base of the inner spring tube and housing socket. Resin should be translucent dark pink in color to indicate a good bond. Conduct the inspection by following the Procedures in Part I of Schweizer Service Bulletin B-283.1 or C1B- 017.1, both dated March 4, 2005, respectively, as applicable. (1) If a scuffmark, indentation, or deformation exists on the outer spring tube, or the inner spring tube is loose or has motion, or the bonding is separated, before further flight, remove the lateral control trim actuator assembly; modify the trim control housing and the inner spring tube; and test run the actuator assembly. Modify and test run the actuator assembly by following the Procedures in Part II of Schweizer Service Bulletin B-283.1 or C1B- 017.1, both dated March 4, 2005, as applicable. (2) If no scuffmark, indentation, or deformation exists on the outer spring tube, or the inner spring tube is not loose, or the bonding is not separated, within the next 25 hours time-in-service (TIS), modify the lateral control trim actuator assembly as required by paragraph (a)(1) of this AD. (b) For Model 269D, Configuration A, S/N 0044 through 0050 with a suffix of A, within the next 50 hours TIS, modify the lateral control trim actuator assembly by following the Procedures in Schweizer Service Bulletin DB-012, paragraphs a through i, dated February 8, 2005. (c) To request a different method of compliance or a different compliance time for this AD, follow the procedures in 14 CFR 39.19. Contact the New York Aircraft Certification Office, FAA, for information about previously approved alternative methods of compliance. (d) Inspect, modify, and test the affected lateral control trim actuator assembly by following Schweizer Service Bulletin DB-012, dated February 8, 2005, or B-283.1, or C1B-017.1, both dated March 4, 2005, as applicable. The Director of the Federal Register approved this incorporation by reference in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Schweizer Aircraft Corporation, 1250 Schweizer Road, Horseheads, New York 14845. Copies may be inspected at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html . (e) This amendment becomes effective on June 2, 2005.