AD 70-02-06

70-02-06 BRITTEN-NORMAN, LTD: Amdt. 39-914. Applies to Britten-Norman Models BN.2 and BN.2A airplanes. Compliance is required within the next 50 hours' time in service, unless already accomplished. To reduce the possibility of failure of the elevator trim tab attachment structure due to cracking, accomplish the following: (a) Visually inspect the elevator trim tab hinge attachment structure for cracks in the angle of the elevator trailing edge member and elevator skin forward of the trim tab. (b) If cracks are found during the inspection required by paragraph (a) which do not exceed four inches in length, repair the cracks in accordance with Britten-Norman Service Bulletin No. BN-2/SB.1, Issue 5, dated 23 June 1969, or an FAA-approved equivalent, before reinforcing the elevator structure as required by paragraph (d). (c) If cracks are found during the inspection required by paragraph (a) which exceed four inches in length, replace the cracked member before reinforcingthe elevator structure as required by paragraph (d). (d) Reinforce the elevator structure by modifying the elevator trailing edge structure at the trim tab outboard hinge in accordance with Britten-Norman Modification Leaflet No. BN.2/NB/M/339, Issue 1, dated 23 July 1969, or an FAA-approved equivalent. This amendment becomes effective January 11, 1970.