80-18-04 R1: Main Rotor Trunnion

80-18-04 R1 BELL: Amendment 39-3884 as amended by Amendment 39-3954. Applies to Models 206A, 206B, 206A-1, 206B-1, 206L, and 206L-1 helicopters equipped with main rotor trunnions, P/N 206-010-104-3, 206-011-113-001, or 206-011-120-001 certificated in all categories (Airworthiness Docket No. 80-ASW-28). Compliance required as indicated. To prevent possible failure of the main rotor trunnion, P/N 206-010-104-3, 206-011-113- 001, and 206-011-120-001 due to fatigue cracks, accomplish the following, unless already accomplished, in accordance with Bell Helicopter Textron Alert Service Bulletin 206-80-7, Revision A, dated February 26, 1980 (206A, 206B, 206A-1, 206B-1) or 206L-80-9, Revision A, dated February 26, 1980 (206L, 206L-1) or FAA approved equivalent. a. For trunnions with less than 1,100 hours' total time in service, on the effective date of this AD, accomplish a magnetic particle inspection prior to attaining 1,200 hours and again prior to attaining 2,400 hours,and thereafter at intervals not to exceed 600 hours. b. For trunnions with more than 1,100 hours and less than 1,700 hours' total time in service, on the effective date of this AD, accomplish a magnetic particle inspection within the next 100 hours' time in service and again prior to attaining 2,400 hours, and thereafter at intervals not to exceed 600 hours. c. For trunnions with 1,700 hours or more total time in service, on the effective date of this AD, accomplish a magnetic particle inspection within the next 100 hours' time in service, and thereafter at intervals not to exceed 600 hours. d. For trunnions with time unknown, on the effective date of this AD, accomplish a magnetic particle inspection within the next 100 hours' time in service, and thereafter at intervals not to exceed 600 hours. e. If a crack is found, remove and replace the trunnion before further flight. f. If no cracks are found, reassemble and install the main rotor hub on the helicopter in accordance with the pertinent Model 206 Maintenance and Overhaul Manual and continue the repetitive inspections specified above. g. Report in writing any cracks found during the inspections required herein to Chief, Engineering and Manufacturing Branch, Federal Aviation Administration, Southwest Region, P.O. Box 1689, Fort Worth, Texas 76101. Each report must include the location of the cracks and the trunnion total time in service. Reporting approved by the Office of Management and Budget under OMB No. 04-R0174. h. If trunnion P/N 206-011-113-103 (206A, 206B, 206A-1, 206B-1) or P/N 206- 011-120-103 (206L, 206L-1) is installed, the inspections specified in this AD are not required. i. The helicopter may be flown in accordance with FAR 21.197 to a base where inspections can be performed. j. Upon submission of substantiating data through an FAA Aviation Safety Inspector, the Chief, Engineering and Manufacturing Branch, Southwest Region, may adjust the inspection intervals. Amendment 39-3884 became effective September 15, 1980. This amendment 39-3954 becomes effective November 24, 1980.