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AD/BELL 205/1 Amdt 33 - Main Rotor Mast and Trunnion - Retirement Index Number (RIN) Recount/Inspection
Bell Helicopter Textron 205 Series HelicBell Helicopter Textron 205 Series Helicopters
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Bell Helicopter Textron 205 Series Helicopters
| AD/BELL 205/1 Amdt 33 | Main Rotor Mast and Trunnion - Retirement Index Number (RIN) Recount / Inspection | 16/2013 |
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| Applicability: | Model 205A, 205A-1, and 205B helicopters, with main rotor mast, part number204-011-450-001, -007, -105, -113, or -119, or main rotor trunnion, part number204-011-105-001, or -103, installed. |
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| Requirement: | For the main rotor mast and trunnion, determine the accumulated Retirement Index Number (RIN), inspect, and action in accordance with the technical requirements of FAA Emergency Airworthiness Directive 2000-15-52, Amendment 39-12042.Bell Helicopter Textron Alert Service Bulletin 205-00-76, dated 8 April 2000 approved by the United States Federal Aviation Administration (FAA) as an Alternative Method of Compliance (AMOC) to FAA AD 2000-15-52, Amendment 39-12042 is considered acceptable for compliance with the equivalent Requirement of this AD. |
| Compliance: | From the effective date of this directive. |
| This Amendment becomes effective on 2 August 2013. | |
| Background: | This Airworthiness Directive mandates life limits and inspections for critical components, to prevent their failure in service from metal fatigue. Amendment 33 removes the requirement for retiring bolts connecting the Drive Link to Rotating Swashplate at 500 hours Time in Service (TIS). Current TIS of 1000 hours per Bell Helicopter Textron Maintenance Manual BHT-205A1-MM-1 is considered acceptable. This amendment also notates the acceptability of an FAA approved AMOC for compliance with the equivalent requirement of this AD.Amendment 32 became effective on 9 August 2000 and was issued in response to a new FAA AD which was prompted by a report of another cracked main rotor mast. Metallurgical inspection revealed that the mast cracked as a result of fatigue in snap ring groove radii that were smaller than the 0.020 inch minimum allowable dimension. The FAA has concluded that several corrections to the RIN counting procedure are required based on a review of the fatigue data and previously issued Directives. |
| The original issue of this Airworthiness Directive became effective on5 September 1968. |
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Image unavailable in extracted text Mike Higgins Delegate of the Civil Aviation Safety Authority