Document ID: chunk:federal_register_of_legislation:F2008L02969:body:0:p1
Version: federal_register_of_legislation:F2008L02969
Segment Type: other
Provision Reference: 
Character Range: 0–3242

AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.001(1) of CASR 1998.  The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

Bell OH-58A (206A-1) Series Helicopters
AD/OH-58/5  Main Rotor Trunnion  9/2008

Applicability:  Model OH-58A (Bell 206A-1) series helicopters, including all certificated versions; with main rotor trunnions part number 206-010-104-3, 206-011-113-001, or
                206-011-120-001, installed.
Requirement:       1. For trunnions with less than 1,100 hours total time in service, accomplish a magnetic particle inspection in accordance with Bell Helicopter Alert Service Bulletin 206-80-7 Rev. A, or later FAA approved revision.

                   2. For trunnions with more than 1,100 hours total time in service and less than 1,700 hours total time in service, accomplish a magnetic particle inspection in accordance with Bell Helicopter Alert Service Bulletin 206-80-7 Rev. A, or later FAA approved revision.

                   3. For trunnions with 1,700 hours or more total time in service accomplish a magnetic particle inspection in accordance with Bell Helicopter Alert Service Bulletin 206-80-7 Rev. A, or later FAA approved revision.

                   4. For trunnions with time unknown, accomplish a magnetic particle inspection in accordance with Bell Helicopter Alert Service Bulletin 206-80-7 Rev. A, or later FAA approved revision.

                If a crack is detected during any inspection, before further flight, replace the cracked trunnion with a serviceable trunnion.

                If no cracking is detected, reassemble and install the main rotor hub on the helicopter in accordance with the applicable Model 206 Maintenance and Overhaul Manual.

                Installation of trunnion part number 206-011-113-103 constitutes terminating action to the requirements of this Directive.

                Note:  FAA AD 80-18-04 R1 Amdt 39-3954 refers.
Compliance:        1. Before accumulating 1,200 hours and repeat before accumulating 2,400 hours, and thereafter at intervals not to exceed 600 hours.

                   2. Within the next 100 hours time in service and repeat before accumulating 2,400 hours, and thereafter at intervals not to exceed 600 hours.

                3. Within the next 100 hours time in service, and thereafter at intervals not to exceed 600 hours.

                4. Within the next 100 hours time in service, and thereafter at intervals not to exceed 600 hours.
             This Airworthiness Directive becomes effective on 28 August 2008.
Background:  The FAA requires certain actions to prevent failure of the main rotor trunnion due to fatigue cracking.

David Villiers
Delegate of the