Document ID: chunk:federal_register_of_legislation:F2008L02968:body:0
Version: federal_register_of_legislation:F2008L02968
Segment Type: other
Provision Reference: 
Character Range: 0–2186

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-58/4  Tail Rotor Blade Skin Surface  9/2008

Applicability:  Model OH-58A (Bell 206A-1) series helicopters, including all certificated versions; with tail rotor blades part number 206-010-750-005 and -007, installed.
Requirement:       1. Perform a visual inspection for chordwise cracks in the tail rotor blade skin surfaces in the area between Blade Station 7.1 and 11.1, using a 3x or higher magnifying glass (Blade Station 0 is the centre of the tail rotor yoke).

                   If cracking is detected during any inspection, before further flight, replace affected blade(s).

                   2. Tail rotor blades with 450 hours or more total time in service must be removed from service.

                   3. Tail rotor blades with less than 450 hours total time in service must be removed from service.

                Note:  FAA AD 80-17-05 Amdt 39-3875 refers.
Compliance:        1. Before the first flight of each day; until blade replacement per Requirement
                   2 or 3.

                   2. Within the next 50 hours time in service, unless already accomplished.

                   3. Upon the accumulation of 500 hours total time in service.
                This Airworthiness Directive becomes effective on 28 August 2008.
Background:     The FAA requires certain actions to prevent failure of the tail rotor blades due to fatigue cracking.

David Villiers
Delegate of the Civil Aviation Safety Authority

14 July 2008