Document ID: chunk:federal_register_of_legislation:F2006B02545:body:0:p2
Version: federal_register_of_legislation:F2006B02545
Segment Type: other
Provision Reference: 
Character Range: 2803–4628

AD/AT/17 Amdt 3 (Continued)

            Background: The initial issue of this AD was the result of in-flight incidents in the USA resulting in partial separation of the fin from the aircraft. Investigations found that the 3/16 inch thick aluminium alloy front spar attachment plate had failed through fatigue.
            Snow Engineering SL #138 introduced a recurring inspection and a terminating modification (steel attachment plate) which was mandated by the AD. Subsequently, an incident occurred where a 1/4 inch aluminium attachment fitting failed in identical circumstances. Amendment 1 expanded the applicability of the AD to all aircraft.
            The terminating modification of SL #138 was applicable to a limited range of models and serial numbers only.

            Snow Engineering has now issued SL #196 which expands the aircraft serial number applicability for the inspections and terminating modification. The FAA has issued AD 2000-11-05 which requires inspection of unmodified aircraft at 100 hour intervals rather than 25 hours as previously.

            Amendment 3 expands the applicability to all the aircraft models listed in Snow Engineering SL #155 which were not covered by the other SL's. The FAA has issued NPRM No. 2000-CE-59-AD to cover the serial numbers listed in SL#155 which are not covered by the other SLs and FAA ADs.

            Amendment 2 of this Airworthiness Directive became effective on 7 September 2000. Amendment 1 of this Airworthiness Directive became effective on 2 October 1996.
            The original issue of this Airworthiness Directive became effective on 11 December 1995.

 David Alan Villiers
 Delegate of the Civil Aviation Safety Authority 7 February 2003

 The above AD is notified in the Commonwealth of Australia Gazette on 26 February 2003.