Document ID: chunk:federal_register_of_legislation:F2006B09134:body:0
Version: federal_register_of_legislation:F2006B09134
Segment Type: other
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Character Range: 0–1410

COMMONWEALTH OF AUSTRALIA (Civil Aviation Regulations 1998), PART 39 - 105 CIVIL AVIATION SAFETY AUTHORITY
 SCHEDULE OF AIRWORTHINESS DIRECTIVES

 DHC-6 (Twin Otter) Series Aeroplanes

 AD/DHC-6/45
 Amdt 1

 Fuselage Side Frames Stns 218.125 and 219.525 4/92

 Applicability: Model DHC-6 Series with serial numbers 1 through 411 inclusive. Requirement:  1. Action in accordance with de Havilland SB 6/371.
            2. Incorporate de Havilland modifications 6/1461 (or 6/1553) and 6/1462.

            Note: Transport Canada AD CF-78-17 R1 refers.

             Compliance: 1. At intervals as specified in the requirement document, until modified in accordance with Requirement 2.

            2. Prior to 1 January 1996.

            The compliance of the previous issue of this Directive was as per Requirement Document.

            This amendment is effective from 2 April 1992.

 Background:   Inter-rivet cracking of the fuselage side frame skin flanges at Stations 218.125 and
            219.525 has occurred on a number of aircraft in service. Cracks are initiated by stress induced by riveting; side frames of material with improved stress corrosion resistance have been introduced by the manufacturer.

            Amendment 1 is issued to align this Directive with a revision of the relevant Country of Origin AD which requires terminating action in lieu of on going repetitive inspections.