Document ID: chunk:federal_register_of_legislation:F2006B02549:body:0:p2
Version: federal_register_of_legislation:F2006B02549
Segment Type: other
Provision Reference: 
Character Range: 2765–5350

500 Series Aeroplanes

 AD/AT/23 Amdt 1 (continued)

              Compliance: 1. Initially inspect upon the accumulation of 1,250 total hours time in service or within the next 100 hours time in service after 30 September 2004, whichever occurs later. Inspect thereafter at intervals not to exceed 100 hours time in service, until the upper and diagonal longerons are replaced and modified in accordance with SL No. 218B, dated 10 November 2003.

2.         Initially inspect upon the accumulation of 1,250 total hours time in service or within the next 100 hours time in service after the last inspection required by the original issue of this Directive, whichever occurs later. Inspect thereafter at intervals not to exceed 100 hours time in service, until the upper and diagonal longerons are replaced and modified in accordance with SL No. 218B, dated 10 November 2003.

3.         Initially inspect upon the accumulation of 4,800 total hours time in service or within the next 100 hours time in service after 30 September 2004, whichever occurs later. Inspect thereafter at intervals not to exceed 100 hours time in service, until the upper longeron is replaced and modified in accordance with SL No. 195A, revised 10 November 2003.

4.         Initially inspect upon the accumulation of 2,800 total hours time in service or within the next 100 hours time in service after 30 September 2004, whichever occurs later. Inspect thereafter at intervals not to exceed 100 hours time in service, until the upper longeron is replaced and modified in accordance with SL No. 195A, revised 10 November 2003.

            This Amendment becomes effective on 30 September 2004.

            Background: The FAA received reports of three occurrences of cracks found on the left hand upper longeron and upper diagonal support tubes where they intersect on the left side of the fuselage frame just forward of the vertical fin front spar attachment point, on Model AT-602 aircraft. The cracks were found by the pilot and/or ground crew when they noticed excessive movement of the empennage due to the loss of torsional rigidity.

            Amendment 1 is issued in response to a new FAA AD, which adds certain AT-500 series aircraft to applicability, changes the compliance times, and incorporates new and revised manufacturer service information that contains a terminating action for the repetitive inspection requirement.

 David Villiers
 Delegate of the Civil Aviation Safety Authority 20 August 2004

 The above AD is notified in the Commonwealth of Australia Gazette on 8 September 2004.