Document ID: chunk:federal_register_of_legislation:F2006B04846:body:0:p2
Version: federal_register_of_legislation:F2006B04846
Segment Type: other
Provision Reference: 
Character Range: 2997–4351

Amendment becomes effective on 1 October 2003.

           Background: The DGAC received a further report of a wing in-flight structural failure. Spar inspections in accordance with Avion Mudry Service Bulletin (SB) No. 15 Revision 1, and the wing covering inspection in accordance with Cap Aviation SB 990501 (mandated by the original issue of this AD) do not appear to have been effective in detecting defects in the wing structure. A single exceedence of the wing limit load factor can result in compression failures inside the wing main spar. These failures can then spread under loads within the aircraft's flight envelope. In extreme cases this can lead to in-flight wing failure within the aircraft's approved flight envelope.

           Hence, aircraft may already contain defects which will remain undetected by SB15 inspection methods. Amendment 2 introduced a new inspection process that replaces the inspection previously required by SB No. 15.

           Amendment 3 is issued in response to a new DGAC AD which was prompted by a new in-flight fracture of a CAP 10B wing in June 2003. Initial investigation indicates a possible incorrect application of SB No. 16.

 David Villiers
 Delegate of the Civil Aviation Safety Authority 25 September 2003

 The above AD is notified in the Commonwealth of Australia Gazette on 1 October 2003.