Document ID: chunk:federal_register_of_legislation:F2006B08486:body:0:p2
Version: federal_register_of_legislation:F2006B08486
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Character Range: 2888–3988

in the "Inspection Table for Cracking in the Airfoil Outer Fillet," Figure 5, of GE SB No. CF6-80E1 S/B 72-0217, Revision 2.

            For the purposes of this AD, cycles-since-overhaul (CSO) is defined as cycles since repair as described in GE SB No. CF6-80E1 S/B 72-0164 dated 16 March 1999.

            The original issue of this Directive became effective on 20 February 2003. This Amendment becomes effective on 30 September 2004.
            Background: An uncontained failure has been attributed to high-pressure turbine stage two nozzle guide vane distress. This directive introduced an inspection program to identify early signs of distress.

            This amendment reduces the inspection interval, because it has been determined that the cracks that develop could grow at a faster rate than originally expected.

            The original issue of this Directive became effective on 20 February 2003.

 Gary J Carr
 Delegate of the Civil Aviation Safety Authority 13 August 2004

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