Document ID: chunk:federal_register_of_legislation:F2009L01010:body:0:p2
Version: federal_register_of_legislation:F2009L01010
Segment Type: other
Provision Reference: 
Character Range: 3632–6248

required inspection, repair the crack(s) in accordance with one of the following, as applicable.  This repair eliminates the repetitive inspections (2,000 hours time in service intervals) specified in Requirement 1 of this Directive for that particular wing spar.

                  a. For Models SA226-T, SA226-T(B), SA226-AT, SA226-TC, SA227-TT,
                  SA-227-AT, SA227-AC, and SA-227-BC aircraft:  In accordance with Fairchild SA226/227 Series Structural Repair Manual, part number (P/N)
                  27-10054-079, pages 77 through 89; Initial Issue: 1 March 1983; Revision 38, dated 30 April 2008.

                  b. For Models SA227-CC and SA227-DC aircraft:  In accordance with Fairchild SA227 Series Structural Repair Manual, P/N 27-10054-127, pages 47 through 60; Initial Issue: 1 December 1991; Revision 17, dated
                  30 April 2008.

             The repetitive inspections required by Requirement 1 of this Directive may be terminated if the wing spar centre web repair specified in Requirement 2 of this Directive has been accomplished on both the left and right wing spar.  If one wing spar centre web has been repaired, then repetitive inspections are still required on the other one if the repair has not been incorporated.

             Note:  FAA AD 2005-06-13 Amdt 39-14023 refers.
Compliance:     1. Upon accumulating 6,500 hours time in service on each wing spar; within the next 2,000 hours time in service after the last inspection accomplished per the applicable Airworthiness Limitations Manual; or within the next 500 hours time in service after 7 July 2005, whichever occurs later, unless already accomplished; and thereafter at intervals not to exceed 2,000 hours time in service.

                2. Before further flight.

                The compliance times remain unchanged by this issue.
             This Amendment becomes effective on 9 April 2009.
Background:  The FAA received reports of cracks in the wing spar centre web cutout of affected aircraft.  The cracks were caused by fatigue, due to aircraft manoeuvring and wing gusts, and if not detected and corrected, could result in structural failure of the wing spar with consequent loss of control of the aircraft.

             Amendment 1 aligned this Directive with the latest FAA AD, with no change to technical content.

             Amendment 2 was issued to update the Requirement documents revision status.

             Amendment 3 is issued to update the Requirement documents revision status.

David Punshon
Delegate of the Civil Aviation Safety Authority

6 February 2009