Document ID: chunk:federal_register_of_legislation:F2006B03658:body:0:p2
Version: federal_register_of_legislation:F2006B03658
Segment Type: other
Provision Reference: 
Character Range: 2990–5780

A) in accordance with Part II of the Accomplishment Instructions section of MSB SB 71-3144 Revision 1, Revised April 1999.

5.        For aircraft equipped with a P/N 129-910047-1 or 910047-13 engine truss assembly, install a P/N 129-910047-15 truss identification placard on the engine truss assembly in accordance with the Accomplishment Instructions section of SB 71-3024, Issued September 1997.

           Note: FAA AD 2001-22-16 Amdt 39-12495 refers.

 Compliance: 1.a. As specified in the Requirement document.

           1.b. Within 100 hours time in service after 24 January 2002.

              2.  Upon accumulating 100 hours time in service on the engine truss assembly, or within 25 hours time in service after 24 January 2002, whichever occurs later; thereafter at intervals not to exceed 100 hours time in service until Requirement 4 is accomplished.

3.a.   Upon accumulating 200 hours time in service on the engine truss assembly, or within 25 hours after 24 January 2002, whichever occurs later, unless already accomplished; thereafter at intervals not to exceed 200 hours time in service; until Requirement 3.b. is accomplished.

3.b.  Upon accumulating 1,200 hours time in service on the engine truss assembly, or within 100 hours time in service after 24 January 2002, whichever occurs later.

4.        Upon accumulating 8,000 hours time in service on the engine truss assembly, or at the next engine truss assembly removal, whichever occurs later.

5.        Within 12 months after 24 January 2002 or upon installation of a P/N 129- 910047-1 or 129-910047-13 engine truss assembly, whichever occurs later.

               This amendment becomes effective on 24 January 2002.

               Background: Reports were received of cracks in the welded joints of the engine truss, which if detected, could lead to engine separation from the aircraft.

               Amendment 1 referenced later service information and required fluorescent penetrant inspection.

               Amendment 2 is issued in response to a new FAA AD which was prompted by further reports of engine truss fatigue cracks on Models 1900, 1900C, and 1900D aircraft.
               The reports reference aircraft that are in compliance with FAA AD 95-02-18. The fatigue cracks are developing as a result of operational stresses in joints, welded bracketry, and linoil holes sealed by screws.

               Amendment 1 to this Airworthiness Directive became effective on 27 April 1995.

               The original issue of this Airworthiness Directive became effective on 5 September 1991.

    David Alan Villiers
    Delegate of the Civil Aviation Safety Authority 4 December 2001

    The above AD is notified in the Commonwealth of Australia Gazette on 9 January 2002.