Document ID: chunk:federal_register_of_legislation:F2011L00236:body:0:p2
Version: federal_register_of_legislation:F2011L00236
Segment Type: other
Provision Reference: 
Character Range: 3218–5838

No. 935-314-S4, dated January 28, 2008, to rework the LPT case; or

                  (b) Install an LPT case that has skin doubler pads and deflectors.

             Previous Credit

             If you previously performed the actions specified in Requirement 1 through Requirement 2 of this AD, using the rework procedures in the following service documents before the effective date of this AD, you have satisfied the compliance requirements of this AD:

                (a) GE SB No. CF6-80C2 S/B 72-1171, dated 25 May 2005 and RD No.
                935-314-S2, dated 4 January 2006, or RD No. 935-314-S3, dated
                10 August 2006.

                (b) GE SB No. CF6-80E1 S/B 72-0303, dated 1 June 2005 and RD No. 935-314-S2, dated 4 January 2006, or RD No. 935-314-S3, dated 10 August 2006.

             Later revisions to GE SB No. CF6-80C2 S/B 72-1171, Revision 1, dated 1 February 2006 or GE SB No. CF6-80E1 S/B 72-0303, Revision 1, dated 1 February 1, 2006, approved by the United States Federal Aviation Administration (FAA) as an Alternative Method of Compliance (AMOC) to FAA 2008-21-11 Amdt 39-15695, are considered acceptable for compliance with the equivalent Requirements of this AD.

             Parts Identification

             LPT case skin doubler pads and deflectors are distinct and separate parts.  For identification purposes, a deflector pad is a square-shaped plate with no threaded stud on it, and a deflector has a threaded stud on it.

             Note 2:  FAA AD 2008-21-11 Amdt 39-15695 dated 10 October 2008 refers.
Compliance:  The next time the LPT module is completely disassembled to piece-part level, but not to exceed 8 years after the original effective date of this AD, unless the actions have already been done.
             This Amendment becomes effective on 14 February 2011.

Background:  This AD results from four events in which hardware fragments were liberated into the engine flowpath and wore through LPT cases on CF6-80C2 and CF6-80E1 series engines.  The issuing of this AD is intended to prevent an uncontained release of engine debris and loss of the structural integrity of the mount system that supports the engine.  Loss of the mount system structural integrity could result in the engine separating from the aeroplane.

             Amendment 1 notates the acceptability of an FAA Approved AMOC for compliance with the equivalent requirements of this AD.

             The original issue of this Directive became effective on 18 December 2008.

David Villiers
Delegate of the Civil Aviation Safety Authority

8 February 2011