Document ID: chunk:federal_register_of_legislation:F2007L01377:body:0:p2
Version: federal_register_of_legislation:F2007L01377
Segment Type: other
Provision Reference: 
Character Range: 2820–4512

boltholes done before the effective date of this AD that use GE ASB No. CT7-TP S/B
                72-A0464, dated 25 February 2003; or Revision 1, dated 12 March 2003; or Revision 2, dated 9 May 2003; or Revision 3, dated 23 July 2004, comply with the requirements specified in this AD.

                Definition of Engine or Hot Section Module Shop Visit

                For the purposes of this AD, an engine or hot section module shop visit is defined as the introduction of the engine or hot section module into a shop that includes separating major case flanges.

             Note:  FAA AD 2007-08-01 Amdt 39-15018 dated 2 April 2007 refers.  This AD supersedes FAA AD 2005-18-01.
Compliance:     1. At the next engine or hot section module shop visit, but before accumulating an additional 6,000 cycles-in-service after the effective date of the AD, unless already done.

                2. From the effective date of this AD.

                3. From the effective date of this AD.
             This Amendment becomes effective on 7 June 2007.
Background:  This AD results from reports of six stage 2 turbine aft cooling plates found cracked during inspection.  The actions specified in this AD are intended to prevent stage 2 aft cooling plate separation, resulting in uncontained engine failure and damage to the aeroplane.

             This amendment results from the manufacturer expanding the list of affected engine models and identifying the affected stage 2 turbine aft cooling plates by serial number.

             The original issue of this AD became effective on 22 December 2005.

David Punshon
Delegate of the Civil Aviation Safety Authority

24 April 2007