Document ID: chunk:federal_register_of_legislation:F2007L01070:body:0
Version: federal_register_of_legislation:F2007L01070
Segment Type: other
Provision Reference: 
Character Range: 0–2241

AIRWORTHINESS DIRECTIVE
For the reasons set out in the background section, the CASA delegate whose signature appears below issues the following Airworthiness Directive (AD) under subregulation 39.001(1) of CASR 1998.  The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct the unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentioned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section.

General Electric Turbine Engines - CF6 Series
AD/CF6/63  Fwd Engine Mount Platform and  5/2007
           Fwd Engine Mount Yoke

Applicability:  General Electric Company turbofan engines listed in FAA AD 2007-05-14, with cast titanium assembly engine mount platforms part numbers 1292M13G06, 1301M28G08, 1459M70G07, and 1846M24G04 and cast titanium assembly engine mount yokes part numbers 9383M43G14 and 9383M43G16, installed.

                The applicable engines are installed on, but not limited to, Boeing 747, Boeing 767, MD-11, Airbus A300-600, and Airbus A310 aircraft.
Requirement:    Action in accordance with the technical requirements of FAA AD 2007-05-14 Amdt 39-14975.

                Note:  General Electric Company Service Bulletins CF6-80C2 S/B 72-1206, dated
                23 December 2005, and CF6-80C2 S/B 72-1207 Revision 01, dated 5 July 2006, refer.
Compliance:     As specified in the Requirement document, with a revised effective date of
                10 May 2007.
                This Airworthiness Directive becomes effective on 10 May 2007.
Background:     The FAA received a report of cracks, in a weld-repaired area on a forward engine mount platform and a forward engine mount yoke, detected during a fluorescent penetrant inspection.  These parts were weld-repaired during manufacture.  Undetected cracking in the forward engine mount platform and/or forward engine mount yoke could result in possible separation of the engine from the aircraft.

David Punshon
Delegate of the Civil Aviation Safety Authority

28 March 2007