Document ID: chunk:federal_register_of_legislation:F2007L02127:body:0:p1
Version: federal_register_of_legislation:F2007L02127
Segment Type: other
Provision Reference: 
Character Range: 0–3903

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/CF6/64  Fuel Shroud Retaining Snap Ring  8/2007

Applicability:  This AD applies to the following General Electric Company (GE) CF6-80C2 series turbofan engines that have incorporated GE Service Bulletin (SB) No. CF6-80C2 S/B 73-0253, or were built with the drainless manifold configuration at the factory during production assembly, and, have one or more fuel shroud retaining rings, part number (P/N) J204P0084, installed:
                CF6-80C2A1   CF6-80C2B1F
                CF6-80C2A2   CF6-80C2B2F
                CF6-80C2A3   CF6-80C2B4F
                CF6-80C2A5   CF6-80C2B5F
                CF6-80C2A8   CF6-80C2B6F
                CF6-80C2A5F  CF6-80C2B6FA
                CF6-80C2B1   CF6-80C2B7F
                CF6-80C2B2   CF6-80C2B8F
                CF6-80C2B4   CF6-80C2D1F
                CF6-80C2B6   CF6-80C2L1F

                This AD also applies to GE CF6-80E1A1, CF6-80E1A2, CF6- 80E1A3,
                CF6-80E1A4, and CF6-80E1A4B turbofan engines that have incorporated GE SB No. CF6-80E1 S/B 73-0026, or were built with the drainless manifold configuration at the factory during production assembly, and, have one or more fuel shroud retaining rings, P/N J204P0084, installed.

                Note 1:  These engines are installed on, but not limited to, Airbus A300, A310, A330, Boeing 747, 767, and McDonnell Douglas MD11 aeroplanes.

                Note 2:  For reference, the following Table 1 lists fuel manifold production P/Ns.

              Table 1.--Reference of Fuel Manifold Production P/Ns
              CF6-80C2 Series Engines
              Drained Fuel Manifold P/N  Drainless Fuel Manifold P/N
              (left side)                (left side)
              1303M31G04
              1303M31G06
              1303M31G07
              1303M31G08
              1303M31G10                 1303M31G12

              Drained Fuel Manifold P/N  Drainless Fuel Manifold P/N
              (right side)               (right side)
              1303M32G04
              1303M32G06
              1303M32G07
              1303M32G08
              1303M32G10                 1303M32G12

              CF6-80 E1 Series Engines
              Drained Fuel Manifold P/N  Drainless Fuel Manifold P/N
              (left side)                (left side)
              1700M34G01                 1303M31G12
              Drained Fuel Manifold P/N  Drainless Fuel Manifold P/N
              (right side)               (right side)
              1700M35G02                 1303M32G12

Requirement:  Replace any fuel shroud retaining rings, P/N J204P0084, with a fuel shroud retaining snap ring, P/N 2186M12P01.  Each engine has a total of 30 rings installed.

                 - For CF6-80C2 series engines, use paragraphs 3.A. through 3.C.(1)(b)2, of GE SB No. CF6-80C2 S/B 73-0337, Revision 3, dated 5 February 2007, to do the replacements.

                - For CF6-80E1 series engines, use paragraphs 3.A. through 3.C.(1)(b)2, of GE SB No. CF6-80E1 S/B 73-0075, Revision 1, dated 27 November 2006, to do the replacements.

             This AD requires no further action if the fuel shroud retaining snap rings were installed in