Document ID: chunk:federal_register_of_legislation:F2011L02514:body:0:p1
Version: federal_register_of_legislation:F2011L02514
Segment Type: other
Provision Reference: 
Character Range: 0–3195

AIRWORTHINESS DIRECTIVE
On the effective date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below revokes Airworthiness Directive (AD) AD/CF6/74 and issues the following 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/CF6/74 Amdt 1   High Pressure Compressor   24/2011
                   Spool Shaft Stage 14 Disc

Applicability:  General Electric Company (GE) CF6-80C2 and CF6-80E1 series turbofan engines with high-pressure compressor rotor (HPCR) spool shaft stage 14 disks, part number (P/N) 1703M49G02, 1703M49G03, or 1509M71G10 installed.

                Note 1:  These engines are installed on, but not limited to, Airbus A300-600R/F, A310-200/300, and A330-200/300, and Boeing 747-200B/300/400/400D/400F,
                767-200/300/400F/400ER, and MD-11 aeroplanes.
Requirement:    Using the following Alert Service Bulletin (ASB) instructions, perform a one-time ECI of the HPCR spool shaft stage 14 disk web for crack indications, and remove from service those parts found to be cracked.

                Use paragraphs 3.B.(1) through 3.B.(5) of the Accomplishment Instructions of GE ASB No. CF6-80C2 S/B 72-A1122, Revision 1, dated 19 June 2006, to ECI the
                CF6-80C2 series engine HPCR spool shaft stage 14 disk web at the module level.

                Use paragraph 3.C.(1) of the Accomplishment Instructions of GE ASB No.
                CF6-80C2 S/B 72-A1122, Revision 1, dated 19 June 2006, to ECI the CF6-80C2 series engine HPCR spool shaft stage 14 disk web at the piece-part level.

                Use paragraphs 3.B.(1) through 3.B.(5) of the Accomplishment Instructions of GE ASB No. CF6-80E1 S/B 72-A0258, Revision 1, dated 15 June 2006, to ECI the
                CF6-80E1 series engine HPCR spool shaft stage 14 disk web at the module level.

                Use paragraph 3.C.(1) of the Accomplishment Instructions of GE ASB No. CF6-80E1 S/B 72-A0258, Revision 1, dated 15 June 2006, to ECI the HPCR spool shaft stage 14 disk web at the piece-part level.

                Previous Credit

                Performance of a one-time ECI of the HPCR spool shaft stage 14 disk web for crack indications, using the procedures defined in the following service documents before the original effective date of this AD, satisfies the compliance requirements specified in this AD:

                a)        GE ASB No. CF6 80C2 S/B 72-A1122, dated 19 January 2004, for
                CF6-80C2 series engines.

                b)        GE ASB No. CF6 80E1 S/B 72-A0258, dated 19 January 2004, for CF6-80E1 series engines.

             Later revisions to GE ASB No. CF6-80C2