Document ID: chunk:federal_register_of_legislation:F2005L01361:body:0:p1
Version: federal_register_of_legislation:F2005L01361
Segment Type: other
Provision Reference: 
Character Range: 0–4070

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/CF6/57 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/CF6/57 Amdt 1  HPT S2 NGV Distress  7/2005

Applicability:  This AD applies to General Electric Company (GE) CF6-80C2A1, -80C2A2,
                -80C2A3, -80C2A5, -80C2A5F, -80C2A8, -80C2B1, -80C2B1F, - 80C2B2,
                -80C2B2F, -80C2B4, -80C2B4F, -80C2B5F, -80C2B6, -80C2B6F, - 80C2B6FA,
                -80C2B7F, -80C2B8F, and -80C2D1F turbofan engines, with the part numbers (P/Ns) of high pressure turbine (HPT) stage 2 nozzle guide vanes (HPT S2 NGVs) listed in the following Table 1, installed:

                Table 1. -Affected HPT S2 NGVs
                HPT S2 NGV:                                                                                                                                                                                Provided that:
                  P/N 1347M66G03, P/N 1347M66G04, and P/Ns 1815M81G01 through 1815M81G07.                                                                                                                   Insert, P/N 1957M40G01 or P/N 1957M40G02, was installed during repair.
                  P/Ns 9373M80G07 through 9373M80G22, and P/Ns 9373M80G25 through 9373M80G32.                                                                                                               Insert, P/N 1957M40G01 or P/N 1957M40G02, was installed during repair, or NGV was repaired by GE between 1 April 1998 through 30 September 1999.
                  P/Ns 9373M80G33 through 9373M80G36                                                                                                                                                        Part was repaired.
                  P/Ns 2080M38G01 through 2080M38G16, and P/Ns 2080M38G19 through 2080M38G24.                                                                                                               Insert, P/N 1957M40G01 or P/N 1957M40G02, was installed during modification or repair.
                  P/Ns 2080M19G01 through 2080M19G04, P/Ns 2080M19G07 through 2080M19G16, P/Ns 2080M19G19 through 2080M19G46, P/Ns 2080M19G49 through 2080M19G70, and P/Ns 2080M19G73 through 2080M19G80.   Insert, P/N 1957M40G01 or P/N 1957M40G02, was installed during modification or repair.

              Note 1:  These engines are installed on, but not limited to, Airbus A300, Airbus A310, Boeing 747, Boeing 767, and McDonnell Douglas MD-11 aeroplanes.
Requirement:     1. Initial Inspection

                 Flex-boroscope inspect the NGVs following paragraph 3.B.(3) through 3.B.(5) of Accomplishment Instructions of GE Service Bulletin (SB) No. CF6-80C2 S/B 72-0952, Revision 6 dated 5 May 2003.

                 For NGVs installed in engines operated as more than one engine model configuration (thrust level), use the lowest applicable initial inspection threshold, and use the reinspection intervals associated with the current engine model.

                 2. Reinspection or removal.

                 Reinspect or remove from service NGVs as detailed in GE SB No. CF6-80C2 S/B 72-0952, Revision 6.

                 For NGVs installed in engines operated as more than one engine model configuration (thrust level), use the lowest applicable initial inspection threshold, and use the reinspection intervals associated with the current engine