Document ID: chunk:federal_register_of_legislation:F2005L01361:body:0:p2
Version: federal_register_of_legislation:F2005L01361
Segment Type: other
Provision Reference: 
Character Range: 3783–6938

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 model.

              Note 2:  FAA AD 2004-22-07 Amdt 39-13835 refers.
Compliance:     Initial Inspection Thresholds

                 1. Remains unchanged as detailed in the original issue of this Directive as: For all P/N NGVs, initial-inspect after 20 January 2005 (the effective date of the original issue of this Directive) at the following applicable initial inspection thresholds:

                   (a) For CF6-80C2A2, -80C2B2, and -80C2B2F engines, inspect at or before accumulating 1,600 HPT cycles-since-overhaul (CSO).

                   (b) For CF6-80C2A1, -80C2A3, -80C2A5, -80C2A5F, -80C2A8, - 80C2B1, -80C2B1F, -80C2B4, -80C2B4F, -80C2B5F, -80C2B6, -80C2B6F, - 80C2B6FA, -80C2B7F, -80C2B8F, and -80C2D1F engines, inspect at or before accumulating 800 CSO.

                   (c) For engines listed in compliance paragraphs (1)(a) and (1)(b) of this Directive that are already beyond the initial inspection thresholds, inspect at or before accumulating an additional 200 CSO after 20 January 2005 (the effective date of the original issue of this Directive).

               Reinspection or removal.

                2. In accordance with the Conditions and Reinspection intervals listed in the "Inspection Table for Cracking in the Airfoil Outer Fillet", Figure 5, Sheets 1 and 2, of GE SB No. CF6-80C2 S/B 72-0952 Revision 6.

                  (a) If the recommendation contained in Figure 5, Sheets 1 and 2, of GE SB No. CF6-80C2 S/B 72-0952, Revision 6, states "reinspect at next regular S2 Blade inspection," then for the purposes of this Directive, the next regular S2 Blade Inspection must be within the following intervals:

                     (i) For CF6-80C2D1F engines with 5.0 or more hours per flight leg, the next regular S2 Blade inspection means within 250 cycles-since-last-inspection (CSLI).

                     (ii) For all other engines applicable to this Directive, the next regular S2 Blade inspection means within 400 CSLI.
             This Amendment becomes effective on 7 July 2005.
Background:  The Directive requires GE CF6-80C2 turbofan engines with certain part number HPT S2 NGV's installed to undertake flex boroscope inspections of the HPT S2 NGV's. This Directive results from an uncontained engine failure due to HPT S2 NGV distress.  The actions detailed in this Directive are to prevent blade separation from HPT S2 NGV distress, which could result in an uncontained engine failure.

             This amendment makes correction to paragraph 2(a)(i) of the compliance section of this Directive to read 5.0 or more hours per flight leg instead of 5.0 or more cycles per flight leg. There are no other changes to the Directive.

             The original issue of this Directive became effective on 20 January 2005.

James Coyne
Delegate of the Civil Aviation Safety Authority

19 May 2005