Airworthiness Directive · Amendment 39-13835 · General Electric Company (GE) CF6-80C2 Turbofan Engines
General Electric Company (GE) CF6-80C2 Turbofan Engines
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:
| 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 April 1, 1998 through September 30, 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. |
These engines are installed on, but not limited to, Airbus A300, Airbus A310, Boeing 747, Boeing 767, and McDonnell Douglas MD-11 airplanes.
The FAA is adopting a new airworthiness directive (AD) for GE CF6-80C2 turbofan engines with certain part number (P/N) high pressure turbine stage 2 nozzle guide vanes (HPT S2 NGVs) installed. This AD requires flex borescope inspections of HPT S2 NGVs installed in CF6- 80C2 turbofan engines. This AD results from an uncontained engine failure due to HPT S2 NGV distress. We are issuing this AD to prevent blade separation from HPT S2 NGV distress, which could result in an uncontained engine failure.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
Flex-borescope 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 May 5, 2003, as follows:
(1) For all P/N NGVs, initial-inspect after the effective date of this AD at the following applicable initial inspection thresholds:
(i) For CF6-80C2A2, -80C2B2, and -80C2B2F engines, inspect at or before accumulating 1,600 HPT cycles-since-overhaul (CSO).
(ii) 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.
(2) For engines listed in paragraphs (f)(1)(i) and (f)(1)(ii) of this AD that are already beyond the initial inspection thresholds, inspect at or before accumulating an additional 200 CSO after the effective date of this AD.
Reinspect or remove from service NGVs following 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, dated May 5, 2003.
(h) If the recommendation contained in Figure 5, Sheets 1 and 2, of GE SB No. CF6-80C2 S/B 72-0952, Revision 6, dated May 5, 2003, states “reinspect at next regular S2 Blade inspection,” then for the purposes of this AD, the next regular S2 Blade Inspection must be within the following intervals:
(1) For CF6-80C2D1F engines with 5.0 or more cycles per flight leg, the next regular S2 Blade inspection means within 250 cycles-since-last-inspection (CSLI).
(2) For all other engines listed in paragraph (c) of this AD, the next regular S2 Blade inspection means within 400 CSLI.
(i) 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.
