Airworthiness directives › 2004-09-34
AD 2004-09-34 Airworthiness Directives; General Electric Company CF6-80E1 Model Turbofan Engines
Applicability*9
This AD applies to General Electric Company (GE) CF6-80E1 engine models with high pressure turbine (HPT) stage 2 (S2) nozzle guide vanes (NGVs), part number (P/N) 1647M84G09 or 1647M84G10, installed. These engines are installed on, but not limited to, Airbus A330 airplanes.
Compliance
You are responsible for having the actions required by this AD performed within the compliance times specified unless the actions have already been done. NGVs Previously Inspected by Flex Borescope (f) For NGVs inspected by flex borescope before the effective date of this AD, reinspect or remove from service the NGVs using the Conditions and Reinspection intervals listed in the “Inspection Table for Cracking in the Airfoil Outer Fillet,” Figure 5, of GE Service Bulletin (SB) No. CF6-80E1 S/B 72-0217, Revision 2, dated January 5, 2004, or within 200 cycles-in-service-since-last inspection (CSLI), whichever is earlier. NGVs Not Previously Inspected by Flex Borescope (g) For NGVs not previously inspected by flex borescope, remove from service, or inspect using the Accomplishment Instructions of GE SB No. CF6-80E1 S/B 72-0217, Revision 2, dated January 5, 2004, at the following: (1) For NGVs with more than 800 cycles-since-overhaul (CSO) on the effective date of this AD, within 50 cycles-in-service (CIS) after the effective date of this AD. (2) For NGVs with 800 or fewer CSO on the effective date of this AD, at the first regular HPT blade inspection after 800 CSO, but before reaching 900 CSO. (3) Reinspect or remove from service NGVs using the Conditions and Reinspection intervals listed in the “Inspection Table for Cracking in the Airfoil Outer Fillet,” Figure 5, of GE SB No. CF6-80E1 S/B 72-0217, Revision 2, dated January 5, 2004. Cycles-Since-Overhaul Defined (h) For the purposes of this AD, cycles-since-overhaul (CSO) is defined as cycles since repair as described in GE SB No. CF6-80E1 S/B 72-0164, dated March 16, 1999. Engines Not Affected by this AD (i) Engines configured with HPT S2 NGV P/Ns 1647M84G05, 1647M84G06, 2080M47G01, 2080M47G02, 2086M62G03, or 2086M62G04 are not affected by this AD. Alternative Methods of
Unsafe condition
This AD results from inspection findings of HPT S2 NGVs that show cracks from distress could occur sooner and propagate faster than originally predicted. We are issuing this AD to prevent failure of HPT rotor blades from HPT S2 NGV distress, which could result in an uncontained engine failure.
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