Airworthiness directives › 2005-26-06
AD 2005-26-06 Airworthiness Directives; General Electric Company CF6-45A, CF6-50A, CF6-50C, and CF6-50E Series Turbofan Engines
Applicability*9
This AD applies to General Electric Company (GE) CF6-45A, CF6-50A, CF6-50C, and CF6-50E series turbofan engines. These engines are installed on, but not limited to, Boeing DC10 and 747 series airplanes, and Airbus Industrie A300 series airplanes.
Compliance
You are responsible for having the actions required by this AD performed at the next disassembly of the LPT stage 2 interstage seal assembly and stage 3 interstage seal assembly from the LPT stator after the effective date of this AD, but no later than December 31, 2010, unless the actions have already been done. Stage 2 Interstage Seal Assemblies (f) Remove from service the pre-GE Service Bulletin (SB) No. CF6-50 72-1268 configuration LPT stage 2 interstage seal assembly. (g) Install a new or reworked configuration LPT stage 2 interstage seal assembly, part number (P/N) 9198M81G05, 2092M13G01, 2092M13G02, or 2092M13G03, or other FAA-approved equivalent part. (h) Information on reworking the pre-SB No. CF6-50 S/B 72-1268 configuration stage 2 interstage seal assembly to the new configuration can be found in GE SB No. CF6-50 S/B 72-1268, dated December 16, 2004. Stage 3 Interstage Seal Assemblies (i) Remove from service the pre-SB No. CF6-50 S/B 72-1268 configuration stage 3 interstage seal assembly. (j) Install a new or reworked configuration LPT stage 3 interstage seal assembly, P/N 9044M29G17 or 2092M14G01, or other FAA-approved equivalent part. (k) Information on reworking the pre-SB No. CF6-50 S/B 72-1268 configuration stage 3 interstage seal assembly to the new configuration can be found in GE SB No. CF6-50 S/B 72-1268, dated December 16, 2004. Prohibition of Pre-SB No. CF6-50 S/B 72-1268 Configurations (l) After the effective date of this AD, do not install pre-SB No. CF6-50 S/B 72-1268 configuration LPT stage 2 interstage seal assemblies or stage 3 interstage seal assemblies into any engine. Alternative Methods of
Unsafe condition
This AD results from reports of fan mid shaft separation, leading to separation of the low pressure turbine (LPT) stage 1 disk, disk overspeed, and uncontained engine failure. We are issuing this AD to prevent uncontained engine failure and damage to the airplane.
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The directive text above is reproduced from the Federal Register, a work of the United States government and in the public domain. The separation into applicability, compliance and required actions is TrackAD's.*1