Airworthiness directives › 2004-16-07
AD 2004-16-07 Airworthiness Directives; General Electric Company (GE); CT7-2D1 Turboshaft Engines.
Applicability*9
This AD applies to General Electric Company (GE) CT7-2D1 turboshaft engines with turbine stage 2 aft cooling plates, part number (P/N) 6064T07P02, and serial numbers (SN) starting with GFFN****, GFFP****, GFFR0*** through GFFR7***, GFFR81** through GFFR89**, GFFR8A** through GFFR8G**, GFFR8H92 through GFFR8H99, and GFFR8H9A through GFFR8H9N installed. Asterisks represent any subsequent number or letter that follow the root SN. These engines are installed on, but not limited to, Sikorsky S-70 helicopters.
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. Cooling Plate Removal (f) At the next disassembly of the gas generator turbine rotor assembly at an FAA-approved overhaul facility, but not later than 5,000 cycles-since-new, replace any turbine stage 2 aft cooling plate, P/N 6064T07P02, with SNs starting with GFFN****, GFFP****, GFFR0*** through GFFR7***, GFFR81** through GFFR89**, GFFR8A** through GFFR8G**, GFFR8H92 through GFFR8H99, and GFFR8H9A through GFFR8H9N, with a cooling plate that does not have a SN specified in this AD. (g) After the effective date of this AD, do not install stage 2 aft cooling plate, P/N 6064T07P02, SNs GFFN****, GFFP****, GFFR0*** through GFFR7***, GFFR81** through GFFR89**, GFFR8A** through GFFR8G**, GFFR8H92 through GFFR8H99, and GFFR8H9A through GFFR8H9N into any engine. Material Incorporated by Reference (h) None. Related Information (i) GE CT7-TS Alert Service Bulletin 72-A0032, dated June 11, 2003, provides additional information regarding the disassembly of the gas generator turbine rotor assembly. Issued in Burlington, Massachusetts, on July 29, 2004. Jay J. Pardee, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. 04-17755 Filed 8-5-04; 8:45 am] BILLING CODE 4910-13-P
Unsafe condition
This AD results from an uncontained failure of a turbine stage 2 aft cooling plate in a GE CT7 turboprop engine. We are issuing this AD to prevent a similar uncontained failure of turbine stage 2 aft cooling plates in GE CT7-2D1 turboshaft engines.
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