Airworthiness directives › 2005-10-13
AD 2005-10-13 Airworthiness Directives; Rolls-Royce Corporation (Formerly Allison Engine Company) 250-B17B, -B17C, -B17D, -B17E, -C20, -C20B, -C20F, -C20J, -C20S, and -C20W Turboprop and Turboshaft Engines
Applicability*9
This AD applies to Rolls-Royce Corporation (RRC) (formerly Allison Engine Company) 250-B17B, B17C, -B17D, -B17E, -C20, -C20B, -C20F, -C20J, -C20S, and -C20W turboprop and turboshaft engines that do not have turbine energy absorbing ring, RRC part number (P/N) 23035175, or an equivalent FAA-approved serviceable turbine energy absorbing ring, installed. These engines are installed on, but not limited to, the following aircraft: Agusta A109 Agusta A109A Agusta A109A II B-N Group BN-2T Bell 206A Bell 206B Bell 206L Bell Helicopter Textron 47G-2A (Supplemental Type Certificate (STC) SH657NW) Bell Helicopter Textron 47G-2A-1 (STC SH657NW) Bell Helicopter Textron 47G-3B (STC SH657NW) Bell Helicopter Textron 47G-3B-1 (TH-13T) (STC SH657NW) Bell Helicopter Textron 47G-3B-2 (STC SH657NW) Bell Helicopter Textron 47G-3B-2A (STC SH657NW) Bell Helicopter Textron 47G-4 (STC SH657NW) Bell Helicopter Textron 47G-4A (STC SH657NW) Bell Helicopter Textron 47G-5 (STC SH657NW) Bell Helicopter Textron 47G-5A (STC SH657NW) Eurocopter Deutchland BO-105C Eurocopter Deutchland BO-105C (STC SH218NW-D) Eurocopter Deutchland BO-105S Eurocopter France AS355E Eurocopter France AS355F Eurocopter France AS355F1 Eurocopter France AS355F2 FH-1100 Manufacturing Corp FH-1100 Hiller Aviation UH-12D (Army UH-23D) (STC SH177WE) MDHI 369D MDHI 369E MDHI 369HM MDHI 369HS MDHI 369HE Rogerson Hiller Corporation UH-12E (STC SH178WE) Rogerson Hiller Corporation UH-12E-L (STC SH178WE) SIAI Marchetti s.r.l. SF600
Compliance
You are responsible for having the actions required by this AD performed at the next time the gas producer turbine rotor is disassembled for any reason, or within 1,750 hours time-since-last-overhaul, time-since-new, time-since-last-heavy-maintenance, or time-since-last-hot section inspection after the effective date of this AD, whichever occurs first, but no later than October 31, 2011, unless already done.
Required actions
Install a turbine energy absorbing ring, RRC P/N 23035175, or an equivalent FAA-approved turbine energy absorbing ring, in the plane of the 1st stage turbine wheel, using paragraphs 1.M., 2.A., and 2.B. of Rolls-Royce Corporation Alert Commercial Engine Bulletin No. CEB-A-1255, Revision 4, dated September 29, 2004, to do the installation. Alternative Methods of
Unsafe condition
This AD results from an unacceptable rate of uncontained 1st stage turbine wheel failures. We are issuing this AD to minimize the risk of uncontained 1st stage turbine wheel fragments from causing damage to the aircraft or damage to the second engine on twin-engine installations, which could lead to loss of control and loss of the aircraft.
Read the original on the Federal Register →
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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