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AD/AL 250/87 - Containment Ring
Allison Turbine Engines - 250 SeriesAllison Turbine Engines - 250 Series
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Allison Turbine Engines - 250 Series
| AD/AL 250/87 | Containment Ring | 8/2005 |
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| Applicability: | 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 part number (P/N) 23035175, or an equivalent approved serviceable turbine energy absorbing ring installed. |
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| Requirement: | Unless previously accomplished, install a turbine energy absorbing ring, RRC P/N 23035175, or an equivalent 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 29 September 2004 to do the installation.Note: FAA AD 2005-10-13Amdt 39-14090 refers. |
| Compliance: | 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 Directive, whichever occurs first, but no later than 31 October 2011. |
| This Airworthiness Directive becomes effective on 4 August 2005. | |
| Background: | This Directive is in response to an unacceptable rate of uncontained 1st stage turbine wheel failures. The fitment of the energy absorbing ring is designed to minimize the risk of uncontained 1st stage turbine wheel fragments from causing damage to the aircraft, which could lead to loss of control and loss of the aircraft. |
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James Coyne
Delegate of the Civil Aviation Safety Authority
24 June 2005