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Interim Recommendation issued to: Allied Signal Aerospace

Recommendation details
Output No: IR19990113
Date issued: 13 August 1999
Safety action status:
Background: Why this Interim Recommendation was developed

Output text

The Bureau of Air Safety Investigation recommends that the engine manufacturer AlliedSignal determine the sensitivity of turbine wheel seals to the initiation of fatigue cracks from slot corners, as a function of slot corner radii.

As a result of investigation into this occurrence, the Bureau simultaneously issues the following interim recommendations and safety advisory notice:


IR19990112

The Bureau of Air Safety Investigation recommends that the engine manufacturer AlliedSignal audit the process employed to manufacture TPE 331 turbine wheel knife-edged seals to determine those factors that may lead to excessive variations in slot corner radii.


IR19990114

The Bureau of Air Safety Investigation recommends that the engine manufacturer AlliedSignal consider, during engine design and the formulation of continuing airworthiness instructions, the possibility that turbine wheel seal fatigue failure may result in hazardous modes of engine failure.


IR19990115

The Bureau of Air Safety Investigation recommends that the Civil Aviation Safety Authority Australia conduct an audit of that part of the aviation safety system that establishes the operational history of life-limited components, to establish why the operational history of second-stage turbine wheel, p/n 868272-1, s/n P03214C, could not be determined with certainty.


SAN19990116

The Federal Aviation Administration should note the safety deficiency identified in this document and take appropriate action as considered necessary.

Initial response
Date issued: 21 October 1999
Response from: Allied Signal Aerospace
Action status: Closed - Accepted
Response text:

Please find attached AlliedSignal's planned actions and AlliedSignal's Materials Analysis (MA) of the 2nd stage turbine wheel from the subject incident.

Based on the MA and review of the engine hardware, AlliedSignal believes that an improper repair of the 2nd stage stator assembly resulted in blocked cooling passages which resulted in reduce cooling flows and higher operating temperatures in the inner support region. This resulted in the separation / uncoupling of the curvic seal from the 2nd stage wheel followed by the uncontained separation of the 2nd stage turbine wheel.

Upon completion of the planned actions associated with the interim recommendations, I will forward any results and/or process changes.

If you have any comments or questions, feel free to contact me via E-mail Thank you for the opportunity to respond to these recommendations.

IR19990113

AlliedSignal agrees to perform a sensitivity study of the slot corner radii of turbine wheel knife-edged seals with respect to fatigue initiation life. This analysis will be completed by March 2000.

As stated above in the response to IR19990112, AlliedSignal does not believe that the seal corner radius was the primary cause of the wheel separation of engine P-03214C.

 
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Last update 01 April 2011