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The cause was not the overload of the wing, as such a design failure would have been detected during the extensive tests conducted by Lockheed or during the earlier operational flights. However, the coupling of the propeller/engine whirl mode with the wing flutter mode had not been taken into account before, and the investigation was then directed towards this issue. The whirl mode was introduced into the analytical flutter solution, and the mechanism of the failure was discovered. The whirl flutter occurrence was also demonstrated on the 1/8 scale aeroelastic wind tunnel model of the Electra, with the reduced stiffness of the engine attachment performed at the NASA Langley transonic wind tunnel.

The vertical motion was restrained and damped by the attachment rod and system of wires. 14. The measurement campaign included various combinations of the structural parameters. Note that the measurement regimes were limited by the windmilling propellers. The major tests were aimed at identifying the causes of the aircraft accidents; therefore various configurations with the reduced starboard outboard engine stiffnesses were performed. States with the reduced damping were also tested. The reduced stiffness parameters were also tested on the inboard power plant, and the combination of two engines was also tested.

C. 20594, Aircraft Accident / Incident, Summary Report: Loss of Control Business Express, Inc. Beechcraft 1900C N811BE Near Block Island, Rhode Island, December 28, 1991, adopted April 27, 1993. 3 Editorial Staff Report: Fatal Commuter Training Flight Cash Blamed On Spatial Disorientation, Poor Judgment, Flight Safety Foundation, Accident Prevention, Vol. 50, No. 10, October 1993. 4 Airline Pilots Association Report, Beechcraft 1900C N811BE, 1992. M. : ‘Aircraft Damage Detection From Acoustic Signals Found By A Cockpit Voice Recorder’, Acoustical Society of America 133rd Meeting, State College, PA, USA, 17 June 1997.

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Arado Ar-240

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