1 fatality

27 Nov 2013: BIESEMEIER DAVID I SMYTH SIDEWINDER (N3786A) — Boulder, CO

Boulder, CO, United States

On 27 Nov 2013, a BIESEMEIER DAVID I SMYTH SIDEWINDER (registration N3786A) was involved in an aviation accident near Boulder, CO. One person was killed. Investigators recorded the probable cause as: The pilot performed an abrupt maneuver that exceeded the structural limits of the left wing, leading to its separation during flight. This summary draws on records from NTSB.

SourcesNTSBPrimary reportUpdated 1778583330Data APIEditorial standards

A single-engine experimental homebuilt airplane crashed near Boulder, Colorado, after the left wing separated from the fuselage during flight.

What happened

On November 27, 2013, a Biesemeier Smyth Sidewinder experimental amateur-built airplane, N3786A, crashed near Boulder, Colorado. The flight departed from Rocky Mountain Metropolitan Airport (BJC) at approximately 11:30 and was en route to Loveland, Colorado.

Radar data indicated that the aircraft maintained a normal departure and climbout for the first 15 minutes of the flight. This was followed by a sudden turn and a rapid descent. A witness reported hearing a loud sound and seeing the aircraft falling from the sky. While witnesses noted the presence of migrating bird flocks in the area at the time of the accident, no radio calls or distress signals were received from the pilot. The pilot, who was the sole occupant, sustained 1 fatal injury.

The investigation

The aircraft's fuselage was located in a creek bed, while the left wing was found approximately 1,156 feet from the main wreckage. Investigators examined the engine and flight controls, finding no mechanical anomalies. The wooden propeller blades showed fractures consistent with the engine being under power upon impact.

Examination of the left wing revealed that the lower left spar cap had fractured about 8 inches outboard of the wing-to-fuselage attachment point. The upper spar cap members exhibited significant S-type bending and fractures between 10 and 12 inches outboard of the attachment point. The fracture faces on both the upper and lower spar cap members had a dull, angled, and grainy appearance. The investigation found no evidence of pre-existing cracks or an in-flight bird strike.

Findings

Structural analysis of the wing components indicated a positive overload condition. Specifically, the lack of deformation in the lower spar cap was consistent with a tension overload failure, while the bending of the upper spar cap was consistent with a compression overload failure. These findings suggest the wing separated due to excessive forces applied to the structure.

Probable cause

The pilot performed an abrupt maneuver that exceeded the structural limits of the left wing, leading to its separation during flight.

Contributing factors

Spar (on wing) — FailureCapability exceededPerformance/control parameters — Not attained/maintainedPilot