1 fatality

14 Jun 2009: BURKHART GROB G103C TWIN III ACRO (N103MS) — SANDHILL SOARING CLUB — Gregory, MI

Gregory, MI, United States

On 14 Jun 2009, a BURKHART GROB G103C TWIN III ACRO (registration N103MS) operated by SANDHILL SOARING CLUB was involved in an aviation accident near Gregory, MI. One person was killed. Investigators recorded the probable cause as: The pilot failed to maintain adequate airspeed while performing a turn to return to the landing area, leading to an unintended stall and spin. The failure of the ground winch tow cable shortly after takeoff also contributed to the accident. This summary draws on records from NTSB; 12 related events involving the same aircraft type or operator are linked below.

SourcesNTSBPrimary reportUpdated 1778583330Data APIEditorial standards

A Burkhart Grob G103C Twin III Acro glider crashed during a landing pattern following a broken tow cable, resulting in one fatality and one serious injury.

What happened

On June 14, 2009, a Burkhart Grob G103C Twin III Acro glider, registration N103MS, crashed near Gregory, Michigan, during a flight conducted under 14 CFR Part 91. The flight, operated by the Sandhill Soaring Club, departed from Richmond Field Airport (69G) using a ground-based winch for takeoff.

During the initial climb, approximately 400 feet above ground level, the winch cable snapped. The pilot responded by lowering the nose to maintain a speed of at least 60 knots and proceeded with an upwind pattern to prepare for a 180-degree right turn toward the landing area.

The pilot reported that while executing the turn, the aircraft's handling changed unexpectedly, though no signs of a stall were initially observed. Before any corrective action could be taken, the nose dropped abruptly, sending the aircraft into a dive toward the intended runway. The glider impacted the ground in a nose-down, right-bank attitude. The collision resulted in 1 fatal injury to the passenger and 1 serious injury to the pilot.

The investigation

Investigators examined the wreckage and found the cockpit area destroyed and the nose section embedded in the ground. While the wings remained attached to the fuselage, the right wing exhibited a gap at the trailing edge. The empennage separated from the aft fuselage, with the separation of the elevator and rudder push-pull tubes appearing consistent with overload forces from the impact.

Post-accident inspection of the flight controls confirmed continuity from the control surfaces to the aft cockpit stick, with no anomalies found that indicated a pre-impact mechanical malfunction of the glider's controls.

A metallurgical examination of the winch cable was performed. The analysis of the cable revealed features, including "cup and cone" fracture surfaces and necking of the wire, which are characteristic of an overstress fracture.

Probable cause

The pilot failed to maintain adequate airspeed while performing a turn to return to the landing area, leading to an unintended stall and spin. The failure of the ground winch tow cable shortly after takeoff also contributed to the accident.

Contributing factors

Causes

Airspeed — Not attained/maintainedPilot

Other contributing factors

Aerial tow equipment section — Failure