On June 14, 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's failure to maintain sufficient airspeed during the turn to return for landing, which resulted an inadvertent stall/spin. Contributing to the accident was the failure of the ground winch tow cable shortly after takeoff. This summary draws on records from NTSB; 12 related events involving the same aircraft type or operator are linked below.
A Burkhart Grob G103C glider, N103MS, was destroyed in a collision with terrain near Gregory, Michigan, on June 14, 2009, after a winch cable broke during a local flight. The pilot was seriously injured, and the passenger was killed.
Accident Overview and Flight Details On June 14, 2009, at approximately 1120 eastern daylight time, a Burkhart Grob G103C Twin III Acro glider, registration N103MS, was destroyed during an in-flight collision with terrain near Gregory, Michigan. The aircraft was piloted by a commercial pilot and was conducting a local flight under 14 Code of Federal Regulations Part 91 without a filed flight plan. Visual meteorological conditions prevailed at the time of the accident. The pilot sustained serious injuries, while the passenger was fatally injured. The flight departed Richmond Field Airport (69G) shortly before the accident. The glider was owned and operated by the Sandhill Glider Club, and the pilot was a member of the club. The airport featured a single north-south turf runway, with published dimensions of 2,471 feet by 100 feet for Runway 18-36. Glider operations were noted as using the turf area west of the runway. The accident takeoff was performed to the south, using Runway 18, with a ground-based winch. The pilot reported that the takeoff and climb were normal until the glider reached approximately 400 feet above ground level, when the winch cable broke. The pilot lowered the nose and established a speed of at least 60 knots, continuing the upwind pattern until the glider was positioned to begin a right 180-degree turn to line up with the landing area, with more than 200 feet of altitude. The pilot noted that at 200 feet, a glider can safely execute a 180-degree turn back to the runway from which it had taken off. The pilot stated that he could feel in the controls that something was not right and that the glider was not responding in the manner he was accustomed to. He reported no signs of a stall and that the glider did not behave as it had during any stall practice. Before he could determine the cause or take any action, the nose abruptly dropped, and the glider dove toward the intended runway. The glider impacted the ground nose down and still in a right bank. A witness stated that the takeoff and transition to a climb appeared normal. However, about 300 to 400 feet above ground level, the cable broke. The witness noted that the pilot lowered the nose of the glider and turned toward the southeast corner of the field. Upon arriving over the southeast corner, the pilot began a 180-degree right turn to line up with the landing area, which was the normal landing area for the gliders. The witness stated that as the glider completed the 180-degree turn, the nose dropped and struck the ground in a near vertical attitude. The witness added that the glider completed about a 90-degree rotation to the right during the descent. ## Personnel Information The accident pilot, age 63, held a commercial pilot certificate with single-engine land airplane and glider ratings. He was issued a third-class airman medical certificate on July 21, 2008, with a restriction for corrective lenses. He successfully added the airplane rating to his pilot certificate on May 1, 2009, which met the requirement for a flight review. The pilot had accumulated 1,150 hours total flight time, with 832 hours in gliders in general and 90 hours specifically in Grob G103C gliders. Within the 30-day period preceding the accident, he had acquired about 1 hour in a Grob G103C glider and 9 hours in single-engine airplanes. The pilot was seated in the aft tandem seating position and had reportedly served as a former president of the glider club. The passenger was a certificated pilot and mechanic. He held a commercial pilot certificate with rotorcraft-helicopter and instrument helicopter ratings, and a flight instructor certificate with a rotorcraft-helicopter rating. He also held a mechanic certificate with airframe and powerplant ratings. He was issued a second-class airman medical certificate on August 11, 2008. He had reported a total flight time of 3,150 hours on the medical certificate application. The pilot-rated passenger had reportedly become a member of the glider club for the day in order to take a glider ride. The accident pilot stated that the passenger was interested in learning to fly gliders. The passenger was seated in the forward tandem seating position. ## Aircraft Information The accident aircraft was a 1990 model year Burkhart Grob G103C Twin III Acro glider, serial number 34156. It incorporated a two-place tandem seating configuration, with a mid-fuselage mono wing and T-tail empennage design. The glider was owned and operated by the Sandhill Soaring Club of Gregory, Michigan. Maintenance records provided by the operator indicated that an annual inspection was completed on March 28, 2009. The glider had accumulated about 1,742 hours total flight time at the time of the accident. Records on file with the FAA indicated that the glider had been involved in a prior landing accident. A Major Repair and Alteration form (FAA form 337), dated January 8, 2003, noted that repairs were made to the fuselage and right wing. ## Meteorological Information Livingston County Spencer J. Hardy Airport (OZW) was about 12 miles north of 69G. Weather conditions recorded by the OZW Automated Weather Observing System (AWOS) at 1116 were: winds calm, 10 miles visibility, scattered clouds at 6,500 feet above ground level, temperature 21 degrees Celsius, dew point 11 degrees Celsius, and altimeter 30.05 inches of mercury. ## Wreckage and Impact Information The glider impacted the open field used for glider operations. It came to rest upright on an east-northeast heading. The cockpit area was destroyed. The nose section of the fuselage, including the landing gear wheel assembly, was embedded into the ground. Both wings remained attached to the fuselage. However, the right wing was dislocated from the fuselage, exhibiting a tapered gap of approximately 4 inches at the trailing edge to no gap (0 inches) at the leading edge. The left and right ailerons and both speed brakes remained attached to the wings. Aileron control continuity was confirmed to the aft cockpit control stick. Movement of the control stick produced corresponding movement of both ailerons. The speed brake mechanism appeared to be restricted due to impact damage. However, limited movement of the speed brake handle produced corresponding movement of the speed brake control surfaces on the wings. The empennage separated from the aft fuselage. It came to rest immediately adjacent to the fuselage at the accident site. The elevator and rudder push-pull tubes were bent/separated at the point where the empennage separated. The elevator push-pull tube was continuous from the aft fuselage to the aft cockpit control stick. The rudder push-pull tube was continuous to the cockpit aft seat position rudder pedals. The linkage to the pedals was bent and deformed consistent with impact damage, but the linkage remained attached to the push-pull tube. The rudder and elevator remained attached to the vertical and horizontal stabilizers, respectively. The control linkage remained attached to the rudder and elevator control surfaces aft of the separation point. The vertical push-pull tube common to the elevator control system was separated at a point inside the vertical stabilizer. The separation appeared consistent with overload failure due to impact forces. No anomalies consistent with a pre-impact failure or malfunction were observed. ## Tests and Research Metallurgical examination of the winch cable revealed features consistent with overstress fracture. Specifically, the fracture surfaces exhibited “cup and cone” features, as well as necking of the wire. Both are characteristic of overstress fracture. Wear on the cable appeared to be in the form of rubbing and shear deformation. Flattening of the wire surfaces was also observed. Individual wires within the cable bundle were broken at several locations on both sections of the cable submitted for examination. ## Additional Information A log of the winch operations was maintained by the glider club. The log contained two entries with 2009 dates. The first was May 8, 2009, and referenced work on the winch truck alternator, battery, and engine choke. The second was dated May 11, 2009, and referenced “39 launches for Boy Scouts.” According to the log, the cable was last replaced on September 24, 2005.