# Accident 20120720014979A: Hawker Beechcraft Corp G58, Medford, OR, July 20, 2012 - Type: FAA accident report (Accident/Incident Data System), as reported - Date: July 20, 2012, 11:30 local time - Place: Medford, OR - Airport: Rogue Valley International-Med - Damage: Substantial damage - Phase of flight: Landing: Touchdown - Operating rules: General operating rules (Part 91) - Location: 42.3742° N, 122.8736° W: From the FAA - Nearby events: https://openairdocs.org/map.md?lat=42.3742&lon=-122.8736&mi=10 - Aircraft: N7122T, a cancelled registration (https://openairdocs.org/deregistered/N7122T-2014-12-30) (OpenAirDocs) - Registry model: Hawker Beechcraft G58 (registry code 4220005, https://openairdocs.org/model/hawker-beechcraft-g58) (OpenAirDocs) - Registry engine: Continental IO-550-C (registry code 17209, https://openairdocs.org/engine/continental-io-550-c) (OpenAirDocs) - Reported make and model: HAWKER BEECHCRAFT CORP G58 - Reported engine: CONT MOTOR IO-550-C - People aboard: 2 - Fatal injuries: 0 - Other injuries: 0 - Pilot certificates: Private pilot - Pilot flight hours: 860 total, 45 in this make and model - NTSB investigation: [NTSB WPR12LA324](https://openairdocs.org/ntsb/WPR12LA324) (OpenAirDocs) - FAA source: FAA Aviation Safety Information Portal (https://asip.faa.gov/) - Page: https://openairdocs.org/incident/20120720014979A ## Narrative As the FAA filed it, in capitals; the FAA replaces private details with ^PRIVACY DATA OMITTED^. ON JULY 20, 2012. APPROXIMATELY 1130 PACIFIC DAYLIGHT TIME, HAWKER BEECHCRAFT G58, N7122T, WAS SUBSTANTIALLY DAMAGED WHEN IT VEERED OFF THE RUNWAY 32 AT THE ROGUE VALLEY INTERNATIONAL AIRPORT, MEDFORD, OR. (MFR). THE AIRCRAFT STRUCK RUNWAY DISTANCE SIGNAGE AND THE LIP OF A DRAINAGE DITCH. THE AIRCRAFT BECAME AIRBORNE AND TRAVELED OVER A TAXIWAY BEFORE COMING TO REST. THE PILOT^PRIVACY DATA OMITTED^ AND HIS PASSENGER WERE UNINJURED. THE PRIVATE PILOTS HOLDS SINGLE-ENGINE LAND, MULTI-ENGINE LAND, AND INSTRUMENT –AIRPLANE RATINGS. THE PILOT'S MOST RECENT FAA MEDICAL WAS ISSUED IN MARCH 2011. THE PART 91 FLIGHT WAS CONDUCTED VMC CONDITIONS. NO FLIGHT PLAN WAS FILED. THE MFR 1153 AUTOMATED WEATHER OBSERVATION INCLUDED VARIABLE WINDS AT 4 KNOTS; VISIBILITY 10 MILES; CLEAR SKIES; TEMPERATURE OF 24 DEGREES C; AND AN ALTERMITER SETTING OF 30.15 INCHES OF MERCURY.PILOT TOTAL FLIGHT TIME WAS APPROXIMATELY 850 HOURS WITH 45 HOURS IN THE ACCIDENT AIRCRAFT. THE ACCIDENT AIRCRAFT WAS MANUFACTURED IN DECEMBER 2011 AND HAD APPROXIMATELY 50 HOURS TOTAL TIME.THE PILOT STATED THAT THE FLIGHT ITSELF AND THE APPROACH WERE NORMAL. HIS FINAL APPROACH WAS MADE AT 85 KNOTS, WITH FULL FLAPS. WHEN THE AIRCRAFT TOUCHED DOWN, IT IMMEDIATELY BECAME UNCONTROLLABLE , SWERVING LEFT AND RIGHT, AND FINALLY TO THE RIGHT AND OFF THE RUNWAY. ALL THREE LANDING GEAR WERE FRACTURE SEPARATED FROM THEIR UPPER STRUT ASSEMBLIES UPON IMPACT WITH THE DITCH. THE AIRCRAFT CAME TO REST UPRIGHT APPROXIMATELY 4000 FEET DOWN RUNWAY 32, AND 500 FEET TO THE RIGHT OF THE RUNWAY CENTERLINE. THE AIRCRAFT WAS RECOVERED BY A REPAIR STATION LOCATED ON THE AIRPORT.INSPECTION OF THE AIRCRAFT TOOK PLACE IN THE MAINTENANCE FACILITY OF A LOCAL REPAIR STATION ON JULY 23 AND 24, 2012. THE AIRCRAFT WAS ON JACKS AND DISPLAYED SUBSTANTIAL DAMAGE TO THE FUSELAGE, WINGS, FLAPS, PROPELLERS, HORIZONTAL STABILIZER, AND LANDING GEAR. THE LOWER FORWARD FUSELAGE WAS CRUSHED BY IMPACT WITH THE DITCH. THE FUSELAGE DISPLAYED TORSIONAL AND COMPRESSION DAMAGE AT THE WING SPAR ATTACHMENT AREAS AND "OIL CANNING" OF THE SKINS AFT OF THE CABIN. THE WINGS SHOWED EVIDENCE OF TORSIONAL DAMAGE IN THE AREAS BETWEEN THE ENGINE NACELLES AND THE FUSELAGE. THE FLAPS WERE DAMAGED BY IMPACT WITH THE GROUND AND THE DEPARTING LANDING GEAR. THE DAMAGE TO THE PROPELLERS INDICATED THAT THE ENGINE WERE PRODUCING POWER AT TIME OF IMPACT. THE LEFT HORIZONTAL STABILIZER HAS A DEEP DENT IN THE LEADING EDGE CONSISTENT WITH IMPACT DAMAGE.CLOSER EXAMINATION OF THE LEFT MAIN GEAR WHEEL, TIRE AND LOWER STRUT SHOWED UNUSUAL DAMAGE TO THE UPPER AND LOWER ANTI-TORQUE LINK ASSEMBLY. THERE WAS NO BOLT, BUSHING, OR ATTACHING HARDWARE AT THE PIVOT POINT. THE LOWER TORQUE LINK INNER CLEVIS WAS BENT INWARDS. NONE OF THE BOLT HOLES DISPLAYED ANY UNUSUAL DAMAGE, OR ELONGATION. THE UPPER TORQUE LINK WAS FRACTURE SEPARATED AT THE UPPER STRUT ATTACH POINT. IN CONTRAST, THE RIGHT MAIN LANDING GEAR WHEEL, TIRE AND LOWER STRUT UPPER TORQUE LINK WAS FRACTURE SEPARATED AT THE UPPER STRUT ATTACH POINT, JUST AS THE LEFT UPPER LINK OF THE LEFT MAIN GEAR WAS. HOWEVER, THE PIVOT BOLT AND ATTACHING HARDWARE WAS IN PLACE AND THE CLEVIS AREA OF THE UPPER AND LOWER TORQUE LINK WAS VIRTUALLY UNDAMAGED. ## The NTSB's investigation of this event (1) From the NTSB's public API. Aircraft are matched to registry aircraft by N-number and event date, checked against the reported serial number, make and model; the registry's history has gaps, so older matches can be wrong. Compare the reported make and model. - [NTSB WPR12LA324](https://openairdocs.org/ntsb/WPR12LA324), Jul 20, 2012: Hawker Beechcraft G58 (N7122T), Medford, OR, substantial damage. Probable cause: A loss of directional control on landing for reasons that could not be determined based on the available evidence. From the FAA Accident/Incident Data System. Reports are matched to registry aircraft by N-number and event date, checked against the reported make and model; the registry's history has gaps, so older matches can be wrong. Compare the reported make and model. For accidents, the NTSB's own investigation is the fuller record. --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.