What happened
The FAA’s narrative, in sentence case. The FAA writes it in capitals and removes private details.
The atlanta FSDO received the following notification: Glennville, GA: privacy data omitted, ultralight, crashed for unknown reasons in the front yard of a residence at privacy data omitted no ground injuries or property damage reported. POB: 1, injuries: fatal, damage: extent unknown. 06/24/2026 2157Z.
The atl FSDO dispatched an inspector to investigate the accident, and the inspector arrived on scene with tattnall county sherriff's office personnel. Aircraft was marked as N8019G, however, investigation found it had been deregistered on aug 4, 2025. No airworthiness certificate was found in the aircraft or in FAA databases. This aircraft did not meet the criteria of 14 CFR part 103.1 and therefore cannot be defined as an ultralight. The aircraft was a Quicksilver GT-400 and should have been registered as an experimental amateur built aircraft, this aircraft would also have required a valid airworthiness certificate to be operated in compliance with federal aviaiton regulations.
The aircraft was found in a nose down position with the tail boom standing vertically, appearing to have struck the ground at a high angle of impact. Broken tree branches were observed directly above the 30 foot diameter debris field, with no witness marks on the surrounding turf that would indicate otherwise.
FAA inspector observed the aircraft was destoyed, with the following notes. Cockpit was crushed in the vertical impact. The right wing was broken across a tree trunk about halfway between the root and wingtip, with control systems torn loose and the aileron cable showing evidence of overload breakage. Flap and aileron were still attached to the wing, though bent and broken. The left wing was mostly intact, though broken and bent. Flap and aileron were still attached to the wing. Vertical stabilizer and rudder were still attached to the tail boom in a normal configuration. Rudder control cable showed signs of overload breakage. Horizontal stabilizer and elevator were intact and attached to the tail boom in a normal configuration. Elevator control rod attachment bolt was broken/sheared with a clean, overstress break being observed. No sign of metal fatigue or corrosion was evident. Both main landing gear and tires were still attached to the aircraft and bent aftward. The tailwheel was still attached and undamaged.
Two five-gallon fuel tanks were found in the wreckage, and both apperared to be approximately one-third full. Engine was displaced in the accident and found on top of the left wing, laying on the engine’s left side. The engine had dual carburetors and the forward carburetor was disconnected from the engine intake, as the impact appeared to have exerted pulling forces on the throttle cable.
The three blade pusher-type propeller was still attached to the engine. One of the three blades had a 1/8” deep nick in the leading edge, two inches from the tip of the blade. One of the blades had damage to the leading edge from the tip to four inches inward. One blade showed no damage.
There were no witnesses to the event.
At the time of this report, toxicology and autopsy reports were still in work by FAA cami and the Georgia bureau of investigation. This report may be amended in the future upon receipt of relevant evidence.
As the FAA filed it
THE ATLANTA FSDO RECEIVED THE FOLLOWING NOTIFICATION: GLENNVILLE, GA: ^PRIVACY DATA OMITTED^, ULTRALIGHT, CRASHED FOR UNKNOWN REASONS IN THE FRONT YARD OF A RESIDENCE AT ^PRIVACY DATA OMITTED^ NO GROUND INJURIES OR PROPERTY DAMAGE REPORTED. POB: 1, INJURIES: FATAL, DAMAGE: EXTENT UNKNOWN. 06/24/2026 2157Z.
THE ATL FSDO DISPATCHED AN INSPECTOR TO INVESTIGATE THE ACCIDENT, AND THE INSPECTOR ARRIVED ON SCENE WITH TATTNALL COUNTY SHERRIFF'S OFFICE PERSONNEL. AIRCRAFT WAS MARKED AS N8019G, HOWEVER, INVESTIGATION FOUND IT HAD BEEN DEREGISTERED ON AUG 4, 2025. NO AIRWORTHINESS CERTIFICATE WAS FOUND IN THE AIRCRAFT OR IN FAA DATABASES. THIS AIRCRAFT DID NOT MEET THE CRITERIA OF 14 CFR PART 103.1 AND THEREFORE CANNOT BE DEFINED AS AN ULTRALIGHT. THE AIRCRAFT WAS A QUICKSILVER GT-400 AND SHOULD HAVE BEEN REGISTERED AS AN EXPERIMENTAL AMATEUR BUILT AIRCRAFT, THIS AIRCRAFT WOULD ALSO HAVE REQUIRED A VALID AIRWORTHINESS CERTIFICATE TO BE OPERATED IN COMPLIANCE WITH FEDERAL AVIAITON REGULATIONS.
THE AIRCRAFT WAS FOUND IN A NOSE DOWN POSITION WITH THE TAIL BOOM STANDING VERTICALLY, APPEARING TO HAVE STRUCK THE GROUND AT A HIGH ANGLE OF IMPACT. BROKEN TREE BRANCHES WERE OBSERVED DIRECTLY ABOVE THE 30 FOOT DIAMETER DEBRIS FIELD, WITH NO WITNESS MARKS ON THE SURROUNDING TURF THAT WOULD INDICATE OTHERWISE.
FAA INSPECTOR OBSERVED THE AIRCRAFT WAS DESTOYED, WITH THE FOLLOWING NOTES. COCKPIT WAS CRUSHED IN THE VERTICAL IMPACT. THE RIGHT WING WAS BROKEN ACROSS A TREE TRUNK ABOUT HALFWAY BETWEEN THE ROOT AND WINGTIP, WITH CONTROL SYSTEMS TORN LOOSE AND THE AILERON CABLE SHOWING EVIDENCE OF OVERLOAD BREAKAGE. FLAP AND AILERON WERE STILL ATTACHED TO THE WING, THOUGH BENT AND BROKEN. THE LEFT WING WAS MOSTLY INTACT, THOUGH BROKEN AND BENT. FLAP AND AILERON WERE STILL ATTACHED TO THE WING. VERTICAL STABILIZER AND RUDDER WERE STILL ATTACHED TO THE TAIL BOOM IN A NORMAL CONFIGURATION. RUDDER CONTROL CABLE SHOWED SIGNS OF OVERLOAD BREAKAGE. HORIZONTAL STABILIZER AND ELEVATOR WERE INTACT AND ATTACHED TO THE TAIL BOOM IN A NORMAL CONFIGURATION. ELEVATOR CONTROL ROD ATTACHMENT BOLT WAS BROKEN/SHEARED WITH A CLEAN, OVERSTRESS BREAK BEING OBSERVED. NO SIGN OF METAL FATIGUE OR CORROSION WAS EVIDENT. BOTH MAIN LANDING GEAR AND TIRES WERE STILL ATTACHED TO THE AIRCRAFT AND BENT AFTWARD. THE TAILWHEEL WAS STILL ATTACHED AND UNDAMAGED.
TWO FIVE-GALLON FUEL TANKS WERE FOUND IN THE WRECKAGE, AND BOTH APPERARED TO BE APPROXIMATELY ONE-THIRD FULL. ENGINE WAS DISPLACED IN THE ACCIDENT AND FOUND ON TOP OF THE LEFT WING, LAYING ON THE ENGINE’S LEFT SIDE. THE ENGINE HAD DUAL CARBURETORS AND THE FORWARD CARBURETOR WAS DISCONNECTED FROM THE ENGINE INTAKE, AS THE IMPACT APPEARED TO HAVE EXERTED PULLING FORCES ON THE THROTTLE CABLE.
THE THREE BLADE PUSHER-TYPE PROPELLER WAS STILL ATTACHED TO THE ENGINE. ONE OF THE THREE BLADES HAD A 1/8” DEEP NICK IN THE LEADING EDGE, TWO INCHES FROM THE TIP OF THE BLADE. ONE OF THE BLADES HAD DAMAGE TO THE LEADING EDGE FROM THE TIP TO FOUR INCHES INWARD. ONE BLADE SHOWED NO DAMAGE.
THERE WERE NO WITNESSES TO THE EVENT.
AT THE TIME OF THIS REPORT, TOXICOLOGY AND AUTOPSY REPORTS WERE STILL IN WORK BY FAA CAMI AND THE GEORGIA BUREAU OF INVESTIGATION. THIS REPORT MAY BE AMENDED IN THE FUTURE UPON RECEIPT OF RELEVANT EVIDENCE.