CEN26FA109

On February 6, 2026, at 1532 mountain standard time, a Tarragon airplane, N35RR, was substantially damaged when it was involved in an accident near Shawmut, Arizona. The pilot was fatally injured and the passenger received serious injuries. The airplane was operated as a Title 14 Code of Federal Regulations (CFR) Part 91 personal flight. According to flight track data downloaded from the airplane’s on-board avionics suite, the airplane departed from the Stellar Airpark (P19), Chandler, Arizona, about 1439. The airplane then flew south-southwest about 26 nautical miles (nm) where it turned to a west heading. The airplane then flew about 26 nm west where the data indicated that a full stop landing was made at the Gila Bend Municipal Airport (E63), Gila Bend, Arizona, with an immediate taxi back to the departure runway. After the subsequent takeoff from E63, the airplane headed east about 14 nm before it turned northeast and flew for about 1 nm, where the recorded data ended. The accident site was located about 2.4 nm north-northwest of the final recorded position. Figure 1. Google Earth plot of the airplane’s flight path. The airplane was equipped with a Galaxy GRS Parachute Rescue System. The parachute was found deployed at the accident scene; however, the bonded-on panels covering the parachute harness straps along the fuselage sides had not separated from the airplane. Additionally, the rocket motor was found about 800 ft south of the main wreckage. Figure 2. The accident airplane during the on-scene examination Examination of the airplane’s primary flight control system did not reveal any preimpact anomalies. The airplane’s landing gear was in the retracted position and the flaps were up. The propeller hub remained attached to the engine propeller flange. One blade remained attached to the hub. The other two blades were broken just outboard of the metal hub with a portion of each blade root retained in the hub. The propeller blades were of wood core construction with composite covering. All 3 propeller blades exhibited minimal damage, and the 2 separated blades were found in the immediate area of the accident site. Figure 3. The airplane’s propeller during on-scene examination. Initial examination of the engine revealed that the propeller flange could only be rotated a few degrees. The No. 1 and No. 2 cylinders were removed which revealed that the end of the No. 2 connecting rod that attached to the crankshaft had failed.