Accident Overview
On August 24, 2025, at about 1500 eastern daylight time, a Raytheon Aircraft Company A36, registration N855DC, was substantially damaged in an accident near Gulf Shores, Alabama. The pilot and passenger sustained serious injuries. The aircraft was operating as a Title 14 Code of Federal Regulations Part 91 personal flight.
Flight and Approach
The pilot departed Cox Field Airport (PRX) in Paris, Texas, en route to Gulf Shores International Airport / Jack Edwards Field (JKA) in Gulf Shores, Alabama. Before departure, he topped off the main fuel tanks. The 3.2-hour flight was uneventful, and the pilot switched fuel tanks every 30 minutes. During the approach to JKA, the pilot reduced throttle, descended to traffic pattern altitude, and configured the GPS for landing. He then switched the fuel selector to the fullest tank, the right tank, which was half full; the left tank was three-eighths full. After lowering the landing gear and flaps, the pilot noticed the airspeed dropped more than desired and increased the throttle. At that point, the engine did not produce power, and the propeller was windmilling. The aircraft was less than 1 mile from the runway threshold when it struck trees and impacted the ground in a vertical descent. The left wing was separated from the airframe during impact.
Post-Accident Examination
Examination of the aircraft revealed that it was equipped with D'Shannon Aviation 20-gallon tip tanks, which included a fuel transfer system; however, these tip tanks were not filled before the accident flight and contained no fuel. The fuel selector operated correctly in the Left, Right, and Off positions when tested with air at each port. The integrity of the fuel lines from the selector to the wing roots and firewall was verified using air. The fuel boost pump operated successfully when connected to the main battery. Fluid samples from the fuel selector and boost pump were consistent with 100LL aviation gasoline and tested negative for water using water-finding paste. The fuel tank filler cap O-rings were intact and undamaged. Neither main fuel tank contained fuel; however, the left tank was breached, and the right tank fuel line was compromised.
Engine and Systems Examination
The engine and propeller were separated from the airframe. The engine-driven fuel injection pump was removed, and its drive coupling was intact and undamaged. Each fuel system line was removed, drained of remaining fluid, and tested for water with water-finding paste, indicating no water. The flexible lines were tested for obstructions with compressed air, with no obstructions found. The fuel metering valve and throttle assembly functioned normally. The fuel manifold was disassembled and found free of contamination, functioning normally. The upper spark plugs were removed and appeared normal for operation and wear. All cylinders were inspected using the thumb method for compression and with a borescope, showing normal operation and wear. Magneto operation was observed from sparks at the lead terminal springs, and timing was verified at 21 to 22 degrees before top dead center for both left and right magnetos. All engine control cables were attached to their respective components, but continuity was breached consistent with impact damage. The exhaust mufflers were removed and inspected; each flame cone in each muffler was intact with no blockage, though the tail pipes were crushed due to impact damage. The air intake from the filter to the throttle assembly was intact and unobstructed.