On July 7, 2025, a Cirrus SR2SST, registration N5656M, was involved in an accident near Sanford, North Carolina, resulting in 4 fatal injuries. The aircraft was being operated under Part 91 for personal flight.
What happened
At 11:03, the aircraft departed from Merrit Island Airport (COI) in Florida, bound for Raleigh Executive Jetport (TTA). Preliminary flight track data indicated the aircraft stopped transmitting ADS-B signals over the Atlantic Ocean, southeast of Palm Coast, Florida. Following the loss of signal, the pilot notified air traffic control of electrical issues but stated the flight would continue under visual flight rules (VFR).
A passenger contacted the fixed-base operator (FBO) at TTA via cell phone to report that the crew lacked functional navigation and communication equipment. The passenger requested information regarding active runway usage and wind conditions. Shortly after this communication, the passenger notified the FBO that the aircraft was experiencing engine problems and required a straight-in emergency landing. There were no further communications.
The aircraft was located in an open field approximately 5 miles from TTA. The main wreckage was oriented approximately 180 degrees opposite the direction of travel.
The investigation
Investigators found that the Cirrus Airframe Parachute System (CAPS) was not deployed; the cockpit deployment handle still had the ground securing pin installed.
Mechanical examination of the aircraft revealed the following:
- The engine and propeller hub assembly remained connected to the firewall, though the engine had separated from the fuselage.
- The engine crankshaft could only rotate about 5 degrees before being obstructed by the crushed oil sump housing.
- The engine mixture and throttle cables were separated near the firewall.
- The right wing fuel tank was breached and contained approximately 3 gallons of 100LL fuel, while the left wing tank was empty and unbreached.
- The fuel selector valve was found in the right tank position.
- The right magneto was non-functional due to a cracked and displaced housing.
- Flight control cable continuity was established from the cockpit to the primary flight control surfaces.
The recoverable data module (RDM) was recovered from the empennage and sent for data extraction.