Accident Details
On January 27, 2023, at 0837 Pacific standard time, a Cessna T210N, registration N4758C, was substantially damaged in an accident near Murrieta, California. The pilot sustained minor injuries and the pilot-rated passenger sustained serious injuries. The airplane was operating as a Title 14 Code of Federal Regulations Part 91 personal flight.
Flight History
The flight originated at Long Beach Airport (LGB), Long Beach, California, destined for French Valley Airport (F70), Murrieta, California, with a planned duration of 26 minutes. The pilot reported that the preflight inspection was normal and that he visually checked the fuel tanks, which contained about 33 gallons of 100LL fuel per side. An engine runup was completed with normal rpm parameters during propeller and magneto drop checks.
Approximately 13 minutes into the flight, the pilot moved the fuel selector from the left tank to the right tank. Upon approaching the airport, the pilot retarded the throttle to near idle while descending, reducing airspeed. He performed a near midfield crossing from west to east and turned right to enter the downwind for landing on runway 36.
Loss of Engine Power
While on the downwind leg at about 1,000 ft agl, the pilot extended the landing gear, deployed flaps to 10°, trimmed for 90 knots, and turned to the base leg. According to ADS-B data, during the turn from base to final the airspeed was 80 knots at about 150 ft agl. The pilot reported that he attempted to add power but the engine did not respond. He cycled the throttle and turned on the auxiliary fuel pump, but the engine remained unresponsive. The airplane descended into a ravine, impacted the ground, and nosed over approximately 2,000 ft short of the runway threshold.
Damage Assessment
The aircraft came to rest with the nose and spinner oriented west and the tail section east. The right wing sustained impact damage to the leading edge, and the spar was fractured near the midpoint of the wing. The right-wing fuel tank was breached, and the vented fuel cap was missing. The left wing sustained leading edge damage, and the outboard third of the wing and aileron were folded underneath. The left fuel tank was also breached, but its vented fuel cap was present and unremarkable. The fuselage remained intact, while the empennage sustained substantial damage.
Postaccident Examination
During a postaccident engine test run using an auxiliary gravity-fed fuel tank attached to the upper fuselage, the engine would not rotate on the first start attempt. Relays were heard during preparation. Multiple impact-damaged circuit breakers near the battery were replaced to facilitate the run. An auxiliary power source was used to connect power to the starter relay, after which the starter operated normally. The engine started but ran with hesitation and ultimately lost power; further start attempts were unsuccessful.
Engine control cable continuity was established to the instrument panel. Examination of the fuel system revealed no anomalies from the left- and right-wing tank fuel lines to the fuel selector. Fuel system integrity was verified from the fuel selector through the manifold to each cylinder’s injectors, which were clear and free of impedance. All six cylinder combustion chambers and piston heads, examined with a lighted borescope, showed normal operational signatures. Intake and exhaust valves were consistent with normal operation. The induction and exhaust systems were clear and free of impedance.