Accident Details
On March 8, 2024, at 1325 Pacific standard time, a Cirrus SR22, registration N2824M, was substantially damaged in an accident near Whitethorn, California. The pilot and one passenger sustained minor injuries, while another passenger was uninjured. The flight was operated as a personal flight under Title 14 Code of Federal Regulations Part 91.
Pilot's Report
The pilot reported departing Shelter Cove Airport (0Q5), Shelter Cove, California, with a planned destination of Santa Rosa, California. While climbing through 2,600 ft mean sea level, the engine sputtered and lost total power. The pilot attempted to restore power by switching fuel tanks, activating the electric boost pump, and manipulating the mixture and throttle controls. Unable to restore engine power, he deployed the Cirrus Airframe Parachute System (CAPS). The airplane descended under parachute into densely tree-covered terrain and became suspended among tree limbs. Subsequently, the airplane fell from the trees and impacted the ground inverted, sustaining substantial damage to the fuselage and empennage.
The pilot stated he had not flown the airplane frequently in the months before the accident. He conducted a preflight inspection, including a visual fuel level check, and determined sufficient fuel was on board. He did not recall if a fuel sample was taken. Recovery personnel observed fuel leaking from the airplane; about 26 gallons of fuel was recovered from the left wing, and none from the right wing.
Data and Examination
The airplane was equipped with an Avidyne primary flight display (PFD) and multifunction flight display (MFD). Data downloaded from the units showed that at 13:17:42, the aircraft was climbing at a pressure altitude of 2,192 ft, indicated airspeed 126 knots, engine speed 2,620 rpm, manifold pressure 26.5 inHg, and fuel flow 25.2 gph. At 13:18:00, at 2,376 ft and 128 knots, engine speed and fuel flow began rapidly decreasing. The last MFD data sample at 13:18:43 recorded engine speed of 1,310 rpm and fuel flow of 0.4 gph.
Postaccident examination established flight control continuity from all primary surfaces to the cockpit controls. The firewall was damaged, but throttle, mixture, and propeller controls moved correspondingly when manipulated. Fuel system continuity was established from wing roots to the fuel injectors. The airframe fuel strainer assembly was removed and was void of fluid and debris.
Examination of the recovered engine showed it was separated from the engine mount and nose gear assembly. No external mechanical damage was observed on the engine crankcase. The oil sump had a 4-inch puncture near the oil drain. Rotational continuity was established throughout the engine and valvetrain, with thumb compression and suction obtained on all six cylinders. The fuel flow manifold was undamaged; its internal diaphragm and spring were intact and free of debris. A liquid substance in the fuel flow manifold tested positive for water using SAR-GEL water-finding paste.
Probable Cause
The official investigation source does not state a probable cause.