Accident Overview
On September 4, 2009, at approximately 1045 Pacific daylight time, a Piper PA-28-180 airplane (registration N2482R) was destroyed during a forced landing following a loss of engine power during the initial climb from Oroville Municipal Airport (OVE) in Oroville, California. The aircraft was registered to and operated by the pilot under Title 14 Code of Federal Regulations Part 91. The private pilot and his passenger sustained minor injuries. Two first responders who arrived at the scene also sustained minor injuries. Visual meteorological conditions prevailed, and no flight plan was filed. The cross-country flight was originating at the time, with an intended destination of Chester, California.
Pilot's Account
The pilot reported that as the airplane reached 200 feet above ground level (agl), he felt a "slight bump" in the airframe, followed by two more bumps. He initiated a 180-degree turn toward the departure runway due to "irregular terrain and trees below." The pilot stated that the engine was running but not producing power. As the descent continued, the engine began "sputtering very badly" and "losing power very quickly." The airplane subsequently struck two fences and landed hard on the ground. During the landing roll, it impacted a large ditch and came to rest upright. The pilot and passenger exited the airplane and observed a post-accident fire originating from the front part of the airplane.
Post-Impact Fire and Examination
Examination of the recovered airframe revealed that the fuselage and right wing were consumed by fire. The left wing was mostly intact. The fuel selector valve was observed in the "LEFT" position. The throttle and mixture control levers were in the "FULL FORWARD" position, and the carburetor heat control lever was in the "COLD" position. Both the left and right fuel tanks were breached. The airframe fuel gascolator was consumed by fire; its screen was present but surrounded by molten material, and the bowl was full of debris.
Engine and Airframe Examination
Examination of the recovered engine showed that all engine mounts were intact. The left and right magnetos remained attached to the engine accessory mounting pads but exhibited severe thermal damage. The fuel pump remained secure at its mounting pad and showed thermal damage. The fuel system was intact from the firewall forward, and all fittings to the fuel pump and carburetor were secure at their respective attachment points. The carburetor remained secure at the mounting pad, but the float bowl had separated and was not located. The throttle and mixture controls remained secure to their respective levers.
The top spark plugs, magnetos, rocker arm covers, and vacuum pump were removed. The engine crankshaft was manually rotated by hand using the propeller. Mechanical continuity was established throughout the engine and valve train, and thumb compression and suction were obtained on all four cylinders.
No anomalies were noted with the recovered airframe or engine that would have precluded normal operation.