Accident Overview
On February 15, 2017, at approximately 1834 Pacific standard time, a Beechcraft F33A, registration N222EN, sustained substantial damage during a forced landing near Pomona, California. The pilot received minor injuries, while the passenger was not injured. The flight was operating under Title 14 Code of Federal Regulations Part 91 as a personal cross-country trip.
Flight Details
The pilot reported that the flight originated from Selma Airport (0Q4) in Selma, California, with a planned destination of Cable Airport (CCB) in Upland, California. A visual flight rules (VFR) flight plan had been filed. During cruise, the engine lost power, prompting the pilot to execute an emergency landing at the Pomona Fairplex Fairgrounds. The pilot estimated that 40 to 45 gallons of fuel remained onboard at the time of the forced landing.
Sequence of Events
According to the pilot's written statement, about 10 miles from the destination, the Southern California (SoCal) approach controller terminated radar services. The flight had been uneventful up to that point and shortly beyond. Nearing the north boundary of Brackett Field Airport (POC) in La Verne, California, the engine "stumbled, shuddered, and stopped making power" without warning. The pilot attempted troubleshooting but was unsuccessful. He noted a drop in manifold pressure, though the engine did not completely quit. The pilot decided to divert to POC and set up for an emergency landing, radioing his intent, and the POC controller cleared him to land. Aware of a drag strip and parking lot near POC, the pilot realized he would not reach the runway as he approached the airport. He aimed for an off-airport landing at the fairgrounds, lowered the landing gear, but could not see the exact landing spot due to darkness. The airplane struck a fence and a seating area. The main landing gear was sheared off, and the right-wing leading edge sustained damage. After exiting, the pilot reported a fuel leak.
Engine Examination
An engine examination and test run were conducted. No mechanical anomalies were found that would have precluded normal operation and power production. The engine remained attached to the airframe, and the three-bladed propeller was secured to the hub and engine. The left side of the induction and exhaust systems showed impact damage, and the mixture control vapor return fitting had broken. Top spark plugs exhibited normal operating signatures, and cylinder borescope inspection revealed no anomalies. The fuel pump drive rotated freely with no binding, and the drive coupling was intact.
For the engine run, the left side induction system was replaced, the left side exhaust removed, and the broken mixture control fitting replaced. The fuel pump and spark plugs were reinstalled. The engine and airframe were secured, and an external fuel supply was connected at the left-wing root. After adjustments, the engine started normally and warmed up. The throttle was advanced to 2150 rpm, and a magneto check at 1200 rpm showed a 75 rpm drop for each magneto. Engine instruments remained within green arcs.