Accident Overview
The pilot of a multi-engine airplane reported that during preflight inspection, he visually checked the main fuel tanks and estimated the fuel level to be 2-3 inches from the top. He later indicated that there was enough fuel for the intended flight of less than 1 hour plus a 45-minute reserve. The pilot also stated that before the accident flight, he had never flown the accident make and model airplane and had not received any flight training in it.
Flight Sequence
The flight departed with passengers on board and climbed to between 4,500 and 6,500 feet mean sea level. During cruise, the pilot leaned the mixture. When 12 miles from the destination airport, he began descending. Pre-landing checks were performed 3 miles from the destination. The flight entered a left downwind, where the pilot lowered the landing gear and turned on the fuel pumps. Abeam the landing point, he reduced power, lowered flaps 10 degrees, and turned onto base leg. While on base leg at 600 feet and rolling out of the turn, the right engine suddenly stopped.
Pilot Response
The pilot banked left to maintain zero sideslip and advanced the mixture, propeller, and throttle controls full forward. He identified that the right engine had failed and pulled the right propeller control to the feather position. However, postaccident examination revealed the right propeller blades were not in the feather position, and there was no evidence of preimpact failure or malfunction of the propeller. The pilot reported that as he pulled the control, the airplane began to yaw and bank right. He then moved the left throttle to idle, and the airplane was on the ground within 6 seconds of the right engine failure.
Postaccident Findings
No fuel leakage was noted at the scene, and no fuel contamination was found in a nearby pond. Only residual fuel was present in the fuel lines of each engine compartment. A total of 4.0 gallons of fuel were drained from the left auxiliary fuel tank and 1.5 gallons from the right auxiliary fuel tank. No evidence of preimpact flight control failure or malfunction was found. Neither propeller was at or near the feather range at impact. Both engines were removed and tested on a stand with a club propeller; both operated normally.
Seat and Structure Examination
Examination of the right seat in the third row (occupied by a passenger who sustained minor injuries) revealed a bent seat frame on the left side and distorted seat feet, but no fractures. The left seat in the third row (occupied by another passenger) exhibited a compressed seatpan, unbuckled lapbelt, bent armrests, and displaced seat frame. The seat and its attach structure were certified for maximum forward and sideward g-loadings of 9 g and 1.5 g, respectively, not including a 1.33 margin of safety. The empennage separated just aft of the aft pressure bulkhead but remained secured by flight control cables. According to the airplane manufacturer, the tested load for the empennage in negative shear corresponds to 14.0 g, with an estimated capability of 18.2 g in negative shear loading.