20010518014199A

(.19)On may 18, 2001, at an undetermined time between 1030 and 1115 hours pacific daylight time, a Beech D45, N8NV, owned by the united states navy and operated by the north island navy flying club, san diego, California, impacted rising terrain while maneuvering in a valley about 6 miles south of Julian, California. Visual meteorological conditions prevailed at the time of the personal flight, and a visual flight rules flight plan was filed. The flight was performed under 14 CFR part 91. The airplane was destroyed by impact forces and a post impact fire. The front seated private pilot and the rear seated pilot-rated passenger were fatally injured. The flight originated from nas north island, at 1011. The global positioning satellite coordinates for the estimated 3,400-foot mean sea level (MSL) elevation accident site are about 32 degrees 59.730 minutes north latitude by 116 degrees 39.553 minutes west longitude. The airplane was found in an upright attitude, on a 345-degree magnetic heading and on rocky, mountainous terrain, having an upslope angle estimated at 15 degrees. Higher elevation terrain was evident on the mountainside ahead and to the east and west of the main wreckage. Terrain to the south of the wreckage was lower in elevation. Evidence of all flight control surfaces was noted along with the main wreckage in the impact area. The fuselage and empennage were consumed by fire. The engine, with one attached propeller blade, was found next to a tree about 115 feet west-southwest of the main wreckage. The second propeller blade was found on rocks about 70 feet southeast of the main wreckage. Both pilots were found in the cockpit. No evidence of parachutes was found. The engine sustained impact damage and the case was cracked in several locations. No evidence of a preimpact oil leak was noted. The crankshaft was rotated and the continuity of the valve and gear train was confirmed. Compression was noted in all cylinders except number six, which was impact damaged. The engine sustained impact damage and the case was cracked in several locations. No evidence of a preimpact oil leak was noted. The crankshaft was rotated and the continuity of the valve and gear train was confirmed. Compression was noted in all cylinders except number six, which was impact damaged. Both propeller blades were observed deformed into an "s" shape. Also, the leading edge of both blades was observed gouged and the blade tips were broken off. (-23) the aircraft came to rest on a 15 degree incline in a shallow box canyon, substantial portions of the wreckage were consumed by post crash fire. Airframe major components including flight controls were intact at impact. The aircraft struck the terrain in a near wings level profile, slightly left wing low. There was no evidence of forward inertia, or rotational forces found at the accident site. Propeller blade inspection indicated that the engine was turning on impact. The engine and propeller departed the aircraft at impact, approximately 90 degrees to the nose slightly aft, depositing debris over an area, 215 feet beyond the crash site. Post crash inspection of the engine found crankshaft continuity, with corresponding accessory gear operation. Both occupants died from blunt trauma forces and burns sustained in the post crash fire.