United States of America

N458J was landing during a rain shower. As the airplane started to flare for landing, the wind caused it to drift to the right. The pilot started to correct this drift, as the rain became heavier. During the touchdown, the pilot lost visual reference with the runway, yet he continued with the landing roll. The airplane drifted off the left side of the runway and ran into soft terrain. Both pilots escaped uninjured and the aircraft was damaged beyond repair.

A Beech 65 collided with trees in mountainous terrain after an inflight loss of control. A pilot observed the airplane start a turn to the right, roll right and continued until inverted and enter into a spin. The aircraft was in a steep nose down attitude when it began its pull out. The engines were heard by a ground witness who initially mistook them for an approach motorcycle. The pilot initially flew the aircraft 45 days before the accident and logged 3.5 dual instruction hours. There was no record in the pilot's logbook of any additional flight training since the initial flight. The pilot satisfactorily completed a before in a Cessna 150 four days before the accident. Examination of the wreckage disclosed the right engine had broken exhaust valve, but the left propeller was feathered. There were no preexisting mechanical malfunctions or failures found with the left engine. The aircraft was destroyed and all six occupants were killed.

After departing Santa Monica at night, Mitsubishi MU-2 pilot contacted tracon for clearance thru TCA at 6,500 feet. Tracon tried to get automated VFR handoff to ARTCC, but was unable. Radar service was terminated and pilot contacted (non-radar equipped) Santa Barbara FSS (home airport). He was advised weather was 500 feet scattered, 2,700 feet broken, 4,000 feet overcast, visibility 6 miles with fog. Pilot had not filed flight plan and began a VOR runway 25 approach without obtaining clearance. As he continued inbound, MU-2 descended thru clouds and converged with Fairchild SA227 that was on IFR approach to airport. ARTCC controller, who had been controlling SA227, advised FSS specialist of situation. Pilots of both aircraft were advised of other aircraft's position. MU-2 pilot did not respond when asked if he was in IMC. MU-2 plt reported 7 or 8 miles out on VOR approach. He was told again of SA227 on final approach and to phone ARTCC after landing. No further radio calls were received from MU-2 pilot. Radar data showed MU-2 converged with 400 feet of SA227. Pilot began left turn over shoreline as if to circle for spacing, but MU-2 entered descent and crashed in ocean. Examination of light bulbs indicated master caution and battery over temp lights were illuminated during impact. All four occupants were killed.

Pilot stated left engine lost power followed by the right engine. He initiated a left turn back to the airport but did not shutdown engines in accordance with emergency procedures. The acft yawed left and fell off on the left wing as if it had stalled. He regained partial control and aimed for a street. Acft hit roof of house while in right bank and then cartwheeled across the street. Left engine was found to have severe detonation damage and the turbocharger waste gate door was missing antivibration spring. The pin connecting the door and actuator was failed. Evidence indicated pin had failed prior to accident flight. Soot inside left wastegate indicated door had been fully closed for sometime. No evidence to indicate failure or malfunction of the right engine was found and right propeller showed damage indicative of rotation under power at ground impact.

The pilot reported that shortly after takeoff on a parachute jumping flight the left engine lost power, but a second later power was restored. Soon afterwards a total power loss occurred. According to the pilot, the propeller stopped rotating and did not windmill. He did not feather the left propeller. He made a shallow left turn toward an open field, while trying to return to the airport. He was unable to maintain adequate airspeed or altitude, and in order to maintain aircraft control, he reduced power on the right engine. He made a forced landing in a wheat field. The airplane came to a stop and all occupants escaped the airplane before it caught fire. The examination of the airplane did not disclose evidence of mechanical malfunction.

The pilot stated that while in level flight the left engine failed and he observed a fire warning light and shut the engine down, the right engine then began to run rough and lose power. He then restarted the left engine but neither developed enough power to sustain flight. He executed a forced landing on a highway and struck a vehicle and a fire erupted. Examination of the left engine revealed a cross threaded fuel nozzle fitting and soot patterns aft of it. No cause for the right engine failure was found. No evidence of an annual inspection was found.

The airplane crashed into a wooded area about 8 minutes after takeoff. Evidence at the wreckage site revealed that the airplane crashed through the trees at a glide angle of 8°. The glide angle for a power-off forced landing is 6° according to the pilot's operating handbook. The propeller did not exhibit rotational damage. Engine teardown revealed that the #1 cylinder had catastrophic detonation. All seven occupants were killed, among them two British, two German and two Swiss tourists, and the US pilot.

The pilots of Mitsubishi MU-2, N106MA, and a Cessna 310 with no registration number elected to fly in formation at night, though neither pilot had formal training in formation flying nor experience in night formation. They joined up in flight and the MU-2 pilot was flying on the wing of the Cessna 310. The MU-2 pilot communicated that he was going to change positions from the right side to the left side of the 310C. The Cessna 310 pilot and his passenger lost sight of the MU-2 when it dropped back to a position in the rear of the Cessna 310. Soon thereafter, the two aircraft collided and the MU-2 went out of control and crashed. The right horizontal stabilizer was torn from the Cessna 310 and the 310's empennage, right wing and props were damaged, but it was landed without injury to its occupants. An investigation revealed the tail light of the Cessna 310 was inoperative. Sole on board, the pilot was killed.

The pilot had just leveled at 4,000 feet when the right engine lost power. He immediately turned back toward his departure field but could not maintain altitude with the remaining engine. He then elected to make a gear up landing in an open field. On touchdown, the aircraft sustained substantial damage as it came to a stop in the grassy field. The pilot and passenger exited through the forward doors without further incident. Both occupants escaped uninjured.

N425EX was on the takeoff roll when the flightcrew experienced a 'thump' that resounded through the airplane. They also observed erratic engine indications from the n°3 engine. The captain aborted the takeoff and stopped the airplane on the runway. The fire warning system activated on the n°3 engine after the airplane came to rest. The crew attempted to extinguish the fire with the airplane's fire extinguishing system; however, they were unsuccessful. The post accident examination of the n°3 engine revealed the high pressure compressor disk had failed due to a fatigue crack that originated from a corrosion pit. The shrapnel from the disk penetrated the engine nacelle and severed the main fuel line for the engine. The fuel ignited and burned into the fuselage, igniting the 12,600 lbs of cargo (US Mail).