Texas

Aircraft was destroyed when it struck power lines and the ground during a single engine go-around. Following a left engine shut down due to severe vibrations, the pilot overflew one airport to return to his home base. En route, he elected not to go to full power due to a 3 minutes limitation he did not want to exceed. The pilot overshot the runway while manually extending the nose gear and elected to attempt a right 270° turn to return to final while at 100-150 feet agl. Nose landing did not extend due to hydraulic pump being on left engine and no pressure. During the turn, the pilot lost control and the aircraft struck the wires. Investigation revealed that one of the blade pitch change links on the left prop had disconnected, allowing one blade to free float. The link pin assembly had backed out as a result of the safety screw backing out due to damaged and stripped threads and an improper length screw being installed. Props had 1/4' safety screws installed instead of 3/8'.

The pilot landed downwind on his private strip. The exact amount of the tailwind could not be determined. A thunderstorm was located just to the east of the runway and could have readily given N448 a strong tailwind. The aircraft touched down 390 feet beyond the threshold. Light braking action was evident from that point up to a point 400 feet from a hangar where all tire marks disappeared. The aircraft collided with the hangar, which was built at the end of and across the runway, approximately 10 feet above the runway surface and was destroyed by the subsequent post crash fire. The passenger was seriously injured and the pilot was killed.

Aircraft was destroyed during an attempted off airport emergency landing following a dual engine failure while leveling off at cruise flight. Pilot stated that left engine, then right engine surged and quit as he was leveling off at 9,000 feet msl. At the time of the engine failures the fuel totalizer was reading 60 gallons, but the aircraft fuel gauges were reading empty. Pilot broke out of overcast at 3,500 msl (about 1,200 feet agl) and was unable to find a suitable clear area to land before committing to an emergency landing in trees. Gear was down, flaps were up and neither engine was feathered at impact. Pilot stated that he knew he was out of gas when both engines quit and that he did not attempt an air start. Both occupants were seriously injured.

The pilot made a fairly long taxi from the ramp to the end of the runway and then started his takeoff roll with the parking brake still partially set. The brakes became very hot and the component parts expanded. After rolling almost 3,000 feet the brakes tightened up to the extent that both main gear tires started leaving black skid marks which continued until the aircraft ran off the end of the runway without obtaining flying speed, a distance of 3,168 feet. It was noted, through a design feature of the aircraft, that the parking brake handle could be placed in the released position without the brake being released. However, this would give the appearance that it had been released. The main gear tires were worn almost slick during this attempted takeoff. Both main gear brakes had been overheated during this time to the extent that they were destroyed. The aircraft was destroyed by collision with trees, rocks and a fire hydrant at the bottom of a hill off the end of the runway. The pilot escaped with serious injuries.

The pilot took off in fog and light rain and climbed into clouds at about 300-400 feet above the ground while both landing lights were extended and illuminated. Also the airport's rotating beacon (located about a mile from the accident site) was flashing on the clouds according to a ground witness. Just after entering the clouds the pilot was issued a left turn from his present heading of 350° to a heading of 270° and told to contact departure control. He did not make this contact and he continued the left turn (now descending) to a heading of 210° at which time the aircraft collided with trees and a large electrical transmission line and then the ground. The engines were operating at a high power setting at the time of impact. All broken flight control cables revealed evidence of overstress separation. No evidence of preimpact mechanical failure or malfunction was found. The pilot, sole on board, was killed.

The airplane was on a positioning flight so it would be in place for an early monday morning freight run. Pilot called for missed approach and after receiving clearance, declared he was in VFR conditions and thought he would land on runway 31. During a turn, the airplane impacted the terrain inverted and burned. Weather at airport 21 minutes prior to accident was: indefinite ceiling 100 feet, sky obscured, visibility 1/4 mile in fog. The pilot, sole on board, was killed.

Southern Air Transport’s LOGAIR 15 flight, a Lockheed L-382G, was cleared for takeoff from Kelly Air Force Base, Texas, on an instrument flight plan to Robins Air Force Base, Georgia, at about 0405 on October 4, 1986. Visual meteorological conditions prevailed. There were three flightcrew members aboard the military contracted domestic cargo flight operating under 14 CFR Part 121. All communications with the air traffic control tower were routine. Radar recorded that the airplane reached an altitude of about 700 feet above ground level. Witnesses reported an abnormally steep climb attitude. followed by a turn and/or bank to the left, after which the airplane continued to roll to the left and struck the ramp area at about a 90° angle to the departure runway in a near-inverted attitude between two hangars and exploded. A severe ground fire ensued. All three flightcrew members were killed.

Witnesses reported a normal takeoff and climb was made to an altitude of approximately 400 feet agl at which time engine power ceased/decreased. The right wing then dropped, the nose and left wing rose and the aircraft entered a near vertical descent to ground impact. Post accident examination of the engines and turbochargers failed to disclose any pre-impact failures. Examination of the prop governors disclosed an rpm setting below takeoff or climb power; however, exact rpm setting could not be determined. The pilot had recently purchased this aircraft and most of his multi-engine experience was in Beech Barons. The throttle quadrant location of the throttle and prop controls on the Baron are in the reverse position of those on the Cessna 421. The pilot also had not been check out in the Cessna 421. All four occupants were killed.

The pilot was being vectored around thunderstorms in the area just prior to the accident. During the last radio contact the pilot was issued a vector to the destination airport. During this turn, for unknown reasons, the pilot lost control of the aircraft and descended from the assigned altitude of 6,000 feet msl to the ground in approximately 40 seconds. The aircraft reportedly was in clear weather conditions at this time and had not encountered adverse weather during the entire flight. The pilot did not mention any problems during the radio transmission with ATC. Impact in a shallow lake occurred while in a near vertical nose down attitude at a high rate of speed. The right propeller was found to have been feathered at the time of impact while the left propeller was set in the cruise range. No evidence of any preimpact failure or malfunction of the right engine or propeller was discovered during post accident tests. Path and toxicological exams revealed no physiological factors. Pilots flight time records not available at time of investigation. Both occupants were killed.

About 6 minutes after takeoff, at 2138:31 cdt, the pilot reported level at 9,000 feet msl. At 2140:17, he transmitted that he had trouble and said he could not control or disconnect the autopilot (a/p) which was causing the aircraft to descend. At 2141:14, he stated he was descending at 6,000 feet/min. Another company pilot in another aircraft asked if he could find the breaker, meaning the a/p circuit breaker. At 2141:27, the pilot of N8CC replied, 'call you back.' Seconds later, radio and radar contact with N8CC were lost. A search was initiated, but the aircraft was not found until the following morning. An exam revealed the aircraft impacted in a steep, nose down, inverted attitude while at high speed; much of the wreckage was buried. No preimpact part failure/malfunction was found. With the a/p engaged, back pressure on the control column would have caused the a/p to trim nose down. Subsequently, the manufacturer issued a precautionary advisory to all MU-2 owner/operators regarding proper operation of the a/p and the various ways in which it can be disengaged. The pilot, sole on board, was killed.