Beechcraft 90 King Air

The pilot stated that after parachutists egressed from the airplane, he returned to the airport and found that he did not have a green down-and-locked indication for the left main landing gear. He stated that he executed emergency procedures and did two fly-bys over the runway. Ground personnel stated that the landing gear appeared to be down-and-locked. During the landing roll, the airplane began to slide side-ways, and the right main landing gear began to collapse and eventually separated from the airplane. The left main gear also collapsed as the airplane slid to a stop. After the accident, the upper torque knee on the left main landing gear was found broken. The failure mode of the upper torque knee was not determined.

On March 28, 1997, about 0803 eastern standard time, a Beech E-90, N90DA, registered to a private individual, landed short of the runway at Huaypetue Airport, Choque, Peru, while on a foreign air taxi flight. Visual meteorological conditions prevailed at the time and a visual flight rules flight plan was filed. The aircraft received substantial damage and the airline transport-rated pilot and six passengers were not injured. The flight originated from Cuzco, Peru, the same day, about 0700. Civil Aviation Authorities stated that while on approach to land the pilot misjudged the distance from the runway and touched down short of the runway. Postcrash examination of the aircraft showed no evidence of precrash mechanical failure or malfunction.

While in cruising altitude on a flight from Saltillo to Monterrey, both engines failed simultaneously. The pilot was able to reduce his altitude and attempted an emergency landing in an open field located near Pesqueria. Both occupants escaped uninjured while the aircraft was damaged beyond repair.

The pilot had made a refueling stop at Vandalia, Illinois. She did not observe the refueling process, but the FBO also operated a King Air and she felt he knew the proper procedure to follow. The airplane was reportedly serviced with 235 gallons of Jet-A fuel (total capacity is 384 gallons). The pilot flew between 7,500 and 10,500 feet. When the airplane was 45 minutes from its destination, the fuel transfer pump lights illuminated, indicating the wing tanks were empty. The nacelle tank gauges registered 3/4 full and the pilot determined she had sufficient fuel to complete the flight. When the airplane was three minutes from its destination, both engines flamed out and the pilot made a wheels up forced landing. When the salvage company recovered the airplane, they reported finding no evidence of fuel aboard. The pilot was provided and used performance charts for the Beech 65-A90 instead of the Beech B90.

There were five recorded transmissions of conversations from one of the pilots aboard the accident airplane and the Fort Dodge, Iowa AFSS; one on 12/27 and four on 12/28. The weather forecast for icing included wording such as '...moderate to isolated severe icing from seven thousand downward for your entire route of flight....' The pilot stated that he received 'Full Flight Service briefings...' and also indicated that he spoke to flight watch prior to takeoff. While executing the ILS approach to the destination airport, the pilot was unable to maintain the proper glidepath even with the application of full power. The pilot maintained marginal control of the airplane during the descent until impact with trees and the terrain about 10 miles west of the destination airport. The pilot and passengers reported 'vibration' and 'shudder' of the airplane prior to the impact. One passenger reported that she saw ice forming on the left 'rear' wings. Persons on the ground reported severe icing conditions around the time of the accident.

The twin engine aircraft departed Heidelberg Airport for a local training flight with three pilots on board. Ten minutes after takeoff, the aircraft entered an uncontrolled descent and crashed in hilly terrain located in the Suikerbosrand Nature Reserve. All three occupants were killed.

The Beechcraft 1900C, N87GL, was in its landing roll on runway 13, and the Beechcraft A90, N1127D, was in its takeoff roll on runway 04. The collision occurred at the intersection of the two runways. The flight crew of the Beechcraft 1900C had made appropriate efforts to coordinate the approach and landing through radio communications and visual monitoring; however they mistook a Cherokee pilot's transmission (that he was holding for departure on runway 04) as a response from the Beechcraft A90 to their request for the Beechcraft A90's intentions, and therefore mistakenly believed that the Beechcraft A90 was not planning to take off until after the Beechcraft 1900C had cleared the runway. The failure of the Beechcraft A90 pilot to announce over the common traffic advisory frequency his intention to take off created a potential for collision between the two airplanes.

The pilot was taking off with 10 jumpers onboard. At the rotation speed of 100 knots, he used elevator trim to rotate the airplane, but it did not lift off the runway. He continued moving the trim wheel violently to pitch the nose up, and attempted to pull back on the yoke, but the airplane collided with rising terrain off the end of the runway. A witness did not see any of the flight controls move during the pilot preflight inspection, and during the takeoff roll, he did not observe a nose up rotation of the airplane. The pilot reported that he removed a single pin control lock from the yoke during preflight. The Beech control lock consisted of two pins, two chains, and a U-shaped engine control lock. The pilot walked away from the wreckage after the accident. No control locks were found in the wreckage. However, the control column shaft exhibited distress signatures on the periphery of the hole where the control lock is installed. No other evidence was found of any other form of mechanical jamming, interference, or discontinuity with the flight controls. Investigators were unable to identify any potential source of interference, other than a control lock, that could have simultaneously jammed both pitch and roll control. According to the airplane's manufacturer, about 3 to 6 degree of trim would have been normal for the airplane's takeoff conditions.

The twin engine aircraft was completing a local post maintenance flight with one pilot and two mechanics on board. Shortly after takeoff, while climbing to a height of 210 feet, the aircraft entered an uncontrolled descent and crashed. All three occupants were killed. According to the representatives of the owner of the airplane, recent maintenance had been performed on the engines, propellers, and the nose landing gear.

The pilot took off on runway 07 and was cleared direct to the Wiscasset NDB, east of the airport. Shortly after takeoff, the airplane began turning to the left. The pilot then asked the controller, '. . . can you tell if I'm in a turn? I have a problem here.' Soon thereafter, the airplane collided with terrain in an uncontrolled descent, about 1.6 miles north of the airport. Investigation revealed that three days before the accident, a refueler had fueled the airplane's left wing with 840 pounds of fuel, then the fuel farm ran out of fuel. No further fueling was accomplished, and the pilot was not advised of the uneven fuel load. Procedures in the Beech E90 Pilot's Operating Manual (POM) included a check of the fuel tanks during preflight. The Beech C90 POM specified a maximum fuel imbalance of 200 pounds, but the E90 POM did not specify a maximum fuel imbalance. During examination of the wreckage, no preimpact malfunction or failure was found.