Test

The crew was completing a post maintenance test flight at Elefsis AFB. On approach, the seaplane crashed in unknown circumstances, killing all three occupants.

The crew was completing a test flight from Toussus-le-Noble to Epinal. On approach to Epinal-Mirecourt Airport, visibility was below minimums. On final, as the crew was unable to locate the runway, he decided to initiate a go-around procedure and increased engine power. The aircraft rolled to the left, causing the left wing and the engine to struck the runway surface. Power was reduced and the aircraft bounced and eventually came to rest 400 metres further. Both occupants were injured and the aircraft was damaged beyond repair.

Airplane was departing on a required maintenance test flight following replacement of both engines. Witnesses stated that the takeoff roll and initial climb appeared normal, but that at about 500 feet agl, the airplane entered a right bank which continued until the wings were vertical and the nose fell through. Airplane impacted in an inverted steep nose down attitude. Examination of wreckage revealed that the right engine had been secured and feathered. Subsequent investigation did not reveal any evidence of pre-impact failure or malfunction of either engine or any of the airframe systems. Engine mounting/rigging continuity could not be established due to impact damage. The pilot was a principal in the operator's organization and not one of the regular line pilots. Evidence indicated that the gear was up and that the left spoiler was deployed at impact. Emerg procedure taught in transition training is to use rudder trim as soon as possible after engine failure to preclude deployment of spoilers. Rudder trim found in neutral position. All three occupants were killed.

The pilot reported that shortly after lifting off, the airplane began decelerating slowly. He thought the throttles had retarded; however, all of the engine instruments indicated takeoff power. Realizing that he could not return to the airport, the pilot selected a forced landing area and aimed the airplane between two trees. Investigation revealed that both props were at or near feather pitch angles at impact and being driven under power. Both engines had been changed immediately prior to the flight and both ground idle stops had been adjusted after the engine change with the left engine being slaved to the right. The system operated off of a squat switch on the right gear. Misriging of the right engine would be reflected in the left and allow oil pressure to be vented from the domes, which in turn would allow the propeller cylinder springs to drive the props toward feather as the right strut extended during takeoff. The pilot, sole on board, was seriously injured.

The Romanian Presidential Airplane was engaged in a series of tests prior to an official flight to China within two days. The crew consisting of pilots and engineers completed several circuits in the region of Bucharest-Otopeni Airport and was preparing to land when the aircraft rolled to the left on short final, causing both left engines n°1 and 2 to struck the runway surface. Fuel line ruptured and fuel ignited. The crew initiated an emergency braking procedure, vacated the runway by a taxiway and stopped the aircraft that was bursting into flames. All 13 occupants escaped uninjured while the aircraft was damaged beyond repair.

The pilot, sole on board, departed Mendoza-El Plumerillo on a post maintenance test flight. En route, the aircraft crashed in unknown circumstances on a hilly terrain located near Manantiales. The pilot was injured.

The airplane had not flown since June 1989. The flight had made 2 high speed taxi operations before takeoff. Immediately after takeoff the flight called to land. The airplane was observed on downwind 200-800 feet agl, 15-25° nose high. The airplane then stalled. The compressor surge valves for the left and right engines were found in the open position. Both occupants were killed.

Parked at Gomel Airport, the aircraft was subject to engine test runs. In unknown circumstances, it went out of control and collided with another parked AN-2 registered CCCP-40842. There were no injuries while both aircraft were damaged beyond repair.

The twin engine aircraft was carrying five mechanics and two pilots and was completing a post maintenance test flight. In unknown circumstances, it struck the slope of a mountain near Llanos del Yarí. All seven occupants were killed.

N3554p was on a maintenance test flight after the right wing was repaired. The pilot lost control of the airplane shortly after liftoff and was unable to regain control prior to the ground impact. The a&p mechanic who performed the repairs, re assembled the right wing aileron control cables per the Piper service manual. Post accident examination of the aileron control system revealed the right wing control cables were reversed on the aileron bellcrank, resulting in both ailerons moving the same direction (either up or down) when the control wheel was turned left or right. Both occupants were seriously injured.