Witnesses reported that the single-engine airplane’s takeoff and climb appeared to be normal. As the airplane climbed through 400 feet, a puff of black smoke was observed emanating from the right side of the engine compartment. The airplane nosed up slightly, then nosed down turning about 360 degrees before descending rapidly from view.
Category: Mechanical Failure
While landing, the nose landing gear collapsed, and the airplane went off the left side of the runway. Four bolts secured the nose landing gear. Two of them were missing, and rust was evident in the slots where the bolts were originally secured. The pilot was able to recover one of the bolts. Examination of the bolt revealed that shearing was evident, consistent with a secondary failure.
The aircraft was landing on runway 36 when the right main landing gear separated. The aircraft departed the right side of the runway and came to rest. The pilot and passenger were not injured. Inspection revealed a fracture of the right spring landing gear leg about one inch outobard of the fuselage skin.
The pilot stated that after four parachutists had boarded the airplane, he began to taxi away from the gate. The pilot stated that the airplane traveled about 25 yards on the upward sloping grass terrain when the right main landing gear collapsed. Examination of the landing gear revealed a break approximately 10 inches from the inboard end of the landing gear leg at a point where it is clamped to the fuselage structure.
The pilot reported that as the airplane was descending through 4,000 feet msl it started loosing power. She leveled off, pulled carburetor heat on, and switched fuel tanks. She reported that, ‘Upon restart the engine backfired and quit.’ She reported that she trimmed the airplane for best glide (80 mph) and flew directly for the airport 2.5 miles away. At .5 miles from the airport she realized she would not make the runway so she decided to land short.
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.
Directional control of the aircraft was lost during the takeoff roll. The aircraft skidded sideways, veered off the runway into an agricultural field and both main landing gear assemblies collapsed.
The pilot departed on a local flight with three passengers. The engine start, taxi, and initial takeoff were normal. As the airplane flew over the end of the runway at 50 to 75 feet, the engine lost power.
The pilot was returning from a skydiving drop when he entered the airport traffic pattern, experienced an inflight loss of control, and then struck trees short of the runway.
The commercial pilot was about 50 feet agl on initial takeoff climb when the airplane started to vibrate and the engine started running rough. The pilot determined that he could not clear trees at the end of an open field and made a forced landing straight ahead maneuvering around some trees and cattle. The pilot stated he flared a little high, landed hard and the right main landing gear separated.
The passengers(parachutists) reported that after the airplane became airborne they heard ‘backfiring’, a ‘bang’ and ‘….Saw white smoke…’ the jumpmaster reported that the engine quit after the airplane turned downwind. The airplane continued to lose altitude on downwind and during the turn to the runway. It crossed the approach end of the runway at a 45-deg angle and dragged a wing on the runway, coming to rest next to the runway.
The pilot stated that on initial climb, at about 400 ft agl, the crew smelled something burning, followed by light smoke in the cabin. Both engines appeared normal visually. The odor and smoke increased, and the left fire warning light illuminated. The left engine was shut down & the prop feathered. The pilot increased power on the right engine; however, the airplane would not climb or maintain airspeed.
The airplane had landed following a sport parachute flight. During the landing roll the nose wheel separated from the strut. The nose strut dug into the sod runway & the airplane nosed over inverted. An faa inspector examined the airplane & noted that the nut & bolt which secured the nose wheel was absent. It was not located. He stated that there was no evidence that the bolt had broken. No maintenance to the nose wheel had been recorded recently, & the last annual inspection was logged 8 months & 72 flight hours before the accident.
The plt rprtd that the left main gear collapsed as he started to taxi from the ramp area on a smooth grass surface. When the gear collapsed, the left wing dropped to the ground & was substantially dmgd. The plt rprtd the left gear leg had broken off 2 inches ‘inside the bulkhead.’ an exam of the broken part revealed it had failed from fatigue.
Shortly after the acft took off with 4 skydivers on board, its eng seized at an alt of about 300 to 400 ft. The plt selected the best available area to land which was a field of tall corn on rolling terrain. During the emerg landing, the acft nosed over. Later, the eng was disassembled & aprx 1 qt of finely ground ferreous material was found deposited in the lower oil pan. The main bearings were found scored & discolored, & the main bearing shells showed evidence of overheating. The connecting rods were also discolored from heat. The screen chamber of the oil pump was found full of ferrous metal which shut off the oil supply to the oil pump gears. The faa maint inspector who examined the eng stated that the ferrous material found in the eng & bottom pan was not from the eng. The source of the material was not determined.
The acft lost part of one blade of the propeller during the climb to cruise phase of operation. The passengers were skydivers so they used their parachutes in an exit of the acft as the airframe started to vibrate. The plt made a successful landing on the arpt without power. All the jumpers landed safety. Visual examination of the propeller showed that the blade had separated 10 to 12 inches outboard from the blade root. The fracture exhibited evidence typical of high cycle fatigue and overload stress.