Ferry

On a previous flight, low power was noted in the right engine, the right engine fuel flow was 5 to 8 gal/hr less than the left engine and the right engine temperature (itt) was about 500° less than the left. A decision was made to ferry the aircraft to a maint facility to have the right engine examined. The pilot took off on a 5,186 feet runway (unrway 02C) with a light tail wind in 95° temperature, though the airport had longer runways (7,702 feet, 8,000 feet and 8,500 feet). A witness noted the aircraft lifted off at the end of the runway (charts showed the takeoff roll with normal power should have been about 3,100 feet). Witnesses reported the aircraft remained low (nearly hitting a 55 feet light standard) until it rolled right and 'dropped like a rock.' Impact occurred in a right wing low attitude about 2 miles from the departure end of runway 02C. The aircraft was extensively damaged by impact and fire; no preimpact part failure was found. Both engines had evidence of engine rotation at the time of impact. The operator's lead mechanic had reported for duty about 3 hours before the accident flight, but he had not been informed of the engine problem before the aircraft took off. The pilot, sole on board, was killed.

About 5-10 min after takeoff the pilot leaned the mixture on a rough running engine. About 30 minutes later the left engine began to overspeed. The pilot was unable to feather the prop. The pilot returned toward the departure point with max power on the right engine. Unable to reach the airport, an emergency landing was made on a highway, directional control was lost, and the airplane collided with trees. Last annual was in 1978. Left propeller start lock pin blade L3 corroded, in extended position. Left propeller pitch control cable separated, frayed, corroded. General deterioration of piston rings and #6 conrod. Right prop governor control cables corroded, frayed. Right engine #5 intake pipe connection and hose missing. All compression rings pistons #1 and #5 severely worn, top two compression rings piston #2 seized. No record that the airplane had been inspected by an a&p mechanic or FAA approved airframe repair station. Pilot stated flight manual not available or used during ground or flight operations.

While approaching Iceland on a ferry flight from Frobisher Bay, the crew declared an emergency due to fuel shortage and requested the permission to divert to Keflavik Airport. On final approach to runway 29, both engines failed simultaneously. The aircraft stalled and crashed on a road located 1,500 meters short of runway. Both pilots were injured and the aircraft was destroyed.

The aircraft suffered an incident in Ecuador few days prior to this accident and damages were reported to the undercarriage. A ferry flight to Calgary was arranged so the aircraft could be repaired by technicians by De Havilland Canada. The flight from Quito to Calgary was completed with the undercarriage down. Upon touchdown on runway 28 at Calgary Airport, the nose gear collapsed. The airplane slid on its nose and came rest, bursting into flames. In a hurry, both pilots escaped the cabin and did not stop both engines. Hydraulic fluids ignited and the aircraft was totally destroyed by fire. Both pilots were uninjured. Dual registration FAE064 and HC-BFH.

The crew was completing a ferry flight from Malmyzh to Kirov following spraying operations and made an intermediate stop in Kaksinvai. He departed Kaksinvai at 1715LT on the second leg and attempted risky manoeuvre at very low height when the aircraft struck trees and crashed in a wooded area located 15 km east of Shurma, bursting into flames. Both pilots and the sole passenger (an aircraft mechanic who was in the second pilot's seat) were killed. At the time of the accident, the crew was intoxicated.

The captain of the airplane elected to take off on a three engine ferry flight without authorization. During the three engine climb out with the n°3 propeller feathered, the n°2 engine caught fire and he could not extinguish the fire. He attempted to return and during the descent the n°1 engine failed. He then intentionally ditched the airplane in the ocean, and received fatal injuries. The airplane was not recovered from the ocean and no determination of cause could be ascertained.

On completion of temporary repairs following a forced landing accident in a paddock, a permit to fly was issued authorising a ferry flight from the accident site to a nearby strip. During the take off roll the pilot was unable to maintain directional control and the aircraft crossed a drain before striking a fence and overturning. An inspection of the aircraft did not reveal any defect which could have contributed to the loss of directional control. Following the landing accident the property owner had rotary-hoed the paddock to a depth of 10 centimetres. Using a motor vehicle, the pilot compacted a 2.5 metre wide strip along the centreline of the paddock, which sloped approximately 3 degrees down to the north. At the time of the takeoff to the north the wind was from the north-east at 5 knots. The pilot selected a takeoff power setting of 53 percent of the maximum power available which effectively increased the take off ground roll required by approximately 170 metres.

While level after descending, the right engine quit. Pilot feathered the propeller, advised ATC, and was diverting to alternate when left engine quit. He positioned the left engine boost pump to high and low with negative results, but did not feather the propeller. Position of boost pumps, when engines quit, was not determined. Aircraft landed on overpass that was under construction. There was fuel leakage after accident due to aircraft damage. Fuel quantity was sufficient. Examination of aircraft revealed right engine flexible duct from turbocharger to plenum chamber separated due to loose clamp. Hose was installed and club prop installed for each engine run. Both engines operated normally. Induction air hose was pulled during right engine run. Engine ran rough due to excessive rich mixture. No determination could be made for the reason of the left engine power loss.

Flight was a 3-engine ferry with the #4 engine shut down. During takeoff roll at V1 the #2 engine overheat light came on. According to the copilot the pilot reduced throttle slightly and continued the takeoff. After lift-off the pilot aborted the takeoff. The airplane could not be stopped on the remaining runway and collided with antennas, approach lights and a construction site 1,180 feet from the departure end of the runway. Postcrash exam of the 3 operating engines did not reveal any evidence of mechanical failure or malfunction. A failed resistor was found in the #2 engine electronic engine control (eec). This would cause the unit to over-schedule fuel to the engine resulting in hotter engine operating temperatures. Retarding the throttle would reduce fuel flow to within normal ranges for engine operation. Under conditions that existed at the time of the accident, the airplane would have a 3-engine rate-of-climb of 1,398 fpm, and a 2-engome rate-of-climb of 350 fpm. The captain was killed while the copilot was seriously injured.

Immediately after takeoff at 200-300 feet agl, a portion of fabric separated from the right aileron. While maneuvering the aircraft the pilot's control wheel became free, and he elected to ditch using full rudder and differential power. Examination of the pilot's control wheel aileron control chain revealed that the chain failed due to overload. The right seat was occupied by a mechanic employed by the operator and held a private pilot certificate with single and multi engine rating. He stated that he suggested to the pilot that his controls were functioning normally, but the pilot disagreed and proceeded to ditch the aircraft. Examination of the right control yoke revealed aileron movement in the correct direction.