Accident Sequence
The aircraft departed from runway 24R at Jandakot Airport, Western Australia, with one pilot and five passengers on board. The flight was conducted under instrument flight rules in the aerial work category. Shortly after becoming airborne, while still over the runway, the pilot recognized symptoms indicative of a right engine failure and chose to continue the takeoff. The pilot retracted the landing gear, selected flaps up, and feathered the right engine's propeller.
The pilot later expressed concern about clearing a residential area and obstructions, including high-voltage powerlines 2,400 meters beyond the runway. When the aircraft was approximately 450 meters past the upwind threshold of runway 24R, the pilot initiated a series of left turns. Radar data showed that during these turns, the airspeed fell significantly below the speed needed for optimal single-engine performance.
The pilot informed the aerodrome controller of an intention to return and land on runway 30. However, as the aircraft maneuvered, airspeed continued to decay, preventing a safe approach to that runway. The pilot could not maintain altitude, and the aircraft descended into scrub terrain with moderate tree cover.
Impact and Fire
At approximately 1537, during the impact sequence, the outboard section of the left wing struck a tree trunk and separated. A large quantity of fuel spilled from the wing tank and ignited, resulting in an intense post-impact fire that destroyed the aircraft. Four passengers and the pilot evacuated the aircraft but sustained serious burns. One of those passengers died from those injuries 85 days after the accident. A fifth passenger did not survive the post-impact fire.
Probable Cause
The official investigation identified the following significant factors: 1. The material specification for the pump bushing replacement in the right engine's engine-driven fuel pump (EDFP) was inappropriate. 2. High torsional loads between the EDFP's spindle shaft and sleeve bearing sheared the pump's drive shaft during a critical phase of flight. 3. The resulting reduction in fuel pressure could not sustain engine operation at takeoff power. 4. The loss of engine power occurred near decision speed with the landing gear extended over the runway. 5. The pilot elected to continue the takeoff. 6. Low-altitude maneuvering, including turns and banks, reduced airspeed below that required for maximum one-engine-inoperative performance. 7. The pilot was unable to maintain altitude over terrain unsuitable for an emergency landing.