What happened
While performing a takeoff from runway 16 at Fukuoka-Itazuke Airport, the aircraft reached a speed of 158 knots before the captain initiated rotation. Shortly after liftoff, at an altitude of approximately 3 metres, the number one engine experienced a significant power loss. This failure was caused by the separation of a first-stage high-pressure compressor disk fan blade. Following the loss of power, the N1 speed decreased to 23.7%, and the flight engineer notified the crew of the engine malfunction five seconds later.
In response to the engine failure, the captain elected to abort the takeoff and returned the aircraft to the runway. Upon touchdown, the aircraft experienced a vertical acceleration of 2.1 g. Although the crew deployed thrust reversers and ground spoilers, the aircraft could not stop within the available runway length. The aircraft overran the runway, crossed a nearby road, and skidded for roughly 620 metres into an open field, where it subsequently caught fire. The accident resulted in three fatalities.
Findings
The investigation determined that the decision to reject the takeoff was made while the aircraft's speed was significantly higher than V1, meaning the aircraft had already transitioned into the takeoff phase. The primary contributing factor was the inadequate judgment of the captain regarding the decision to abort the takeoff under those specific circumstances.
Technical analysis revealed that the failed turbine blade had completed 30,913 hours of operation and 6,182 cycles. This exceeded the 6,000-cycle limit previously recommended by General Electric for the disposal of such components.