Both engines had detached from the aircraft during the accident sequence. The extent of the rotational damage observed on both propellers indicated that both engines were producing significant power at the time of impact (Figure 6).
The right propeller assembly was attached to the engine and was intact apart from a small section of the tip of one blade which was located in the wreckage trail. The left propeller assembly had sustained a direct impact at the hub; the propeller subsequently breaking into several pieces and releasing the propeller blades. Only two of the three blades were located at the accident site; however, all of the other components of the propeller assembly were accounted for. The propeller hub fracture surfaces were inspected, with no pre-existing defects identified. Figure 6 shows the left engine with the relocated propeller components placed back in position.
