Background
On 17 January 2014, the pilot departed from Ogle International Airport (SYGO) flying a Cessna 208B (registration 8R-GHT) accompanied by a third crew/loader and an aircraft engineer. The task was a two-day shuttle operation between Olive Creek, Ekereku Bottom, and Imbaimadai airstrips.
Events of 17 January
During a landing at Ekereku Bottom, the aircraft encountered severe wind conditions resulting in a hard landing. The pilot logged the hard landing in the Aircraft Technical Log and expressed concern to several individuals. The engineer visually inspected the aircraft and declared it fit for flight. However, while taxiing for takeoff, the aircraft experienced a right brake seizure. The engineer freed and bled the brake line, after which tests were performed and the aircraft was flown to Olive Creek. The hard landing and brake failure were reported to base, and instructions were given for another pilot to return 8R-GHT to Ogle. The accident aircraft, another Cessna 208B (registration 8R-GHS), was left for the pilot to complete the shuttle schedule the next day. In the afternoon, the pilot flew 8R-GHS to Kamarang Airstrip and overnighted there.
Events of 18 January
On 18 January 2014, the pilot departed Kamarang at 10:30 UTC for Olive Creek with the engineer and loader. The engineer was left at Olive Creek. The pilot and loader completed one shuttle from Olive Creek to Imbaimadai, returned for refueling, then performed three additional shuttles between Olive Creek and Imbaimadai. After refueling again, they completed one shuttle (Olive Creek–Imbaimadai–Olive Creek) and had just taken off on the second shuttle of that series when the accident occurred during midmorning. Both the pilot and the third crew/loader were killed.
Accident Details
The crash occurred 2½ minutes after takeoff. There was no fire. The weather was satisfactory for visual flight rules (VFR) operations. The wreckage site was difficult to access, and the unavailability of suitable equipment contributed to a delay in body extraction.
Investigation Findings
The probable cause of the accident was a power loss suffered by the engine. The power loss was associated with the fracture of one of the 1st stage compressor stator vanes due to fatigue. The fatigue crack originated from a lack of brazing adhesion extending over approximately 0.280 inches along the chord length and 0.050 inches in the direction of the shroud thickness, located between the leading edge and mid-chord of the vane. The investigation also noted that the pilot had completed five shuttles on the day of the accident before the sixth, which was the accident flight. The hard landing and brake failure on the originating day had upset the pilot and caused him concern. A decision was made to replace the original aircraft with another that also had the Blackhawk modification.