Investigation Summary
The investigation determined that the engine failure was initiated by the fracture of multiple compressor turbine blades. This mechanical failure caused extensive internal damage to the turbine station mechanism. Analysis of the wreckage indicated that the gas generator was rotating at low speed and the propeller had been feathered prior to the first impact with the ground. Investigators found evidence of high heat concentration in the compressor section and combustion chamber, suggesting the crew made multiple unsuccessful attempts to restart the engine or keep the compressor operational after the initial blade failure. The aircraft ultimately impacted terrain that was not suitable for an emergency landing, leading to the destruction of the airframe.
Final Conclusions
The accident was caused by a sudden engine failure resulting from the fracture of more than one compressor turbine blade. The subsequent loss of power forced an emergency landing on unsuitable terrain. The investigation was conducted by the SVIA (Sección de Investigación de Accidentes) and concluded with the release of report SVIA-12-2008.
Video Analysis
No video analysis linked for this case file yet.
Airframe & Maintenance
Systems & Failure Modes
Pratt & Whitney Canada PT6A-114 Engine
The aircraft's single turboprop engine suffered a catastrophic internal failure when compressor turbine blades fractured, leading to a total loss of power.
Propeller Feathering System
The propeller was found in the feathered position, indicating the pilot followed emergency procedures to reduce drag during the forced landing attempt.
Interesting Facts
- 01The engine failure was caused by the fracture of multiple compressor turbine blades.
- 02The aircraft was a Cessna 208 Caravan I manufactured in 2000 (MSN 20800327).
- 03Three of the fourteen occupants survived the crash.
- 04The investigation lasted 4 years and 5 months before the final report was issued.
Safety Actions & Advisories
Engine Component Investigation
Source ↗The SVIA investigation focused on the fracture of compressor turbine blades, leading to detailed metallurgical analysis of the PT6A-114 engine components to understand the failure mode and prevent similar occurrences in the Caravan fleet.