N891LLCessna U206G · 1986

On August 25, 2016, about 1005 central daylight time, a Cessna U206G airplane, N891LL, was substantially damaged during a forced landing near Cave-In-Rock, Illinois. The pilot received minor injuries and the camera operator received serious injuries. The airplane was registered to and operated by the State of Illinois under the provisions of 14 Code of Federal Regulations Part 91 as a public use flight. Day visual meteorological conditions prevailed for the local flight, which departed without a flight plan from Abraham Lincoln Capital Airport (SPI), Springfield, Illinois at 0845.

Prior to departure for the aerial mapping flight, the pilot stated the fuel tanks were dipped to confirm a desired fuel load of 550 lbs (89 gallons). During the first 45 minutes of the flight, the fuel selector was in the "both" tanks position. After noticing a fuel imbalance, the pilot moved the fuel selector to the "right" tank position, where it remained for about the next 30 minutes.

While wings level at 3,500 ft above ground level (agl), the pilot and photographer noticed an abrupt loss of engine power. The pilot switched the fuel selector back to the "both" tanks position and was unsuccessful in restarting the engine three times. During the restart attempts and engine out descent, the pilot elected not to feather the propeller due to his concern of the time required to unfeather the propeller. Step No. 2 of the 'Engine Restart During Flight' checklist in the airplane's Pilot Operating Handbook directs the propeller control be placed to feather. With the propeller not feathered, the pilot stated the airplane descended at a high vertical speed.

The pilot executed a forced landing, during which the airplane impacted a grassy area at a high descent rate. Both wings and the engine firewall were damaged when the airplane hit a berm. Prior to egressing the airplane, the pilot turned the battery switch off and moved the fuel selector to the "off" position.

Examination at the accident site revealed the airplane was resting left wing low, with fuel leaking out of the left-wing tank vent. During recovery operations, 20 gallons of fuel were drained from the right wing and 5 gallons from the left wing. After removal from the accident site, the airplane was placed in the operator's hangar, where the investigative team performed a records review and examined the airframe and engine systems.

In 1988, a Soloy Turbine PAC engine was installed in accordance with supplemental type certificate (STC) SA2353NM. This powerplant conversion included an Allison 250-C20S free turboshaft engine and a Soloy reduction gearbox.

Examination of the engine revealed no evidence of engine fire, uncontained failure or malfunction. Minor impact damage was present on the outer combustion chamber, but the engine was otherwise undamaged. Both oil and fuel filters were equipped with bypass indicators. Neither filter indicated bypass.

The N2 rotor rotated smoothly by manually turning the power output shaft. Rotational continuity from the power turbine to the propeller was confirmed and the power turbine was not damaged. The N1 rotor rotated normally after energizing the starter-generator. The N1 spun up normally. Borescope inspection of turbine blades revealed no evidence of thermal erosion, foreign object damage or abnormal combustion.

The fuel supply line was disconnected from the fuel spray nozzle, revealing a few drops of fuel in the line. The starter-generator was engaged to check for fuel flow to the fuel spray nozzle; no fuel flowed. The fuel line to the fuel-flow transducer was disconnected and the starter-generator was engaged, with no fuel flow.

The fuel line to the check valve assembly was disconnected and the starter-generator was engaged. After a brief purge of air, fuel flowed freely from the fuel supply line. The disconnected fuel lines were reconnected, the fuel spray nozzle was connected to the fuel supply line, and the starter-generator was engaged again. After air was purged from the fuel pump, fuel flowed freely to the fuel nozzle, which produced a normal spray pattern.

The purpose of the check valve assembly is to prevent a buildup of raw fuel in the combustion case if the burner drain valve remains in the open position when the engine is not operating, which could result in a hot start. The check valve also prevents fuel nozzle drip at shutdown, reducing the risk of a fire. Based on the design, an engine restart is not possible when air from the fuel system has reached the check valve, and there is no procedure to clear the air while in-flight.

A vacuum test was performed on the engine fuel system. The fuel line at the fuel selector switch was capped off, and 8 pounds per square in vacuum (PSIV) was applied to the drain port of the engine-mounted fuel pump. The system held the vacuum for two minutes.

The wing fuel vent systems were examined by applying compressed air through each wing fuel vent line, with no blockages observed. Both wing fuel vent valves operated normally, with no restrictions. Both wing float switches were electrically tested, with no anomalies. The respective wing fuel low level lights illuminated when each wing fuel float valve reached about 2 inches from the bottom of the respective fuel tank. A vacuum test was performed from the engine pump filter bowl to the fuel valve, with no defects noted.

Compressed air was applied to test for air leaks in the wing fuel feed tubes/lines, from the wing to each fuel reservoir. No anomalies were noted. The fuel selector valve was removed from the airplane and the bottom plate was removed to expose the plate with the ports. The valve was selected to each position (OFF, LEFT, RIGHT, BOTH), with no anomalies noted.

After completion of the examination, the engine was shipped to the Rolls-Royce engine testing facility, where an engine functional test run was conducted. The engine started normally. Since a propeller was not available to prevent an overspeed, the engine was only accelerated past ground idle enough to demonstrate normal acceleration capability. The fuel pump was dissembled and there was no evidence of cavitation or other malfunction.

The Shadin Fuel Flow Indicator was removed from the airplane and shipped to the National Transportation Safety Board Vehicle Recorder Division. The unit displayed engine fuel flow, fuel used, and fuel remaining. The unit did not interface with airplane's fuel quantity indicating system and required the crew to enter the initial fuel onboard. All calculations and data provided by the unit were based on fuel flow. Between power cycles, the indicator retained the last fuel used and fuel remaining. After power up, the unit indicated fuel remaining was 325 lbs. and fuel used was 225 lbs.