Pilot Debrief

BR LEGEND LLC TURBINE LEGEND near West Columbia, SC — 2015-05-23

Final reportERA15FA221
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Date
2015-05-23
Location
West Columbia, SC, USA
Airport
CAE
Aircraft
BR LEGEND LLC TURBINE LEGEND
Registration
N42BR
Category
Airplane
Highest injury
Fatal
Fatalities
1
Phase of flight
Initial climb

Probable cause

An engine flame-out due to fuel starvation as the result of an improperly-installed auxiliary fuel pump fitting, and the pilot's failure to promptly feather the propeller following the engine-flame out, which resulted in decreased glide capability and impact with terrain. Contributing to the accident was the pilot's operation of the airplane with no emergency electric propeller feathering system.

Contributing factors

Contributing to the accident was the pilot's operation of the airplane with no emergency electric propeller feathering system.

NTSB narrative

The commercial pilot departed on a cross-country flight in the experimental, amateur-built, turboprop airplane. About 3 minutes after takeoff, the pilot initiated a return to the departure airport. About 6.8 nautical miles (nm) from the runway, at an altitude of about 6,500 ft mean sea level, the pilot declared an emergency, stating that he had "lost" the engine. Shortly thereafter, he informed air traffic control that the airplane had experienced a loss of fuel pressure. Witnesses saw the airplane collide with a tree and subsequently impact a pond about 1.2 nm from the runway. They reported no engine sound. Examination of the airplane revealed no evidence of preimpact failures or malfunctions of the flight controls that would have precluded normal operation. The landing gear and flaps were found retracted. There was no evidence of preimpact failure or malfunction of the engine core. The engine-driven fuel pump showed signs of internal cavitation, while the auxiliary fuel pump, which provided fuel under pressure to the engine-driven fuel pump, flowed nearly 48% less than specified by the manufacturer, and had an inconsistent/intermittent laboring sound during testing. Disassembly revealed an improperly-installed fitting, which resulted in the decreased fuel flow rate, a loss of fuel pressure, and a subsequent engine flame-out. Inspection also revealed that a component of the fuel pump had been replaced after manufacture, but there was no record of this maintenance in the airplane's logbooks. While it was not known if the pilot attempted to perform an air restart of the engine, a worn ignitor box and ignitor plug may have precluded a successful restart of the engine. Although the pilot descended the airplane at its published best glide airspeed in his attempt to return to the airport, because the airplane was not equipped with an electrically-operated feathering pump, the propeller blade angle remained where it was set when the engine flame-out occurred, which was likely flat pitch. The flat pitch of the propeller blades significantly decreased the airplane's engine-out glide ratio. Had the pilot promptly feathered the propeller blades to reduce drag following engine flame-out, or had the airplane been equipped with a feathering pump, it is likely the airplane would have been able to reach the intended runway and land uneventfully. Although an enlarged heart was noted during the autopsy and toxicological testing detected quinine, given that the pilot was actively controlling the airplane just before the accident, there is no evidence that a medical condition or use of quinine contributed to the pilot's inability to fly the airplane.

Analysis

Primary failure mode
Engine power loss
First missed decision gate
Pilot could have aborted takeoff after engine failure declaration.

NTSB coding

Evidence available

  • ATC audio
  • Photos
  • 23 docket documents
View NTSB final reportView NTSB docket

Docket documents23

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