N485DA

On February 27, 2024, at 1822 eastern standard time, a Cirrus Design Corp SR20, N485DA, was substantially damaged when it was involved in an accident near Sanford, Florida. The pilot receiving instruction was seriously injured; the flight instructor and a pilot-rated passenger were not injured. The airplane was operated as a Title 14 Code of Federal Regulations Part 91 instructional flight.

The flight departed Sanford International Airport (SFB), Sanford, Florida, at 1718 for an instrument training lesson. On the return flight to SFB, the pilot under instruction was utilizing a view-limiting device to conduct a practice instrument approach to runway 9R. The pilot stated that the tower controller “switched them back and forth between 9R and 9L” before the flight instructor requested runway 9C. When the flight instructor advised the pilot to remove the view-limiting device, the pilot immediately observed that the airplane was low on the approach path. The flight instructor acknowledged that the airplane was low and told the pilot receiving instruction to set up for a practice short field landing. During the approach, the flight instructor noted that they were still low, so he took control of the airplane and added power. Shortly thereafter, the engine lost all power. The airplane subsequently impacted a parked, unoccupied airplane short of the runway, and came to rest on a grassy area next to the airport ramp. The airplane caught fire, and was subsequently extinguished by first responders. The airplane sustained substantial damage to both wings and the fuselage.

According to the flight instructor, prior to departing, an additional 34 gallons of fuel was added between the two fuel tanks that already had an unknown quantity of fuel in them. This brought the fuel tanks up to “tab plus 5 gallons” on each side. The flight instructor confirmed that the 34 gallons of fuel added to the airplane was divided between the two fuel tanks. A review of the fueling documents provided by the flight school showed that 34 gallons of 100LL was added to the airplane, but there was no documentation to show the total fuel quantity onboard the airplane prior to departure.

The engine and flight data from the Multi-Function Display and the Primary Flight Display (PFD) were examined.. An initial reduction of fuel flow at 18:17:55 was observed from the engine during the descent. Fuel flow briefly increased at 18:18:20 before decreasing gradually starting at 18:18:30 down to 2.5gph. A loss of engine power occurred at 18:18:50. For a detailed timeline of events, reference “Cockpit Display – Recorded Flight Data – Specialist’s Factual Report” in the public docket.

According to the airframe manufacturer, in SR20 series airplanes equipped with the Avidyne Entegra display system, there was no warning displayed on the MFD for fuel quantity. Fuel quantity was indicated only by a gauge forward of the fuel selector. There was an Amber “FUEL” caution light on the annunciator panel that would illuminate to indicate a low fuel condition. The “FUEL” caution light would illuminate when approximately 14 gallons of total useable fuel remained between both fuel tanks. This light would not illuminate if one tank was depleted to the unusable fuel level, while the other fuel tank had more than 14 gallons remaining. Furthermore, the remaining fuel caution was dependent on a pilot setting initial fuel quantity and was based on the fuel flow transducer.

Postaccident examination of the engine revealed the crankshaft was capable of rotating 720° when force was applied to the propeller. Compression and suction were established on all six cylinders. Continuity of the camshaft to the crankshaft was confirmed. The rocker covers were removed from the engine cylinders and valvetrain continuity was established. The oil filter element was examined with no contamination noted. The oil level gauge measured about 6 1/2 quarts of clean oil. There were no mechanical defects or discrepancies noted with the engine that would have precluded normal operation.

During the airframe examination, it was noted that the right wing fuel tank was not breached during the accident sequence. The fuel remaining in the right wing was drained and 1/4 of a gallon of clean, 100LL aviation fuel was collected from the tank. The left wing fuel tank had been breached during the accident sequence and the burn areas of the postimpact fire was primarily confined to the aft left side of the airframe. The fuel selector was found in the “right” position and was not manipulated by first responders. The first responders did manipulate the airframe boost pump toggle switch, and the fuel mixture knob to the “off” and “idle cut-off” positions, respectively.

The airplane flap position switch and flap actuator were found in the 0% or “UP” position. According to the Cirrus Pilot Operating Handbook, the normal approach speed, with flaps up, is 88 knots. The total useable fuel is 56 gallons, and the total fuel capacity is 60.5 gallons. Filling the airplane to the “tabs” equates to 20 gallons per tank.The airplane PFD recorded that the airplane’s indicated airspeed was 68 knots about 6 seconds before the impact.

Review of the operator’s checklist for the airplane revealed that during the landing approach, the fuel selector should be placed to the “fullest tank.”