Cessna 310D N6861T

Summary

On 17 April 2003 at about 23:39 local time, a Cessna 310D registered N6861T, operated by Advantage Aviation, Inc., was involved in an accident near Provo, Utah, United States. 3 people were on board and 3 died. The aircraft was destroyed. The NTSB has published a probable cause for this accident; it is quoted in full below.

Date

17 April 2003 at 23:39

Classification

Accident

Location

Provo, Utah, United States

Nearest airport

Provo Municipal (PVU)

Coordinates

40.2417, -111.7178

Aircraft

Cessna 310D

Registration

N6861T

Category

Airplane

Engines

2

Operator

Advantage Aviation, Inc.

Operating rule

Part 91: General Aviation

Purpose of flight

Instructional

Phase of flight

Not recorded

Route

Provo → Provo

Aircraft damage

Destroyed

Weather

VMC

Light

Day

NTSB number

DEN03FA068

3 people died.

failure of the student to maintain aircraft control. Contributing factors were the instructor's inattention to the fuel supply, fuel exhaustion, an inadvertent stall/spin during the turn from base leg to final approach. and the instructor's inadequate supervision of the flight.

Quoted verbatim from the NTSB record. This site does not paraphrase or interpret it.

Read the full NTSB narrative

The airplane's main fuel tanks were full (100 gallons useable) when it departed on a 1.6 hour instructional flight. The auxiliary fuel tanks had been placarded inoperative. Visual inspection confirmed the tanks were half-full at the conclusion of the flight. The accident flight took off and was aloft for approximately 1.7 hours. It, too, was an instructional flight. According to a tape recording and transcript of radio communications, the instructor reported they would be entering a right downwind for runway one eight, flying a single engine pattern. Shortly thereafter, he called the pilot of an airplane that was in front on them and asked, "Can we get priority to the runway? We've got a difficulty." The consensus of 27 witnesses was that the airplane made a steep right turn from base leg to final approach, and then it descended vertically to the ground, exploded on impact, and burned. Measurements taken indicated the landing gear was retracted and the flaps were extended 5 degrees. It was noted that when the rudder was aligned with the vertical stabilizer, the rudder trim tab was fully deflected to the right. Measurement of the rudder actuator confirmed this observation (left rudder). The right aileron trim tab was deflected full up (aileron down, wing up). Measurement of the elevator trim tab actuator indicated the tab was 15 degrees down (elevator up). According to the Cessna Aircraft Company, this is about half of the total deflection range. Disassembly of the engines revealed no anomalies. Components and accessories were bench tested and found to operate satisfactorily within service limits. Disassembly of the propellers revealed neither propeller was feathered. The left propeller was at the low pitch stop, and the right propeller was just past this position (low power). According to the airplane's Climb Data and Cruise Performance Charts, each engine will consume between 14.9 and 26.6 gallons per hour (gph) at 7,500 feet msl and under standard atmospheric conditions, depending on power setting (manifold pressure and rpm). During climb between 5,000 and 7,500 feet msl, each engine will consume between 6.2 and 7.5 gph (depending on power setting). Airworthiness Directive 69-15-09, entitled "To Prevent Fuel Starvation During High Angle Descent," was issued to mandate compliance with Cessna Service Letter ME69-19, entitled "Minimum Fuel and Power Setting Placards." The service letter stated (in part), "Operation with less than five gallons of fuel in each main tank is prohibited. Useable fuel in each tank is 45 gallons. Maintain power within the green arc during descent."

Quoted verbatim from the NTSB record.