Incident Cessna TU206-A VH-DGD, Thursday 18 February 1988
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Date:Thursday 18 February 1988
Type:Cessna TU206-A
Registration: VH-DGD
MSN: U206-0522
Fatalities:Fatalities: 0 / Occupants: 2
Other fatalities:0
Aircraft damage: Substantial
Location:30km SSE of Proserpine, QLD -   Australia
Phase: Landing
Departure airport:YBCS
Destination airport:YBMK
Investigating agency: BASI
Confidence Rating: Accident investigation report completed and information captured
Before departure, the pilot removed the fuel filler caps and checked that both tanks were full. He calculated the fuel endurance as 300 minutes. The flight proceeded normally with fuel selection being alternated between the left and right tanks. After a flight time of about 207 minutes, and with the left tank selected, the engine began to surge in a manner described by the pilot as typical of a tank running dry. The pilot immediately selected the right tank and turned the auxiliary fuel pump to "LO". The surging continued so he reselected the left tank and then the right tank, operating the auxiliary fuel pump on "HI" in short bursts. The engine did not restart. By this time, the aircraft had descended to about 2500 feet above ground level so the pilot ceased trouble-shooting and concentrated on landing the aircraft. The aircraft was landed in a cleared area but sustained damage when it nosed into a ditch late in the landing roll. Calculations indicated that 123 litres of fuel had been used from the left tank and 84 litres from the right tank. This was the first occasion since the pilot had been flying the aircraft that he had used more than 90 litres from the left tank. Inspection of the aircraft revealed that the right tank was about one third full. The left tank, however, was dry and five press studs attached to the upper surface of the fuel cell had become detached from the wing upper skin. This allowed the roof of the cell to sag, thus reducing the cell's capacity. The fuel gauge continued to indicate normally. There was, therefore, no way the pilot could have detected the fault other than to run the tank dry. The auxiliary fuel pump is operated by two switches situated side by side on the instrument panel. The right switch is labelled "LO" and is used for engine starting. It will only operate when the ignition switch is turned to start. The left switch, labelled "HI", is used for engine operation should the engine driven pump fail, and also when switching from an empty tank to one containing fuel. Tests determined that the auxiliary fuel pump in the aircraft was operating correctly on both settings. The pilot was under the impression that to leave the auxiliary pump on "HI" would flood the engine. For this reason, he selected "LO" and operated the "HI" switch in short bursts. These actions, along with changing back to the (empty) left tank, were insufficient to purge the air from the fuel lines in the short time the pilot was able to devote to trouble shooting the problem. A placard on the instrument panel lists the procedures to be followed in the event of a major fuel flow fluctuation/power surge. The first item on the list is "AUXILIARY FUEL PUMP ON" but there is no reference to the "HI" or "LO" switches. Had the placard read "AUXILIARY FUEL PUMP - HI", the uncertainty felt by the pilot concerning use of the "HI" setting may not have arisen.

Accident investigation:
Investigating agency: BASI
Report number: 
Status: Investigation completed
Download report: Final report


Revision history:

24-Nov-2018 04:52 Pineapple Added

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