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John (Jack) Clark's Web Site
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Date: 2-11-2014
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Number of Hours: 2.00
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Manual Reference:
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Brief Description: Tested Fuel Flow in the Level Position
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Testing the Supply Capability of the Fuel System started today. With the aircraft level, fuel was added to the tanks and then the pump flow was measured for one minute. After the minute rate was known, continued pumping of the tank until dry allowed the calculation of the amount of fuel that was unusable in the tank. By subtracting the pumped volume from the known amount that was added to the tank in the beginning, the missing volume value was the amount of unusable fuel left in the tank. The process was repeated twice to verify result.
To calculate the needed number of ounces of fuel required per minute, the following formula was used for a 200 HP engine: 200 x 1.25 x 0.36 = 90 ounces per minute. My needed value is 90 oz./min. So far, this value has been easily met while testing the Fuel Flow in the Level Position from both tanks.
In the next step of the process of testing, the pumps need to be tested with the aircraft in about a 10 degree nose down attitude. After that test, the process will be again ran with the aircraft in approximately a 25 degree nose high attitude. All of this is to insure adequate fuel flow to the engine in these attitudes. As a Class, too many Experimental Amateur Built Aircraft's first flights experience fuel starvation accidents. Doing these tests will hopefully demonstrate the ability of the fuel system to supply adequate fuel flows to the engine in all of the normal attitudes of flight. As mentioned earlier, he pump produced 97 ounces per minute from each side. After determining the fuel flow, the pump was then ran again until not further fuel flowed. Subtracting the minute flow volume and the run to no flow volume from the known starting volume produced the unusable fuel volume value. This was approximately 14 ounces in each tank.
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