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Baker's RV-6
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Date: 4-23-2014
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Number of Hours: 5.00
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Manual Reference:
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Brief Description: Conducted Fuel Flow Tests/Unusable Fuel Calc
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The aircraft's tail was placed on a stand so that the fuselage was level. With Randy Brooks' help, we did the fuel flow test. Two gallons of avgas was poured into each fuel tank. I ran the fuel pump switch and Randy collected the fuel in the can. We ran the electric fuel pump for one minute, once there was a steady stream of fuel coming thru the plastic tube that had been placed over the fuel line fitting. Randy held the fuel line fitting at the same level it went into the carburetor. The carburetor inlet fitting was attached to the fuel line during these tests.
The five gallon gas can had been weighed prior to adding the avgas, after four gallons of avgas had been added, and then after two gallons had been poured into the left fuel tank. This gave us the weight of the gas added to each tank.
After the fuel had been pumped out of the left tank for one minute, the can was weighed. Per the chart "Fuel Flow vs Horsepower," I calculated that the 180 HP engine should put out 130 lbs/hr of fuel. The fuel-flow requirement for a low-wing engine is 125% of the calculated fuel-flow value using an electric fuel-pump system, or 162.5 lb/hr. This equates to a fuel flow of 2.71 lb/min. The fuel collected in one minute amounted to 3.9 lb, or 234 lb/hr. This confirms that the pump meets the fuel-flow test requirement.
After the fuel flow test for the left tank was completed, the electric pump was run using the left tank until the fuel stopped flowing. The gas can was weighed to determine the amount of fuel remaining in the left tank-the unusable fuel. This amount was 0.7 gallons of unusable fuel in the left tank.
The test was repeated for the right fuel tank, to confirm the fuel flow thru the other lines as well. The fuel flow was 3.8 lb/min, or 228 lb/hr.
The calculation of unusable fuel for the right tank was 1.1 gallons.
My fuel and vent system was installed per the design of Van's aircraft. This is why the fuel flow test was performed in a level attitude.
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The aircraft ready for the fuel flow test
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