FULL FUEL FLOW TEST TO SPIDER NOTE: The fuel line to the mechanical pump was disconneted and the systems was flushed prior to the start of this test. To flush the system, a brake bleeding pump was attached to the disconnected fuel line. The fuel line to mechanical pump was reattached. Test starts now...
Plane @ 1.5° nose up. Fuel tank connected. Fuel servo is bypassed. (Photo 2) Line disconnected at spider and ball valve installed. Line added from ball valve to container. Pressure and flow was read on G3X panel using sensors installed on aircraft. The ball valve was used to control fuel flow. Pump was shut off when tone changed. (Photo 1) RIGHT TANK R Test 1 - this was our "learning" test. Learned various pump sounds, ball valve angles to control flow. 1745 g fuel added - 1363 g fuel exited = 383 g retained. Approximately 18 fl oz unusable. Stabilized at 26.8 psi with a flow of 12.9 gal/hr R Test 2 - (24 gal/hr @ 25.7 psi) (stabilized 12 gal/hr @ 26.9 psi) (photo 3) 527 g unusable R Test 3 - (52.8 gal/hr @ 11 psi...wide open) (stabilized 12.1 gal/hr @ 26.9 psi) 550 g unusable LEFT TANK L Test 1 - (stabilized 12.8 gal/hr @ 26.9 psi) 180 g unusable L Test 2 - (stabilized 12.7 gal/hr @ 26.9 psi) 194 g unusable L Test 3 - (stabilized 12.3 gal/hr @ 26.9 psi) 213 g unusable Note: The ball valve created bubbles in fuel exiting. A clear line was added ahead of ball valve to validate no air in system.
