Brief Description: Fuel Test 3 - Plane at 11.5 degree climb
FULL FUEL FLOW TEST TO SPIDER Plane @ 11.5° nose up. (Photo 1) Tail tie down ring is 2" from ground. (Photo 2) NOTE: Greater angle not needed due to fuel tank design. Fuel tank connected. Fuel servo is bypassed. 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. Target flow for this test is 24 gal/hr.
RIGHT TANK (stabilized 24.4 gal/hr @ 25.5 psi) 136 g unusable LEFT TANK (stabilized 26.0 gal/hr @ 25.4 psi) 116 g unusable
