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RV-6A - GBC
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Date: 1-3-2011
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Number of Hours: 1.50
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Manual Reference:
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Brief Description: Left flap, trim & hinge pin work
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After making additional adjustments on the sweep and incidence angles, I was confident to make some adjustments in the flap fit (trim) and extension of linkage testing.
Although the sweep is still not completely "set" (the rear spar attach is not drilled), the measurement shows the inboard end of the UPPER flap surface was too close to the fuselage skin to fully position the sweep. It's close but not quite there. So a slight (1/16th inch) trim was taken on the edge. With the hinge pins in place, flap linkage connected to flap control tube, and manually raising and lowering the flap, I measured the flap range of extension.
At the topmost position, the upper surface shows 11.0 degs of down angle ON THE SURFACE with the flap fully RETRACTED, therefore, ZERO flap extension at this point. With the flap fully extended (almost popping the leading edge from the trailing surface of the upper wing skin), the flap was extended to 56.0 degs on the surface, meaning 45 degs of flap extension. As the components are bolted, tightened, and adjusted for the last time, it will be within expected limits of travel.
NOTE: The flap link is VA-158 (RV-9 hex link) trimmed to length. This item is pre-drilled/tapped for 1/4-28 NF and considerably sturdier than RV-6 materials (AL Tube) that must be drilled/tapped by builder.
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Insufficient clearance
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Full extension
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Flap linkage
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