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Going to anneal this piece of .063 thick 2024-T3 (after taking the plastic off, of course).
Why?
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Because I'm going to fabricate the doublers for the forward ribs from this material and
I want the doublers to nest nicely with the ribs, so the bend radius needs to be quite small.
However, in the -T3 condition, the bend radius needs to be 3x the thickness, or 3/16". Way
too big. In the -O condition, I can bend with 1x the thickness or 1/16".
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While that was annealing, I decided how to go about fitting the strip(s) which will bridge
the gap between the forward skin and the canopy skin. It's going to require removing a bit
of the top flange of these ribs to let the strip(s) pass across the width of the fuselage
as a continuous piece.
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...thusly.
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In order to fit those strips, I need to have the top flanges in place. These top flanges,
in turn need to be spaced down sufficiently to provide space to mount the strips. I temporarily
positioned the center left top flange, using two pieces of .025 material to space it down
from the underside of the canopy skin.
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With the magnets holidng it in place, I moved the canopy frame and skin out of the way and
traced the top edge of the sub panel. Now I just need to provide a 1/2 overlap of the flange
and the sub panel (i.e. 1/4 edge distance on each part).
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After sanding down the excess height of the flange, I center punched and drilled the flange
#40, then transferred these holes to the sub panel.
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Started the same process on the right, before knocking off for the evening.
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