1. posterid:2321248
  2. Wing Load Testing -- Wing damage

Re: Wing Load Testing -- Wing damage

Kevin Boddicker
 

Mike,
Follow the repair plans in the plans manual. I think it states to
sand back each ply and expose at least one inch of each ply. So the
sanding needs to be a sort of scarf. Then
re-apply the glass cloth in it's original place per the lay-up
schedule. Then apply one bid over the whole repair. I think it is in
chapter three of the plans.
My opinion is that to test without the repairs would be a waste of
time. It would be interesting, but not much value to the question at
hand.

Kevin Boddicker
Tri Q 200 N7868B 115.3 hours
Luana, IA.

On Jan 20, 2009, at 3:53 PM, Mike Perry wrote:

I am still looking for ideas on repair of the wing prior to testing,
esp. the leading edge where it attached to the seatback bulkhead.

I would also like to hear any ideas for how to jig the wing prior to
testing since the wing is no longer attached to the fuselage.

Mike Perry

Mike Perry wrote:

I picked up the wing this weekend from Sam Kittle and brought it
home.
The wing was cut out of the fuselage with a sawzall and their is
damage
in two areas. (The fuselage is going to be used in a motor
glider.) I
am asking for opinions on repairs.

The front edge of the wing attaches to the rear of the seatback
bulkhead. In this area the wing was separated with a rather wavy cut
about 1 inch from the bulkhead. This cut exposes the foam core
but does
not enter the spar caps.

The rear edge of the wing has 2 cuts parallel to the fuselage
wall and
about 1 inch in. The longest of these is about 3.5 inches in length.

In all cases the damage appears to involve the 45 deg Uni but not
the
spar caps.

Two questions: Do we need to repair these areas before testing? What
repair would you do on the leading edge?

Thanks for any help --

Mike Perry
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