Quickie Q2 Lite Construction Manual - page 166

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The top canard skins are laminated similarly to the bottom skin 

lamination. The skin is the same two UNI at 45 degrees to the T.E., 

draping over the T.E. down to the bottom of the shear web, and the spar 

caps are G thru Q this time. At the leading edge of the main wing, 

overlap the bottom skin with the top skin a minimum of 111. Rather than 

let all the spar caps drape over the T.E. and down the shear web, trim 

every other one off at the T.E.. Peel Ply the shear web and all joints. 

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Don't touch the canard for at least 48 hours. Before removing the 

lumber, bondo a level board at about midspan on each canard. 

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You now deserve to celebrate for two days straight; you have just 

finished the final MAJOR layup in your aircraft. By the way, that top 

canard lamination that you just completed was the most difficult and 

critical lamination in the whole aircraft, and yet we have such 

confidence in you at this point, that we only devoted a very few words to 

it.