Pietenpol-List: Re: Pietenpol-List Digest: 20 Msgs - 08/08/02

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Pietenpol-List: Re: Pietenpol-List Digest: 20 Msgs - 08/08/02

Post by matronics »

Original Posted By: rhartwig11(at)juno.com
Subject: Pietenpol-List: Re: Pietenpol-List Digest: 20 Msgs - 08/08/02
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Re: Pietenpol-List: Fabric testing

Post by matronics »

Original Posted By: The Huizenga's
This is how I did it:Re latex paint:1) I used Sherman Willams products,varnish, reducer & color & aircraft silver paste2) Brush on two cross coats of varnish. Sand between coats & don't sparethetack rag.3) mix silver paste (the quantity is on the can ) with 1/2 pint reducer.Dump that into the varnish can, & spray one cross coat. Sand & tack rag.Isprayed the silver ony on the top of the wing. Also I did not silver thebottom of the fuselage.4) two cross coats of color & you are done.Caution-varnish will run, so apply it to a horizontal surface.Good luck, but remember I did this 14 years ago, so I hope I got itright.Suggest you do a test piece first.Mike B Piet N 687MB ( Mr Sam ) ----- Original Message -----
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Re: Pietenpol-List: Re: Pietenpol-List Digest: 20 Msgs - 08/08/02

Post by matronics »

Original Posted By:
I believe in the piet manual that Don Pietenpol sells along with the plans,the wedges are mentioned and they were manditory because of the strengthfactor.I found that Wicks is a little faster than AS&S when it comes to spruce. Iuse to get my capstrips within a few days and the cost was reasonable. Onesix foot piece should cover the wedge problem and you would know that it wasdone per the plans. Just a thought.Carl L.----- Original Message -----
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Pietenpol-List: Re: Pietenpol-List Digest: 20 Msgs - 08/08/02

Post by matronics »

Original Posted By: "Gene Rambo"
Subject: Pietenpol-List: Re: Pietenpol-List Digest: 20 Msgs - 08/08/02The reason to laminate the lower longerons is that then theey are a joy to work with, they are in the proper curvature, and the internal stresses are almost non-existant. Besides, if one of the laminations had a compressive fracture (hard to see) it really wouldn't matter, the other laminations are plenty strong enough to carry their loads. I didn't use any material longer than 12', mostly I have used 8'. I cut a 1 in 12 bevel and splice with no worries about strength. The joints are stronger than the rest of the wood. ________________________________________________________________________________
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RE: Pietenpol-List: Re: Pietenpol-List Digest: 20 Msgs - 08/08/02

Post by matronics »

Original Posted By: owner-pietenpol-list-server(at)matronics.com
In my opinion, if you have an upright on each side of the spar and you gluethe uprights to the spar so as to create a loadbearing joint with the liftforces transferred from the ribs to the spar in shear, then the wedges atthe top of the spar are not required. this is how all the other aircraftare done.Chris bobkaTech Counselor-----Original Message-----
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