Return-Path: Received: from ddi.digital.net ([198.69.104.2]) by truman.olsusa.com (Post.Office MTA v3.1.2 release (PO203-101c) ID# 0-44819U2500L250S0) with ESMTP id AAA25103 for ; Wed, 23 Sep 1998 06:29:55 -0400 Received: from john (max-tnt-78.digital.net [208.14.41.78]) by ddi.digital.net (8.9.1/8.9.1) with SMTP id GAA25271 for ; Wed, 23 Sep 1998 06:29:49 -0400 (EDT) Message-Id: <3.0.3.32.19980923061643.006c3330@mail.digital.net> Date: Wed, 23 Sep 1998 06:16:43 -0400 To: lancair.list@olsusa.com From: John Cooper Subject: Rollover support in the 320/360 In-Reply-To: <001401bde621$d3e8cac0$6a35ebc6@jimmy.solect.com> X-Mailing-List: lancair.list@olsusa.com Mime-Version: 1.0 <<<<<<<<<<<<<<<<--->>>>>>>>>>>>>>>> << Lancair Builders' Mail List >> <<<<<<<<<<<<<<<<--->>>>>>>>>>>>>>>> >> James-- >I looked at several aircraft, and most noticably Orin Riddel's (sp?, from >the >factory) has a very odd shape. The doc's recommend a uniform 3 inch >width, and yet most I have seen taper towards the longerons. Has anyone >seen, or >could recommend reasons for the irregular shape? > Those of us who are tall had to recline the seat-back several inches behind the rollover. This left the bottom of the structure hanging down in mid air, ready to gouge into our shoulders. In my case, I tapered the bottom of the rollover somewhat so it would clear my shoulder, and blended it into the side of the fuselage. >A second question: the manual indicates that the longeron's, once >installed, should have the innermost spruce laminate running the complete >length of the wood, i.e. no trimming. However, the manual says nothing >with respect to finishing the piece, should it me layered with a 2 bid >layup? bonded to the honeycomb? suggestions also welcome... > The longerons are STRUCTURAL! Do not trim them in whatsoever - they need all the cross-sectional area possible since they are what is supporting your engine hanging out there in front. I know enough about statics to be dangerous, and when I ran the numbers I got real scared. Based on my simplified calculations, I figgured the longerons should snap in tension directly above the main spars at about 10Gs, assuming that they had no holes in them. Therefore I did not install the NACA ducts in the side of the fuselage in this area, neither did I drill any holes for the canopy mounts in my longerons. I also beefed up my longerons with unidirectional carbon fiber in the critical area. Yeah, I know that mixing carbon and glass is not recommended, but I figure the worst that can happen is the carbon debonds from the regular glass and I will be no worse off than I was before... At least I won't be worring about the front half of my plane breaking off on a hard landing . But I digress...yes, you attach the longerons to the fuselage with 2 bid. --John, L-235