Mine is exactly the same. In fact, I remember before doing the weight increase mod I put one of the brand new bushes on the brand new spar pins and was surprised by how much it wobbled about. But whe
Author: GRAHAM SINGLETON <grahamsingleton@btinternet.com>
Date: Mon, 17 Jan 2011 19:10:44
First, the (black bolt)pins are undersize, (pip pins are spot on and the bu shes =0Apretty good)=0AThe tightness is cause by miss alignment of the bush es, both linear and angular. =0APoor jigging in
Phew J I had visions of yet another rework Will First, the (black bolt)pins are undersize, (pip pins are spot on and the bushes pretty good) The tightness is cause by miss alignment of the bushes, bo
MY perception is that the bushings are quite soft which seems strange to me Will First, the (black bolt)pins are undersize, (pip pins are spot on and the bushes pretty good) The tightness is cause by
Author: GRAHAM SINGLETON <grahamsingleton@btinternet.com>
Date: Mon, 17 Jan 2011 22:21:46
They are, they're aluminium alloy but hard anodized. That's why it's better not =0Ato ream them=0AGraham=0A=0A=0A=0A=0A_______________________________ _=0AFrom: William Daniell <wdaniell@etb.net.co>=
In support of Bud and Pete=99s notes I can confirm that flexing of the fuselage is important. The LAA had considerable concerns that the tail dragger conversion would stiffen the structure in such a
BINGO !! This is one of those times when I truly value this forum...I've been following this thread w/ only mild interest...to this non-engineer's mind, the assumed function of the lift pins was prim
<<.. would stiffen the structure in such a way that it could lead to overloading of the forward lift pin >> Ian, How does that work, if the lift pins are designed to carry the lift loads in the first
This topic is a moving target, a lot like fiberglass... Most of the flex of the spars is in the thinner section reaching maximum nearing the spar socket area. The spar at the root does not move, and
Author: GRAHAM SINGLETON <grahamsingleton@btinternet.com>
Date: Mon, 24 Jan 2011 23:19:56
Not convinced Duncan. The spar resists bending and the leverage is enormous , =0Afrom the centre of lift of the wing 30% span? The load on the root rib s is shear =0Aand some bending of the pins. Don
This has sparked an extremely interesting and thought provoking debate. The only real solution is to model the aircraft using Finite Element Analysis to truly see how the airframe moves under differi
All this talk of taildraggers has got me interested now ..... The new owners of Europa use FEA. Also, I believe that they have scanned some or all of the aircraft. They would therefore be the best pe
Author: GRAHAM SINGLETON <grahamsingleton@btinternet.com>
Date: Tue, 25 Jan 2011 10:11:29
Anyone chat with them at the Dinner?=0AGraham=0A=0A=0A=0A=0A_______________ _________________=0AFrom: flyingphil2 <ptiller@lolacars.com>=0ATo: europa-l ist@matronics.com=0ASent: Tuesday, 25 January,
Here is a question with respect to this topic =93 albeit a bit of a sensitive one. But maybe it is the acid test. Is there any experience of this part of the aircraft failing apart? =93 I have heard
Author: Kevin Challis <kevinmarie@blueyonder.co.uk>
Date: Tue, 25 Jan 2011 18:07:17
Hi I have flown in mountain wave in a valley in the pyrenees. It was bad, my wi fe cried! I hope i never test the plane like that again. But the plane was a nd is fine. Kevin ensitive one. But maybe
Author: Paul McAllister <paul.the.aviator@gmail.com>
Date: Tue, 25 Jan 2011 13:46:26
cried! I hope i never test the plane like that again. But the plane was and is fine. I had ATC vector me into a big ass'd cloud one time. Instead of responding 'unable' I took the vector. Gee it was
Graham, I agree with all that you say, so unsure why you're not convinced. The lift load is spread on the wings, but comes to a point at the lift pins; the stress path being either via the spar and r