Lightning-List Digest Archive

Sun 02/04/07


Total Messages Posted: 6



Today's Message Index:
----------------------
 
     1. 05:47 AM - glass or carbon  (Kayberg@aol.com)
     2. 05:58 AM - Re: glass or carbon (georgiemun)
     3. 07:20 AM - Re: Re: glass or carbon (nick otterback)
     4. 08:22 AM - Re: glass or carbon (georgiemun)
     5. 11:10 AM - construction questions (Tex Mantell)
     6. 01:52 PM - Re: Re: glass or carbon (Kayberg@AOL.COM)
 
 
 


Message 1


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    Time: 05:47:40 AM PST US
    From: Kayberg@aol.com
    Subject: glass or carbon
    I undestand that when you make absolute statements you can be found wrong sometimes, but the cut and paste below came from the Arion website, "Specifications" page. Construction Vacuum infused oven post cured fiberglass I was also basing my conclusions from my own hands-on building of our first Lightning. We did the preliminary assemble in Shelbyville next to a carbon-fiber build of an Esqual. Quite an obvious difference in color and texture of the cloth. There are a couple items on a Lightning that may be carbon fiber, but they are not major airframe components. But I am feeling a bit suckered. If the static load was taken to 5 gs and the design was higher yet, I would not personally care if it was constructed of banana peels and peanut butter. But it isn't. Vacuum infused, oven post cured fiberglass is the industry standard, not only for airplanes but a whole universe of stuff. When I visited the Pulsar factory, they were doing VACUUM INFUSED OVEN POST CURED FIBERGLASS! (in a bit of an archaic manner, which is why they are no longer significant players) Their shop forman had gained his experience doing VACUUM INFUSED OVEN POST CURED FIBERGLASS in the Phillipines working for LANCAIR. If the Arion folks want to throw some carbon cloth in the epoxy, that is fine with me. I wouldnt care if the edges flapped in the breeze before I ground them off. I would like to see some testing if they want to use banana peels. Doug Koenigsberg


    Message 2


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    Time: 05:58:54 AM PST US
    Subject: Re: glass or carbon
    From: "georgiemun" <georgiemun@yahoo.com>
    Hey, no problem; I'm just trying to learn as much as I can about the construction of the aircraft that I might be buying. I do have a question for Nick tho... One that I asked earlier, but was overlooked. Why does the carbon fiber stop at the root of the wing and does not continue through to the tip of the spar? Is there a reason for this? Also, it appears then that the spar is of a somewhat hollow construction with the foam creating the cavity? I guess this is done to save weight for the a solid wing spar is not necessary in this case? Thanks for any clarification that you guys can give. Kayberg(at)aol.com wrote: > I undestand that when you make absolute statements you can be found wrong sometimes Read this topic online here: http://forums.matronics.com/viewtopic.php?p=92780#92780


    Message 3


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    Time: 07:20:51 AM PST US
    From: nick otterback <vettin74@yahoo.com>
    Subject: Re: glass or carbon
    The wing spar is of fiberglass, carbon fiber, foam , and wood construction.....the root end which is in the fuselage is 1/16 per laminet wood core being 1" thick this stops at the wing root and is than a fibergalss foam woven core... this mean the the foam core has woven fiberglass in it for more strength....the wood is used as a high density light filler at the root end.....the spar caps ar 1"by1" rolled unidirectional glass which tapers down to 1"by 1/2" at the tip.....The material thru out the spar is heavier at the root end and lightens up at the tip as to be expected....... yes there is a carbon fiber laminte in the spar... this runs from just inside of the outboard spar bolt hole and out in to the wing some 48"...again something hard to tell from a picture unless you have seen it built or designed the wing!... There is absolutly no problem with the use of a carbon structure use in conjunction with a fiberglass one and i would be very leary of anything else that maybe discussed by the earlier mentioned forwarded post......We all know what assuming does for us and it is best to get information form the horses mouth....again my opinion but we all have them.. Nick georgiemun <georgiemun@yahoo.com> wrote: Hey, no problem; I'm just trying to learn as much as I can about the construction of the aircraft that I might be buying. I do have a question for Nick tho... One that I asked earlier, but was overlooked. Why does the carbon fiber stop at the root of the wing and does not continue through to the tip of the spar? Is there a reason for this? Also, it appears then that the spar is of a somewhat hollow construction with the foam creating the cavity? I guess this is done to save weight for the a solid wing spar is not necessary in this case? Thanks for any clarification that you guys can give. Kayberg(at)aol.com wrote: > I undestand that when you make absolute statements you can be found wrong sometimes Read this topic online here: http://forums.matronics.com/viewtopic.php?p=92780#92780 --------------------------------- Food fight? Enjoy some healthy debate in the Yahoo! Answers Food & Drink Q&A.


    Message 4


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    Time: 08:22:10 AM PST US
    Subject: Re: glass or carbon
    From: "georgiemun" <georgiemun@yahoo.com>
    Thanks Nick for that detiailed explaination. While I do not understand all of the technical ramafications, I appreciate you taking the time to help me understand how the aircraft is put together. pequeajim: I will shoot you an email soon and then as you suggested, we can both go down to Green Landings so I can see the aircraft in person and perhaps get a ride in it too. Georgie Read this topic online here: http://forums.matronics.com/viewtopic.php?p=92809#92809


    Message 5


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    Time: 11:10:04 AM PST US
    From: "Tex Mantell" <wb2ssj@earthlink.net>
    Subject: construction questions
    I have a few questions on the building of the Lighting. 1. Page 23-2 (rudder hinge installation) a picture shows the support on the elevator below the mating bracket which is on the vertical fin. Does the lower bracket also go below the its mating bracket? 2. The bearings for the brackets on the rudder are .650 in diameter. The holes are .625. What has anybody addressed this so far? 3. When doing the firewall, you need to put a slight radius bend into the edge all around. What tool have you used? Thanks for your reply. TEX


    Message 6


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    Time: 01:52:30 PM PST US
    From: Kayberg@AOL.COM
    Subject: Re: glass or carbon
    And I stand corrected. Thanks Nick doug In a message dated 2/4/2007 10:23:22 AM Eastern Standard Time, vettin74@yahoo.com writes: The wing spar is of fiberglass, carbon fiber, foam , and wood construction.....the root end which is in the fuselage is 1/16 per laminet wood core being 1" thick this stops at the wing root and is than a fibergalss foam woven core... this mean the the foam core has woven fiberglass in it for more strength....the wood is used as a high density light filler at the root end.....the spar caps ar 1"by1" rolled unidirectional glass which tapers down to 1"by 1/2" at the tip.....The material thru out the spar is heavier at the root end and lightens up at the tip as to be expected....... yes there is a carbon fiber laminte in the spar... this runs from just inside of the outboard spar bolt hole and out in to the wing some 48"...again something hard to tell from a picture unless you have seen it built or designed the wing!... There is absolutly no problem with the use of a carbon structure use in conjunction with a fiberglass one and i would be very leary of anything else that maybe discussed by the earlier mentioned forwarded post......We all know what assuming does for us and it is best to get information form the horses mouth....again my opinion but we all have them..




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