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02-17-2012, 06:37 AM
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Join Date: Feb 2008
Location: Pensacola, FL
Posts: 374
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Carbon and Al
Seeing a lot more Carbon parts. Isn't there a galvanic corrosion issue there?
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RV-? in planning stages.
RV-14 #140050 SOLD
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02-17-2012, 08:37 AM
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Join Date: Dec 2009
Location: Boulder, CO
Posts: 4,428
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Quote:
Originally Posted by LAMPSguy
Seeing a lot more Carbon parts. Isn't there a galvanic corrosion issue there?
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Sure there is. But any non-conductive barrier layer between them will prevent that. The fasteners could be an issue, so the same care is needed for them.
Another issue is that carbon parts have a coefficient of thermal expansion quite close to zero. This is about as big a mismatch with aluminum as Plexiglas is, but in the other direction. This can lead to distortion or cracking.
Dave
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02-17-2012, 08:52 AM
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Join Date: Feb 2008
Location: Pensacola, FL
Posts: 374
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fasteners
So, for fasteners do you just ensure they are primed?
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RV-? in planning stages.
RV-14 #140050 SOLD
Permanently willing to contribute fuel for RV rides
Helicopter ATP/CFI(I)
ASEL/AMEL Commercial/Inst/CFI(I)
Aerobatic Instruction available
Atlanta based.
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02-17-2012, 09:37 AM
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Join Date: Jun 2005
Location: Federal Way, Wa
Posts: 264
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Other things to think about
If the structure never gets wet, corrosion won't occur.
If you are planning of bolted joints for carbon fiber composites, there are other considerations.
Edge margin is wider (from the fastener center). Don't quote me on this but I think 4D is typical.
Composites are very weak in bolt bearing so the laminate must be thicker than what is needed for the rest of the structure.
The fiber orientation plays a large role in stresses around the hole. For metals, the stress concentration of a hole is 3 times the field stress. In composites, with the wrong layup, the stresses concentration can be as high as 6 times the field stresses. A symmetric, quasi-isotropic layup [0/45/90/-45]S is typical to keep stress concentrations down around 3.
Hole tolerance is much more critical than with metals because the material will not yield around the fastener. But the material is more difficult to drill properly, making the right drill selection and process critical.
If riveting, the swelling of the shank will load the hole in compression (good in metal, bad in composite) and can initiate a delamination.
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Brice
RV-9A 90897 FLYING
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02-17-2012, 09:48 AM
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Join Date: Oct 2005
Location: 08A
Posts: 9,477
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Brice, please post more often.
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Dan Horton
RV-8 SS
Barrett IO-390
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02-17-2012, 10:53 AM
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Join Date: Jan 2006
Location: Winston-Salem, N.C.
Posts: 1,210
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Carbon vs. Aluminum
I am in the heavy aircraft overhaul bussiness with a backround in corrosion prevention and dissimilar materials compatability..These two items are very galvanic if allowed to touch "uncoated". Virtually all principal structural elements of aircraft where this is accepeted, such as wing panels,cowlings ect. require the aluminum to be well prepared with primer and topcoat, and the carbon panel is primed as well. the fastener issue is critical, as aluminum rivets will eventually disintegrate, so the standard practice is most often a titanium rivet,bolt,screw or hilok, with a special coating applied (usually aluminum to protect the aluminum structure from the titanium...so as you can see, it is an issue to consider, however in our world of RV's, I believe we are not going to see these conditions, as long as the carbon part is painted, the aircraft aluminum is at least primed, and I would recomend using stainless hardware. I think the carbon fairings will retain shape better than some of the glass stuff,and I would not be afraid to use them...may even be cool clearcoated. Just take a look ata Carbon Cub cowling some time.
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Bill E.
RV-4/N76WE
8A7 / Advance NC
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02-17-2012, 11:18 AM
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Senior Curmudgeon
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Join Date: Sep 2005
Location: Dayton Airpark, NV A34
Posts: 15,408
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Whatever you do with attachment, and protection of same, I would think that inspection in these areas for corrosion should be a mandatory part of your "annual".
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Mike Starkey
VAF 909
Rv-10, N210LM.
Flying as of 12/4/2010
Phase 1 done, 2/4/2011 
Sold after 240+ wonderful hours of flight.
"Flying the airplane is more important than radioing your plight to a person on the ground incapable of understanding or doing anything about it."
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02-17-2012, 05:25 PM
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Join Date: May 2009
Location: Wahpeton, ND
Posts: 167
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Carbon Tape
How about using carbon fiber tape? Was thinking of using this on the joint between the fiberglass tips and aluminum on empennage. Maybe not now!!
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Brian Steeves
#40955 RV-10 - N413BS - Sold
It is Airworthy and Flying. But are they ever done?
First Flight 9/28/2013
#41714 RV-10 - N272BS
Phase 1 Finished, Getting Painted
#120849 RV-12 - N112AB
Flying. First flight Nov 26, 2017
Challenger II - N272MP - Sold
First Flight in 2011
www.briansrv10.com
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02-17-2012, 05:47 PM
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Join Date: Nov 2008
Location: McMinnville, Oregon: HOME of the SPRUCE GOOSE
Posts: 540
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corrosion
Corrosion w/dissimilar metals on the RV's. It is reported that Boeing uses this option.
A post from another thread has addressed this for one option seen below:
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I used light grey 2 part Teflon paint in lieu of the tape, and really like the results. Its the same paint we use on the flaps of all Boeing products where the seals rub the flap leading edges.It is available in white,grey and several other colors..I masked so it does not show when flaps retracted, and applied with a roller to the flap LE as well as the bottom of the wing skin,the same as we do on the big birds.We use Akzo Nobel paint, but others sell it also.This teflon paint is also applied to all of my fairing mating surfaces,gear leg upper and lower ends and cowl flanges. Its super easy to brush on a fresh coat at annual time and keep everything fresh, plus it doesnt peel, yellow or degrade from oil. Try it, you'll like it !
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Bill E.
RV-4/N76WE
Advance NC/8A7
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