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<DIV><FONT face=Arial size=2>Gray, do you think the CTE of the AeroSlave
laminate would be different than the styrofoam laminate used by many
others?</FONT></DIV>
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<DIV style="FONT: 10pt arial">----- Original Message ----- </DIV>
<DIV
style="BACKGROUND: #e4e4e4; FONT: 10pt arial; font-color: black"><B>From:</B>
<A title=gfowler@raytheon.com href="mailto:gfowler@raytheon.com">Gray E
Fowler</A> </DIV>
<DIV style="FONT: 10pt arial"><B>To:</B> <A
title=nsrca-discussion@lists.nsrca.org
href="mailto:nsrca-discussion@lists.nsrca.org">NSRCA Mailing List</A> </DIV>
<DIV style="FONT: 10pt arial"><B>Sent:</B> Monday, May 08, 2006 10:51 AM</DIV>
<DIV style="FONT: 10pt arial"><B>Subject:</B> Re: [NSRCA-discussion] Elevator
trim change</DIV>
<DIV><BR></DIV><BR><FONT face=sans-serif size=2>Fiberglass laminate CTE = 6
X10 -6/in/in/F</FONT> <BR><BR><FONT face=sans-serif size=2>CF pushrod CTE = 1
X 10 -6 /in/in/F ....could actually be 0 if fiber vloume is > 58% an
all uni fibers</FONT> <BR><BR><BR><BR><FONT face=sans-serif
size=2><BR><BR><BR>Gray Fowler<BR>Principal Chemical Engineer<BR>Composites
Engineering</FONT>
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