Today's Message Index:
----------------------
1. 06:16 AM - Re: Glasair spars (Bruce Gray)
2. 09:50 AM - Re: Glasair spars (B.J. McClure)
3. 10:35 AM - Re: Glasair spars (Bruce Gray)
4. 10:53 AM - Re: Glasair spars (Craymondw@aol.com)
5. 11:04 AM - Re: Glasair spars (B.J. McClure)
Message 1
| INDEX | Back to Main INDEX |
| NEXT | Skip to NEXT Message |
| LIST | Reply to LIST Regarding this Message |
| SENDER | Reply to SENDER Regarding this Message |
|
Actually, there has been a structural failure of a Glasair III. It was
similar to the Columbia incident. Chip Beck was flying his GIII at an
airshow, during his acro routine he experienced a wing skin/spar
delamination. Fuel was sloshing all over. He said he was pulling about 9
G's
at the time. The wing was originally closed by Phoenix Composites using
a
non-standard closing method and material.
Bruce
www.Glasair.org
-----Original Message-----
From: owner-glasair-list-server@matronics.com
[mailto:owner-glasair-list-server@matronics.com] On Behalf Of
Craymondw@aol.com
Sent: Tuesday, December 14, 2010 11:45 AM
Subject: Glasair-List: Glasair spars
I just read a report about a wing skin on a Cessna Columbia "disbonding
seven feet during a production acceptance flight test." The FAA is
issuing
an AD and looking into if "unsafe condition is likely to exist in other
products of the same type of design." As I was building my Glasair I
needed
to disbond my rudder skins because of a mistake I made and was surprised
how
easily they came apart and hoped my wing skins would fair better. I had
a
friend that manufactured glass sail boats help me and he sanded my spars
and
wing skins with 80 grit paper and washed them with acetone before
laminating
them together. During the construction he would comment on the parts and
would ask in his thick German accent; ""Vat did Glasair design..a
tank?!!"
When I incorrectly laminated a foot long fiber glass right angle to the
inside of a fuselage skin I at first tried to pop it off using a hammer
and
chisel and couldn't and ended spending a long time sawing it off with a
hack
saw blade. Four years later when my nose gear sheared off the plane as I
was
landing on a sandy soil threshold causing my right wing dug into the
ground
and cart wheeling the plane. My concern was disbonding of the wing
skins. I
tapped the entire length of the spar with a coin and couldn't detect any
disbonding. My German fiberglass expert friend advised that if my skins
hadn't rippled there wouldn't be any disbonding. All of my damage was at
the
point of contact. My G-Meter was pegged at 14G's and I couldn't decide
if
the wing actually stood 14 G's or if that was the shock of the nose
digging
into the ground. Bob Heredeen pulled very high G's in both his Glasair 2
and
3 for years. Also Glasair uses a different resin than Lancair that may
be
stronger. I completed my plane in the spring of 1991 and had the nose
wheel
assembly part company in 1996. After I repaired my plane I pulled my
chute
from my Pitt's S1S and flew up to 6,000 feet and did aerobatics to test
my
wings and pulled close to six G's. I never bailed out of a plane before
and
hoped I wouldn't have to. I would also add that there has never been an
in
flight structural failure of a Glasair. My hope is that the FAA doesn't
jump
the gun and issue an AD on Glasair's and that they first contact the
company
and retrieve some data.
Message 2
| INDEX | Back to Main INDEX |
| PREVIOUS | Skip to PREVIOUS Message |
| NEXT | Skip to NEXT Message |
| LIST | Reply to LIST Regarding this Message |
| SENDER | Reply to SENDER Regarding this Message |
|
On Thu, 2010-12-16 at 09:13 -0500, Bruce Gray wrote:
> The wing was originally closed by Phoenix Composites using a
> non-standard closing method and material.
Would you elaborate on this a little. What exactly was the "method" and
"materials". Thanks in advance.
B.J. McClure
Glasair III N300JJ
Thu Dec 16 12:44:20 EST 2010, RHEL 6, Linux 2.6.32-71.7.1.el6.x86_64
x86_64
Message 3
| INDEX | Back to Main INDEX |
| PREVIOUS | Skip to PREVIOUS Message |
| NEXT | Skip to NEXT Message |
| LIST | Reply to LIST Regarding this Message |
| SENDER | Reply to SENDER Regarding this Message |
|
>From what I've been told is that they used a mixture of resin, mill
fiber,
and cabosil. Cabosil in high strength bonds is a no-no. All it does is
weaken the bond.
Bruce
www.Glasair.org
-----Original Message-----
From: owner-glasair-list-server@matronics.com
[mailto:owner-glasair-list-server@matronics.com] On Behalf Of B.J.
McClure
Sent: Thursday, December 16, 2010 12:47 PM
Subject: RE: Glasair-List: Glasair spars
On Thu, 2010-12-16 at 09:13 -0500, Bruce Gray wrote:
The wing was originally closed by Phoenix Composites using a
non-standard
closing method and material.
Would you elaborate on this a little. What exactly was the "method" and
"materials". Thanks in advance.
B.J. McClure
Glasair III N300JJ
Thu Dec 16 12:44:20 EST 2010, RHEL 6, Linux 2.6.32-71.7.1.el6.x86_64
x86_64
Message 4
| INDEX | Back to Main INDEX |
| PREVIOUS | Skip to PREVIOUS Message |
| NEXT | Skip to NEXT Message |
| LIST | Reply to LIST Regarding this Message |
| SENDER | Reply to SENDER Regarding this Message |
|
| Subject: | Re: Glasair spars |
Know your materials and in critical areas follow the manual. In a
message dated 12/16/2010 1:36:08 P.M. Eastern Standard Time, bgray@glasair
.org
writes:
>From what I=99ve been told is that they used a mixture of resin,
mill
fiber, and cabosil. Cabosil in high strength bonds is a no-no. All it doe
s is
weaken the bond.
Bruce
www.Glasair.org
-----Original Message-----
From: owner-glasair-list-server@matronics.com
[mailto:owner-glasair-list-server@matronics.com] On Behalf Of B.J. McClure
Sent: Thursday, December 16, 2010 12:47 PM
Subject: RE: Glasair-List: Glasair spars
On Thu, 2010-12-16 at 09:13 -0500, Bruce Gray wrote:
The wing was originally closed by Phoenix Composites using a non-standard
closing method and material.
Would you elaborate on this a little. What exactly was the "method" and
"materials". Thanks in advance.
B.J. McClure
Glasair III N300JJ
Thu Dec 16 12:44:20 EST 2010, RHEL 6, Linux 2.6.32-71.7.1.el6.x86_64
x86_64
========================
============
(http://www.aeroelectric.com/)
(http://www.buildersbooks.com/)
(http://www.homebuilthelp.com/)
(http://www.matronics.com/contribution)
========================
============
(http://www.matronics.com/Navigator?Glasair-List)
========================
============
========================
============
Message 5
| INDEX | Back to Main INDEX |
| PREVIOUS | Skip to PREVIOUS Message |
| NEXT | Skip to NEXT Message |
| LIST | Reply to LIST Regarding this Message |
| SENDER | Reply to SENDER Regarding this Message |
|
Thanks. Appreciate the info.
On Thu, 2010-12-16 at 13:24 -0500, Bruce Gray wrote:
> >From what Ive been told is that they used a mixture of resin, mill
> fiber, and cabosil. Cabosil in high strength bonds is a no-no. All it
> does is weaken the bond.
>
>
>
>
> Bruce
> www.Glasair.org
>
>
>
> -----Original Message-----
> From: owner-glasair-list-server@matronics.com
> [mailto:owner-glasair-list-server@matronics.com] On Behalf Of B.J.
> McClure
> Sent: Thursday, December 16, 2010 12:47 PM
> To: glasair-list@matronics.com
> Subject: RE: Glasair-List: Glasair spars
>
>
>
> On Thu, 2010-12-16 at 09:13 -0500, Bruce Gray wrote:
>
>
>
> The wing was originally closed by Phoenix Composites using a
> non-standard closing method and material.
>
>
> Would you elaborate on this a little. What exactly was the "method"
> and "materials". Thanks in advance.
>
> B.J. McClure
> Glasair III N300JJ
>
> Thu Dec 16 12:44:20 EST 2010, RHEL 6, Linux 2.6.32-71.7.1.el6.x86_64
> x86_64
>
>
>
>
>
>
>
>
>
Thu Dec 16 14:00:14 EST 2010, RHEL 6, Linux 2.6.32-71.7.1.el6.x86_64
x86_64
Other Matronics Email List Services
These Email List Services are sponsored solely by Matronics and through the generous Contributions of its members.
-- Please support this service by making your Contribution today! --
|