Cracks in tail stinger bulkhead

[Al Paxhia]

Hi Gang,
Brian Godden has been here for the past three days helping do the annual
inspection of the Moose,
464 hours total time, 74 hours on wheels, 390 on floats, 200 hours this past
year. I had noted that the tail wrap fitting where the stinger exits the
tail cone had damage.
Brian found cracks in the bulkhead that holds the tail stinger, it was the
first place he looked. Brian's comment was "that is where they all crack".
He said Darryl's position was that the cracking was an anomaly.
Brian's fix was to install an angle on each side over the crack and attach
the angle to the side of the tailcone by added an additional angle down the
side of the tail wrap, backing the existing flange.
We are not sure the fix is a great fix, needs more engineering. Brian thinks
the bulkhead is way under designed for the size of the airplane and that
area need lots of beefing up. My friend Graham Clapp, retired Boeing
Structures Engineer says the stinger needs to float in a shock mount at the
forward end. That will absorb some of the shock load of the stinger. He
thinks the rigid mounting is a major part of the problem.
I just don't know what to think, what do you guys think? I will post
pictures.
Al
Moose, N526AP





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[Dick Shotwell]

Hi Al,
Let us know where you are posting the pictures. Thanks for this
information.
Dick and Dave Shotwell
Moose 096
N235DS
Twin Falls, ID


----- Original Message -----
From: "Al Paxhia" <paxhia2@comcast.net>
To: <rebel-builders@dcsol.com>
Sent: Thursday, March 31, 2005 21:01 PM
Subject: Cracks in tail stinger bulkhead

Hi Gang,
Brian Godden has been here for the past three days helping do the annual
inspection of the Moose,
464 hours total time, 74 hours on wheels, 390 on floats, 200 hours this

past

year. I had noted that the tail wrap fitting where the stinger exits the
tail cone had damage.
Brian found cracks in the bulkhead that holds the tail stinger, it was the
first place he looked. Brian's comment was "that is where they all crack".
He said Darryl's position was that the cracking was an anomaly.
Brian's fix was to install an angle on each side over the crack and attach
the angle to the side of the tailcone by added an additional angle down

the

side of the tail wrap, backing the existing flange.
We are not sure the fix is a great fix, needs more engineering. Brian

thinks

the bulkhead is way under designed for the size of the airplane and that
area need lots of beefing up. My friend Graham Clapp, retired Boeing
Structures Engineer says the stinger needs to float in a shock mount at

the

forward end. That will absorb some of the shock load of the stinger. He
thinks the rigid mounting is a major part of the problem.
I just don't know what to think, what do you guys think? I will post
pictures.
Al
Moose, N526AP





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[larry173]

Cessna has done it for years in the 180 and 1185 and don't have a problem. I
think they use a rubber bushing at the front end. Is the cracking at the
front or rear attach point.
----- Original Message -----
From: "Al Paxhia" <paxhia2@comcast.net>
To: <rebel-builders@dcsol.com>
Sent: Thursday, March 31, 2005 11:01 PM
Subject: Cracks in tail stinger bulkhead

Hi Gang,
Brian Godden has been here for the past three days helping do the annual
inspection of the Moose,
464 hours total time, 74 hours on wheels, 390 on floats, 200 hours this
past
year. I had noted that the tail wrap fitting where the stinger exits the
tail cone had damage.
Brian found cracks in the bulkhead that holds the tail stinger, it was the
first place he looked. Brian's comment was "that is where they all crack".
He said Darryl's position was that the cracking was an anomaly.
Brian's fix was to install an angle on each side over the crack and attach
the angle to the side of the tailcone by added an additional angle down
the
side of the tail wrap, backing the existing flange.
We are not sure the fix is a great fix, needs more engineering. Brian
thinks
the bulkhead is way under designed for the size of the airplane and that
area need lots of beefing up. My friend Graham Clapp, retired Boeing
Structures Engineer says the stinger needs to float in a shock mount at
the
forward end. That will absorb some of the shock load of the stinger. He
thinks the rigid mounting is a major part of the problem.
I just don't know what to think, what do you guys think? I will post
pictures.
Al
Moose, N526AP





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[Scott Aldrich]

Thanks Al, let us know when the pictures are posted.

Did you guys accomplish your "fix" through the single side inspection hole
or did you remove the horizontal stab and lower tail wrap? I suspect you
removed everything.

I added angles and a rear fin spar bottom stinger wrap back when I closed
that all up so I am hoping it will be okay for awhile anyway.

Steve has the best I have seen so far; the entire forward stab bulkhead is
fabricated out of heavy gauge aluminum with the side and stinger attach
flanges all welded together.

What do I think? I think it is more than an anomaly and that everyone's
will eventually crack and that it was a known issue since Arlington 2002
when the demonstrator had an obvious "fix" back there. What should MAM do?
Fix the current kits before they go out the door, post a bulletin for past
kits. Should they pay for it like they are the wing tip fix? In my opinion
no, (and I don't really see why they are paying for that one either) this is
experimental and crap happens. Just let us know about issues as they arise
(even if they think it is just an "anomaly"), I don't need practice removing
rivets.

Oh, why I am at it, I still think the main gear attach set up on the
SR/Moose is crap too, and that "anomaly" will arise (or collapse:) ) again
in the future.

Scott
Moose 174

-----Original Message-----
From: mike.davis@dcsol.com [mailto:mike.davis@dcsol.com] On Behalf Of Al
Paxhia
Sent: Thursday, March 31, 2005 9:01 PM
To: rebel-builders@dcsol.com
Subject: Cracks in tail stinger bulkhead

Hi Gang,
Brian Godden has been here for the past three days helping do the annual
inspection of the Moose,
464 hours total time, 74 hours on wheels, 390 on floats, 200 hours this
past
year. I had noted that the tail wrap fitting where the stinger exits the
tail cone had damage.
Brian found cracks in the bulkhead that holds the tail stinger, it was the
first place he looked. Brian's comment was "that is where they all crack".
He said Darryl's position was that the cracking was an anomaly.
Brian's fix was to install an angle on each side over the crack and attach
the angle to the side of the tailcone by added an additional angle down
the
side of the tail wrap, backing the existing flange.
We are not sure the fix is a great fix, needs more engineering. Brian
thinks
the bulkhead is way under designed for the size of the airplane and that
area need lots of beefing up. My friend Graham Clapp, retired Boeing
Structures Engineer says the stinger needs to float in a shock mount at
the
forward end. That will absorb some of the shock load of the stinger. He
thinks the rigid mounting is a major part of the problem.
I just don't know what to think, what do you guys think? I will post
pictures.
Al
Moose, N526AP





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[Barnhart]

Al,

Did Brian mention what the cause of it was?

Maybe more two wheel landings.

Maybe a different length on the tiger tail.......


Barny
SR 103 20bt


----- Original Message ----- > From: "Al Paxhia" <paxhia2@comcast.net>

To: <rebel-builders@dcsol.com>
Sent: Thursday, March 31, 2005 21:01 PM
Subject: Cracks in tail stinger bulkhead

Hi Gang,
Brian Godden has been here for the past three days helping do the annual
inspection of the Moose,
464 hours total time, 74 hours on wheels, 390 on floats, 200 hours this

past

year. I had noted that the tail wrap fitting where the stinger exits

the

tail cone had damage.
Brian found cracks in the bulkhead that holds the tail stinger, it was

the

first place he looked. Brian's comment was "that is where they all

crack".

He said Darryl's position was that the cracking was an anomaly.
Brian's fix was to install an angle on each side over the crack and

attach

the angle to the side of the tailcone by added an additional angle down

the

side of the tail wrap, backing the existing flange.
We are not sure the fix is a great fix, needs more engineering. Brian

thinks

the bulkhead is way under designed for the size of the airplane and that
area need lots of beefing up. My friend Graham Clapp, retired Boeing
Structures Engineer says the stinger needs to float in a shock mount at

the

forward end. That will absorb some of the shock load of the stinger. He
thinks the rigid mounting is a major part of the problem.
I just don't know what to think, what do you guys think? I will post
pictures.
Al
Moose, N526AP





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[Al Paxhia]

Barny,
Brian said the cause was not keeping the airplane on the amphib floats...Al
----- Original Message -----
From: "Barnhart" <dsbarno@vbe.com>
To: <rebel-builders@dcsol.com>
Sent: Friday, April 01, 2005 6:57 AM
Subject: Re: Cracks in tail stinger bulkhead

Al,

Did Brian mention what the cause of it was?

Maybe more two wheel landings.

Maybe a different length on the tiger tail.......


Barny
SR 103 20bt


----- Original Message ----- > From: "Al Paxhia" <paxhia2@comcast.net>

To: <rebel-builders@dcsol.com>
Sent: Thursday, March 31, 2005 21:01 PM
Subject: Cracks in tail stinger bulkhead

Hi Gang,
Brian Godden has been here for the past three days helping do the
annual
inspection of the Moose,
464 hours total time, 74 hours on wheels, 390 on floats, 200 hours this

past

year. I had noted that the tail wrap fitting where the stinger exits

the

tail cone had damage.
Brian found cracks in the bulkhead that holds the tail stinger, it was

the

first place he looked. Brian's comment was "that is where they all

crack".

He said Darryl's position was that the cracking was an anomaly.
Brian's fix was to install an angle on each side over the crack and

attach

the angle to the side of the tailcone by added an additional angle down

the

side of the tail wrap, backing the existing flange.
We are not sure the fix is a great fix, needs more engineering. Brian

thinks

the bulkhead is way under designed for the size of the airplane and
that
area need lots of beefing up. My friend Graham Clapp, retired Boeing
Structures Engineer says the stinger needs to float in a shock mount at

the

forward end. That will absorb some of the shock load of the stinger. He
thinks the rigid mounting is a major part of the problem.
I just don't know what to think, what do you guys think? I will post
pictures.
Al
Moose, N526AP





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