Today's Message Index:
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0. 12:17 AM - Fund Raiser Lagging Last Year By Over 30%... (Matt Dralle)
1. 04:26 PM - All 601XL grounded in Belgium (David X)
2. 05:11 PM - Re: All 601XL grounded in Belgium (Craig Payne)
3. 06:32 PM - Re: All 601XL grounded in Belgium (David X)
4. 08:30 PM - 601XL - Aileron Trim Tab Deflection (Dave VanLanen)
5. 08:37 PM - Re: 601XL - Aileron Trim Tab Deflection (Paul Mulwitz)
6. 09:09 PM - Re: 601XL - Aileron Trim Tab Deflection (Terry Phillips)
7. 10:33 PM - Re: All 601XL grounded in Netherlands (David X)
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| Subject: | Fund Raiser Lagging Last Year By Over 30%... |
As of the 13th, the Fund Raiser is currently about 30% behind last year in terms
of the number of Contributions. Yet, oddly the number of messages posted per
day is up by 10 to 20% on the average. It costs real money to run these Lists
and they are supported 100% though your Contributions during the Fund Raiser.
Won't you please take a minute right now to make your Contribution to keep
these Lists up and running?
Contribution Page:
http://www.matronics.com/contribution
Thank you for your support!
Matt Dralle
Email List Admin.
Message 1
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| Subject: | All 601XL grounded in Belgium |
My purpose in posting this is to make information available to builders and owners.
This may affect your periodic or annual inspection. Attention should be given
to the rear attach points at the wing root and the cable tensions, particularly
the ailerons.
I received a call from the FAA today. They wanted me to be aware of the grounding
of all 601XL in Belgium, which was built by Czech Aircraft Works. There are
perhaps 2 in the US that were build by CZAW. One was crashed by my friend in
Virginia (the NTSB preliminary report indicated that there was no fuel in the
wing tanks, fuel lines or carburetor bowls). I own the only remaining 601XL in
the US built by CZAW.
The issues of concern that were conveyed to me by the FAA were aileron flutter
and wing folding. There has not been a conclusion by the NTSB regarding the wing
folding incidents. The aileron flutter is a point of interest but it is not
known whether it is a factor in the Belgium crash.
The thought is that a flutter condition could cause a wing failure if torsional
(twisting) forces were high enough. This is not something unique to the 601XL
but a possible condition in any aircraft with unbalanced control surfaces. By
unbalanced, I mean that there is no counter-weight in aileron, elevator or rudder
to keep them in a neutral position absent any outside force (such as air
flow or control inputs).
I was told that the engineers at the NTSB have reviewed the 601XL design and by
all indications it is a 6G aircraft (theoretical) and is as advertised by the
designer. Of course, it is rated much lower for margin of safety.
The only other information I was given was to make sure that the POH has the correct
calibrated air speeds. Calibrated speeds are preferred over indicated (the
latter varying depending on density altitude, temperature and altitude).
I am not speculating, but simply conveying what I was told over the phone by the
FAA. I'm conveying this in my own words. Nothing in this post are official NTSB
findings.
I have flown my 601XL for 300+ hours. I also flew it coast to coast over the Rockies
twice and I have had zero issues whatsoever with aileron flutter. Years
ago, after hearing about the wing folding incidents, I spot painted the the rear
spar connection points and the main spar attach points as a way to detect any
shift. I have seen zero shift in 3 years of flying.
Linked below are service bulletins issued by something and AMD that apply to this
particular situation. I've included a few links that speak to this situation.
http://www.zenairulm.com/News/pdfdocs/ZE-2008-01.pdf
http://www.newplane.com/Service_Letters_Bulletines/SAFETY_ALERT_october_29_2008.pdf
http://www.zenairulm.com/News/index_files/Page349.htm
http://www.zenairulm.com/News/index_files/Page350.htm
--------
Zodiac 601 XL - CZAW Built - Rotax 912S
DO NOT ARCHIVE
Read this topic online here:
http://forums.matronics.com/viewtopic.php?p=214284#214284
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| Subject: | All 601XL grounded in Belgium |
"There are perhaps 2 in the US that were build by CZAW."
I thought that the Xl that went down in Florida near Sun-n-fun was also a
CZAW plane?
NTSB:
<quote>
NTSB Identification: NYC08FA158
Accident occurred Monday, April 07, 2008 in Polk City, FL
Aircraft: Chech Aircraft Works SPOL SRO CH 601 XL RTF, registration: N357DT
Injuries: 1 Fatal.
This is preliminary information, subject to change, and may contain errors.
Any errors in this report will be corrected when the final report has been
completed.
On April 7, 2008 about 1700 eastern daylight time, a Czech Aircraft Works
SPOL SRO CH 601 XL RTF, N357DT, was substantially damaged when it impacted
trees and terrain following an uncontrolled descent near Polk City, Florida.
<endquote>
FAA database:
N357DT is Assigned
Aircraft Description
Serial Number 6-9733 Type Registration
Individual
Manufacturer Name CZECH AIRCRAFT WORKS SPOL SRO
Certificate Issue Date 11/28/2007
Model CH 601 XL RTF Status Valid
Type Aircraft Fixed Wing Single-Engine Type Engine
Reciprocating
Pending Number Change None Dealer No
Date Change Authorized None Mode S Code
50777453
MFR Year 2005 Fractional Owner NO
-- Craig
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| Subject: | Re: All 601XL grounded in Belgium |
I recall that there was a 3rd, but the NTSB seems to be under the impression that
there were only two. Thank you for the info. I'll pass it along.
--------
Zodiac 601 XL - CZAW Built - Rotax 912S
DO NOT ARCHIVE
Read this topic online here:
http://forums.matronics.com/viewtopic.php?p=214299#214299
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| Subject: | 601XL - Aileron Trim Tab Deflection |
I just finished installing my aileron trim, and when I tested it, I can only
get a total of 40 degrees of deflection. According to the plans, I should
be able to get 50 degrees of deflection (25 up and 25 down). Adjusting the
length of the control rod only changes the distribution of the 40 degrees
between up and down - it does not increase the total deflection. I checked
that the servo was working correctly, which it was (.7" travel per specs).
I also checked that there was no binding of the control rod clevis with the
trim tab horn angle. The only thing I could find was that the center of the
control rod mounting hole in the horn angle was 13 mm up from the flange
instead of the 12 mm specified in the plans. I find it hard to believe that
1 mm would cause a 10 degree loss in deflection.
Has anyone else experienced this problem, and if so, what did you do to
resolve?
Thanks,
Dave Van Lanen
601XL - tail done, flaps done, working on ailerons
Message 5
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| Subject: | Re: 601XL - Aileron Trim Tab Deflection |
Hi Dave,
One thought is the servo you have is not the
correct one. There is a 1.2 inch servo from the
same folks as the .7 inch one. I'm not sure
which one I have or what displacement I get.
One other thought is the prints are sometimes a
bit optimistic on things like this. The flaps
are notorious for this issue since ZAC decided to
change the entire flap motor mechanism to achieve
only 20 degrees instead of the 30 provided by the
older motor. Since there is no version control
on the drawings, the details on your drawings
depend on the exact date they were printed but
the parts depend on the exact date they were
shipped. I guess a call to ZAC is the only way
to answer either of the questions I raised.
(Don't you just hate people who answer questions with further questions?)
Paul
XL getting close
At 08:28 PM 11/14/2008, you wrote:
>I just finished installing my aileron trim, and
>when I tested it, I can only get a total of 40
>degrees of deflection. According to the plans,
>I should be able to get 50 degrees of deflection
>(25 up and 25 down). Adjusting the length of
>the control rod only changes the distribution of
>the 40 degrees between up and down ' it does not
>increase the total deflection. I checked that
>the servo was working correctly, which it was
>(.7=94 travel per specs). I also checked that
>there was no binding of the control rod clevis
>with the trim tab horn angle. The only thing I
>could find was that the center of the control
>rod mounting hole in the horn angle was 13 mm up
>from the flange instead of the 12 mm specified
>in the plans. I find it hard to believe that 1
>mm would cause a 10 degree loss in deflection.
>
>Has anyone else experienced this problem, and if
>so, what did you do to resolve?
>
>Thanks,
>
>Dave Van Lanen
>
>601XL ' tail done, flaps
Message 6
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| Subject: | Re: 601XL - Aileron Trim Tab Deflection |
Dave
I was only able to get +20 -19=B0 in mine. See my Kitlog Pro entry for
1/23/08 (link below). I called ZAC and Caleb told me that would probably be
more than enough. I decided to just live it.
I thought the difference might have been that ZAC has started issuing an
aileron trim tab control horn, 6-ATO-1-6 that is identical to the elevator
trim control horn. When I noticed that the part in my kit differed from the
drawing, they sent me a new one. But the new one was identical to the 1st
one.
If I were doing the ailerons again (and I just might), I would do what
Mirko reported doing. I.e., I'd rivet a length of L-angle on the inside of
the aileron top skin under the servo attachment holes to reduce flexing of
the skin when the trim tab is actuated. Or else, I might just use a spring
loaded internal trim like Klaus Truemper did on his HDS.
Terry
At 10:28 PM 11/14/2008 -0600, you wrote:
>I just finished installing my aileron trim, and when I tested it, I can
>only get a total of 40 degrees of deflection. According to the plans, I
>should be able to get 50 degrees of deflection (25 up and 25
>down). Adjusting the length of the control rod only changes the
>distribution of the 40 degrees between up and down ' it does not increase
>the total deflection. I checked that the servo was working correctly,
>which it was (.7=94 travel per specs). I also checked that there was no
>binding of the control rod clevis with the trim tab horn angle. The only
>thing I could find was that the center of the control rod mounting hole in
>the horn angle was 13 mm up from the flange instead of the 12 mm specified
>in the plans. I find it hard to believe that 1 mm would cause a 10 degree
>loss in deflection.
>
>Has anyone else experienced this problem, and if so, what did you do to
>resolve?
>
>Thanks,
>
>Dave Van Lanen
>
>601XL ' tail done, flaps done, working on ailerons
Terry Phillips ZBAGer
ttp44~at~rkymtn.net
Corvallis MT
601XL/Jab 3300 s .. l .. o .. o .. w build kit - Tail, flaps, & ailerons
are done; working on the wings
http://www.mykitlog.com/N47TP/
Message 7
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| Subject: | Re: All 601XL grounded in Netherlands |
To anyone who read this post before I edited it ... the country in question is
the Netherlands, not Belgium.
--------
Zodiac 601 XL - CZAW Built - Rotax 912S
DO NOT ARCHIVE
Read this topic online here:
http://forums.matronics.com/viewtopic.php?p=214327#214327
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