L23 weight and balance

I understand how to determine the CG from the charts in the manual. But,
I would like to do it the traditional way - you know, moment = arm *
weight....

The manual does not provide the arm numbers for the various positions,
not does it tell you the numeric CG range. A bit odd, I think, but there
you are.

I would appreciate any one having that data to kindly point me to it.

Thanks and regards,

Tony V.

Tony.. I have referenced my L-23S manual and the USAF Flight Test Center
"SPIN TEST" report on the L-23.

The reference datum is 93.6 in aft of the sailplane nose (paragraph 6.3)
This also correlates to the leading edge of Rib #1, Table in Para 6.6, arm
for reference for installing instruments defines "Arm from the reference
plane (rib #1 in ft.", this becomes the "zero" line). Front instrument panel
is -5.82ft and rear instrument panel is -1.81ft. Yes.. moment arms are
negative because you are in front of the reference datum.

-5.82 x12 = -69.84 inches (moment arm), -1.82 x12= 21.72 inches
There are rear instrument panel references from -1.79 to -1.87 (something
lost in translation or factory typing error?)

I have made measurements for the seat positions (remember to measure to the
belly button) and determined that the P1(front) is apx -49.9inches and
P2(Rear) is apx -5.8inches (these are personal measurements of the aircraft
and not the manufacturers numbers).

Doing the math from the reference datum to convert %MAC to "inches", I came
up with 23%MAC = 4.397inches aft of datum and 40%MAC is 12.78inches aft of
datum.

For the particular L-23S that this was computed for (empty wt 712# at 21.54
arm (67.4%MAC)
Min pilot weight no ballast was 100#, extreme aft CG limit. Max Solo pilot
wt 225#, extreme forward limit.

Use the W&B factory data to get your numbers.

send me your email, I'll send you a spreadsheet
http://members.cox.net/btiz2 for my address.

BT

"Tony Verhulst" wrote in message
...
I understand how to determine the CG from the charts in the manual. But, I
would like to do it the traditional way - you know, moment = arm *
weight....

The manual does not provide the arm numbers for the various positions, not
does it tell you the numeric CG range. A bit odd, I think, but there you
are.

I would appreciate any one having that data to kindly point me to it.

Thanks and regards,

Tony V.

Perfect! Exactly what I need. Thanks!

Tony

Go to the FAA site listed below.
The TCDS has all the numbers you are looking for.
The L 23 TCDS is G60EU


http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgMakeModel.nsf/0/8108911a16190383862570e60055cd92/$FILE/G60eu.pdf

If you know the pilot weight and the empty weight and CG location, you
can also determine the pilot arm algebraically. See step 4B about 2/3
of the way down this Dick Schreder article:

http://www.soaridaho.com/Schreder/Sc...976_HP-18.html

Thanks, and best regards to all

Bob K.

yes it does.. thanx..
BT

wrote in message
oups.com...
Go to the FAA site listed below.
The TCDS has all the numbers you are looking for.
The L 23 TCDS is G60EU


http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgMakeModel.nsf/0/8108911a16190383862570e60055cd92/$FILE/G60eu.pdf