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1. 11:50 AM - Re: Re: Weight and Balance (teamgrumman@AOL.COM)
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| Subject: | Re: Weight and Balance |
Just in case you didn't read the limits, they are in your Weight and
Balance. It's 92.5 inches aft in a Tiger. I really don't care how the
FAA and Grumman-American came to that conclusion. Their reasoning for
choosing those limits is not my concern.
My point is, and was, the sample loading given in the W&B for ALL of
the Grumman American and Gulfstream-American AA5x aircraft uses a
forward location for the front seat passengers. If one religiously
does his weight and balance (using the sample loading moment arms in
the W&B) and is thinking he is legal when loaded in a loading
configuration that places him 1 inch forward of the aft CG, he will be
aft of that CG, i.e., flying in an unapproved loading configuration,
when he and his co-pilot get in the plane and move their seats to the
aft location.
I know two pilots who use the sample loading sheet as if it were
gospel. There is nothing in the W&B sample loading to differentiate
between fore and aft pilot/co-pilot seat locations.
-----Original Message-----
From: Richard Mutzman <rcmutz@msn.com>
Sent: Sun, Jun 21, 2009 5:25 am
Subject: TeamGrumman-List: Re: Weight and Balance
Not sure which regs the Grumman products were certified under, but I
would consult with FAR 23 or CAR 3 for how they define the aft limit.
There is probably some per
centage forward of neutral stablity that they
used in definingwhere the aft limit should be set. In the case of the
F-16, I believe at its aft limit it has 7% RELAXED static stability,
but a flight control system that constantly moves the tail surface to
maintain the pointy end forward. The B-2 was neutral to slightly
unstable, with quad redundant flight control computers, and the F-22 is
unstable with triplex computers to keep in pointed in the right
direction.
Richard Mutzman
N399RM
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