Procedure for calculating weight and balance

The manual for my aircraft gives figures for MOM and ARM at various
stations, but it doesn't actually explain how to use these to
calculate weight and balance. I want to place the load so that the
aircraft neither pitches down nor pitches up. Can someone provide me
with a pointer to an explanation of the procedure on the Web
somewhere?

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Recently, Mxsmanic posted:

The manual for my aircraft gives figures for MOM and ARM at various
stations, but it doesn't actually explain how to use these to
calculate weight and balance. I want to place the load so that the
aircraft neither pitches down nor pitches up. Can someone provide me
with a pointer to an explanation of the procedure on the Web
somewhere?

The calculations are simple math. Why would you need a pointer to anything
but an elementary math book?

Neil

Neil Gould writes:

The calculations are simple math. Why would you need a pointer to anything
but an elementary math book?

I'm sure the calculations are simple, but I still need an explanation
of which calculations to perform.

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No one places the loads to exactly so as to balance the airplane. The
elevator downward force is increased or decreased during flight to
balance the airplane for varying load conditions. For example, when a
passenger walks forward, the elevator downward force must be increased
to counteract that. The CG is calculated using the moments and arms to
make sure that it falls within the approved limits. If the CG falls too
far forward or too far backward, the elevator may not be able to
provide the force necessary to balance the airplane.
See he http://en.wikipedia.org/wiki/Center_...%28aircraft%29


Mxsmanic wrote:
The manual for my aircraft gives figures for MOM and ARM at various
stations, but it doesn't actually explain how to use these to
calculate weight and balance. I want to place the load so that the
aircraft neither pitches down nor pitches up. Can someone provide me
with a pointer to an explanation of the procedure on the Web
somewhere?

--
Transpose mxsmanic and gmail to reach me by e-mail.

"Mxsmanic" wrote in message
...
Neil Gould writes:

The calculations are simple math. Why would you need a pointer to
anything
but an elementary math book?

I'm sure the calculations are simple, but I still need an explanation
of which calculations to perform.


An Example should be in the POH that explains everything

BT

Andrew Sarangan writes:

No one places the loads to exactly so as to balance the airplane. The
elevator downward force is increased or decreased during flight to
balance the airplane for varying load conditions. For example, when a
passenger walks forward, the elevator downward force must be increased
to counteract that. The CG is calculated using the moments and arms to
make sure that it falls within the approved limits. If the CG falls too
far forward or too far backward, the elevator may not be able to
provide the force necessary to balance the airplane.
See he http://en.wikipedia.org/wiki/Center_...%28aircraft%29

I didn't realize Wikipedia had an article on this. I'll take a look.

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BT writes:

An Example should be in the POH that explains everything

I looked, and there are charts, but nothing specific on how to
actually calculate things. The Wikipedia article helped, although I
still don't know how to find the center of gravity in the aircraft, as
apparently manufacturers don't set their reference point at the actual
center of gravity (the point that would keep the aircraft level).

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also check faa.gov AC-61-238 "Pilots' Handbook of Aeronautical
Knowledge" will answer all your questions (I hope).


Mxsmanic wrote:
Andrew Sarangan writes:

No one places the loads to exactly so as to balance the airplane. The
elevator downward force is increased or decreased during flight to
balance the airplane for varying load conditions. For example, when a
passenger walks forward, the elevator downward force must be increased
to counteract that. The CG is calculated using the moments and arms to
make sure that it falls within the approved limits. If the CG falls too
far forward or too far backward, the elevator may not be able to
provide the force necessary to balance the airplane.
See he http://en.wikipedia.org/wiki/Center_...%28aircraft%29

I didn't realize Wikipedia had an article on this. I'll take a look.

In article ,
Mxsmanic wrote:

Neil Gould writes:

The calculations are simple math. Why would you need a pointer to anything
but an elementary math book?

I'm sure the calculations are simple, but I still need an explanation
of which calculations to perform.


All W & B calculations result from taking the sum of all moments and
dividing by the sum of the associated weights.

Sum (arm*weight) / sum (weight) = CG

The arms are referenced to the datum -- an arbitrary point -- sometimes
the LE of the wing, sometimes a point ahead of the nose; but nonetheless
it is THE reference point for a given aircraft.

The POH will list the arms for each seat, fuel, oil, baggage, etc.

Mxsmanic opined

Neil Gould writes:

The calculations are simple math. Why would you need a pointer to anything
but an elementary math book?

I'm sure the calculations are simple, but I still need an explanation
of which calculations to perform.
__
\
\
arm * weight = (arm * weight )
aircraft aircraft / components components
/__





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