EXAMPLE OF THE DETERMINATION OF THE NUMBER OF
PASSENGERS AND BAGGAGE PERMISSIBLE WITH FULL FUEL

Divide the TM (total moment) by the TW (total weight) to obtain the
loaded center of gravity.

The above computations show that with full fuel, 100 pounds of baggage
and two passengers in the rear seat may be carried in this aircraft
without exceeding either the maximum weight or the approved C.G. range.

This condition may be entered in the loading schedule as follows:

Only two passengers are listed to prevent the maximum weight

of 2100 lbs. from being exceeded.

FIGURE 16-12-Loading conditions: Determination of the number of passengers and baggage permissible with full fuel.

EXAMPLE OF THE DETERMINATION OF THE POUNDS OF FUEL
AND BAGGAGE PERMISSIBLE WITH MAXIMUM PASSENGERS

Divide the TM (total moment) by the TW (total weight) to obtain the loaded center of gravity.

The above computations show that with the maximum number of passengers, 39 gallons of fuel and zero pounds of baggage may be carried in this aircraft without exceeding either the maximum weight or the approved C.G. range.

This condition may be entered in the loading schedule as follows:

FIGURE 16-18-Loading conditions: Determination of the fuel and baggage permissible with maximum passengers.

EXAMPLE OF THE DETERMINATION OF THE FUEL AND THE NUMBER AND
LOCATION OF PASSENGERS PERMISSIBLE WITH MAXIMUM BAGGAGE

The above computations show that with maximum baggage, full
fuel and 2 passengers (1 in the front seat and 1 in the rear seat)
may be carried in this aircraft without exceeding either the
maximum weight or the approved C.G. range.

FIGURE 16-14-Loading conditions: Determination of the fuel and the number and location of passenger permissible with maximum baggage.

FIGURE 16-15-Effects of the addition of equipment items on balance.

FIGURE 16-16-Example of moment and weight changes resulting from equipment changes.

1. Leveling means: level top longeron between front and rear seats.

2. Main wheel weighing point is located

of datum.

_"FORWARD) (+ 3" AFT)

3. Actual measured distance from the main weight point centerline to the tail (or nose) point centerline_222_".

4. Oil over and above "ZERO" tank reading = (a._—_ Gals.)(b._—_Lbs.)(c.__—__In.)

(a) Tail wheel airc. (Item 10a ̧ + 7.6) added to (Item 2, + 3) = ± 10.6′′ = C.G.| (b) No se wheel airc. (Item 10b,

added to (Item 2,

COMPUTE IF AIRCRAFT WEIGHED WITH OIL (Item 4)

=

= C.G.

FIGURE 16-17-Sample weight and balance report to determine empty weight center-of-gravity.