12.108 Weight and Loading

12.108.2 Given a basic aircraft load sheet/data, demonstrate the ability to:

(a) calculate the C of G position;

to calculate the center of gravity (C of G) position, you need to know the weight and arm of each item loaded on the aircraft. The C of G position can be calculated by dividing the sum of the moments by the sum of the weights. The formula is: C of G position = (Sum of the moments) / (Sum of the weights) Once you have calculated the C of G position, you can compare it to the longitudinal C of G range and associated limits to ensure that it is within the acceptable range. If the C of G position is outside of the acceptable range, you will need to adjust the loading of the aircraft to bring it back within the acceptable range.

(b) use a typical loading graph to determine C of G position;

To use a typical loading graph to determine C of G position, you need to know the weight and arm of each item loaded on the aircraft. The loading graph is a visual representation of the weight and balance of the aircraft. The graph typically shows the weight and arm of each item loaded on the aircraft, as well as the moment for each item. The graph also shows the longitudinal C of G range and associated limits. To determine the C of G position using the loading graph, you need to plot the weight and moment of each item on the graph. Once you have plotted all of the weights and moments, you can draw a line connecting the points. The intersection of this line with the longitudinal C of G range is the C of G position. If the C of G position is within the acceptable range, the aircraft is considered to be properly loaded. If the C of G position is outside of the acceptable range, you will need to adjust the loading of the aircraft to bring it back within the acceptable range.