If the CG range is from 82.1 to 86.7 inches and the total weight is 2,950 pounds with a total moment of 240,700 pound-inches, what action should you take?

If the CG range is from 82.1 to 86.7 inches and the total weight is 2,950 pounds with a total moment of 240,700 pound-inches, what action should you take?

• A. Leave the load as is
• B. Move some load forward in the aircraft
• C. Move some load aft in the aircraft
• D. Remove some baggage

Answer: (C)

To determine the correct action regarding aircraft weight and balance, it's essential to look at the center of gravity (CG) relative to the specified range and the given weight and moment. In this scenario, the CG range is defined as being between 82.1 and 86.7 inches. The total weight is specified as 2,950 pounds, and the total moment is 240,700 pound-inches. To find the actual CG position, you can use the formula: \[ \text{CG} = \frac{\text{Total Moment}}{\text{Total Weight}} \] Substituting the values: \[ \text{CG} = \frac{240,700}{2,950} = 81.6 \text{ inches} \] Calculating this indicates that the CG is located at 81.6 inches, which is below the minimum acceptable limit of 82.1 inches. Since the CG is located forward of the desired range, moving some load aft (toward the tail of the aircraft) will help to adjust the CG position upward toward the acceptable range. By transferring weight aft, you would increase the CG, helping bring it into the operational range of 82.1 to 86.

To determine the correct action regarding aircraft weight and balance, it's essential to look at the center of gravity (CG) relative to the specified range and the given weight and moment.

In this scenario, the CG range is defined as being between 82.1 and 86.7 inches. The total weight is specified as 2,950 pounds, and the total moment is 240,700 pound-inches. To find the actual CG position, you can use the formula:

[ \text{CG} = \frac{\text{Total Moment}}{\text{Total Weight}} ]

Substituting the values:

[ \text{CG} = \frac{240,700}{2,950} = 81.6 \text{ inches} ]

Calculating this indicates that the CG is located at 81.6 inches, which is below the minimum acceptable limit of 82.1 inches. Since the CG is located forward of the desired range, moving some load aft (toward the tail of the aircraft) will help to adjust the CG position upward toward the acceptable range.

By transferring weight aft, you would increase the CG, helping bring it into the operational range of 82.1 to 86.