What is the CG expressed in %MAC based on the following weights: Nose wheel 20,500 lbs, Right wheel 70,000 lbs, Left wheel 70,500 lbs?

To determine the Center of Gravity (CG) expressed in % Mean Aerodynamic Chord (MAC), you first need to calculate the total weight of the aircraft and how the weight is distributed across the wheels.

The total weight is the sum of all the wheel weights:

Nose wheel: 20,500 lbs

Right wheel: 70,000 lbs

Left wheel: 70,500 lbs

Total Weight = 20,500 + 70,000 + 70,500 = 161,000 lbs.

Next, you would calculate the moments for each wheel, which is typically done by multiplying the weight by its respective arm (distance from a reference point). However, since the actual distances (arms) are not provided in this question, we can simplify by focusing on the percentage calculation.

To find the CG in %MAC, you would compare the measured CG (which you would find by calculating the moments if you had the arms) to the total Mean Aerodynamic Chord of the aircraft. The %MAC is calculated using the formula:

%MAC = (CG position / MAC) * 100.

Without the specific CG value and the MAC, it's presumed in a practical scenario that you've calculated these values externally, perhaps through additional data