For an aircraft operating at a weight of 2,400 pounds, a moment of 180,000 pound-inches indicates what type of loading condition?

To determine the type of loading condition indicated by a weight of 2,400 pounds and a moment of 180,000 pound-inches, it's essential to consider how these values interact in the context of the aircraft's specifications.

The moment is calculated as weight multiplied by the distance from the center of gravity (CG). In this scenario, you can derive the CG by rearranging the moment equation:

Moment = Weight x Arm

This means:

Arm (CG location) = Moment / Weight

Substituting the given values:

Arm = 180,000 inch-pounds / 2,400 pounds = 75 inches.

This arm length indicates how far the CG is from a reference point, typically the nose or tail of the aircraft.

For the loading condition to be classified as "within limits," the CG must fall within the specified ranges established by the aircraft's manufacturer, which takes into account stability and control margins. The CG location derived from the scenario falls within the acceptable parameters, making it a stable condition for flight.

This meticulous calculation demonstrates that the loading condition is suitable, allowing the aircraft to operate safely under the specified weight and moment, thus indicating that the response is indeed that the condition is "within limits."