AMT Aircraft Weight and Balance Questions and Answers

Question 1

An aircraft is loaded such that its center of gravity (CG) is located aft of the allowable range. Which of the following is a likely consequence of this condition?

Accepted Answer

Difficulty recovering from a stall.

Answer

An aft CG location reduces longitudinal stability, making the aircraft tail-heavy. This condition makes it more difficult to recover from a stall or spin because the center of gravity is closer to the center of pressure, reducing the natural nose-down pitching moment that aids in recovery.

Question 2

Which of the following defines an aircraft's 'useful load'?

Accepted Answer

The difference between the maximum takeoff weight and the basic empty weight.

Answer

The useful load is the weight of the pilot, copilot, crew, passengers, baggage, and usable fuel. It is calculated by subtracting the basic empty weight (which includes the airframe, engines, and fixed equipment) from the maximum allowable takeoff weight.

Question 3

A technician must calculate the center of gravity of an aircraft. What is the correct formula to use?

Accepted Answer

Total Moment / Total Weight

Answer

The center of gravity (CG) is calculated by dividing the total moment by the total weight of the aircraft. The moment is the product of a weight and its arm (the distance from a reference datum).

Question 4

During a pre-weighing inspection, a technician is preparing an aircraft according to the Type Certificate Data Sheet (TCDS) and maintenance manual. Which of the following is a critical step in this preparation?

Accepted Answer

Leveling the aircraft both longitudinally and laterally.

Answer

To ensure an accurate weight and balance measurement, the aircraft must be in a specific level flight attitude as defined by the manufacturer. This is achieved by leveling it both longitudinally (pitch) and laterally (roll) using jacks and leveling tools specified in the maintenance manual.

Question 5

A modification adds a new antenna weighing 5 pounds at an arm of +150 inches. The aircraft's total weight before the modification was 2,500 pounds with a total moment of 212,500 inch-pounds. What is the new center of gravity?

Accepted Answer

85.05 inches

Answer

First, calculate the moment of the new antenna: 5 lbs * 150 in = 750 in-lbs. Next, add the new weight and moment to the existing totals: New Weight = 2,500 + 5 = 2,505 lbs. New Moment = 212,500 + 750 = 213,250 in-lbs. Finally, calculate the new CG: New CG = New Moment / New Weight = 213,250 / 2,505 = 85.13 inches.

(AMT) Aviation Maintenance Technician Practice Test

(AMT) Aviation Maintenance Technician Practice Test

AMT Aircraft Weight and Balance Questions and Answers