FAA Weight and Balance Test 2

Question 1

Determine the moment with the following data:

Accepted Answer

74.9 pound-inches.

Answer

A moment is calculated by multiplying a force by its perpendicular distance (arm) from a reference point or fulcrum (Moment = Force × Arm). Since the specific force and arm values are not provided in the question, a direct calculation is not possible. However, if the appropriate data were given, the resulting moment would be 74.9 pound-inches, representing the rotational effect of the force.

Question 2

Determine the aircraft loaded moment and the aircraft category.

Accepted Answer

79.2, normal category.

Answer

To determine the aircraft's loaded moment, one must sum the moments of all individual components (empty weight, fuel, occupants, baggage) by multiplying each item's weight by its arm. The aircraft category (Normal or Utility) is then determined by comparing the calculated center of gravity (CG) to the aircraft's approved CG envelope, typically found in the Pilot's Operating Handbook. A total moment of 79.2 and a CG falling within the normal category limits would be derived from correctly applying these calculations to the specific data provided in the associated figures.

Question 3

Upon landing, the front passenger (180 pounds) departs the airplane. A rear passenger (204 pounds) moves to the front passenger position. What effect does this have on the CG if the airplane weighed 2,690 pounds and the MOM\/100 was 2,260 just prior to the passenger transfer?

Accepted Answer

The CG moves forward approximately 3 inches.

Answer

The CG shift is calculated by multiplying the weight shifted by the distance it was shifted, then dividing by the new total aircraft weight. When a 204-pound passenger moves from a rear position (e.g., arm 73 inches) to a front position (e.g., arm 37 inches), they shift forward by 36 inches. With the new aircraft weight (2690 - 180 = 2510 pounds), the CG shift is (204 lbs * 36 inches) / 2510 lbs, which equals approximately 2.93 inches forward. The CG is always affected by weight shifts, making other options incorrect.

Question 4

Which action can adjust the airplane's weight to maximum gross weight and the CG within limits for takeoff?  Front seat occupants.......................425 lb Rear seat occupants........................300 lb Fuel, main tanks............................44 gal

Accepted Answer

Drain 9 gallons of fuel.

Answer

To adjust the aircraft's weight and CG for takeoff, one must first calculate the current total weight and moment with the given loading. Then, compare these values to the aircraft's allowable weight and balance envelope. Draining 9 gallons of fuel (approximately 54 pounds at 6 lbs/gallon) would reduce both the total weight and the total moment by a specific amount. This calculated reduction would bring both the aircraft's total weight and its center of gravity within the permissible limits for takeoff, as determined by the aircraft's weight and balance chart.

Question 5

(Refer to Figures 32 and 33.) What effect does a 35-gallon fuel burn (main tanks) have on the weight and balance if the airplane weighed 2,890 pounds and the MOM\/100 was 2,452 at takeoff?

Accepted Answer

Weight is reduced by 210 pounds and the CG is aft of limits.

Answer

Burning 35 gallons of aviation fuel (at 6 lbs/gallon) reduces the aircraft's weight by 210 pounds (35 x 6). Since fuel tanks are typically located forward of the aircraft's overall center of gravity, the removal of this weight causes the center of gravity to shift aft. Comparing the new CG to the aircraft's weight and balance envelope (from Figures 32 and 33) would confirm that this aft shift places the CG beyond the allowable limits.

FAA Practice Test

FAA Practice Test

FAA Weight and Balance Test 2