Test on Aircraft Weight and Balance Fundamentals

Question 1: The different categories under which an aircraft can be licensed always have the same maximum gross weights and center of gravity ranges.

A. Ano

B. Ne

Explanation: The different categories under which an aircraft can be licensed have different maximum gross weights and different center of gravity ranges.

Question 2: Residual fuel is not considered part of the aircraft's empty weight.

A. Ano

B. Ne

Explanation: Residual fuel, also known as undrainable or unusable fuel, is part of the aircraft's empty weight as it remains in the tanks, lines, and engine after draining.

Question 3: According to manufacturers, what is the primary benefit when an aircraft's empty weight CG falls within its specified empty weight CG range?

A. It makes the aircraft suitable for immediate commercial operation.

B. It eliminates the need for a forward or aft weight and balance check if standard loading and seating arrangements are used.

C. It signifies that the aircraft can be operated with minimal fuel.

D. It ensures the aircraft's center of gravity will always be within limits regardless of load.

Explanation: When the empty weight CG falls within the empty weight CG range, it is unnecessary to perform a forward or aft weight and balance check if standard loading and seating arrangements are used.

Question 4: According to the study materials, how is 'minimum fuel' defined for weight and balance computations?

A. The maximum amount of fuel allowed for normal operation.

B. No more fuel than the quantity necessary for 30 minutes of operation at rated maximum continuous power.

C. The fuel remaining in the tanks, lines, and engine after draining.

D. The total fuel capacity minus the residual fuel.

Explanation: The study materials define 'minimum fuel' as 'No more fuel than the quantity necessary for 30 minutes of operation at rated maximum continuous power'.

Question 5: Sufficient aircraft stability may lead to difficulty in controlling the aircraft.

A. Ano

B. Ne

Explanation: Difficulty in controlling an aircraft results from insufficient stability, not sufficient stability.