With flaps at 0 degrees, what are the maneuvering load factors?

With flaps at 0 degrees, what are the maneuvering load factors?

• A. -0.5 to 2.0 G
• B. -2.0 to 2.5 G
• C. -1.0 to 3.0 G
• D. -1 to 3.2 G

Answer: (D)

The maneuvering load factors are the structural limits the airplane is designed to sustain during maneuvers in the current configuration. When the flaps are at 0 degrees (clean configuration), the aircraft is built to handle up to a positive load of 3.2 G and up to a negative load of 1.0 G. So the safe maneuvering envelope is from -1.0 G to +3.2 G. These limits come from the aircraft’s structural design to protect against excessive forces during pullups (positive G) and pushovers or negative-G situations (negative G). The positive limit is higher because the wing and airframe are generally stressed more in positive-G maneuvers than in negative-G conditions. The other ranges don’t match the design limits: they either cap the positive side too low or permit too much negative loading.

The maneuvering load factors are the structural limits the airplane is designed to sustain during maneuvers in the current configuration. When the flaps are at 0 degrees (clean configuration), the aircraft is built to handle up to a positive load of 3.2 G and up to a negative load of 1.0 G. So the safe maneuvering envelope is from -1.0 G to +3.2 G.

These limits come from the aircraft’s structural design to protect against excessive forces during pullups (positive G) and pushovers or negative-G situations (negative G). The positive limit is higher because the wing and airframe are generally stressed more in positive-G maneuvers than in negative-G conditions.

The other ranges don’t match the design limits: they either cap the positive side too low or permit too much negative loading.