In flap-down configuration, what is the maximum positive load factor?

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Multiple Choice

In flap-down configuration, what is the maximum positive load factor?

When flaps are down, the airplane’s structural envelope tightens. The high-lift configuration increases wing loads and puts different stresses on the wing and flap system, so the permitted load factor is reduced to protect the airframe. In flap-down, the allowable positive load factor is limited to +2.0 G, and the corresponding negative limit is effectively 0.0 G, meaning downward-G maneuvers are not allowed with flaps extended. This gives a flap-down envelope of +2.0 / 0.0 G. The other options suggest higher positive limits or nonzero negative limits that aren’t permitted when the flaps are deployed.

When flaps are down, the airplane’s structural envelope tightens. The high-lift configuration increases wing loads and puts different stresses on the wing and flap system, so the permitted load factor is reduced to protect the airframe. In flap-down, the allowable positive load factor is limited to +2.0 G, and the corresponding negative limit is effectively 0.0 G, meaning downward-G maneuvers are not allowed with flaps extended. This gives a flap-down envelope of +2.0 / 0.0 G. The other options suggest higher positive limits or nonzero negative limits that aren’t permitted when the flaps are deployed.

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