What is the maneuvering load acceleration limit in configurations with slats and/or flaps extended?

What is the maneuvering load acceleration limit in configurations with slats and/or flaps extended?

• A. -1 g to +2.5 g
• B. 0 g to +2 g
• C. +1 g to +3 g
• D. -0.5 g to +1.5 g

Answer: (B)

When slats or flaps are extended, the aircraft’s wings and the flap/slat mechanisms carry more complex stresses during maneuvers, and the margin before structural limits is reduced. Because of this, the permissible load factors are tightened to a safe envelope. In this configuration, you’re allowed to experience zero or positive loading during maneuvers, with a maximum of about +2 g. Negative g is not permitted because applying downward loading while the devices are extended can push the structure toward limits or cause undesirable interactions with the extended surfaces and mechanisms. So the maneuvering load acceleration limit is 0 g to +2 g.

When slats or flaps are extended, the aircraft’s wings and the flap/slat mechanisms carry more complex stresses during maneuvers, and the margin before structural limits is reduced. Because of this, the permissible load factors are tightened to a safe envelope. In this configuration, you’re allowed to experience zero or positive loading during maneuvers, with a maximum of about +2 g. Negative g is not permitted because applying downward loading while the devices are extended can push the structure toward limits or cause undesirable interactions with the extended surfaces and mechanisms. So the maneuvering load acceleration limit is 0 g to +2 g.