What are the flight load factors with flaps down?

What are the flight load factors with flaps down?

• A. +3.5g
• B. +2.5g
• C. +4.0g
• D. +3.0g

Answer: (A)

The key idea is how much structural stress the airframe can accept in flight, expressed as load factor in g. Load factor is the lift required divided by weight, so higher g means more upward force on the wings during maneuvers. With flaps down on a Cessna 152, the published positive limit load factor is +3.5 g. This value reflects the airframe’s structural capability when the wing configuration is extended to help you fly at lower speeds (and for steeper approaches), but it still can’t be exceeded without risking structural damage. The other numbers would represent different limits not published for flap-down operation, or would exceed the airframe’s safe stress range under flap-down conditions.

The key idea is how much structural stress the airframe can accept in flight, expressed as load factor in g. Load factor is the lift required divided by weight, so higher g means more upward force on the wings during maneuvers.

With flaps down on a Cessna 152, the published positive limit load factor is +3.5 g. This value reflects the airframe’s structural capability when the wing configuration is extended to help you fly at lower speeds (and for steeper approaches), but it still can’t be exceeded without risking structural damage. The other numbers would represent different limits not published for flap-down operation, or would exceed the airframe’s safe stress range under flap-down conditions.