Ch 4 Section B: Stability

In what flight condition must an aircraft be placed in order to spin? A - Both wings are stalled. B - Neither wing is stalled. C - Only the left wing is stalled.

A

Loading an airplane to the most aft CG will cause the airplane to be A - less stable at all speeds. B - less stable at slow speeds, but more stable at high speeds. C - less stable at high speeds, but more stable at low speeds.

A

What determines the longitudinal stability of an airplane? A - The location of the CG with respect to the center of lift. B - The effectiveness of the horizontal stabilizer, rudder, and rudder trim tab. C - The relationship of thrust and lift to weight and drag.

A

An airplane has been loaded in such a manner that the CG is located aft of the aft CG limit. One undesirable flight characteristic a pilot might experience with this airplane would be A - a longer takeoff run. B - difficulty in recovering from a stalled condition. C - stalling at higher-than-normal airspeed.

B

An airplane said to be inherently stable will A - be difficult to stall. B - require less effort to control. C - not spin.

B

What causes an airplane (except a T-tail) to pitch nosedown when power is reduced and controls are not adjusted? A - The CG shifts forward when thrust and drag are reduced. B - The downwash on the elevators from the propeller slipstream is reduced and elevator effectiveness is reduced. C - When thrust is reduced to less than weight, lift is also reduced and the wings can no longer support the weight.

B

In what flight condition must an aircraft be placed in order to spin? A - Partially stalled with one wing low. B - In a deep diving spiral. C - Stalled.

C