1	Load factor is the lift generated by the wings of an aircraft at any given time divided by the total weight of the aircraft. divided by the basic empty weight of the aircraft. multiplied by the total weight of the aircraft.
2	Baggage weighing 90 pounds is placed in a normal category airplane's baggage compartment which is placarded at 100 pounds. If this airplane is subjected to a positive load factor of 3.5 G's, the total load of the baggage would be 350 pounds and would not be excessive. 315 pounds and would be excessive. 315 pounds and would not be excessive.
3	While holding the angle of bank constant in a level turn, if the rate of turn is varied the load factor would vary depending upon the resultant lift vector. vary depending upon speed and air density provided the resultant lift vector varies proportionately. remain constant regardless of air density and the resultant lift vector.
4	During the transition from straight-and-level flight to a climb, the angle of attack is increased and lift is momentarily increased. remains the same. is momentarily decreased.
5	Lift on a wing is most properly defined as the differential pressure acting perpendicular to the chord of the wing. force acting perpendicular to the relative wind. reduced pressure resulting from a laminar flow over the upper camber of an airfoil, which acts perpendicular to the mean camber.
6	As airspeed decreases in level flight below that speed for maximum lift/drag ratio, total drag of an airplane increases because of increased induced drag. increases because of increased parasite drag. decreases because of lower parasite drag.
7	What performance is characteristic of flight at maximum lift/drag ratio in a propeller-driven airplane? Maximum range and maximum distance glide. coefficient of lift and minimum coefficient of drag. gain in altitude over a given distance.
8	Recovery from a stall in any airplane becomes more difficult when its elevator trim is adjusted nosedown. center of gravity moves forward. center of gravity moves aft.
9	The need to slow an aircraft below VA is brought about by the following weather phenomenon: High density altitude which increases the indicated stall speed. Turbulence which causes an increase in stall speed. Turbulence which causes a decrease in stall speed.
10	(Refer to figure 35.) GIVEN: Temperature 85 °F Pressure altitude 6,000 ft Weight 2,800 lb Headwind 14 kts Determine the approximate ground roll. 742 feet. 1,280 feet. 1,480 feet.

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