What force provides the forward motion necessary to move a glider through the air?

A. Lift.

B. Centripetal force.

C. Gravity.

(Refer to figure 55 .) What approximate lift/drag ratio will the glider attain at 68 MPH in still air?

A. 10.5:1.

B. 21.7:1.

C. 28.5:1.

What effect would gusts and turbulence have on the load factor of a glider with changes in airspeed?

A. Load factor decreases as airspeed increases.

B. Load factor increases as airspeed increases.

C. Load factor increases as airspeed decreases.

(Refer to figure 54 .) Calculate the weight and balance of the glider, and determine if the CG is within limits. Pilot (fwd seat) 160 lb Passenger (aft seat) 185 lb

A. CG 71.65 inches aft of datum - out of limits forward.

B. CG 79.67 inches aft of datum - within limits.

C. CG 83.43 inches aft of datum - within limits.

A pilot plans to fly solo in the front seat of a two-place glider which displays the following placards on the instrument panel: MINIMUM PILOT WEIGHT: 135 LB MAXIMUM PILOT WEIGHT: 220 LB NOTE: Seat ballast should be used as necessary. The recommended towing speed for all tows is 55 - 65 knots. What action should be taken if the pilot's weight is 125 pounds?

A. Add 10 pounds of seat ballast to the rear seat.

B. Add 10 pounds of seat ballast.

C. Add 45 pounds of seat ballast to obtain the average pilot weight of 170 pounds.

A pilot plans to fly solo in the front seat of a two-place glider which displays the following placards on the instrument panel: MINIMUM PILOT WEIGHT: 135 LB MAXIMUM PILOT WEIGHT: 220 LB NOTE: Seat ballast should be used as necessary. The recommended towing speed for all tows is 55 - 65 knots. What action should be taken if the pilot's weight is 115 pounds?

A. Add 20 pounds of seat ballast to the rear seat.

B. Add 55 pounds of seat ballast to obtain the average pilot weight of 170 pounds.

C. Add 20 pounds of seat ballast.

(Refer to figure 1 .) The acute angle A is the angle of

A. incidence.

B. attack.

C. dihedral.

The term 'angle of attack' is defined as the angle

A. between the wing chord line and the relative wind.

B. between the airplane's climb angle and the horizon.

C. formed by the longitudinal axis of the airplane and the chord line of the wing.

One of the main functions of flaps during approach and landing is to

A. decrease the angle of descent without increasing the airspeed.

B. permit a touchdown at a higher indicated airspeed.

C. increase the angle of descent without increasing the airspeed.

In what flight condition must an aircraft be placed in order to spin?

A. Partially stalled with one wing low.

B. In a steep diving spiral.

C. Stalled.

During a spin to the left, which wing(s) is/are stalled?

A. Both wings are stalled.

B. Neither wing is stalled.

C. Only the left wing is stalled.

(Refer to figure 55 .) How many feet will the glider sink in 1 statute mile at 53 MPH in still air?

A. 144 feet.

B. 171 feet.

C. 211 feet.

(Refer to figure 55 .) At what speed will the glider attain a sink rate of 5 feet per second in still air?

A. 75 MPH.

B. 79 MPH.

C. 84 MPH.

(Refer to figure 55 .) At what speed will the glider gain the most distance while descending 1,000 feet in still air?

A. 44 MPH.

B. 53 MPH.

C. 83 MPH.

(Refer to figure 55 .) How many feet will the glider descend at minimum sink speed for 1 statute mile in still air?

A. 132 feet.

B. 170 feet.

C. 180 feet.

The purpose of wing spoilers is to decrease

A. the drag.

B. landing speed.

C. the lift of the wing.

If the glider`s radius of turn is 175 feet at 40 MPH, what would the radius of turn be if the TAS is increased to 80 MPH while maintaining a constant angle of bank?

A. 350 feet.

B. 525 feet.

C. 700 feet.

The maximum airspeed at which abrupt and full deflection of the controls would not cause structural damage to a glider is called the

A. speed-to-fly.

B. maneuvering speed.

C. never-exceed speed.

Minimum sink speed is the airspeed which results in the

A. least loss of altitude in a given time.

B. least loss of altitude in a given distance.

C. shallowest glide angle in any convective situation.

In regard to the location of the glider's CG and its effect on glider spin characteristics, which is true? If the CG is too far

A. aft, a flat spin may develop.

B. forward, spin entry will be impossible.

C. aft, spins will degenerate into CG high-speed spirals.

The reason for retaining water ballast while thermals are strong, is to

A. decrease forward speed.

B. decrease cruise performance.

C. increase cruise performance.

Which procedure can be used to increase forward speed on a cross-country flight?

A. Maintain minimum sink speed plus or minus one-half the estimated wind velocity.

B. Use water ballast while thermals are strong and dump the water when thermals are weak.

C. Use water ballast while thermals are weak and dump the water when thermals are strong.

If all index units are positive when computing weight and balance, the location of the datum would be at the

A. centerline of the main wheels.

B. nose, or out in front of the airplane.

C. centerline of the nose or tailwheel, depending on the type of airplane.

The CG of an aircraft may be determined by

A. dividing total arms by total moments.

B. dividing total moments by total weight.

C. multiplying total weight by total moments.

GIVEN: Weight A. 155 pounds at 45 inches aft of datum Weight B. 165 pounds at 145 inches aft of datum Weight C. 95 pounds at 185 inches aft of datum Based on this information, where would the CG be located aft of datum?

A. 86.0 inches.

B. 116.8 inches.

C. 125.0 inches.

The CG of an aircraft can be determined by which of the following methods?

A. Dividing total arms by total moments.

B. Multiplying total arms by total weight.

C. Dividing total moments by total weight.

(Refer to figure 36 .)

GIVEN:	WEIGHT	ARM	MOMENT
Empty weight	610	96.47	?
Pilot (fwd seat)	150	?	?
Passenger (aft seat)	180	?	?
Radio and batteries	10	23.20	?
TOTALS	?	?	?

The CG is located at station

A. 33.20.

B. 59.55.

C. 83.26.

With respect to using the weight information given in a typical aircraft owner's manual for computing gross weight, it is important to know that if items have been installed in the aircraft in addition to the original equipment, the

A. allowable useful load is decreased.

B. allowable useful load remains unchanged.

C. maximum allowable gross weight is increased.

Lift on a wing is most properly defined as the

A. force acting perpendicular to the relative wind.

B. differential pressure acting perpendicular to the chord of the wing.

C. reduced pressure resulting from a laminar flow over the upper camber of an airfoil, which acts perpendicular to the mean camber.

Load factor is the lift generated by the wings of an aircraft at any given time

A. divided by the total weight of the aircraft.

B. multiplied by the total weight of the aircraft.

C. divided by the basic empty weight of the aircraft.

While holding the angle of bank constant in a level turn, if the rate of turn is varied the load factor would

A. remain constant regardless of air density and the resultant lift vector.

B. vary depending upon speed and air density provided the resultant lift vector varies proportionately.

C. vary depending upon the resultant lift vector.

When a slight upward or negative flap deflection is used, the result is

A. increased drag.

B. decreased drag.

C. decreased lift.

The best lift/drag ratio of a glider occurs when parasite drag is

A. equal to total drag.

B. equal to induced drag.

C. less than induced drag.

Which subsonic planform provides the best lift coefficient?

A. Tapered wing.

B. Elliptical wing.

C. Rectangular wing.

Aspect ratio of a wing is defined as the ratio of the

A. wingspan to the wing root.

B. wingspan to the mean chord.

C. square of the chord to the wingspan.

At a constant velocity in airflow, a high aspect ratio wing will have (in comparison with a low aspect ratio wing)

A. increased drag, especially at a low angle of attack.

B. decreased drag, especially at a high angle of attack.

C. increased drag, especially at a high angle of attack.

(Refer to figure 21 .) Which aircraft has the highest aspect ratio?

A. 2.

B. 3.

C. 4.

The reason for retaining water ballast while thermals are strong and dumping the water when thermals weaken is to

A. decrease forward speed.

B. increase forward speed.

C. decrease the rate of descent.

Which is true about the effect on a glider's performance by the addition of ballast or weight?

A. The glide ratio at a given airspeed will increase.

B. A higher airspeed is required to obtain the same glide ratio as when lightly loaded.

C. The heavier the glider is loaded, the less the glide ratio will be at all airspeeds.

Which characteristic of a spin is not a characteristic of a steep spiral?

A. Stalled wing.

B. High rate of rotation.

C. Rapid loss of altitude.

What would be the new CG location if 135 pounds of weight were added at Station 109.0? Total weight 2,340 lb CG location Station 103.0

A. Station 103.3.

B. Station 104.2.

C. Station 109.3.

The angle between the chord line of an airfoil and the relative wind is known as the angle of

A. lift.

B. attack.

C. incidence.

The angle of attack of a wing directly controls the

A. angle of incidence of the wing.

B. amount of airflow above and below the wing.

C. distribution of positive and negative pressure acting on the wing.

Which action will result in a stall?

A. Flying at too low an airspeed.

B. Raising the aircraft's nose too high.

C. Exceeding the critical angle of attack.

The resistance, or skin friction, due to the viscosity of the air as it passes along the surface of a wing is called

A. form drag.

B. profile drag.

C. parasite drag.

Changes in the center of pressure of a wing affect the aircraft's

A. lift/drag ratio.

B. lifting capacity.

C. aerodynamic balance and controllability.

(Refer to figure 20 .) At the airspeed represented by point A, in steady flight, the aircraft will

A. have its maximum lift/drag ratio.

B. have its minimum lift/drag ratio.

C. be developing its maximum coefficient of lift.

As airspeed increases in level flight, total drag of an aircraft becomes greater than the total drag produced at the maximum lift/drag speed because of the

A. increase in induced drag.

B. decrease in induced drag.

C. increase in parasite drag.

Why does increasing speed also increase lift?

A. The increased velocity of the relative wind overcomes the increased drag.

B. The increased impact of the relative wind on an airfoil's lower surface creates a greater amount of air being deflected downward.

C. The increased speed of the air passing over an airfoil's upper surface increases the pressure, thus creating a greater pressure differential between the upper and lower surface.

Lift produced by an airfoil is the net force developed perpendicular to the

A. chord.

B. relative wind.

C. longitudinal axis of the aircraft.

Which statement relates to Bernoulli's principle?

A. For every action there is an equal and opposite reaction.

B. An additional upward force is generated as the lower surface of the wing deflects air downward.

C. Air traveling faster over the curved upper surface of an airfoil causes lower pressure on the top surface.

An aircraft wing is designed to produce lift resulting from

A. negative air pressure below the wing's surface and positive air pressure above the wing's surface.

B. positive air pressure below the wing's surface and negative air pressure above the wing's surface.

C. a larger center of pressure above the wing's surface and a lower center of pressure below the wing's surface.

The tendency of an aircraft to develop forces that further remove the aircraft from its original position, when disturbed from a condition of steady flight, is known as

A. static instability.

B. dynamic instability.

C. positive static stability.

If the aircraft's nose initially tends to return to its original position after the elevator control is pressed forward and released, the aircraft displays

A. positive static stability.

B. neutral dynamic stability.

C. negative dynamic stability.

The capability of an aircraft to respond to a pilot's inputs, especially with regard to flightpath and attitude, is

A. response.

B. controllability.

C. maneuverability.

The three axes of an aircraft intersect at the

A. center of gravity.

B. center of pressure.

C. midpoint of the mean chord.

If the aircraft's nose remains in the new position after the elevator control is pressed forward and released, the aircraft displays

A. neutral static stability.

B. negative static stability.

C. positive static stability.

The tendency of an aircraft to develop forces which restore it to its original condition, when disturbed from a condition of steady flight, is known as

A. stability.

B. controllability.

C. maneuverability.

The purpose of aircraft wing dihedral angle is to

A. increase lateral stability.

B. increase longitudinal stability.

C. increase lift coefficient of the wing.

(Refer to figure 18 .) A 70 percent increase in stalling speed would imply a bank angle of

A. 67°.

B. 70°.

C. 83°.

If severe turbulence is encountered, the aircraft's airspeed should be reduced to

A. maneuvering speed.

B. normal structural cruising speed.

C. the minimum steady flight speed in the landing configuration.

Maximum gliding distance of an aircraft is obtained when

A. parasite drag is the least.

B. induced drag and parasite drag are equal.

C. induced drag equals the coefficient of lift.

(Refer to figure 23 .) Which is a slotted flap?

A. 1.

B. 3.

C. 4.

What is the effect of center of gravity on the spin characteristics of an aircraft?

A. A flat spin may develop if the CG is too far aft.

B. If the CG is too far forward, spin entry will be difficult.

C. If the CG is too far aft, spins can become high-speed spirals.

If the CG of an aircraft is moved from the aft limit to beyond the forward limit, how will it affect the cruising and stalling speed?

A. Increase both the cruising speed and stalling speed.

B. Decrease both the cruising speed and stalling speed.

C. Decrease the cruising speed and increase the stalling speed.

An aircraft is loaded with the CG aft of the aft limit. What effect will this have on controllability?

A. Stall and spin recovery may be difficult or impossible.

B. A stall will occur at a lower airspeed, but recovery will be easier because of reduced wing loading.

C. A stall will occur at a higher indicated airspeed due to the greater downloading on the elevator.

As the CG location is changed, recovery from a stall becomes progressively

A. less difficult as the CG moves rearward.

B. more difficult as the CG moves rearward.

C. more difficult as the CG moves either forward or rearward.

It is possible to fly an aircraft just clear of the ground at a slightly slower airspeed than that required to sustain level flight at higher altitudes. This is the result of

A. interference of the ground surface with the airflow patterns about the aircraft in flight.

B. a cushioning effect of the air as it is trapped between the ground and the descending aircraft.

C. ground interference with the static pressure system which produces false indications on the airspeed indicator.

What will cause the nose of an aircraft to move in the direction of the turn before the bank starts in a turn entry?

A. Rudder being applied too late.

B. Rudder being applied too soon.

C. Failure to apply back elevator pressure.

When rolling out of a steep-banked turn, what causes the lowered aileron to create more drag than when rolling into the turn?

A. The wing's angle of attack is greater as the rollout is started.

B. The wing being raised is traveling faster through the air than the wing being lowered.

C. The wing being lowered is traveling faster through the air and producing more lift than the wing being raised.

(Refer to figure 22 .) While rolling into a right turn, if the inclinometer appears as illustrated in A, the HCL and CF vectors would be acting on the aircraft as illustrated in

A. 2, and more left pedal pressure is needed to center the ball.

B. 2, and more right pedal pressure is needed to center the ball.

C. 4, and more right pedal pressure is needed to center the ball.

Which would likely result in a slipping turn?

A. Not holding bottom rudder in a turn.

B. Increasing the rate of turn without using rudder.

C. Increasing the rate of turn without increasing bank.

Two distinct flight situations should be covered when teaching slow flight. These are the establishment and maintenance of

A. airspeeds appropriate for landing approaches, and flight at reduced airspeeds.

B. an airspeed which gives a stall warning indication, and an airspeed at which complete recovery can be made from stalls.

C. an airspeed at which the airplane is operating on the back side of the power curve, and an airspeed at which the elevator control can be held full-back with no further loss of control.

Which statement is true relating to the factors which produce stalls?

A. The critical angle of attack is a function of the degree of bank.

B. The stalling angle of attack depends upon the speed of the airflow over the wings.

C. The stalling angle of attack is independent of the speed of airflow over the wings.

If an accelerated stall occurs in a steep turn, how will the aircraft respond?

A. The inside wing stalls first because it is flying at a higher angle of attack.

B. The outside wing stalls first because it is flying at a higher angle of attack.

C. In a slip, the high wing stalls first; in a skid, the low wing stalls first; in coordinated flight, both wings stall at the same time.

The objective of a cross-control stall demonstration is to

A. emphasize the hazard of an excessive slip during a landing approach.

B. teach the proper recovery technique should this type of stall occur during final approach.

C. show the effect of improper control technique and emphasize the importance of coordinated control when making turns.

Which statement is true concerning the aerodynamic conditions which occur during a spin entry?

A. After a full stall, both wings remain in a stalled condition throughout the rotation.

B. After a partial stall, the wing that drops remains in a stalled condition while the rising wing regains and continues to produce lift, causing the rotation.

C. After a full stall, the wing that drops continues in a stalled condition while the rising wing regains and continues to produce some lift, causing the rotation.

Adverse yaw during a turn entry is caused by

A. increased induced drag on the lowered wing and decreased induced drag on the raised wing.

B. decreased induced drag on the lowered wing and increased induced drag on the raised wing.

C. increased parasite drag on the raised wing and decreased parasite drag on the lowered wing.

What is the maximum weight that could be added at Station 130.0 without exceeding the aft CG limit? Total weight 2,900 lb CG location Station 115.0 Aft CG limit Station 116.0

A. 14 pounds.

B. 140 pounds.

C. 207 pounds.

(Refer to figure 34 .) How should the 500-pound weight be shifted to balance the plank on the fulcrum?

A. 1 inch to the left.

B. 1 inch to the right.

C. 4.5 inches to the right.

(Refer to figure 35 .) If 50 pounds of weight is located at point X and 100 pounds at point Z, how much weight must be located at point Y to balance the plank?

A. 30 pounds.

B. 50 pounds.

C. 300 pounds.

(Refer to figure 33 .) How should the 200-pound weight be shifted to balance the plank on the fulcrum?

A. 2.5 inches to the left.

B. 2 inches to the right.

C. 2 inches to the left.

How does the wake turbulence vortex circulate around each wingtip?

A. Inward, upward, and around each tip.

B. Inward, upward, and counterclockwise.

C. Outward, upward, and around each tip.