AVIA 1113 Stage 1 Exam Flashcards

A. To enable the pilot to make steeper approaches to a landing without increasing the airspeed.

What is one purpose of wing flaps?
A. To enable the pilot to make steeper approaches to a landing without increasing airspeed
B. To relieve the pilot of maintaining continuous pressure on the controls
C. To decrease wing area to vary the lift

C. Increase the angle of descent without increasing the airspeed

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

A. To control yaw

What is the purpose of a rudder on an airplane?

A. To control yaw

B. To control overbanking tendency

C. To control roll

A. Flaps

Which is not a primary flight control surface?

A. Flaps

B. Stabilator

C. Ailerons

B. Lateral

The elevator controls movement around which axis?

A. Longitudinal

B. Lateral

C. Vertical

A. The effectiveness of each control surface increases with speed because there is more airflow over them

Which statement is true concerning primary flight controls?

A. The effectiveness of each control surface increases with speed because there is more airflow over them

B. Only when all three primary flight controls move in sequence do the airflow and pressure distribution change over and around the airfoil

C. Primary flight controls include ailerons, rudder, elevator, and trim systems

B. Flaps allow an increase in the angle of descent without increasing airspeed

Which of the following is true concerning flaps?

A. Flaps are attached to the leading edge of the wing and are used to increase wing lift

B. Flaps allow an increase in the angle of descent without increasing airspeed

C. Flaps are high drag devices deployed from the wings to reduce lift

A. Spoilers

Which device is a secondary flight control?

A. Spoilers

B. Ailerons

C. Stabilators

A. They relieve the pilot of the need to maintain constant pressure on the flight controls

Trim systems are designed to do what?

A. They relieve the pilot of the need to maintain constant pressure on the flight controls

B. They are used during approach and landing to increase wing lift

C. They move in the opposite direction from one another to control roll

A. lift, weight, thrust, and drag

The four forces acting on an airplane in flight are:

A. lift, weight, thrust, and drag

B. lift, weight, gravity, and thrust

C. lift, gravity, power, and friction

A. During unaccelerated level flight

When are the four forces that act on an airplane in equilibrium?

A. During unaccelerated level flight

B. When the aircraft is accelerating

C. When the aircraft is at rest on the ground

A. Lift equals weight and thrust equals drag

What is the relationship of lift, drag, thrust, and weight when the airplane is in straight-and-level flight?

A. Lift equals weight and thrust equals drag

B. Lift, drag, and weight equal thrust

C. Lift and weight equal thrust and drag

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

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 airfoil deflects air downward

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

B. Attack

The acute angle A is the angle of:

A. Incidence

B. Attack

C. Dihedral

A. chord line of the wing and the relative wind

The term ‘angle of attack’ is defined as the angle between the:

A. chord line of the wing and the relative wind

B. airplane’s longitudinal axis and that of the air striking the airfoil

C. airplane’s center line and the relative wind

B. attack

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

C. Remain the same regardless of gross weight

The angle of attack at which an airplane stalls will:

A. increase if the CG is moved forward

B. change with an increase in gross weight

C. remain the same regardless of gross weight

C. remain the same regardless of altitude

As altitude increases, the indicated airspeed at which a given airplane stalls in a particular configuration will:

A. decrease as the true airspeed decreases

B. decrease as the true airspeed increases

C. remain the same regardless of altitude

C. Stalled

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

A. Both wings are 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

A. The result of the interference of the surface of the Earth with the airflow patterns about an airplane

What is ground effect?

A. The result of the interference of the surface of the Earth with the airflow patterns about an airplane

B. The result of an alteration in airflow patterns increasing induced drag about the wings of an airplane

C. The result of the disruption of the airflow patterns about the wings of an airplane to the point where the wings will no longer support the airplane in flight

A. less than the length of the wingspan above the surface.

Floating caused by the phenomenon of ground effect will be most realized during an approach to land when at:

A. less than the length of the wingspan above the surface.

b. twice the length of the wingspan above the surface

C. a higher-than-normal angle of attack

B. Induced drag decreases; therefore any excess speed at the point of flare may cause considerable floating

What must a pilot be aware of as a result of ground effect?

A. Wingtip vortices increase creating wake turbulence problems for arriving and departing aircraft

B. Induced drag decreases; therefore any excess speed at the point of flare may cause considerable floating

C. A full stall landing will require less up elevator deflection than would a full stall when done free of ground effect

B. experience an increase in induced drag and a decrease in performance

An aircraft leaving ground effect during takeoff will:

A. experience a reduction in ground friction and require a slight power reduction

B. experience an increase in induced drag and a decrease in performance

C. require a lower angle of attack to maintain the same lift coefficient

B. becoming airborne before reaching recommended takeoff speed

Ground effect is most likely to result in which problem?

A. settling to the surface abruptly during landing

B. becoming airborne before reaching recommended takeoff speed

C. inability to get airborne even though airspeed is sufficient for normal takeoff needs

A. The horizontal component of lift

What force makes an airplane turn?

A. The horizontal component of lift

B. The vertical component of lift

C. Centrifugal force

A. The location of the CG with respect to the center of lift

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

B. require less effort to control

An airplane said to be inherently stable will:

A. be difficult to stall

B. require less effort to control

C. not spin

C. aerodynamic balance and controllability

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

B. difficulty in recovering from a stalled condition

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. The downwash on the elevators from the propeller slipstream is reduced and elevator effectiveness is reduced

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

A. Both aircraft groundspeed and angle of attack will increase

What is the effect of advancing the throttle in flight?

A. Both aircraft groundspeed and angle of attack will increase

B. Airspeed will remain relatively constant but the aircraft will climb

C. The aircraft will accelerate, which will cause a turn to the right

A. less stable at all speeds

Loading an airplane to the most aft CG will cause an 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 slow speeds

C. increase the likelihood of inadvertent overstress

An airplane loaded with the CG rear of the aft CG limit could:

A. make it easier to recover from stalls and spins

B. make it more difficult to flare for landing

C. increase the likelihood of inadvertent overstress

A. Low airspeed, high power, high angle of attack

In what flight condition are torque effects more pronounced in a single-engine airplane?

A. Low airspeed, high power, high angle of attack

B. Low airspeed, low power, low angle of attack

C. High airspeed, high power, high angle of attack

B. propeller blade descending on the right, producing more thrust than the ascending blade on the left

The left turning tendency of an airplane caused by P-factor is the result of:

A. clockwise rotation of the engine and the propeller turning the airplane counterclockwise

B. propeller blade descending on the right, producing more thrust than the ascending blade on the left

C. gyroscopic forces applied to the rotating propeller blades acting 90 degrees in advance of the point the force was applied

B. When at high angles of attack

When does P-factor cause the airplane to yaw to the left?

A. When at low angles of attack

B. When at high angles of attack

C. When at high airspeeds

C. Gyroscopic precession in a tricycle gear airplane

Which of the following is not a left-turning tendency at high power during takeoff?

A. Spiraling slipstream

B. Gyroscopic precession in a conventional gear ‘tail dragger’

C. Gyroscopic precession in a tricycle gear airplane

C. 3960 pounds

If an airplane weighs 3300 pounds, what approximate weight would the airplane structure be required to support during a 30° banked turn while maintaining altitude?

A. 1200 pounds

B. 3100 pounds

C. 3960 pounds

C. 4600 pounds

If an airplane weighs 2300 pounds, what approximate weight would the airplane structure be required to support during a 60° banked turn while maintaining altitude?

A. 2300 pounds

B. 3400 pounds

C. 4600 pounds

B. 6750 pounds

If an airplane weighs 4500 pounds, what approximate weight would the airplane structure be required to support during a 45° banked turn while maintaining altitude?

A. 4500 pounds

B. 6750 pounds

C. 7200 pounds

B. Turns

Which basic flight maneuver increases the load factor on an airplane as compared to straight-and-level flight?

A. Climbs

B. Turns

C. Stalls

B. speed of the airplane

The amount of excess load that can be imposed on the wing of an airplane depends upon the:

A. position of the CG

B. speed of the airplane

C. abruptness at which the load is applied

A. stall at a higher airspeed

During an approach to stall, an increased load factor will cause the aircraft to:

A. stall at a higher airspeed

B. have a tendency to spin

C. be more difficult to control

C. Vne

Structural damage or failure is more likely to occur in smooth air at speeds above:

A. Vno

B. Va

C. Vne

C. maximum sustainable load to the gross weight of the airplane

Limit load factor is the ratio of:

A. angle of attack to stall speed

B. angle of attack to power-on configuration specific stall speed

C. maximum sustainable load to the gross weight of the airplane

A. stall

A positive load factor of 2 at 80mph would cause the airplane to:

A. stall

B. break apart

C. operate normally, as it is within the normal operating range

C. 2.0

What load factor would be created if positive 15 feet per second gusts were encountered at 120mph?

A. 2.8

B. 3.0

C. 2.0

B. normal stall speed

The airspeed indicated by points A and J is:

A. maximum structural cruising speed

B. normal stall speed

C. maneuvering speed

C. an aircraft is accelerated while on an east or west heading

In the Northern Hemisphere, a magnetic compass will normally indicate a turn toward the north if:

A. an aircraft is decelerated while on an east or west heading

B. a left turn is entered from a west heading

C. an aircraft is accelerated while on an east or west heading

C. magnetic fields within the aircraft distorting the lines of magnetic force

Deviation in a magnetic compass is caused by the:
A. presence of flaws in the permanent magnets of the compass

B. difference in the location between true north and magnetic north

C. magnetic fields within the aircraft distorting the lines of magnetic force

A. Only in straight-and-level unaccelerated flight

During flight, when are the indications of a magnetic compass accurate?

A. Only in straight-and-level unaccelerated flight

B. As long as the airspeed is constant
C. During turns if the bank does not exceed 18°

B. certain metals and electrical systems within the aircraft

Deviation error of the magnetic compass is caused by:

A. a northerly turning error

B. certain metals and electrical systems within the aircraft

C. the difference in location of true north and magnetic north

B. correctly when on a north or south heading

In the Northern Hemisphere, if an aircraft is accelerated or decelerated, the magnetic compass will normally indicate:

A. a turn momentarily

B. correctly when on a north or south heading

C. a turn toward the south

B. a right turn is entered from a north heading

In the Northern Hemisphere, a magnetic compass will normally indicate initially a turn toward the west if:

A. a left turn is entered from a north heading

B. a right turn is entered from a north heading

C. an aircraft is accelerated while on a north heading