ATPL - PRINCIPLES OF FLIGHT EXAM
GRADED A+
1. Which statement is true regarding the opposing forces acting on an aeroplane in
steady-state level flight?
a. Thrust is greater than drag and weight and lift are equal
b. These forces are equal
c. Thrust is greater than drag and lift is greater than weight
d. Thrust is slightly greater than lift, but the drag and weight are equal - Answer- b.
These forces are equal
2. The stalling speed of an aeroplane is most affected by:
a. Changes in air density
b. Variations in aeroplane loading
c. Variations in flight altitude
d. Changes in pitch attitude - Answer- b. Variations in aeroplane loading
3. To ensure some degree of longitudinal stability in flight, the position of the CG:
a. Must always coincide with the AC
b. Must be forward of the Neutral Point
c. Must be aft of the Neutral Point
d. Must not be forward of the aft CG limit - Answer- b. Must be forward of the Neutral
Point
4. The purpose of a trim tab is:
a. To assist the pilot in initiating movement of the controls
b. To zero the load on the pilot controls in the flight attitude required
c. To provide feel to the controls at high speed
d. To increase the effectiveness of the controls - Answer- b. To zero the load on the
pilot controls in the flight attitude required
5. What criteria determine which engine is the "critical" engine of a twin-engine
aeroplane?
a. The one with the center of thrust farthest from the centreline of the fuselage
b. The one with the center of thrust closest to the centreline of the fuselage
c. The one designated by the manufacturer which develops most usable thrust
d. The failure of which causes the least yawing moment - Answer- b. The one with the
center of thrust closest to the centreline of the fuselage
, 6. The angle of attack of a fixed pitch propeller:
a. Depends on forward speed only
b. Depends on forward speed and engine rotational speed
c. Depends on engine rotational speed only
d. Is constant for a fixed pitch propeller - Answer- b. Depends on forward speed and
engine rotational speed
7. Which statement is true relative to changing angle of attack?
a. A decrease in angle of attack will increase pressure below the wing and decrease
drag
b. An increase in angle of attack will decrease pressure below the wing and decrease
drag
c. An increase in angle of attack will increase drag
d. An increase in angle of attack will decrease the lift coefficient - Answer- c. An
increase in angle of attack will increase drag
8. If the angle of attack is increased beyond the critical angle of attack, the wing will no
longer produce sufficient lift to support the weight of the aircraft:
a. Unless the airspeed is greater than the normal stall speed
b. Regardless of airspeed or pitch attitude
c. Unless the pitch attitude is on or below the natural horizon
d. In which case, the control column should be pulled-back immediately - Answer- b.
Regardless of airspeed or pitch attitude
9. A stall warning device must be set to operate:
a. At the stalling speed
b. At a speed just below the stalling speed
c. At a speed about 5% to 10% above the stalling speed
d. At a speed about 20% above the stalling speed - Answer- c. At a speed about 5% to
10% above the stalling speed
10. Lowering the flaps during a landing approach:
a. Increases the angle of descent without increasing the airspeed
b. Decreases the angle of descent without increasing power
c. Eliminates floating
d. Permits approaches at a higher indicated airspeed - Answer- a. Increases the angle
of descent without increasing the airspeed
11. A constant rate of climb in an aeroplane is determined by:
a. Wind speed
GRADED A+
1. Which statement is true regarding the opposing forces acting on an aeroplane in
steady-state level flight?
a. Thrust is greater than drag and weight and lift are equal
b. These forces are equal
c. Thrust is greater than drag and lift is greater than weight
d. Thrust is slightly greater than lift, but the drag and weight are equal - Answer- b.
These forces are equal
2. The stalling speed of an aeroplane is most affected by:
a. Changes in air density
b. Variations in aeroplane loading
c. Variations in flight altitude
d. Changes in pitch attitude - Answer- b. Variations in aeroplane loading
3. To ensure some degree of longitudinal stability in flight, the position of the CG:
a. Must always coincide with the AC
b. Must be forward of the Neutral Point
c. Must be aft of the Neutral Point
d. Must not be forward of the aft CG limit - Answer- b. Must be forward of the Neutral
Point
4. The purpose of a trim tab is:
a. To assist the pilot in initiating movement of the controls
b. To zero the load on the pilot controls in the flight attitude required
c. To provide feel to the controls at high speed
d. To increase the effectiveness of the controls - Answer- b. To zero the load on the
pilot controls in the flight attitude required
5. What criteria determine which engine is the "critical" engine of a twin-engine
aeroplane?
a. The one with the center of thrust farthest from the centreline of the fuselage
b. The one with the center of thrust closest to the centreline of the fuselage
c. The one designated by the manufacturer which develops most usable thrust
d. The failure of which causes the least yawing moment - Answer- b. The one with the
center of thrust closest to the centreline of the fuselage
, 6. The angle of attack of a fixed pitch propeller:
a. Depends on forward speed only
b. Depends on forward speed and engine rotational speed
c. Depends on engine rotational speed only
d. Is constant for a fixed pitch propeller - Answer- b. Depends on forward speed and
engine rotational speed
7. Which statement is true relative to changing angle of attack?
a. A decrease in angle of attack will increase pressure below the wing and decrease
drag
b. An increase in angle of attack will decrease pressure below the wing and decrease
drag
c. An increase in angle of attack will increase drag
d. An increase in angle of attack will decrease the lift coefficient - Answer- c. An
increase in angle of attack will increase drag
8. If the angle of attack is increased beyond the critical angle of attack, the wing will no
longer produce sufficient lift to support the weight of the aircraft:
a. Unless the airspeed is greater than the normal stall speed
b. Regardless of airspeed or pitch attitude
c. Unless the pitch attitude is on or below the natural horizon
d. In which case, the control column should be pulled-back immediately - Answer- b.
Regardless of airspeed or pitch attitude
9. A stall warning device must be set to operate:
a. At the stalling speed
b. At a speed just below the stalling speed
c. At a speed about 5% to 10% above the stalling speed
d. At a speed about 20% above the stalling speed - Answer- c. At a speed about 5% to
10% above the stalling speed
10. Lowering the flaps during a landing approach:
a. Increases the angle of descent without increasing the airspeed
b. Decreases the angle of descent without increasing power
c. Eliminates floating
d. Permits approaches at a higher indicated airspeed - Answer- a. Increases the angle
of descent without increasing the airspeed
11. A constant rate of climb in an aeroplane is determined by:
a. Wind speed
