POF ATPL Version A

How would the TODR (take-off distance required) for a fixed wing aircraft vary with increasing flap settings (from retracted to full flaps)?. It would decrease. It would increase. It would decrease and then increase. It would increase and then decrease.

A microburst encounter on the approach is a hazardous situation. When approaching the microburst, the airplane will initially: Tend to go below the glide path. Have an increased rate of descent. Encounter increasing headwind. Encounter increasing tailwind.

Calculate the turn radius for an aircraft with a TAS of 120 kt and a 60° bank angle. (Assume g=10 m/s²). 550 m. 220 m. 739 m. 2 000 m.

Which statement is correct regarding a windmilling propeller on a multi-engine airplane?. The windmilling drag is much higher than for a feathered propeller. The drag of a windmilling and a feathered propeller is almost the same. The windmilling drag is only significant at negative blade angles. A windmilling propeller hardly affects low speed controllability.

Which statement, about an airplane leaving ground effect at constant angle of attack, is correct? I) The lift coefficient CL remains constant. II) The induced drag coefficient CDI decreases. I is incorrect, II is incorrect. I is correct, II is correct. I is correct, II is incorrect. I is incorrect, II is correct.

A swept-back wind, in comparison to a straight wing, has an increased tendency to…. mid-wing stall. high-speed stall. tip stall. root stall.

Which statement concerning sweepback is correct?. Sweepback provides a positive contribution to static lateral stability. A disadvantage of sweepback is that it decreases MCRIT. Sweepback is mainly intended to increase static directional stability. Sweepback increases speed stability at Mach numbers above MCRIT.

Located on the underside of a wing’s leading edge, Vortilons produce a vortex on the wing’s…. lower surface, at low angles of attach, to provide improved roll control. upper surface, at cruise angles of attack, to keep the boundary layer attached to the wing. lower surface, at high angles of attack, to keep the boundary layer attached to the wing. upper surface, at high angles of attack, to reduce the spanwise flow of air.

The critical Mach of a conventional aerofoil section decreases if: Its leading-edge radius is decreased. It is flown at lower angles of attack. Its camber is decreased. Its thickness to chord ratio is increased.

A normal shock wave is a discontinuity plane: Across which the temperature drops suddenly. That is always normal to the surface. That is normal to the local flow. Across which the pressure drops suddenly.

Wing-tip vortices are formed by the: Spanwise flow of higher-pressure air from beneath the wing outward and upward into the lower pressure air above the wing. Rotational velocity imparted to the free stream air resulting from the propeller wash across the top of the wing. Aerodynamic interference of boundary layers from different parts of the airplane with those of the wing. Mixing of the high energy airflow over the wing with the free stream air behind the trailing edge of the wing.

Extending flap will (1) _____ CL, (2) _____ speed and (3) _____ stall speed. (1) Increase, (2) decrease, (3) decrease. (1) Decrease, (2) decrease, (3) decrease. (1) Increase, (2) increase, (3) decrease. (1) Decrease, (2) decrease, (3) increase.

During a descent at a constant Mach number (assume zero thrust and standard atmospheric conditions): The pitch angle will increase. The TAS will decrease. The descent angle will decrease. The angle of attack will decrease.

Assuming no flow separation and no compressibility effects, the location of the Center of Pressure of a positively cambered aerofoil section: Moves forward when the angle of attack increases. Is at approximately 25% chord irrespective of angle of attack. Moves backwards and then forwards when the angle of attack increases. Moves backward when the angle of attack increases.

Which of the following flight phenomena can occur at Mach numbers below the critical Mach number?. Dutch roll. Tuck under. Shock stall. Mach buffet.

Which statement about propeller icing is correct? I) Propeller icing reduces blade elements drag and increases blade element lift. II) Propeller icing does not affect propeller efficiency. I is incorrect, II is correct. I is correct, II is correct. I is correct, II is incorrect. I is incorrect, II is incorrect.

The result of propeller tip speeds exceeding sonic speed is: Propeller efficiency is unchanged. Increased propeller efficiency. Decreased noise. Increased noise.

The elevator deflection required for a given maneuver will be: Larger at low IAS when compared to high IAS. Larger for an aft CG position when compared to a fwd position. The same for all CG positions. The same at all speeds.

The difference between a propeller’s blade angle and its angle of attack is called: Propeller slip. The helix angle. The effective pitch. The propeller angle.

The angle of attack of a two-dimensional wing section is the angle between: The fuselage core line and the free stream direction. The chord line of the aerofoil and the fuselage centerline. The chord line of the aerofoil and the free stream direction. The chord line and the camber line of the aerofoil.

What is the SI unit for measurement for pressure?. bar/dm². kg/m³. lb/gal. N/m².

How does the location of the CG influence VMCL?. A forward CG reduces VMCL. A forward CG increases VMCL. The CG location does NOT influence VMCL if within the permissible CG limits. The CG location does NOT influence VMCL.

You are flying a crop duster in the utility category with a VS0 of 45 kt and a VS1 of 58 kt. What is the Va speed?. 66 kt. 113 kt. 122 kt. 94 kt.

After an engine failure on a twin-engine aircraft, banking towards the live engine is limited to 5 degrees. What is correct if greater angles of bank are used?. The lateral component of weight decreases. The risk of fin stall decreases. The risk of fin stall increases. The lift required decreases.

An airplane is descending at a constant Mach number from FL350. What is the effect on the true airspeed?. It decreases as altitude decreases. It decreases as pressure increases. It increases as the temperature increases. It remains constant.

Refer to the figure. Choose the correct statement: Aerofoil 4 corresponds to line 3. Aerofoil 2 corresponds to line 4. Aerofoil 1 corresponds to line 1. Aerofoil 3 corresponds to line 2.

At a constant airspeed, a reduction in an aerofoil’s angle of attack results in the speed of the flow over the upper surface to…. Decrease and the lifting ability of the aerofoil to decrease. Increase and the lifting ability of the aerofoil to increase. Decrease and the lifting ability of the aerofoil to increase. Increase and the lifting ability of the aerofoil to decrease.

After suspecting a fuel leak, the aircrew flying a jet transport aircraft decides to divert to the nearest suitable airport. At what speed should they fly?. Maximum Range Speed. Maximum Endurance Speed. MMO. Long Range Speed.

On a wing fitted with a “Fowler” type trailing edge flap, the “Full extended” position will produce: An unaffected CD, at a given angle of attack. An increase in wing area and camber. An unaffected wing area and increase in camber. An increase in wing area only.

If the Mach number is 0.8 and the TAS is 480 kt, what is the speed of sound?. 750 kt. 384 kt. 600 kt. 560 kt.

MCRIT is the free stream Mach number at which: The critical angle of attack is reached. Somewhere about the airframe Mach 1 is reached locally. Shock stall occurs. Mach buffet occurs.

For a fixed-pitch propeller, the blade angle of attack: Can never become negative. Decreases during the take-off. Is always positive during idling descent. Decreases when the airplane speed decreases (with constant engine RPM).

A stick pusher: Pushes the elevator control forward when a specified value of angle of attack is exceeded. Vibrates the elevator control. Pushes the elevator control forward prior to stick shaker activation. Pushes the elevator control to avoid a stall at a negative load factor.

Refer to the figure. Which line in the diagram illustrates an airplane which is statically longitudinally stable at all angles of attack?. Line 2. Line 1. Line 4. Line 3.

Assuming no flow separation, when speed is decreased in straight and level flight on a positively cambered aerofoil, what happens to the: I) center of pressure, II) the magnitude of the total lift force. I) moves forward, II) remains constant. I) moves aft, II) remains constant. I) moves aft, II) increases. I) moves forward, II) decreases.

The torque reaction of a rotating fixed pitch propeller will be greatest at: High airplane speed and low engine power. High airplane speed and maximum engine power. Low airplane speed and low engine power. Low airplane speed and maximum engine power.

Which of these statements about stall speed is correct?. Decreasing forward sweep decreases stall speed. Increasing wing anhedral decreases stall speed. Decreasing wing anhedral decreases stall speed. Decreasing forward sweep increases stall speed.

During an approach and coming to land, the pilots configure the full flaps landing. However, the left leading-edge slats do not extend. Which statement is true?. The right-wing stalls if speed increases/decreases. The left wing may stall if speed decreases. The left wing may stall if speed increases. No noticeable change for landing.

In order to prevent flight control surface flutter, the center of mass of the flight control should be: In the middle of the flight control surface. In front of the hinge line. At the hinge line. Behind the hinge line.

The Lift Coefficient versus the Angle of Attack curve of a negatively cambered aerofoil section intersects the horizontal axis of the graph: At the origin. At no point. To the left of the origin. To the right of the origin.

Which statement about negative tail stall is correct?. When a negative tail stall occurs, the airplane will show an uncontrollable pitch-up moment. When a negative tail stall occurs, the airplane will show an uncontrollable pitch-down moment. Negative tail stall is a stall of the fin with a negative sideslip angle (nose pointing to the right of the relative airflow). Negative tail stall is a stall of the tailplane when the aerodynamic force is in upward direction.

Calculate the lift (N) when in a 30° gliding descent, given: Drag: 103 500 N Mass: 12 500 kg. 10 825 N. 61 313 N. 106 196 N. 6 250 N.

How will the Center of Gravity (CG) affect asymmetric yaw?. CG FWD will result in an increased yaw. CG FWD will result in a reduced yaw. CG AFT will result in a reduced yaw. It is independent of CG.

Assuming constant IAS, when an airplane enters ground effect: The induced angle of attack increases. Downwash does not change. The effective angle of attack decreases. Induced drag reduces.

The contribution of the wing to the static longitudinal stability of an airplane: Depends on CG location relative to the wing aerodynamic center. Is always negative. Is positive if the wing has a positive cambered aerofoil section and the aerodynamic center is ahead of the CG. Depends on the wing location relative to the fuselage.

High-speed buffet is induced by: The bow wave in front of the wing. Boundary layer control. Interaction between flow separation and shock wave motion. A shift of the center of gravity.