081.05 CONTROL

Question 1

Rolling is the rotation of the aeroplane about the (…) axis and controlled by (…).

Answer 1

Rolling is the rotation of the aeroplane about the (longitudinal) axis and controlled by (ailerons).

Question 2

Pitching is the rotation of the aeroplane about the (…) axis and controlled by (…).

Answer 2

Pitching is the rotation of the aeroplane about the (lateral) axis and controlled by (elevators).

Question 3

Yawing is the rotation of the aeroplane about the (…) axis and controlled by (…).

Answer 3

Rolling is the rotation of the aeroplane about the (normal or vertical) axis and controlled by (rudders).

Question 4

Flight path angle is defined as the angle between (longitudinal axis/flight path vector) and (flight path vector/horizontal plane).

Answer 4

Flight path angle is defined as the angle between (flight path vector) and (horizontal plane).

Question 5

Pitch angle is defined as the angle between (longitudinal axis/flight path vector) and (flight path vector/horizontal plane).

Answer 5

Pitch angle is defined as the angle between (longitudinal axis) and (horizontal plane).

Question 6

An aircraft is approaching to land with its CG at the FWD limit. Compared to a situation with CG at the AFT limit, the control forces in pitch during the flare will be (higher/lower) and V_REF would be (higher/lower).

Answer 6

An aircraft is approaching to land with its CG at the FWD limit. Compared to a situation with CG at the AFT limit, the control forces in pitch during the flare will be (higher) and V_REF would be (higher).

Question 7

Fairings of tail mounted engines give (positive/negative/zero) pitching moment.

Answer 7

Fairings of tail mounted engines give (positive) pitching moment.

- because of drag above the CG, so disregard thrust in this question! -

Question 8

A T-tail has (more/less) stabilizing effect than a low tail due to receiving (more/less) downwash.

Answer 8

A T-tail has (more) stabilizing effect than a low tail due to receiving (less) downwash.

Question 9

Full rudder deflection is limited on CAT aeroplanes as (IAS/altitude) increases becasue a full rudder deflection could in that case cause (an excessive load on the structure of the aeroplane/the aircraft to enter a spiral dive).

Answer 9

Full rudder deflection is limited on CAT aeroplanes as (IAS) increases becasue a full rudder deflection could in that case cause (an excessive load on the structure of the aeroplane).

Question 10

A Frise aileron is an aileron where the leading edge protrudes (below/above) the wing when teh aileron is raised, but not (below/above) it when the aileron is lowered.

Answer 10

A Frise aileron is an aileron where the leading edge protrudes (below) the wing when teh aileron is raised, but not (above)​ it when the aileron is lowered.

Question 11

When an aileron is defelcted upwards, (induced/wave/interference/form) drag increases the most.

Answer 11

When an aileron is defelcted upwards, (form) drag increases the most.

Question 12

Adverse yaw is the tendency of an aeroplane to yaw in the (same/opposite) direction of turn mainly due to the difference in (induced/form) drag on each wing.

Answer 12

Adverse yaw is the tendency of an aeroplane to yaw in the (opposite) direction of turn mainly due to the difference in (induced) drag on each wing.

Question 13

An example of differential aileron defelction to initiate a left turn is left aileron (up/down) (2°/5°) and right aileron (up/down) (2°/5°).

Answer 13

An example of differential aileron defelction to initiate a left turn is left aileron (up) (5°) and right aileron (down) (2°)​.

Question 14

If a turbulent gust causes an aeroplane to roll, the up-going wing experiences (an increase/a decrease/no change) in AoA.

Answer 14

If a turbulent gust causes an aeroplane to roll, the up-going wing experiences (an increase) in AoA.

Question 15

A given aileron deflection affects (bank angle/roll rate) and is depentent on (IAS/TAS).

Answer 15

A given aileron deflection affects (roll rate) and is depentent on (IAS).

- Lift formula uses dynamic pressure which is IAS -

Question 16

Yaw is followed by roll because the (rolling/yawing) moment generated by rudder deflection causes a speed increase of the (inner/outer) wing, which increases the lift on that wing so that the aerpolane starts to roll in the direction of (yaw/turn).

Answer 16

Yaw is followed by roll because the (yawing) moment generated by rudder deflection causes a speed increase of the (outer) wing, which increases the lift on that wing so that the aerpolane starts to roll in the direction of (yaw).

Question 17

The difference between a balance tab and servo tab is that with a balance tab, the control surface deflects the (elevator/tab) while with a servo tab the (elevator/tab) is deflected.

Answer 17

The difference between a balance tab and servo tab is that with a balance tab, the control surface deflects the (elevator) while with a servo tab the (tab) is deflected.

Question 18

A spring tab operates like a servo tab at higher (altitude/temperature/TAS or IAS).

Answer 18

A spring tab operates like a servo tab at higher (TAS or IAS).

Question 19

A horn balance is used for aerodynamic balancing and is done by locating a part of the control surface (ahead/behind) of the hinge line to protrude in the airflow.

Answer 19

A horn balance is used for aerodynamic balancing and is done by locating a part of the control surface (ahead) of the hinge line to protrude in the airflow.

source: http://www.pilotfriend.com/training/flight_training/fxd_wing/trim.htm

Question 20

Stick forces, provided by an elevator feel system, depend on (stabilizer position/elevator deflection) and (dynamic/stratic/total) pressure.

Answer 20

Stick forces, provided by an elevator feel system, depend on (elevator deflection) and (dynamic) pressure.

Question 21

In case of manual reversion of fully powered flight controls, a (anti-balance/balance/servo/spring) tab is commonly used.

Answer 21

In case of manual reversion of fully powered flight controls, a (servo) tab is commonly used.

- only tab that can be operated without moving the control itself, which would be too heavy -

Question 22

Primary input for an artificial feel system is (static pressure/IAS/TAS/Mach number).

Answer 22

Primary input for an artificial feel system is (IAS).

Question 23

If a pilot moves the control stick of an elevator equipped with an anti-balance tab, the anti-balance tab moves in the (same/opposite) direction as the elevator.

Answer 23

If a pilot moves the control stick of an elevator equipped with an anti-balance tab, the anti-balance tab moves in the (same) direction as the elevator.

Question 24

A trim tab (increases/reduces) hinge moment and (increases/reduces) control surface efficiency.

Answer 24

A trim tab (reduces) hinge moment and (reduces) control surface efficiency.

Question 25

In the unlikely event of an aircraft becoming airborne with the elevator control lock engaged, operation of an elevator trim tab control in the normal direction to counteract a nose up tendency would result in a(n) **(reduction/increase)** of the nose up tendency.

Answer 25

In the unlikely event of an aircraft becoming airborne with the elevator control lock engaged, operation of an elevator trim tab control in the normal direction to counteract a nose up tendency would result in an **(increase)** of the nose up tendency. *- trim tab moves in opposite direction -*

Question 26

Fly-by-wire controlled aircraft operate in three different control laws. Name them.

Answer 26

Normal, alternate and direct law