081.05 CONTROL Flashcards

1
Q

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

A

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

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2
Q

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

A

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

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3
Q

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

A

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

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4
Q

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

A

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

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5
Q

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

A

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

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6
Q

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 VREF would be (higher/lower).

A

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 VREF would be (higher).

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7
Q

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

A

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

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

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8
Q

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

A

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

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9
Q

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).

A

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).

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10
Q

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.

A

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.

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11
Q

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

A

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

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12
Q

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.

A

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.

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13
Q

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°).

A

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

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14
Q

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

A

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

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15
Q

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

A

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

- Lift formula uses dynamic pressure which is IAS -

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16
Q

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).

A

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).

17
Q

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.

A

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.

18
Q

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

A

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

19
Q

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.

A

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

20
Q

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

A

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

21
Q

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

A

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 -

22
Q

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

A

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

23
Q

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.

A

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.

24
Q

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

A

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

25
Q

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.

A

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 -

26
Q

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

A

Normal, alternate and direct law