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Question 274-1 : A free wheel is fitted to a helicopter to ? [ Analysis topography ]
Prevent the rotor from driving the engine
Question 274-2 : When right pedal is applied to a hovering helicopter whose main rotor is rotating clockwise when viewed from above 1 the power required will 2 the helicopter will yaw to the ?
1 increase 2 right.
2404with a main rotor rotating clockwise when viewed from above you have to overcome torque by moving forward the right pedal just to maintain the heading while hovering now when right pedal is applied to yaw the helicopter to the right more power is required since you must overcome the torque and yaw the helicopterif you want to yaw to the left you simply have to release your foot pressure from the right pedal the torque effect will made the helicopter yaw to the left less power is resquired(1) decrease, (2) right. (1) increase, (2) left. (1) decrease, (2) left.
Question 274-3 : For a given quantity of air if pressure and temperature remain the same and humidity is increased the air will become ?
Less dense.
More dense. neither more or less dense. incompressible.
Question 274-4 : As airspeed increases during the transition from the hover to the climb the rate of climb improves due to a ?
Reduction in induced drag.
Reduction in skin friction reduction in rotor profile drag greater induced flow
Question 274-5 : Maximum permissable rotor rpm in powered flight are governed by ?
Engine and hub limitations.
Retreating blade stall compressibility limit of forward cyclic
Question 274-6 : Flying for range in autorotation requires ?
High forward speed combined with low rotor rpm.
Low forward speed combined with high rotor rpm low forward speed combined with low rotor rpm high forward speed combined with high rotor rpm
Question 274-7 : Retreating blade stall is most likely to occur at ?
High forward speed at high aum high altitude temperature and humidity.
Low forward speed with high aum vortex ring, (settling with power) high aum
Question 274-8 : On a see saw rotor the axis of rotation of the shaft of the main rotor is ?
Perpendicular to the hub plane.
Perpendicular to the plane of rotation. perpendicular to the plane of the swash plate. always perpendicular to the airframe reference plane.
Question 274-9 : The rotor disc is ?
Perpendicular to the lift.
Perpendicular to the main rotor shaft parallel to the plan of the swash plate parallel to the relative airflow
Question 274-10 : The load of a blade is equal to ?
Its average lift per unit of area of the blade.
The average stress due to the centrifugal force the rotor power divided by the number of blades average lift per revolution
Question 274-11 : The pitch angle of the blade sections ?
Varies with the twist of the blade.
Is constant throughout the span of the blade is regarded as constant along the blade is conserved during a rotation
Question 274-12 : The mean induced airflow velocity is considered perpendicular to the ?
Rotor disc.
Airframe reference plan drive plan plane of swash plate
Question 274-13 : In the hover the induced airflow velocity ?
Increases further after having passed the rotor.
Decreases after having passed the rotor is equal above and below the rotor remains constant after having passed the rotor
Question 274-14 : For a rotor which turns in a clockwise direction seen from above in a sideways hover to the right with zero wind the pilot will see the retreating blade ?
Behind him.
On his right. on his left. in front of him.
Question 274-15 : The position of the advancing blade relative to the pilot in forward flight ?
Depends on the direction of rotation of the main rotor.
Is to the left. is to the right. depends on wind direction.
Question 274-16 : For a rotor which turns in an anti clockwise direction seen from above in a sideways hover to the left with zero wind the pilot will have the retreating blade ?
Behind him.
On his left. on his right. in front of him.
Question 274-17 : For a rotor which turns in a clockwise direction seen from above in a sideways hover to the left with zero wind the pilot will have the retreating blade ?
In front of him.
On his right on his left behind him
Question 274-18 : The position of the retreating blade relative to the pilot in forward flight ?
Depends on the direction of rotation of the main rotor.
Is to the left is to the right depends on wind direction
Question 274-19 : In a stationary hovering relative to the ground the position of the retreating blade relative to the pilot ?
Depends on the direction of rotation of the main rotor and wind direction.
Is to the left. is to the right. depends only on the rotor's direction of rotation.
Question 274-20 : Blade sailing is a condition which may occur ?
During starting or stopping the main rotor s in strong winds.
During a vertical autorotation at the onset of retreating blade stall at the onset of vortex ring (settling with power)
Question 274-21 : If the helicopter is affected by a strong gust of headwind whilst the rotor rpm is low ?
There is a danger of the main rotor blades striking the tail boom.
Cyclic control will be effective in keeping the disc level groundcrew, standing in front of the helicopter, are in danger from a blade strike the effect on the rotor blades will depend on the direction of rotation
Question 274-22 : To minimise the dangers of blade sailing ?
The start up and shut down should be carried out with the helicopter facing slightly out of wind.
The start-up and shut-down should be carried out facing directly into wind. flapping restrictors, if fitted, should be withdrawn before start-up or shut-down. ensure that rotor rpm during start-up or shut-down are increased or decreased as slowly as possible.
Question 274-23 : The helicopter is said to be statically stable if after a disturbance in flight ?
It has the tendency to return to its original position without a control input from the pilot.
It remains in the new position without a control input from the pilot pilot control input is required to regain the original position it continues to move steadily and smoothly away from its original position
Question 274-24 : Dynamic stability in a helicopter can only exist if there is ?
Static stability.
Static instability sufficient control force available sufficient forward speed
Question 274-25 : A helicopter in the hover is statically ?
Stable and dynamically unstable.
Question 274-26 : A stabiliser fitted to the tail boom of a helicopter in forward flight will 1 stability in 2 ?
1 increase 2 pitch.
(1) decrease (2) roll (1) increase (2) roll (1) decrease (2) pitch
Question 274-27 : A stabiliser fitted to the tail boom of a helicopter in rearward flight will 1 stability in 2 ?
Question 274-29 : Control power is the effectiveness of ?
The cyclic control in achieving changes in fuselage attitude.
2405The collective control in achieving changes in height the throttle in achieving changes of rotor rpm the cyclic control in achieving changes in direction
Question 274-30 : The addition of a mass in the blade tip at 60% of the chord will ?
Modify twist behaviour under operation.
Not modify twist behaviour under operation not modify the graduation in pitch of the polar curve for the hover outside of ground effect not modify the graduation in pitch of the polar curve for the hover in ground effect
Question 274-31 : Centrifugal force ?
Increases with mass and the square of rotational speed.
Decreases with mass and rotational speed decreases with mass and increases with rotational speed increases with mass and decreases with rotational speed
Question 274-32 : In level steady forward flight an increase of the speed of the main rotor without any change in lift will ?
Increases the stresses in the blade fasteners.
Increases conicity. causes the onset of blade stalling in forward flight. decreases control surface efficiency.
Question 274-33 : Flapping is the ?
Angular movement of a blade perpendicular to the hub plane.
Movement, in the plane of rotation, of a rotor blade from its neutral position trimming of a rotor blade to ensure accurate and consistent tracking flexing of a blade along its length as a result of turbulence
Question 274-34 : During steady level forward flight forces acting on a helicopter are ?
The vertical component of total rotor thrust equal and opposite to weight the horizontal component equal and opposite to drag.
Lift, equal and opposite to weight, horizontal thrust opposite to but greater than drag the vertical component of total rotor thrust opposite to weight, the horizontal component opposite and equal to tail rotor thrust total rotor thrust equal and opposite to weight, the horizontal component of total rotor thrust equal and opposite to drag
Question 274-35 : Moving the centre of gravity to the extreme aft position will ?
Reduce the effective cyclic pitch forward range of movement.
Reduce the effective cyclic stick aft range of movement not affect the position of the cyclic fore and aft control due to phase lag, produce a tendency to roll in the direction of the advancing blade side
Question 274-36 : A helicopter is statically stable when it shows the ?
Tendency to return to its original attitude after having been displaced.
Ability to rotate about an axis tendency to pitch at low airspeed ability to resist dynamic roll-over
Question 274-37 : The 'vortex ring state' which may develop under conditions of a power on descent at low forward airspeed is ?
An unstable condition which may result in an uncontrolled rate of descent.
A stable condition which reduces the rate of descent a desirable condition since it causes the helicopter to flare automatically on landing normally controlled by increasing the collective pitch on the main rotor blades
Question 274-38 : The principle of virtual offset hinges are used in a hingeless rotor system which has the effect of 1 stability and 2 control power ?
Question 274-39 : In most helicopter types the rotor brake is normally situated ?
Immediately after the main gearbox on the intermediate drive shaft.
Between the engine gearbox and the main rotor gearbox. after the main gearbox and before the main rotor head. between the main gearbox and the swashplate.
Question 274-40 : The non rotating scissors of a swashplate control system are attached at their lower attachment point to the ?
Rotor gearbox.
Fuselage structure. drive shaft. rotor mast.
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