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Question 276-1 : During flight the cyclic stick determines ? [ Analysis topography ]

Attitudeairspeed and horizontal movement

Question 276-2 : During balanced level flight the pitch angle of the main rotor blade ?

Decreases on the advancing side increases on the retreating side.

exemple 380: Decreases on the advancing side increases on the retreating side — Increases on the advancing side, decreases on the retreating side. remains constant on both sides. varies according to the circumference of the disc decreases in the front position, increases in the back position.

Question 276-3 : For a rotor which turns in a clockwise direction seen from above when transitioning from hover to forward flight the swash plate is moved so that the pitch operating arms start to move upwards ?

On the left hand side of the swash plate.

Cyclic control must tilt the rotor disc forward the minimum pitch angle will be on the advancing blade the pitch operating arm starts to move up when it is on the left hand side of the swash plate the pitch operating arm was before at its lowest position then due to phase lag the blade will flap to its lowest position 90° later in front of the pilot then when the blade is in front of the pilot the pitch arm reaches its highest position and the blade will start to flap up as it rotates to its retreating position

exemple 384: On the left hand side of the swash plate — On the right hand side of the swash plate. at the front of the swash plate. at the rear of the swash plate.

Question 276-4 : Factors which influence the ground effect of a hovering helicopter include ?

The hover height type of ground surface slope of the ground wind direction.

exemple 388: The hover height type of ground surface slope of the ground wind direction — The hover height, power applied, type of surface, proximity of obstructions. wind strength, shape of fuselage, hover height, size of rotor disc, power applied. wind strength, aum, position of cyclic, shape of fuselage, power applied.

Question 276-5 : Translational lift is due to ?

The increase in main rotor efficiency when moving from hovering to forward flight.

exemple 392: The increase in main rotor efficiency when moving from hovering to forward flight — The relationship between total reaction and total rotor drag. an increase in tail rotor efficiency due to forward speed. an increase in power required due to forward speed.

Question 276-6 : A 'transition' in a helicopter is ?

A change in the flight condition from or to hovering flight.

exemple 396: A change in the flight condition from or to hovering flight — Tilting the disc as a result of cyclic control movement. the force acting on the rotor head in forward flight. the take-off.

Question 276-7 : The flare in a helicopter is ?

A change of the main rotor disc attitude to reduce forward speed.

exemple 400: A change of the main rotor disc attitude to reduce forward speed — A method of reducing speed without gaining height. a method of reducing forward speed in stages. carried out after an autorotation.

Question 276-8 : Flare effects in a helicopter include ?

Thrust reversal increase in rotor rpm increase in total rotor thrust.

exemple 404: Thrust reversal increase in rotor rpm increase in total rotor thrust — Thrust reversal, rapid deceleration and tendency to pitch up large increase in parasite drag with tendency to overpitch an increase in the coning angle thus reducing the conservation of angular momentum

Question 276-9 : The maximum speed in backward flight is mainly limited by ?

The restricted rearward movement of the cyclic.

exemple 408: The restricted rearward movement of the cyclic — Interference between the main rotor and tail rotor slipstream. the danger of blade sailing. the maximum power of the engine.

Question 276-10 : Asymmetry of lift is eliminated by ?

The advancing blade reducing the angle of attack and the retreating blade increasing the angle of attack.

exemple 412: The advancing blade reducing the angle of attack and the retreating blade increasing the angle of attack — Moving the cyclic control forward. adjustment of the flapping stops. washout along the blade.

Question 276-11 : Airflow reversal may occur ?

At the root end of the retreating blade.

exemple 416: At the root end of the retreating blade — At the tip of the retreating blade. if the windspeed is less than 30 knots. in the flare.

Question 276-12 : During flight the yaw pedals are used to control ?

Aircraft heading balance slip and skid.

exemple 420: Aircraft heading balance slip and skid — Aircraft direction, slip and skid turning, balance, direction and slip direction of movement and heading

Question 276-13 : A tail rotor is fitted to most helicopters to compensate for ?

Main rotor torque reaction and give directional control.

exemple 424: Main rotor torque reaction and give directional control — Main rotor torque reaction and give thrust in sideways flight sideways drift when in hovering flight main rotor torque reaction when entering autorotation

Question 276-14 : In hovering flight if not corrected the tail rotor has a tendency to cause the helicopter to ?

Drift.

exemple 428: Drift — Turn to the right. turn to the left. pitch.

Question 276-15 : If the collective pitch is increased and rotor rpm reduced to a safe minimum during autorotation the rate of descent ?

Decreases.

exemple 432: Decreases — Increases remains the same fluctuates depending on windspeed

Question 276-16 : Retreating rotor blade stall can be detected by ?

Vibration erratic cyclic stick forces tendency to pitch up and roll towards the retreating side.

exemple 436: Vibration erratic cyclic stick forces tendency to pitch up and roll towards the retreating side — Vibration, stick shake, increased flap back. loss of directional control, large reduction in rotor rpm, height loss. vibration, erratic cyclic stick forces, tendency to pitch up and roll towards advancing side.

Question 276-17 : In autorotation if the cyclic control is pulled back speed will reduce and ?

Rate of descent will decrease coning angle will increase and rotor rpm will increase.

exemple 440: Rate of descent will decrease coning angle will increase and rotor rpm will increase — Lift will increase, coning angle will increase and rotor rpm will decrease. lift will increase, coning angle will decrease and rotor rpm will decrease. lift, coning angle and rotor rpm will remain unchanged.

Question 276-18 : If the engine fails in the hover at 3 ft skid height in still air in a single engine helicopter the recommended action is ?

Counteract yaw with pedals maintain position with cyclic cushion touchdown with collective.

exemple 444: Counteract yaw with pedals maintain position with cyclic cushion touchdown with collective — Use rudder to prevent yaw, hold cyclic steady, lower collective briefly then raise to cushion landing counteract yaw with pedals, use cyclic to raise tail rotor, lower collective slightly to maintain rotor rpm use rudder to prevent yaw, push cyclic forward for touchdown, use collective to cushion landing

Question 276-19 : Unintentional over pitching is likely to occur ?

At low airspeed in a transition to or from the hover.

Because of the downwash of the main rotor on the stabiliser fitted to the tail boom

exemple 448: At low airspeed in a transition to or from the hover — As a result of excessive cyclic movement. after attaining effective translational lift. when commencing a flare.

Question 276-20 : In the event of an engine failure in a single engine helicopter in the cruise the recommended sequence of immediate actions is ?

Lower collective counteract yaw with pedals select attitude with cyclic select landing site transmit mayday position helicopter for an into wind landing.

exemple 452: Lower collective counteract yaw with pedals select attitude with cyclic select landing site transmit mayday position helicopter for an into wind landing — Correct yaw with pedals, lower collective, transmit mayday, select landing site, use cyclic and collective to position for landing flare with cyclic, counteract yaw with pedals, establish descent with collective, select landing site, adjust collective for range, land into wind, transmit mayday lower collective, adjust yaw pedals, select airspeed, transmit mayday, autorotate to open ground, adjust speed for landing

Question 276-21 : In the event of an engine failure in a single engine helicopter in the cruise a delay in lowering the collective lever to enter autorotation will ?

Cause rotor rpm to reduce increase the coning angle increase the angle of attack of the blades.

exemple 456: Cause rotor rpm to reduce increase the coning angle increase the angle of attack of the blades — Increase the coning angle, cause the rotor rpm to reduce, decrease the angle of attack of the blades. slow the rate of descent, cause the rotor rpm to reduce, increase the coning angle. increase the rate of descent, increase the coning angle, cause a decrease in pitch.

Question 276-22 : The aerofoil shape of the blade produces lift because ?

Airflow speeds up over the top surface and pressure decreases relative to the pressure of the slower air over the lower surface.

exemple 460: Airflow speeds up over the top surface and pressure decreases relative to the pressure of the slower air over the lower surface — Airflow speeds up over the top surface and pressure increases relative to the pressure of the slower air over the lower surface. pressure of the air above the blade decreases as the speed of the air increases under the blade. the faster air over the top of the blade causes suction which raises the blade.

Question 276-23 : The centre of pressure of an aerofoil section is ?

The point on the chord line through which the resultant of all aerodynamic forces acts.

exemple 464: The point on the chord line through which the resultant of all aerodynamic forces acts — Where the largest component of lift is said to be produced where the resultant of all the centrifugal forces acts relative to the shape of the aerofoil the point about which the airflow is deflected around the aerofoil

Question 276-24 : Ground cushion effect is caused by ?

The airflow through the disc creating a divergent duct with higher pressure beneath the rotor.

Question 276-25 : A fully articulated helicopter rotor is one in which the blades are ?

Free to flap drag and change pitch through hinges or bearings.

exemple 472: Free to flap drag and change pitch through hinges or bearings — Without individual flapping and dragging hinges but the blades can move about a central gimbal not mounted on flapping or dragging hinges hinged with the axis parallel to the rotor plane of rotation which permits the blades to flap up or down

Question 276-26 : Vortex ring settling with power is most likely to occur with ?

Low airspeed power applied rate of descent greater than 300ftmin.

exemple 476: Low airspeed power applied rate of descent greater than 300ftmin — Zero airspeed, partial power, rate of descent less than 300ft/min cruise airspeed, partial power, rate of descent greater than 300ft/min low airspeed, zero power, rate of descent greater than 300ft/min

Question 276-27 : The plane of rotation is tilted by the pilot ?

Moving the cyclic control.

exemple 480: Moving the cyclic control — Raising and lowering the collective lever moving the yaw pedals allowing the blades freedom to flap

Question 276-28 : The amount of induced power required after achieving translational lift is ?

Less than was required to hover.

exemple 484: Less than was required to hover — More than was required to hover the same as was required to hover equivalent to that required for take-off

Question 276-29 : A helicopter whose centre of gravity is outside authorised limits will be unsafe because ?

There will be insufficient control movement available for safe flight.

exemple 488: There will be insufficient control movement available for safe flight — There will be oscillations of the fuselage the tail rotor will strike the ground when lifting to the hover there will be insufficient clearance between the main rotor and the tail boom

Question 276-30 : Blade stall can be alleviated by increasing the ?

Speed of the rotor.

exemple 492: Speed of the rotor — Pitch angle forward speed angle of attack

Question 276-31 : Rotor blade sections are designed so that the centre of pressure ?

Is normally positioned close to the feathering axis.

exemple 496: Is normally positioned close to the feathering axis — Has a large degree of movement for stability at high and low speeds can move forward rapidly to counteract forward c of g moves forward and backward according to the rotor speed

Question 276-32 : The plane of rotation of the rotor blades is parallel to ?

The tip path plane.

2407

exemple 500: The tip path plane — The relative airflow. the plane of the main rotor hub. the horizon.

Question 276-33 : The effect of main rotor torque reaction will be to rotate the fuselage in the ?

Opposite direction to the main rotor blades.

exemple 504: Opposite direction to the main rotor blades — Same direction as the main rotor blades. same direction as the tail rotor blades. opposite direction to the tail rotor blades.

Question 276-34 : Tail rotor roll may be prevented by ?

Raising the tail rotor hub to the same level as the main rotor hub.

exemple 508: Raising the tail rotor hub to the same level as the main rotor hub — Tilting the main rotor disc when the collective is raised. cyclic input from the pilot. yaw pedal inputs from the pilot.

Question 276-35 : The angle of attack of a rotor blade is ?

Never equal to the pitch angle during powered flight.

exemple 512: Never equal to the pitch angle during powered flight — Always equal to the pitch angle during powered flight always equal to the pitch angle during autorotative flight always determined solely by the rotational speed of the rotor blades

Question 276-36 : Flapping is ?

The angular movement of the blade relative to the hubplane.

exemple 516: The angular movement of the blade relative to the hubplane — Corrected by causing the disc to tilt to the left when collective lever is raised controlled in the tail rotor by moving the yaw pedals the angular movement of the blade above or below the horizontal plane

Question 276-37 : A increase in pitch angle during the revolution causes the affected blade to ?

Flap up thus decreasing the angle of attack.

exemple 520: Flap up thus decreasing the angle of attack — Flap down, thus increasing the angle of attack flap down, thus decreasing the angle of attack flap up, thus increasing the angle of attack

Question 276-38 : Lead lagging or dragging is ?

Blades moving in the plane of rotation independent of each other.

exemple 524: Blades moving in the plane of rotation independent of each other — Movement of the rotor blades to reposition themselves after a collective pitch change the blades moving at 90 degrees to the plane of rotation caused only by blade drag changes

Question 276-39 : In a constant speed vertical climb outside ground effect if the effects of parasite drag on the helicopter fuselage are ignored ?

Total rotor thrust will equal aircraft weight.

exemple 528: Total rotor thrust will equal aircraft weight — Total rotor thrust will need to be greater than aircraft weight. blade section pitch angle will be decreased. blade angle of attack must be greater than the pitch angle.

Question 276-40 : When a helicopter is operating in ground effect ige under the same environmental conditions as the helicopter out of ground effect oge for all blade sections the blade section ?

Pitch angle is lower.

exemple 532: Pitch angle is lower — Pitch angle is higher angle of attack is higher angle of attack is lower

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