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Question 276-1 : During balanced level flight, the pitch angle of the main rotor blade ? [ Analysis topography ]

Decreases on the advancing side, increases on the retreating side.

exemple 376 Decreases on the advancing side, increases on the retreating side.

Question 276-2 : 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 380 On the left hand side of the swash plate.

Question 276-3 : 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 384 The hover height, type of ground surface, slope of the ground, wind direction.

Question 276-4 : Translational lift is due to ?

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

exemple 388 The increase in main rotor efficiency when moving from hovering to forward flight.

Question 276-5 : A 'transition' in a helicopter is ?

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

exemple 392 A change in the flight condition from or to hovering flight.

Question 276-6 : The flare in a helicopter is ?

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

exemple 396 A change of the main rotor disc attitude to reduce forward speed.

Question 276-7 : Flare effects in a helicopter include ?

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

exemple 400 Thrust reversal, increase in rotor rpm, increase in total rotor thrust

Question 276-8 : The maximum speed in backward flight is mainly limited by ?

The restricted rearward movement of the cyclic.

exemple 404 The restricted rearward movement of the cyclic.

Question 276-9 : Asymmetry of lift is eliminated by ?

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

exemple 408 The advancing blade reducing the angle of attack and the retreating blade increasing the angle of attack.

Question 276-10 : Airflow reversal may occur ?

At the root end of the retreating blade.

exemple 412 At the root end of the retreating blade.

Question 276-11 : During flight the yaw pedals are used to control ?

Aircraft heading, balance, slip and skid

exemple 416 Aircraft heading, balance, slip and skid

Question 276-12 : A tail rotor is fitted to most helicopters to compensate for ?

Main rotor torque reaction and give directional control

exemple 420 Main rotor torque reaction and give directional control

Question 276-13 : In hovering flight, if not corrected, the tail rotor has a tendency to cause the helicopter to ?

Drift.

exemple 424 Drift.

Question 276-14 : If the collective pitch is increased and rotor rpm reduced to a safe minimum during autorotation the rate of descent ?

Decreases

exemple 428 Decreases

Question 276-15 : Retreating rotor blade stall can be detected by ?

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

exemple 432 Vibration, erratic cyclic stick forces, tendency to pitch up and roll towards the retreating side.

Question 276-16 : 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 436 Rate of descent will decrease, coning angle will increase and rotor rpm will increase.

Question 276-17 : 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 440 Counteract yaw with pedals, maintain position with cyclic, cushion touchdown with collective

Question 276-18 : 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 444 At low airspeed in a transition to or from the hover.

Question 276-19 : 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 448 Lower collective, counteract yaw with pedals, select attitude with cyclic, select landing site, transmit mayday, position helicopter for an into wind landing

Question 276-20 : 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 452 Cause rotor rpm to reduce, increase the coning angle, increase the angle of attack of the blades.

Question 276-21 : 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 456 Airflow speeds up over the top surface and pressure decreases relative to the pressure of the slower air over the lower surface.

Question 276-22 : 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 460 The point on the chord line through which the resultant of all aerodynamic forces acts

Question 276-23 : Ground cushion effect is caused by ?

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

exemple 464 The airflow through the disc creating a divergent duct with higher pressure beneath the rotor.

Question 276-24 : A fully articulated helicopter rotor is one in which the blades are ?

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


Question 276-25 : Vortex ring settling with power is most likely to occur with ?

Low airspeed, power applied, rate of descent greater than 300ft/min

exemple 472 Low airspeed, power applied, rate of descent greater than 300ft/min

Question 276-26 : The plane of rotation is tilted by the pilot ?

Moving the cyclic control

exemple 476 Moving the cyclic control

Question 276-27 : The amount of induced power required after achieving translational lift is ?

Less than was required to hover

exemple 480 Less than was required to hover

Question 276-28 : 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 484 There will be insufficient control movement available for safe flight

Question 276-29 : Blade stall can be alleviated by increasing the ?

Speed of the rotor

exemple 488 Speed of the rotor

Question 276-30 : Rotor blade sections are designed so that the centre of pressure ?

Is normally positioned close to the feathering axis

exemple 492 Is normally positioned close to the feathering axis

Question 276-31 : The plane of rotation of the rotor blades is parallel to ?

The tip path plane.

. 2407 exemple 496 The tip path plane.

Question 276-32 : The effect of main rotor torque reaction will be to rotate the fuselage in the ?

Opposite direction to the main rotor blades.

exemple 500 Opposite direction to the main rotor blades.

Question 276-33 : Tail rotor roll may be prevented by ?

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

exemple 504 Raising the tail rotor hub to the same level as the main rotor hub.

Question 276-34 : The angle of attack of a rotor blade is ?

Never equal to the pitch angle during powered flight

exemple 508 Never equal to the pitch angle during powered flight

Question 276-35 : Flapping is ?

The angular movement of the blade relative to the hubplane

exemple 512 The angular movement of the blade relative to the hubplane

Question 276-36 : A increase in pitch angle during the revolution causes the affected blade to ?

Flap up, thus decreasing the angle of attack

exemple 516 Flap up, thus decreasing the angle of attack

Question 276-37 : Lead lagging or dragging is ?

Blades moving in the plane of rotation independent of each other

exemple 520 Blades moving in the plane of rotation independent of each other

Question 276-38 : 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 524 Total rotor thrust will equal aircraft weight.

Question 276-39 : 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 528 Pitch angle is lower

Question 276-40 : In straight and level flight, as forward speed is increased, rotor thrust is ?

Increased

exemple 532 Increased


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