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Question 253-1 : Advance angle is an angle between the ? [ Explanation maintenance ]

Pitch link attachement on the swash plate and the longitudinal axis of the blade

exemple 353 Pitch link attachement on the swash plate and the longitudinal axis of the blade

Question 253-2 : Main rotor freedom of movement is defined as ?

Feathering, flapping and dragging.

exemple 357 Feathering, flapping and dragging.

Question 253-3 : During flight the cyclic stick determines ?

Attitude,airspeed and horizontal movement.

exemple 361 Attitude,airspeed and horizontal movement.

Question 253-4 : During balanced level flight, the pitch angle of the main rotor blade ?

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

exemple 365 Decreases on the advancing side, increases on the retreating side.

Question 253-5 : 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.

exemple 369 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.

Question 253-6 : 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 373 The hover height, type of ground surface, slope of the ground, wind direction.

Question 253-7 : Translational lift is due to ?

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

exemple 377 The increase in main rotor efficiency when moving from hovering to forward flight.

Question 253-8 : A 'transition' in a helicopter is ?

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

exemple 381 A change in the flight condition from or to hovering flight.

Question 253-9 : The flare in a helicopter is ?

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

exemple 385 A change of the main rotor disc attitude to reduce forward speed.

Question 253-10 : Flare effects in a helicopter include ?

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

exemple 389 Thrust reversal, increase in rotor rpm, increase in total rotor thrust

Question 253-11 : The maximum speed in backward flight is mainly limited by ?

The restricted rearward movement of the cyclic.

exemple 393 The restricted rearward movement of the cyclic.

Question 253-12 : Asymmetry of lift is eliminated by ?

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

exemple 397 The advancing blade reducing the angle of attack and the retreating blade increasing the angle of attack.

Question 253-13 : Airflow reversal may occur ?

At the root end of the retreating blade.

exemple 401 At the root end of the retreating blade.

Question 253-14 : During flight the yaw pedals are used to control ?

Aircraft heading, balance, slip and skid

exemple 405 Aircraft heading, balance, slip and skid

Question 253-15 : A tail rotor is fitted to most helicopters to compensate for ?

Main rotor torque reaction and give directional control

exemple 409 Main rotor torque reaction and give directional control

Question 253-16 : In hovering flight, if not corrected, the tail rotor has a tendency to cause the helicopter to ?

Drift.

exemple 413 Drift.

Question 253-17 : If the collective pitch is increased and rotor rpm reduced to a safe minimum during autorotation the rate of descent ?

Decreases

exemple 417 Decreases

Question 253-18 : Retreating rotor blade stall can be detected by ?

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

exemple 421 Vibration, erratic cyclic stick forces, tendency to pitch up and roll towards the retreating side.

Question 253-19 : 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 425 Rate of descent will decrease, coning angle will increase and rotor rpm will increase.

Question 253-20 : 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

Question 253-21 : Unintentional over pitching is likely to occur ?

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

exemple 433 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.

Question 253-22 : 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 437 Lower collective, counteract yaw with pedals, select attitude with cyclic, select landing site, transmit mayday, position helicopter for an into wind landing

Question 253-23 : 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.

Question 253-24 : 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.

Question 253-25 : 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 449 The point on the chord line through which the resultant of all aerodynamic forces acts

Question 253-26 : Ground cushion effect is caused by ?

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

exemple 453 The airflow through the disc creating a divergent duct with higher pressure beneath the rotor.

Question 253-27 : A fully articulated helicopter rotor is one in which the blades are ?

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

Question 253-28 : Vortex ring settling with power is most likely to occur with ?

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

exemple 461 Low airspeed, power applied, rate of descent greater than 300ft/min

Question 253-29 : The plane of rotation is tilted by the pilot ?

Moving the cyclic control

exemple 465 Moving the cyclic control

Question 253-30 : The amount of induced power required after achieving translational lift is ?

Less than was required to hover

Question 253-31 : 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 473 There will be insufficient control movement available for safe flight

Question 253-32 : Blade stall can be alleviated by increasing the ?

Speed of the rotor

exemple 477 Speed of the rotor

Question 253-33 : Rotor blade sections are designed so that the centre of pressure ?

Is normally positioned close to the feathering axis

exemple 481 Is normally positioned close to the feathering axis

Question 253-34 : The plane of rotation of the rotor blades is parallel to ?

The tip path plane.

exemple 485 The tip path plane. — . 2407

Question 253-35 : The effect of main rotor torque reaction will be to rotate the fuselage in the ?

Opposite direction to the main rotor blades.

exemple 489 Opposite direction to the main rotor blades.

Question 253-36 : Tail rotor roll may be prevented by ?

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

exemple 493 Raising the tail rotor hub to the same level as the main rotor hub.

Question 253-37 : The angle of attack of a rotor blade is ?

Never equal to the pitch angle during powered flight

exemple 497 Never equal to the pitch angle during powered flight

Question 253-38 : Flapping is ?

The angular movement of the blade relative to the hubplane

exemple 501 The angular movement of the blade relative to the hubplane

Question 253-39 : A increase in pitch angle during the revolution causes the affected blade to ?

Flap up, thus decreasing the angle of attack

exemple 505 Flap up, thus decreasing the angle of attack

Question 253-40 : Lead lagging or dragging is ?

Blades moving in the plane of rotation independent of each other

exemple 509 Blades moving in the plane of rotation independent of each other

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