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Question 278-1 : When in the hover, movement of the collective lever upwards will change the pitch angle of the main rotor blades ? [ Analysis topography ]

By an equal amount throughout 360 of rotation

exemple 378 By an equal amount throughout 360 of rotation

Question 278-2 : In a tail rotor, asymmetry of lift ?

May be reduced by allowing blade flapping

exemple 382 May be reduced by allowing blade flapping

Question 278-3 : A helicopter having an anti clockwise rotating main rotor when seen from above , with power on, will have a tendency to drift ?

To the right.

exemple 386 To the right.

Question 278-4 : In a hingeless main rotor there are ?

Feathering bearing but no dragging or flapping hinges.

exemple 390 Feathering bearing but no dragging or flapping hinges.

Question 278-5 : In a shrouded tail rotor fenestron the blades ?

Respond to tail rotor collective pitch control.

exemple 394 Respond to tail rotor collective pitch control. — The control of the tail rotor thrust is achieved by collective variation of the pitch angle of the blades...the pitch control tail rotor blades system is connected to the rudder pedals.

Question 278-6 : Ground resonance can be prevented from developing to a critical point, if action is taken early enough, by ?

Applying collective pitch control and lifting off.

exemple 398 Applying collective pitch control and lifting off.

Question 278-7 : The three main features which define the maximum speed of a helicopter are ?

Compressibility limit of advancing blade, retreating blade stall and design limits of cyclic control

exemple 402 Compressibility limit of advancing blade, retreating blade stall and design limits of cyclic control

Question 278-8 : During autorotative flight ?

The fuselage will tend to rotate in the same direction as the rotor.

exemple 406 The fuselage will tend to rotate in the same direction as the rotor.

Question 278-9 : Blade sailing, with the attendant possibility of a blade strike on the tail boom or rear fuselage, is most likely to occur ?

During very low rotor rpm conditions, particularly whilst starting or stopping the engine in gusty conditions

exemple 410 During very low rotor rpm conditions, particularly whilst starting or stopping the engine in gusty conditions

Question 278-10 : The primary factor which prevents the main rotor blade coning upwards on an articulated rotor head is ?

The centrifugal force acting on the blades.

exemple 414 The centrifugal force acting on the blades.

Question 278-11 : Blades with a positive coning angle flapping upwards tend to ?

Increase rotational speed.

exemple 418 Increase rotational speed.

Question 278-12 : An increase in angle of attack of a rotor blade element, below the stall angle, causes an increase in ?

Drag and lift forces.

exemple 422 Drag and lift forces.

Question 278-13 : A shrouded tail rotor fenestron ?

Largely removes lift dissymmetry and the attendant need for cyclic feathering of the tail rotor

exemple 426 Largely removes lift dissymmetry and the attendant need for cyclic feathering of the tail rotor

Question 278-14 : During an autorotative descent the maximum gliding distance will be obtained at ?

A speed greater than that associated with the minimum rate of descent

exemple 430 A speed greater than that associated with the minimum rate of descent

Question 278-15 : In forward flight the lift produced by a given blade element is dependent upon ?

Angle of attack and the square of its air speed

exemple 434 Angle of attack and the square of its air speed

Question 278-16 : When the cyclic pitch control is forward, a main rotor blade will reach its maximum pitch ?

On the retreating side.

exemple 438 On the retreating side.

Question 278-17 : Blade hinges arranged with a 'delta three' hinge effect ?

Decrease their pitch angle with flap up.

exemple 442 Decrease their pitch angle with flap up.

Question 278-18 : Some tail rotor hinges are not perpendicular to the feathering axis in order to ?

Reduce the effects of dissymmetry of lift with forward speed

exemple 446 Reduce the effects of dissymmetry of lift with forward speed — .since the tail rotor is subjected to dissymmetry of rotor thrust it is often fitted with flapping hinges. normally they have delta 3 hinges that decrease the angle of attack when the blade flaps up and vice versa.

Question 278-19 : The normal or yaw axis of a helicopter is a straight line ?

Passing through the centre of gravity perpendicular to the longitudinal and lateral axes

exemple 450 Passing through the centre of gravity perpendicular to the longitudinal and lateral axes

Question 278-20 : The angle of attack of an aerofoil section is the angle between the ?

Chord line and the relative airflow

exemple 454 Chord line and the relative airflow

Question 278-21 : A helicopter is statically stable when it exhibits the ?

Tendency to return to its original attitude after a disturbance

exemple 458 Tendency to return to its original attitude after a disturbance

Question 278-22 : The amount of lift produced by a given helicopter rotor blade element is dependent upon ?

The angle of attack of the blade, the square of the air velocity relative to the blade element and the air density

exemple 462 The angle of attack of the blade, the square of the air velocity relative to the blade element and the air density

Question 278-23 : Phase lag is the ?

Azimuthal angle through which a blade moves between a pitch value input and the corresponding flapped position

exemple 466 Azimuthal angle through which a blade moves between a pitch value input and the corresponding flapped position

Question 278-24 : As speed increases the parasite drag of a helicopter fuselage will ?

Tend to cause the nose to pitch down

Question 278-25 : 'coning angle' is defined as the angle between the rotor blade's longitudinal axis and the ?

Tip path plane.

exemple 474 Tip path plane. — . 2407

Question 278-26 : Disc loading is defined as the ?

Ratio of the total weight of the helicopter, per unit of the disc area

exemple 478 Ratio of the total weight of the helicopter, per unit of the disc area

Question 278-27 : In order to reduce the effects of retreating blade stall on a helicopter in flight, the ?

Collective pitch should be lowered to decrease pitch

exemple 482 Collective pitch should be lowered to decrease pitch

Question 278-28 : If a helicopter is loaded for flight and the centre of gravity is within limits for take off ?

The centre of gravity position needs to be calculated for landing

exemple 486 The centre of gravity position needs to be calculated for landing

Question 278-29 : In order to produce a stable teetering rotor it may be necessary to ?

Stabilise it by use of rotating masses

exemple 490 Stabilise it by use of rotating masses

Question 278-30 : A tilt of the rotor disc plane will cause the helicopter to accelerate ?

In the direction of tilt

exemple 494 In the direction of tilt

Question 278-31 : The avoid areas in a 'height velocity diagram' define the height/velocity combination ?

From which safe autorotative descent and landing after engine failure may not easily be accomplished

exemple 498 From which safe autorotative descent and landing after engine failure may not easily be accomplished

Question 278-32 : In a hingeless rotor head, flapping movements ?

Are accommodated for by the rotor blades flexible attachements to the hub.

exemple 502 Are accommodated for by the rotor blades flexible attachements to the hub.

Question 278-33 : When a cyclic control input has been made, the rotor blade pitch will be ?

Increasing for one half revolution and decreasing for the next half

exemple 506 Increasing for one half revolution and decreasing for the next half

Question 278-34 : What effect does an increase in density altitude have on the amount of anti torque pedal required to maintain heading in the hover and why ?

Increased because power required increases and the tail rotor is less effective

exemple 510 Increased because power required increases and the tail rotor is less effective

Question 278-35 : If the centre of gravity is at the rear limit ?

Then forward cyclic travel is reduced.

exemple 514 Then forward cyclic travel is reduced.

Question 278-36 : With a centre of gravity position near the front limit what will be the effect upon fuselage attitude and cyclic stick position, in a still air hover ?

Nose down, cyclic stick back.

exemple 518 Nose down, cyclic stick back. — . 2411

Question 278-37 : The principal forces acting on a helicopter in forward flight are ?

Main rotor thrust, weight, parasite drag and main rotor profile drag.

Question 278-38 : A nose down pitch attitude in forward flight is caused by ?

The horizontal component of total rotor thrust acting above parasite drag.

exemple 526 The horizontal component of total rotor thrust acting above parasite drag.

Question 278-39 : To increase forward speed in straight and level flight ?

Total rotor thrust must be increased.

exemple 530 Total rotor thrust must be increased.

Question 278-40 : The induced flow component of airflow through the rotor disc ?

Decreases with forward flight.

exemple 534 Decreases with forward flight.

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