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Session > helipad : An artificial feel unit is necessary in the pitch channel when ?

Question 21-1 : The elevators are actuated by irreversible servo control units the elevators are actuated by reversible servo control units there is a trimmable stabilizer the elevators are fitted with servo tabs or trim tabs

Irreversible system fully powered system the pilot has no direct connection to the control surface he has no feel so an artificial feel system must be included this system works in parallel to the irreversible servo control unit.reversible system power assisted system similar to the power assisted steering for a car the pilot feel a part of the load he receives assistance from the hydraulic system to move the control surface exemple 121 the elevators are actuated by irreversible servo-control units.the elevators are actuated by irreversible servo-control units.

An artificial feel system ?

Question 21-2 : Functions in parallel to an irreversible servo control unit is necessary in a reversible flight control actuator unit functions in series to an irreversible servo control unit is mounted in parallel on a spring tab

Irreversible system fully powered system the pilot has no direct connection to the control surface he has no feel so an artificial feel system must be included this system works in parallel to the irreversible servo control unit.reversible system power assisted system similar to the power assisted steering for a car the pilot feel a part of the load he receives assistance from the hydraulic system to move the control surface exemple 125 functions in parallel to an irreversible servo-control unit.functions in parallel to an irreversible servo-control unit.

For most large aeroplanes spoilers are ?

Question 21-3 : Upper wing surface devices and their deflection can be symmetrical or asymmetrical lower wing surface devices and their deflection can be symmetrical or asymmetrical upper wing surface devices and their deflection is always asymmetrical lower wing surface devices and their deflection is always asymmetrical

exemple 129 upper wing surface devices and their deflection can be symmetrical or asymmetrical.upper wing surface devices and their deflection can be symmetrical or asymmetrical.

A krueger flap is normally located at the ?

Question 21-4 : Leading edge trailing edge trailing edge close to the wing tip trailing edge close to the wing root

847..a krueger flap is a leading edge flap and they are most of the time located at the wing root .krueger flap is high lift device it is hinged directly to the leading edge without any form of a slot exemple 133 leading edge.leading edge.

The expression 'primary flight control' applies to the.1 elevator.2 speed ?

Question 21-5 : 1 and 4 2 and 3 1 2 3 and 4 2 and 4

exemple 137 1 and 4.1 and 4.

Which of these statements about a gust lock system are correct or incorrect .i ?

Question 21-6 : I is correct ii is correct i is correct ii is incorrect i is incorrect ii is correct i is incorrect ii is incorrect

Irreversible system fully powered system the pilot has no direct connection to the control surface he has no feel so an artificial feel system must be included at stop the hydraulic actuators will be in hydraulic lock therefore the control surface will not move.reversible system power assisted system similar to the power assisted steering for a car the pilot feel a part of the load he receives assistance from the hydraulic system to move the control surface it is called 'reversible' because if someone moves the external surfaces the stick or control column moves inside the cockpit you need a gust lock systems inside the aircraft and outside. 848 exemple 141 i is correct, ii is correct.i is correct, ii is correct.

Which of these statements about a gust lock system are correct or incorrect .i ?

Question 21-7 : I is correct ii is correct i is correct ii is incorrect i is incorrect ii is correct i is incorrect ii is incorrect

Irreversible system fully powered system the pilot has no direct connection to the control surface he has no feel so an artificial feel system must be included at stop the hydraulic actuators will be in hydraulic lock therefore the control surface will not move.reversible system power assisted system similar to the power assisted steering for a car the pilot feel a part of the load he receives assistance from the hydraulic system to move the control surface it is called 'reversible' because if someone moves the external surfaces the stick or control column moves inside the cockpit you need a gust lock systems inside the aircraft and outside. 848..the suitable design is the red color with the famous 'remove before flight' tag exemple 145 i is correct, ii is correct.i is correct, ii is correct.

Which of these statements about rudder limiting are correct or incorrect .i a ?

Question 21-8 : I is correct ii is correct i is incorrect ii is incorrect i is correct ii is incorrect i is incorrect ii is correct

A rudder limiting system will reduce the deflection because as speed increases the force on the vertical stabilizer could be too strong and could lead to aircraft destruction.rudder ratio changer system limits excessive rudder deflection at high speed rudder movement is limited not the pedals movement.a variable stop system limits both rudder and rudder pedal deflection as the ias increases exemple 149 i is correct, ii is correct.i is correct, ii is correct.

Given a conventional transport aeroplane with irreversible flight controls on ?

Question 21-9 : The rudder moves the rudder pedals move in the corresponding direction the rudder trim tab moves and the rudder pedals do not move the 'zero force point' of the artificial feel system changes the rudder does not move the rudder moves the rudder pedals do not move

The information that the engines are running is important since it means that the hydraulic or electric actuators on the control surface are operating .concerning the rudder on the ground if the wind or an airport equipment moves the rudder the control surface located on the vertical stabilizer the pilot will feel this motion on the rudder pedals .concerning the rudder trim now the trim system will move the control surface but also the rudder pedals in order to be aware of the actual position of the control surface not only on the ground but also in flight exemple 153 the rudder moves, the rudder pedals move in the corresponding direction.the rudder moves, the rudder pedals move in the corresponding direction.

The function of the rudder limiter system is ?

Question 21-10 : To restrict rudder deflection during flight at high ias to limit pedal movement in heavy turbulence to restrict the rudder deflection during flight at mach numbers to reduce pilot's workload during engine failure

A rudder limiting system will reduce the deflection because as speed increases the force on the vertical stabilizer could be too strong and could lead to aircraft destruction.see causes of american airlines flight 587 crash .a pilot who has fully deflected rudder in both sides in high ias overloaded structure of plane which has fallen into the city killing all passengers and some people on ground . 849 exemple 157 to restrict rudder deflection during flight at high ias.to restrict rudder deflection during flight at high ias.

The expression 'secondary flight control' applies to the.1 elevator.2 speed ?

Question 21-11 : 2 3 1 2 3 4 2 4 1 4

In addition to the primary flight controls for roll pitch and yaw there are often secondary controls available to give the pilot finer control over flight or to ease the workload. the most commonly available control is a wheel or other device to control stabiliser trim so that the pilot does not have to maintain constant backward or forward pressure to hold a specific pitch attitude other types of trim for rudder and ailerons are common on larger aircraft but may also appear on smaller ones. many aircraft have wing flaps controlled by a switch or a mechanical lever or in some cases are fully automatic by computer control which alter the shape of the wing for improved control at the slower speeds used for takeoff and landing other secondary flight control systems may be available including slats spoilers and speed brakes exemple 161 2, 3.2, 3.

Control surface flutter can be avoided by.1 a high torsional stiffness of the ?

Question 21-12 : 1 3 2 4 1 4 2 3

Flutter is a divergent oscillatory motion of a control surface caused by the interaction of aerodynamic forces inertia forces and the stiffness of the structure it is a combination of bending and torsion of the structure. aero elastic coupling affects flutter characteristics . the risk of flutter increases as ias increases . if flutter occurs ias should be reduced . resistance to flutter increases with increasing wing stiffness exemple 165 1, 3.1, 3.

Primary flight controls are ?

Question 21-13 : Ailerons elevators and rudder control wheel or stick rudder pedals flap lever and throttle ailerons elevators rudder and flaps control wheel or stick rudder pedals and speed brake

exemple 169 ailerons, elevators and rudder.ailerons, elevators and rudder.

An aeroplane equipped with irreversible flight controls ?

Question 21-14 : Need not be equipped with a separate gust lock system does not require an artificial feel system may be equipped with simple spring type feel units on all flight controls must have a mechanical back up control system

Irreversible system fully powered system the pilot has no direct connection to the control surface he has no feel so an artificial feel system must be included this system works in parallel to the irreversible servo control unit.there is no need for a gust lock system on irreversible flight controls because the hydraulic actuators will be in hydraulic lock therefore the control surface will not move . 852.look at the left and right ailerons of this airbus a330 irreversible flight controls they both are down and in locked postion as for the elevator exemple 173 need not be equipped with a separate gust lock system.need not be equipped with a separate gust lock system.

An aeroplane equipped with irreversible flight controls ?

Question 21-15 : Requires an artificial feel system does not require an artificial feel system remains flyable even in the total lost of power in the flight control system must be equipped with control locks

Irreversible system fully powered system the pilot has no direct connection to the control surface he has no feel so an artificial feel system must be included this system works in parallel to the irreversible servo control unit.reversible system power assisted system similar to the power assisted steering for a car the pilot feel a part of the load he receives assistance from the hydraulic system to move the control surface exemple 177 requires an artificial feel system.requires an artificial feel system.

The automatic ground spoiler extension system is normally activated during ?

Question 21-16 : Main wheel spin up ground spoiler handle idle thrust selection brake pressure application

Ground spoiler automatic extension must be selected before landing speed brake lever must be in 'armed' position with the automatic speed brake system armed and upon touchdown the speed brake lever moves to the up position and all flight and ground spoilers extend.note if a wheel spin up signal is not detected when the air/ground system senses ground mode any gear strut compresses the speed brake lever moves to the up position and flight spoiler panels deploy automatically when the right main landing gear strut compresses a mechanical linkage opens the ground spoiler bypass valve and the ground spoilers deploy

Which of these statements about a gust lock system are correct or incorrect .i ?

Question 21-17 : I is incorrect ii is incorrect i is correct ii is correct i is correct ii is incorrect i is incorrect ii is correct

exemple 185 i is incorrect, ii is incorrect.i is incorrect, ii is incorrect.

Which of these statements about rudder limiting are correct or incorrect .i a ?

Question 21-18 : I is incorrect ii is incorrect i is correct ii is correct i is correct ii is incorrect i is incorrect ii is correct

A rudder limiting system will reduce the deflection because as speed increases the force on the vertical stabilizer could be too strong and could lead to aircraft destruction.rudder ratio changer system limits excessive rudder deflection at high speed rudder movement is limited not the pedals movement.a variable stop system limits both rudder and rudder pedal deflection as the ias increases

Which of these statements about a gust lock system are correct or incorrect .i ?

Question 21-19 : I is correct ii is incorrect i is incorrect ii is correct i is incorrect ii is incorrect i is correct ii is correct

Irreversible system fully powered system the pilot has no direct connection to the control surface he has no feel so an artificial feel system must be included at stop the hydraulic actuators will be in hydraulic lock therefore the control surface will not move.reversible system manual flight controls power assisted system similar to the power assisted steering for a car the pilot feel a part of the load he receives assistance from the hydraulic system to move the control surface it is called 'reversible' because if someone moves the external surfaces the stick or control column moves inside the cockpit you need a gust lock systems inside the aircraft and outside . 848 exemple 193 i is correct, ii is incorrect.i is correct, ii is incorrect.

Which of these statements about a gust lock system are correct or incorrect .i ?

Question 21-20 : I is correct ii is incorrect i is incorrect ii is correct i is incorrect ii is incorrect i is correct ii is correct

exemple 197 i is correct, ii is incorrect.i is correct, ii is incorrect.

Which of these statements about rudder limiting are correct or incorrect .i a ?

Question 21-21 : I is correct ii is incorrect i is incorrect ii is correct i is correct ii is correct i is incorrect ii is incorrect

A rudder limiting system will reduce the deflection because as speed increases the force on the vertical stabilizer could be too strong and could lead to aircraft destruction .rudder ratio changer system limits excessive rudder deflection at high speed rudder movement is limited not the pedals movement.a variable stop system limits both rudder and rudder pedal deflection as the ias increases exemple 201 i is correct, ii is incorrect.i is correct, ii is incorrect.

Which of these statements about a gust lock system are correct or incorrect .i ?

Question 21-22 : I is incorrect ii is correct i is incorrect ii is incorrect i is correct ii is incorrect i is correct ii is correct

exemple 205 i is incorrect, ii is correct.i is incorrect, ii is correct.

Which of these statements about a gust lock system are correct or incorrect .i ?

Question 21-23 : I is incorrect ii is correct i is incorrect ii is incorrect i is correct ii is correct i is correct ii is incorrect

exemple 209 i is incorrect, ii is correct.i is incorrect, ii is correct.

Which of these statements about trimming in a irreversible flight control ?

Question 21-24 : I is incorrect ii is correct i is incorrect ii is incorrect i is correct ii is incorrect i is correct ii is correct

Irreversible system fully powered system the pilot has no direct connection to the control surface he has no feel so an artificial feel system must be included this system works in parallel to the irreversible servo control unit.reversible system power assisted system similar to the power assisted steering for a car the pilot feel a part of the load he receives assistance from the hydraulic system to move the control surface.here we are talking about an irreversible flight control system.on a conventional aeroplane using an irreversible flight control system e g b737 ng with variable incidence trimming tailplane the trim is achieved by changing the full elevator deflection the zero force position of the control column does not change.for the aileron trim a variable incidence wing system does not exist on commercial airplane you can not 'trim' the wing thus when trimmed the control wheel will be biased to the right or to the left artificially and the zero force position of the control wheel will change exemple 213 i is incorrect, ii is correct.i is incorrect, ii is correct.

Which of these statements about rudder limiting are correct or incorrect .i a ?

Question 21-25 : I is incorrect ii is correct i is incorrect ii is incorrect i is correct ii is incorrect i is correct ii is correct

A rudder limiting system will reduce the deflection because as speed increases the force on the vertical stabilizer could be too strong and could lead to aircraft destruction.rudder ratio changer system limits excessive rudder deflection at high speed rudder movement is limited not the pedals movement.a variable stop system limits both rudder and rudder pedal deflection as the ias increases exemple 217 i is incorrect, ii is correct.i is incorrect, ii is correct.

Trimming of aileron and rudder in an irreversible flight control system ?

Question 21-26 : Is achieved by adjusting the 'zero force point' of the feel system is not necessary is not possible is achieved by adjusting the neutral point of the flight control actuator

Irreversible system fully powered system the pilot has no direct connection to the control surface he has no feel so an artificial feel system must be included this system works in parallel to the irreversible servo control unit.reversible system power assisted system similar to the power assisted steering for a car the pilot feel a part of the load he receives assistance from the hydraulic system to move the control surface.the question is about an irreversible flight control system there is no mechanical connection between control wheel or stick and ailerons rudder pedals and rudder the pilot is provided with artificial feel/force and when trimmed this is adjusted to give zero force on the control wheel or stick and the pedals exemple 221 is achieved by adjusting the 'zero force point' of the feel system.is achieved by adjusting the 'zero force point' of the feel system.

An aeroplane equipped with reversible flight controls ?

Question 21-27 : Does not require an artificial feel system need not be equipped with a separate gust lock system is equipped with simple spring type feel units does not have mechanical back up

exemple 225 does not require an artificial feel system.does not require an artificial feel system.

Most large conventional aeroplanes are not provided with aileron and rudder ?

Question 21-28 : Trimming is possible by adjusting the neutral point of the artificial feel mechanism by means of a trim switch no because without trim tabs trimming is not possible but trimming is only possible when the autopilot is engaged but trimming is only possible when before the flight the respective auxiliary surfaces are correctly adjusted for cruising conditions by the maintenance department

exemple 229 yes, trimming is possible by adjusting the neutral point of the artificial feel mechanism by means of a trim switch.yes, trimming is possible by adjusting the neutral point of the artificial feel mechanism by means of a trim switch.

On a large transport aeroplane the auto slat system ?

Question 21-29 : Extends part of the slats automatically when a certain value of angle of attack is exceeded provides for automatic slat retraction after take off ensures that the part of slats are always extended when the ground/flight system is in the 'ground' position assist the ailerons

The auto slat system is designed to enhance airplane stall characteristics at high angles of attack during takeoff or approach to landing. as the airplane approaches the stall angle the slats automatically begin driving to the full extended position prior to stick shaker activation the slats return to the extend position when the pitch angle is sufficiently reduced below the stall critical attitude exemple 233 extends (part of) the slats automatically when a certain value of angle of attack is exceeded.extends (part of) the slats automatically when a certain value of angle of attack is exceeded.

Most transport aeroplanes are provided with protection against control jamming ?

Question 21-30 : The flight control system has provisions to disconnect the part of the control system that becomes blocked the aeroplane is protected against the adverse effects of strong electromagnetic radiation seized brakes can be released from the cockpit in case of seizure engine control is taken over automatically by an alternate electric circuit

Fcom boeing 737 .the columns and wheels are connected through transfer mechanisms which allow the pilots to bypass a jammed control or surface. elevator control column override mechanism .in the event of a control column jam an override mechanism allows the control columns to be physically separated applying force against the jam will breakout either the captain's or first officer's control column whichever column moves freely after the breakout can provide adequate elevator control... aileron transfer mechanism .if the ailerons or spoilers are jammed force applied to the captain's and the first.officer's control wheels will identify which system ailerons or spoilers is usable.and which control wheel captain's or first officer's can provide roll control if the aileron control system is jammed force applied to the first officer's control wheel provides roll control from the spoilers the ailerons and the captain's control wheel are inoperative if the spoiler system is jammed force applied to the captain's control wheel provides roll control from the ailerons the spoilers and the first officer's control wheel are inoperative. rudder .the rudder provides yaw control about the airplane's vertical axis each set of rudder pedals is mechanically connected by cables to the input levers.of the main and standby rudder pcus the main pcu consists of two independent input rods two individual control valves and two separate actuators one for hydraulic system a and one for hydraulic system b the standby rudder pcu is controlled by a separate input rod and control valve and powered by the standby hydraulic system all three input rods have individual jam override mechanisms that allows input commands to continue to be transferred to the remaining free.input rods if an input rod or downstream hardware is hindered or jammed exemple 237 the flight control system has provisions to disconnect the part of the control system that becomes blocked.the flight control system has provisions to disconnect the part of the control system that becomes blocked.

A flight control surface actuator is said to be 'irreversible' when ?

Question 21-31 : There is no feedback to the pilot's controls of the aerodynamic forces acting on the control surface the pilot does not feel any force when moving that control surface in flight there is a need to lock the flight controls on the ground the flight control system has an alternate means of control in case of a control jam

An irreversible flight control system is where there is not a direct mechanical linkage connection between the control lever in the cockpit and the flight control surface in an irreversible mechanical system the control lever in the cockpit moves a spool valve on a hydraulic power control unit pcu. a mechanical linkage drives the spool the mechanical linkage will consist of a combination of bellcranks pushrods cable systems pogos summing linkages etc the design of a mechanical irreversible system is similar to the design of a reversible flight control system the main difference will be the spool forces are better defined than surface hinge moments. also an artificial feel system is required for irreversible flight control systems because there is no feedback to the pilot's controls of the aerodynamic forces acting on the control surface

Given an aeroplane with irreversible primary flight controls how is control ?

Question 21-32 : The remaining systems will take over control sufficient reserve hydraulic fluid is available to compensate the effects of the leak by switching the flight control system to the reversible mode by switching to manual back up mode

exemple 245 the remaining systems will take over control.the remaining systems will take over control.

Which of these statements about a gust lock system are correct or incorrect .i ?

Question 21-33 : I is incorrect ii is incorrect i is correct ii is incorrect i is correct ii is correct i is incorrect ii is correct

There is no need for a gust lock on irreversible flight controls because the hydraulic actuators will be in hydraulic lock therefore the control surface will not move. 852.look at the left and right ailerons of this airbus a330 irreversible flight controls they both are down and in locked postion as for the elevator. manual flight controls means reversible flight controls you need a gust lock systems inside the aircraft and outside . 848

The reason for a double switch on the elevator trim is ?

Question 21-34 : To reduce the probability of a trim runaway to prevent both pilots from performing opposite trim inputs because there are two trim motors to be able to use two different trim speeds slow trim rate at high speed and high trim rate at low speed

exemple 253 to reduce the probability of a trim runaway.to reduce the probability of a trim runaway.

A flight control surface actuator is said to be 'reversible' when ?

Question 21-35 : There is feedback to the pilot's controls of the aerodynamic forces acting on the control surface the pilot does not feel any force when moving that flight control surface in flight there is a need to have an artificial feel system the flight control system has an alternate means of control in case of a control jam

exemple 257 there is feedback to the pilot's controls of the aerodynamic forces acting on the control surface.there is feedback to the pilot's controls of the aerodynamic forces acting on the control surface.

For a jar25 aeroplane spoilers are ?

Question 21-36 : Upper wing surface devices their deflection can be symmetrical or asymmetrical lower wing surface devices their deflection can be symmetrical or asymmetrical upper wing surface devices their deflection is always asymmetrical lower wing surface devices their deflection is always asymmetrical

exemple 261 upper wing surface devices, their deflection can be symmetrical or asymmetrical.upper wing surface devices, their deflection can be symmetrical or asymmetrical.

Which of these statements regarding most gust lock systems is correct ?

Question 21-37 : When the gust lock is on there is protection to prevent take off a gust lock is only fitted on the elevator and the rudder a gust lock can be used in flight to reduce the effect of turbulence on reversible flight controls there is no need for a gust lock

exemple 265 when the gust lock is on there is protection to prevent take-off.when the gust lock is on there is protection to prevent take-off.

The expression 'secondary flight control' applies to the.1 stabiliser.2 ?

Question 21-38 : 1 3 1 2 3 4 2 4 2 3

In addition to the primary flight controls for roll pitch and yaw there are often secondary controls available to give the pilot finer control over flight or to ease the workload the most commonly available control is a wheel or other device to control stabiliser trim so that the pilot does not have to maintain constant backward or forward pressure to hold a specific pitch attitude other types of trim for rudder and ailerons are common on larger aircraft but may also appear on smaller ones. many aircraft have wing flaps controlled by a switch or a mechanical lever or in some cases are fully automatic by computer control which alter the shape of the wing for improved control at the slower speeds used for takeoff and landing other secondary flight control systems may be available including slats spoilers and air brakes exemple 269 1, 3.1, 3.

Ruddertrim adjustment in an aeroplane with irreversible flight controls is ?

Question 21-39 : An adjustment of the zero force rudder position an adjustment of the rudder ratio changer an adjustment of the rudder trim tab unnecessary because this aeroplane does not need rudder trim

.your flight controls are subjected to aerodynamic forces light aircraft will always have trim for the elevator to reduce these forces but as you climb out at low speed and high power you will have to apply a lot of leg force and hold in a lot of rudder right rudder on most aircraft due to right hand rotation of the propeller if you had a rudder trim you would adjust it until the force was zero.the question is about a fully powered rudder control irreversible there is no mechanical connection between rudder pedals and rudder the pilot is provided with artificial feel/force and when trimmed this is adjusted to give zero force on the pedals a conventional trim tab would have no feedback to the pilot because of the design of irreversible controls exemple 273 an adjustment of the zero force rudder position.an adjustment of the zero force rudder position.

Which of these statements about trimming in a irreversible flight control ?

Question 21-40 : I is correct ii is correct i is incorrect ii is incorrect i is correct ii is incorrect i is incorrect ii is correct

.irreversible system fully powered system the pilot has no direct connection to the control surface he has no feel so an artificial feel system must be included this system works in parallel to the irreversible servo control unit.reversible system power assisted system similar to the power assisted steering for a car the pilot feel a part of the load he receives assistance from the hydraulic system to move the control surface.here we are talking about an irreversible flight control system.on a conventional aeroplane using an irreversible flight control system e g b737 ng with variable incidence trimming tailplane the trim is achieved by changing the full elevator deflection the zero force position of the control column does not change.for the aileron trim a variable incidence wing system does not exist on commercial airplane you can not 'trim' the wing thus when trimmed the control wheel will be biased to the right or to the left artificially and the zero force position of the control wheel will change exemple 277 i is correct, ii is correct.i is correct, ii is correct.

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