From the following fuselage profile sort them from the worst to the best one concerning the pressurization 818 ?
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The illumination of the green landing gear light indicates that the landing gear is ?
The damping element in a landing gear shock absorber used on large aircrafts is ?
'nose wheel shimmy' may be described as A possibly damaging vibration of nose wheel when moving on ground, aircraft vibration caused the nose wheel upon extension of gear, oscillatory movement of nose wheel when extended prior to landing, amount of free movement of nose wheel before steering takes effect. 
The abs auto brake system being disconnected after landing By pilot action, automatically, at a certain low speed, system always armed. 1 auto brake disarm light illuminated (amber) speed brake lever moved to down detent during rto or landing manual brakes applied during rto or landing thrust lever(s) advanced during rto or landing except during first 3 seconds after touchdown landing landing made with rto selected rto mode selected on ground illuminates one to two seconds then extinguishes a malfunction exists in automatic braking system. extinguished auto brake select switch set to off autobrake armed. 2 auto brake select switch off autobrake system deactivated. 1, 2, 3, or max selects desired deceleration rate landing switch must be pulled out to select max deceleration. rto automatically applies maximum brake pressure when thrust levers are retarded to idle at or above 90 knots. 3 antiskid inoperative (antiskid inop) light illuminated (amber) a system fault detected antiskid monitoring system. extinguished antiskid system operating normally. 
The purposes of oil and nitrogen in an oleo pneumatic strut are The oil supplies damping function the nitrogen supplies spring function, oil supplies spring function the nitrogen supplies damping function, oil supplies sealing lubrication function, nitrogen supplies damping function, oil supplies damping lubrication function, nitrogen supplies heat dissipation function. 
The highest load on torsion link in a bogie gear Whilst turning on ground with a small radius, on touch down with a strong crosswind, when gear selected down, when braking with an inoperative anti skid system. Question Flight Controls 20 Answer 8
The function of a fusible plug to Protect tyre against explosion due to excessive temperature, protect brake against brake disk fusion due to excessive temperature, function as a special circuit breaker in electric system, protect against excessive pressure in pneumatic system. Question Flight Controls 20 Answer 9
Compared to a tyre fitted with an inner tube a tubeless tyre presents following characteristics 1 high heating2 valve fragility3 lower risk of bursting4 better adjustment to wheelsthe combination containing all correct statements 3 4, 2 4,, 2, 3 4, 2 3. Question Flight Controls 20 Answer 10
An under inflated tyre will Experience increased wear at shoulders, be more subject to viscous aquaplaning, have an increased hydroplaning speed, experience reduced wear at shoulders. Question Flight Controls 20 Answer 11
A scissor torsion link a component found on landing gears its function to Prevent any rotation of oleo strut in landing gear shock absorber, make body gears pivot when nosewheel turned through more than 2 °, transform translational movement of rudder pedals into rotational movement of nosewheel, create wheel pitch on bogie gears. The torque links prevent rotation about vertical axis to maintain wheel alignment in fore and aft direction throughout vertical range of oleo travel. in maintaining proper wheel alignment, torque links stabilize any torsional oscillations (shimmy). by their design, torque links have their maximum mechanical advantage control when oleo compressed, minimum advantage when oleo fully extended. sometime it doesn't work Question Flight Controls 20 Answer 12
Associate correct legend to each of numbered diagrams 841 cantilever 2fork 3half fork 4dual wheels,half fork 2single trace 3cantilever 4dual wheels,cantilever 2dual wheels 3half fork 4fork,half fork 2fork 3cantilever 4tandem Question Flight Controls 20 Answer 13
The function of an accumulator in a hydraulic brake system To supply a limited amount of brake energy in event of failure of hydraulic system normally supplying brakes, a damping accumulator designed to damp fluctuations of auto brake system, to store hydraulic energy recovered the anti skid system preventing wheel locking, to function as a buffer to assist hydraulic system during heavy braking. Question Flight Controls 20 Answer 14
A red or an amber light on an undercarriage position indicator signifies At least one wheel in travelling or unlocked condition, all wheels are up locked, all wheels are down locked, the landing has been selected down using emergency extension system. Question Flight Controls 20 Answer 15
In some aircraft there a protection device to avoid landing gear being inadvertently retracted on ground it consists of A latch located in landing gear lever, an aural warning horn, a warning light which activated the wow (weight on wheels) sensor system, a bolt. Question Flight Controls 20 Answer 16
Overcentre mechanisms in landing gear systems are used to Lock landing gear in up and/or down positions, lock landing gear in up position only, ensure that nose wheel does not exceed maximum steering arc, ensure nose wheel positioned fore aft prior to retraction. That naturally depends on type of aircraft. main undercarriage units are locked down mechanical overcentre geometric locks. hook locks are generally used the up position. Question Flight Controls 20 Answer 17
The systems used emergency extension of landing systems may comprise 1 compressed c0²2 compressed nitrogen3 compressed oxygen4 mechanical/manual system5 freefallthe combination containing all of correct statements 2, 4, 5,, 2, 5, 2, 3, 4,, 3, 4. Question Flight Controls 20 Answer 18
The working principle of anti skid system Reduction of brake pressure at slower turning wheels, reduction of brake pressure at faster turning wheels, increase of brake pressure at faster turning wheels, increase of brake pressure at slower turning wheels. Anti skid protection provided to allow maximum braking efficiency, which in turn minimizes landing distances. if pilot applies enough brake pedal force to cause slippage between tires the runway, wheel speed transducer data received a control box will indicate a sudden deceleration the slipping wheel. the control box will determine severity of impending skid send appropriate current signal to anti skid servo valve to reduce brake pressure accordingly. dual servo valves reduce pressure either brake independently. therefore, a single wheel skid will result in reduction of brake pressure at skidding wheel only. Question Flight Controls 20 Answer 19
Vle the maximum Flight speed with landing gear down, speed at which landing gear can be operated with full safety, speed with flaps extended in a given position, stall speed. Question Flight Controls 20 Answer 20
Vlo the maximum Speed at which landing gear can be operated with full safety, flight speed with landing gear down, speed with flaps extended in a given position, cruising speed not to be exceeded except in still air with caution. Question Flight Controls 20 Answer 21
What the correct statement about rudder deflection and steering nose When performing a rudder check during taxiing, an additional pilot action required to avoid deflection of nose wheel, steering nose movement completely achieved with rudder pedals as well as with hand wheel controller, for takeoff run hand wheel controller well suitable controlling aeroplane, rudder deflection steering movement are also interconnected during flight. Revised ecqb03, september 2016. during taxiing, if pilots want to use rudder pedals to check rudder deflection without interfering with steering, they have a pushbutton on either steering hand wheel (on a320) or tiller must be physically held so as to prevent aircraft from turning (for b737). the hand wheel controller (tiller) only suitable at beginning of take off roll. on a320, effectiveness of hand wheel diminished above 20 kt, is canceled above 80 kt. on b737, hand wheel controller was to be used under 60 kt. Question Flight Controls 20 Answer 22
To avoid risk of tyre burst from overheating there A thermal plug that deflates tyre at a specific temperature, 'emergency burst' function of anti skid system that adapts braking to tyre temperature, a pressure relief valve situated in filler valve, water injection triggered at a fixed temperature in order to lower tyre temperature. Question Flight Controls 20 Answer 23
Which of these statements about an anti skid system are correct or incorrect 1 in case of failure of an anti skid system auto brake system takes over regulation of slip ratio2 careful brake application the pilot in case of anti skid failure can never achieve same performance as a properly functioning anti skid system ) incorrect, 2) correct,) correct, 2) incorrect,) incorrect, 2) incorrect,) correct, 2) correct. Ecqb03, september 2016. the 'regulation of slip ratio' function of an anti skid system ensures optimum braking performance. in case of failure of anti skid system, auto brake system can not take over 'regulation of slip ratio'. careful brake application the pilot in case of anti skid failure can never achieve same performance as a properly functioning anti skid system. the anti skid system, through various mechanisms, compares speed of aircraft with rotational speed of each main wheel. if speed of any wheel too slow the existing aircraft speed, brake on that wheel (or wheels) released momentarily to allow wheel speed to increase prevent wheel from skidding. the system fully automatic is active from immediately after initial wheel spin up on landing (during which time brake activation might (or might not) be inhibited) down to a design limited minimum speed usually about 15 kt. anti skid systems are designed to minimise aquaplaning the potential tyre damage which can occur when a wheel locked or rotating at a speed which does not correspond to speed of aircraft. anti skid removes possibility of reverted rubber skids caused locked wheels. an anti skid system also greatly improves stopping distance on substandard surfaces such as gravel or grass is particularly effective on surfaces contaminated with frozen contaminants such as ice or slush ensuring maximum effective breaking. Question Flight Controls 20 Answer 24
Which of these statements about an anti skid system are correct or incorrect 1 the 'regulation of slip ratio' function of an anti skid system ensures optimum braking performance2 careful brake application the pilot in case of anti skid failure can achieve same performance as a properly functioning anti skid system ) correct, 2) incorrect,) incorrect, 2) correct,) incorrect, 2) incorrect,) correct, 2) correct. Ecqb03, september 2016. the 'regulation of slip ratio' function of an anti skid system ensures optimum braking performance. in case of failure of anti skid system, auto brake system can not take over 'regulation of slip ratio'. careful brake application the pilot in case of anti skid failure can never achieve same performance as a properly functioning anti skid system. the anti skid system, through various mechanisms, compares speed of aircraft with rotational speed of each main wheel. if speed of any wheel too slow the existing aircraft speed, brake on that wheel (or wheels) released momentarily to allow wheel speed to increase prevent wheel from skidding. the system fully automatic is active from immediately after initial wheel spin up on landing (during which time brake activation might (or might not) be inhibited) down to a design limited minimum speed usually about 15 kt. anti skid systems are designed to minimise aquaplaning the potential tyre damage which can occur when a wheel locked or rotating at a speed which does not correspond to speed of aircraft. anti skid removes possibility of reverted rubber skids caused locked wheels. an anti skid system also greatly improves stopping distance on substandard surfaces such as gravel or grass is particularly effective on surfaces contaminated with frozen contaminants such as ice or slush ensuring maximum effective breaking. Question Flight Controls 20 Answer 25
On diagram landing gear element indicated the number 11 842 Bogie beam, torque links, bogie pitch trimmer, retraction actuator. Question Flight Controls 20 Answer 26
Which statement correct concerning auto brake system When using manual braking during taxiing, auto brake system remains armed, when auto brake inoperative take off should not be allowed because manual braking does not support loads of emergency braking, when previously selected, landing distance will have a fixed value, when being used, auto brake ventilates brake fans. During rto or landing, auto brake system automatically disconnected when using manual braking, but not during taxiing. 1 auto brake disarm light illuminated (amber) speed brake lever moved to down detent during rto or landing manual brakes applied during rto or landing thrust lever(s) advanced during rto or landing except during first 3 seconds after touchdown landing landing made with rto selected rto mode selected on ground illuminates one to two seconds then extinguishes a malfunction exists in automatic braking system. extinguished auto brake select switch set to off autobrake armed. 2 auto brake select switch off autobrake system deactivated. 1, 2, 3, or max selects desired deceleration rate landing switch must be pulled out to select max deceleration. rto automatically applies maximum brake pressure when thrust levers are retarded to idle at or above 90 knots. 3 antiskid inoperative (antiskid inop) light illuminated (amber) a system fault detected antiskid monitoring system. extinguished antiskid system operating normally. Question Flight Controls 20 Answer 27
Which of these statements about an anti skid system are correct or incorrect 1 the 'regulation of slip ratio' function of an anti skid system ensures optimum braking performance2 careful brake application the pilot in case of anti skid failure can never achieve same performance as a properly functioning anti skid system ) correct, 2) correct,) incorrect, 2) correct,) correct, 2) incorrect,) incorrect, 2) incorrect. The 'regulation of slip ratio' function of an anti skid system ensures optimum braking performance. in case of failure of anti skid system, auto brake system can not take over 'regulation of slip ratio'. careful brake application the pilot in case of anti skid failure can never achieve same performance as a properly functioning anti skid system. the anti skid system, through various mechanisms, compares speed of aircraft with rotational speed of each main wheel. if speed of any wheel too slow the existing aircraft speed, brake on that wheel (or wheels) released momentarily to allow wheel speed to increase prevent wheel from skidding. the system fully automatic is active from immediately after initial wheel spin up on landing (during which time brake activation might (or might not) be inhibited) down to a design limited minimum speed usually about 15 kt. anti skid systems are designed to minimise aquaplaning the potential tyre damage which can occur when a wheel locked or rotating at a speed which does not correspond to speed of aircraft. anti skid removes possibility of reverted rubber skids caused locked wheels. an anti skid system also greatly improves stopping distance on substandard surfaces such as gravel or grass is particularly effective on surfaces contaminated with frozen contaminants such as ice or slush ensuring maximum effective breaking. Question Flight Controls 20 Answer 28
Which of these statements about an anti skid system are correct or incorrect 1 in case of failure of an anti skid system auto brake system takes over regulation of slip ratio2 careful brake application the pilot in case of anti skid failure can achieve same performance as a properly functioning anti skid system ) incorrect, 2) incorrect,) correct, 2) correct,) incorrect, 2) correct,) correct, 2) incorrect. The 'regulation of slip ratio' function of an anti skid system ensures optimum braking performance. in case of failure of anti skid system, auto brake system can not take over 'regulation of slip ratio'. careful brake application the pilot in case of anti skid failure can never achieve same performance as a properly functioning anti skid system. the anti skid system, through various mechanisms, compares speed of aircraft with rotational speed of each main wheel. if speed of any wheel too slow the existing aircraft speed, brake on that wheel (or wheels) released momentarily to allow wheel speed to increase prevent wheel from skidding. the system fully automatic is active from immediately after initial wheel spin up on landing (during which time brake activation might (or might not) be inhibited) down to a design limited minimum speed usually about 15 kt. anti skid systems are designed to minimise aquaplaning the potential tyre damage which can occur when a wheel locked or rotating at a speed which does not correspond to speed of aircraft. anti skid removes possibility of reverted rubber skids caused locked wheels. an anti skid system also greatly improves stopping distance on substandard surfaces such as gravel or grass is particularly effective on surfaces contaminated with frozen contaminants such as ice or slush ensuring maximum effective breaking. Question Flight Controls 20 Answer 29
Which of these statements about an auto brake system are correct or incorrect 1 an auto brake system can function properly even when anti skid system inoperative2 in rto mode maximum anti skid braking applied ) incorrect, 2) correct,) correct, 2) incorrect,) correct, 2) correct,) incorrect, 2) incorrect. Proper functioning of an auto brake system requires proper functioning of anti skid system. in rto (rejected take off) mode maximum anti skid braking applied. the 'regulation of slip ratio' function of an anti skid system ensures optimum braking performance. using rto mode provides best stopping performance during a rejected take off (the deceleration will not be constant, it will increase as speed decreases). Question Flight Controls 20 Answer 30
At take off rto mode rejected take off of an auto brake system disengages automatically When both air/ground systems indicate 'air' mode, from v , at 8kt, briefly pressing rudder pedals after takeoff. The rto mode automatically disarmed when both air/ground systems indicate air mode. Question Flight Controls 20 Answer 31
Rotor brake discs are manufactured from Steel or carbon fibre, aluminium or steel, steel or titanium, boron aluminide or titanium. Question Flight Controls 20 Answer 32
On diagram landing gear element indicated the number 3 fr_a_021 1056 err Shock absorber, retraction actuator, torque links, bogie beam. Please download diagram of a nose landing gear used as a reference at exam PDF 021_nose_landing_gear Question Flight Controls 20 Answer 33
If anti skid system inoperative may auto brake system can be used No, never, yes, without any limitation, yes, if selected to minimum, only if full reverse thrust used. Ecqb04, october 2017 anti skid system protection provided during auto brake operation, therefore, if anti skid inoperative you can not use auto brake system. Question Flight Controls 20 Answer 34
Shimmy occurs on nose wheel landing gear during taxiing when 1 wheels tend to describe a sinusoidal motion on ground2 wheels no longer respond to pilot's actions this effect overcome means of 3 torque link 4 an accumulator associated with steering cylinder the combination of correct statements , 4,, 3, 2, 4, 2, 3. shimmy of aircraft nose wheel landing gear a coupled lateral torsional dynamic instability that may occur during take off, taxi, landing. the potential shimmy often discovered when aircraft undergoes taxi (runway) tests. at this stage options available to designer are limited, often to introducing a damper in steering degree of freedom. >gxqnntxkyzm Question Flight Controls 20 Answer 35
Tyre 'creep' may be described as Circumferential movement of tyre in relation to wheel flange, increase in inflation pressure due to decrease in ambient temperature, decrease in inflation pressure due to increase in ambient temperature, gradual circumferential increase of tyre wear. Question Flight Controls 20 Answer 36
A single action actuator Is powered in one direction only hydraulic power, return movement being under spring force, travels one direction under one application of hydraulic power in opposite direction under a second application of hydraulic power, cannot be used variable position operations as it designed to lock in extremities of travel, is a one shot actuator used emergency systems only. Question Flight Controls 20 Answer 37
Axial piston pumps are often used in hydraulic systems due to Their ability to produce high pressure when required but can be off loaded to reduce power consumption, their low cost, simplicity durability, their ability to produce high pressure combined with constant high flow rate, the safety feature of quill drive shearing due to pump seizure the ease of repair replacement of pump shaft only. high pressure large flow are symptomatic of a hydraulic system. axial piston pumps can produce high pressure, but can be off loaded to reduce power consumption. Question Flight Controls 20 Answer 38
The trim tab Reduces hinge moment control surface efficiency, reduces hinge moment increases control surface efficiency, increases hinge moment control surface efficiency, increases hinge moment reduces control surface efficiency. The trim tab reduces hinge load because it uses tab to move control surface so there no external load imposed the pilot it reduces control surface effectiveness because it using part of control area trimming leaving less manoeuvre. Question Flight Controls 20 Answer 39
The purpose of a trim tab device to Reduce or to cancel control forces, trim aeroplane during normal flight, trim aeroplane at low airspeed, lower manoeuvring control forces. A trim tab a small, adjustable hinged surface on trailing edge of aileron, rudder, or elevator control surfaces. trim tabs are labour saving devices that enable pilot to release manual pressure on primary controls. some airplanes have trim tabs on all three control surfaces that are adjustable from cockpit others have them only on elevator rudder some have them only on elevator. some trim tabs are ground adjustable type only. the tab moved in direction opposite that of primary control surface, to relieve pressure on control wheel or rudder control. for example, consider situation in which we wish to adjust elevator trim level flight. ('level flight' the attitude of airplane that will maintain a constant altitude.) assume that back pressure required on control wheel to maintain level flight that we wish to adjust elevator trim tab to relieve this pressure. since we are holding back pressure, elevator will be in 'up' position. the trim tab must then be adjusted downward so that airflow striking tab will hold elevators in desired position. conversely, if forward pressure being held, elevators will be in down position, so tab must be moved upward to relieve this pressure. in this example, we are talking about tab itself not cockpit control. rudder aileron trim tabs operate on same principle as elevator trim tab to relieve pressure on rudder pedals sideward pressure on control wheel, respectively. Question Flight Controls 20 Answer 40
The advantages of fly wire control are 1 reduction of electric and hydraulic power required to operate control surfaces2 lesser sensitivity to lightning strike3 direct and indirect weight saving through simplification of systems4 immunity to different interfering signals5 improvement of piloting quality throughout flight envelopethe combination regrouping all correct statements The power required to operate control surfaces remains same. fly by wire (fbw) a system that replaces conventional manual flight controls of an aircraft with an electronic interface. the movements of flight controls are converted to electronic signals transmitted wires (hence fly by wire term), flight control computers determine how to move actuators at each control surface to provide ordered response. the fly by wire system also allows automatic signals sent the aircraft's computers to perform functions with or without pilot's input, as in systems that automatically help stabilize aircraft.
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