On the ground during a right turn the turn indicator indicates ?
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Other study patent: Telepilote theorique examen 48
On the ground during a left turn the turn indicator indicates ?
When in flight the needle and ball of a needle and ball indicator are on the left the aircraft is ?
When in flight needle and ball of a needle and ball indicator are on right aircraft Turning right with too much bank. 
When in flight needle of a needle and ball indicator on right and ball on left aircraft Turning right with not enough bank. 
When in flight needle of a needle and ball indicator on left and ball on right aircraft Turning left with not enough bank. 
A stand horizon or emergency attitude indicator Contains its own separate gyro. Question 48-8
In building principle of a gyroscope best efficiency obtained through concentration of mass On periphery with a high rotational speed. Question 48-9
The diagram representing a left turn with insufficient rudder 1045 On periphery with a high rotational speed. fgabrys i'm pretty sure that correct answer n°3 diagram n°4 represents a left turn with too much rudder in a slipping turn ball will be displaced in direction of turn (in opposite direction a skidding turn) you now have two solutions push on left rudder pedal or decrease bank angle. Question 48-10
The maximum directional gyro error due to earth rotation On periphery with a high rotational speed. apparent drift due to earth's rotation is 15° x sin (latitude) in degrees per hour the latitude in this case the latitude of actual position of aircraft for latitude change (flight north or south) take mean aircraft latitude the period involved. Question 48-11
Heading information given a gyro platform given a gyro at 2 degrees of freedom in horizontal axis. A directional gyro consists of a 2 degrees of freedom horizontal axis gyro it must be aligned corrected the pilot (drift due to earth's rotation transport wander). Question 48-12
Among systematic errors of 'directional gyro' error due to earth rotation make north reference turn in horizontal plane at a mean latitude of 45°n this reference turns 5°/hour to right. earth rate 15°/h at 45°north earth rate 15°/h x sin 45° = 10 6°/h in northern hemisphere gyro drifting at a rate of 15°/h to right (the heading increases). Question 48-13
A turn indicator an instrument which indicates rate of turn rate of turn depends upon 1 bank angle 2 aeroplane speed 3 aeroplane weight the combination regrouping correct statements 5°/hour to right. earth rate 15°/h at 45°north earth rate 15°/h x sin 45° = 10 6°/h in northern hemisphere gyro drifting at a rate of 15°/h to right (the heading increases). Question 48-14
The diagram which shows a 40° left bank and 15° nose down attitude number 1046 5°/hour to right. your aircraft seen from behind. Question 48-15
The heading read on dial of a directional gyro subject to errors one of which due to movement of aircraft this error Is dependent on ground speed of aircraft its true track the latitude of flight. buhoraptor and if it on equator ? the error depends upon position of aircraft on earth the drift error = 0 at equator but this not what question states the question states that apparent drift error depends on ground speed true track the latitude even if it on equator if resulting error zero. Question 48-16
A gravity erector system used to correct errors on An artificial horizon. buhoraptor and if it on equator ? the error depends upon position of aircraft on earth the drift error = 0 at equator but this not what question states the question states that apparent drift error depends on ground speed true track the latitude even if it on equator if resulting error zero. Question 48-17
During a deceleration phase at constant attitude control system of an air driven artificial horizon results in horizon bar indicating a An artificial horizon. errors in the artificial horizon (suction) acceleration errors (linear acceleration) these errors are also known as 'takeoff' errors as they are most noticeable during takeoff two elements cause errors pendulous unit vanes error from the pendulous unit the pendulous unit makes rotor bottom heavy as aircraft accelerates a force from inertia of unit felt at bottom the unit tends to lag behind it tends to swing bottom of gyro towards pilot air driven rotors spin anti clockwise (when viewed from above) so this inertial force will precess through 90° in an anti clockwise direction lifting up right hand side of outer gimbal the skyplate attached to outer gimbal rotates in an anti clockwise direction lifting up right hand side of outer gimbal the skyplate attached to outer gimbal rotates anti clockwise and bank indicates a false right bank error from exhaust vanes during acceleration vanes on right left sides are thrown rearward the result that right hand port more than half open the left side port more than half closed this upsets balanced exhaust of air more air being discharged from right side than from left side the reaction occurs on left side precesses through 90° and lifts up inner gimbal from point nearest pilot to indicate a false climb thus with gyro running anti clockwise a slight indication of right bank climb are obtained during an acceleration. Question 48-18
In a directional gyro gimballing errors are due to An artificial horizon. the term 'gimballing error' used to describe errors which occur when gyro has reached its physical limit in pitch or roll any gimballing errors are due to banked attitudes will disappear after turn complete. Question 48-19
Parallax error An artificial horizon. the ball centered parallax error due to a reading under an oblique angle. Question 48-20
The apparent wander of a directional gyro 15°/h An artificial horizon. 15°/h at poles 0° at equator. Question 48-21
The artificial horizon uses a gyroscope with note degree s of freedom of a gyro does not take into account its rotor spin axis Two degrees of freedom its rotor spin axis continuously maintained to local vertical an automatic erecting system. 15°/h at poles 0° at equator. Question 48-22
The inertia of a gyroscope greater when its rotation speed Higher the mass of spinning wheel located further from axis of rotation. 15°/h at poles 0° at equator. Question 48-23
The rate of turn indicator uses a gyroscope 1 spinning wheel axis of which parallel to yawing axis2 spinning wheel axis of which parallel to pitch axis3 spinning wheel axis of which parallel to roll axis4 with one degree of freedom5 with two degrees of freedomthe combination regrouping all correct statements nb degree s of freedom of a gyro does not take into account its rotor spin axis Higher the mass of spinning wheel located further from axis of rotation. the spin axis of turn indicator gyro aligned along pitch axis (lateral axis) the number of independent ways which a dynamical system can move without violating any constraint imposed on it called degree of freedom the gyro in turn and slip indicator rotates in vertical plane (one degree of freedom only) corresponding to airplane's longitudinal axis a single gimbal limits planes in which gyro can tilt a spring tries to return it to center. Question 48-24
The latitude at which apparent wander of a directional gyro equal to 0 Higher the mass of spinning wheel located further from axis of rotation. 15°/h at poles 0° at equator. Question 48-25
The gyroscope used in an attitude indicator has a spin axis which Higher the mass of spinning wheel located further from axis of rotation. 15°/h at poles 0° at equator. Question 48-26
For an aircraft flying a true track of 360° between 5°s and 5°n parallels precession error of directional gyro due to apparent drift equal to Approximately °/hour. 15°/h at poles 0° at equator. Question 48-27
A rate gyro used in a 1 directional gyro indicator2 turn co ordinator3 artificial horizonthe combination regrouping all correct statements Approximately °/hour. an instrument which measures rate of rotation of an object about an axis a spinning gyroscope precesses or tilts when it rotated in a plane at right angles to its own spin axis the amount gyroscope tilts proportional to rate at which it rotated about an axis at right angles to both its spin axis the axis of its precession (the axis about which it tilts) rate gyros are used in turn slip indicators turn coordinators the spin axis of turn indicator gyro aligned along pitch axis (lateral axis) of aircraft. Question 48-28
A directional gyro consists of a nb degree s of freedom of a gyro does not take into account its rotor spin axis 2 degrees of freedom horizontal axis gyro. an instrument which measures rate of rotation of an object about an axis a spinning gyroscope precesses or tilts when it rotated in a plane at right angles to its own spin axis the amount gyroscope tilts proportional to rate at which it rotated about an axis at right angles to both its spin axis the axis of its precession (the axis about which it tilts) rate gyros are used in turn slip indicators turn coordinators the spin axis of turn indicator gyro aligned along pitch axis (lateral axis) of aircraft. Question 48-29
The spin axis of turn indicator gyro aligned along Lateral axis of aircraft. The spin axis of turn indicator gyro aligned along pitch axis (lateral axis) . Question 48-30
The properties of a gyroscope are 1 rigidity in space 2 rigidity on earth 3 precession 4 schuler oscillations the combination regrouping all correct statements Lateral axis of aircraft. The spin axis of turn indicator gyro aligned along pitch axis (lateral axis) . Question 48-31
The rate of turn given the rate of turn indicator valid For airspeed range defined during calibration of instrument. The spin axis of turn indicator gyro aligned along pitch axis (lateral axis) . Question 48-32
Without any external action axis of a free gyroscope fixed with reference to For airspeed range defined during calibration of instrument. The spin axis of turn indicator gyro aligned along pitch axis (lateral axis) . Question 48-33
Due to rotation of earth apparent drift of a horizontal free gyroscope at a latitude of 45°n ° per hour to right. Earth rate 15°/h at 45°north earth rate 15°/h x sin 45° = 10 6°/h in northern hemisphere gyro drifting at a rate of 15°/h to right (the heading increases). Question 48-34
Due to rotation of earth apparent drift of a horizontal free gyroscope at a latitude of 30°s 7 5° per hour to left. Earth rate 15°/h at 30°south earth rate 15°/h x sin 30° = 7 5°/h in southern hemisphere gyro drifting at a rate of 15°/h to left (the heading decreases). Question 48-35
Due to rotation of earth apparent drift of a horizontal free gyroscope at a latitude of 30°n 7 5° per hour to right. Earth rate 15°/h at 30°north earth rate 15°/h x sin 30° = 7 5°/h in northern hemisphere gyro drifting at a rate of 15°/h to right (the heading increases). Question 48-36
A free gyro has axis of spinning rotor horizontal and aligned with geographic meridian if this free gyro situated at latitude 60°n apparent drift rate according to earthbound observer 7 5° per hour to right. earth rate 15°/h at 60°north earth rate 15°/h x sin 60° = 13°/h in northern hemisphere gyro drifting at a rate of 15°/h to right (the heading increases) kn0027 in northern hemisphere earth rate causes dgi indication to decrease not increase 15sin(lat) this would appear to show a turn to left in northern hemisphere earth rotation which our only consideration negative which means readings will decrease due to apparent drift when viewed from top compass card will appear to have turned clockwise which right where as anti clockwise considered left. Question 48-37
For a directional gyro system which detects local vertical supplies A levelling erection torque motor. the question refers to a gyro compass levelling system a gyro compass nothing more than a sophisticated direction indicator the aim of game to keep gyro spin axis horizontal with reference to gravity acting on a pendulum if we take each answer in turn a torque motor on sensitive axis gyro has two degrees of freedom which gives two sensitive axes not one two torque motors arranged horizontally only one torque motor required to keep spin axis horizontal a nozzle integral with outer gimbal ring in an air driven system twin air jets are used not a single nozzle a levelling erection torque motor a single torque motor inducing topple in vertical plane to keep gyro spin axis horizontal. Question 48-38
A directional gyro corrected an apparent drift due to earth's rotation at latitude 30°s during a flight at latitude 60°n a drift rate of 15 5°/h to right observed the apparent wander due to change of aircraft position A levelling erection torque motor. earth rate 15°/h if gyro had been corrected at 30°south latitude nut would have been adjusted 15 x sin 30 = 7 5°/h at 60°north earth rate should be 15 sin 60° = 13° 13° + ( 7 5) = 20 5° the gyro drifting at a rate of 15 5° to right apparent wander due to change of aircraft position is 20 5 + 15 5 = 5° to left. Question 48-39
A control system consisting of four pendulous vanes used in An air driven artificial horizon. air driven artificial horizon the rotor mounted in a sealed housing spins in a horizontal plane about vertical axis the housing pivots about lateral axis on a gimbal which in turn free to pivot about longitudinal axis the instrument case the third gimbal necessary universal mounting the horizon bar linked to gyro a lever attached to a pivot on rear of gimbal frame connected to gyro housing a guide pin when attitude indicator in operation gyroscopic rigidity maintains horizon bar parallel to natural horizon when pitch or bank attitude of aircraft changes miniature aircraft being fixed to case moves with it these movements of instrument case with respect to gyro are shown on face of instrument as pitch bank attitude changes of miniature aircraft with respect to horizon bar air sucked through filter then through passages in rear pivot inner gimbal ring then into housing where it directed against rotor vanes through two openings on opposite sides of rotor the air then passes through four equally spaced ports in lower part of rotor housing is sucked out into vacuum pump or venturi tube the chamber containing ports the erecting device that returns spin axis to its vertical alignment whenever a precessing force such as friction displaces rotor from its horizontal plane the four exhaust ports are each half covered a pendulous vane which allows discharge of equal volumes of air through each port when rotor properly erected any tilting of rotor disturbs total balance of pendulous vanes tending to close one vane of an opposite pair while opposite vane opens a corresponding amount the increase in air volume through opening port exerts a precessing force on rotor housing to erect gyro the pendulous vanes return to a balanced condition acceleration deceleration induce precession errors depending upon amount extent of force applied during acceleration horizon bar moves down indicating a climb control applied to correct this indication will result in a pitch attitude lower than instrument shows the opposite error results from deceleration other errors such as 'transport precession' 'apparent precession' relate to rotation of earth are of importance to pilots navigators concerned with high speed long range flight. Question 48-40
Considering an air driven artificial horizon when an airplane accelerates during take off r the result A false nose up indication. errors in the artificial horizon (suction) acceleration errors (linear acceleration) these errors are also known as 'takeoff' errors as they are most noticeable during takeoff two elements cause errors pendulous unit vanes error from the pendulous unit the pendulous unit makes rotor bottom heavy as aircraft accelerates a force from inertia of unit felt at bottom the unit tends to lag behind it tends to swing bottom of gyro towards pilot air driven rotors spin anti clockwise (when viewed from above) so this inertial force will precess through 90° in an anti clockwise direction lifting up right hand side of outer gimbal the skyplate attached to outer gimbal rotates in an anti clockwise direction lifting up right hand side of outer gimbal the skyplate attached to outer gimbal rotates anti clockwise and bank indicates a false right bank error from exhaust vanes during acceleration vanes on right left sides are thrown rearward the result that right hand port more than half open the left side port more than half closed this upsets balanced exhaust of air more air being discharged from right side than from left side the reaction occurs on left side precesses through 90° and lifts up inner gimbal from point nearest pilot to indicate a false climb thus with gyro running anti clockwise a slight indication of right bank climb are obtained during an acceleration.
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