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Quiz > landing : Considering an air driven artificial horizon when an airplane decelerates on ?

Question 49-1 : A false nose down indication a false nose up indication a correct and constant pitch indication a right or left wing down indication depending on the runway direction

.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 the errors. the pendulous unit.. the vanes...error from the pendulous unit.the pendulous unit makes the rotor bottom heavy.as the aircraft accelerates a force from inertia of the unit is felt at the bottom and the unit tends.to lag behind it tends to swing the bottom of the gyro towards the 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 the right hand side of the outer gimbal.the skyplate attached to the outer gimbal rotates in an anti clockwise direction lifting up the right.hand side of the outer gimbal the skyplate attached to the outer gimbal rotates anti clockwise.and the bank indicates a false right bank...error from exhaust vanes.during acceleration the vanes on the right and left sides are thrown rearward.the result is that the right hand port is more than half open and the left side port is more than.half closed this upsets the balanced exhaust of air more air being discharged from the right.side than from the left side the reaction occurs on the left side and precesses through 90° and.lifts up the inner gimbal from the point nearest the pilot to indicate a false climb.thus with the gyro running anti clockwise a slight indication of right bank and climb are obtained.during an acceleration exemple 149 a false nose-down indication.a false nose-down indication.

Concerning the directional gyro the apparent drift rate due to the earth's ?

Question 49-2 : Latitude longitude latitude and longitude magnetic longitude

exemple 153 latitude.latitude.

The spin axis of the turn indicator gyroscope is parallel to the ?

Question 49-3 : Pitch axis roll axis yaw axis longitudinal axis

exemple 157 pitch axis.pitch axis.

Parallax error is due to ?

Question 49-4 : A reading under an oblique angle temperature pressure aircraft accelerations

. 1002.the ball is centered parallax error is due to a reading under an oblique angle exemple 161 a reading under an oblique angle.a reading under an oblique angle.

What angle of bank should you adopt on the attitude indicator for a standard ?

Question 49-5 : 18° 36° 12° 30°

.the rate of turn is the number of degrees your heading changes in a period of time usually one second or one minute .a standard rate turn 'rate 1' typically spoken of in terms of instrument flight is performed at 180 degrees of heading change in a one minute period 3° per second this gives a complete 360° turn in two minutes.a convenient approximation for the bank angle in degrees is taking 15% of ias.15% of 120 kt = 18 exemple 165 18°.18°.

The term drift refers to the wander of the axis of a gyro in ?

Question 49-6 : Horizontal plane any plane vertical plane vertical and horizontal plane

.for information .drift is the wander in the horizontal plane .topple is the wander in the vertical plane exemple 169 horizontal plane.horizontal plane.

What causes a freely suspended space gyroscope to precess ?

Question 49-7 : The gyro will precess when a force is applied to the spinning rim of the gyroscope in the same direction as the axis of rotation a turning force applied around the axis of rotation there is a tendency to precess when force is applied at 90 degrees to the axis of rotation a turning force applied against the axis of rotation

exemple 173 the gyro will precess when a force is applied to the spinning rim of the gyroscope in the same direction as the axis of rotation.the gyro will precess when a force is applied to the spinning rim of the gyroscope in the same direction as the axis of rotation.

While inertial platform system is operating on board an aircraft it is ?

Question 49-8 : With damping and a period of about 84 minutes without damping and a period of about 84 minutes without damping and a period of about 84 seconds with damping and a period of 84 seconds

Schuler oscillations have a period of 84 4 minutes and are damped out .when a gyro stabilised platform is moved over the surface of the earth the gyro control system moves it to the local horizontal but it ends up oscillating about the new horizontal schuler figured that it would act as if it was swinging about at the end of a pendulum the period of oscillation of a pendulum depends on the square root of its length and schuler suggested that it would swing about as if the length of the pendulum was the radius of the earth and that gives us a period of oscillation of 84 4 minutes exemple 177 with damping and a period of about 84 minutes.with damping and a period of about 84 minutes.

In order to align an irs it is required to insert the local geographical ?

Question 49-9 : 1 3 1 2 2 3 1 2 3

Compared with a conventional gyro a laser gyro ?

Question 49-10 : Has a longer life cycle consumes a lot of power is influenced by temperature has a fairly long starting cycle

Laser gyros are used in inertial reference systems and use a partially silvered mirror and 2 contra rotating laser beams that go the opposite direction to each other .compared with a conventional gyro a laser gyro is more accurate and has a longer life cycle because there are no moving parts and therefore no friction exemple 185 has a longer life cycle.has a longer life cycle.

The mode selector of an inertial unit comprises the off stby align nav att ?

Question 49-11 : 4 2 5 1 3 5 1 2 4

The principle of a laser gyro is based on ?

Question 49-12 : Frequency difference between two laser beams rotating in opposite direction a gyroscope associated with a laser compensating for apparent wander due to the rotation of the earth a gyroscope associated with a laser compensating for gimballing errors two rotating cavities provided with mirrors

Two light beams travelling a different distance in the same time because of rotation of the device rate of rotation is proportional to phase difference exemple 193 frequency difference between two laser beams rotating in opposite direction.frequency difference between two laser beams rotating in opposite direction.

As a result of the failure of the adc the inertial navigation system ins will ?

Question 49-13 : Wind direction and speed time at the next waypoint wpt ground speed drift

.ins by itself does not know wind direction and velocity it only knows ground speed using true airspeed tas from an air data source they can easily calculate wind .the ins get data tas and altitude from an air data computer .from position ins can provide information about drift and can compute time at the next waypoint exemple 197 wind direction and speed.wind direction and speed.

In order to align an inertial reference system irs it is required to insert ?

Question 49-14 : Compare the latitude it finds with that entered by the operator compare the longitude it finds with that entered by the operator find true north initialise the fms flight plan

exemple 201 compare the latitude it finds with that entered by the operator.compare the latitude it finds with that entered by the operator.

Compared with a conventional gyro a laser gyro ?

Question 49-15 : Is much more cumbersome is influenced by temperature consumes much more power consumes a lot of power

exemple 205 is much more cumbersome.is much more cumbersome.

The operating principle of an inertial system consists in ?

Question 49-16 : Measuring the acceleration of the aircraft and performing integrations to elaborate the ground speed and the position measuring the acceleration speed and position of the aircraft measuring the position of the aircraft and performing integrations to elaborate the ground speed and acceleration measuring the earth rotation and performing integrations to elaborate the aircraft ground speed and position

.the ins measures accelerations north/south and accelerations east/west which go through two integrations to give distance travelled north/south and east/west from initial position and distances travelled north/south and east/west it computes present position and from change of position it computes track and ground speed exemple 209 measuring the acceleration of the aircraft and performing integrations to elaborate the ground speed and the position.measuring the acceleration of the aircraft and performing integrations to elaborate the ground speed and the position.

Compared with a stabilised platform inertial system a strapdown inertial system ?

Question 49-17 : 2 3 1 2 3 1 2 3

exemple 213 2, 3.2, 3.

In an inertial navigation system to know the distance travelled ?

Question 49-18 : Integrating once the speed in time is sufficient it is necessary to integrate once the speed in time and to know the initial speed only it is necessary to integrate once the speed in time and to know the initial position only it is necessary to integrate once the speed in time and to know the initial speed and the initial position

.distance travelled = speed x time.and in the 'integrating once the speed in time is sufficient' is just the formula exemple 217 integrating once the speed in time is sufficient.integrating once the speed in time is sufficient.

To obtain the instantaneous speed from the accelerations ?

Question 49-19 : It is necessary to integrate the acceleration once in time and to know the initial speed only it is necessary to integrate the acceleration once in time and to know the initial position only it is necessary to integrate the acceleration once in time and to know the initial speed and the initial position integrating the acceleration once in time is sufficient

exemple 221 it is necessary to integrate the acceleration once in time, and to know the initial speed only.it is necessary to integrate the acceleration once in time, and to know the initial speed only.

To obtain the instantaneous position from the accelerations ?

Question 49-20 : It is necessary to integrate twice the acceleration in time and to know the initial position and the initial speed it is necessary to integrate twice the acceleration in time and to know the initial position only it is necessary to integrate twice the acceleration in time and to know the initial speed only integrating twice acceleration in time is sufficient

exemple 225 it is necessary to integrate twice the acceleration in time, and to know the initial position and the initial speed.it is necessary to integrate twice the acceleration in time, and to know the initial position and the initial speed.

In a inertial navigation system the integration process makes a ?

Question 49-21 : Time multiplication time division distance multiplication distance division

.acceleration x time = change of speed.speed x time = distance travelled exemple 229 time multiplication.time multiplication.

If the acceleration of an aircraft is zero its velocity ?

Question 49-22 : Is constant will decrease is always zero will increase

exemple 233 is constant.is constant.

The time for a normal alignment not a quick alignment of a strapdown inertial ?

Question 49-23 : 3 to 10 minutes 1 to 2 minutes less than 1 minute 15 to 20 minutes

.a rapid self alignment of a strapdown inertial system irs can be performed in less than 10 minutes inertial reference systems with laser gyro has caused a technological revolution in the design of inertial reference and navigation systems this solid state high precision angular rate sensor is ideally suited for highly reliable strap down system configuration .it eliminates the need for gimbals bearings torque motors and other moving parts and consequently changes the system operation considerably from conventional inertial navigation systems ins exemple 237 3 to 10 minutes.3 to 10 minutes.

The position error of a stand alone inertial system is approximately ?

Question 49-24 : 0 5 to 2 nm per hour 0 01 to 0 2 nm per hour 6 to 8 nm per hour 8 to 10 nm per hour

The output data of an irs include.1 attitude.2 altitude.3 present position ?

Question 49-25 : 1 3 1 2 3 1 3 4 1 2 3 4

.in their normal navigation mode the irss provide attitude true and magnetic heading acceleration vertical speed ground speed track present position and wind data to appropriate airplane systems irs outputs are independent of external navigation aids exemple 245 1, 3.1, 3.

The alignment sequence of an irs consists of.1 searching for the local ?

Question 49-26 : 1 2 et 4 2 et 3 1 2 et 3 1 et 3

The output data of an irs include .1 present position lat long .2 total ?

Question 49-27 : 1 4 1 3 1 2 4 2 3

.in their normal navigation mode the irss provide attitude true and magnetic heading acceleration vertical speed ground speed track present position and wind data to appropriate airplane systems irs outputs are independent of external navigation aids exemple 253 1, 4.1, 4.

The output data of an irs include .1 satellites status.2 altitude.3 drift ?

Question 49-28 : 3 4 1 3 4 4 2 4

.in their normal navigation mode the irss provide attitude true and magnetic heading acceleration vertical speed ground speed track present position and wind data to appropriate airplane systems irs outputs are independent of external navigation aids exemple 257 3, 4.3, 4.

The output data of an irs include .1 angle of attack.2 altitude.3 ground ?

Question 49-29 : 3 1 3 1 2 2

.in their normal navigation mode the irss provide attitude true and magnetic heading acceleration vertical speed ground speed track present position and wind data to appropriate airplane systems irs outputs are independent of external navigation aids exemple 261 3.3.

The output data of an irs include .1 number of satellites tracked.2 mach ?

Question 49-30 : 3 4 1 4 2 3 1 2 3 4

.in their normal navigation mode the irss provide attitude true and magnetic heading acceleration vertical speed ground speed track present position and wind data to appropriate airplane systems irs outputs are independent of external navigation aids such as satellite the adc air data computer will compute the mach number exemple 265 3, 4.3, 4.

To obtain the instantaneous position from the accelerations it is necessary ?

Question 49-31 : 1 2 3 1 1 2 1 3

exemple 269 1, 2, 3.1, 2, 3.

To obtain the instantaneous speed from the accelerations it is necessary to.1 ?

Question 49-32 : 1 3 1 1 2 1 2 3

.the first integration of acceleration with respect to time gives change of speed apply this to the initial speed and you have instantaneous speed exemple 273 1, 3.1, 3.

In an inertial navigation system the principle used to obtain position is .1 ?

Question 49-33 : 2 or 3 1 3 1 or 4

exemple 277 2 or 3.2 or 3.

Considering a strapdown inertial system the operating principle requires the ?

Question 49-34 : 3 laser gyros and 3 accelerometers 2 laser gyros and 3 accelerometers 3 laser gyros and 2 accelerometers 2 laser gyros and 2 accelerometers

exemple 281 3 laser gyros and 3 accelerometers.3 laser gyros and 3 accelerometers.

Compared with a stabilised platform inertial system a strapdown inertial system ?

Question 49-35 : 2 3 2 4 1 3 1 4

exemple 285 2, 3.2, 3.

A strapdown inertial system consists in ?

Question 49-36 : A platform attached to the aircraft chassis and which includes gyroscopes and accelerometers a platform free of the aircraft chassis which includes gyroscopes and accelerometers accelerometers attached to the aircraft chassis and gyroscopes which are not gyroscopes attached to the aircraft chassis and accelerometers which are not

exemple 289 a platform attached to the aircraft chassis and which includes gyroscopes and accelerometers.a platform attached to the aircraft chassis and which includes gyroscopes and accelerometers.

In an inertial navigation system integrating once the speed in gives ?

Question 49-37 : A distance travelled a position an instantaneous acceleration an average acceleration

exemple 293 a distance travelled.a distance travelled.

An inertial navigation system ins is ?

Question 49-38 : A self contained system which operates without signals from the ground a radio navigation system a hyperbolic navigation system a system which operates on the doppler principle

exemple 297 a self contained system which operates without signals from the ground.a self contained system which operates without signals from the ground.

A ring laser gyro can measure ?

Question 49-39 : Rotation about its sensitive axis accelerations about its sensitive axis rotation in all directions accelerations in all direction

The ring laser gyro is a rate sensing gyro and senses the rate of rotation around its axis exemple 301 rotation about its sensitive axis.rotation about its sensitive axis.

The data that needs to be inserted into an inertial reference system in order ?

Question 49-40 : Aircraft position in latitude and longitude or airport icao identifier aircraft heading the position of an in range dme the navigation database reference

exemple 305 aircraft position in latitude and longitude or airport icao identifier.aircraft position in latitude and longitude or airport icao identifier.

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