Test ATPL INS 3

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the following coefficients were obtained during the swing of a direct reading compass A + 3 B -3 C +3

Assuming that deviations were caused only by coefficients A, B and C the compass reading with the aircraft on a heading of 260 (T) where local varia

. 238

. 282

. 270

. 250

an aircraft flying at mach .86 temperature 218 kelvin the tas is

. 494

. 477

. 607

. 575

compressibility error is caused by a false -------of-----pressure requiring a ------correction to the RAS to obtain EAS . the words to correctly complete the sentence above are:

. decrease , pito,positive

. increase dynamic negative

. decrease dynamic positive

. increase static negative

the subscacle of an altimeter is set to 1030 MB and indcites 45000 ft when the QNH is 996 mb assuming 1mb equals 30 ft the true heigh of the aircraft AMSL is

. 3180 ft

. 3990 ft

. 5520 ft

. 3480 ft

the DI is set to read 339 when stationary on the ground in latitude 59N the reading after 36 minutes will be

. 335,58

. 337.00

. 341.00

. 342,42

The DI is set to 270 in an aircraft tracking west along the parallel if. 45n at a groundspeed of 545 kt . the reading after 80 minutes will be

. 280.57

. 277.93

. 255.40

. 260.22

during the take off run the air driven ah will indicate

. a climb due to the pendulosity of the inner gimbal

. a climb due to the action of the pendulous vanes

. a right turn due to the pendulosity of the outer gimbal

. a right turn due to the action of the pendulous vanes

if a simple flux valve lies -----the earths filed the current induced in pick off coil will be .... and the frequency will be ,,,, te input frequency. the words to correctly complete the sentence above are:

. in line with, minimum, twice

. a t 90 to, minimum, half

. at 90 to, maximum, half

. in line with maximum twice

Refer to the above diagram of a servo altimeter, the correct description of the components labelled B D and H order are:

. indicator, transducer cam

. two way motor, transducer, sub scale setting knob

. amplifier, two way motor cam and follower

. two way motor follower sub scale setting knob

In the VSI , viscosity

. affects the capillary tube in the restricted choke

. affects the knife edge orifice in the restricted choke

. affects the bi-metallic strip and the compensating spring

. is compensated for by resetting the VSI to read zero on the ground before take off

the precession of a gyroscope varies

. directly with the applied force and directly wilth the inertia of the rotor

. indirectly with the applied force and indirectly with the inertia of the rotor

. directly with the applied force and indirectly with the inertia of the rotor

. indirectly with the applied force and directly with the inertia of the rotor

in the above diagram, the turn and slip indicator is showing a turn of

. 6 / sec with too much bank for the TAS

. 3 / sec with too little bank for the TAS

. 3/sec with too much bank for the TAS

. 6/sec with too little bank for the TAS

An aircraft is to fly over high ground 4730 meters AMSL. the track is 140(M) the QNH is 995 mb, the required clearance is a minimum of a 1500 ft assuming 1mb equals 30 ft, the minimum IMC flight level is.

. 175

. 195

. 190

. 215

the air driven ah, uses -----guroscope which is maintained -----by means of-----

. a free, horizontal, case leveling

. an earth, vertical, pendulous vanes

. a space, horizontally pitch bank erection system

. an earth, vertical, torque motors

The corrections fed to the platform gimbal motors of a north referenced inertial navigation system during the align mode use inputs from

. latitude setting the accelerometer

. the longitude setting, the latitude setting, the air data computer

. the latitude setting the longitude setting the accelerometers

. all the factors mentioned in a b and c

value of coefficient C was

. +4

. =2

. +2

. -4

After correcting for A B and C the compass heading on 272(M) was

. 270

. 274

. 266

. 272

in the diagram above of a mach meter the parts labelled order

. pitot entry altimeter capsule ranging arm

. static entry altimeter capsule ratio arm

. static entry ASI capsule ratio arm

. pitot entry aside capsule ranging arm

in a turn form 045 to 315 through north in the Northern hemisphere the movement of the manger system of a direct reading compass when viewed from above and the effect of liquid swirl on the error caused by the movement ara:

. anticlockqwse - reduced

. clockwise-increase

. anti clockwise -increase

. clockwise -reduce

the rotor of a pitch correction motor of the electical artificial horizons on

. the outer gimbal

. the inner gimbal

. the instrument case

. the top of the gyro unit

An aircraft flying at FL1000 and at a constant RAS lied from an area of warm air into an area of cold air, assuming the QNH is the same during the change of temperature,. the aircraft height AMSL and the TAS will haveL

. decrsced -incresed

. increased-increased

. decreased-decreased

. increased-decresced

two chcks that can be carried out to check that two selected sequentialwaypoints habve been entered correctly are

. select DSR TK/STS and check that the status is less than 4; select DIS/TIME and check that the time agrees with the flight pleb time

. Select DS/TIME and check that the distance agrees with the distance on the flight plan then check that the time agrees with the flight time for the leg.

. Select DIS/TIME and check that the distance agrees with the distance on the flight plan..sleect DSR TK.STS and check that the track agrees with the flight plan track for the leg

. Select the DIS/TIME and check that the distance agrees with the distance on the flight plan select HDG/DA and check that the heading agrees with the flight plan heading for the leg .

An aircraft is climbing at a constant Mach number assuming the temperature Sid ISA the RAS will

. rise due to TAS increasing with falling density

. fall due to density decreasing due to the increase in the local speed of sound

. rise due to the decreasing pressure

. fall due to the increasing density error

A the end f a 6 hour 24 minutes flight an aircraft is parked on a parking where the coordinates are S 36520E152170 the readout on the INS was S37080 E 151 52 0 the radial error rate for the flight was

. 4.0 nm/hr

. 4.6 nm/hr

. 5.0 nm/hr

. 5.6 nm/hr

the main function of the annuciator in a gyro magnetic compass is

. to keep the gyro unit aligned with the earths field

. to maintain the gyro unit horizontal

. to indicate correct functioning of the compass system

. to ensure correct alignment with compass north

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