Test ATPL INS 4

the following readings were obtained surging the swing of. a direct reading of magnetic compass

. -3 -1 +3

. -3 +1 -3

. +3-1+3

. +3-2-3

An aircraft id descending at a constant mach number. If the aircraft is descending through an inversion layer, the Ras will

. remain constant

. increase

. decrease

. decrease then decrease more slowly

Equivalent airspeed EAS is

. IAS corrected for compressibility

. IAS corrected for instrument error only

. RAS corrected for compressibility

. RAS corrected for position error

the FL being flown and the actual ground clearance are

. 215-3879 ft

. 195-2930 ft

. 195 3440 ft

. 215 2930 ft

The computer of a north referenced INS in flight provides compensation for .

. aircraft maneuvers, real wander, apparent wander, transport wander

. Coriolis, real wander, apparent wander, transport wander

. earth rotation, transport wander, Coriolis

. transport wander, apparent wander, Coriolis, magnetic variation

when DSRTK/STS is selected on the CDU, the left window will show:

. 74

. 86

. 68

. 80

When the XTK/TKE is selected on th eCDU, the display will show ( to the nearest whole number)

. 5L----080

. 5R----6R

. 5L----6L

. 6R----5L

The DI is set to read 1000 in an aircraft stationary on the ground in latitude 45 N the reading after 45 minutes will be

. 092.33

. 102.50

. 097.78

. 103.75

the Di is set to read 270 in an aircraft tracking along the 60N parallel at groundspeed 545 kt. the Di reading after 80 minutes is

. 254.66

. 283.66

. 286.80

. 257.33

In the diagram above of a gyromagnetic compass system, the components A, C and E in order are

. flux valve rotors enunciator

. signal selsyn stators gyroscope unit

. flux valve stators gyroscope unit

. indicator flux valve amplifier

Dynamic pressure is

. static pressure minus pito pressure

. pitot pressure plus static pressure

. density and static pressure

. pitot pressure minus static pressure

when accelerating on a an easterly heading in the NH the magnet system of a direct reading magnetic compass will

. turn clockwise indicating an aparent turn towards the north

. turn anti clockwise indicating an apparent turn towards the north

. turn clockwise indicating an apparent turn towards the south

. turn anti clockwise indicating an apparent turn towards the south

the product of the second integration of the E/W accelerometer output in an INS system is

. longitude

. departure

. E/W acceleration

. E/W groundspeed

Density varies

. Directly with pressure inversely with temperature

. Directly with temperature and pressure

. inversely with temperature and pressure

. inversely with pressure and directly with temperature

An aircraft flying at a TAS of 1100 kT and FL650, A change of 0.1 mach causes a change in TAS of 57kt, Th temperature deviation at FL650 assuming an ISA atmosphere is

. -6

. +6

. -3

. +3

The deviating effect of a vertical soft iron (VSI) ---------with decrease of magnetic latitude due to ------of H and the -----of Z The line containing the words to correctly complete the above statement is

. increase, decrease, increase

. decrease, increase, decrease

. decrease increase increase

. increase decrease decrease

If during a climb the static source becomes blocked the vertical speed indicator VSI will show

. a decreased rate of climb

. a zero rate of climb

. an increased rate of climb

. a normal rate of climb

Angle of attack may be sensed by means of -------mounted-------

. a stick pushed, adjacent to the flying controls

. an indexer in the flight director

. a conical slotted probe on the wing leading edge

. a hid vane sensor on the wing leading edge

the speed at the upper end of the green arc on the ASI is ?

. VRA

. VNO

. VNE

. VMC

The rate gyro indicates the correct rate of turn when the ------precession due to the spring is -----to the ----rate of turn

the line containing the words to correctly complete the above statements

. secondary. equal. aircraft

. torqued. opposite. primary

. primary. balanced by equal aircraft

. secondary. opposite. aircraft

the servo altimeter is superior to the sensitive altimeter because

. it reduces barometric error

. it reduces high altitude error

. it reduces temperature error

. all of the above

An aircraft is flying at FL290, TAS 5000 KT mach number .86 the temperature deviation from ISA is

. -7

. +7

. -15

. +25

The advantages of the electrical AH over the air driven one are.

. ramdom wander reduced- greater rigidity

. acceleration errors reduced-less rigidity

. greater rigidity- accelerations errors reduced - turning errors reduced

. fast erection button fitted quicker precession allowing faster indication cut-out switches reduce turning errors

The rotor of a rate gyroscope is overspending, the pilot carries out a turn with the rate gyroscope indicating rate 1. The actual rate of turn will be

. 3 per second

. more than 3 per second

. less than 3 per second

. 6 per second

With reference to the altimeter pressure fluctuations at the static vent cause

. Barometric error

. temperature error

. position error

. hysteresis error

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