Test ATPL INS 2

figure C is a diagram of

. an altimeter

. a vsi ( vertical speed indicator)

. a machmeter

. an air speed indicator

refer to the above diagram of a servo-altimeter. the correct description of the components labelled C,D and E in order are:

. capsule stack, cam, inductive pick off

. amplifier, cam,inductive pick off

. amplifier, transducer, capsule stack

. two-phase motor, transducer, inductive pick off

the restricted choke in the VSI

. will prevent the instrument being damaged by high rates of climb and descent.

. compensates for changes in temperature and density only

. creates a differential pressure between the capsule and the case as its main function

. compensates for time lag in the instruments

an aircraft is flying at a constant RAS if the ambient temperature the TAS will..... due to ....the words to correctly complete the above statement:

. falls, fall decreasing density

. rises rise increasing density

. rises rise decreasing density

. falls fall decreasing pressure

the latitude correcting device of an air driven directional gyro is

. an adjustable weight attached to the outer gimbal of the DI

. an adjustable weight attached to the inner gimbal of the DI

. the air jet which drives the rotor

. a chamber with four exit slots half covered by pendulous vanes

appendix A , figure D is a diagram of

. an altimeter

. a vertical speed indicator

. a machmeter

. an air speed indicator

the gyro is set to read 100 the gyro rating after 45 minutes when stationary on the ground in latitude 25 S is

. 087

. 113

. 103.5

. 096.5

the gyro is set to read 090 the gyro reading after flying for 80 minutes n a track of 090 T along the parallel of of 20 N at a groundspeed of 540 kt is

. 093.5

. 107.5

. 102.5

. 072.5

if the static source to an altimeter becomes blocked during a descent the instrument:

. will overread by a constant amount

. continues to show the height at which the blockage occurred

. will progressively unde read

. pinter will return to indicate a height equivalent to the sub scale setting

elect the line of phrases given below that would complete the above statement correctly

An electrical ah employs----------an-------tomaintain its position related to-------------

. erection chamber pendulous vanes space

. fast erect buttons, micro switches, local longitude

. mercury switches, torque motors , the local vertical

. precession circuit, torque motor, azimuth

value coefficient A

. +3

. -3

. -12

. +4

the value of coefficient B is

. +2

. -2

. -1

the value coefficient C is

. +2

. -2

. -1

. or 0

refer to the above diagram of a gyro magnetic compass system, The correct description of the components labelled A, C and E in order are:

. flux valve system, stators, gyro unit

. synchronizing unit, stators, motor

. signal selsyn stators, follow up motor

. stator system rotor gyro unit

refer to appendix a figure B is a diagram of

. an altimeter

. a vertical speed indicator

. a machmeter

. an air speed indicator

an aircraft is require d to clear high ground at 6300 ft amsl by at least 700 meters, the regional QNH is 102 mb, the aircraft track is 348 M, assume 1mb + 30 ft

Using the above information answer the following two questions.

the lowest quadrant le

. FL85

. Fl65

. FL245

. Fl225

The qfe at a nearby airfield elevation 1410 ft amsl is

. 1010 mb

. 1037 mb

. 977 mb

. 966 mb

refer to appendix a figure A is a diagram of

. an altimeter

. a vertical speed indicator

. a machmeter

. an airspeed indicator

the product of the first integration of the output from the N/S accelerometer in INS equipment is

. departure

. latitude

. velocity along the local meridian

. distance along the local meridian

the principle of operation of the turn and slip indicator is best described as

. a space gyro which uses the force of precession against a spring toggle a reading of the aircraft rate turn

. a single gimbal gyroscope whose primary precession is opposed by a spring which in turn produces a second precession equal and opposite to the aircraft rate of turn

. a single gimbal gyroscope in which a spring opposing the primary precession in turn produces a secondary precesision equal to the aircraft rate rturn

. an oath gyro in which a calibrated spring ensures the tiilt of the gyro is proportional to the aircraft rate of turn

A compass swing is carrie out on ana aircraft and the values of the coefficients of the direct reading compass were A=+3 B=-3 and c=+1 the observed deviation on south was +3 before correction the compass was then corrected for A B and C

If the local v

. 193

. 165

. 192

. 167

An aircraft is descending at a constant mach no, through an isotherms layer. the RAS of the aircraft will

. decrease

. remain the same

. increase

. decrease quickly initially and then remain the same

with reference to a note referenced inertial navigation system (INS) gyro compassing is

. the process by which the inertial platform is aligned with magnetic north during the ALIGH phase

. carried out in the STANDBY mode by aligning the platform sing the aircraft gyromagnetic compass system to define true north

. the process by which the platform is leveled and aligned with the true north using the earths gravity in the ALIGN mode

. the process by which the platform is maintained in correct alignment with true north during flight

when accelerating on a westerly heading in the NH the magnetic assembly of a direct reading magnetic compass when viewed from above will.

. turn clockwise indicating an apparent turn towards the north

. turn anti clockwise indicating an apparent turn towards the north

. turn clockwise indicating and apparent turn towards the south

. turn anti clockwise indicating an apparent turn towards the south

The position indicated by the INS in an aircraft on the ramp at the end of a fire hour flight is 5229 N 0047 W if the ramp position is 5218 N 0012W. the hourly radial error rate for the flight was:

. 7,34 nm

. 5.31 nm

. 4,81

. 3,66 nm

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