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ATPL INS 2

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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