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NAV-LX-MODULE3
1.
Which of the following statement is correct concerning gyro-compassing of an inertial navigation system (INS)?
a) Gyro-compassing of an INS is possible in flight because it can differentiate between movement induced and misalignment induced accelerations.
b) Gyro-compassing of an INS is not possible in flight because it cannot differentiate between movement induced and misalignment induced accelerations.
c) Gyro-compassing of an INS is possible in flight because it cannot differentiate between movement induced and misalignment induced accelerations.
d) Gyro-compassing of an INS is not possible in flight because it can differentiate between movement induced and misalignment induced accelerations.
2.
Which of the following statements concerning the loss of alignment by an Inertial Reference System (IRS) in flight is correct?
a) The IRS has to be coupled to the remaining serviceable system and a realignment carried out in flight
b) The navigation mode, including present position and ground speed outputs, is inoperative for the remainder of the flight
c) It is not usable in any mode and must be shut down for the rest of the flight
d) The mode selector has to be rotated to ATT then back through ALIGN to NAV in order to obtain an in-flight realignment
3.
Which of the following statements concerning the alignment procedure for Inertial Navigation Systems (INS)/Inertial Reference Systems (IRS) at mid-latitudes is correct?
a) INS/IRS can be aligned in either the ALIGN or ATT mode
b) INS/IRS can be aligned in either the ALIGN or NAV mode
c) INS/IRS can only be aligned in the ALIGN mode
d) INS/IRS can only be aligned in NAV mode
4.
The term drift refers to the wander of the axis of a gyro in:
a) any plane
b) the vertical plane
c) the horizontal plane
d) the vertical and horizontal plane
5.
A pilot accidentally turning OFF the INS in flight, and then turns it back ON a few moments later. Following this incident:
a) it can only be used for attitude reference
b) the INS is usable in NAV MODE after a position update
c) no useful information can be obtained from the INS
d) everything returns to normal and is usable
6.
The resultant of the first integration of the output from the east/west accelerometer of an inertial navigation system (INS) in NAV MODE is:
a) vehicle longitude
b) velocity along the local parallel of latitude
c) departure
d) change of longitude
7.
What is the name given to an Inertial Reference System (IRS) which has the gyros and accelerometers as part of the unit's fixture to the aircraft structure?
a) Strapdown
b) Ring laser
c) Solid state
d) Rigid
8.
Which of the following lists the first three pages of the FMC/CDU normally used to enter data on initial start-up of the B737-400 Electronic Flight Instrument System?
a) IDENT - RTE - DEPARTURE
b) POS INIT - RTE - IDENT
c) POS INIT - RTE - DEPARTURE
d) IDENT - POS INIT - RTE
9.
In order to maintain an accurate vertical using a pendulous system, an aircraft inertial platform incorporates a device:
a) with damping and a period of 84.4 SEC
b) with damping and a period of 84.4 MIN
c) without damping and a period of 84.4 MIN
d) without damping and a period of 84.4 SEC
10.
Some inertial reference and navigation systems are known as "strapdown". . This means that?
a) the gyroscopes and accelerometers become part of the unit's fixture to the aircraft structure
b) gyros and accelerometers are mounted on a stabilised platform in the aircraft
c) gyros and accelerometers need satellite information input to obtain a vertical reference
d) only the gyros, and not the accelerometers, become part of the unit's fixture to the aircraft structure
11.
ATT Mode of the Inertial Reference System (IRS) is a back-up mode providing:
a) only attitude information
b) altitude, heading and position information
c) navigation information
d) only attitude and heading information
12.
During initial alignment an inertial navigation system is north aligned by inputs from:
a) vertical accelerometers and the north gyro
b) horizontal accelerometers and the east gyro
c) the aircraft remote reading compass system
d) computer matching of measured gravity magnitude to gravity magnitude of initial alignment
13.
Which of the following correctly lists the order of available selections of the Mode Selector switches of an inertial reference system (IRS) mode panel?
a) OFF - ALIGN - ATT - NAV
b) OFF - STBY - ALIGN - NAV
c) OFF - ON - ALIGN - NAV
d) OFF - ALIGN - NAV - ATT
14.
Which of the following statements concerning the operation of an Inertial Navigation System (INS)/Inertial Reference System (IRS) is correct?
a) NAV mode must be selected prior to movement of the aircraft off the gate
b) NAV mode must be selected on the runway just prior to take-off
c) NAV mode must be selected prior to the loading of passengers and/or freight
d) NAV mode must be selected when the alignment procedure is commenced
15.
The resultant of the first integration from the north/south accelerometer of an inertial navigation system (INS) in the NAV MODE is:
a) latitude
b) change latitude
c) groundspeed
d) velocity along the local meridian
16.
The principle of 'Schuler Tuning' as applied to the operation of Inertial Navigation Systems/ Inertial Reference Systems is applicable to:
a) only gyro-stabilised systems
b) only to 'strapdown' laser gyro systems
c) both gyro-stabilised and laser gyro systems but only when operating in the non 'strapdown' mode
d) both gyro-stabilised platform and 'strapdown' systems
17.
With reference to an inertial navigation system (INS), the initial great circle track between computer inserted waypoints will be displayed when the control display unit (CDU) is selected to:
a) DSRTK/STS
b) HDG/DA
c) TK/GS
d) XTK/TKE
18.
Which of the following statements concerning the aircraft positions indicated on a triple fit Inertial Navigation System (INS)/ Inertial Reference System (IRS) on the CDU is correct?
a) The positions will only differ if an error has been made when inputting the present position at the departure airport
b) The positions will be the same because they are an average of three different positions
c) The positions are likely to differ because they are calculated from different sources
d) The positions will only differ if one of the systems has been decoupled because of a detected malfunction
19.
Gyrocompassing of an inertial reference system (IRS) is accomplished with the mode selector switched to:
a) ON
b) ALIGN
c) STBY
d) ATT/REF
20.
Waypoints can be entered in an INS memory in different formats. . In which of the following formats can waypoints be entered into all INSs?
a) hexadecimal
b) by waypoints name
c) geographic coordinates
d) bearing and distance
21.
Which of the following lists, which compares an Inertial Reference System that utilises Ring Laser Gyroscopes (RLG) instead of conventional gyroscopes, is completely correct?
a) It does not suffer from 'lock in' error and it is insensitive to gravitational ('g') forces
b) There is little or no 'spin up' time and it does not suffer from 'lock in' error
c) There is little or no 'spin up' time and it is insensitive to gravitational ('g') forces
d) The platform is kept stable relative to the earth mathematically rather than mechanically but it has a longer 'spin up' time
22.
The alignment time, at mid-latitudes, for an Inertial Reference System using laser ring gyros is approximately:
a) 20 MIN
b) 10 MIN
c) 5 MIN
d) 2 MIN
23.
Where and when are the IRS positions updated?
a) Only on the ground during the alignment procedure
b) IRS positions are updated by pressing the 'Take-off/ Go-around' button at the start of the take-off roll
c) Updating is normally carried out by the crew when over-flying a known position (VOR station or NDB)
d) During flight IRS positions are automatically updated by the FMC
24.
If the acceleration of an aircraft is zero, its velocity?
a) Will decrease.
b) Will increase.
c) Is constant.
d) Is always zero.
25.
Double integration of the output from the east/west accelerometer of an inertial navigation system (INS) in the NAV MODE give:
a) vehicle longitude
b) distance north/south
c) velocity east/west
d) distance east/west
26.
What additional information is required to be input to an Inertial Navigation System (INS) in order to obtain an W/V readout?
a) TAS
b) IAS
c) Mach Number
d) Altitude and OAT
27.
The first law of Kepler states?
a) Planets move around the sun in a circular path.
b) All planets orbit around the sun at the same speed.
c) The angular speed of the planets in the orbit around the sun is constant.
d) Planets move in elliptic orbits with the sun at one of the foci.
28.
In an Inertial Navigation System (INS), Ground Speed (GS) is calculated:
a) by integrating gyro precession in N/S and E/W directions respectively
b) from TAS and W/V from Air Data Computer (ADC)
c) from TAS and W/V from RNAV data
d) by integrating measured acceleration
29.
The drift of the azimuth gyro on an inertial unit induces an error in the position given by this unit. "t" being the elapsed time. . The total error is?
a) sinusoîdal
b) proportional to the square of time, t²
c) proportional to t/2
d) proportional to t
30.
A ring laser gyro is?
a) An optical accelerometer.
b) Used for stabilising the INS platform.
c) A device which measures earth rate precession.
d) A device which measures angular movements.
31.
The platform of an inertial navigation system (INS) is maintained at right angles to the local vertical by applying corrections for the effects of:
a) aircraft manoeuvres, earth rotation, transport wander and coriolis
b) movement in the yawing plane, secondary precession and pendulous oscillation
c) gyroscopic inertia, earth rotation and real drift
d) vertical velocities, earth precession, centrifugal forces and transport drift
32.
An aircraft equipped with an Inertial Navigation System (INS) flies with INS 1 coupled with autopilot 1. Both inertial navigation systems are navigating from way-point A to B. The inertial systems' Central Display Units (CDU) sho shows: . XTK on INS 1 = 0 XTK on INS 2 = 8L (XTK = cross track) . From this information it can be deduced that?
a) only inertial navigation system No. 1 is drifting
b) the autopilot is unserviceable in NAV mode
c) at least one of the inertial navigation systems is drifting
d) only inertial navigation system No. 2 is drifting
33.
Which of the following statements concerning the position indicated on the Inertial Reference System (IRS) display is correct?
a) It is not updated once the IRS mode is set to NAV
b) The positions from the two IRSs are compared to obtain a 'best position' which is displayed on the IRS
c) It is constantly updated from information obtained by the FMC
d) It is updated when 'go-around' is selected on take-off
34.
The sensors of an INS measure:
a) acceleration
b) velocity
c) the horizontal component of the earth's rotation
d) precession
35.
During the initial alignment of an inertial navigation system (INS) the equipment:
a) will accept a 10° error in initial latitude and initial longitude
b) will not accept a 10° error in initial latitude or initial longitude
c) will not accept a 10° error in initial latitude but will accept a 10° error in initial longitude
d) will accept a 10° error in initial latitude but will not accept a 10° error in initial longitude
36.
What is the source of magnetic variation information in a Flight Management System (FMS)?
a) Magnetic variation is calculated by each IRS based on the respective IRS position and the aircraft magnetic heading
b) The FMS calculates MH and MT from the FMC position
c) Magnetic variation information is stored in each IRS memory; it is applied to the true heading calculated by the respective IRS
d) The main directional gyro which is coupled to the magnetic sensor (flux valve) positioned in the wingtip
37.
One of the errors inherent in a ring laser gyroscope occurs at low input rotation rates tending towards zero when a phenomenon known as 'lock-in' is experienced. What is the name of the technique, effected by means of a piezo-electric motor, that is used to correct this error?
a) cavity rotation
b) zero drop
c) beam lock
d) dither
38.
With reference to inertial navigation systems, a TAS input is:
a) required to provide a W/V read out
b) required for rhumb line navigation
c) not required
d) required for Polar navigation
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