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NAV-LX-MODULE8-INS
1.
The purpose of the Flight Management System (FMS), as for example installed in the B737-400, is to provide:
a) both manual navigation guidance and performance management
b) manual navigation guidance and automatic performance management
c) continuous automatic navigation guidance as well as manual performance management
d) continuous automatic navigation guidance and performance management
2.
Which component of the B737-400 Flight Management System (FMS) is used to enter flight plan routeing and performance parameters?
a) Flight Management Computer
b) Flight Director System
c) Inertial Reference System
d) Multi-Function Control Display Unit
3.
What indication, if any, is given in the B737-400 Flight Management System if radio updating is not available?
a) A warning message is displayed on the EHSI and MFDU
b) A warning message is displayed on the Flight Director System
c) A warning message is displayed on the IRS displays
d) No indication is given so long as the IRS positions remain within limits
4.
What is the validity period of the 'permanent' data base of aeronautical information stored in the FMC In the B737-400 Flight Management System?
a) 3 calendar months
b) 28 days
c) 14 days
d) one calendar month
5.
In the B737-400 Flight Management System the CDUs are used during pre-flight to:
a) manually initialise the Flight Director System and FMC with dispatch information
b) automatically initialise the IRSs and FMC with dispatch information
c) manually initialise the IRSs and FMC with dispatch information
d) manually initialise the IRSs, FMC and Autothrottle with dispatch information
6.
How is the radio position determined by the FMC in the B737-400 Electronic Flight Instrument System?
a) DME/DME or VOR/DME
b) VOR/DME range and bearing
c) DME ranges and/ or VOR/ADF bearings
d) DME/DME
7.
In which of the following situations is the FMC present position of a B737-400 Electronic Flight Instrument System likely to be least accurate?
a) At top of climb
b) At top of descent
c) On final approach
d) Just after take-off
8.
What are, in order of highest priority followed by lowest, the two levels of message produced by the CDU of the B737-400 Electronic Flight Instrument System?
a) Urgent and Advisory
b) Priority and Alerting
c) Urgent and Routine
d) Alerting and Advisory
9.
Which of the following can all be stored as five letter waypoint identifiers through the CDU of a B737-400 Electronic Flight Instrument System?
a) Airway names; navaid identifiers; airport names; waypoint code numbers
b) Waypoint names; navaid identifiers; runway numbers; airport ICAO identifiers
c) Waypoint names; navaid frequencies; runway codes; airport ICAO identifiers
d) Waypoint names; navaid positions; airport ICAO identifiers; airport names
10.
Which of the following lists all the methods that can be used to enter 'Created Waypoints' into the CDU of a B737-400 Electronic Flight Instrument System?
a) Identifier bearing/distance; place bearing/place bearing; latitude and longitude; waypoint name
b) Identifier bearing/distance; place bearing/place bearing; along-track displacement; latitude and longitude
c) Identifier bearing/distance; place distance/place distance; along-track displacement; latitude and longitude
d) Identifier bearing/distance; place bearing/place distance; along/across-track displacement; latitude and longitude
11.
Which FMC/CDU page normally appears on initial power application to the B737-400 Electronic Flight Instrument System?
a) INITIAL
b) POS INIT
c) PERF INIT
d) IDENT
12.
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 - POS INIT - RTE
b) POS INIT - RTE - IDENT
c) IDENT - RTE - DEPARTURE
d) POS INIT - RTE - DEPARTURE
13.
With reference to inertial navigation systems, a TAS input is:
a) required for rhumb line navigation
b) not required
c) required for Polar navigation
d) required to provide a W/V read out
14.
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) movement in the yawing plane, secondary precession and pendulous oscillation
b) gyroscopic inertia, earth rotation and real drift
c) aircraft manoeuvres, earth rotation, transport wander and coriolis
d) vertical velocities, earth precession, centrifugal forces and transport drift
15.
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
16.
In order to maintain an accurate vertical using a pendulous system, an aircraft inertial platform incorporates a device:
a) without 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) with damping and a period of 84.4 SEC
17.
The term drift refers to the wander of the axis of a gyro in:
a) the horizontal plane
b) the vertical plane
c) the vertical and horizontal plane
d) any plane
18.
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) groundspeed
c) velocity along the local meridian
d) change latitude
19.
Double integration of the output from the east/west accelerometer of an inertial navigation system (INS) in the NAV MODE give:
a) distance east/west
b) velocity east/west
c) vehicle longitude
d) distance north/south
20.
In an Inertial Navigation System (INS), Ground Speed (GS) is calculated:
a) from TAS and W/V from Air Data Computer (ADC)
b) by integrating measured acceleration
c) from TAS and W/V from RNAV data
d) by integrating gyro precession in N/S and E/W directions respectively
21.
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) zero drop
b) cavity rotation
c) beam lock
d) dither
22.
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) departure
b) velocity along the local parallel of latitude
c) change of longitude
d) vehicle longitude
23.
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) The platform is kept stable relative to the earth mathematically rather than mechanically but it has a longer 'spin up' time
c) There is little or no 'spin up' time and it does not suffer from 'lock in' error
d) There is little or no 'spin up' time and it is insensitive to gravitational ('g') forces
24.
The principle of 'Schuler Tuning' as applied to the operation of Inertial Navigation Systems/ Inertial Reference Systems is applicable to:
a) both gyro-stabilised and laser gyro systems but only when operating in the non 'strapdown' mode
b) only to 'strapdown' laser gyro systems
c) only gyro-stabilised systems
d) both gyro-stabilised platform and 'strapdown' systems
25.
What additional information is required to be input to an Inertial Navigation System (INS) in order to obtain an W/V readout?
a) Altitude and OAT
b) TAS
c) IAS
d) Mach Number
26.
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) Ring laser
b) Solid state
c) Rigid
d) Strapdown
27.
During initial alignment an inertial navigation system is north aligned by inputs from:
a) horizontal accelerometers and the east gyro
b) computer matching of measured gravity magnitude to gravity magnitude of initial alignment
c) vertical accelerometers and the north gyro
d) the aircraft remote reading compass system
28.
During the initial alignment of an inertial navigation system (INS) the equipment:
a) will accept a 10° error in initial latitude but will not accept a 10° error in initial longitude
b) will not accept a 10° error in initial latitude but will accept a 10° error in initial longitude
c) will not accept a 10° error in initial latitude or initial longitude
d) will accept a 10° error in initial latitude and initial longitude
29.
Which of the following statement is correct concerning gyro-compassing of an inertial navigation system (INS)?
a) Gyro-compassing of an INS is not 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 possible in flight because it can differentiate between movement induced and misalignment induced accelerations.
30.
Which of the following statements concerning the loss of alignment by an Inertial Reference System (IRS) in flight is correct?
a) It is not usable in any mode and must be shut down for the rest of the flight
b) The navigation mode, including present position and ground speed outputs, is inoperative for the remainder of the flight
c) The mode selector has to be rotated to ATT then back through ALIGN to NAV in order to obtain an in-flight realignment
d) The IRS has to be coupled to the remaining serviceable system and a realignment carried out in flight
31.
The alignment time, at mid-latitudes, for an Inertial Reference System using laser ring gyros is approximately:
a) 10 MIN
b) 20 MIN
c) 5 MIN
d) 2 MIN
32.
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 NAV mode
b) INS/IRS can only be aligned in the ALIGN mode
c) INS/IRS can only be aligned in NAV mode
d) INS/IRS can be aligned in either the ALIGN or ATT mode
33.
A pilot accidentally turning OFF the INS in flight, and then turns it back ON a few moments later. Following this incident:
a) the INS is usable in NAV MODE after a position update
b) it can only be used for attitude reference
c) everything returns to normal and is usable
d) no useful information can be obtained from the INS
34.
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) proportional to t/2
b) proportional to the square of time, t²
c) proportional to t
d) sinusoîdal
35.
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
36.
Gyrocompassing of an inertial reference system (IRS) is accomplished with the mode selector switched to:
a) ATT/REF
b) ALIGN
c) STBY
d) ON
37.
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 - NAV - ATT
b) OFF - ON - ALIGN - NAV
c) OFF - STBY - ALIGN - NAV
d) OFF - ALIGN - ATT - NAV
38.
ATT Mode of the Inertial Reference System (IRS) is a back-up mode providing:
a) navigation information
b) altitude, heading and position information
c) only attitude information
d) only attitude and heading information
39.
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 the loading of passengers and/or freight
b) NAV mode must be selected when the alignment procedure is commenced
c) NAV mode must be selected on the runway just prior to take-off
d) NAV mode must be selected prior to movement of the aircraft off the gate
40.
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 be the same because they are an average of three different positions
b) The positions will only differ if an error has been made when inputting the present position at the departure airport
c) The positions will only differ if one of the systems has been decoupled because of a detected malfunction
d) The positions are likely to differ because they are calculated from different sources
41.
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) geographic coordinates
c) bearing and distance
d) by waypoints name
42.
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) the autopilot is unserviceable in NAV mode
b) only inertial navigation system No. 2 is drifting
c) only inertial navigation system No. 1 is drifting
d) at least one of the inertial navigation systems is drifting
43.
What is the source of magnetic variation information in a Flight Management System (FMS)?
a) The main directional gyro which is coupled to the magnetic sensor (flux valve) positioned in the wingtip
b) Magnetic variation information is stored in each IRS memory; it is applied to the true heading calculated by the respective IRS
c) Magnetic variation is calculated by each IRS based on the respective IRS position and the aircraft magnetic heading
d) The FMS calculates MH and MT from the FMC position
44.
Where and when are the IRS positions updated?
a) Only on the ground during the alignment procedure
b) During flight IRS positions are automatically updated by the FMC
c) IRS positions are updated by pressing the 'Take-off/ Go-around' button at the start of the take-off roll
d) Updating is normally carried out by the crew when over-flying a known position (VOR station or NDB)
45.
Which of the following statements concerning the position indicated on the Inertial Reference System (IRS) display is correct?
a) It is constantly updated from information obtained by the FMC
b) The positions from the two IRSs are compared to obtain a 'best position' which is displayed on the IRS
c) It is not updated once the IRS mode is set to NAV
d) It is updated when 'go-around' is selected on take-off
46.
The sensors of an INS measure:
a) precession
b) velocity
c) acceleration
d) the horizontal component of the earth's rotation
47.
A ring laser gyro is?
a) Used for stabilising the INS platform.
b) A device which measures earth rate precession.
c) A device which measures angular movements.
d) An optical accelerometer.
48.
If the acceleration of an aircraft is zero, its velocity?
a) Is always zero.
b) Will decrease.
c) Is constant.
d) Will increase.
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