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NAV-RH-MODULE4-TEST LEARN
1.
The purpose of the TAS input, from the air data computer, to the Inertial Navigation System is for:
a) the calculation of drift
b) the calculation of wind velocity
c) position update in Navigation mode
d) position update in Attitude mode
2.
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 – ALIGN – ATT – NAV
d) OFF – STBY – ALIGN – NAV
3.
A pilot accidently turning OFF the INS in flight, and then turns it back ON a few moments later. Following this incident:
a) no useful information can be obtained from the INS
b) everything returns to normal and is usable
c) the INS is usable in NAV MODE after a position update
d) it can only beused for attitude reference
4.
What is the sequence of pages on start-up of the Boeing 737-400 FMS?
a) IDENT, POS INIT, RTE
b) POS INIT, IDENT, DEPARTURES
c) IDENT, POS INIT, DEPARTURES
d) POS INIT, RTE, IDENT
5.
An INS platform is kept at right angles to local gravity by applying corrections for the effects of:
i. Aircraft manoeuvres
ii. Earth rotation
iii. Transport wander
iv. Coriolis
v. Gyroscopic inertia
a) i, iii and v
b) ii, iv and v
c) ii, iii and iv
d) ii, iii and v
6.
Which of the following statements concernikng the operation of an Inertial Navigation System (INS)/Inertial Reference System (IRS) is correct?
a) NAV mode must be selected when the alignment procedure is commenced
b) NAV mode must be selected prior to the loading of passengers and/or freight
c) NAV mode must be selected prior to movement of the aircraft off the gate
d) NAV mode must be selected on the runway just prior to take-off
7.
Where and when are the IRS positions updated?
a) Only on the ground during the alignment procedure
b) Updating is normally carried out by the crew when over-flying a known
position (VOR station or NDB)
c) IRS positions are updated by pressing the Take-off/Go-around button at
the start of the take-off roll
d) During flight IRS positions are automatically updated by the FMC
8.
Calibrated Airspeed (CAS) is indicated Airspeed (IAS) corrected for:
a) density
b) compressibility error
c) temperature and pressure error
d) instrument error and position error
9.
Which of the following statements concerning the position indicated on the Inertial Reference System (IRS) display is correct?
a) The positions from the two IRSs are compared to obtain a best position
which is displayed on the IRS
b) It is updated when go-around is selected on take-off
c) It is not updated once the IRS mode is set to NAV
d) It is constantly updated from information obtained by the FMC
10.
In the Boeing 737-400 FMS, the CDU is used to:
a) automatically initialise the IRS and FMC with dispatch information
b) manually initialise the Flight Director System, FMC and Autothrottle with dispatch information
c) manually initialise the Flight Director System and FMC with dispatch information
d) manually initialise the IRS and FMC with dispatch information
11.
Comparing the Present Position display on the Boeing 737-400 FMC, you note that there is a 10-mile difference between the left IRS and the right IRS positions. This means that:
a) At least one of the IRS is drifting
b) One system is in IRS ONLY NAV operation and the other has the VHF Nay Radios selected to AUTO
c) One position has been computer generated from radio nay positions whilst the other is raw IRS
d) No special significance – this is normal
12.
When can a pilot change the data in the FMS data base?
a) Every 28 days
b) He can’t; for the pilot the FMS data base is read only
c) When there is a fault
d) When deemed necessary
13.
An aircraft equipped with an Inertial Navigation System (INS) flies with INS 1 coupled with autopilot 1. Both inertial navigation systems are navigating from waypoint A to B. The inertial systems Central Display Units (CDU) shows:
-XTK on INS 1 = 0 –XTK on INS 2 = BL (XTK = cross track)
From this information it can be deduced that:
a) at least one of the inertial navigation systems is drifting
b) only inertial navigation system No. 1 is drifting
c) only inertial navigation system No. 2 is drifting
d) the autopilot is unserviceable in NAV mode
14.
In an IRS:
a) accelerometers and platform are both gyro-stabilised
b) accelerometers and platform are both strapped down
c) the platform is strapped down but the accelerometers are gyro-stabilised
d) the accelerometers are strapped down but the platform is gyro stabilised
15.
In a Flight Management System (FMS), control Display Units (CDUs) are used pre-flight to
a) manually initialise the Flight Director System and FMC with dispatch
information
b) manually initialise the IRSs and FMC with dispatch information
c) automatically initialise the IRSs and FMC with dispatch information
d) manually initialise the IRSs, FMC and Air Data Computer with dispatch
information
16.
IRS differs from INS in that it:
a) has a longer spin-up time and is not affected by vertical accelerations due to gravity
b) does not experience Schuler errors as accelerometers are strapped down and are not rotated by a V/R feedback loop
c) does not need to correct for coriolis and central acceleration
d) has a shorter spin-up time and suffers from laser lock
17.
During the initial alignment of an inertial navigation system (INS) the equipment:
a) will accept a 10o error in initial latitude but will not accept a 10o error in
initial longitude
b) will accept a 10o error in initial latitude and initial longitude
c) will not accept a 10o error in initial latitude or initial longitude
d) will not accept a 10o error in initial latitude but will accept a 10o error in
initial longitude
18.
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) both gyro-stabilised and laser gyro systems but only when operating in the non strapdown mode
c) both gyro-stabilised platform and strapdown systems
d) only to strapdown laser gyro systems
19.
In an Inertial Navigation System (INS), Ground speed (GS) is calculated:
a) by integrating measured acceleration
b) by integrating gyro precession in N/S and E/W directions respectively
c) from TAS and W/V from Air Data Computer (ADC)
d) from TAS and W/V from RNAV data
20.
Within the platform levelling loop of an earth-vertical referenced INS:
a) The levelling signals are bounded, with a period of 84.4 seconds
b) The levelling signals are bounded with a period of 84.4 minutes
c) The levelling signals are unbounded, with a period of 84.4 seconds
d) The levelling signals are unbounded, with a period of 84.4 minutes
21.
A useful method of a pilot resolving, during a visual flight, any uncertainty in the aircraft’s position is to maintain visual contact with the ground and:
a) fly the reverse of the heading being flown prior to becoming undertain until a pinpoint is obtained
b) fly expanding circles until a pinpoint is obtained
c) set heading towards a line feature such as a coastline, motorway, river or railway
d) fly reverse headings and associated timings until the point of departure is regained.
22.
What measurement is used to carry out alignment of an Inertial Navigation System?
a) Acceleration sensed by the north gyro ertical accelerometer
b) Difference in magnitude of the value of gravity compared with the gravity at the last known position
c) Acceleration sensed by the north gyro horizontal accelerometer
d) Acceleration sensed by the east gyro horizontal accelerometer
23.
You are flying a VFR route and have become uncertain of your position. Which is the best course of action?
a) Turn round and fly your flight plan in reverse back to base
b) Turn round and fly your flight plan tracks in reverse until you see something you recognised before
c) Set heading towards a line feature – coastline, river, or motorway
d) Fly a series of ever-expanding circles from your present position till you find your next check point
24.
Some inertial reference systems are known as strapdown. This means:
a) the gyros are fixed but the accelerometers are stabilised
b) the system is mounted and fixed to the aircraft structure
c) the accelerometers are fixed bu the gyros are stabilised
d) the system is mounted on a stabilised platform
25.
Isogrivs on a chart indicate lines of:
a) equal grivation
b) equal magnetic dip
c) equal horizontal directive force
d) zero magnetic variation
26.
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) 28 days
b) 14 days
c) 3 calendar months
d) One calendar month
27.
After alignment of the stable platform of the Inertial Navigation System, the output data from the INS computer to the platform is:
a) attitude
b) accelerations from the accelerometers
c) latitude and longitude
d) rate corrections to the gyros
28.
Which component of the B737-400 Flight Management System (FMS) is used to enter flight plan routeing and performance parameters?
a) Flight Director System
b) Multi-Function Control Display Unit
c) Flight Management Computer
d) Inertial Reference System
29.
Which of the following statements is correct concerning gyro-compassing of an inertial navigation system (INS)?
a) Gyro-compassing of an INS is not possible in flight because it cannot differentiate between movement induced and misalignment induced accelerations
b) Gyro-compassing of an INS is not possible in flight because it can differentiate between movement induced and misalignment induced accelerations
c) Gyro-compassing of an INS is possible in flight because it can differentiate between movement induced and misalignment induced accelerations
d) Gyro-compassing of an INS is possible in flight because it cannot differentiate between movement induced and misalignment induced accelerations
30.
What does the sensor of an INS/IRS measure?
a) Horizontal Earth Rate
b) Velocity
c) Acceleration
d) Precession
31.
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 one of the systems has been decoupled
because of a detected malfunction
b) The positions will be the same because they are an average of three
difference positions
c) The positions are likely to differ because they are calculated from
different sources
d) The positions will only differ if an error has been made when inputting the
present position at the departure airport
32.
What is the effect on the Mach number and TAS in an aircraft that is climbing with constant CAS?
a) Mach number increases; TAS increases
b) Mach number remains constant; TAS increases
c) Mach number decreases; TAS decreases
d) Mach number increases; TAS remains constant
33.
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) Geographic co-ordinates
b) By waypoints name
c) Hexadecimal
d) Bearing and distance
34.
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, in 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
35.
When is the last point at which an INS or IRS may be selected to NAV mode?
a) On operation of the TOGA switch when opening the throttles for the take-off
b) Immediately prior to push back or taxi from the gate
c) After passengers and freight are aboard
d) At the holding point
36.
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) vehicle longitude
c) velocity along the local parallel of latitude
d) change of longitude
37.
What method of entering waypoints can be used on all INS equipments?
a) Latitude and longitude
b) Waypoint name
c) Distance and bearing
d) Navaid identifier
38.
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 are likely to differ because they are calculated from
different sources
b) The positions will only differ if one of the systems has been decoupled
because of a detected malfunction
c) The positions will only differ if an error has been made when inputting the
present position at the departure airport
d) The positions will be the same because they are an average of three
different positions
39.
Some inertial reference and navigation systems are known as strapdown. This means that:
a) gyros, and accelerometers are mounted on a stabilised platform in the
aircraft
b) only the gyros and not the accelerometers, become part of the units fixture to the aircraft structure
c) the gyroscopes and accelerometers become part of the units fixture to the aircraft structure
d) gyros and accelerometers need satellite information input to obtain a
vertical reference
40.
In order to maintain an accurate vertical using a pendulous sytem, an aircraft inertial platform incorporates a device:
a) with damping and a period of 84.4 min
b) without damping and a period of 84.4 sec
c) without damping and a period of 84.4 min
d) with damping and a period of 84.4 sec
41.
Gyro-compassing of an inertial reference system (IRS) is accomplished with the mode selector switched to:
a) STBY
b) ATT/REF
c) ALIGN
d) ON
42.
In an Inertial Reference System, accelerations are measured in relation to:
a) WGS 84 Earth co-ordinates
b) local vertical at the aircraft position
c) aircraft axis
d) the direction of true north
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 9flux valve) positioned in the wing-tip
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) Magnetic variation is calculated by each IRS based on the respective IRS position and the aircraft magnetic heading
44.
After alignment, is it possible to update IRS positions?
a) No
b) Yes, the pilots can insert updates
c) Yes – by operation of the TO/GA switch, the runway threshold co-
ordinates are inserted into the IRS
d) Yes, theprocess is automatic in flight from the DMEs
45.
After alignment of the stable platform of an Inertial Navigation System, the output data from the platform is:
a) latitude, longitude and attitude
b) acceleration north/south and east/west, attitude and true heading
c) latitude, longitude and true heading
d) acceleration north/south and east/west and true heading
46.
A laser reference system (IRS), as compared to a gyro reference system (INS):
a) the platform is strapped down but the accelerometers are not
b) is strapped down and is not adversely affected by g-forces
c) is not strapped down and is adversely affected by g-forces
d) the accelerometers are strapped down but the platform is not
47.
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) gyroscopic inertia, earth precession and pendulous oscillation
b) movements in the yawing plane, secondary precession and pendulous oscillation
c) aircraft manoeuvres, earth rotation, transport wander and coriolis
d) vertical velocities, earth precession, centrifugal forces and transport drift
48.
On a triple-fit IRS system, present positions on the CDU:
a) will only differ if one IRS has been decoupled due to a detected
malfunction
b) will not differ as the information is averaged
c) will only differ if an initial input error of aircraft position has been made
d) are likely to differ as the information comes from different sources
49.
The azimuth gyro of an inertial unit has a drift of 0.0*Q After a flight of 12 hrs with a ground speed of 500 kt, the error on the aeroplane position is approximately:
a) 6 NM
b) 60 NM
c) 12 NM
d) 1 NM
50.
On an INS, what is the output of the E/W second-stage integrator?
a) Velocity E/W
b) Distance E/W
c) Velocity N/S
d) Distance N/S
51.
Which of the following can be input to the FMC using a maximum of 5 alphanumerics:
a) Waypoints, airway designators and latitude and longitude
b) Navigation facilities, reporting points and airway designators
c) Waypoints, latitude and longitude and SIDs/STARs
d) ICAO aerodrome indicators, navigation facilities and SIDs/STARs
52.
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
53.
In a ring laser gyro, the purpose of the dither motor is to:
a) overcome laser lock
b) compensate for transport wander
c) stabilise the laser frequencies
d) enhance the accuracy of the gyro at all rotational rates
54.
The FMC position is:
a) The average of the IRS and radio navigation positions
b) Computer generated from the radio navigation positions
c) The average of the IRS positions
d) Computer generated from the IRS and radio navigation positions
55.
What is the name given to an Inertial Reference System (IRS) which has the gyros and accelerometers as part of the units fixture to the aircraft structure?
a) Rigid
b) Strapdown
c) Ring laser
d) Solid state
56.
On the IRS, selection of ATT mode gives?
a) attitude information only
b) altitude, heading, and groundspeed
c) altitude, attitude, and heading
d) attitude and heading
57.
Double integration of the output from the east/west accelerometer of an inertial navigation system (INS) in the NAV MODE give:
a) velocity east/west
b) distance east/west
c) vehicle longitude
d) distance north/south
58.
Gyro-compassing in an INS:
a) is not possible in flight as the gyros can differentiate between acceleration
due to aircraft movement and initial alignment errors
b) is possible in flight as the gyros can differentiate between acceleration due
to aircraft movement and initial alignment errors
c) is not possible in flight as the gyros cannot differentiate between
acceleration due to aircraft movement and initial alignment errors
d) is possible in flight as the gyros cannot differentiate between acceleration
due to aircraft movement and initial alignment errors
59.
In what formats can created waypoints be entered into the scratch pad of the B737-400 FMS?
a) Place, Place Bearing/Distance, Along-Track Displacement, Latitude and
Longitude
b) Place Bearing/Distance, Place Bearing/Place Bearing, Along-Track
Displacement, Latitude and Longitude
c) Place Bearing/Distance, Place Bearing/Place Bearing, Across-Track
Displacement, Latitude and Longitude
d) Place Bearing/Distance, Place Distance/Place Distance, Along-Track
Displacement, Latitude and Longitude
60.
Alignment of INS and IRS equipments can take place in which of the following modes?
a) NAV and ALIGN
b) ATT and ALIGN
c) NAV and ATT
d) ALIGN and ATT
61.
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 prior to movement of the aircraft off the gate
c) NAV mode must be selected on the runway just prior to take-off
d) NAV mode must be selected when the alignment procedure is commenced
62.
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 the square of time, t?
b) sinusoidal
c) proportional to t
d) proportional to t/2
63.
In what plane is gyro wander known as drift?
a) Horizontal and vertical
b) Neither – it is a separate phenomenon
c) Vertical
d) Horizontal
64.
Which of the following lists the first three pages of the FMC/CDU normally used to enter data on initial start-up of te B737-400 Electronic Flight Intrument System?
a) IDENT – POS INIT – RTE
b) IDENT – RTE – DEPARTURE
c) POS INIT – RTE – IDENT
d) POS INIT – RTE – DEPARTURE
65.
The period of validity of an FMS database is:
a) varies depending on the area of operational cover
b) 56 days
c) 28 days
d) one week
66.
The full alignment of the stable platform on an Inertial Navigation System:
a) may be carried out on the ground or when in straight and level flight
b) may be carried out during any phase of flight
c) may be carried out at any time so long as an accurate position is inserted into the system
d) is only possible on the ground when the aircraft is at a complete stop
67.
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) XTK/TKE
d) TK/GS
68.
The alignment time, at mid-latitudes, for an Inertial Reference System using laser ring gyros is approximately:
a) 2 min
b) 5 min
c) 20 min
d) 10 min
69.
Aircraft position determined by radio navigation in an FMC is derived from:
a) VOR/DME
b) VOR/ADF
c) DME only
d) DME ranges and/or VOR/ADF bearings
70.
The sensors of an INS measure:
a) acceleration
b) the horizontal component of the earth’s rotation
c) velocity
d) precession
71.
How is the radio position determined by the FMC in the B737-400 Electronic Flight Instrument System?
a) DME ranges and/or VOR/ADF bearings
b) DME/DME
c) VOR/DME range and bearing
d) DME/DME or VOR/DME
72.
When initial position is put into an FMS, the system:
a) cannot detect input errors, and accepts whatever is put in
b) rejects initial longitude error, but it will accept latitude error
c) rejects initial latitude or longitude error
d) rejects initial latitude error, but it will accept longitude error
73.
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) There is little or no spin up time and it is insensitive to gravitational (g) forces
b) The platform iskept stable relative to the earth mathematically rather than mechanically but it has a longer spin up time
c) It does not suffer from lock in error and it is insensitive to gravitational (g) forces
d) There is little or no spin up time and it does not suffer from lock in error
74.
The resultant of the first integration from the north/south accelerometer of an inertial navigation system (INS) in the NAV MODE is:
a) change latitude
b) groundspeed
c) velocity along the local meridian
d) latitude
75.
An aircraft in the northern hemisphere is making an accurate rate one turn to the right.If the initial heading was 135o, after 30 seconds the direct reading magnetic compass should read:
a) more than 225o
b) less than 225o
c) 225o
d) more or less than 225o depending on the pendulous suspension used
76.
The data that needs to be inserted into an Inertial Reference System in order to enable the system to make a successful alignment for navigation is:
a) aircraft position in latitude and longitude
b) the position of an in-range DME
c) airport ICAO identifier
d) aircraft heading
77.
During initial alignment an inertial navigation system is north aligned by inputs from:
a) vertical accelerometers and the north gyro
b) computer matching of measured gravity magnitude to gravity magnitude of initial alignment
c) horizontal accelerometers and the east gyro
d) the aircraft remote reading compass system
78.
What are the positions (in the order left to right) on the Boeing 737-400 IRS MSU mode selector?
a) OFF ON ALIGN NAV
b) OFF STBY ALIGN NAV
c) OFF ALIGN NAV ATT
d) OFF STBY ATT NAV
79.
With reference to inertial navigation systems, a TAS input is:
a) not required
b) required for rhumb line navigation
c) required for Polar navigation
d) required to provide a W/V read out
80.
Inertial Reference System sensors include:
a) one east-west and one north-south gyro; one east-west and one north-
south accelerometer
b) laser gyros mounted in the direction of the aircraft axis
c) accelerometers, and laser gyros, mounted in the direction of the aircraft
axis
d) accelerometers mounted in the direction of the aircraft axis
81.
An Inertial Navigation System, what is the output of the first stage North/South integrator?
a) Latitude
b) Velocity along the local meridian
c) Change of latitude
d) Groundspeed
82.
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) Beam lock
c) Dither
d) Zero drop
83.
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) gyroscopic inertia, earth rotation and real drift
b) vertical velocities, earth precession, centrifugal forces and transport drift.
c) movement in the yawing plane, secondary precession and pendulous
oscillation
d) aircraft manoeuvres, earth rotation, transport wander and coriolis
84.
The ICAO definition of ETA is the:
a) estimated time en route
b) estimated time of arrival at an en-route point or fix
c) actual time of arrival at a point or fix
d) estimated time of arrival at destination
85.
ATT Mode of the Inertial Reference System (IRS) is a back-up mode providing:
a) only attitude information
b) navigation information
c) only attitude and heading information
d) altitude, heading and position information
86.
In the B737-400 Flight Management System the CDUs are used during pre-flight to:
a) manually initialise the IRSs, FMC and Autothrotle with dispatch
information
b) manually initialise the Flight Director System and FMC with dispatch
information
c) automatically initialise the IRSs and FMC with dispatch information
d) manully initialise the IRSs and FMC with dispatch information
87.
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) On final approach
b) Just after take-off
c) At top of climb
d) At top of descent
88.
From the departure point, the distance to the point of equal time is:
a) inversely proportional to the total distance to go
b) proportional to the sum of ground speed out and ground speed back
c) inversely proportional to ground speed back
d) inversely proportional to the sum of ground speed out and ground speed back
89.
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 only be aligned in the ALIGN mode
b) INS/IRS can be aligned in either the ALIGN or ATT mode
c) INS/IRS can only be aligned in NAV mode
d) INS/IRS can be aligned in either the ALIGN or NAV mode
90.
When and where are IRS positions updated?
a) When the FMS is in IRS ONLY NAV operation
b) When the VHF Nav Radios are selected to AUTO
c) Only on the ground during the alignment procedure
d) During all phases of flight
91.
An aircraft is climbing at a constant CAS in ISA conditions . What will be the effect on TAS and Mach No?
a) TAS decreases and Mach No increases
b) Both increase
c) TAS increases and Mach No decreases
d) Both decrease
92.
The term drift refers to the wander of the axis of a gyro in:
a) the vertical plane
b) the vertical and horizontal plane
c) the horizontal plane
d) any plane
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