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Rolled Instruments 1
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Questions in this quiz (42)
1Total Air Temperature (TAT) is:
- AHigher or equal to the Static Air Temperature (SAT); TAT is a function of altitude and SAT.
- BLower than Static Air Temperature (SAT); TAT is a function of altitude and SAT
- CLower than Static Air Temperature (SAT); TAT is a function of Mach number and SAT
- DHigher or equal to Static Air Temperature (SAT); TAT is a function of Mach number and SAT
2The air speed indicator is a differential manometer measuring the difference between:
- AThe static pressure and the dynamic pressure
- BThe total pressure and the static pressure
- CThe total pressure and the dynamic pressure
- DThe dynamic pressure and the static pressure
3Indication of Mach number is obtained from:
- AAn ordinary airspeed indicator scaled for Mach numbers instead of knots
- BA kind of echo sound comparing velocity of sound with indicated airspeed
- CIndicated speed and altitude using a speed indicator with an altimeter type aneroid
- DIndicated speed (IAS) compared with true airspeed (TAS) from the air data computer
4The alternate static source of a non-pressurised aircraft is located in the flight deck; when used, the static pressure sensed is likely to be
- AHigher than ambient pressure due to aerodynamic suction
- BHigher than ambient pressure if QNH is greater than 1013 hpa
- CLower than ambient pressure if QNH is greater than 1013 hpa
- DLower than ambient pressure due to aerodynamic suction
5EAS is equal to:
- ATAS corrected for compressibility and density errors
- BCAS corrected for compressibility error
- CTAS corrected for compressibility error
- DCAS corrected for density error
6The parameter that determines the relationship between EAS and TAS is:
- AMach number
- BPressure altitude
- CDensity altitude
- DOAT
7If the static ports are completely clogged up by ice during a climb, the vertical speed indicator shows:
- AAn increasing rate of climb f the ambient static pressure decreases
- BZero
- CA descent if the outside static pressure is less than the pressure in the instrument's gauge
- DA constant rate of climb, even if the aircraft is levelling out
8If the pitot tube becomes blocked during a descent, the airspeed indicator
- AUnder-reads or over-reads, depending on the air density
- BOver-reads
- CIndicates a constant speed
- DUnder-reads
9The open-ended tube parallel to the longitudinal axis of the aircraft senses the:
- ADynamic pressure
- BTotal pressure plus static pressure
- CTotal pressure
- DStatic pressure
10The response time of the vertical speed detector may be decreased by adding a:
- AReturn spring
- BSecond calibrated port
- CBimetallic strip
- DCorrection based on an acceleration sensor.
11Which of the following statements about hard and soft iron in relation to magnetism is correct?
- ABoth hard and soft iron are of non-permanent nature.
- BHard iron magnetism is of a permanent nature, and soft iron is of a non-permanent nature
- CHard iron is of a non-permanent nature, and soft iron is of a permanent nature
- DBoth hard and soft iron are of a permanent nature
12When turning onto a northerly heading the rose of a magnetic compass tends to "undershoot", when turning onto a southerly heading it tends to "overshoot":
1) these compass indications are less reliable in the Northern Hemisphere than in the Southern Hemisphere.
2) there commas oscillations following a lateral gust are not identical if the aircraft is heading north or south
3) this behaviour is due to the mechanical construction of the compass
4) this behaviour is a symptom of a badly sun compass- A2 and 3
- B1 and 3
- C1, 2, and 4
- D2, 3, and 4
13The purpose of compass swinging is to determine the deviation of a magnetic compass:
- AAt any latitude
- BOn any heading
- COn a given heading
- DAt a given latitude
14A pilot wishes to turn right on to a southerly heading with 20 bank at latitude 20N. Using a direct reading magnetic compass, in order to achieve this he must stop the turn on an approximate heading of:
- A200
- B160
- C170
- D180
15Among the systematic errors of the directional gyro, the error due to the earth rotation make the north reference turn in the horizontal plane. At a mean latitude of 45N, this reference turns by:
- A7.5/hour to the left
- B10.5/hour to the right
- C7.5/hour to the right
- D15/hour to the right
16Concerning the directional gyro, the apparent drift rate due to the Earth's rotation is a function of
- ALongitude
- BMagnetic longitude
- CLatitude and longitude
- DLatitude
17After the initial 90 degrees of a turn at constant pitch and bank, a classic artificial horizon indicates:
- AToo much nose-up and too much bank
- BPitch and bank correct
- CToo much nose-up and bank correct
- DToo much nose-up and too little bank
18The flux valve of a gyromagnetic compass:
1. Feeds the error detector
2. Feeds the direct indicating compass
3. Gives the earth's magnetic field direction
The combination regrouping all of the correct statements is:- A1, 2
- B3
- C2, 3
- D1, 3
19The accelerometers of a strap-down IRS are in line with:
- AThe geographical directions
- BThe aircraft axes
- CThe local meridian and parallel
- DThe local vertical and the local meridian
20In an INS, ground speed is calculated:
- ABy integrating gyro precession in N/S and E/W directions respectively
- BBy integrating measured acceleration
- CFrom TAS and W/V from ADC
- DFrom TAS and W/V from RNAV data
21Considering a stabilised platform inertial system, the principle of operation requires the use of at least
- A3 rate gyros and 2 accelerometers.
- B3 rate gyros and 4 accelerometers.
- C2 rate gyros and 3 accelerometers.
- D2 rate gyros and 2 accelerometers.
22The sensors of an INS measure
- AThe horizontal component of the earth's rotation
- BVelocity
- CAcceleration
- DPrecession
23The Notification (LOG ON) is a FANS application which consists in:
- ARequesting to transfer datalink communication to the next ATC centre on the route
- BSending automatically aircraft surveillance data to the ATS facility
- CEstablishing air/ground connection to verify if the datalink communication can be performed
- DTransmitting datalink messages between the pilot and ATC controller
24The ADS-C is a FANS application performed:
- ASemi automatically, the pilot has to define a set of data to downlink but cannot define the type of report contract
- BManually, the pilot has to define the set of data to downlink and the type of report contract
- CSemi automatically, the pilot cannot define the set of data to downlink but can define the type of report contract
- DAutomatically, without any crew action to define the set of data to downlink or the type of report contract
25The FMS enables to fly an optimum flight profile. For this, the FMC uses:
1. Flight crew entered flight plan data
2. Data from the ADC
3. Aircraft position
4. A memorised relief world data base
5. Data from the FMC navigation
The combination that regroups all of the correct statements is:- A1, 2, 5
- B1, 2, 3, 5
- C1, 3, 5
- D2, 3, 4
26Concerning the FMS, entering a cost index of zero results in:
- AMinimum airspeed.
- BMinimum range airspeed
- CMaximum cruising airspeed
- DMaximum range airspeed
27In LEGS mode the FMS displays the following: (Select those that apply):
i) True Track
ii) Variation
iii) Elevation of Waypoints
iv) TAS
v) Distance to Waypoints- Aii, iv, v
- Bi, ii, iii, iv, v
- Ci, v
- Di, ii, iv
28The FMS vertical navigation management is generally performed based on:
- AThe baro altitude input from the ADC
- BThe GPS altitude computed by the GPS receiver
- CA mix of bars and GPS altitudes
- DThe geometric altitude input from the TAWS
29The radio altimeter is required to indicate zero heigh AGL as the main wheels touch down on the runway. For this reason, it is necessary to:
- AAdjust the gross height according to the aeroplane instantaneous pitch
- BCompensate for residual cable height and cable length
- CHave a specific radio altimeter dedicated to automatic landing
- DChange the display scale in short final, in order to have a precise readout
30The radio altimeter supplies data to the following system(s):
1. Altitude alert system
2. TCAS
3. GPWS
4. Automatic landing system
The combination that regroups all the correct statements is:- A3
- B3, 4
- C1, 4
- D2, 3, 4
31An EFIS includes the following components:
- AFMS, symbol generator, display unit(s)
- BADC, inertial navigation computer, display unit(s)
- CDisplay unit(s) only
- DSymbol generator, display unit(s), control panel
32The purpose of the Navigation Display (ND) is to display the following information:
- ATerrain map, navaid bearings, flight director active modes
- BFlight plan, weather radar, terrain map, TCAS symbols
- CFlight plan, engine failure, naiads, resolution advisory (RA)
- DIntruding traffics, TCAS symbols, weather radar
33The characteristics of the SATCOM transmissions, used for data link communications are
- ALine of sight limitation, no variable quality of signals distorted by ionospheric conditions
- BNo line of sight limitation, no variable quality of signals distorted by ionospheric conditions
- CLine of sight limitation, variable quality of signals distorted by ionospheric conditions
- DNo line of sight limitation, variable quality of signals distorted by ionospheric conditions
34According to AMC 25-11 concerning the electronic display systems, the colour associated with a warning-type alert is:
- AMagenta
- BYellow
- CRed
- DAmber
35On a modern aircraft, the flight director modes are displayed on the:
- AControl panel of the flight director only
- BUpper strip of the ND
- CUpper strip of the PFD
- DUpper strip of the ECAM
36The Navigation Display (ND) of an EFIS equipped aircraft can display the following data:
- AFlight plan, weather radar, terrain map, intruding traffics
- BFlight plan, engine failure, navaids, resolution advisories
- CIntruding traffics, altitude, autopilot active modes, weather radar
- DTerrain map, navaid bearings, flight director active modes
37In a radio altimeter, the height measurement is based upon:
- AA pulse transmission, for which time between transmission and reception is measured on a circular scanning screen.
- BA wave transmission, for which the frequency shift by doppler effect after ground reflection is measured.
- CA frequency modulated wave, for which the frequency difference between the transmitted wave and the received wave after ground reflection is measured
- DA triangular amplitude modulation wave, for which modulation phase shift between transmitted and received waves after ground reflection is measured
38The radio altimeter:
1. Operates in the 1600-1660 kHz range
2. Operates in the 4200-4400 Mhz range
3. Measures a frequency difference
4. Measures an amplitude difference
The combination that regroups all of the correct statements is:- A1, 3
- B2, 3
- C1, 4
- D2, 4
39When climbing at a constant CAS above the tropopause in ISA:
- ATAS and Mach will increase
- BTAS will increase, and Mach No will remain constant
- CTAS and Mach No will remain constant
- DTAS will increase, and Mach No will decrease
40Increasing the altimeter sub-scale setting by 1hPa will:
- Adecrease the altimeter reading by about 30 feet at all altitudes
- BDecrease the altimeter reading by an amount between 30 and 100 feet, depending on the aircraft altitude
- CIncrease the altimeter reading by about 30 feet at all altitudes
- DIncrease the altimeter reading by an amount between 30 and 100 feet, depending on the aircraft altitude
41In an INS, the E/W accelerations are converted into an E/W speed (kts) at the first stage of integration and into E/W distance (nm) at the second stage of integration. This gives:
- Adeparture, which is multiplied by the Cosine of the present latitude to obtain d long (min) which is used to automatically update the present longitude
- Bd long (min) which is used to automatically update the present longitude
- Cdeparture, which is multiplied by the Sine of the present latitude to obtain d long (min) which is used to automatically update the present longitude
- Ddeparture, which is multiplied by Secant of the present latitude to obtain d long (min) which is used to automatically update the present longitude.
42By definition an Earth gyro is a
- AGyro having 2 degrees of freedom
- BGyro having 2 degrees of freedom, but controlled by some external force
- CTied gyro controlled by gravity
- DGyro having one plane of freedom at right angles to the plane of Earth rotation
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- Jakobus Pretoriu
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