Casa de juan

Written at October 5, 2010 on English with a size of 194.32 KB.

"Heading hold" is normally: REGARDED AS A BASIC OF AUTOMATIC STABILISATION EQUIPMENT
1 - Route modifications2 - Crossing constraints3 - Transfer of ATC center 4 - Speed changes. The combination which regroups all of the correct statements is: 1, 2, 3, 4
1 - TAS2 - IAS 3 - Mach NUmber. The combination that regroups all of the correct statements is: 2, 3
A "Bourdon Tube" is used in: PRESSURE SENSORS
A blocked pitot head with a clear static source causes the airspeed indicator to: REACT LIKE AN ALTIMETER
A closed loop control system in which a small power input controls a much larger power output in a strictly proportionate manner is known as: A SERVOMECHANISM
A control system consisting of four pendulous vanes is used in: AN AIR DRIVEN ARTIFICIAL HORIZON
A D-ATIS is: AN ATIS MESSAGE RECEIVED BY DATALINK
A directional gyro consists of a: NB: the degree(s) of freedom of a gyro does not take into account its rotor spin axis: 2 DEGREES-OF-FREEDOM HORIZONTAL AXIS GYRO
A directional gyro is corrected for an apparent drift due to the earth's rotation at latitude 30°S. During a flight at latitude 60°N, a drift rate of 15.5°/h to the right is observed.The apparent wander due to change of aircraft position is: 5 °/h TO THE LEFT
A directional gyro is:; 1- a gyroscope free around two axis; 2- a gyroscope free around one axis; 3- capable of self- orientation around an earth-tied direction; 4- incapable of self-orientation around an earth-tied direction; The combination which regroups all of the correct statements is: 1-4
A dynamic pressure measurement circuit is constituted of the following pressure probes: TOTAL PRESSURE AND STATIC PRESSURE
A flight control system is fail-operational if, in the event of a failure: THE APROACH, FLARE AND LANDING CAN BE COMPLETED AUTOMATICALLY
A flight control system is fail-passive if, in the event of a failure: THERE IS NO SIGNIFICANT OUT-OF-TRIM CONDITION OR DEVIATION OF FLIGHT PATH OT ATTITUDE BUT THE LANDING IS NOT COMPLETED AUTOMATICALLY
A flight control system which can, in the event of a failure, complete automatically the approach, flare and landing is called fail ... OPERATIONAL
A float type fuel gauge:; 1 - gives a mass information; 2 - gives information independent of aircraft's manoeuvres and attitude changes; 3 - gives information all the more accurate as the tank is full; 4 - is typically a DC powered system; The combination that regroups all of the correct statements is: 4
A flux valve detects the horizontal component of the earth''s magnetic field 1- the flux valve is made of a pair of soft iron bars 2- the information can be used by a "flux gate" compass or a directional gyro 3- the flux gate valve casing is dependent on the aircraft three inertial axis 4- the accuracy on the value of the magnetic field indication is less than 0,5°.; The combination regrouping all the correct statements is : 2-4
A free gyro has its rotor axis horizontal and is aligned with the geographic meridian. If this stationary free gyro is situated at latitude 60°N, the apparent drift rate according to the earthbound observer is: 13 °/H TO THE RIGHT
A Full Authority Digital Engine Control (FADEC) has the following functions :; 1- flow regulation (fuel, decelerations and accelerations monitoring); 2- automatic starting sequence ; 3- transmissions of engine data to the pilot's instruments; 4- thrust management and protection of operation limits ; 5- monitoring of the thrust reversers; The combination regrouping all the correct statements is: 1, 2, 3, 4 ,5
A gravity erector system is used to correct the errors on: AN ARTIFICIAL HORIZON
A gravity type erector is used in a vertical gyro device to correct errors on: AN ARTIFICIAL HORIZON
A ground proximity warning system (GPWS), when mandatory installed on board an aircraft, must in all cases generate : AT LEAST ONE SOUND ALARM TO WHICH A VISUAL ALARM CAN BE ADDED
A gyromagnetic compass is a system which always consists of:; 1 - a horizontal axis gyro; 2 - a vertical axis gyro; 3 - an earth's magnetic field detector; 4 - an erection mechanism to maintain the gyro axis horizontal; 5 - a torque motor to make the gyro precess in azimuth; The combination regrouping all the correct statements is: 1, 3, 4, 5
A laser gyro can measure: A ROTATION MOTION
A leak in the pitot total pressure line of a non-pressurized aircraft to an airspeed indicator would cause it to: UNDER-READ
A magnetic tachometer consists of: A PERMANENT MAGNET TURNING INSIDE A NON MAGNETIC DRAG CUP
A manifold pressure gauge of a piston engine measures : absolute pressure in intake system near the inlet valve
A MAYDAY datalink message can be sent to the ATC via the: CPDLC application.
A millivoltmeter measuring the electromotive force between the "hot junction" and the "cold junction" of a thermocouple can be directly graduated in temperature values provided that the temperature of the: COLD JUNCTION IS MAINTAINED CONSTANT
A pilot engages the control wheel steering (CWS) of a conventional autopilot and carries out a manoeuvre in roll. When the control wheel is released, the autopilot will: MAINTAIN THE FLIGHT ATTITUDE OBTAINED AT THAT MOMENT
A pilot wishes to turn left on to a northerly heading with 10° bank at a latitude of 50° North. Using a direct reading compass, in order to achieve this he must stop the turn on an approximate heading of: 030 °
A pilot wishes to turn left on to a southerly heading with 20° bank at a latitude of 20° North. Using a direct reading compass, in order to achieve this he must stop the turn on an approximate heading of: 160°
A pilot wishes to turn right on to a southerly heading with 20° bank at a latitude of 20° North. Using a direct reading compass, in order to achieve this he must stop the turn on an approximate heading of: 200°
A pilot wishes to turn right through 90° on to North at rate 2 at latitude of 40 North using a direct reading compass. In order to achieve this the turn should be stopped on an indicated heading of approximately: 330°
A pitot tube covered by ice which blocks the ram air inlet will affect the following instrument (s): AIRSPEED INDICATOR
A pitot tube covered by ice which blocks the ram air inlet will affect the following instrument (s): AIRSPEED INDICATOR ONLY
A radio altimeter can be defined as a: SELF-CONTAINED ON-BOARD AID USED TO MEASURE THE TRUE HEIGHT OF THE AIRCRAFT
A radio altimeter uses the following frequency band: SHF (SUPER HIGH FREQUENCY)
A radio altimeter uses the following frequency band: 4200 MHZ TO 4400 MHZ
A radio altimeter uses: TWO ANTENNAS: ONE FOR THE TRANSMISSION AND AN OTHER FOR THE RECEPTION
A rate gyro is used in a: 1 - directional gyro indicator. 2 - turn co-ordinator. 3 - artificial horizon. The combination regrouping all the correct statements is: 2
A ring laser gyro can measure: ROTATION ABOUT ITS SENSITIVE AXIS
A ring laser gyro is: a device which measures angular movements.
A servo-assisted altimeter is more accurate than a simple altimeter because the small movements of: THE CAPSULES ARE DETECTED BY A VERY SENSIBLE ELECTRO-MAGNETIC PICK-OFF
A stall warning system is based on measuring the ANGLE OF ATTACK
A Stand-by-horizon or emergency attitude indicator: COTAINS ITS OWN SEPARATE GYRO
A strapdown inertial system consists in: a platform attached to the aircraft chassis and which includes gyroscopes and accelerometers.
A synchroscope is used on aircraft to: SET SEVERAL ENGINES TO THE SAME SPEED
A TCAS 2 (Traffic Collision Avoidance System) provides: THE INTRUDER RELATIVE POSITION AND POSSIBLY AND INDICATION OF A COLLISION AVOIDANCE MANOUBRE WTHIN THE VERTICAL PLANE ONLY
A TCAS II generates a resolution advisory (RA) when: A SERIOUS COLLISION THREAT EXISTS
A TCAS II generates a traffic advisory (TA) when: A POTENTIAL COLLISION THREAT EXISTS
A TCAS Resolution Advisory (RA) voice message "CLIMB - CLIMB NOW" repeated twice is generated: after a "DESCEND" RA when a reversal in the vertical manoeuvre sense is required.
A temperature sensor has a recovery factor of 0,95. The temperature measured is equal to: STATIC AIR TEMPERATURE (SAT) + 95% OF THE RAM RISE
A thermocouple consists of: A JUNCTION OF TWO DISSIMILAR METALS
A thermocouple type temperature sensing is composed of: TWO DISSIMILAR METALS JOINED TOGUETHER AT ONE END (CALLED HOT JUNCTION OR MEASURE JUNCTION)
A thermocouple type thermometer consists of: TWO METAL CONDUCTORS OF DIFFERENT TYPE CONNECTED AT TWO POINTS
A three-phase electrical tachometer consists of: A THREE-PHASE GENERATOR, S SYNCHRONOUS MOTOR AND A MAGNETIC TACHOMETER
A three-phase electrical tachometer utilises a generator feeding: A SYNCHRONOUS MOTOR TURNING A DRAG CUP
A turn indicator is an instrument which indicates rate of turn. Rate of turn depends upon: 1: bank angle 2: aeroplane speed 3: aeroplane weight The combination regrouping the correct statements is: 1 AND 2
A vertical speed indicator measures the difference between: THE INSTANTANEOUS STATIC PRESSURE AND THE STATIC PRESSURE AT A PREVIOUS MOMENT
A vibration indicator receives a signal from different sensors (accelerometers). It indicates the: VIBRATION AMPLITUDE AT A GIVEN FREQUENCY
A VMO-MMO warning device consists of an alarm connected to: A BAROMETRIC ANEROID CAPSULE SUBJECTED TO A STATIC PRESSURE AND AN AIRSPEED SENSOR SUBJECTED TO A DYNAMIC PRESSURE
About a magnetic compass: TURNING ERROR IS DUE TO THE VERTICAL COMPONENT OF THE EARTH’S MAGNETIC FIELD
According to AMC 25-11 concerning the electronic display systems, the colour associated with a caution-type alert is: AMBER OR YELOW
According to AMC 25-11 concerning the electronic display systems, the red colour is associated with the following alert: WARNING
According to AMC 25-11 concerning the electronic display systems, the green colour is associated with the following indication: ENGAGED MODE
According to AMC 25-11 concerning the electronic display systems, the colour associated with an armed mode is: WHITE OR CYAN
According to AMC 25-11 concerning the electronic display systems, the colour associated with an engaged mode is: GREEN
According to AMC 25-11 concerning the electronic display systems, the colour associated with an armed mode is: white or cyan.
According to AMC 25-11 concerning the electronic display systems, the green colour is associated with the following indication: engaged mode.
According to AMC 25-11 concerning the electronic display systems, the colour associated with a caution-type alert is: amber or yellow.
According to AMC 25-11 concerning the electronic display systems, when exceeding the limits of the flight envelope, the colour accepted to alert the flight crew is: red.
According to AMC 25-11 concerning the electronic display systems, the colours used are: red for flight enveloppe and system limits, green for autopilot or flight director engaged modes.
According to AMC 25-11 concerning the electronic display systems, the colour associated with an engaged mode is: green.
According to AMC 25-11 concerning the electronic display systems, the white/cyan colours are associated with the following indication: armed mode.
According to AMC 25-11 concerning the electronic display systems, the red colour is associated with the following alert: warning.
According to AMC 25-11 concerning the electronic display systems, the amber/yellow colours are associated with the following alert: caution.
According to AMC 25-11 concerning the electronic display systems, the colour associated with a warning-type alert is: red.
According to CS 25, section 3 concerning the Electronic Display Systems, the white/cyan colours are associated with the following indication: ARMED MODE
According to CS25, a CVR (Cockpit Voice Recorder) must record:; 1 - communications transmitted from or received in the aeroplane by radio; 2 - communications of flight-crew members on the flight deck; 3 - communications of flight-crew members on the flight deck using the aeroplane's interphone system; 4 - audio signals identifying navigation or approach aids introduced into a headset or speaker; The combination regrouping all the correct statements is: 1, 2, 3, 4
According to CS25, the definition of the control wheel steering mode (CWS) is: "Where the pilot has the ability to make inputs to the: automatic pilot by movement of the normal control wheel".
According to the range of pressure to be measured (low, medium, high), different types of pressure sensors are used.; Classify the following sensors by order of increasing pressure for which they are suitable:; 1- bellows type; 2- Bourdon tube type; 3- aneroid capsule: 3, 1, 2
After an aircraft has passed through a volcanic cloud which has blocked the total pressure probe inlet of the airspeed indicator, the pilot begins a stabilized descent and finds that the indicated airspeed: DECREASES STEADILY
After having programmed your flight director, you see that the indications of your ADI (Attitude Director Indicator) are as represented in diagram N°1 of the appended annex. On this instrument, the command bars indicate that you must bank your airplane to the left and : INCREASE THE FLIGHT ATTITUDE UNTIL THE COMMAND BARS RECENTRE ON THE SYMPOLOGIC AIRPLANE
After having programmed your flight director, you see that the indications of your ADI (Attitude Director indicator) are as represented in diagram N°1 of the appended annex. On this instrument, the command bars indicate that you must : INCREASING THE FLIGHT ATTITUDE AND BANK YOUR AIRPLANE TO THE LEFT UNTIL THE COMMAND BARS RECENTRE ON THE SYMBOLIC AEROPLANE
After the initial 90 degrees of a turn at constant pitch and bank, a classic artificial horizon indicates: TOO MUCH NOSE-UP AND TOO LITLE BANK
Alarms are standardised and follow a code of colours. Those requiring action but not immediately, are signalled by the colour: AMBER
Among the following functions of an autopilot, those related to the aeroplane stabilization are:; 1 - pitch attitude holding; 2 - IAS or Mach number holding; 3 - horizontal wing holding; 4 - VOR radial holding; The combination that regroups all of the correct statements is: 1, 3
Among the following functions of an autopilot, those related to the airplane guidance are:; 1- pitch attitude holding; 2- horizontal wing holding; 3- indicated airspeed or Mach number holding; 4- altitude holding; 5- VOR axis holding; 6- yaw damping; The combination regrouping all the correct statements is: 3, 4 AND 5
Among 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 45°N, this reference turns by... 10. 5 °/ HOUR TO THE RIGHT
An "altitude warning system" must at least warn the crew :; 1- when approaching the pre-selected altitude; 2- when the airplane is approaching the ground too fast; 3- in case of a given deviation above or below the pre-selected altitude (at least by an aural warning); 4- in case of excessive vertical speed; 5- when approaching the ground with the gear retracted; The combination regrouping all the correct statements is : 1, 3
An aeroplane is cruising at FL 220. The auto-throttle maintains a constant CAS.; If the OAT increases, the Mach number: REMAINS CONSTANT
An aeroplane is cruising at FL 60 with a TAS of 100 kt in standard atmosphere.; In these conditions:; 1 - the TAS is approximately 10% higher than the IAS; 2 - the difference between the EAS and the CAS is negligible; 3 - the speed displayed on the airspeed indicator is a CAS if the position error and instrument error are zero; The combination regrouping all of the correct statements is: 1, 2, 3.
An aeroplane is cruising at FL 60 with a TAS of 100 kt in standard atmosphere. In these conditions: 1 - the TAS is approximately 10% higher than the IAS 2 - the difference between the EAS and the CAS is negligible 3 - the speed displayed on the airspeed indicator is a CAS if the position error and instrument error are zero The combination regrouping all of the correct statements is: 1, 2, 3.
An aeroplane is flying at FL300 with a TAS of 470kt in standard conditions. The Mach number is: 0.80
An aeroplane is in a steady climb. The auto-throttle maintains a constant Mach number. If the total temperature remains constant, the calibrated airspeed: DECREASES
An aeroplane is in steady climb. The auto-throttle maintains a constant calibrated airspeed. If the total temperature remains constant, the Mach number: INCREASES
An aeroplane is in steady cruise at flight level 270. The auto-throttle maintains a constant calibrated airspeed. If the static air temperature decreases, the Mach number: REMAINS CONSTANT
An aeroplane is in steady descent. The auto-throttle maintains a constant calibrated airspeed. If the total temperature remains constant, the Mach number: DECREASES
An air data computer 1. supplies the ground speed and the drift (angle) 2. determines the total temperature and the true altitude 3. receives the static pressure and the total pressure 4. supplies the true airspeed to the inertial unit 5. determines the Mach number, the outside (static) air temperature The combination regrouping all the correct statements is: 3, 4 AND 5
An airborne instrument, equipped with a gyro with 1 degree of freedom and a horizontal spin axis is a: NB: the degree(s) of freedom of a gyro does not take into account its rotor spin axis. TURN INDICATOR
An airborne instrument, equipped with a gyro with 2 degrees of freedom and a horizontal spin axis is: NB: the degree(s) of freedom of a gyro does not take into account its rotor spin axis: A DIRECTIONAL GYRO
An aircraft flies steadily on a heading 270°. The flight director is engaged in the heading select mode (HDG SEL), heading 270° selected. If a new heading 360° is selected, the vertical trend bar: DEVIATED TO THE RIGHT AND WILL BE CENTRED AS SOON AS YOU ROLL THE AIRCRAFT TO THE BANK ANGLE CALCULATED BY THE FLIGHT DIRECTOR
An aircraft is descending from FL 390 to ground level at maximum speed. The limits in speed will be: INITIALLY THE MMO, THE THE VMO BELOW A CERTAIN FLIGHT LEVEL
An aircraft is equipped with an autopilot and an auto-throttle. When the altitude hold mode (ALT HOLD) is active: THE INDICATED AIRSPEED (IAS) IS MAINTAINED CONSTANT BY THE AUTO-THROTTLE SYSTEM
An aircraft is equipped with one altimeter that is compensated for position error and another one altimeter that is not. Assuming all other factors are equal, during a straight symmetrical flight: THE GREATER THE SPEED, THE GREATER THE ERROR BETWEEN THE TWO ALTIMETERS
An aircraft is flying at flight level FL180 and Mach number 0.36. Its onboard thermometer reads TAT = - 5°C. Considering that the probe recovery coefficient is 0.84, the present weather conditions compared with the standard atmosphere are: STANDARD + 10°C
An aircraft is in a steady left turn, with too much left rudder (skidding turn). The yaw damper system: IS NOT DESIGNED TO PROVIDE A BALANCED TURN
An aircraft is in a steady right turn, with not enough right rudder (slipping turn). The yaw damper system: is not designed to provide a balanced turn.
An aircraft is turning right, with too much bank (slipping turn). The yaw damper system: IS NOT DESIGNED TO PROVIDE A BALANCED TURN
An aircraft takes-off on a runway with an alignment of 045°; the compass is made for the northern hemisphere. During rolling take-off, the compass indicates: A VALUE BELOW 045°
An airplane is cruising at FL 190. The auto-throttle maintains a constant CAS. If the OAT decreases, the Mach number: REMAINS CONSTANT
An airplane is cruising at FL 220. The auto-throttle maintains a constant CAS. If the OAT decreases, the Mach number: REMAINS CONSTANT
An airplane is flying at FL140 with a CAS of 260kt in standard conditions. The Mach number is: 0.51
An airplane is in steady cruise at flight level 290. The auto-throttle maintains a constant Mach number. If the total temperature increases, the calibrated airspeed: REMAINS CONSTANT
An airspeed indicator displays: IAS
An airspeed indicator includes a capsule; inside this capsule is: TOTAL PRESSURE AND OUTSIDE IS STATIC PRESSURE
An altimeter contains one or more aneroid capsules. Inside these capsules is: A VERY LOW RESIDUAL PRESSURE AND OUTSIDE IS STATIC PRESSURE
An aneroid capsule: 1 - measures differential pressure 2 - measures absolute pressure 3 - is used for low pressure measurement 4 - is used for very high pressure measurement The combination regrouping all the correct statements is: 2, 3
An angle of attack sensor may consist of:; 1 - an inertial system computing the difference between flight path and flight attitude; 2 - a conical slotted probe which positions itself to determine the angle of attack; 3 - a vane detector which positions the rotor of a synchro; The combination regrouping all the correct statements is: 2, 3
An automatic ILS approach can be flown only: WITHIN A RANGE OF CROSSWINDS AND LEVELS OF TURBULENCE
An automatic landing system necessitating that the landing be continued manually in the case of a system failure during an automatic approach is called "FAIL...." “PASSIVE”
An autopilot capable of holding at least altitude and heading mode is compulsory: FOR IFR OR NIGHT FLIGHTS WITH ONLY ONE PILOT
An autopilot system: MUST PROVIDE AT LEAST AIRCRAFT STABILISATION FUNCTIONS
An EFIS includes the following components: symbol generator, display unit(s), control panel.
An inertial Navigation System (INS) is: A SELF CONTAINED SYSTEM WHICH OPERATES WITHOUT SIGNALS FROM THE GROUND
An inertial navigation system: can operate as stand alone equipment without any interface with other navigation equipments.
An inertial reference and navigation system is a "strapdown" system when: THE GYROSCOPES AND ACCELEROMETERS ARE APRT OF THE UNIT’S FIXTURE TO THE AIRCRAFT STRUCTURE
An outer loop Automatic Flight Control System (AFCS), is a system which: CONTAINS A PARALLEL ACTUATOR WHICH PROVIDES CONTROL THROUGH 100% OF THE CONTROL RANGE AND MOVES BOTH THE CVONTROL IMPUTS AND THE COCKPIT CONTOL STICK
Any vibration displayed on an engine vibration monitoring system for a turbojet: INDICATES ROTOR IMBALANCE
As a result of the failure of the central air data computer (CADC), the inertial navigation system (INS) will no longer provide information about: THE WIND DIRECTION AND SPEED
Assuming that the CAS remains constant, if the total pressure probe is blocked, the IAS: REMAINS CONSTANT DURING LEVEL FLIGHT, INCREASES DURING A CLIMB AND DECREASES DURING A DESCENT
Assuming the flight level and Mach number remain constant, when the OAT decreases: IAS REMAINS CONSTANT AND TAS DECREASES
Assuming the flight level and Mach number remain constant, when the OAT increases: IAS REMAINS CONSTANT AND TAS INCREASES
At a given altitude, the hysteresis error of an altimeter varies substantially with the: TIME PASSED AT THIS ALTITUDE
At a given altitude, the hysteresis error of an altimeter varies substantially with the: TIME PASSED AT A GIVEN ALTITUDE
At a low bank angle, the measurement of rate-of-turn actually consists in measuring the: YAW RATE OF THE AIRCRAFT
At flight level and mach number constant, if OAT decreases, the CAS: REMAINS CONSTANT
At flight level and mach number constant, if OAT increases, the CAS REMAINS CONSTANT
Automatic Flight Control System (AFCS) parallel actuator position is: PASSED TO THE PILOT VIA CONTROL STICK POSITION
Automatic Flight Control System (AFCS) series actuator is: NOT DISPLAYED IN THE COCKPIT DUE TO SHORT DURATION OF OPERATION
Below the tropopause in standard conditions, when climbing at a constant Mach number: TAS DECREASES
Below the tropopause in standard conditions, when descending at a constant Mach number: TAS INCREASES
Below the tropopause with no temperature inversion, when climbing at constant Mach number: TAS DECREASES
Below the tropopause, when descending at a constant CAS: MACH NUMBER DECREASES AND THE VELOCITY OF SOUND INCREASES
Below the tropopause, with no temperature inversion, when descending at constant Mach number: TAS INCREASES
Calibrated Air Speed (CAS) is obtained from Indicated Air Speed (IAS) by correcting for the: POSITION AND INSTRUMENT ERRORS
Calibrated Air Speed (CAS) is obtained from Indicated Air Speed (IAS) by correcting for the following errors: 1 - position 2 - compressibility 3 - instrument 4 - density The combination regrouping all the correct statements is: 1, 3
Calibrated Air Speed (CAS) is: INDICATED AIR SPEED (IAS) CORRECTED FOR POSITION AND INSTRUMENT ERRORS
CAS can be obtained from the following data: EAS AND PRESSURE ALTITUDE
CAS is equal to: IAS CORRECTED FOR POSITION AND INSTRUMENT ERRORS
CAS is obtained from IAS by correcting for the: POSITION AND INSTRUMENT ERRORS
Command bars of the flight director may be present on the:; 1 - HSI; 2 - CDU; 3 - ADI; The combination that regroups all of the correct statements is: 3
Compared with a conventional gyro, a laser gyro : HAS A LONGER LIFE CYCLE
Compared with a stabilised platform inertial system, a strapdown inertial system:1 - can aligne while the aircraft is moving2 - has a quicker alignment phase3 - is more reliable in time. The combination that regroups all the correct statements is: 2, 3
Compared with a stabilised platform inertial system, a strapdown inertial system:; 1 - has a longer alignment phase in time; 2 - has a shorter alignment phase in time; 3 - is more reliable in time.; 4 - is less reliable in time; The combination that regroups all of the correct statements is: 2, 3
Comparing the media used to transmit datalink communications, the appropriate classification from the slowest to the fastest data transmission rate is: HF DATALINK, VHF DATALINK, SATCOM
Comparing the radio navigation system and the inertial navigation system: 1 - the radio position is accurate when in DME range 2 - the radio position may be obtained whatever the position on the earth 3 - the inertial position may be obtained whatever the position on the earth. The combination regrouping all the correct statements is: 1, 3.
Components of the FMS are:1 - CDU (Control and Display Unit)2 - Database3 - FMC (Flight Management Computer)4 - Electronic check-lists5 - GPWS mode controllerThe combination that regroups all of the correct statements is: 1, 2, 3
Concerning a fail-operational flight control system, in the event of a failure: 1 - the system will operate as a fail-passive system. 2 - the landing is not completed automatically. 3. - the landing is completed automatically.The combination that regroups all of the correct statements is: 1, 3.
Concerning a fail-passive flight control system, in the event of a failure:; 1 - there may be a significant deviation of flight path or attitude; 2 - there is no significant deviation of flight path or attitude; 3 - there is no significant out-of-trim condicondition; 4 - there may be a significant out-of-trim condition; The combination that regroups all of the correct statements is: 2, 3
Concerning a fail-passive flight control system, in the event of a failure:; 1 - there may be a significant deviation of flight path or attitude; 2 - there is no significant deviation of flight path or attitude; 3 - the landing is not completed automatically; 4 - the landing is completed automatically; The combination that regroups all of the correct statements is: 2, 3
Concerning a fail-passive flight control system, in the event of a failure: 1 - there may be a significant deviation of flight path or attitude 2 - there is no significant deviation of flight path or attitude 3 - there is no significant out-of-trim condicondition 4 - there may be a significant out-of-trim condition The combination that regroups all of the correct statements is: 2, 3.
Concerning a fuel gauge system, a pilot is more interested by the: MASS OF THE FUEL THAN THE VOLUME OF THE FUEL
Concerning the airspeed indicator, IAS is: THE INDICATED READING ON THE INSTRUMENT
Concerning the command bars of a flight director: IT IS POSSIBLE TO REMOVE THEM BY SWITCHING THE FLIGHT DIRECTOR OFF
Concerning the direct reading magnetic compass, the turning error: INCREASES WITH THE MAGNETIC LATITUDE
Concerning the directional gyro, the apparent drift rate due to the earth's rotation is a function of: LATITUDE
Concerning the flexible take-off mode, the temperature selected in the FMS is: higher than the ambiant airfield temperature, in order to achieve a reduced power setting.
Concerning the flight warning system (FWS), advisory messages may be: ANY COLOUR EXPECT RED, AND PRESERABLY NOT AMBER
Concerning the flight warning system (FWS), caution messages: ARE THE NEXT HIGHEST PRIORITY ALERT MESSAGES AFTER WARNING MESSAGES
Concerning the flight warning system (FWS), if aural signals are provided, the signal for: A WARNING SHOULD ALWAYS TAKE PRIORITY OVER THAT FOR A CAUTION
Concerning the flight warning system (FWS), warning messages: ARE HIGHUEST PRIORITY ALERT MESSAGES
Concerning the FMS (Flight Management System), entering a cost index of zero results in: MAXIMUM RANGE AIRSPEED
Concerning the FMS (Flight Management System), entering a cost index of zero: RESULTS IN MINIMUM TRIP FUEL
Concerning the FMS (Flight Management System), entering a high cost index results in: HIGH AIRSPEED AND HIGH FUEL TRIP
Concerning the FMS (Flight Management System), the cost index is determined by dividing: AIRCRAFT OPERATING COST BY FUEL COST
Concerning the FMS, the parameters used to work out the vertical flight profile are:; 1 - zero fuel weight; 2 - cost index; 3 - fuel quantity; 4 - oxygen quantity available for flight crew; 5 - minimum safe enroute altitude; The combination that regroups all of the correct statements is: 1, 2, 3
Concerning the pitot and static system, the static pressure error varies according to: 1 - altimeter setting 2 - speed 3 - angle of attack The combination that regroups all of the correct statements is: 2 and 3.
Concerning the pitot and static system, the static pressure error: is caused by disturbed airflow around the static ports.
Concerning the radio altimeter, the maximum range for indication is typically from touchdown to: 2500 FT
Concerning the TCAS 2, when receiving a resolution advisory (RA), crew members should: INMEDIATELY INITIATE THE REQUIRED MANOUEUVRE
Concerning the TCAS II: NO PROTECTION IS AVAILABLE AGAINST AIRCRAFT NOT EQUIPPED WITH A SERVICEABLE SSR TRANSPONDER
Concerning the TCAS II:; 1 - Neither advisory nor traffic display is provided for aircraft that do not have an operating transponder; 2 - TCAS II operation is independent of ground-based air traffic control; 3 - TCAS II has feeds from the radioaltimeter; The combination that regroups all of the correct statements is: 1, 2, 3
Considering a flight director of the "command bars" type: 1 - the vertical bar is always associated with the roll channel 2 - the vertical bar may be associated with the pitch channel 3 - the horizontal bar may be associated with the roll channel 4 - the horizontal bar is always associated with the pitch channel The combination regrouping all the correct statements is: 1, 4
Considering a flight director of the "command bars" type: THE HORIZONTAL BAR IS ASSOCIATED WITH THE PITCH CHANNEL
Considering a flight director of the "command bars" type: THE VERTICAL BAR IS ASSOCIATED WITH THE ROLL CHANNEL
Considering a flight director of the command bars type: ; 1 - the vertical bar is always associated with the roll channel ; 2 - the vertical bar may be associated with the pitch channel ; 3 - the horizontal bar may be associated with the roll channel ; 4 - the horizontal bar is always associated with the pitch channel ; The combination that regroups all of the correct statements is: 1, 4
Considering a flight director of the command bars type: THE HORIZONTAL BAR IS ASSOCIATED WITH THE PITCH CHANNEL
Considering a flight director of the command bars type: THE VERTICAL BAR IS ASSOCIATED WITH THE ROLL CHANNEL
Considering a modern thrust computer, during a steady climb: N1 IS AUTOMATICALLY ADJUSTED AS AIRCRAFT CLIMBS
Considering a modern thrust computer, during a steady climb: N1 is automatically adjusted as aircraft climbs.
Considering a stabilised platform inertial system, this platform:1 - can be servo-controlled in azimuth2 - is kept levelled during alignment phase only3 - is always kept levelled. The combination that regroups all of the correct statements is: 1,3
Considering a stabilised platform inertial system:; 1 - the rate gyros and the accelerometers are mounted on the same platform; 2 - the rate gyros and the accelerometers are mounted on two separated platforms; 3 - the principle of operation requires at least 2 2 rate gyros; 4 - the principle of operation requires at least 2 accelerometers; The combination that regroups all of the correct statements is: 1, 4
Considering a strapdown inertial system, the IRU (Inertial Reference Unit) measures: accelerations and angular rates.
Considering a strapdown inertial system, the operating principle requires the use of at least: 3 laser gyros and 3 accelerometers.
Considering an air driven artificial horizon, when an airplane accelerates during the take-off run, the result is: A FALSE NOSE-UP INDICATION
Considering an air driven artificial horizon, when an airplane decelerates on ground during the landing, the result is: A FALSE NOSE-DOWN INDICATION
Considering an airspeed indicator, a second stripped needle, if installed, indicates: MAXIMUM OPERATING AIRSPEED (VMO)
Considering the relationship between CAS and EAS:EAS IS ALWAYS LOWER THAN OR EQUAL TO CAS
Direct reading magnetic compass errors are: DUE TO NORTH CHANGE, DEPENDING ONTHE BANK ANGLE AND MAGNETIC HEADING
Due to its conception, the altimeter measures a: PRESSURE ALTITUDE
Due to the rotation of the earth, the apparent drift of a horizontal free gyroscope at a latitude of 30°N is: 7. 5 ° PER HOUR TO THE RIGHT
Due to the rotation of the earth, the apparent drift of a horizontal free gyroscope at a latitude of 30°S is: 7. 5 ° PER HOUR TO THE LEFT
Due to the rotation of the earth, the apparent drift of a horizontal free gyroscope at a latitude of 45°N is: 11 ° PER HOUR TO THE RIGHT
During a category III automatic approach, the position signals in the vertical plane under 200 ft are based on: A RADIO ALTIMETER
During a climb at a constant calibrated airspeed (CAS) below the tropopause in ISA conditions: THE MACH NUMBER INCREASES AND THE LOCAL SPEED OF SOUND DECREASES
During a climb at a constant calibrated airspeed (CAS) below the tropopause in standard conditions: TAS AND MACH NUMBER INCREASE
During a climb at a constant CAS below the tropopause in standard atmosphere: TAS AND MACH NUMBER INCREASE
During a climb at a constant CAS below the tropopause in standard atmosphere: THE MACH NUMBER INCREASES AND THE SPEED OF SOUND DECREASES
During a climb at a constant IAS below the tropopause in ISA conditions: THE MACH NUMBER AND THE TRUE AIRSPEED INCREASE
During a climb at a constant Mach number below the tropopause in ISA conditions: CAS AND TAS DECREASE
During a climb at a constant Mach number below the tropopause in ISA conditions: IAS AND TAS DECREASE
During a climb at a constant Mach number below the tropopause in standard atmosphere: CAS AND TAS DECREASE
During a climb with the autopilot engaged in the V/S mode (holding of vertical speed), the auto-throttle: can be operated in the SPEED mode (holding of IAS).
During a climb, if the total pressure head is rapidly clogged up by ice, the sensed total pressure remains constant and: TEH STATIC PRESSURE DECREASES, IMPLYING AND INCREASING IAS
During a climb, the total pressure probe of the airspeed indicator becomes blocked; if the pilot maintains a constant indicated airspeed, the true airspeed: DECREASES UNTIL REACHING THE STALL SPEED
During a deceleration phase at constant attitude, the control system of an air driven artificial horizon results in the horizon bar indicating a: NOSE DOWN ATTITUDE
During a descent at a constant calibrated airspeed (CAS) below the tropopause in ISA conditions: MACH NUMBER AND TAS DECREASE
During a descent at a constant CAS below the tropopause in standard atmosphere: MACH NUMBER AND TAS DECREASE
During a descent at a constant IAS below the tropopause in ISA conditions: MACH NUMBER AND TAS DECREASE
During a descent at a constant Mach number below the tropopause in ISA conditions: CAS AND TAS INCREASE
During a descent at a constant Mach number below the tropopause in ISA conditions: IAS AND TAS INCREASE
During a final approach, if the flight director system is engaged in the G/S mode (holding of ILS Glide Slope), the position of the horizontal command bar indicates: THE CORRECTION ON THE PITCH TO BE APPLIIED TO JOIN AND FOLLOW THE ILS GLIDE SLOPE
During a final approach, the flight director is engaged in the G/S mode (holding of ILS Glide Slope). If the horizontal command bar is deviating upward, it means that: THE PITCH ATTITUDE MUST BE INCREASED
in the LOC mode (holding of localizer axis). If the vertical command bar is deviating to the left, it means that the aircraft: MUST BE ROLLED TO THE LEFT
During a final approach, the flight director system is engaged in the G/S mode (holding of ILS Glide Slope). The position of the horizontal command bar indicates:; 1 - the position of the aircraft relative to the ILS Glide Slope; 2 - the correction on the pitch to be applied to join and follow the ILS Glide Slope; 3 - the pitch attitude of the aircraft; The combination regrouping all the correct statements is: 2
During a final approach, the flight director system is engaged in the LOC mode (holding of Localizer axis). The position of the vertical command bar indicates: THE CORRECTION ON THE BANK TO BE APPLIED TO JOIN AND FOLLOW THE LOCALIZER AXIS
During a manual ILS final approach, the auto-throttle: CAN BE OPERATED IN THE SPEED MODE (HOLDING OF IAS)
During an acceleration phase at constant attitude, the control system of the artificial horizon results in the horizon bar indicating a: NOSE-UP ATTITUDE
During an autocoupled ILS approach followed by an automatic landing, the guidance signals in the vertical plane under 200 ft are computed according to the: RADIO ALTITUDE
During an autocoupled ILS approach followed by an automatic landing, the guidance signals in the vertical plane under 200 ft are computed according to the: radio altitude.
During an automatic ILS final approach, the auto-throttle: can be operated in the SPEED mode (holding of IAS).
During an automatic landing, between 50 FT AGL and touch down, the autopilot maintains: A VERTICAL SPEED ACCORDING TO THE RADIO ALTIMETER HEIGHT
During deceleration following a landing in a southerly direction, a magnetic compass made for the northern hemisphere indicates: NO APPARENT TURN
During deceleration following a landing in a westerly direction, a magnetic compass made for the northern hemisphere indicates: AN APPARENT TURN TO THE SOUTH
During deceleration following a landing in an easterly direction, a magnetic compass made for the northern hemisphere indicates: AN APPARENT TURN TO THE SOUTH
During deceleration following a landing in an easterly direction, a magnetic compass made for the southern hemisphere indicates: AN APPARENT TURN TO THE NORTH
During descent, the total pressure probe of the airspeed indicator becomes blocked. In this case: 1 - IAS becomes greater than CAS 2 - IAS becomes lower than CAS 3 - maintaining IAS constant, VMO may be exceeded 4 - maintaining IAS constant, aircraft may stall The combination regrouping all the correct statements is: 2, 3
During large control inputs from an automatic flight control system (AFCS), the control stick in the cockpit is moved to inform the pilot of the action. This is: ACHIEVES BY A PARALLEL ACTUATOR
During the approach, the radio altimeter indicates 950 ft. This is: THE HEIGHT OF THE LOWEST WHEELS WITH REGARD TO THE GROUND
During the ground run take-off phase, the auto-throttles allow to: HOLD N1
EAS can be obtained from the following data: CAS AND PRESSURE ALTITUDE
EAS is equal to: CAS CORRECTED FOR COMPRESSIBILITY ERROR
EAS is equal to: IAS CORRECTED FOR POSITION, INSTRUMENT AND COMPRESSIBILITY ERRORS
Electrical requirements for an alumel/chromel indicating system are: POWER FOR GAUGE LIGHTNING ONLY
Equivalent Air Speed (EAS) is obtained from Calibrated Air Speed (CAS) by correcting for: COMPRESSIBILITY ERROR
Equivalent Air Speed (EAS) is obtained from Calibrated Air Speed (CAS) by correcting for the following errors: 1 - position 2 - compressibility 3 - instrument 4 - density The combination regrouping all the correct statements is: 2
Equivalent Air Speed (EAS) is obtained from Indicated Air Speed (IAS) by correcting for the following errors: 1 - instrument 2 - position 3 - density 4 - compressibility The combination regrouping all the correct statements is: 1, 2, 4
Equivalent Air Speed (EAS) is: CALIBRATED AIRSPEED (CAS) CORRECTED FOR COMPRESSIBILITY ERROR
Equivalent Air Speed (EAS) is: INDICATED AIR SPEED (IAS) CORRECTED FOR POSITION, INSTRUMENT AND COMPRESSIBILITY ERRORS
Except for airplanes under 5,7 t airworthiness certificate of which is subsequent to 31 march 1998, a flight data recording system must be able to store the recorded data for a minimum of the last : 25 HOURS
Flight Director Information supplied by an FD computer is presented in the form of command bars on the following instrument: ADI ATTITUDE DIRECTOR INDICATOR
Flying manually during a final approach, the flight director system is engaged in the G/S mode (holding of ILS Glide Slope). If the aircraft is above the ILS Glide Slope, the horizontal command bar: MAY BE CENTRED IF THE PILOT IS CORRECTING TO COME BACK ON THE ILS GLIDE SLOPE
Flying manually during a final approach, the flight director system is engaged in the LOC mode (holding of localizer axis). If the aircraft is left of the Localizer axis, the vertical command bar: MAY BE CENTRED IF THE PILOTS IS CORRECTING TO COME BACK ON THE LOCALIZER AXIS
Flying manually during a final approach, the flight director system is engaged in the LOC mode (holding of localizer axis). If the aircraft is right of the Localizer axis, the vertical command bar: MAY BE CENTRED IF THE PILOTS ITS CORRECTING TO COME BACK ON THE LOCALIZER AXIS
Flying manually during a final approach, the flight director system is engaged in the G/S mode (holding of ILS Glide Slope). If the aircraft is below the ILS Glide Slope, the horizontal command bar: MAY BE CENTRED IF THE PILOT IS CORRECTING TO COME BACK ON THE ILS GLIDE SLOPE
For a directional gyro, the system which detects the local vertical supplies: A LEVELLING ERECTION TORQUE MOTOR
For a FMS designed with the lateral navigation (LNAV) capability coupled to the autopilot, the FMS lateral command output is: A ROLL ANGLE OR A HEADING TARGET
For a FMS designed with the vertical navigation (VNAV) capability coupled to the autopilot, the FMS vertical command output can be:; 1 - an angle of attack; 2 - a flight path angle; 3 - a speed target; The combination that regroups all of the correct statements is: 2, 3
For an aircraft EFIS equipped:; 1- the ND displays flight director command bars; 2- the PFD displays the altimeter setting; 3- the ND displays the attitude of the aircraft; 4- the flight mode annunciator is part of the ND; The combination regrouping all the correct statements is: 2
For an aircraft flying a true track of 360° between the 5°S and 5°N parallels, the precession error of the directional gyro due to apparent drift is equal to: APPROXIMATELY 0°/HOUR
For compatibility between the different components of a flight warning system, the priority from the highest to the lowest is: STALL, WINDSHEAR, GPWS, TCAS
For most FMS the Fuel prediction function, which computes the remaining fuel along the flight plan, takes into account the following situations:; 1- the additional drag resulting in a flight carried out with the landing gear extended; 2- the current wind computed or the resulting ground speed; 3- the additional drag resulting in a flight carried out with the flaps stucked, partly extended; 4- the additional drag resulting in a missing fuselage or wing element in compliance with the CDL; The combination that regroups all of the correct statements is: 2
For most FMS the Fuel prediction function, which computes the remaining fuel along the flight plan, takes into account the following situations: 1- the additional drag resulting in a flight carried out with the landing gear extended 2- the additional drag resulting in a missing fuselage or wing element in compliance with the CDL 3- the additional drag resulting in a flight carried out with the flaps stucked, partly extended 4- the current wind computed or the resulting ground speed The combination that regroups all of the correct statements is: 4.
For most FMS the Fuel prediction function, which computes the remaining fuel along the flight plan, takes into account the following situations: 1- the additional drag resulting in a flight carried out with the landing gear extended 2- the current wind computed or the resulting ground speed 3- the additional drag resulting in a flight carried out with the flaps stucked, partly extended 4- the additional drag resulting in a missing fuselage or wing element in compliance with the CDL The combination that regroups all of the correct statements is: 2.
For TAS calculations, the ADC uses the following parameters: 1) SAT 2) TAT 3) static pressure 4) total pressure The combination regrouping all the correct statements is: 2, 3, 4
For the same TAS, when pressure altitude decreases below the tropopause: MACH NUMBER DECREASES
For the same TAS, when pressure altitude increases below the tropopause: MACH NUMBER INCREASES
Gas turbine engine rotational speed (RPM) is usually sensed using eitheR: A 3 PHASE AC TACHOMETER GENERATOR OR AN AC PHONIC WHEEL SYSTEM
Given the following parameters, in a capacitance fuel gauge, the correct formula is:A = area of platesD = distance between platesE = dielectric permittivity: CAPACITANCE= E X A/D
Given: - Ts the static temperature (SAT) - Tt the total temperature (TAT) - Kr the recovery coefficient - M the Mach number The total temperature can be expressed approximately by the formula: TT=TS (1+0.2 M2)
Given: E = electromotive force (emf) T = hot junction temperature K = constant The relationship that applies to a thermocouple is: E = K x T
Given: E = electromotive force (emf) Tc = cold junction temperature Th = hot junction temperature K = constant. The relationship that applies to a thermocouple is: E= K X TH
Given: M is the Mach number Ts is the static temperature Tt is the total temperature: TS=TT (1+ 0.2 M2)
Given: Mach number M = 0.70 measured impact temperature = - 48 °C the recovery factor (Kr) of the temperature probe = 0.85 The OAT is: - 65°C
Given: MH = magnetic heading of the aircraft Omega = yawing rate of the aircraft The yaw damper computer sends a motion order to the rudder if: the derivative of Omega according to time is not equal to zero.
Given: Pt = total pressure Ps = static pressure Dynamic pressure is: PT-PS
Given: Pt = total pressure Ps = static pressure Pd = dynamic pressure: PT=PD+PS
Given: Pt = total pressure Ps = static pressure Pso = static pressure at sea level Dynamic pressure is: PT-PS
Given: Pt = total pressure Ps = static pressure Pso = static pressure at sea level. Calibrated airspeed (CAS) is a function of: PT-PS
Given: Pt: total pressure Ps: static pressure Pd: dynamic pressure The altimeter is fed by: PT-PD
Given: Pt: total pressure Ps: static pressure Pd: dynamic pressure The airspeed indicator is fed by: PD
Given: Zp = pressure altitude Zd = density altitude TAS can be obtained from the following data: EAS AND ZD
Given:Pt: total pressure. Ps: static pressure. Pd: dynamic pressure. The airspeed indicator measures: PT-PS
Graphic at reference shows three gyro assemblies: A, B and C. Among these gyros,; -one is a roll gyro (noted 1); -one is a pitch gyro (noted 2); -one is a yaw gyro (noted 3); The correct matching of gyros and assemblies is: 1B, 2C, 3A
Heading information given by a gyro platform, is given by a gyro at : 2 DEGREES-OF-FREEDOM IN THE HORIZONTAL AXIS
If a manifold pressure gauge consistently registers atmospheric pressure, the cause is probably: LEAK IN PRESSURE GAUGE LINE
If a TCAS Resolution Advisory (RA) requires an immediate descent while at the same time ATC requests an immediate climb, the crew should: FOLOW THE TCAS RA AND INFORM THE ATC
If an aircraft maintaining a constant CAS and flight level is flying from a warm air mass into colder air: TAS DECREASES
If an aircraft maintaining a constant CAS and flight level is flying from a cold air mass into warmer air: TAS INCREASES
If an EPR is set at a constant barometric pressure, with an increasing OAT, the thrust: REMAINS CONSTANT
If crew awareness is required and subsequent crew action may be required, the flight warning system (FWS) generates: A CAUTION MESSAGE
If immediate crew awareness is required and subsequent crew action will be required, the flight warning system (FWS) generates: A WARNING MESSAGE
If immediate recognition and corrective or compensatory action by the crew is required, the flight warning system (FWS) generates: A WARNING MESSAGE
If OAT decreases when at a constant Mach number: TAS DECREASES
If OAT decreases when at a constant TAS: MACH NUMBER INCREASES
If OAT decreases whilst maintaining a constant CAS and flight level: MACH NUMBER REMAINS CONSTANT
If OAT increases when at a constant Mach number: TAS INCREASES
If OAT increases when at a constant TAS: MACH NUMBER DECREASES
If OAT increases whilst maintaining a constant CAS and flight level: MACH NUMBER REMAINS CONSTANT
If the acceleration of an aircraft is zero, its velocity: is constant.
If the computed aircraft position becomes less accurate, the Enhanced GPWS (EGPWS) function(s) affected is (are):; 1- the "FIVE HUNDRED" voice call out; 2- the excessive rate of descent ; 3- the terrain display on the navigation display; 4- the negative climb rate or altitude loss after takeoff; The combination that regroups all of the correct statements is: 3
If the computed aircraft position becomes less accurate, the Enhanced GPWS (EGPWS) function(s) affected is (are): 1- the excessive rate of descent 2- the terrain display on the navigation display 3- the flight into terrain when not in landing conditions 4- the excessive downward deviation from an ILS The combination that regroups all of the correct statements is: 2.
If the computed aircraft position becomes less accurate, the Enhanced GPWS (EGPWS) function(s) affected is (are): 1- the "FIVE HUNDRED" voice call out 2- the excessive rate of descent 3- the terrain display on the navigation display 4- the negative climb rate or altitude loss after takeoff The combination that regroups all of the correct statements is: 3.
If the GPWS (Ground Proximity Warning System) activates, and alerts the pilot with an aural warning "DON'T SINK" (twice times), it is because : DURING TAKE-OFF OR MISSED APPROACH MANOEUVRE, THE AIRCRAFT HAS STARTED TO LOSE ALTITUDE
If the navigation function of an INS is inoperative and the control rotary switch is set to ATT, the output data of the INS is (are): ATTITUDE AND HEADING
If the navigation function of an INS is inoperative and the control rotary switch is set to ATT, the output data of the INS is (are): attitude and heading.
If the navigation function of an INS is inoperative and the control rotary switch is set to ATT, the output data of the INS are: attitude and heading.
If the navigation function of an INS is inoperative, the back up mode if existing, used to operate the INS is: THE ATT MODE WHICH SUPPLIES ATTITUDE AND HEADING DATA
If the navigation function of an INS is inoperative, the back up mode if existing, used to operate the INS is: the ATT mode which supplies attitude and heading data.
If the outside temperature at 35 000 feet is -40°C, the local speed of sound is: 595 KT
If the pilot increases the reference pressure using the sub-scale setting knob, the altitude indicated by the altimeter: INCREASES
If the pitot tube becomes blocked during a descent, the airspeed indicator: UNDER-READS
If the pitot tube ices up during a flight, the affected equipment(s) is (are): 1 - the altimeter 2 - the variometer 3 - the airspeed indicator The combination regrouping all the correct statements is: 3
If the position data (lat, long) is no longer computed an IRS, the affected system(s) is (are): the FMS.
If the static intakes are completely clogged up by ice during a climb, the VSI shows: ZERO
If the static ports are completely clogged up by ice during a climb, the vertical speed indicator shows: ZERO
If the static source of an altimeter becomes blocked during a descent the instrument will: CONTINUE TO DISPLAY THE READING AT WHICH THE BLOCKAGE OCCURRED
If the static source to an airspeed indicator (ASI) becomes blocked during a descent the instrument will: OVER-READ
If the static source to an altimeter becomes blocked during a climb, the instrument will: CONTINUE TO INDICATE THE READING AT WHICH THE BLOCKAGE OCCURRED
If the tanks of your aircraft only contain water, the capacitor gauges indicate: A MASS OF WATER DIFFERENT FROM ZERO, BUT INACCURATE
If the total pressure intake on the pitot tube is rapidly clogged up by ice during flight, what effect will it have on the airspeed indication during a climb? THE TOTAL PRESSURE IS TRAPPED WHILE THE STATIC PRESSURE DECREASES, IMPLYING AN INCREASING INDICATED AIRSPEED
If warning, caution, or advisory lights are installed in the cockpit, they must, unless otherwise approved by the Authority, be green, for: SAFE OPERATION LIGHTS
If warning, caution, or advisory lights are installed in the cockpit, they must, unless otherwise approved by the Authority, be red for: WARNING LIGHTS
If warning, caution, or advisory lights are installed in the cockpit, they must, unless otherwise approved by the Authority, be amber for: CAUTION LIGHTS
If, during a descent:; - the pneumatic altimeter reading is constant; - the vertical speed indicator shows zero; - the IAS is increasing; the most likely explanation is that: THE STATIC PORTS ARE COMPLETELY BLOCKED
If, in the event of a failure, the approach, flare and landing can be completed by the remaining part of the automatic system, such an automatic landing system is considered as: FAIL-OPERATIONAL
If, in the event of a failure, there is no significant out-of-trim condition or deviation of flight path or attitude but the landing is not completed automatically, such an automatic landing system is considered as: FAIL- PASSIVE
If, with the automatic flight control system (AFCS) engaged, the pilot presses the force trim release button to allow a manual input to the flight controls: THE SPRING UNITS WILL BECOME INEFFECTIVE
In a 3-phase synchronous motor type tachometer indicator :; 1- the transmitter is a direct current generator; 2- the voltage is proportional to the transmitter drive speed ; 3- the frequency is proportional to the transmitter drive speed; 4- the speed indicating element is a galvanometer; 5. the speed indicating element is an asynchronous motor driving a magnetic tachometer; The combination regrouping all the correct statements is: 3, 5
In a datalink system, the downlink communications consist in transmitting data: FROM THE AIRCRAFT TO THE GROUND
In a datalink system, the uplink communications consist in transmitting data: FROM THE GROUND TO THE AIRCRAFT
In a datalink system, the uplink communications consist in transmitting data: from the the ground to the aircraft.
In a directional gyro, gimballing errors are due to: A BANKED ATTITUDE
In a FMS, MCDUs are used pre-flight to manually initialise with dispatch information the:; 1 - Inertial Reference System (when installed). ; 2 - Flight Director and Auto Flight Control System.; 3 - Air Data Computer.; 4 - Flight Management Computer .; The combination regrouping all of the correct statements is: 1, 4
In a gyromagnetic compass, the direction of the earth's magnetic field is given by the: FLUX VALVE
In a gyromagnetic compass, the flux valve feeds the: ERROR DETECTOR
In a gyromagnetic compass, the gyro axis:1 - is maintained vertical2 - is maintained horizontal3 - is servo-controlled in azimuth4 - is free in azimuth. The combination that regroups all of the correct statements is: 2, 3
In a gyromagnetic compass, the signal feeding the precession amplifier comes from: ERROR DETECTOR
In a inertial navigation system, the integration process makes a: TIME MULTIPLICATION
In a inertial navigation system, the integration process makes a: time multiplication.
In a radio altimeter, the height measurement is based upon: A FREQUENT MODULATION WAVE, FOR WHICH THE FREQUENTY VARIATION BETWEEN THE TRANSMITTED WAVE AND THE RECIEVED WAVE AFTER GROUND REFLECTION IS MEASURED
In a stabilised platform inertial system, the accelerations are measured in a trihedron which is: (NB : "aircraft trihedron" = pitch, roll and yaw axis): free from the aircraft trihedron.
In a standard atmosphere and at the sea level, the equivalent airspeed (EAS) is: EQUAL TO THE TRUE AIRSPEED (TAS)
In a strapdown inertial system, the accelerations are measured in a trihedron which is fixed regarding to the: aircraft's trihedron (pitch, roll and yaw axis).
In a transport airplane, an autopilot comprises, in addition to the mode display devices, the following fundamental elements :; 1- Airflow valve; 2- Sensors; 3- Comparators; 4- Computers; 5- Amplifiers; 6- Servo-actuators; The combination regrouping all the correct statements is: 2,3, 4, 5, 6
In a turn at a constant angle of bank, the turn indicator reading is: INVERSELY PROPORTIONAL TO THE AIRCRAFT TRUE AIRSPEED
In a yaw damper system, sensing of a disturbance in yaw is usually by: A RATE GYRO OR AN ACCELEROMETER
In An Air Data Computer (ADC), aeroplane altitude is calculated from: MESAUREMENT OF BAROMETIC PRESSURE FROM A STATIC SOURCE ON THE FUSELAGE
In an auto-pilot slaved powered control circuit, the system which ensures synchronisation: CAN ITSELF, WHEN IT FAILS, PREVENT THE AUTOMATIC PILOT FROM BEING ENGAGED
In an autopilot system, the basic stabilisation modes are: 1 - altitude hold 2 - pitch attitude hold 3 - roll attitude hold 4 - IAS hold The combination regrouping all the correct statements is: 2, 3.
In an autopilot system, the basic stabilisation modes are:1 - altitude hold2 - pitch attitude hold3 - roll attitude hold4 - IAS hold. The combination regrouping all the correct statements is: 2, 3
In an autopilot system, the flight path modes are:1 - Pitch attitude hold2 - IAS and Mach number hold3 - Altitude hold4 - Glide slope intercept and track The combination regrouping all the correct statements is: 2, 3, 4
In an autopilot system, the function consisting in controlling the movements around the center of gravity of the aircraft is provided by the: INNER LOOP SYSTEMS
In an autopilot system, the functions consisting in controlling the path of the aircraft are the: GUIDANCE FUNCTIONS
In an autopilot system: THE INNER LOOPS PROVIDE THE STABILITY FUNCTIONS AND THE OUTER LOOPS PROVIDE THE GUIDANCE FUNCTIONS
In an engine vibration monitoring system for a turbojet any vibration produced by the engine is: AMPLIFIED AND FILETED BEFORE BEING FED TO THE COCKPIT INDICATOR
In an inertial navigation system (INS), should the platform be displaced from the horizontal, it would oscillate with a period, called Schuler period, of about: 84 MINUTES
In an inertial navigation system, integrating once the speed in gives: A DISTANCE TRAVELLED
In an inertial navigation system, integrating once the speed in gives: a distance travelled.
In an inertial navigation system, the integration process: 1 - amounts to making a time division. 2 - amounts to making a time multiplication. 3 - enable to get accelerations from position. 4 - enable to get position from accelerations. The combination that regroups all of the correct statements is: 2, 4.
In an inertial navigation system, the principle used to obtain position is:; 1 - single integration of acceleration according to time.; 2 - double integration of acceleration according to time.; 3 - single integration of speed according to time.; 4 - double integration of speed according to time.; The combination that regroups all of the correct statements is: 2 OR 3
In an inertial navigation system, the principle used to obtain the change in speed is: single integration of acceleration according to time.
In an inertial navigation system, to know the distance travelled, it is necessary to:1 - integrate once the speed in time2 - to know the initial position3 - to know the initial Speed. The combination that regroups all of the correct statements is: 1
In an inertial navigation system, to know the distance travelled: integrating once the speed in time is sufficient.
In case of accidental closing of an aircraft's left static pressure port (rain, birds), the altimeter: OVERREADS THE ALTITUDE IN CASE OF A SIDESLIP TO THE LEFT AND DISPLAYS THE CORRECT INFORMATION DURING A SYMETRIC FLIGHT
In case of excesive descent rate, the GPWS generates the following aural warnings: “SINK RATE, SINK RATE” FOLLOWED BY “WHOOP WHOOP PULL UP” (TWICE)
In case of impending stall, the flight warning system (FWS) generates: A WARNING MESSAGE
In case of static blockage, the airspeed indicator: under-reads in climb and over-reads in descent.
In order to align an inertial reference system (IRS), it is required to insert the local geographical coordinates. This enables the IRS to: COMPARE THE LATITUDE IT FINDS WITH THAT ENTERED BY THE OPERATOR
In order to align an IRS, it is required to insert the local geographical coordinates. This enables the IRS to:; 1 - compare the computed latitude with the one entered by the pilot; 2 - compare the computed longitude with the one entered by the pilot; 3 - know the longitude; The combination that regoups all of the correct statements is: 1, 3
In order to know in which mode the auto-throttles are engaged, the crew will check the: PFD ( PRIMARY FLIGHT DISPLAY)
In order to measure temperature the cylinder head temperature (CHT) gauge utilises a: THERMOCOUPLE CONSISTING OF TWO DISSIMILAR METALS
In standard atmosphere at sea level, the EAS is: EQUAL TO THE TAS
In standard atmosphere, when climbing at constant CAS: TAS AND MACH NUMBER INCREASE
In standard atmosphere, when descending at constant CAS: TAS DECREASES
In the absence of position and instrument errors, CAS is equal to: IAS
In the absence of position and instrument errors, IAS is equal to: CAS
In the absence of position and instrument errors: IAS=CAS
In the building principle of a gyroscope, the best efficiency is obtained through the concentration of the mass: ON THE PEROPHERY AND WITH A HIGH ROTATIONAL SPEED
In the case of altitude loss during the initial climb after take off, GPWS generates an aural alert: “DON’T SHINK”
In the case of altitude loss during the initial climb after take off, GPWS generates an aural alert: "DON'T SINK".
In the directional gyro the detection system of the local vertical feeds: A LEVELLING ERECTION TORQUE MOTOR
In the event of a conflict, the TCAS 2 (Traffic Collision alert and Avoidance System) presents warnings to the crew such as: “CLIMB” OR “DESCENT”
In the event of a failure, a fail-operational flight control system will operate as a: FAIL-PASSIVE SYSTEM
In the event of a failure, a fail-operational flight control system will operate as a: fail-passive system.
In the following formula EAS = CAS x K , the compressibility factor K:; 1 - may be greater than 1; 2 - is always lower or equal to 1; 3 - depends on Mach number only; 4 - depends on pressure altitude only; The combination that regroups all of the correct statements is: 2, 3
In the gyromagnetic compass, the heading information from the flux valve is sent to the: ERROR DETECTOR
In the northern hemisphere, during a take-off run in a westerly direction, a direct reading magnetic compass indicates: AN APPARENT TURN TO THE NORTH
In the northern hemisphere, during deceleration following a landing in a southerly direction, a direct reading magnetic compass indicates: NO APPARENT TURN
In the northern hemisphere, during the take-off run in an easterly direction, a direct reading magnetic compass indicates: AN APPARENT TURN TO THE NORTH
Indication of Mach number is obtained from: INDICATED SPEED AND ALTITUDE USING A SPEED INDICATOR EQUIPPED WITH AN ALTIMETER TYPE ANEROID
Lights indicating a hazard which may require immediate corrective action must be: RED
Lights indicating the possible need for future corrective action must be: AMBER
Mach Trim is a device to compensate for: BACKING OF THE AERODYNAMIC CENTRE AT HIGH MACH NUMBERS BY MOVING THE ELEVATOR TO NOSE-UP
Machmeter readings are subject to: POSITION PRESSURE ERROR
Magnetic compass errors are: ABOUT NORTH CHANGE, DEPENDING ON THE BANK ANGLE AND MEGNETIC HEADING
Maintaining CAS and flight level constant, a fall in ambient temperature results in: LOWER TAS BECAUSE AIR DENSITY INCREASES
Mode "Localizer ARM" active on Flight Director means: SYSTEM IS ARMED FOR LOCALIZER APPROACH AND COUPLING WILL OCCUR UPON CAPTURING CENTRE LINE
Modern low altitude radio altimeters emit waves in the following frequency band: SHF (SUPER HIGH FREQUENCY)
On a large aeroplane and according to the CS25: the regulatory margin between the stall and stall warning is: 5 KT OR 5 % OF THE CAS WHICHEVER IS THE GREATER
On a large aeroplane and according to the CS25: the regulatory margin between the stall and stall warning is: 5 kt or 5% of the CAS whichever is the greater.
On a large aeroplane and according to the CS25: the stall warning system must provide an alarm with sufficient margin to prevent inadvertent stalling: WITH THE FLAPS AND LANDING GEAR IN ANY NORMAL POSITION
On a large aeroplane and according to the CS25: the stall warning system must provide an alarm with sufficient margin to prevent inadvertent stalling: with the flaps and landing gear in any normal position.
On a large aeroplane and according to the CS25: when the speed is reduced, the stall warning must begin: AT A SPEED EXCEEDING THE STALL SPEED BY NOT LESS THAN 5 KT OR 5% CAS
On a large aeroplane, the computer of a stall warning system receives information about the: ; 1 - angle of attack; 2 - engine R.P.M.; 3 - configuration; 4 - pitch and bank attitude; 5 - sideslip; The combination that regroups all of the correct statements iS: 1, 3
On a large aeroplane, the input data of the stall warning system are:1 - angle of attack2 - weight3 - bank angle4 - configuration (slats / flaps)The combination that regroups all of the correct statements is: 1, 4
On a modern aircraft, the flight director modes are displayed on the: UPPER STRIP OF THE PFD (PRIMARY FLIGHT DISPLAY)
On a modern transport category aeroplane, the engagement of the automatic pilot is checked on the display of: THE PFD (PRIMARY FLIGHT DISPLAY)
On a TCAS 2 (Traffic Collision Avoidance System) the preventive "resolution advisory" (RA) is a "resolution advisory": THAT ADVISES THE PILOT TO AVOID CERTAIN DEVIATIONS FROM THE CURRENT VERTICAL RATE BUT OES NOT REQUIRE ANY CHANGE TO BE MADE TO THAT RATE
On a TCAS 2 (Traffic Collision Avoidance System), a preventative resolution advisory: ADVISES THE PILOT TO KEEP THE VERTICAL SPEED WITHIN GIVEN LIMITS
On a TCAS2 (Traffic Collision Avoidance System), a corrective "resolution advisory" (RA) is a "resolution advisory": ASKING THE PILOT TO MODIFY EFFECTEVELY THE VERTICAL SPEED OF HIS AIRCRAFT
On the airspeed indicator of a twin-engine aeroplane, the blue radial line corresponds to the: BEST SINGLE-ENGINE RATE OF CLIMB
On the display of a TCAS 2 (Traffic alert and Collision Avoidance System), the traffic being the cause of a resolution advisory (RA) is represented by: A RED FULL SQUARE
On the display of a TCAS 2 (Traffic alert and Collision Avoidance System), a traffic advisory (TA) is represented by: AN AMBER SOLID CIRCLE
On the display of a TCAS 2 (Traffic alert and Collision Avoidance System), a resolution advisory (RA) is represented by: A RED FULL SQUARE
On the display of a TCAS 2 (Traffic alert and Collision Avoidance System), the traffic being the cause of a resolution advisory (RA) is represented by: A RED FULL SQUARE
On the display of a TCAS II (Traffic alert and Collision Avoidance System), a proximate traffic is represented by: A WHITE OR CYAN SOLID LEZENGE
On the display of a TCAS II, a traffic advisory is represented by: AN AMBER SOLID CIRCLE
On the ground, during a left turn, the turn indicator indicates: NEEDLE TO THE LEFT, BALL TO THE RIGHT
On the ground, during a right turn, the turn indicator indicates: NEEDLE TO THE RIGHT, BALL TO THE LEFT
On the INS control panel, the rotary knob can be selected to OFF, NAV or ATT positions. The correct statement is: NAV IS THE NORMAL SETTING; THE ATT POSITION IS THE BACK UP POSITION IN CASE OF FAILURE OF THE NAVIGATION FUNCTION
On the INS control panel, the rotary knob can be selected to OFF, NAV or ATT positions. The correct statement is: NAV is the normal system setting; the ATT position is the back up position in case of failure of the navigation function.
On the navigation display (ND) of an EFIS equipped aircraft, the colours used are: MAGENTA OR WHITE TO THE ACTIVE WAYPOINT (TO WAYPOINT), GREEN FOR LIGHT PRECIPITATION
One of the disadvantages of an electronic tachometer is the: NECESSITY OF A POWER SUPPLE
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: DITHER
Parallax error is: A READING ERROR
Should a defect arise in the stability augmentation system (SAS) during flight: THE PILOT WILL BE ADVISED BY AN AMBER WARNING
Some of the FMS have a navigation mode called Dead Reckoning mode (DR), computing airspeed, heading, wind data ground speed and time. This mode is: A BACK UP NAVIGATION MODE TO COMPUTE A FMS POSITION WHEN THE OTHER NAVIGATION SENSORS ARE NO LONGER OPERATING
Sound propagates through the air at a speed which only depends on: TEMPERATURE
Speed of sound is proportional to: THE SQUARE ROOT OF THE ABSOLUTE TEMPERATURE
TAS can be obtained from the following data: EAS AND DENSITY ALTITUDE
TAS is equal to: CAS CORRECTED FOR COMPRESSIBILITY AND DENSITY ERRORS
TAS is equal to: EAS CORRECTED FOR DENSITY ERROR
TAS is equal to: IAS CORRECTED FOR INSTRUMENT, POSITION, COMPRESSIBILITY AND DENSITY ERRORS
TAS is obtained from EAS by correcting for: DENSITY ERROR
TCAS 2 (Traffic Collision Avoidance System) uses for its operation: THE REPLIES FROM THE TRANSPONDERS OF OTHER AIRCRAFTS
TCAS II uses for its operation: THE REPLIES FROM THE TRANSPONDERS OF OTHER AIRCRAFT
The "airspeed hold " mode can be engaged and maintained during: CLIMBS, DESCENTS, TURNS AND POWER CHANGES
The "Bourdon tube" is used to measure: PRESSURE
The "guidance" functions of a autopilot consist in: MONITORING THE MOVEMENTS OF THE CENTRE OF GRAVITY IN THE THREE DIMENSIONS OF SPACE
The "overfly" symbol related to a waypoint on an FMS page indicates that: THE AIRCRAFT IS REQUIRED TO PASS DIRECTLY OVER THIS WAYPOINT
The ACARS allows air/ground datalink communications for: Airline Operational and Air Traffic Communications (AOC & ATC).
The accelerometers of a strap-down Inertial Reference System are in line with: THE AIRCRAFT AXES
The accelerometers of a strap-down Inertial Reference System are in line with: the aircraft axes.
The accuracy of the altitude computed by a stand alone inertial system: DECREASES EXPONENTIALLY WITH FLIGHT TIME
The accuracy of the altitude computed by a stand alone inertial system: decreases exponentially with flight time.
The ADC uses the following parameters as input data: STATIC PRESSURE, TOTAL PRESSURE, TOTAL AIR TEMPERATURE
The ADC uses the following parameters as input data: static pressure, total pressure, TAT.
The ADS is a FANS application performed: AUTOMATICALLY, WITHOUT ANY CREW ACTION TO DEFINE THE SET OF DATA TO DOWNLINK OR THE TYPE OF REPORT CONTRACT
The ADS is a FANS application which consists in: sending automatically aircraft surveillance data to the air traffic controller.
The advantages of a D.C. generator tachometer are:; 1- easy transmission of the information.; 2- independence of the information relative to the airborne electrical power supply.; 3- freedom from any spurious current due to the commutator.; The combination regrouping all the correct statements is: 1, 2
The advantages of a float type fuel gauge are (is):; 1- easy construction; 2- independence of indications with regard to aircraft attitude; 3- independence of indications with regard to the accelerations ; 4- independence of indications with regard to temperature variations; The combination that regroups all of the correct statements is: 1
The advantages of an "electric" fuel (float) gauge are :; 1- easy construction; 2- independence of indications with regard to airplane attitude; 3- independence of indications with regard to the accelerations ; 4- independence of indications with regard to temperature variations; 5- independence of indications with regard to vibrations; The combination regrouping all the correct statements is: 1
The advantages of an electrical induction tachometer are:; 1- the display is not sensitive to line resistance; 2- the measurement is independent of aircraft power supply; 3- the measurement is independent of temperature variations; 4- the option to use without restriction several indicators connected in parallel to a single transmitter; The combination regrouping all the correct statements is: 1, 2, 4
The advantages of single-phase A.C. generator tachometer are:; 1- the suppression of spurious signals due to a D.C. generator commutator; 2- the importance of line resistance on the information value; 3- the independence of the information in relation to the airborne electrical power supply; 4- the ease of transmission of the information; The combination regrouping all the correct statements is: 1, 3
The aircraft outside air temperature "probe" measures the: “TOTAL” AIR TEMPERATURE MINUS KINETIC HEATING EFFECTS IN ORDER TO OBTAIN IN THE STATIC TEMPERATURE
The aircraft radio equipment which emits on a frequency of 4400 MHz is the: RADIO ALTIMETER
The airspeed indicator of a twin-engine aircraft comprises different sectors and colour marks. The blue line corresponds to the: OPTIMUM CLIMBING SPEED WITH ONE ENGINE INOPERATIVE, OR VY
The alignment of a gyro stabilized inertial platform consists in positionning the platform relative to: the vertical axis and true north.
The alignment of a strapdown inertial system consists in: MEASURING THE EARTH ROTATION AND LOCAL GRAVITATION TO POSITION THE REFERENCE TRIHEDRON
The alignment of an inertial system can be sucessfully performed: when the aircraft is stationary.
The alignment phase of a gyro stabilized platform consists in: LEVELLING THE PALTFORM AND DETERMINING ITS ORIENTATION
The alignment phase of a gyro stabilized platform consists in: levelling the platform and determining its orientation.
The alignment sequence of an IRS consists of:; 1 - searching for the local vertical; 2 - searching for the true north; 3 - searching for the latitude; 4 - searching for the longitude; 5 - comparison between the computed longitude and the one entered by the pilot; 6 - comparison between the computed latitude and the one entered by the pilot; The combination that regroups all of the correct statements is: 1, 2, 3, 6
The alignment time of a strapdown inertial system takes longer time when the aircraft is: at a high latitude.
The alternate static source is used: when the static ports become blocked.
The alternate static source of a light non-pressurized aeroplane is located in the flight deck; when used: THE AIRSPEED INDICATOR TENDS TO OVER-READ
The alternate static source of a light non-pressurized aeroplane is located in the flight deck; when used, the altimeter: TENDS TO OVER-READ
The alternate static source of a light non-pressurized aeroplane is located in the flight deck; when used, the altimeter: tends to over-read.
The alternate static source of a light non-pressurized aeroplane is located in the flight deck; when used: the airspeed indicator tends to over-read.
The alternate static source of a light non-pressurized aircraft is located in the flight deck; as the alternate static source is opened, the vertical airspeed indicator may: INDICATE A MOMENTARY CLIMB
The alternate static source of a light non-pressurized aircraft is located in the flight deck; when used, the static pressure sensed is likely to be: lower than ambient pressure due to aerodynamic suction.
The alternate static source of a light non-pressurized aircraft is located in the flight deck; as the alternate static source is opened, the vertical airspeed indicator may: indicate a momentary climb.
The alternate static source of a non-pressurized aircraft is located in the cabin. As the alternate static source is opened, the vertical airspeed indicator may: SHOW A MOMENTARY CLIMB
The altimeter consists of one or several aneroid capsules located in a sealed casing. The pressures in the aneroid capsule (i) and casing (ii) are respectively: (1) VACUUM (OR A VERY LOW PRESSURE) (2) STATIC PRESSURE
The altimeter indicates true altitude: IN ISA CONDITIONS ONLY
The altimeter is subject to static pressure error. This error results from: INCORRECT PRESSURE SENSING CAUSED BY DISTURBED AIRFLOW AROUND THE STATIC PORTS
The altimeter is subject to static pressure error. This error results from: INCORRECT PRESSURE SENSING CAUSED BY DISTURBED AIRFLOW AROUND THE STATIC PORTS
The altimeter is subject to static pressure error. This error varies according to: TAS and angle of attack.
The altimeter is subject to the position error; this error varies substantially with the: MACH NUMBER
The altimeter is supplied with: STATIC PRESSURE
The altimeter of your aircraft indicates 10000 ft with a subscale-setting of 1013,25 mb. OAT is +5°C. The pressure altitude of the aircraft is: 10000 FT
The altimeter of your aircraft indicates 11000 ft with a subscale-setting of 1013,25 mb. QNH is 1023 hPa. OAT is +3°C. The pressure altitude of the aircraft is: 11000 FT
The altimeter of your aircraft indicates 12000 ft with a subscale-setting of 1013,25 mb. QNH is 999 hPa. The pressure altitude of the aircraft is: 12000 FT
The altimeter of your aircraft indicates 15000 ft with a subscale-setting of 1013,25 mb. OAT is -21°C. The pressure altitude of the aircraft is: 15000 FT
The altimeter of your aircraft indicates 16000 ft with a subscale-setting of 1013,25 mb. QNH is 993 hPa. OAT is -3°C. The pressure altitude of the aircraft is: 16000 FT
The altimeter of your aircraft indicates 17000 ft with a subscale-setting of 1013,25 mb. QNH is 1031 hPa. The pressure altitude of the aircraft is: 17000 FT
The altitude alerting system: ALERTS THE FLIGHT CREW UPON APPROACHING A PRE-SELECTED ALTITUDE
The angle of attack transmitter placed laterally on the forward part of the fuselage supplies an electrical signal which can indicate the angular position of:; 1 - a specific slaved pitot probe ;; 2 - a vane detector ;; 3 - a conical slotted probe .; The combination regrouping all the correct statements is: 2, 3
The apparent wander of a directional gyro is 15°/h: AT THE NORTH POLE
The artificial horizon uses a gyroscope with: (note: the degree(s) of freedom of a gyro does not take into account its rotor spin axis.) TWO DEGREES OF FREDOM, AND ITS ROTOR SPIN AXIS IS CONTINUOSLY MAINTAINED TO LOCAL VERTICAL BY AN AUTOMATIC ERECTING SYSTEM
The atmospheric pressure at FL 70 in a "standard + 10" atmosphere is: 781. 85 HPA
The attitude data computed by an IRS can be used by the: AUTO PILOT SYSTEM
The aural alert associated with the mode 1 (excessive descent rate) of the GPWS is: “SINKRATE”
The aural alert associated with the mode 2 (excessive terrain closure rate) of the GPWS is: “TERRAIN”
The aural alert associated with the mode 3 (altitude loss after take-off or go-around) of the GPWS is: ”DON’T SHINK”
The aural alert associated with the mode 5 (excessive deviation below Glideslope) of the GPWS is: ”GLIDESLOPE”
The aural alert(s) associated with the mode 1 (excessive descent rate) of the GPWS is (are):1 - "TERRAIN"2 - "DON'T SINK"3 - "SINKRATE"4 - "PULL UP" The combination that regroups all of the correct statements is: 3, 4
The aural alert(s) associated with the mode 3 (altitude loss after take-off or go-around) of the GPWS is (are):1 - "DON'T SINK"2 - " SINKRATE "3 - "TERRAIN"4 - "PULL UP" The combination that regroups all of the correct statements is: 1
The aural alert(s) associated with the mode 4 of the GPWS (unsafe terrain clearance while not in the landing configuration) is (are): “TOO LOW GEAR”, “TOO LOW FLAPS”, “ TO LOW TERRAIN”
The aural alert(s) associated with the mode 4 of the GPWS (unsafe terrain clearance while not in the landing configuration) is (are): 1 - "TOO LOW GEAR " 2 - "TOO LOW TERRAIN " 3 - "TOO LOW FLAPS" 4 - "PULL UP" The combination that regroups all of the correct statements is: 1, 2, 3.
The aural alert(s) associated with the mode 5 (excessive deviation below Glideslope) of the GPWS is (are): 1 - "TERRAIN” 2 - "TOO LOW GLIDESLOPE" 3 - "GLIDESLOPE" 4 - "PULL UP" The combination that regroups all of the correct statements is: 3
The automatic pitch trim:; 1 - ensures the aeroplane is properly trimmed when the autopilot is engaged; 2 - permits the elevator to always be in neutral position with respect to horizontal stabiliser; 3- ensures the aeroplane is properly trimmed when the autopilot is disengaged.; The combination regrouping all the correct statements is: 2, 3
The automatic power control system (autothrottle) of a transport airplane has the following mode(s) :; 1- capture and holding of speeds; 2- capture and holding of Mach number; 3- capture and holding of flight angle of attack; 4- capture and holding of N1 or EPR (Engine Power Ratio); 5- capture and holding of flight paths; The combination regrouping all the correct statements is : 1, 2, 4
The automatic synchronisation function of an autopilot control system:; 1 - operates only when the autopilot is engaged; 2 - prevents the aircraft's control system from jerking when disengaging the autopilot; 3 - prevents the aircraft's control system from jerking when engaging the autopilot; The combination that regroups all of the correct statements is: 3
The automatic synchronisation function of an autopilot control system: 1 - operates only when the autopilot is engaged 2 - prevents the aircraft''s control system from jerking when disengaging the autopilot 3 - enables the cancellation of the rudder control signals 4 - prevents the aircraft''s control system from jerking when engaging the autopilot The combination regrouping all the correct statements is: 4
The automatic trim is a component of the autopilot pitch channel. Its function is to: TRANSFER A STABILIZED AEROPLANE TO THE PILOT DURING AUTOPILOT DISENGAGEMENT
The autothrottle :; 1- enable to catch and to maintain the N1 RPM; 2- enable to catch and to maintain the N2 RPM; 3- enable to catch and to maintain an airplane indicated airspeed (IAS); 4- is always engaged automatically at the same time as the autopilot; The combination regrouping all the correct statements is: 1 AND 3
The auto-throttle system of a transport aeroplane has the following mode(s):; 1- capture and holding of IAS; 2- capture and holding of Mach number; 3- capture and holding of flight angle of attack; 4- capture and holding of N1 or EPR; 5- capture and holding of flight paths; The combination that regroups all of the correct statements is: 1, 2 4
The autothrottle system: CAN BE USED FOR TAKE-OFF
The auto-throttle:; 1- can capture and maintain the N1 RPM; 2- can capture and maintain the N2 RPM; 3- can capture and maintain an IAS; 4- is always engaged automatically at the same time as the autopilot; The combination that regroups all of the correct statements is: 1, 3
The auto-throttles enables to hold: 1 - a true airspeed; 2 - a Mach number; 3 - an indicated airspeed; 4 - a N1 thrust. The combination regrouping all the correct statements is: 2, 3, 4
The basic modes of an autopilot consist in: STABILIZING THE AIRCRAFT AROUND ITS CENTRE OF GRAVITY
The basic on-board datalink communication system is typically composed by the following sub systems: 1 - Communication Management Unit (CMU) 2 - Multi-purpose Control and Display Unit (MCDU) 3 - Communication unit (VHF, HF, Satcom) The combination which regroups all of the correct statements is: 1, 2, 3.
The basic principle of a capacitance fuel gauge system is that the: CAPACITY OF A CAPACITOR DEPENDS ON THE NATURE OF THE DIELECTRIC IN WHICH IT IS IMMERSED
The block diagram of an auto-pilot is shown in the annex.; For each control channel (pitch, roll and yaw) the piloting law is the relationship between the deflection of the control surface commanded by the computer (BETA c) and the: OFFSET EPSILON AT THE COMPUTER INPUT
The calibrated airspeed (CAS) or Mach holding mode is carried out by:; 1- the autopilot pitch channel in the climb mode at a constant calibrated airspeed (CAS) or Mach number; 2- the autothrottles in the climb mode at a constant calibrated airspeed (CAS) or Mach number; 3- the autopilot pitch channel in the altitude or glide path holding mode; 4- the autothrottles in the altitude or glide path holding mode; The combination regrouping all the correct statements is: 1 AND 4
The CAS is obtained from IAS by correcting for the following errors:1 - position2 - compressibility3 - instrument4 – density. The combination that regroups all of the correct statements is: 1,3
The center of gravity of the compass rose of a direct reading magnetic compass lies below the pivot point in order to reduce the influence of the: magnetic inclination.
The characteristics of the directional gyro used in a gyro stabilised compass system are: NB: the degree(s) of freedom of a gyro does not take into account its rotor spin axis.: TWO DEGREES OF FREDOM, WHOSE HORIZONTAL AXIS CORRESPONDING TO THE REFERENCE DIRECTION IS MAINTAINED IN THE HORIZONTAL PLANE BY AN AUTOMATIC ERECTING SYSTEM
The characteristics of the earth which are being used during the alignment of an INS platform are: EARTH ROTATION AND GRAVITY
The characteristics of the gyroscope used in a gyromagnetic compass system are:(NB: the rotor spin axis is not counted for the number of degrees of freedom of the gyro): TWO DEGREES OF FREEDOM, WHOSE HORIZONTAL AXIS CORRESPONDING TO THE REFERENCE DIRECTION IS MAINTAINED IN THE HORIZONTAL PLANE BY AN ERECTING SYSTEM
The characteristics of the SATCOM transmissions, used for datalink communications are: NO LINE OF SIGHT LIMITATION, NO VARIABLE QUALITY OF SIGNALS DISTURBED BY IONOSPHERIC CONDITIONS
The command bars of a flight director are generally represented on an: ADI (ATTITUDE DIRECTOR INDICATOR)
The command bars of a flight director: MAY BE DISPLAYED WHEN FLYING MANUALLY OR WITH THE AUTOPILOT ENGAGED
The command bars of a flight director: MAY BE DISPLAYED WHEN FLYING MANUALLY
The commands sent out by the yaw damper computer: ARE ADDED OR SUBSTRACTED FROM THE RUDDER DEFLECTION ORDERS SENT OUT BY THE PILOT OR THE AUTOPILOT
The commands sent out by the yaw damper computer: are added to or substracted from the rudder deflection orders sent out by the pilot or the autopilot. A flight control system is fail-passive if, in the event of a failure: there is no significant out-of-trim condition or deviation of flight path or attitude but the landing is not completed automatically.
The compass heading can be derived from the magnetic heading by reference to a: COMPASS DEVIATION CARD
The components of an autopilot system are the: 1- actuators 2- mode control panel 3- EFIS control panel 4- mode annunciator panel The combination that regroups all of the correct statements is: 1, 2, 4.
The components of an autopilot system are the:1- actuators2- mode control panel3- mode annunciator panel4- computer. The combination that regroups all of the correct statements is: 1, 2, 3, 4
The compressibility correction to CAS to give EAS: 1 - may be positive 2 - is always negative 3 - depends on Mach number only 4 - depends on pressure altitude only The combination regrouping all the correct statements is: 2, 3
The compressibility error must be taken into account only for aeroplane with: TAS GREATER THAN APPROCIMATELY 200 KT
The computer of the autopilot system uses, among others, input signals from the:1- attitude reference system2- mode annunciator panel3- ADC4- mode control panel. The combination that regroups all of the correct statements is: 1, 3 4
The computer of the autopilot system uses, among others, the following parameters:CAS, altitude, vertical speed, heading, attitude.
The control law of a transport airplane autopilot control channel may be defined as the relationship between the : COMPUTER INPUT DEVIATION DATA AND THE OUTPUT CONTROL DEFLECTION SIGNALS
The corresponding mode is: CONTROL WHEEL STEERING (CWS)
The CPDLC function consists in exchanging messages relative to: 1 - Route modifications 2 - Crossing constraints 3 - Transfer of ATC center 4 - Speed changes The combination which regroups all of the correct statements is: 1, 2, 3, 4.
The CPDLC is a FANS application which consists in: TRANSMITTING DATALINK FORMATTED MESSAGES BETWEEN THE PILOT AND THE ATC CONTROLLER
The CPDLC is a FANS application which consists in: transmitting datalink formatted messages between the pilot and ATC controller.
The CPDLC messages may concerne: 1 - Route modifications 2 - Speed changes 3 - Voice contact request 4 - Emergency messages The combination regrouping all the correct statements is: 1, 2, 3, 4.
The CS 25 gives the following definition: "Where the pilot has the ability to make inputs to the automatic pilot by movement of the normal control wheel".
The CS 25 gives the following definition: "Where the pilot has the ability to make inputs to the automatic pilot by movement of the normal control wheel". The corresponding mode is: control wheel steering (CWS).
The CVR (Cockpit Voice Recorder) includes:; 1. a microphone; 2. a recorder in compliance with the shock and fire resistance standards; 3. an independent battery; 4. a flight data recorder; The combination regrouping all the correct statements is: 1, 2
The data output from the ADC are:1- Barometric altitude2- Mach number3- CAS4- TAS5- SAT. The combination that regroups all of the correct statements is: 1, 2, 3, 4, 5
The data supplied by a radio altimeter: INDICATES THE DISTANCE BETWEEN THE GROUND AND THE AIRCRAFT
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: AIRCRAFT POSITION IN LATITUDE AND LONGITUDE OR AIRPORT ICAO IDENTIFIER
The datalink communications between the aircraft and the ground can be performed by the following system: ACARS
The Decision Height (DH) warning light comes on when an aircraft: DESCENDS BELOW A PRE-SET RADIO ALTITUDE
The density altitude is : THE ALTITUDE OF THE STANDARD ATMOSPHERE ON WHICH THE DENSITY IS EQUAL TO THE ACTUAL DENSITY OF THE ATMOSPHERE
The diagram representing a left turn with insufficient rudder is: 4
The diagram which shows a 40° left bank and 15° nose down attitude is n°: 1
The different types of ADS contracts can be:1 - periodic: at periodic time intervals2 - on demand: when asked for by the ATC3 - on event: whenever a specified event occurs. The combination which regroups all of the correct statements is: 1, 2, 3
The direct reading magnetic compass is no more reliable when approaching:; 1 - the magnetic poles.; 2 - the magnetic equator with a east or west heading.; 3 - the magnetic equator with a north or south heading.; The combination that regroups all of the correct statements is: 1
The disadvantages of a float type fuel gauge are:; 1- the design is complex; 2- the indications are influenced by the aircraft attitude variations; 3- the indications are influenced by the accelerations ; 4- the indications are influenced by temperature variations; The combination that regroups all of the correct statements is: 2, 3, 4
The disadvantages of a single-phase A.C. generator tachometer are:; 1- the presence of spurious signals due to a D.C. generator commutator; 2- the importance of line resistance on the information value; 3- the influence of temperature on the tachometer information; The combination regrouping all the correct statements is: 2
The disavantages of an "electric" fuel (float) gauge are :; 1- the design is complex; 2- the indications are influenced by the airplane attitude variations; 3- the indications are influenced by the accelerations ; 4- the indications are influenced by temperature variations; 5- that an alternative current supply is necessary; The combination regrouping all the correct statements is : 2, 3, 4
The drift of the gyroscopes of a stand alone inertial system: IS THE MAIN ERROR SOURCE
The drift of the gyroscopes of a stand alone inertial system: is the main error source.
The duration of a FMS navigation database loaded before expiring is: 28 DAYS
The EAS is obtained from the CAS by correcting for the following errors:1 - position2 - compressibility3 - instrument4 - densityThe combination that regroups all of the correct statements is: 2
The EAS is obtained from the CAS by correcting for: COMPRESSIBILITY ERROR
The EAS is obtained from the IAS by correcting for the following errors:1 - instrument2 - position3 - density 4 – compressibility. The combination that regroups all of the correct statements is: 1, 2, 4
The EGPWS may propose the following functions:; 1 - Abnormal Take-off Configuration (ATC); 2 - Terrain Clearance Floor (TCF); 3 - Predictive Wind Shear (PWS); 4 - Terrain Look Ahead Alerting; 5 - Terrain Alerting and Display (TAD); The combination regrouping all of the correct statements is: 2, 4 5
The EGPWS may propose the Terrain Look-Ahead Alerting function; this function uses: an electronic map of the world giving ground elevation.
The EGPWS: is an enhanced GPWS which has a its own world terrain database.
The electric float gauge: 1 - gives a mass information; 2 - gives information independent of aircraft's manoeuvres and attitude changes; 3 - gives information all the more accurate as the tank is full; 4 - is typically a DC powered system. The combination regrouping all the correct statements is: 4
The electronic tachometer sensor is composed of: A NOTCHED WHEEL ROTATING IN FRONT OF AN ELECTRO-MAGNET
The elements which take part in the local vertical alignment of an inertial strap-down unit are: THE ACCELEROMETERS
The energy required to operate a strapdown inertial system is supplied by: THE ELECTRICAL SYSTEM
The engine instrument utilising an aneroid pressure diaphragm is the: MANIFOLD PRESSURE GAUGE
The Enhanced GPWS (EGPWS) terrain display uses with the following colours: green, amber, red, magenta.
The EPR (Engine Pressure Ratio) is: THE RATIO OF THE TURBINE OUTLET TOTAL PRESSURE TO THE COMPRESSOR INLET TOTAL PRESSURE
The EPR is computed by: DIVIDING TURBINE DISCHARGE PRESSURE BY COMPRESSOR INLET PRESSURE
The error in altimeter readings caused by the variation of the static pressure near the source is known as: POSITION ERROR
The error induced by the location of the static pressure source is known as the: POSITION ERROR
The essential components of a flight director are: 1- a computer 2- an automatic pilot 3- an auto-throttle 4- command bars The combination regrouping all the correct statements is: 1, 4
The FADEC (Full Authority Digital Engine Control) provides: 1 - engine automatic shut-down if maximum N1 is exceeded 2 - engine automatic shut-down if maximum EGT is exceeded 3 - automatic thrust rating control 4 - fully automatic engine starting The combination that regroups all of the correct statements is: 3, 4.
The FADEC (Full Authority Digital Engine Control): 1 - provides fully automatic engine starting 2 - modifies aircraft airspeed in order to allow for the lowest fuel consumption 3 - counters any yaw movement in case of engine failure 4 - provides thrust reverser control The combination that regroups all of the correct statements is: 1, 4.
The FANS concept includes: A DATALINK COMMUNICATION BETWEEN THE AIRCRAFT AND THE ATC CENTERS TO REPLACE THE VOICE COMMUNICATION
The fields affecting a magnetic compass originate from: 1. magnetic masses 2. ferrous metal masses 3. non ferrous metal masses 4. electrical currents The combination regrouping all the correct statements is: 1,2 , 4
The flexible take-off mode: 1 - can be used only if the engines are recent 2 - reduces engine wear 3 - can be used in situations where take-off can be executed without the need for full engine power 4 - can only be used with an auto-throttle The combination that regroups all of the correct statements is: 2, 3.
The flexible take-off mode:; 1 - can be used only if the engines are recent; 2 - reduces engine wear; 3 - can be used in situations where take-off can be executed without the need for full engine power; 4 - can only be used with an auto-throttle; The combination that regroups all of the correct statements is: 2, 3
The flight director command bars provide the pilot with corrections to apply to: PITCH AND/ OR ROLL ATTITUDE
The flight director computer continuously: COMPARES THE CURRENT ALTITUDE WITH THE COMPUTED ALTITUDE
The flight director computer continuously: compares the current attitude with the computed attitude.
The flight director indicates the: OPTIMUM INSTANTANEOUS PATH TO REACH SELECTED RADIAL
The flight director is engaged in the heading select mode (HDG SEL) , heading 180° selected. When heading is 160°, the vertical bar of the FD: IS CENTERED IF THE BANK ANGLE OF THE AIRCRAFT IS EQUAL TO THE BANK ANGLE COMPUTED BY THE FLIGHT DIRECTOR CALCULATOR
The flight director provides information for the pilot: TO JOIN TO A DESIRED PATH WITH THE OPTIMUM ATTITUDE
The flight envelope protection function(s) consist(s) in: 1 - alerting the flight crew in case of dangerous proximity with the ground 2 - avoiding midair collision 3 - preventing the aircraft from exceeding some aerodynamic limits The combination that regroups all of the correct statements is: 3.
The flight envelope protection function(s) consist(s) in: 1 - automatically performing an evasion manoeuvre if necessary 2 - preventing the aircraft from exceeding the limits for specific flight parameters 3 - alerting the flight crew in case of dangerous proximity with a threatening traffic 4 - preventing any incursion beyond an ATC clearance The combination that regroups all of the correct statements is: 2.
The flight envelope protection function(s) consist(s) in:; 1 - alerting the flight crew in case of dangerous proximity with the ground; 2 - avoiding midair collision; 3 - preventing the aircraft from exceeding some aerodynamic limits; The combination that regroups all of the correct statements is: 3
The flight envelope protection function(s) consist(s) in:; 1 - automatically performing an evasion manoeuvre if necessary; 2 - preventing the aircraft from exceeding the limits for specific flight parameters; 3 - alerting the flight crew in case of dangerous proximity with a threatening traffic; 4 - preventing any incursion beyond an ATC clearance; The combination that regroups all of the correct statements is: 2
The flight envelope protection system prevents the aircraft from exceeding the limits of the following parameters (among others):; 1 - cabin altitude; 2 - bank angle; 3 - angle of attack; 4 - speed; 5 - pitch attitude; The combination that regroups all of the correct statements is: 2, 3, 4, 5
The flight envelope protection system prevents the aircraft from exceeding the limits of the following parameters (among others): 1 - N1 2 - angle of attack 3 - speed 4 - pitch attitude 5 - flight level The combination that regroups all of the correct statements is: 2, 3, 4.
The flight warning system (FWS) generates a caution message if: CREW AWARENESS IS REQUIRED AND SUBSEQUENT CREW ACTION MAY BE REQUIRED
The flight warning system (FWS) generates a warning message if: INMEDIATE RECOGNITION AND CORRECTIVE OR COMPENSATORY ACTION BY THE CREW IS REQUIRED
The flight warning system (FWS) generates an advisory message if: CREW AWARENESS IS REQUIRED AND SUBSEQUENT CREW ACTION MAY BE REQUIRED
The flight warning system (FWS): 1 - increases the situation awareness of the crew. 2 - transmits automatically to ATC distress messages. 3 - gives suitable indications to the crew of the action necessary to avoid impending danger. 4 - prioritises warnings. 5 - can not generate alerts in case of aerodynamic limits exceeding. The combination that regroups all of the correct statements is: 1, 3, 4
The flight warning system (FWS):; 1 - draws the attention of the crew to the existence of an abnormal condition; 2 - gives indications to the crew to identify an abnormal condition; 3 - transmits automatically to ATC urgency messages; 4 - can not generate alerts in case of engine malfunctions; 5 - prioritises warnings; The combination that regroups all of the correct statements is: 1, 2, 5
The float type fuel gauges provide information on: VOLUME WHOSE INDICATION VARIES WITH THE TEMPERATURE OF THE FUEL
The flux valve of a gyromagnetic compass:1 - feeds the error detector2 - feeds the direct indicating compass3 - gives the earth's magnetic field directionThe combination regrouping all of the correct statements is: 1, 3
The FMC determines and update present aircraft position from the following systems:1- SATCOM2- GPS3- DME4- IRS. The combination that regroups all of the correct statements is: 2, 3, 4
The FMC determines and update present aircraft position from the following systems:1 - GPS2 – IRS 3 - Navigation radios 4 – ACARS The combination that regroups all of the correct statements is: 1, 2, 3
The FMC determines and update present aircraft position from the following systems: 1- SATCOM 2- GPS 3- DME 4- IRS The combination that regroups all of the correct statements is: 2, 3, 4.
The FMC determines and update present aircraft position from the following systems: 1 - GPS 2 - IRS 3 - Navigation radios 4 - ACARS The combination that regroups all of the correct statements is: 1, 2, 3.
The FMS cross track (XTK) is: THE ABEAM DISTANCE ERROR, TO THE LEFT OR RIGHT FROM THE DESIRED FLIGHT PLAN LEF TO THE AIRCRAFT POSITION
The FMS cross track (XTK) is: THE ABEAM DISTANCE ERROR, TO THE LEFT OR RIGHT FROM THE DESIRED FLIGHT PLAN LEF TO THE AIRCRAFT POSITION
The FMS enables to fly an optimum flight profile. For this, the FMC (Flight Management Computer) uses: ; 1 - flight-crew entered flight plan data; 2 - data from ADC; 3 - aircraft position; 4 - a memorised relief world data base; 5 - data from the FMC navigation data base; The combination that regroups all of the correct statements is: 1, 2, 3, 5
The FMS FLIGHT PLAN or LEG page displays the following parameters relative to the flight plan legs or waypoints:1 - track2 - magnetic variation3 - waypoint elevation4 – Speedy The combination that regroups all of the correct statements is: 1, 4
The FMS FLIGHT PLAN or LEG page displays the following parameters relative to the flight plan legs or waypoints:1 - aircraft position (Long / Lat)2 - speed3 - distance4 – track The combination that regroups all of the correct statements is: 2, 3, 4
The FMS FLIGHT PLAN or LEG page displays the following parameters relative to the flight plan legs or waypoints: 1 - track 2 - magnetic variation 3 - waypoint elevation 4 - speed The combination that regroups all of the correct statements is: 1, 4.
The FMS is approved for Localizer approaches: IF THE LOCALIZER SIGNALS ARE USED BY THE FMS
The FMS is approved to provide guidance for the following approaches: 1- RNAV 2- ILS 3- MLS 4- VOR, NDB The combination which regroups all of the correct statements is: 1, 4
The FMS is approved to provide guidance for the following approaches: 1- RNAV 2- PAR 3- VOR/DME, VOR 4- MLS The combination which regroups all of the correct statements is: 1, 3
The FMS is approved to provide guidance for the following approaches: NON PRECISION APPROACHES
The FMS lateral offset function consists in: FLYING ALONG THE FLIGHT PATH LEGS WITH A CONSTANT RIGHT OR LEFT OFFSET MANUALLY ENTERED ON THE FMS CDU
The FMS lateral offset function consists in: flying along the flight plan legs with a constant right or left offset manually entered on the FMS CDU.
The FMS lateral offset function consists in: FLYING AROUND THE FLIGHT PLAN LEGS WITH A CONSTANT RIGHT OR LEFT OFFSET MANUALLY ENTERED ON THE FMS CDU
The FMS navigation database includes the following data: 1 - airports 2 - obstacles 3 - navaids 4 - airways 5 - relief The combination that regroups all of the correct statements is: 1, 3, 4.
The FMS navigation database includes the following data: 1 - airports 2 - take off speeds 3 - navaids 4 - relief 5 - runways The combination that regroups all of the correct statements is: 1, 3, 5.
The FMS navigation database includes the following data: 1 - obstacles 2 - waypoints 3 - SID, STAR 4 - relief 5 - magnetic variation The combination that regroups all of the correct statements is: 2, 3, 5.
The FMS navigation database includes the following data: 1- airports 2- take off speeds 3- navaids 4- terrain cells 5- runways The combination which regroups all of the correct statements is: 1, 3, 5
The FMS navigation database includes the following data: 1- airports 2- obstacles 3- navaids 4- airways 5- terrain cells The combination which regroups all of the correct statements is: 1, 3, 4
The FMS navigation database includes the following data: 1- obstacles 2- waypoints 3- SID, STAR 4- terrain cells 5- magnetic variation The combination which regroups all of the correct statements is: 2, 3, 5
The FMS navigation database includes the following data: 1- obstacles 2- navaids 3- SID, STAR and approaches procedures 4- waypoints 5- airways The combination which regroups all of the correct statements is: 2, 3, 4, 5
The FMS navigation database includes the following data:1 - airports2 - obstacles3 - navaids4 - airways5 – relief The combination that regroups all of the correct statements is: 1, 3, 4
The FMS navigation database includes the following data:1 - obstacles2 - waypoints3 - SID, STAR4 - relief 5 - magnetic variation. The combination that regroups all of the correct statements is: 2, 3, 5
The FMS navigation database includes the following data:1- obstacles2- navaids3- SID, STAR and approaches procedures4- waypoints5- airways. The combination that regroups all of the correct statements is: 2, 3, 4, 5
The FMS navigation database processing should include the following check(s): AT EACH PHASE OF THE PROCESS, FROM THE RECEPTION OF EACH SUPPLIER’S DATA TO THE DISTRIBUTION AND LOADING OF THE FORMATTED DATABASE
The FMS Overfly function consists in: MANUALLY SELECTING A FLIGHT PLAN WAYPOINT TO FLY OVER WHEN SEQUENCING IT INSTEAD OF FLYING BY AT THE TRANSITION
The FMS provides the following functions: 1 - aid for fuel management 2 - lateral flight plan management 3 - check-list completion 4 - aircraft position computation The combination that regroups all of the correct statements is: 1, 2, 4.
The FMS provides the following functions: 1 - traffic advisories emission 2 - resolution advisories emission 3 - aid for fuel management 4 - lateral flight plan management The combination that regroups all of the correct statements is: 3, 4.
The FMS provides the following functions: 1- aircraft position computation 2- traffic alerts 3- lateral flight plan management 4- fuel management The combination which regroups all of the correct statements is: 1, 3, 4
The FMS provides the following functions: 1- fuel management 2- lateral flight plan management 3- de icing management 4- aircraft position computation The combination which regroups all of the correct statements is: 1, 2, 4
The FMS provides the following functions: 1- lateral and vertical flight plan management 2- de icing management 3- aircraft position computation 4- terrain awareness and warning The combination that regroups all of the correct statements is: 1, 3.
The FMS provides the following functions: 1- radio tuning 2- fuel management 3- lateral flight plan management 4-traffic alerts The combination which regroups all of the correct statements is: 1, 2 3
The FMS provides the following functions: 1- vertical flight plan management 2- fuel management 3- lateral flight plan management 4- terrain awareness and warning The combination which regroups all of the correct statements is: 1, 2, 3
The FMS provides the following functions:1 - aid for fuel management2 - lateral flight plan management3 - check-list completion4 - aircraft position computation. The combination that regroups all of the correct statements is: 1,2, 4
The FMS provides the following functions:1 - traffic advisories emission2 - resolution advisories emission3 - aid for fuel management4 - lateral flight plan Management. The combination that regroups all of the correct statements is: 3, 4
The FMS provides the following functions:1- lateral and vertical flight plan management 2- de icing management3- aircraft position computation4- terrain awareness and warning. The combination that regroups all of the correct statements is: 1,3
The FMS Required Time of Arrival (RTA) function can provide: A SPEED TARGET TO SATISFY A TIME CONTRAINT ENTERED AT A FLIGHT PLAN WAYPOINT
The FMS Required Time of Arrival (RTA) function can provide: A SPEED TARGET TO SATISFY A TIME CONSTRAINT ENTERED AT A FLIGHT PLAN WAYPOINT
The FMS vertical navigation management is generally performed based on: THE BARO ALTITUDE INPUT FROM THE AIR DATA SYSTEM
The FMS vertical navigation management is generally performed based on: THE BARO ALTITUDE INPUT FROM THE ADC
The following ATC clearances can be received via the datalink application: DEPARTURE, OCEANIC
The Fuel management performed by most FMS along the flight plan is considered as: A FUNCTION WHICH HELPS THE CREW TO ESTIMATE THE REMAINING FUEL QUANTITY ALONG THE FLIGHT PLAN BUT SHOULD NOT BE CONSIDERED AS AN ACCURATE AND RELIABLE MEAN
The functions of the altitude alerting system is to alert the flight crew: 1 - upon approaching a pre-selected altitude 2 - upon approaching a pre-selected altitude, during climb only 3 - of a loss of altitude during take-off or missed approach 4 - of a wrong landing configuration 5 - when deviating from the selected altitude The combination regrouping all the correct statements is: 1, 5
The gauge indicating the quantity of fuel measured by a capacity gauging system can be graduated directly in weight units because the dielectric constant of fuel is: TWICE THAT OF AIR AND VARIES DIRECTLY WITH DENSITY
The GPWS automatically provides distinctive warning to the flight crew in case of:; 1 - impeding stall; 2 - excessive descent rate; 3 - altitude loss after take-off or go-around; 4 - unsafe terrain clearance with flaps not in landing configuration; 5 - dangerous ground proximity; 6 - downward glide-slope deviation; The combination that regroups all of the correct statements is: 2, 3, 4, 5, 6
The GPWS can warn the crew in case of: 1 - excessive climb rate2 - unsafe terrain clearance when not in landing configuration3 - descent path angle greater than 5 degrees4 – windshear The combination that regroups all of the correct statements is: 2, 4
The GPWS can warn the crew in case of:1 - excessive deviation below selected altitude2 - windshear3 - excessive terrain closing rate. The combination that regroups all of the correct statements is: 2, 3
The GPWS computer receives the following signals:; 1 - vertical speed; 2 - radio altimeter height; 3 - pressure altitude; 4 - glidepath deviation ; 5 - gear and flaps position; 6 - flight path angle; The combination that regroups all of the correct statements is: 1, 2, 4, 5
The GPWS CPU (Central Processing Unit) is able to detect: 1- excessive descent rate. 2- excessive rate of terrain closure. 3- excessive angle of attack. 4- too high descent attitude. 5- loss of altitude after take-off. 6- abnormal gear/flaps configuration. 7- excessive glidepath deviation. The combination that regroups all of the correct statements is: 1, 2, 5, 6, 7
The GPWS generates a warning in the following cases:; 1 - excessive descent rate; 2 - excessive terrain closure rate; 3 - altitude loss after take-off or go-around; 4 - unsafe terrain clearance with abnormal gear/flaps configuration; 5- excessive deviation under the glidepath; 6- abnormal airbrakes configuration; The combination regrouping all the correct statements is: 1, 2, 3, 4, 5
The GPWS is able to detect:; 1 - excessive descent rate ; 2 - excessive terrain closing rate; 3 - excessive angle of attack; 4 - excessive descent pitch attitude; The combination that regroups all of the correct statements is: 1, 2
The GPWS receives data from the following systems: 1- landing gear and flaps systems 2- engine control computer (FADEC or ECU) 3- radio altimeter 4- TCAS The combination that regroups all of the correct statements is: 1, 3.
The GPWS warns the crew in case of: 1 - excessive descent rate 2 - excessive terrain closure rate 3 - potential midair collision threat 4 - serious midair collision threat 5 - unsafe terrain clearance with landing gear not down The combination that regroups all of the correct statements is: 1, 2, 5.
The GPWS warns the crew in case of:; 1 - deviation above or below the selected altitude; 2 - deviation below the selected altitude; 3 - unsafe terrain clearance with flaps not in landing configuration; 4 - unsafe terrain clearance with landing gear not down; The combination that regroups all of the correct statements is: 3, 4
The Ground Proximity Warning System (GPWS) generates the following sound signal or signals when the aircraft is sinking after a take-off or a go-around: DONT SHINK REPETITIVE ONLY
The Ground Proximity Warning System (GPWS) is a system working according to a height span ranging from: 50 FT TO 2500 FT
The ground routing of the ATC datalink communications is performed: BY SERVICE PROVIDERS (SITA, ARINC…) THAT CAN BE INTERCONNECTED TO PROVIDE CONTINUITY OF THE TRANSMISSIONS
The gyro axis of an electric artificial horizon is tied to the: EARTH’S VERTICAL BY TWO MERCURY LEVEL SWITCHES AND TWO TORQUE MOTORS
The gyromagnetic compass torque motor: CAUSES THE DIRECTIONAL GYRO UNIT TO PROCESS
The gyroscope of a turn indicator has:; (NB: the degree(s) of freedom of a gyro does not take into account its rotor spin axis.) 1 DEGREE OF FREEDOM
The gyroscope used in an attitude indicator has a spin axis which is: VERTICAL
The heading read on the dial of a directional gyro is subject to errors, one of which is due to the movement of the aircraft. This error... IS DEPENDENT ON THE GROUND SPEED OF THE AIRCRAFT, ITS TRUE TRACK AND THE LATITUDE OF THE FLIGHT
The horizontal command bar of a flight director: 1 - repeats the position information given by the ILS in the horizontal plane 2 - repeats the position information given by the ILS in the vertical plane 3 - gives information about the direction and the amplitude of the corrections to be applied on the pitch of the aircraft. The combination regrouping all the correct statements is: 3
The horizontal command bar of a flight director: GIVES INFORMATION ABOUT THE DIRECTION AND THE AMPLITUDE OF THE CORRECTIONS TO BE APPLIED ON THE PITCH OF THE AIRCRAFT
The indicated Mach number is independent from: TEMPERATURE
The indication of a fuel float gauge varies with:; 1 - pitch attitude; 2 - accelerations; 3 - fuel temperature; The combination that regroups all of the correct statements is: 1, 2, 3
The indication of the directional gyro is valid only for a limited period of time. The causes of this inaccuracy are:; 1 - rotation of the earth; 2 - longitudinal accelerations; 3 - aircraft's moving over the surface of the earth; 4 - vertical components of of the earth's magnetic field; The combination regrouping all the correct statements is: 1, 3
The indications on a directional gyroscope are subject to errors. The most significant are:; 1- apparent wander due to earth rotation.; 2- apparent wander due to change of aircraft position.; 3- gimballing errors.; 4- north change.; 5- mechanical defects.; The combination regrouping the correct statement is: 1, 2, 3, 5
The inertia of a gyroscope is greater when: ITS ROTATION SPEED IS HIGHER AND THE MASS OF THE SPINNING WHEEL IS LOCATED FURTHER FROM THE AXIS OF ROTATION
The initiation of an automatic go-around can be: IN A RANGE OF APPROACH AIRSPEEDS
The input data of an ADC are: 1 - OAT 2 - TAT 3 - static pressure 4 - total pressure The combination regrouping all the correct statements is: 2, 3, 4
The input data to the GPWS originate from the:1 - transponder2 - angle of attack sensor3 - auto throttle system4 – ADC. The combination that regroups all of the correct statements is: 4
The input signal of the amplifier of the gyromagnetic compass resetting device originates from the: ERROR DETECTOR
The input(s) of a VMO/MMO warning system is (are): STATIC PRESSURE AND TOTAL PRESSURE
The inputs to the GPWS (Ground Proximity Warning System), are: 1- Air Data Computer - (Mach number and Vertical Speed) 2- Radio Altimeter 3- NAV/ILS (Glide Slope) 4- NAV/VOR 5- Flap (position) 6- Weight of the aircraft 7- Landing Gear (position)The combination of correct statement is: 1, 2, 3, 5, 7
The inputs to the GPWS (Ground Proximity Warning System), are:; 1- Air Data Computer - (Mach number and Vertical Speed) ; 2- Radio Altimeter; 3- NAV/ILS (Glide Slope); 4- NAV/VOR; 5- Flap (position); 6- Angle of Attack; 7- Landing Gear (position); The combination of correct statement is: 1,2, 3, 5, 7
The lateral flight path modes of an autopilot system are: 1 - Heading hold 2 - Speed hold 3 - FMS lateral navigation 4 - TAS hold 5 - Localizer intercept and track The combination that regroups all of the correct statements is: 1, 3, 5.
The lateral flight path modes of an autopilot system are: 1 - Speed hold 2 - Localiser intercept and track 3 - Track hold 4 - FMS lateral navigation 5 - Pitch attitude hold The combination that regroups all of the correct statements is: 2, 3, 4.
The lateral flight path modes of an autopilot system are:1 - Heading hold2 - Speed hold3 - FMS lateral navigation4 - TAS hold5 - Localizer intercept and track The combination that regroups all of the correct statements is: 1, 3, 5
The latitude at which the apparent wander of a directional gyro is equal to 0 is: THE EQUATOR
The limits of the green scale of an airspeed indicator are: VS1 FOR THE LOWER LIMIT AND VNO FOR THE UPPER LIMIT
The limits of the green scale of an airspeed indicator are:VS1 and VNO.
The limits of the white scale of an airspeed indicator are: VSO FOR THE LOWER LIMIT AND VFE FOR THE UPPER LIMIT
The limits of the yellow scale of an airspeed indicator are: VNO FOR THE LOWER LIMIT AND VNE FOR THE UPPER LIMIT
The Low Altitude Radio Altimeter uses the following wavelengths: CENTIMETRIC
The low-altitude radio altimeters used in precision approaches:; 1 operate in the 1540-1660 MHz range.; 2 are of the pulsed type.; 3 are of the frequency modulation type.; 4 have an operating range of 0 to 5000 ft.; 5 have a precision of +/- 2 feet between 0 and 500 ft and +/- 1.5% whichever is the greatest.; ; The combination of the correct statements is : 3, 5
The Mach Number is proportional to the ratio: NB: "a" indicates the local speed of sound: TAS/A
The mach number is the: TRUE AIRSPEED (TAS) DIVIDED BY THE LOCAL SPEED OF SOUND
The Mach number is: THE RATIO OF THE AIRCRAFT TRUE AIRSPEED TO THE SONIC VELOCITY AT THE ALTITUDE CONSIDERED
The Mach trim system allows to: INCREASE THE LONGITUDINAL STATIC STABILITY OF THE AIRCRAFT BU CHANGING THE HORIZONTAL STABILICER ACORDING TO THE MACH NUMBER
The machmeter is subject to position error. This error concerns: PITOT TUBES AND STATIC PORTS
The machmeter is subject to position error. This error concerns: pitot tubes and static ports.
The Machmeter is subject to position error. This error results from: INCORRECT PRESSURE SENSING CAUSED BY DISTURBED AIRFLOW AROND THE PILOT TUBE AND/OR STATIC PORTS
The Machmeter is subject to position error. This error results from: incorrect pressure sensing caused by disturbed airflow around the pitot tube and/or static ports.
The machmeter is subject to position error. This error varies according to: 1 - angle of attack 2 - OAT 3 - TAS The combination that regroups all of the correct statements is: 1, 3.
The machmeter is subject to position error. This error varies according to: TAS and angle of attack.
The magnetic heading can be derived from the true heading by means of a: MAP SHOWING THE ISOGONAL LINES
The main function(s) of a TCAS is to:; 1 - alert the crew to ground proximity; 2 - alert the crew to possible conflicting traffic; 3 - provide terrain alerting and display; 4 - automatically resolve conflict when autopilot engaged; The combination that regroups all of the correct statements is: 2
The main input data to the Stall Warning Annunciator System are: 1- Mach Meter indication 2- Angle of Attack 3- Indicate Airspeed (IAS) 4- Aircraft configuration (Flaps/Slats) The combination regrouping all the correct statements is: 2, 4
The main inputs to the flight envelope protection system are: 1 - GPWS signals 2 - ACAS signals 3 - angle of attack 4 - bank angle The combination that regroups all of the correct statements is: 3, 4.
The maximum directional gyro error due to the earth rotation is: 15 °/H
The maximum operating speed VMO is expressed in: cas or eas
The maximum TAS is obtained at: The flight level at which simultaneously cas = vmo and m= mmo
The measurement of the turbine temperature or of the EGT (Exhaust Gas Temperature) is carried out at the: HIGH PRESSURE TURBINE OUTLET
The mode selector of an inertial unit comprises the OFF - STBY - ALIGN - NAV - ATT positions: 1 - on "STBY", the unit aligns on the local geographic trihedron; 2 - the "ATT" position is used in automatic landing (mode LAND); 3 - on "NAV" the coordinates of the start position can be entered; 4 - the platform is levelled before azimuth alignment; 5 - in cruise, the unit can only be used in "NAV" mode. The combination regrouping all the correct statements is: 4
The mode selector of an inertial unit comprises the OFF - STBY - ALIGN - NAV - ATT positions:; 1 - on "STBY", the unit aligns on the local geographic trihedron;; 2 - the "ATT" position is used in automatic landing (mode LAND);; 3 - on "NAV" the coordinates of the departure position can be entered; 4. the horizontal alignment precedes the unit orientation calculation; 5. in cruise, the unit can only be used in "NAV" mode; The combination regrouping all the correct statements is: 4
The most common sensors interfacing a FMS to compute the aircraft position along the flight plan are: 1- MLS 2- GPS 3- VOR 4- IRS The combination which regroups all of the correct statements is: 2, 3, 4
The most common sensors interfacing a FMS to compute the aircraft position along the flight plan are: 1- IRS 2- DME 3- NDB 4- GPS The combination which regroups all of the correct statements is: 1, 2, 4
The most common sensors interfacing a FMS to compute the aircraft position along the flight plan are: 1- GPS 2- NDB 3- DME 4- LOCALIZER The combination which regroups all of the correct statements is: 1, 3
The most common sensors interfacing a FMS to compute the aircraft position along the flight plan are: 1- DME 2- GPS 3- LOCALIZER 4- NDB The combination which regroups all of the correct statements is: 1, 2
The most common sensors interfacing a FMS to compute the aircraft position along the flight plan are:1- GPS2- NDB3- DME4- LOCALIZER. The combination that regroups all of the correct statements is: 1, 3
The most common system used to monitor turbine gas exhaust temperature is the: HOT AND COLD JUNCTION, ALUMEL/CHROMEL SYSTEM
The most favourable conditions to apply the flexible take-off procedure are:; 1 - high take-off mass; 2 - low take-off mass; 3 - high outside temperature; 4 - low outside temperature; 5 - high atmospheric pressure; 6 - low atmospheric pressure; The combination grouping all the correct answers is: 2, 4, 5
The most significant advantages of an air data computer (ADC) are:; 1. Position error correction; 2. Hysteresis error correction; 3. Remote data transmission capability; 4. Gimballing errors correction; The combination regrouping all the correct statements is: 1,3
The Navigation Display (ND) modes can be: 1 - ARC or MAP, covering 45 degrees on either side of the instantaneous track 2 - ROSE or MAP CENTERED: rose with current heading up 3 - PLAN: map orientated to true north The combination that regroups all of the correct statements is: 1, 2, 3.
The Navigation Display (ND) of an EFIS equipped aircraft can display the following data: flight plan, weather radar, terrain map, intruding traffics.
The navigation precision of a stand alone inertial system decreases along the flight, due to: the drift of the gyroscopes.
The Notification phase (LOG ON) is a FANS application which consists in: ESTABLISHING AIR/GROUND CONNECTION TO VERIFY IF THE DATALINK COMMUNICATION CAN BE PERFORMED
The notification phase (LOG ON) is a FANS application which consists in transmitting aircraft information and: ASSOCIATED DATALINK CAPABILITY, PRIOR TO OPERATING ANY DATALINK COMMUNICTIONS WITH ATC
The notification phase (LOG ON) is a FANS application which consists in transmitting aircraft information and: associated datalink capability, prior to operating any datalink communications with ATC.
The Notification phase (LOG ON) is a FANS application which consists in: establishing air/ground connection to verify if the datalink communication can be performed.
The on-board communication devices to transmit and receive datalink communication can be: 1- VHF COM 2- HF COM 3- SATCOM The combination which regroups all of the correct statements is: 1, 2, 3.
The open-ended tube parallel to the longitudinal axis of the aircraft senses the: TOTAL PRESSURE
The operating frequency range of a low altitude radio altimeter is: 4200 MHX TO 4400 MHZ
The operating principle of an "electronic" tachometer is to measure the: FREQUENCY OF THE ELECTRIC IMPULSE CREATED BY A NOTCHED WHEEL ROTATING IN A MAGNETIC FIELD
The operating principle of an inductive probe tachometer is to measure the: FREQUENCY OF THE ELECTRIC IMPULSE CREATED BY A NOTCHED WHEEL ROTATING IN A MAGNETIC FIELD
The operating principle of an inertial system consists in: MEASURING THE ACCELERATION OF THE AIRCRAFT AND PERFORMING INTEGRATIONS TO ELABORATE THE GROUND SPEED AND THE POSITION
The operating principle of the "induction" type of tachometer is to measure the: ROTATION SPEED OF AN ASYNCHOROUS MOTOR ENERGIZED BY AN ALTERNATOR
The operating principle of the vertical speed indicator (VSI) is based on the measurement of the rate of change of: STATIC PRESSURE
The operation of the GPWS (Ground Proximity Warning System) is governed by laws taking the aircraft height into account as well as :; 1- the descent rate; 2- the climb rate; 3- the aircraft configuration; 4- the selected engine rpm; The combination of correct statements is : 1, 3
The operation of the GPWS (Ground Proximity Warning System) is governed by laws taking the aircraft height into account as well as: 1- the descent rate 2- the climb rate 3- the aircraft configuration 4- the selected engine rpm The combination regrouping all the correct statements is : 1, 3
The operation of the radio altimeter of a modern aircraft is based on: FREQUENCY MODULATION OF THE CARRIER WAVE
The output data from the ADC are used by: 1- Transponder 2- EFIS 3- Automatic Flight Control System (AFCS) The combination that regroups all of the correct statements is: 1, 2, 3.
The output data of an IRS include: 1 - angle of attack 2 - altitude 3 - ground speed The combination regrouping all the correct statements is: 3.
The output data of an IRS include: 1 - attitude 2 - altitude 3 - present position (lat, long) 4 - static air temperature The combination regrouping all the correct statements is: 1, 3.
The output data of an IRS include: 1 - present position (lat, long)2 - altitude3 - ground speed4 - true heading. The combination regouping all the correct statements is: 1, 3, 4
The output data of an IRS include: 1 - present position (lat, long) 2 - TAS 3 - attitude 4 - ground speed The combination regrouping all the correct statements is: 1, 3, 4.
The output data of an IRS include: 1 - present position (lat, long) 2 - total pressure 3 - static air temperature 4 - true heading The combination regrouping all the correct statements is: 1, 4.
The output data of an IRS include: 1 - present position (lat, long) 2 - altitude 3 - ground speed 4 - true heading The combination regouping all the correct statements is: 1, 3, 4.
The output data of an IRS include: 1 - satellites status 2 - altitude 3 - drift angle 4 - present position (lat, long) The combination regrouping all the correct statements is: 3, 4.
The output data of an IRS include:1 - angle of attack2 - altitude3 - ground Speedy. The combination regrouping all the correct statements is: 3
The output data of an IRS include:1 - attitude2 - altitude3 - present position (lat, long)4 - static air temperature The combination regrouping all the correct statements is: 1, 3
The output data of an IRS include:1 - present position (lat, long)2 - TAS3 - attitude4 - ground Speedy. The combination regrouping all the correct statements is: 1, 3, 4
The output data of the flight director computer are: TWO CHANNELS:PITCH AND ROLL
The output from an engine vibration transducer is: ALWAYS FILTERED TO REMOVE UNWANTED FREQUENCIES
The parameter that determines the relationship between EAS and TAS is: DENSITY ALTITUDE
The parameters taken into account by the flight director computer in the altitude hold mode (ALT HOLD) are: 1 - altitude deviation 2 - engine rpm 3 - ground speed 4 - pitch attitude The combination regrouping all the correct statements is: 1, 4
The position data (lat, long) computed by an IRS can be used by the: FMS
The position error of a stand alone inertial system is: small a few minutes after initialisation and increases along the flight.
The position error of a stand alone inertial system, is approximately: 0.5 to 2 NM per hour.
The position error of a stand alone inertial system: INCREASES ALONG THE TIME
The position error of a stand alone inertial system: increases along the time.
The position error of the static vent on which the altimeter is connected varies substantially with the: MACH NUMBER OF THE AIRCRAFT
The position of a Flight Director command bars:; INDICATED THE MANOUVRES TO EXECUTE, TO ACHIEVE OR MAINTAIN A FLIGHT SITUATION
The position of the command bars of a flight director enables the pilot to know: THE DIRECTION OF THE AMPLITUDE OF THE CORRECTIONS TO APPLY ON THE CONTROLS
The position of the command bars of a flight director enables the pilot to know:; 1 - the direction and the amplitude of the corrections to apply on the controls.; 2 - only the direction of the corrections to apply on the controls.; 3 - the attitude of the aircraft.; The combination that regroups all of the correct statements is: 1
The position of the command bars of a flight director enables the pilot to know: the direction and the amplitude of the corrections to apply on the controls.
The pressure altitude is the altitude corresponding : IN STANDARD ATMOSPHERE, TO THE PRESSURE PS PREVAILING AT THIS POINT
The pressure capsule of an airspeed indicator is sensitive to the difference: (TOTAL PRESSURE- STATIC PRESSURE), CALLED DYNAMIC PRESSURE
The Primary Flight Display (PFD) displays information dedicated to: PILOTING
The Primary Flight Display (PFD) of an EFIS equipped aircraft can display information relative to the following conditions: ALTITUDE CAPTURE, TCAS RESOLUTION ADVISORY, AUTOPILOT AND FLIGHT DIRECTOR MODE CHANGES
The Primary Flight Display (PFD) of an EFIS equipped aircraft displays the following parameters: IAS, attitude, altitude, heading.
The Primary Flight Display (PFD) of an EFIS equipped aircraft displays the following parameters: 1- radio height 2- IAS 3- Localizer and Glide slope deviation pointers 4- flight director modes 5- autopilot modes The combination that regroups all of the correct statements is: 1, 2, 3, 4, 5.
The principle of a laser gyro is based on: FREQUENCY DIFFERENCE BETWEEN TWO LASER BEAMS ROTATING IN OPPOSITE DIRECTION
The principle of capacity gauges is based on the capacitance variation of: A CAPACITOR WITH THE TYPE OF DIELECTRIC
The principle of the Mach indicator is based on the computation of the ratio : (PT-PS)/PS
The principle of the Schuler pendulum is used in the design of a: STABILISED PLATFORM INERTIAL SYSTEM
The principle of the TCAS makes use of: TRANSPONDERS FITTED IN THE AIRCRAFT
The probe used to measure the air intake pressure of a gas turbine engined powerplant is: AN ANEROID CAPSULE
The properties of a gyroscope are: 1 - rigidity in space 2 - rigidity on earth 3 - precession 4 - Schuler oscillations The combination regrouping all the correct statements is: 1, 3
The properties of a single-phase electrical tachometer are: 1 - indication depending on the line resistance. 2 - independance from the aircraft airborne power supply. 3 - simple design The combination that regroups all of the correct statements is: 1, 2, 3
The purpose of a flight director is to: REDUCE THE PILOTS WORKLOAD BY PRESENTING DATA IN THE FORM OF CONTROL COMMANDS
The purpose of an aeroplane automatic trim system is to trim out the hinge moment of the: ELEVATOR(S)
The purpose of Auto Throttle is: TO MAINTAIN CONSTANT ENGINE POWER OR AEROPLANE SPEED
The purpose of Auto Trim function in autopilot is to: CONTROL ELEVATOR TRIM TAB IN ORDER TO RELIEVE ELEVATOR LOAD
The purpose of magnetic chip detectors is to: WARN OF IMPENDING FAILURE
The purpose of the altitude alert system is to generate a visual and aural warning to the pilot when the: AEROPLANE ATTITUDE DIFERS FROM A SELECTED ALTITUDE
The purpose of the autopilot Control Wheel Steering (CWS) mode is: to consider as target parameters, the current pitch and roll angles at the time the mode becomes active.
The purpose of the FMS temperature compensation function is: TO PROVIDE COMPENSATED ALTITUDES FOR TEMPERATURES DIFFERENT FROM STANDARD ATMOSPHERE ALONG THE VERTICAL APPROACH PROFILE
The purpose of the Navigation Display (ND) is to display the following information: FLIGHT PLAN, WEATHER RADAR, TERRAIN MAP, TCAS SYMBOLS
The purpose of the vibrating device of an altimeter is to: REDUCE THE EFFECT OF FRICTION IN THE LINKAGES
The purpose(s) of the flight director system is (are) to: 1 - give the position of the aircraft according to radioelectric axis. 2 - give the position of the aircraft according to waypoints. 3 - to aid the pilot when flying manually. The combination that regroups all of the correct statements is:: 3
The QNH is by definition the value of the: ALTIMETER SETTING SO THAT THE ALTIMETER, ON THE APRON OF THE AERODROME FOR WHICH IT IS GIVEN, READS THE ELEVATION
The QNH is by definition the value of the: ALTIMETER SETTING SO THAT THE ALTIMETER, ON THE APRON OF THE AERODROME FOR WHICH IT IS GIVEN, READS THE ELEVATION
The radio altimeter is required to indicate zero height AGL as the main wheels touch down on the runway. For this reason, it is necessary to: COMPENSATE FOR RESIDUAL HEIGHT AND CABLE LENGTH
The radio altimeter supplies data to the following system(s):1 - altitude alert system2 - TCAS3 - GPWS4 - automatic landing system. The combination that regroups all the correct statements is: 2, 3, 4
The radio altimeter uses the following wavelengths: CENTIMETRIC
The 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 regrouping all the correct statements is: 2 AND 3
The range of a low altitude radio altimeter is: 2500 FT
The rate of turn given by the rate of turn indicator is valid: FOR THE AIRSPEED RANGE DEFINED DURING THE CALIBRATION OF THE INSTRUMENT
The rate of turn indicator uses a gyroscope: 1 - the spinning wheel axis of which is parallel to the yawing axis. 2 - the spinning wheel axis of which is parallel to the pitch axis. 3 - the spinning wheel axis of which is parallel to the roll axis. 4 - with one degree of freedom. 5 - with two degrees of freedom The combination regrouping all the correct statements is: NB: the degree(s) of freedom of a gyro does not take into account its rotor spin axis: 2, 4
The rate-of-turn is the: CHANGE-OF-HEADING RATE OF THE AIRCRAFT
The reading of a Mach indicator is independent of: THE OUTSIDE TEMPERATURE
The requirement to carry a GPWS (Ground Proximity Warning System) concerns aeroplanes which are, depending on their age, weight and passenger capacity :; 1- turboprop-powered; 2- piston-powered; 3- jet-powered; The combination regrouping all the correct statements is : 1, 3
The response time of a vertical speed detector may be increased by adding a: CORRECTION BASED ON AN ACCELEROMETER SENSOR
The role of the FMS is to aid the flight crew with: 1 - immediate actions in case of emergency procedure2 - navigation3 - in-flight performance optimization4 - electronic check-lists. The combination that regroups all of the correct statements is: 2, 3
The role of the FMS is to: 1 - aid the crew with navigation 2 - shut down the engine in case of a malfunction 3 - automatically avoid conflicting traffic when autopilot engaged 4 - reduce crew workload 5 - aid fuel efficiency The combination that regroups all of the correct statements is: 1, 4, 5.
The role of the FMS is to:; 1 - aid the crew with navigation; 2 - shut down the engine in case of a malfunction ; 3 - automatically avoid conflicting traffic when autopilot engaged ; 4 - reduce crew workload; 5 - aid fuel efficiency; The combination that regroups all of the correct statements is: 1, 4 5
The RPM indicator (or tachometer) of a piston engine can include a small red arc within the arc normally used (green arc) In the RPM range corresponding to this small red arc the: PROPELLER GENERATES VIBRATION, CONTINUOUS RATING IS FORBIDDEN
The RPM indicator (or tachometer) of a piston engine can include a small red arc within the arc normally used (green arc) In the RPM range corresponding to this small red arc the: PROPELLER GENERATES VIBRATION, CONTINUOUS RATING IS FORBIDDEN
The sensor(s) feeding the EPR-indicator is(are): PRESSURE PROBES, ONE LOCATED UPSTREAM FROM THE COMPRESSOR INLET, AND THE OTHER DOWNSTREAM FROM THE TURBINE OUTLET
The sensors used to measure the exhaust gas temperature on an aircraft equipped with gas turbine engine are: THERMOCOUPLES
The sequence of the automatic landing comprises several phases (from final approach to touch-down) actuated by: THE RADIO ALTIMETER
The sideslip indication diplayed on the PFD (Primary Flight Display) is generated by: THE INERTIAL SYSTEM
The signal supplied by a transmitter fitted with a 3-phase AC generator, connected to RPM indicator, is: A THREE-PHASE VOLTAGE, THE FREQUENCY OF WHICH VARIES WITH THE RPM, THE INDICATOR IS PROVIDED WITH A MOTOR WHICH DRIVES A MAGNETIC TACHOMETER
The signal supplied by a transmitter fitted with a magnetic sensor, connected to an RPM indicator is: AN AC VOLTAGE, THE FREQUENCY OF WHICH VARIES WITH THE RPM, THE INDICATOR COVERTS THE SIGNAL INTO SQUARE SIGNALS WHICH ARE THEN COUNTED
The signal transmitted by a radio altimeter is: A FREQUENCY MODULATED CARIER WAVE
The spin axis of the turn indicator gyro is aligned along the: LATERAL AXIS OF THE AIRCRAFT
The spin axis of the turn indicator gyroscope is parallel to the: PITCH AXIS
The stall warning computer of a large aeroplane uses the following data: 1 - pitch attitude2 - angle of attack3 - configuration (slats / flaps). The combination that regroups all of the correct statements is: 2, 3
The stall warning computer uses the following data:; 1- mass of the aeroplane; 2- angle of attack; 3- wing flap deflection; 4- position of the landing gear; 5- TAT; 6- pressure altitude; The combination that regroups all of the correct statements is: 2, 3
The stall warning is inhibited: 1 - when the flaps are retracted 2 - when the aeroplane is on the ground 3 - when encountering a windshear 4 - upon receiving a GPWS alert The combination regouping all the correct statements is: 2.
The stall warning system of a large aeroplane includes:1 - an angle of attack sensor 2 - a computer3 - an independent pitot probe4 - a transmitter of the flap/slat position indicating system. The combination that regroups all of the correct statements: 1, 2, 4
The stall warning system of a large transport aeroplane includes: 1- an angle of attack sensor 2- a computer 3- a transmitter originating from the anemometer 4- an independent pitot probe 5- a transmitter of the flap/slat position indicating system. The combination regrouping all the correct statements is: 1, 2, 5
The stall warning system receives information about the :; 1- airplane angle of attack; 2- airplane speed; 3- airplane bank angle; 4- airplane configuration; 5- load factor on the airplane; The combination regrouping all the correct statements is: 1, 4
The Static Air temperature (SAT) is: the ambiant outside air temperature
The Static Air temperature (SAT) is: THE AMBIENT OUTSIDE AIR TEMPERATURE
The systems that can be connected to the Communication Management Unit (CMU), are:1 - EGPWS 2 - HF Communication Unit3 - Multipurpose Control and Display Unit (MCDU)4 - VHF Communication Unit5 – Satcom. The combination which regroups all of the correct: 2, 3, 4, 5
The systems that can be connected to the Communication Management Unit (CMU), are:; 1 - Flight Director; 2 - FMS; 3 - Multipurpose Control and Display Unit (MCDU); 4 - communication unit (VHF, HF, Satcom); The combination which regroups all of the correct statements is: 2, 3, 4
The systems that can be connected to the Communication Management Unit (CMU), are: 1 - EGPWS 2 - HF Communication Unit 3 - Multipurpose Control and Display Unit (MCDU) 4 - VHF Communication Unit 5 - Satcom The combination which regroups all of the correc: 2, 3, 4, 5.
The TAS is equal to the EAS only if: P= 1013, 25 HPA AND OAT= 15C
The TAS is obtained from the CAS by correcting for the following errors: 1 - instrument2 - compressibility3 - position4 – density. The combination that regroups all of the correct statements is: 2, 4
The TAS is obtained from the IAS by correcting for the following errors:1 - instrument2 - position3 - compressibility 4 – density. The combination that regroups all of the correct statements is: 1, 2, 3, 4
The TCAS (Traffic Collision Avoidance System) computer receives information: ; 1 - about the aircraft true airspeed; 2 - about the airplane configuration; 3 - about the pressure altitude through the mode C transponder; 4 - from the radio altimeter; The combination regrouping all the correct statements is: 2, 3, 4
The TCAS 2 (Traffic Collision Avoidance System) provides :; 1- traffic information (TA: Traffic Advisory); 2- horizontal resolution (RA: Resolution Advisory); 3- vertical resolution (RA: Resolution Advisory); 4- ground proximity warning; The combination regrouping all the correct statements is: 1, 3
The TCAS 2 data display devices can be in the form of: 1- a specific dedicated screen 2- a screen combined with the weather radar 3- a variometer represented on a liquid crystal screen which allows the display of Traffic Advisory (TA) and Resolution Advisory (RA) 4- an EFIS (Electronic Flight Instrument System) screen.; The combination regrouping all the correct statements is: 1, 2, 3 AND 4
The TCAS II gives avoidance resolutions: ONLY IN THE VERTICAL PLANE
The TCAS II has inputs from the radio altimeter in order to: GRADUALLY INHIBIT THE RESOLUTION ADVISORIES (RAS) WHEN GETTING CLOSER TO THE GROUND
The time for a normal alignment (not a quick alignment) of a strapdown inertial system is: 3 TO 10 MINUTES
The time for a normal alignment (not a quick alignment) of a strapdown inertial system is: 3 to 10 minutes.
The Total Air Temperature (TAT) is: THE TEMPERATURE RESULTING FORM THE AIRCRAFT MOTION IN THE AIR
The Total Air Temperature (TAT) is: the temperature resulting from the aircraft motion in the air.
The total pressure head comprises a mast which moves its port to a distance from the aircraft skin in order: TO LOCATE IT OUTSIDE THE BOUNDARY LAYER
The total pressure probe (pitot tube) comprises a mast which moves its port to a distance from the aircraft skin in order: TO LOCATE IT OUTSIDE THE BOUNDARY LAYER
The total pressure probe (pitot tube) is mounted at a distance from the aeroplane skin such that: IT IS LOCATED OUTSIDE THE BOUNDARY LAYER
The transmitter of RPM indicator may consist of :; 1- a magnetic sensor supplying an induced AC voltage; 2- a DC generator supplying a DC voltage; 3- a single-phase AC generator supplying an AC voltage; 4- a three-phase AC generator supplying a three-phase voltage; The combination of correct statements is : 1, 2, 3, 4
The turning error of a direct reading magnetic compass: INCREASES WHEN THE MAGNETIC LATITUDE INCREASES
The turning errors of a direct reading magnetic compass are: MAXIMUM AT THE MAGNETIC POLES
The two main sources of information used to calculate turbojet thrust are the: FAN ROTATION SPEED (OR N1) OR THE EPR (ENGINE PRESSURE RATIO)
The unit used to measure the capacitance of a capacitor is the: FARAD
The upper antenna of the TCAS II is: DIRECTIONAL TO IMPROVE THE SURVEILLANCE OF INTRUDERS
The use of an alternate static source fed from within the cabin results that the static pressure sensed is likely to be: LOWER THAN AMBIENT PRESSURE DUE TO AERODYNAMIC SUCTION
The validity period of the 'permanent' data base of aeronautical information stored in the database of a FMS is: 28 DAYS
The velocity of sound at the sea level in a standard atmosphere is: 661 KT
The vertical command bar of a flight director: 1 - repeats the position information given by the EHSI 2 - repeats the position information given by the VOR 3 - gives information about the direction and the amplitude of the corrections to be applied on the bank of the aircraft The combination regrouping all the correct statements is: 3
The vertical command bar of a flight director: GIVES INFORMATION ABOUT THE DIRECTION AND THE AMPLITUDE OF THE CORRECTIONS TO BE APPLIED ON THE BANK OF THE AIRCRAFT
The vertical flight path modes of an autopilot system are: 1- Pitch attitude hold 2- Altitude hold 3- Track hold 4- Glide slope intercept and track The combination that regroups all of the correct statements is: 2, 4.
The vertical flight path modes of an autopilot system are:1- Pitch attitude hold 2- Altitude hold 3- Track hold 4- Glide slope intercept and track The combination that regroups all of the correct statements is: 2, 4
The vertical speed indicator (VSI) is fed by: STATIC PRESSURE
The yaw damper affects: RUDDER ONLY
The yaw damper system acts on: THE RUDDER ONLY
The yaw damper system acts on: the rudder only.
The yaw damper system acts on: THE RUDDER WITHOUT MOVING THE RUDDER PEDALS
The yaw damper system acts on: the rudder without moving the rudder pedals.
The yaw damper system controls: THE RUDDER, WITH THE ANGULAR RATE ABOUT THE YAW AXIS AS THE INPUT SIGNAL
The yaw damper system is operative: DURING MANUAL OR AUTOMATIC FLIGHT
The yaw damper system is operative: during manual or automatic flight.
The yaw damper system sends a motion order to the rudder if the yawing rate of the aircraft: IS NOT CONSTANT
The yaw damper system sends a motion order to the rudder if the yawing rate of the aircraft: is not constant.
The Yaw Damper system: 1 - counters any wrong pilot action on the rudder pedals; 2 - counters dutch roll; 3 - is active only when autopilot is engaged. The combination regrouping all the correct statements are: 2
To allow the coupling of a dual channel flight director: BOTH AUTOPILOT CHANNELS MUST BE SELECTED ON
To be as accurate as possible, an anemometer must be calibrated according to the following formula: SAINT-VENANT, TAKING INTO ACCOUNT THE AIR COMPRESSIBILITY
To indicate a temperature, a thermocouple requires: NO POWER SUPPLY
To obtain the instantaneous position from the accelerations, it is necessary to: 1 - integrate twice the acceleration in time 2 - know the initial position 3 - know the initial speed The combination that regroups all of the correct statements is: 1, 2, 3.
To obtain the instantaneous position from the accelerations: IT ISNECESSARY TO INTEGRATE TWICE THE ACCELERATION IN TIME, AND TO KNOW THE INITIAL POSITION AND THE INITIAL SPEED
To obtain the instantaneous position from the accelerations: it is necessary to integrate twice the acceleration in time, and to know the initial position and the initial speed.
To obtain the instantaneous speed from the accelerations, it is necessary to:1 - integrate once the acceleration in time2 - know the initial position 3 - know the initial speedThe combination that regroups all of the correct statements is: 1, 3
To obtain the instantaneous speed from the accelerations: IT IS NECESARY TO INTEGRATE THE ACCELERATION ONCE IN TIME, AND TO KNOW THE INITIAL SPEED ONLY
To permit turbine exit temperatures to be measured, gas turbines are equipped with thermometers which work on the following principle: THERMOCOUPLE
Torque can be determined by measuring the: OIL PRESSURE AT THE FIXED CROWN OF AN EPICYCLOIDAL REDUCER OF THE MAIN ENGINE GEAR BOX
Total Air Temperature (TAT) is: HIGUER OR EQUAL TO STATIC AIR TEMPERATURE (SAT) DEPENDING ON MACH NUMBER AND SAT
True Air Speed (TAS) is equal to Equivalent Air Speed (EAS) only if: P= 1013, 25 HPA AND OAT= 15°C
True Air Speed (TAS) is obtained from Calibrated Air Speed (CAS) by correcting for the following errors: 1 - instrument 2 - compressibility 3 - position 4 - density The combination regrouping all the correct statements is: 2, 4
True Air Speed (TAS) is obtained from Equivalent Air Speed (EAS) by correcting for: DENSITY ERROR
True Air Speed (TAS) is obtained from Indicated Air Speed (IAS) by correcting for the following errors: 1 - instrument 2 - position 3 - compressibility 4 - density The combination regrouping all the correct statements is: 1, 2, 3, 4
True Air Speed (TAS) is: EQUIVALENT AIRSPEED (EAS) CORRECTED FOR DENSITY ERROR
True Air Speed (TAS) is: CALIBRATED AIRSPEED(CAS) CORRECTED FOR COMPRESSIBILITY AND DENSITY ERRORS
True Air Speed (TAS) is: EQUIVALENT AIRSPEED (EAS) CORRECTED FOR DENSITY ERROR
True Air Speed (TAS) is: INDICATED AIR SPEED (IAS) CORRECTED FOR INSTRUMENT, POSITION, COMPRESSIBILITY AND DENSITY ERRORS
Under normal operating conditions, when an aircraft is in a banked turn, the rate-of-turn indicator is a valuable gyroscopic flight control instrument ; when it is associated with an attitude indicator it indicates :; 1. the angular velocity of the aircraft about the yaw axis; 2. The bank of the aircraft; 3. The direction of the aircraft turn; 4. The angular velocity of the aircraft about the real vertical; The combination of correct statements is : 1, 3
VFE is the maximum speed: WITH THE FLAPS EXTENDED FOR EACH APPROVED FLAP POSITION
VFE is the maximum speed: WITH THE FLAPS EXTENDED IN A GIVEN POSITION
VLO is the maximum : SPEED AT WHICH THE LANDING GEAR CAN BE OPERATED WITH FULL SAFETY
VNE is the maximum speed: WHICH MUST NEVER BE EXCEEDED
VNO is the maximum speed: NOT TO BE EXCEEDED EXCEPT IN STILL AIR AND WITH CAUTION
When a TCAS is operating, a failure of the active transponder will cause the TCAS to: NO LONGER OPERATE NORMALLY
When a TCAS Resolution Advisory (RA) climb instruction is generated, the required vertical speed range displayed on the vertical speed indicator: DOES NOT TAKE INTO ACCOUNT THE STALL MARGIN
When an aircraft has turned 360 degrees with a constant attitude and bank, the pilot observes the following on a classic artificial horizon: ATTITUDE AND BANK CORRECT
When an aircraft has turned 90 degrees with a constant attitude and bank, the pilot observes the following on a classic artificial horizon : TOO MUCH NOSE-UP AND BANK TOO LOW
When an aircraft, operating in the VOR coupled mode, approaches the "cone of confusion" over a VOR station, the roll channel of the autopilot: TEMPORARILY MAINTAINS A HEADING
When available, the yaw damper indicator supplies the pilot with information regarding the: YAW DAMPER ACTION ON THE RUDDER
When being engaged, and without selecting a particular mode, an automatic pilot enables: AEROPLANE STABILISATION WITH ALTITUDE HOLD OR MAINTAINING VERTICAL SPEED AND POSSIBLY AUTOMATIC TRIM
When climbing at a constant CAS in a standard atmosphere: 1 - TAS decreases 2 - TAS increases 3 - Mach number increases 4 - Mach number decreases The combination regrouping all the correct statements is: 2, 3
When climbing at a constant CAS in a standard atmosphere: TAS INCREASES
When climbing at a constant CAS through an isothermal layer, the Mach number: INCREASES
When climbing at a constant CAS: EAS DECREASES
When climbing at a constant CAS: MACH NUMBER INCREASES
When climbing at a constant Mach number through an isothermal layer, the CAS: DECREASES
When climbing at a constant Mach number: CAS DECREASES
When compared with the volumetric fuel flowmeter, the mass fuel flowmeter takes into account the fuel: DENSITY
When comparing a TCAS Traffic Advisory (TA) and a Resolution Advisory (RA), which of the following statements is correct? A TA indicates the relative position of the intruding traffic; an RA provides a vertical traffic avoidance manœuvre.
When cruising, the autothrottle system can be engaged in the following mode(s): holding of constant: 1 - TAS 2 - IAS 3 - Mach number The combination that regroups all of the correct statements is: 2, 3.
When descending at a constant CAS in a standard atmosphere: 1 - TAS increases 2 - TAS decreases 3 - Mach number increases 4 - Mach number decreases The combination regrouping all the correct statements is: 2, 4
When descending at a constant CAS through an isothermal layer, the Mach number: DECREASES
When descending at a constant CAS: EAS INCREASES
When descending at a constant CAS: MACH NUMBER DECREASES
When descending at a constant Mach number: CAS INCREASES
When disengaging the autopilot, the function providing a smooth 'hand-over' is the: automatic pitch trim function.
When engaged in the FMS lateral navigation mode (LNAV) the autopilot uses: THE ROLL OR HEADING COMMAND COMPUTED BY THE FMS
When engaged in the FMS lateral navigation mode (LNAV) the autopilot uses the command provided by the: FMS.
When engaged in the FMS lateral navigation mode (LNAV) the autopilot uses: the roll or heading command computed by the FMS.
When engaged in the lateral navigation mode (LNAV) the autopilot uses: THE FMS OR HEADING COMMAND
When engaged in the pitch hold mode, the autopilot uses data issued by the: ATTITUDE REFERENCE SYSTEM
When engaged in the pitch hold mode, the autopilot uses data issued by the: attitude reference system.
When engaging the autopilot, the function providing a smooth 'take-over' is the: AUTOMATICALLY SYNCHRONISATION FUNCTION
When Enhanced GPWS (EGPWS) terrain is displayed, if the computed aircraft position becomes less accurate: THE TERRAIN DISPLAY WILL DIVERGE FROM THE REAL TERRAIN ENVIRONMENT AROUND THE AIRCRAFT POSITION
When flying in cold air (colder than standard atmosphere), indicated altitude is: HIGHER THAN THE TRUE ALTITUDE
When flying in cold air (colder than standard atmosphere), the altimeter will: OVERSTIMATE
When flying in warm air (warmer than standard atmosphere), indicated altitude is: LOWER THAN THE TRUE ALTITUDE
When pressing the push button EVENT on the unit control of flight data recorder: A MARK IS SET ON THE RECORDING, ENABLING THIS EVENT TO BE FOUND RAPIDLY AT A SUBSEQUENT ANALYSIS
When required, the ground proximity warning system (GPWS) must automatically provide distinctive warning to the flight crew of: 1 - impeding stall 2 - excessive sink rate 3 - altitude loss after take-off or go-around 4 - incorrect landing configuration 5 - dangerous ground proximity 6 - downward glide-slope deviation The combination regrouping all the correct statements is: 2, 3, 4, 5, 6
When sent, a MAYDAY datalink message to the ATC has the following effect on ADS: THE ADS CONTRACT IS SWITCHED TO HIGH PERIODIC REPORTING RATE
When the autopilot is engaged, the role of the automatic trim is to: RELIEVE THE A. P. SERVO MOTOR AND RETURN THE AIRCRAFT IN-TRIM AT A.P. DISCONNECT
When the flight warning system (FWS) identifies an overspeed condition (airspeed exceeding Vmo/Mmo), it generates: A WARNING MESSAGE
When the intruding aircraft is equipped with a serviceable mode C transponder, the TCAS 2 (Traffic Collision Avoidance System) generates a:”TRAFFIC ADVISORY” AND VERTICAL “RESOLUTION ADVISORY”
When the intruding aircraft is equipped with a transponder without altitude reporting capability, the TCAS (Traffic Collision Avoidance System) issues a: “TRAFFIC ADVISORY” ONLY
When the rotary knob on the INS control panel is set to "NAV" mode, it is: THE NORMAL OPERATING MODE ALLOWING USE OF ALL THE FUNCIONS OF THE SYSTEM
When the TCAS 2 (Traffic alert and Collision Avoidance System) generates a Resolution Advisory (RA), the associated intruder appears on TCAS display as a: SOLID RED SQUARE
When the yaw damper system sends motion orders to the rudder: NO FEEDBACK IS PROVIDED ON THE RUDDER PEDALS
When two waypoints are entered on the FMS flight plan page, a track between the two fixes is computed and can be displayed on the Navigation map display (ND). This leg created is: A GREAT CIRCLE ARC
When, in flight, the needle and ball of a needle-and-ball indicator are on the left, the aircraft is: TURNING LEFT WITH TOO MUCH BANK
When, in flight, the needle and ball of a needle-and-ball indicator are on the right, the aircraft is: TURNING RIGHT WITH TOO MUCH BANK
When, in flight, the needle of a needle-and-ball indicator is on the right and the ball on the left, the aircraft is: TURNING RIGHT WITH NOT ENOUGH BANK
When, in flight, the needle of a needle-and-ball indicator is on the left and the ball on the right, the aircraft is: TURNING LEFT WITH NOT ENOUGH BANK
Which of the following statements about hard and soft iron in relation to magnetism is correct? Hard iron magnetism is of a permanent nature and soft iron is of a non-permanent nature.
Which of the following statements are correct for an aeroplane cruising at FL 60 with a true airspeed (TAS) of 100 kt in standard atmospheric conditions? 1 - The TAS is approximately 10% higher than the IAS. 2 - The difference between the equivalent airspeed (EAS) and the calibrated airspeed (CAS) is negligible. 3 - The speed displayed on the airspeed indicator is a calibrated airspeed (CAS) if the position error and instrument error are zero: 1, 2 AND 3 ARE ALL CORRECT
Which of these statements about the activation of the take-off warning when a take-off is initiated are correct or incorrect?; I. An aural warning is given when the stabiliser is not in a safe position for take-off.; II. An aural warning is given when the parking brake is still ON: 1 AND 2 ARE CORRECT
Which of these statements about the activation of the take-off warning when a take-off is initiated are correct or incorrect?; I. An aural warning is given when the elevator is not in a safe position for take-off.; II. An aural warning is given when the parking brake is still ON: 1 IS INCORRECT, 2 IS CORRECT
Which of these statements about the activation of the take-off warning when a take-off is initiated are correct or incorrect? I. An aural warning is given when the stabiliser is not in a safe position for take-off. II. An aural warning is given when the brake pressure is too low: I is correct, II is incorrect.
Which one of the following statements is true with regard to the operation of a Mach trim system: IT ONLY COMPARES ABOV A PRE-DETERMINED MACH NUMBER
While inertial platform system is operating on board an aircraft, it is necessary to use a device with the following characteristics, in order to keep the vertical line with a pendulous system: WITH DAMPING AND A PERIOD OF ABOUT 84 MINUTES
With a TCAS II, when a corrective resolution is generated: THE VERTICAL SPEED MUST BE EFFECTIVELY MODIFIED WITHOUT DELAY
With CAS and pressure altitude, we can deduce: EAS
With constant weight and configuration, an aeroplane always takes off at the same: EAS
With constant weight and configuration, an aircraft always takes off at the same: EQUIVALENT AIRSPEED
With EAS and density altitude, we can deduce: TAS
With EAS and pressure altitude (Zp), we can deduce: CAS
Without any external action, the axis of a free gyroscope is fixed with reference to: SPACE
Your aircraft and an intruding aircraft both are TCAS 2 (Traffic alert and Collision Avoidance System) equipped. Your TCAS determines the bearing of the intruding aircraft by: USING A SPECIFIC DIRECTIONAL ANTENNA
Your aircraft and an intruding aircraft both are TCAS 2 (Traffic alert and Collision Avoidance System) equipped. Your TCAS determines the range of the intruding aircraft by: MEASURING THE TIME LAPSE BETWEEN THE TRANSMISSION OF AN INTERROGATION SIGNAL AND THE RECEPTION OF A REPLY SIGNAL TRANSPONDER OF THE INTRUDER
Your aircraft and an intruding aircraft both are TCAS II equipped. If the transponder of the intruder is switched off or unserviceable: THE INTRUDING AIRCRAFT IS INVISIBLE TO YOUR TCAS EQUIPMENT
Your aircraft and an intruding traffic are both TCAS II equipped. Your TCAS can generate: COORDINATED AND COMPLEMENTARY RESOLUTION ADVISORIES
Your aircraft and an intruding traffic are both TCAS II equipped. Your TCAS: CAN GENERATE COORDINATED RESOLUTION ADVISORIES
Your aircraft and an intruding traffic are both TCAS II equipped. The information available to your TCAS equipment is: TWO DIMENSIONAL: YOUR TCAS CAN GENERATE BOTH TAS (TRAFFIC ADVOSORIES) AND RAS (RESOLUTION ADVISORIES)
Your aircraft and an intruding traffic are TCAS II equipped. Your TCAS can generate: CORDINATED RESOLUTION ADVISORIES
Your aircraft and an intruding traffic both are TCAS II equipped. Your TCAS determines the relative height of the intruding aircraft by: COMPARING THE ALTITUDES OF THE TWO AIRCRAFT
Your aircraft is TCAS II equipped. To be able to generate a resolution advisory (RA), the intruder must be at least equipped with: A TRANSPONDER MODE C
Your aircraft is TCAS II equipped. To be able to generate a traffic advisory (TA), the intruder must be at least equipped with: A TRANSPONDER MODE A
Your aircraft is TCAS II equipped; an intruding traffic only has a mode C transponder. The information available to your TCAS equipment is: THREE DIMENSIONAL; YOUR TCAS CAN GENERATE BOTH TAS (TRAFFIC ADVOSORIES) AND RAS (RESOLUTION ADVISORIES)
Your aircraft is TCAS II equipped; an intruding traffic only has a mode A transponder. The information available to your TCAS equipment is: TWO DIMENSIONAL ONLY, YOUR TCAS CANNOT GENERATE RAS (RESOLUTION ADVISORIES)

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