Aviation Instrumentation Questions PDF

0001. A blocked pitot head with a clear static source causes the airspeed indicator to ; a) react like an altimeter. b) read like a vertical speed indicator. c) freeze at zero. d) operate...

0001. A blocked pitot head with a clear static source causes the airspeed indicator to ; a) react like an altimeter. b) read like a vertical speed indicator. c) freeze at zero. d) operate normally. Answer ; a) react like an altimeter. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0002. A “Bourdon Tube” is used in ; a) vibration detectors. b) turbine temperature probes. c) smoke detectors. d) pressure sensors. Answer ; d) pressure sensors. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0003. 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) a servomechanism. b) a feedback control circuit. c) an amplifier. d) an autopilot. Answer ; a) a servomechanism. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0004. A control system consisting of four pendulous vanes is used in ; a) a directional gyro indicator. b) a strap down inertial system. c) an air driven artificial horizon. d) a gyromagnetic indicator. Answer ; c) an air driven artificial horizon. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0005. A D-ATIS is ; a) an ATIS message received by datalink. b) a short ATIS that only includes parameters that have changed from previous ATIS record. c) an ATIS message broadcasted on HF when out of the VHF radio range from the airport. d) a Divertion ATIS for the alternate airport. Answer ; a) an ATIS message received by datalink. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0006. A directional gyro consists of a ; NB : the degree(s) of freedom of a gyro does not take into account its rotor spin axis. a) 1 degrees-of-freedom vertical axis gyro. b) 2 degrees-of-freedom horizontal axis gyro. c) 1 degrees-of-freedom horizontal axis gyro. d) 2 degrees-of-freedom vertical axis gyro. Answer ; b) 2 degrees-of-freedom horizontal axis gyro. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0007. 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 ; NB : the degree(s) of freedom of a gyro does not take into account its rotor spin axis. a) 1 , 4. b) 1 , 3. c) 2 , 4. d) 2 , 3. Answer ; a) 1 , 4. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- Ateş Murat Üstünbıçak , ATPL 1 Instrumentation 0008. A directional gyro is corrected for an apparent drift due to the earth’s rotation at latitude 30ºS. During a flight at latitude 60ºN , a drift rate of 15.5º/h to the right is observed. The apparent wander due to change of aircraft position is ; a) 2.5º/h to the right. b) 2.5º/h to the left. c) 5º/h to the right. d) 5º/h to the left. Answer ; d) 5º/h to the left. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0009. A dynamic pressure measurement circuit is constituted of the following pressure probes ; a) total pressure and standard pressure. b) total pressure and static pressure. c) total pressure only. d) static pressure only. Answer ; b) total pressure and static pressure. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0010. A flight control system is fail-operational if , in the event of a failure ; a) the approach only can be completed automatically. b) the landing is not completed automatically. c) the approach , flare and landing can be completed automatically. d) there is no significant out-of-trim condition or deviation of flight path or attitude but the landing is not compleed automatically. Answer ; c) the approach , flare and landing can be completed automatically. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0011. A flight control system is fail-passive if , in the event of a failure ; a) the system operates as a fail-operational system. b) there is no significant out-of-trim condition or deviation of flight path or attitude but the landing is not completed automatically. c) there is no significant out-of-trim condition or deviation of flight path or attitude but the landing is completed automatically. d) the system operates as a fail-operational hybrid landing system. Answer ; b) there is no significant out-of-trim condition or deviation of flight path or attitude but the landing is not completed automatically. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0012. A flight control system which can , in the event of a failure , complete automatically the approach , flare and landing is called fail ; a) soft. b) operational. c) hard. d) passive. Answer ; b) operational. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0013. 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 ; a) 1 , 2 , 3 , 4. b) 1 , 3 , 4. c) 4. d) 1. Answer ; c) 4. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- Ateş Murat Üstünbıçak , ATPL 2 Instrumentation 0014. 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 signal comes from the magnetic compass. 4. the accuracy on the value of the magnetic field indication is less than 0.5°. The combination regrouping all the correct statements is ; a) 2 , 4. b) 1 , 2 , 4. c) 1 , 2. d) 1 , 4. Answer ; a) 2 , 4. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0015. 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 ; a) 1 , 3 , 4. b) 2 , 4. c) 1 , 2 , 4. d) 1 , 2 , 3 , 4. Answer ; b) 2 , 4. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0016. 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 ; a) 7.5º/h to the right. b) 13º/h to the left. c) 13º/h to the right. d) 7.5º/h to the left. Answer ; c) 13º/h to the right. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0017. A free gyro has the axis of the spinning rotor horizontal and aligned with the geographic meridian. If this free gyro is situated at latitude 60°N , the apparent drift rate according to the earthbound observer is ; a) 13º/h to the right. b) 13º/h to the left. c) 7.5º/h to the left. d) 7.5º/h to the right. Answer ; a) 13º/h to the right. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0018. 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 ; a) 1 , 3 , 4 , 5. b) 2 , 4 , 5. c) 1 , 2 , 3 , 4 , 5. d) 1 , 3 , 5. Answer ; c) 1 , 2 , 3 , 4 , 5. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0019. A gravity erector system is used to correct the errors on ; a) a directional gyro. b) an artificial horizon. c) a turn indicator. d) a gyromagnetic compass. Answer ; b) an artificial horizon. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- Ateş Murat Üstünbıçak , ATPL 3 Instrumentation 0020. A gravity type erector is used in a vertical gyro device to correct errors on ; a) a directional gyro unit. b) a gyromagnetic indicator. c) an artificial horizon. d) a turn indicator. Answer ; c) an artificial horizon. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0021. A ground proximity warning system ( GPWS ) , when mandatory installed on board an aircraft , must in all cases generate ; a) a visual alarm to which a sound alarm can be. b) a sound alarm or a visual alarm. c) a sound and visual alarm. d) at least one sound alarm to which a visual alarm can be added. Answer ; d) at least one sound alarm to which a visual alarm can be added. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0022. 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 ; a) 1 , 3 , 4 , 5. b) 2 , 3 , 5. c) 1 , 4. d) 2 , 3. Answer ; a) 1 , 3 , 4 , 5. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0023. A laser gyro can measure ; a) an acceleration and a rotation motion. b) an acceleration and a speed. c) an acceleration. d) a rotation motion. Answer ; d) a rotation motion. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0024. A leak in the pitot total pressure line of a non-pressurized aircraft to an airspeed indicator would cause it to ; a) under-read in a climb and over-read in a descent. b) over-read. c) over-read in a climb and under-read in a descent. d) under-read. Answer ; d) under-read. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0025. A magnetic tachometer consists of ; a) a single-phase generator connected to an asynchronous motor. b) a single-phase generator connected to a synchronous motor. c) a permanent magnet turning inside a non magnetic drag cup. d) a three phase generator connected to a synchronous motor. Answer ; c) a permanent magnet turning inside a non magnetic drag cup. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0026. A manifold pressure gauge of a piston engine measures ; a) absolute airpressure entering the carburettor. b) absolute pressure in intake system near the inlet valve. c) fuel pressure leaving the carburettor. d) vacuum in the carburettor. Answer ; b) absolute pressure in intake system near the inlet valve. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- Ateş Murat Üstünbıçak , ATPL 4 Instrumentation 0027. A MAYDAY datalink message can be sent to the ATC via the ; a) ACAS ( Aircraft Collision Avoidance System ) application. b) ADS application. c) AFN application. d) CPDLC application. Answer ; d) CPDLC application. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0028. 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 ; a) hot junction is maintained constant. b) cold junction is maintained constant. c) hot junction is maintained at 15 °C. d) cold junction is maintained at 15 °C. Answer ; b) cold junction is maintained constant. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0029. 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 ; a) roll wings level and maintain the heading obtained at that moment. b) restore the flight attitude and the rate of turn selected on the autopilot control display unit. c) maintain the track and the flight attitude obtained at that moment. d) maintain the flight attitude obtained at that moment. Answer ; d) maintain the flight attitude obtained at that moment. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0030. 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 ; a) 015° b) 330° c) 030° d) 355° Answer ; c) 030° ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0031. 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 ; a) 160° b) 170° c) 190° d) 200° Answer ; a) 160° ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0032. 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 ; a) 200° b) 150° c) 180° d) 170° Answer ; a) 200° ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0033. 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 ; a) 010° b) 330° c) 360° d) 030° Answer ; b) 330° ----------------------------------------------------------------------------------------------------------------------------------------------------------------- Ateş Murat Üstünbıçak , ATPL 5 Instrumentation 0034. A pitot tube covered by ice which blocks the ram air inlet will affect the following instrument(s) ; a) airspeed indicator , altimeter and vertical speed indicator. b) vertical speed indicator only. c) airspeed indicator only. d) altimeter only. Answer ; c) airspeed indicator only. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0035. A radio altimeter can be defined as a ; a) self-contained on-board aid used to measure the true height of the aircraft. b) ground radio aid used to measure the true height of the aircraft. c) self-contained on-board aid used to measure the true altitude of the aircraft. d) ground radio aid used to measure the true altitude of the aircraft. Answer ; a) self-contained on-board aid used to measure the true height of the aircraft. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0036. A radio altimeter uses ; a) two antennas ; both of them for simultaneous transmission and reception. b) four antennas ; two for the transmission and two for the reception. c) a single antenna for simultaneous transmission and reception. d) two antennas ; one for the transmission and an other for the reception. Answer ; d) two antennas ; one for the transmission and an other for the reception. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0037. A radio altimeter uses the following frequency band ; a) HF ( High Frequency ). b) VLF ( Very Low Frequency ). c) SHF ( Super High Frequency ). d) VHF ( Very High Frequency ). Answer ; c) SHF ( Super High Frequency ). ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0038. A radio altimeter uses the following frequency band ; a) 4200 KHz to 4400 KHz. b) 1600 KHz to 1660 KHz. c) 1600 GHz to 1660 GHz. d) 4200 MHz to 4400 MHz. Answer ; d) 4200 MHz to 4400 MHz. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0039. 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 ; a) 1. b) 1 , 2 , 3. c) 2. d) 1 , 2. Answer ; c) 2. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0040. A ring laser gyro can measure ; a) rotation about its sensitive axis. b) accelerations in all direction. c) accelerations about its sensitive axis. d) rotation in all directions. Answer ; a) rotation about its sensitive axis. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- Ateş Murat Üstünbıçak , ATPL 6 Instrumentation 0041. A ring laser gyro is ; a) a device which measures angular movements. b) a device which measures the earth rate precession. c) an optical accelerometers. d) used for stabilising the INS platform. Answer ; a) a device which measures angular movements. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0042. A servo-assisted altimeter is more accurate than a simple altimeter because the small movements of ; a) the capsules are detected by a very sensitive electro-magnetic pick-off. b) the capsules are not taken into account. c) the capsules are inhibited. d) the pointers are detected by a very sensitive electro-magnetic pick-off. Answer ; a) the capsules are detected by a very sensitive electro-magnetic pick-off. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0043. A slaved directional gyro derives it’s directional signal from ; a) the air-data-computer. b) the flux valve. c) the flight director. d) a direct reading magnetic compass. Answer ; b) the flux valve. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0044. A stability augmentation system ( SAS ) in a helicopter ; a) assists in static stability only. b) assists in static and dynamic stability. c) assists in dynamic stability only. d) has full control of dynamic stability. Answer ; a) assists in static stability only. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0045. A stall warning system is based on a measure of ; a) groundspeed. b) angle of attack. c) airspeed. d) attitude. Answer ; b) angle of attack. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0046. A Stand-by-horizon or emergency attitude indicator ; a) is automatically connected to the primary vertical gyro if the alternator fails. b) contains its own separate gyro. c) is fully independent of external energy resources in an emergency situation. d) only works of there is a complete electrical failure. Answer ; b) contains its own separate gyro. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0047. A strapdown inertial system consists in ; a) a platform free of the aircraft chassis which includes gyroscopes and accelerometers. b) accelerometers attached to the aircraft chassis and gyroscopes which are not. c) gyroscopes attached to the aircraft chassis and accelerometers which are not. d) a platform attached to the aircraft chassis and which includes gyroscopes and accelerometers. Answer ; d) a platform attached to the aircraft chassis and which includes gyroscopes and accelerometers. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0048. A synchroscope is used on aircraft to ; a) reduce the vibration of each engine. b) achieve optimum control of on-board voltages. c) set several engines to the same speed. d) reduce the rpm of each engine. Answer ; c) set several engines to the same speed. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- Ateş Murat Üstünbıçak , ATPL 7 Instrumentation 0049. A TCAS 2 generates a resolution advisory ( RA ) when ; a) the intruder becomes “proximate traffic”. b) a potential collision threat exists. c) the intruder becomes “other traffic”. d) a serious collision threat exists. Answer ; d) a serious collision threat exists. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0050. A TCAS 2 ( Traffic Collision Avoidance System ) provides ; a) a simple intruding airplane proximity warning. b) the intruder relative position and possibly an indication of a collision avoidance manoeuvre within the vertical plane only. c) the intruder relative position and possibly an indication of a collision avoidance manoeuvre within the horizontal plane only. d) the intruder relative position and possibly an indication of a collision avoidance manoeuvre within both the vertical and horizontal planes. Answer ; b) the intruder relative position and possibly an indication of a collision avoidance manoeuvre within the vertical plane only. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0051. A TCAS Resolution Advisory ( RA ) voice message “CLIMB - CLIMB NOW” repeated twice is generated ; a) after a “DESCEND” RA when a reversal in the vertical manoeuvre sense is required. b) each time a “CLIMB” RA is announced by a voice message. c) when cleared of conflict , and below the cruise altitude. d) after a “CLIMB” RA when the climb vertical rate is too weak. Answer ; a) after a “DESCEND” RA when a reversal in the vertical manoeuvre sense is required. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0052. A temperature sensor has a recovery factor of 0.95. The temperature measured is equal to ; a) 95% of the ram air temperature ( RAT ). b) static air temperature ( SAT ) + 95% of the ram rise. c) 95% of the static air temperature ( SAT ). d) ram air temperature ( RAT ) + 95% of the ram rise. Answer ; b) static air temperature ( SAT ) + 95% of the ram rise. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0053. A thermocouple can be made of ; a) a three wire coil. b) two metal conductors of the same nature fixed together at two points. c) two metal conductors of different nature fixed together at a single point. d) a single wire coil. Answer ; c) two metal conductors of different nature fixed together at a single point. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0054. A thermocouple consists of ; a) a junction of two dissimilar metals. b) several layers of identical metals, but with different thickness. c) two layers of identical metals , both having the same size. d) two layers of identical metals , one being longer than the other. Answer ; a) a junction of two dissimilar metals. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0055. A thermocouple type temperature sensing is composed of ; a) two identical metals joined together at one end ( called hot junction or measure junction ). b) two identical metals joined together at both ends ( called hot and cold junctions ). c) a single-wire metal winding. d) two dissimilar metals joined together at one end ( called hot junction or measure junction ). Answer ; d) two dissimilar metals joined together at one end ( called hot junction or measure junction ). ----------------------------------------------------------------------------------------------------------------------------------------------------------------- Ateş Murat Üstünbıçak , ATPL 8 Instrumentation 0056. A thermocouple type thermometer consists of ; a) two metal conductors of the same type connected at two points. b) a single-wire metal winding. c) a Wheatstone bridge connected to a voltage indicator. d) two metal conductors of different type connected at two points. Answer ; d) two metal conductors of different type connected at two points. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0057. A three-phase electrical tachometer consists of ; a) a three-phase generator , a synchronous motor and a magnetic tachometer. b) three associated dynamos. c) three speed probes and a phonic wheel. d) a speed probe and a phonic wheel. Answer ; a) a three-phase generator , a synchronous motor and a magnetic tachometer. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0058. A three-phase electrical tachometer utilises a generator feeding ; a) a synchronous motor turning a drag cup. b) directly a voltmeter. c) directly a drag cup. d) directly a galvanometer. Answer ; a) a synchronous motor turning a drag cup. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0059. 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 ; a) 2 and 3. b) 1 and 3. c) 1 and 2. d) 1 , 2 and 3. Answer ; c) 1 and 2. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0060. A vertical speed indicator measures the difference between ; a) the total pressure and the static pressure. b) the total instantaneous pressure and the total pressure at a previous moment. c) the dynamic pressure and the static pressure. d) the instantaneous static pressure and the static pressure at a previous moment. Answer ; d) the instantaneous static pressure and the static pressure at a previous moment. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0061. A vibration indicator receives a signal from different sensors ( accelerometers ). It indicates the ; a) vibration period expressed in seconds. b) vibration frequency expressed in Hz. c) acceleration measured by the sensors , expressed in g. d) vibration amplitude at a given frequency. Answer ; d) vibration amplitude at a given frequency. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0062. A VMO-MMO warning device consists of an alarm connected to ; a) a barometric aneroid capsule and an airspeed sensor subjected to dynamic pressure. b) a barometric aneroid capsule subjected to a static pressure and an airspeed sensor subjected to a dynamic pressure. c) a barometric aneroid capsule subjected to a dynamic pressure and an airspeed sensor subjected to a static pressure. d) a barometric aneroid capsule and an airspeed sensor subjected to a static pressure. Answer ; b) a barometric aneroid capsule subjected to a static pressure and an airspeed sensor subjected to a dynamic pressure. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- Ateş Murat Üstünbıçak , ATPL 9 Instrumentation 0063. About a magnetic compass ; a) errors of parallax are due to the oscillation of the compass rose. b) acceleration errors are due to the angle of dip. c) acceleration errors are due to Schüler oscillations. d) turning error is due to the vertical component of the earth’s magnetic field. Answer ; d) turning error is due to the vertical component of the earth’s magnetic field. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0064. According to AMC 25-11 concerning the electronic display systems , the amber/yellow colours are associated with the following alert ; a) advisory. b) warning. c) status. d) caution. Answer ; d) caution. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0065. According to AMC 25-11 concerning the electronic display systems , the colour associated with a caution-type alert is ; a) red. b) white. c) magenta. d) amber or yellow. Answer ; d) amber or yellow. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0066. According to AMC 25-11 concerning the electronic display systems , the colour associated with a warning-type alert is ; a) amber. b) red. c) magenta. d) yellow. Answer ; b) red. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0067. According to AMC 25-11 concerning the electronic display systems , the colour associated with an armed mode is ; a) magenta. b) white or cyan. c) yellow. d) green. Answer ; b) white or cyan. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0068. According to AMC 25-11 concerning the electronic display systems , the colour associated with an engaged mode is ; a) magenta. b) green. c) amber. d) white. Answer ; b) green. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0069. According to AMC 25-11 concerning the electronic display systems , the colours used are ; a) red for caution & abnormal sources , white for flight enveloppe limits. b) amber for the system limits , white for autopilot of flight director engaged modes. c) red for warnings , magenta for autopilot or flight director engaged modes. d) red for flight enveloppe and system limits , green for autopilot or flight director engaged modes. Answer ; d) red for flight enveloppe and system limits , green for autopilot or flight director engaged modes. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0070. According to AMC 25-11 concerning the electronic display systems , the green colour is associated with the following indication ; a) engaged mode. b) advisory. c) armed mode. d) status. Answer ; a) engaged mode. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- Ateş Murat Üstünbıçak , ATPL 10 Instrumentation 0071. According to AMC 25-11 concerning the electronic display systems , the red colour is associated with the following alert ; a) warning. b) status. c) caution. d) advisory. Answer ; a) warning. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0072. According to AMC 25-11 concerning the electronic display systems , the white/cyan colours are associated with the following indication ; a) warning. b) armed mode. c) engaged mode. d) caution. Answer ; b) armed mode. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0073. 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 ; a) magenta. b) red. c) amber. d) yellow. Answer ; b) red. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0074. According to CS 25 , 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 ; a) 1 , 2. b) 1 , 2 , 3 , 4. c) 1 , 3. d) 2 , 4. Answer ; b) 1 , 2 , 3 , 4. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0075. According to CS 25 , section 3 concerning the Electronic Display Systems , the white/cyan colours are associated with the following indication ; a) warning. b) engaged mode. c) caution. d) armed mode. Answer ; d) armed mode. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0076. According to CS25 , the definition of the control wheel steering mode ( CWS ) is ; “Where the pilot has the ability to make inputs to the ; a) flight director by movement of the normal control wheel”. b) automatic pilot by movement of the normal control wheel”. c) flight director by movement of the alternate control wheel”. d) automatic pilot by movement of the alternate control wheel”. Answer ; b) automatic pilot by movement of the normal control wheel”. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- Ateş Murat Üstünbıçak , ATPL 11 Instrumentation 0077. 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. a) 3 , 2 , 1. b) 2 , 1 , 3. c) 1 , 2 , 3. d) 3 , 1 , 2. Answer ; d) 3 , 1 , 2. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0078. 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 ; a) decreases abruptly towards zero. b) increases abruptly towards VNE. c) increases steadily. d) decreases steadily. Answer ; d) decreases steadily. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0079. ( For this question use annex 022-11232A ) Annex 022-11232A 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 ; a) increase the flight attitude and bank your aeroplane to the right until the command bars recentre on the symbolic aeroplane. b) increase the flight attitude and bank your airplane to the left until the command bars recentre on the symbolic aeroplane. c) decrease the flight attitude and bank your airplane to the right until the command bars recentre on the symbolic aeroplane. d) decrease the flight attitude and bank your airplane to the left until the command bars recentre on the symbolic aeroplane. Answer ; b) increase the flight attitude and bank your airplane to the left until the command bars recentre on the symbolic aeroplane. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- Ateş Murat Üstünbıçak , ATPL 12 Instrumentation 0080. ( For this question use annex 022-10217A ) Annex 022-10217A 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 ; a) increase the flight attitude until the command bars recentre on the symbolic airplane. b) increase the flight attitude until the command bars recentre on the horizon. c) decrease the flight attitude until the command bars recentre on the symbolic airplane. d) decrease the flight attitude until the command bars recentre on the horizon. Answer ; a) increase the flight attitude until the command bars recentre on the symbolic airplane. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0081. After the initial 90 degrees of a turn at constant pitch and bank , a classic artificial horizon indicates ; a) too much nose-up and too much bank. b) pitch and bank correct. c) too much nose-up and too little bank. d) too much nose-up and bank correct. Answer ; c) too much nose-up and too little bank. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0082. Alarms are standardised and follow a code of colours. Those requiring action but not immediately , are signalled by the colour ; a) flashing red. b) red. c) green. d) amber. Answer ; d) amber. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- Ateş Murat Üstünbıçak , ATPL 13 Instrumentation 0083. 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 ; a) 1 , 2 , 3 and 6. b) 3 , 4 and 5. c) 1 , 2 and 6. d) 1 , 3 , 4 and 5. Answer ; b) 3 , 4 and 5. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0084. Among the following functions of an autopilot , those related to the airplane stabilization are ; 1. pitch attitude holding. 2. IAS or Mach number holding. 3. horizontal wing holding. 4. VOR radial holding. The combination regrouping all the correct statements is ; a) 2 , 4. b) 1 , 3. c) 1 , 2 , 3 , 4. d) 1 , 2 , 3. Answer ; b) 1 , 3. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0085. Among the following functions of an autopilot , those related to the airplane stabilization are ; 1. pitch attitude holding. 2. horizontal wing holding. 3. displayed heading or inertial track holding. 4. indicated airspeed or Mach number holding. 5. yaw damping. 6. VOR axis holding. The combination regrouping all the correct statements is ; a) 3 , 4 , 5 , 6. b) 1 , 2. c) 2 , 4 , 5. d) 1 , 2 , 5. Answer ; b) 1 , 2. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0086. 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 ; a) 10.5°/hour to the right. b) 15°/hour to the right. Drift due to Earth rate will make the gyro rotate cloclwise c) 7.5°/hour to the left. ( to the right ) in the northern hemisphere at a rate of ; d) 7.5°/hour to the right. 15 x sin °/lat = 15 x sin 45 = 10.5°/hr Answer ; a) 10.5°/hour to the right. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0087. 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 ; a) 2 , 3. b) 1 , 3. c) 1 , 2 , 3. d) 1 , 2. Answer ; c) 1 , 2 , 3. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- Ateş Murat Üstünbıçak , ATPL 14 Instrumentation 0088. An aeroplane is cruising at FL 220. The auto-throttle maintains a constant CAS. If the OAT increases , the Mach number ; a) decreases. b) decreases if OAT is lower than standard temperature , increases in the opposite case. c) remains constant. d) increases. Answer ; c) remains constant. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0089. An aeroplane is flying at FL300 with a TAS of 470 kt in standard conditions. The Mach number is ; a) 0.83 b) 0.80 Öncelikle FL300’de ISA’ya göre olması gereken sıcaklık bulunur ; ( 2 x 30 ) – 15 = –45°C. c) 0.82 Đkinci adım olarak DR kompitüründe MACH NO INDEX oku – 45’e hizalanır. Dış skalada d) 0.53 yer alan 47 değerinin ( 470 kt TAS ) karşısında , iç skalada yaklaşık olarak 0.80 Mach değeri Answer ; okunur. b) 0.80 ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0090. An aeroplane is in steady climb. The auto-throttle maintains a constant calibrated airspeed. If the total temperature remains constant , the Mach number ; a) increases. b) decreases if the static temperature is lower than the standard temperature. c) decreases. d) remains constant. Answer ; a) increases. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0091. An aeroplane is in steady climb. The auto-throttle maintains a constant Mach number. If the total temperature remains constant , the calibrated airspeed ; a) remains constant. b) decreases if the static temperature is lower than the standard temperature , increases if higher. c) increases. d) decreases. Answer ; d) decreases. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0092. 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 ; a) decreases. b) remains constant. c) increases. d) increases if the outside temperature is higher than the standard temperature , decreases if lower. Answer ; b) remains constant. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0093. An aeroplane is in steady cruise at flight level 270. The auto-throttle maintains a constant calibrated airspeed. If the static air temperature increases , the Mach number ; a) decreases. b) increases. c) remains constant. d) decreases if the outside temperature is higher than the standard temperature , increases if lower. Answer ; c) remains constant. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0094. An aeroplane is in steady cruise at flight level 290. The auto-throttle maintains a constant Mach number. If the total temperature decreases , the calibrated airspeed ; a) decreases. b) decreases if the outside temperature is lower than the standard temperature , increases if higher. c) remains constant. d) increases. Answer ; c) remains constant. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- Ateş Murat Üstünbıçak , ATPL 15 Instrumentation 0095. An aeroplane is in steady descent. The auto-throttle maintains a constant calibrated airspeed. If the total temperature remains constant , the Mach number ; a) decreases. b) increases. c) increases if the static temperature is lower than the standard temperature , decreases if higher. d) remains constant. Answer ; a) decreases. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0096. 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 ; a) 2 , 3 and 4. b) 3 , 4 and 5. c) 2 and 5. d) 1 and 2. Answer ; b) 3 , 4 and 5. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0097. 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. a) turn indicator. b) fluxgate compass. c) directional gyro. d) gyromagnetic compass. Answer ; a) turn indicator. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0098. 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) a directional gyro. b) an artificial horizon. c) a turn indicator. d) a fluxgate compass. Answer ; a) a directional gyro. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0099. 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 ; a) deviates to the right and will be centred as soon as you roll the aircraft to the bank angle calculated by the flight director. b) deviates to its right stop as long as the aeroplane is more than 10° off the new selected heading. c) deviates to the right and remains in that position until the aircraft has reached heading 360°. d) disappears , the new heading selection has deactivated the HDG mode. Answer ; a) deviates to the right and will be centred as soon as you roll the aircraft to the bank angle calculated by the flight director. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0100. An aircraft is descending from FL 390 to ground level at maximum speed. The limits in speed will be ; a) the VMO only. b) initially the VMO , then the MMO below a certain flight level. c) the MMO only. d) initially the MMO , then the VMO below a certain flight level. Answer ; d) initially the MMO , then the VMO below a certain flight level. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- Ateş Murat Üstünbıçak , ATPL 16 Instrumentation 0101. An aircraft is equipped with an autopilot and an auto-throttle. When the altitude hold mode ( ALT HOLD ) is active ; a) the indicated airspeed ( IAS ) is maintained constant by the autopilot by means of elevator. b) the indicated airspeed ( IAS ) is maintained constant by the auto-throttle system. c) the true airspeed ( TAS ) is maintained constant by the auto-throttle system. d) the true airspeed ( TAS ) is maintained constant by the autopilot by means of elevator. Answer ; b) the indicated airspeed ( IAS ) is maintained constant by the auto-throttle system. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0102. 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 ; a) the greater the speed , the lower the error between the two altimeters. b) the greater the speed , the greater the error between the two altimeters. c) the lower the speed , the greater the error between the two altimeters. d) the error between the two altimeters does not depend on the speed. Answer ; b) the greater the speed , the greater the error between the two altimeters. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0103. 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 ; a) Standard + 20°C. b) Standard. c) Standard + 30°C. d) Standard + 10°C. Answer ; d) Standard + 10°C. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0104. An aircraft is in a steady left turn , with too much left rudder ( skidding turn ). The yaw damper system ; a) acts only in case of slipping turns ( turn with too much bank ). b) acts on the left rudder pedal to provide a balanced turn. c) acts on the right rudder pedal to provide a balanced turn. d) is not designed to provide a balanced turn. Answer ; d) is not designed to provide a balanced turn. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0105. An aircraft is in a steady right turn , with not enough right rudder ( slipping turn ). The yaw damper system ; a) acts on the left rudder pedal to provide a balanced turn. b) acts only in case of skidding turns ( turn with not enough bank ). c) acts on the right rudder pedal to provide a balanced turn. d) is not designed to provide a balanced turn. Answer ; d) is not designed to provide a balanced turn. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0106. An aircraft is turning right , with too much bank ( slipping turn ). The yaw damper system ; a) is not designated to provide a balanced turn. b) acts only in case of skidding turns ( turn with not enough bank ). c) acts on the right rudder pedal to provide a balanced turn. d) ats on the left rudder pedal to provide a balanced turn. Answer ; a) is not designated to provide a balanced turn. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0107. 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) a value above 045° in the northern hemisphere. b) a value above 045° in the southern hemisphere. c) a value below 045°. d) 045°. Answer ; c) a value below 045°. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- Ateş Murat Üstünbıçak , ATPL 17 Instrumentation 0108. An airplane is cruising at FL 190. The auto-throttle maintains a constant CAS. If the OAT decreases , the Mach number ; a) decreases if OAT is lower than standard temperature , increases in the opposite case. b) increases. c) remains constant. d) decreases. Answer ; c) remains constant. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0109. An airplane is cruising at FL 220. The auto-throttle maintains a constant CAS. If the OAT decreases , the Mach number ; a) decreases. b) remains constant. c) increases. d) decreases if OAT is lower than standard temperature , increases in the opposite case. Answer ; b) remains constant. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0110. An airplane is flying at FL140 with a CAS of 260 kt in standard conditions. The Mach number is ; a) 0.43 b) 0.41 c) 0.53 d) 0.51 Answer ; d) 0.51 ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0111. An airplane is in steady cruise at flight level 290. The auto-throttle maintains a constant Mach number. If the total temperature decreases , the calibrated airspeed ; a) decreases. b) remains constant. c) decreases if the outside temperature is lower than the standard temperature , increases if higher. d) increases. Answer ; b) remains constant. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0112. 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 ; a) increases. b) increases if the static temperature is higher than the standard temperature , decreases if lower. c) remains constant. d) decreases. Answer ; c) remains constant. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0113. An airspeed indicator displays ; a) TAS. b) CAS. c) IAS. d) EAS. Answer ; c) IAS. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0114. An airspeed indicator includes a capsule , inside this capsule is ; a) a very low residual pressure and outside is static pressure. b) static pressure and outside is dynamic pressure. c) total pressure and outside is static pressure. d) dynamic pressure and outside is static pressure. Answer ; c) total pressure and outside is static pressure. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0115. An altimeter contains one or more aneroid capsules. Inside these capsule is ; a) static pressure and outside a very low residual pressure. b) static pressure and outside is dynamic pressure. c) a very low residual pressure outside is static pressure. d) dynamic pressure and outside is static pressure. Answer ; c) a very low residual pressure outside is static pressure. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- Ateş Murat Üstünbıçak , ATPL 18 Instrumentation 0116. 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 ; a) 1 , 3 , 4. b) 2 , 4 , 5. c) 1 , 2 , 3 , 4 , 5. d) 1 , 3. Answer ; d) 1 , 3. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0117. 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 ; a) 2 , 3. b) 1 , 4. c) 1 , 3. d) 2 , 4. Answer ; a) 2 , 3. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0118. 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 ; a) 1 , 2 , 3. b) 2 , 3. c) 1 , 2. d) 1 , 3. Answer ; b) 2 , 3. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0119. An automatic ILS approach can be flown only ; a) within a range of levels of turbulence and no limit for crosswinds. b) within a range of crosswinds and levels of turbulence. c) without limits for crosswind or turbulence. d) within a range of crosswinds and no limit for turbulence. Answer ; b) within a range of crosswinds and levels of turbulence. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0120. 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....” ; a) “OPERATIONAL” b) “PASSIVE” c) “SAFE” d) “REDUNDANT” Answer ; b) “PASSIVE” ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0121. An autopilot capable of holding at least altitude and heading mode is compulsory ; a) on multi-pilot airplanes. b) for IFR or night flights with only one pilot. c) on airplanes over 5.7 t. d) for VFR and IFR flights with only one pilot. Answer ; b) for IFR or night flights with only one pilot. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- Ateş Murat Üstünbıçak , ATPL 19 Instrumentation 0122. An autopilot system ; a) must provide at least aircraft guidance functions. b) may provide automatic take off functions. c) must provide at least aircraft stabilisation functions. d) must provide automatic take off functions. Answer ; c) must provide at least aircraft stabilisation functions. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0123. An EFIS includes the following components ; a) FMS , symbol generator , display unit(s). b) ADC , inertial navigation computer , display unit(s). c) symbol generator , display unit(s) , control panel. d) display unit(s) only. Answer ; c) symbol generator , display unit(s) , control panel. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0124. An inertial navigation system ; a) can only operate when interfacing with the radionavigation equipments. b) can only operate when communicating with ground installations. c) can operate as stand alone equipment without any interface with other navigation equipments. d) can only operate when interfacing with the GPS equipment. Answer ; c) can operate as stand alone equipment without any interface with other navigation equipments. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0125. An inertial Navigation System ( INS ) is ; a) a radio navigation system. b) a self contained system which operates without signals from the ground. c) a system which operates on the Doppler principle. d) a hyperbolic navigation system. Answer ; b) a self contained system which operates without signals from the ground. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0126. An inertial reference and navigation system is a “strapdown” system when ; a) gyros and accelerometers are mounted on a stabilised platform in the aircraft. b) gyros and accelerometers need satellite information input to obtain a vertical reference. c) the gyroscopes and accelerometers are part of the unit’s fixture to the aircraft structure. d) only the gyros , and not the accelerometers , are part of the unit’s fixture to the aircraft structure. Answer ; c) the gyroscopes and accelerometers are part of the unit’s fixture to the aircraft structure. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0127. An outer loop Automatic Flight Control System ( AFCS ) , is a system which ; a) contains a parallel actuator which provides control through 100% of the control range and moves the control inputs only. b) controls the aircraft about the lateral axis only ( PITCH ). c) contains a parallel actuator which provides control through 100% of the control range and moves both the control inputs and the cockpit control stick. d) controls the aircraft about the longitudinal axis only ( ROLL ). Answer ; c) contains a parallel actuator which provides control through 100% of the control range and moves both the control inputs and the cockpit control stick. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0128. Any vibration displayed on an engine vibration monitoring system for a turbojet ; a) is presented without any amplification or filtering. b) varies inversely as the square of the engine speed. c) indicates rotor imbalance. d) is directly proportional to engine speed. Answer ; c) indicates rotor imbalance. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- Ateş Murat Üstünbıçak , ATPL 20 Instrumentation 0129. As a result of the failure of the central air data computer ( CADC ) , the inertial navigation system ( INS ) will no longer provide information about ; a) the ground speed. b) the time ( TIME ) at the next waypoint ( WPT ). c) the wind direction and speed. d) the drift. Answer ; c) the wind direction and speed. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0130. Assuming that the CAS remains constant , if the total pressure probe is blocked , the IAS ; a) remains constant during all the phases of the flight. b) remains constant during level flight , increases during a climb and decreases during a descent. c) increases during level flight , remains constant during a climb and a descent. d) remains constant during level flight , decreases during a climb and increases during a descent. Answer ; b) remains constant during level flight , increases during a climb and decreases during a descent. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0131. Assuming the flight level and Mach number remain constant , when the OAT decreases ; a) IAS decreases and TAS increases. b) IAS increases and TAS decreases. c) IAS and TAS increase. d) IAS remains constant and TAS decreases. Answer ; d) IAS remains constant and TAS decreases. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0132. Assuming the flight level and Mach number remain constant , when the OAT increases ; a) IAS increases and TAS decreases. b) IAS decreases and TAS increases. c) IAS remains constant and TAS increases. d) IAS and TAS decrease. Answer ; c) IAS remains constant and TAS increases. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0133. At a given altitude , the hysteresis error of an altimeter varies substantially with the ; a) aircraft attitude. b) time passed at this altitude. c) static temperature. d) mach number of the aircraft. Answer ; b) time passed at this altitude. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0134. At a low bank angle , the measurement of rate-of-turn actually consists in measuring the ; a) roll rate of the aircraft. b) yaw rate of the aircraft. c) pitch rate of the aircraft. d) bank of the aircraft. Answer ; b) yaw rate of the aircraft. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0135. At flight level and Mach number constant , if OAT decreases the CAS ; a) remains constant. b) decreases. c) decreases if OAT is lower than standard temperature , increases in the opposite case. d) increases. Answer ; a) remains constant. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0136. At flight level and Mach number constant , if OAT increases the CAS ; a) decreases if OAT is lower than standard temperature , increases in the opposite case. b) remains constant. c) increases. d) decreases. Answer ; b) remains constant. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- Ateş Murat Üstünbıçak , ATPL 21 Instrumentation 0137. Automatic Flight Control System ( AFCS ) parallel actuator position is ; a) passed to the pilot via control stick position. b) displayed in the cockpit as a function of input and output signals. c) displayed to the pilot by movement on the ADI only. d) not displayed in the cockpit due to short duration of operation. Answer ; a) passed to the pilot via control stick position. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0138. Automatic Flight Control System ( AFCS ) series actuator is ; a) passed to the pilot via control stick position. b) displayed in the cockpit as a function of input and output signals. c) displayed to the pilot by movement on the ADI/EADI. d) not displayed in the cockpit due to short duration of operation. Answer ; d) not displayed in the cockpit due to short duration of operation. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0139. Below the tropopause in standard conditions , when descending at a constant Mach number ; a) the difference between surrounding condition and ISA must be known to deduce the TAS variation. b) TAS decreases. c) TAS remains constant. d) TAS increases. Answer ; d) TAS increases. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0140. Below the tropopause in standard conditions , when climbing at a constant Mach number ; a) the difference between surrounding condition and ISA must be known to deduce the TAS variation. b) TAS remains constant. c) TAS increases. d) TAS decreases. Answer ; d) TAS decreases. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0141. Below the tropopause , when descending at constant CAS ; a) Mach number increases and the velocity of sound decreases. b) Mach number decreases and the velocity of sound increases. c) Mach number and the velocity of sound decrease. d) Mach number and the velocity of sound increase. Answer ; b) Mach number decreases and the velocity of sound increases. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0142. Below the tropopause , with no temperature inversion , when climbing at constant Mach number ; a) the difference between surrounding conditions and ISA must be known to deduce the TAS variation. b) TAS remains constant. c) TAS decreases. d) TAS increases. Answer ; c) TAS decreases. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0143. Below the tropopause , with no temperature inversion , when descending at constant Mach number ; a) the difference between surrounding conditions and ISA must be known to deduce the TAS variation. b) TAS decreases. c) TAS increases. d) TAS remains constant. Answer ; c) TAS increases. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- 0144. Calibrated Air Speed ( CAS ) is ; a) Equivalent Air Speed ( EAS ) corrected for density error. b) Equivalent Air Speed ( EAS ) corrected for compressibility and density errors. c) Indicated Air Speed ( IAS ) corrected for compressibility error. d) Indicated Air Speed ( IAS ) corrected for position and instrument errors. Answer ; d) Indicated Air Speed ( IAS ) corrected for position and instrument errors. ----------------------------------------------------------------------------------------------------------------------------------------------------------------- Ateş Murat Üstünbıçak , ATPL 22 Instrumentation 0145. Calibrated Air Speed ( CAS ) is obtained from Indicated Air Speed ( IAS ) by correcting for the ; a) position and density errors.