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ATPL 22 AIRCRAFT GENERAL KNOWLEDGE – INSTRUMENTATION |
| 22.02 MEASUREMENT OF AERODYNAMIC PARAMETERS |
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1
The turn rate indicator uses a gyroscope: 1 - with one degree of freedom. 2 - with two degrees of freedom 3 - the frame of which is supported by two return springs. 4 - the spinning wheel axis of which is parallel to the pitch axis. 5 - the spinning wheel axis of which is parallel to the yawing axis. 6 - the spinning wheel axis of which is horizontal. the combination regrouping all the correct statements is:
01-mar |
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2
An aircraft is flying at a 120 kt true airspeed (vv), in order to achieve a rate 1 turn, the pilot will have to bank the aircraft at an angle of:
18§. |
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3
A stand-by-horizon or emergency attitude indicator:
Contains its own separate gyro |
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4
The altitude select system: selected altitude
Is annunciated by light and/or sound when airplane is approaching |
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5
The correction of the control surface deflection made by the automatic pilot calculator in order to stabilize the longitudinal attitude will be all the more significant as the : 1- difference between the reference attitude and the instantaneous attitude is high. 2- rate of change of the difference between the reference attitude and the instantaneous attitude is high. 3- temperature is low. 4- pressure altitude is high. the combination regrouping all the correct statements is:
1,2. |
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6
The correction of the control surface deflection made by the auto-pilot calculator in order to keep a given altitude will be all the more significant when the : 1- difference between the attitude necessary to keep the given or reference altitude and the instantaneous attitude is high. 2 - variation speed of the difference between the attitude necessary to maintain the altitude and the instantaneous attitude is high. 3 - difference between the altitude of reference and the instantaneous altitude is high. 4 - variation speed of the difference between the reference altitude and the instantaneous altitude is high. the combination regrouping the correct statements is:
1, 2, 3 and 4. |
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7
A gyromagnetic compass or heading reference unit is an assembly which always consists of : 1- a directional gyro 2- a vertical axis gyro 3- an earth"s magnetic field detector 4- an azimuth control 5- a synchronising control the combination of correct statements is :
1,3,5 |
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8
An automatic landing is carried out when the automatic pilot :
And the autothrottle ensure a correct final approach, at least up to ground roll |
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9
A pilot has to carry out a single-pilot ifr flight on a light twin-engined aircraft for cargo transport. the purpose of the automatic pilot is at least to hold the:
Heading and to hold the altitude |
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10
The basis properties of a gyroscope are : 1. the gyro"s weight. 2. the rigidity in space. 3. the inertia. 4. the high rpm. 5. the precession the combination of correct statements is :
2,5 |
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11
The indication of the directional gyro as an on-board instrument are valid only for a short period of time. the causes of this inaccuracy are : 1. the earth"s rotation 2. the longitudinal acceleration 3. the aircraft"s motion over the surface of the earth. 4. the mechanical defects of the gyro 5. the gyro"s weight 6. the gimbal mount of the gyro rings the combination of correct statements is :
1,3,4,6 |
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12
The characteristics of the directional gyro (dg) used in a gyro stabilised compass system are :
Two degrees of freedom, whose horizontal axis corresponding to the reference direction is maintained in the horizontal plane by an automatic erecting system. |
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13
A gravity type erector is used in a vertical gyro device to correct errors on :
An artificial horizon |
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14
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 |
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15
When an aircraft has turned 270 degrees with a constant attitude and bank, the pilot observes the following on a classic artificial horizon :
Too much nose-up and bank too high. |
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16
Among the flight control instruments, the artificial horizon plays an essential part. it uses a gyroscope with : note : in this question, the degrees of freedom of a gyro are determined by the number of gimbal rings it comprises.
Two degrees of freedom, whose axis is oriented and continously maintained to local vertical by an automatic erecting system. |
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17
A laser gyro consists of :
A laser generating two provided with mirrors |
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18
A failed rmi rose is locked on 090§and the adf pointer indicates 225§. the relative bearing to the station is :
135§. |
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19
A slaved directional gyro derives it"s directional signal from :
The flux valve. |
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20
(for this question use annex 022-3880a) 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. |
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21
A turn indicator is built around a gyroscope with:
2 degrees of freedom. |
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22
The white sector of the arc of a temperature gauge corresponds to:
A special operating range. |
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23
The directional gyro axis no longer spins about the local vertical when it is located :
On the equator |
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24
A thermocouple type thermometer consists of:
Two metal conductors of different type connected at one point. |
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25
In order to align a strapdown inertial unit, it is required to insert the local geographical coordinates. this is necessary to:
Position the computing trihedron with reference to earth. |
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26
W hile 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. |
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27
The diagram on annex 022-648a 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 |
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28
The indications on a directional gyroscope or gyrocompass are subject to errors, due to: 1- rotation of earth. 2- aeroplane motion on earth. 3- lateral and transversal aeroplane bank angles. 4- north change. 5- mechanical defects. chose the combination with true statements only:
1,2,3,5. |
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29
The yellow sector of the temperature gauge corresponds to:
An exceptional operating range. |
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30
At a low bank angle, the measurement of rate-of- turn actually consists in measuring the :
Yaw rate of the aircraft |
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31
An airborne instrument, equipped with a gyro with 2 degrees of freedom and a horizontal spin axis is:
A directional gyro |
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32
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 |
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33
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 |
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34
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 |
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35
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 |
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36
On the ground, during a left turn, the turn indicator indicates :
Needle to the left, ball to the right |
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37
The rate-of-turn is the:
Change-of-heading rate |
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38
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. |
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39
In a turn-indicator, the measurement of rate-of- turn consists for :
Low bank angles, in measuring the yaw rate |
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40
In a turn at constant rate, the turn indicator reading is:
Inversely proportional to the aircraft true airspeed |
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41
An airborne instrument, equipped with a gyro with 2 degrees of freedom and a horizontal spin axis is :
A directional gyro |
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42
An airborne instrument, equipped with a gyro with 1 degree of freedom and a horizontal spin axis is a :
Turn indicator |
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43
The vertical reference unit of a three-axis data generator is equipped with a gyro with :
2 degrees of freedom and vertical spin axis |
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44
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 |
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45
On the ground, during a right turn, the turn indicator indicates :
Needle to the right, ball to left |
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46
A landing will be considered to be performed in the semi- automatic mode when: 1- the autopilot maintains the airplane on the ils beam until the decision height is reached then is disengaged automatically. 2- the autothrottle maintains a constant speed until the decision height is reached then is disengaged automatically. 3- the autopilot maintains the airplane on the ils beam until the flare. 4- the autothrottle decreases the thrust when the height is approximately 30 ft. 5- the flare and the ground roll are performed automatically. the combination regrouping all the correct statements is:
1 and 2. |
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47
When using the autopilot, the function of the pitch channel automatic trim is to: 1- cancel the hinge moment of the elevator 2- ease as much as possible the load of the servo-actuator 3- restore to the pilot a correctly trimmed airplane during the autopilot disengagement the combination regrouping all the correct statements is:
1, 2 and 3. |
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48
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. |
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49
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:
1, 2 and 5. |
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50
In order to measure temperature the cylinder head temperature (cht) gauge utilises a :
Thermocouple consisting of two dissimilar metals. |
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51
The interception of a localizer beam by the autopilot takes place :
At a constant heading |
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52
The heading reference unit of a three-axis data generator is equipped with a gyro with:
2 degrees of freedom and horizontal spin axis |
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53
Following 180§stabilized turn with a constant attitude and bank, the artificial horizon indicates :
Too high pitch-up and too low banking |
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54
The gyromagnetic compass torque motor :
Causes the directional gyro unit to precess |
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55
The heading information originating from the gyromagnetic compass flux valve is sent to the:
Error detector. |
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56
The input signal of the amplifier of the gyromagnetic compass resetting device originates from the:
Error detector. |
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57
A rate integrating gyro is a detecting element used in 1. an inertial attitude unit 2. an automatic pilot 3. a stabilizing servo system 4. an inertial navigation system 5. a rate-of-turn indicator the combination of correct statements is :
1,4. |
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58
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. |
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59
The gimbal error of the directional gyro is due to the effect of :
A bank or pitch attitude of the aircraft |
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60
The pendulum type detector system of the directional gyro feeds :
A levelling erection torque motor |
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61
The directional gyro axis spins about the local vertical by 15§/hour :
On the north pole |
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62
Landing shall be considered as having been carried out automatically when the autopilot and the auto- throttle of an aircraft are disengaged by flight crew :
During ground roll. |
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63
Compared with a conventional gyro, a laser gyro :
Has a longer life cycle |
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64
The total air temperature (tat) is always :
Higher than static air temperature (sat) depending on the calibrated air speed (cas). |
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65
Given : m is the mach number ts is the static temperature tt is the total temperature
Ts = tt /(1+0.2. môì) |
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66
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:
Hot maintained constant. |
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67
The main advantage of a ratiometer-type temperature indicator is that it:
Carries out an independent measurement of the supply voltage. |
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68
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. |
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69
When an automatic landing is interrupted by a go-around : 1- the autothrottle reacts immediately upon the pilot action on the to/ga (take- off/go-around) switch in order to recover the maximum thrust 2- the autopilot monitors the climb and the rotation of the airplane 3- the autopilot retracts the landing gear and reduces the flap deflection in order to reduce the drag 4- the pilot performs the climb and the rotation of the airplane 5- the pilot retracts the landing gear and reduces the flap deflection in order to reduce the drag the combination regrouping all the correct statements is:
1, 2 and 5. |
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70
A landing will be considered to be performed in the automatic mode when: 1- the autopilot maintains the airplane on the ils beam until the decision height is reached then is disengaged automatically. 2- the autothrottle maintains a constant speed until the decision height is reached then is disengaged automatically. 3- the autopilot maintains the airplane on the ils beam until the flare. 4- the autothrottle decreases the thrust when the height is approximately 30 ft. 5- the flare and the ground roll are performed automatically. the combination regrouping all the correct statements is:
3, 4 and 5. |
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71
In transport airplanes, the temperatures are generally measured with : 1- resistance thermometers 2- thermocouple thermometers 3- reactance thermometers 4- capacitance thermometers 5- mercury thermometers the combination regrouping all the correct statements is :
1, 2 |
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72
An autopilot capable of holding at least altitude and heading mode is compulsory:
For ifr or night flights with only one pilot. |
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73
From a flight mechanics point of view, the "guidance" functions of a transport airplane autopilot consist in:
Monitoring the movements of the centre of gravity in the three dimensions of space (path). |
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74
The functions of an autopilot (basic modes) consist of :
Stabilizing and monitoring the movement around the airplane centre of gravity. |
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75
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. |
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76
During a category ii automatic approach, the height information is supplied by the :
Radio altimeter. |
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77
An automatic pilot is a system which can ensure the functions of:
Piloting and guidance of an aircraft in both the horizontal and vertical planes. |
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78
When being engaged, and without selecting a particular mode, an automatic pilot enables :
Aeroplane stabilisation with attitude hold or maintaining vertical speed and possibly lines. |
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79
On an autopilot coupled approach, go around mode is engaged:
By the pilot pushing a button located on the throttles. |
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80
The electromotive force of a thermocouple is not modified if one or several intermediate metals are inserted in the circuit provided that:
Contact points are maintained at equal temperature between these different metals. |
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81
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 |
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82
The engagement of an autopilot is not possible when: 1- there is a fault in the electrical power supply 2- the controlled-turn knob is not set to centre-off 3- there is a synchronization fault in the pitch channel 4- there is a fault in the attitude reference unit the combination regrouping all the correct statements is:
1, 2, 3, 4. |
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83
The purpose of the altitude alert system is to generate a visual and aural warning to the pilot when the:
Airplane altitude differs from a selected altitude. |
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84
In automatic landing mode, in case of failure of one of the two autopilots, the system is considered:
Fail passive or without failure effect but with disconnection. |
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85
In automatic landing mode, when the 2 autopilots are used, the system is considered:
Fail survival or without failure effect with function always ensured. |
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86
When only one autopilot is used for climbing, cruising and approach, the system is considered:
Fail soft or with minimized failure effect. |
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87
The measurement of the turbine temperature or of the egt (exhaust gas temperature) is carried out at the :
High pressure turbine outlet. |
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88
The sensors used to measure the exhaust gas temperature on an aircraft equipped with turbojets are:
Thermocouples. |
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89
The autopilot basic modes include, among other things, the following functions : 1- pitch attitude hold 2- pressure altitude hold 3- horizontal wing hold 4- heading hold the combination regrouping all the correct statements is :
1, 3 |
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90
Heading information from the gyromagnetic compass flux gate is transmitted to the :
Error detector. |
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91
The control law of a transport airplane autopilot control channel may be defined relationship between the :
Computer input deviation data and the output control deflection signals. airplane). |
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92
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 |
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93
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 switches over to the heading mode. |
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94
A landing is performed automatically when the autopilot and auto- throttle ensure good performance from the final approach :
During the landing roll and sometimes until the aircraft comes to a complete stop. |
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95
The airplane outside air temperature "probe" measures the :
Total air temperature minus kinetic heating effects in order to obtain the static temperature. |
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96
A semi-automatic landing system disconnects itself automatically:
At approximately 100 ft. |
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97
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 |
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98
An automatic landing system which can keep on operating without deterioration of its performances following the failure of one of the autopilots is called "fail...:
Operational |
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99
During an automatic landing, from a height of about 50 ft the: descent until landing.
Autopilot maintains a vertical speed depending on the radio altimeter height. |
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100
The synchronization of the autopilot control channel system : 1- enables the prevention of jerks during disengagement 2- enables the cancellation of rudder control signals 3- enables the prevention of jerks during engagement 4- functions in the heading, navigation, approach modes the combination regrouping all the correct statements is:
3, 4 |
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101
In a selected axis capture mode, the autopilot gives a bank attitude input : not exceeding a given value.
Proportional to the deviation between the selected heading and the current heading but |
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102
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. |
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103
A thermocouple can be made of:
Two metal conductors of different nature fixed together at two points. |
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104
During an acceleration phase at constant attitude, the resetting principle of the artificial horizon results in the horizon bar indicating a :
Nose-up attitude |
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105
To permit turbine exit temperatures to be measured, gas turbines are equipped with thermometers which work on the following principle:
Thermocouple |
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106
Heading information given by a gyro platform, is given by a gyro at :
2 degrees-of-freedom in the horizontal axis |
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107
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. |
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108
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 average latitude of the flight |
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109
A gravity erector system is used to correct the errors on :
An artificial horizon. |
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110
The static air temperature (sat) is :
An absolute temperature expressed in degrees celsius |
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111
The maximum directional gyro error due to the earth rotation is:
15§/hour |
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112
An autopilot is selected "on" in mode "altitude hold," the pilot alters the barometric pressure set on the sub-scale of his altimeter the: pressure, 1013.25 hpa
Aircraft will remain at the same altitude, the autopilot takes its pressure information from the static source |
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113
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:
01-abr |
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114
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. |
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115
The command functions of an autopilot include, among others, the holding of : 1- vertical speed 2- altitude 3- attitude 4- bank 5- heading the combination which regroups all of the correct statements is :
01/02/2005 |
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116
For an aircraft flying a true track of 360§between the 005§s and 005§n parallels, the precession error of the directional gyro due to apparent drift is equal to:
0§/hour |
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117
When the auto-pilot 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. |