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ATPL 22 AIRCRAFT GENERAL KNOWLEDGE – INSTRUMENTATION |
| 22.01 INSTRUMENT AND INDICATION SYSTEMS |
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1
On a modern aircraft, the flight director modes are displayed on the:
Upper strip of the pfd (primary flight display). |
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2
In case of accidental closing of an aircraft"s left static pressure port (rain, birds), the altimeter:
Overreads the altitude in case of a sideslip to the left and displays the correct information during symmetric flight. |
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3
Considering the maximum operational mach number (mmo) and the maximum operational speed (vmo), the captain of a pressurized aircraft begins his descent from a high flight level. in order to meet his scheduled time of arrival, he decides to use the maximum ground speed at any time of the descent. he will be limited :
Initially by the mmo, then by the vmo below a certain flight level |
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4
Mode "localizer arm" active on flight director means: line
System is armed for localizer approach and coupling will occur upon capturing center |
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5
If an aircraft is equipped with one altimeter which is compensated for position error and another altimeter which is not . and all other factors being equal...
At high speed, the non- compensated altimeter will indicate a higher altitude |
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6
Indication of mach number is obtained from:
Indicated speed and altitude using a speed an altimeter type aneroid |
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7
An air data computer (adc) :
Transforms air data measurements into electric impulses driving servo motors in instruments |
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8
In an air data computer (adc), aeroplane altitude is calculated from:
Measurement of absolute barometric pressure from a static source on the fuselage |
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9
The hysteresis error of an altimeter varies substantially with the:
Time passed at a given altitude. |
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10
In a non-pressurized aircraft, if one or several static pressure ports are damaged, there is an ultimate emergency means for restoring a practically correct static pressure intake :
Breaking the rate-of- climb indicator glass window |
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11
The essential components of a flight director are : 1- a computer 2- an automatic pilot 3- an autothrottle 4- command bars the combination of correct statements is :
1,4 |
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12
Today"s airspeed indicators (calibrated to the saint-venant formula), indicate, in the absence of static (and instrumental) error :
The conventional airspeed (cas) in all cases |
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13
The altimeter consists of one or several aneroid capsules located in a sealed casing. the pressures in the aneroid capsule (i) and casing (ii) are respectively :
(i) vacuum (or a very low pressure) (ii) static pressure |
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14
Sound propagates through the air at a speed which only depends on :
Temperature. |
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15
The aim of the flight director is to provide information to the pilot:
Allowing him to return to a desired path in an optimal way. |
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16
(for this question use annex 022-9768a) an aircraft is under guidance mode following a vor radial. from the adi and hsi information represented in the enclosed annex, it is possible to deduce that the aircraft is :
Experiencing a leftside wind. |
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17
(for this question use annex 022-9771a) the atmospheric pressure at fl 70 in a "standard + 10" atmosphere is:
781.85 hpa. |
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18
All the anemometers are calibrated according to:
St-venant" formula which takes into account the air compressibility. |
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19
The velocity of sound at the sea level in a standard atmosphere is:
661 kt. |
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20
In a standard atmosphere and at the sea level, the calibrated airspeed (cas) is :
Equal to the true airspeed (tas). |
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21
The qnh is by definition the value of the:
Altimeter setting so that the needles of the altimeter indicate altitude of the location for which it is given. |
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22
A vmo-mmo warning device consists of an alarm connected to :
A barometric aneroid capsule subjected to a static pressure and an airspeed sensor subjected to a dynamic pressure. |
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23
When flying from a sector of warm air into one of colder air, the altimeter will :
Overread. |
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24
With a constant weight, irrespective of the airfield altitude, an aircraft always takes off at the same :
Calibrated airspeed. |
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25
During a climb after take-off from a contaminated runway, if the total pressure probe of the airspeed indicator is blocked, the pilot finds that indicated airspeed :
Increases steadily |
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26
The mach number is the:
True airspeed (tas) (eas) divided by the speed of sound |
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27
The principle of the mach indicator is based on the computation of the ratio :
(pt - ps) to ps |
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28
The reading of a mach indicator is independent of :
The outside temperature |
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29
The calibrated airspeed (cas) is obtained by applying to the indicated airspeed (ias) :
An instrument and position/pressure error correction. |
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30
The velocity maximum operating (v.m.o.) is a speed expressed in :
Calibrated airspeed (cas). |
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31
The limits of the white scale of an airspeed indicator are :
Vso for the lower limit and vfe for the upper limit |
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32
The limits of the green scale of an airspeed indicator are :
Vs1 for the lower limit and vno for the upper limit |
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33
The limits of the yellow scale of an airspeed indicator are :
Vno for the lower limit and vne for the upper limit |
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34
During a straight and uniform climb, the pilot maintains a constant calibrated airspeed (cas) :
The mach number increases and the true airspeed (tas) increases. |
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35
With a pitot probe blocked due to ice build up, the aircraft airspeed indicator will indicate in descent a :
Decreasing speed. |
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36
At sea level, on a typical servo altimeter, the tolerance in feet from indicated must not exceed :
+/-60 feet |
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37
After an aircraft has passed through a volcanic cloud which has blocked the total pressure probe inlet of the airspeed indicator, the pilot begins a stabilized descent and finds that the indicated airspeed :
Decreases steadily |
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38
The static pressure error of the static vent on which the altimeter is connected varies substantially with the:
Mach number of the aircraft |
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39
The pressure altitude is the altitude corresponding :
In standard atmosphere, to the pressure ps prevailing at this point |
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40
The response time of a vertical speed detector may be increased by adding a:
Correction based on an accelerometer sensor. |
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41
The density altitude is :
The altitude of the standard atmosphere on which the density is equal to the actual density of the atmosphere |
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42
On board an aircraft the altitude is measured from the:
Pressure altitude |
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43
The altitude indicated on board an aircraft flying in an atmosphere where all the atmosphere layers below the aircraft are cold is :
Lower than the real altitude. |
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44
The purpose of the vibrating device of an altimeter is to:
Reduce the effect of friction in the linkages |
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45
Vle is the maximum :
Flight speed with landing gear down |
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46
Vlo is the maximum :
Speed at which the landing gear can be operated with full safety. |
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47
Vne is the maximum speed :
Which must never be exceeded |
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48
Vno is the maximum speed :
Not to be exceeded except in still air and with caution. |
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49
The vertical speed indicator of an aircraft flying at a true airspeed of 100 kt, in a descent with a slope of 3 degrees, indicates :
- 500 ft/min. |
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50
The advantages provided by an air data computer to indicate the altitude are : 1. position/pressure error correction 2. hysteresis error correction 3. remote data transmission capability 4. capability of operating as a conventional altimeter in the event of a failure the combination of correct statements is :
1,3,4 |
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51
The altitude indicated on board an aircraft flying in an atmosphere where all atmosphere layers below the aircraft are warm is:
Higher than the real altitude. |
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52
For a constant calibrated airspeed (cas) and a level flight, a fall in ambient temperature will result in a:
Lower true airspeed (tas) due to an increase in air density |
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53
When climbing at a constant mach number below the tropopause, in isa conditions, the calibrated airspeed (cas) will:
Decrease |
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54
If the static source to an airspeed indicator (asi) becomes blocked during a descent the instrument will:
Over-read |
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55
If the static source to an altimeter becomes blocked during a climb, the instrument will:
Continue to indicate the reading at which the blockage occured |
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56
The primary factor which makes the servo- assisted altimeter more accurate than the simple pressure altimeter is the use of:
An induction pick-off device |
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57
If the static source of an altimeter becomes blocked during a descent the instrument will:
Continue to display the reading at which the blockage occured |
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58
A leak in the pitot total pressure line of a non- pressurized aircraft to an airspeed indicator would cause it to:
Under-read. |
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59
The pressure measured at the forward facing orifice of a pitot tube is the :
Total pressure. |
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60
The airspeed indicator circuit consists of pressure sensors. the pitot tube directly supplies:
The static pressure |
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61
If the outside temperature at 35 000 feet is -40§c, the local speed of sound is :
596 kt. |
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62
The head up display (hud) is a device allowing the pilot, while still looking outside, to have:
A synthetic view of the instrument procedure. |
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63
Flight director information supplied by an fd computer is presented in the form of command bars on the following instrument:
Adi attitude display indicator. |
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64
The error in altimeter readings caused by the variation of the static pressure near the source is known as:
Position pressure error. |
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65
When descending through an isothermal layer at a constant calibrated airspeed (cas), the true airspeed (tas) will:
Decrease |
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66
Machmeter readings are subject to:
Position pressure error |
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67
At a constant mach number, the calibrated air speed (cas) :
Decreases when the altitude increases |
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68
At a constant calibrated airspeed (cas), the mach number :
Increases when the altitude increases |
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69
The mach number is :
The ratio of the aircraft true airspeed to the sonic velocity at the altitude considered |
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70
The use of the tcas (traffic collision avoidance system) for avoiding an aircraft in flight is now general. tcas uses for its operation :
The replies from the transponders of other aircraft |
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71
Different pressure sensors are used according to the intensity of the pressure measured (low, medium or high) classify the following sensors by order of increasing pressure for which they are suitable : 1- bellows type 2- bourdon tube type 3- aneroid capsule type
3,1,2 |
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72
The airspeed indicator of a twin-engined aircraft comprises different sectors and color marks. the blue line corresponds to the :
Optimum climbing speed with one engine inoperative, or vy |
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73
The airspeed indicator of an aircraft is provided with a moving red and white hatched pointer. this pointer indicates the:
Maximum speed in vmo operation versus altitude |
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74
A pitot blockage of both the ram air input and the drain hole with the static port open causes the airspeed indicator to :
React like an altimeter. |
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75
Vfe is the maximum speed :
With the flaps extended in a given position. |
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76
A pitot tube covered by ice which blocks the ram air inlet will affect the following instrument (s) :
Airspeed indicator only. |
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77
Given : - ts the static temperature (sat) - tt the total temperature (tat) - kr the recovery coefficient - m the mach number the total temperature can be expressed approximately by the formula :
Tt = ts(1+0.2 môì) |
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78
A manifold pressure gauge of a piston engine measures :
Absolute pressure in intake system near the inlet valve. |
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79
If a manifold pressure gauge consistently registers atmospheric pressure, the cause is probably.
Leak in pressure gauge line. |
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80
The "bourdon tube" is used to measure :
Pressure. |
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81
The probe used to measure the air intake pressure of a gas turbine engined powerplant is:
An aneroid capsule. |
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82
The pressure probe used to measure the pressure of a low pressure fuel pump is:
An aneroid capsule. |
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83
(for this question use 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 :
Increase the flight attitude until the command bars recentre on the symbolic airplane. |
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84
The command bars of a flight director are generally represented on an:
Adi (attitude director indicator) |
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85
Alarms are standardised and follow a code of colours. those requiring action but not immediately, are signalled by the colour:
Amber |
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86
An aeroplane is equipped with a flight director (with crosshair trend bars), heading 270§, in hdg mode (heading hold). a new heading, of 360§, is selected the vertical trend bar :
Deviates to the right and will be centred as soon as you roll the aircraft to the bank angle calculated by the flight director. |
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87
The altimeter is fed by :
Static pressure |
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88
The vertical speed indicator (vsi) by :
Static pressure |
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89
Among the following engine instruments, the one operating with an aneroid pressure diaphragm is the :
Manifold pressure gauge. |
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90
In a modern airplane equipped with an ecam (electronic centralized aircraft monitor), when a failure occurs in a circuit, the centralized flight management system: 1- releases an aural warning 2- lights up the appropriate push- buttons on the overhead panel 3- displays the relevant circuit on the system display 4- processes the failure automatically the combination regrouping all the correct statements is:
1, 2, 3. |
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91
The flight director indicates the : distance.
Optimum instantaneous path to reach radial. |
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92
The position of a flight director command bars:
Indicates the manoeuvers to execute, to achieve or maintain a flight situation. |
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93
When the altitude acquisition mode is engaged on a jet transport airplane equipped with autopilot (ap) and auto-throttle (ats) systems the:
Indicated airspeed (ias) is maintained constant by the autopilot by means of elevator. |
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94
A "bourdon tube" is used in:
Pressure sensors |
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95
The operating principle of the vertical speed indicator (vsi) is based on the measurement of the rate of change of:
Static pressure |
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96
(for this question use 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 :
Increase the flight attitude and bank your airplane to the left until the command bars recentre on the symbolic aeroplane. |
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97
For capturing and keeping a preselected magnetic heading, the flight director computer takes into account: 1- track deviation 2- rate of track closure 3- rate of change of track closure 4- wind velocity given by the inertial reference unit the combination regrouping all the correct statements is :
1,2,3 |