WorksheetsINSTRUMENT 3
Total questions: 51
Worksheet time: 26mins
A transport airplane is compelled to carry on board a Ground Proximity Warning
System (GPWS). This system will warn the crew in case of: 1 - keeping the altitude at a
lower level than the one shown in the flight plan entered in the FMS. 2 - dangerous ground
proximity. 3 - loss of altitude during take-off or missed approach. 4 - wrong landing
configuration. 5 - descent
1, 3, 4
2
2, 3, 4, 5
2, 5
A "TCAS II" (Traffic Collision Avoidance System) provides:
the intruder relative position and possibly an indication of a collision avoidance manoeuvre within both the vertical and horizontal planes.
a simple intruding airplane proximity warning.
the intruder relative position and possibly an indication of a collision avoidance manoeuvre within the vertical plane only.
the intruder relative position and possibly an indication of a collision avoidance manoeuvre within the horizontal plane only.
In some configurations, modern aircraft do not respect the regulatory margins between stall and natural buffet. The warning system supplies the corresponding alarm. The required margin related to the stall speed is:
7%
5%
10%
3%
The main input data to the Stall Warning Annunciator System are: 1- Mach Meter indication 2- Angle of Attack 3- Indicate Airspeed (IAS) 4- Aircraft configuration (Flaps/Slats). The combination regrouping all the correct statements is:
2,4
2,3
1,4
1,2
The stick shaker calculator receives the following informations: 1- mass of the airplane 2- angle of attack 3- wing flap deflection 4- position of the landing gear 5- total air temperature 6- pressure altitude. The combination regrouping all the correct statements is:
a) 2, 3, 5
b) 2, 3
c) 1, 2, 3, 4
d) 1, 2, 3, 4, 5, 6
The angle of attack transmitter provides an electric signal varying with: 1- the angular position of a wind vane 2- the deviation between the airplane flight attitude and the path calculated by the inertial unit 3- a probe differential pressure depending on the variation of the angle of attack The combination regrouping all the correct statements is:
1, 2 and 3.
1 and 3.
1.
2 and 3.
The angle of attack transmitters placed laterally on the forward part of the fuselage supply an electrical signal indicating: 1- the angular position of a wind vane 2- a differential pressure in a probe, depending on the variation of the angle of attack 3- a differential pressure in a probe, depending on the variation of the speed. The combination regrouping all the correct statements is:
2, 3.
1, 2, 3.
1, 2.
1, 3.
The oncoming stall of a large transport airplane appears in the form of:
control stick vibrations simulating natural buffeting.
an orange light on the warning display.
a natural buffeting which occurs prior to the simulated buffeting.
a bell type warning.
The stall warning system of a large transport airplane includes: 1- an angle of attack sensor 2- a computer 3- a transmitter originating from the anemometer 4- an independent pitot probe 5- a transmitter of the flap/slat position indicating system. The combination regrouping all the correct statements is:
1, 2, 4.
1, 2, 5.
1, 4.
1, 2, 4, 5.
In accordance with (ICAO) Annex 6 part I, the flight data recorder is to be located in the aircraft:
as near to the landing gear as practicable
as far forward as practicable
as far to the rear as practicable
at the right or left wing tip
Flight recorder duration must be such that flight data, cockpit voice and sound warnings may respectively be recorded during at least:
48 hours for flight data, 60 minutes for cockpit voices and warnings horns
24 hours for flight data, 60 minutes for cockpit voices and warnings horns
20 hours for flight data, 15 minutes for cockpit voices and warnings horns
25 hours for flight data, 30 minutes for cockpit voices and warnings horns.
The flight data recorder must start data recording automatically:
before the airplane is able to move by under its own power.
when taking-off.
when the landing gear is retracted.
when lining up.
The flight data recorder must automatically stop data recording when the:
main gear shock strut compresses when touching the runway.
airplane cannot any longer move by its own power.
landing gear is extended and locked.
airplane clears the runway.
Except for airplanes under 5,7 t airworthiness certificate of which is subsequent to 31 March 1998, a flight data recording system must be able to store the recorded data for a minimum of the last:
25 hours.
10 hours.
30 minutes.
60 minutes.
The CVR (Cockpit Voice Recorder) includes: 1. a microphone 2. a recorder in compliance with the shock and fire resistance standards 3. an independent battery 4. a flight data recorder. The combination regrouping all the correct statements is:
1, 4
1, 2
1, 2, 3, 4
2, 4
A cockpit voice recorder (CVR) will record: 1- the information exchanged by the cabin crew 2- the conversations between the crew members and voice communications transmitted from or received on the flight deck by radio 3- the announcements made via the public address even if it has not been selected 4- the conversations and alarms audible in the cockpit 5- the captain conversations only. The combination re-grouping all the correct statements is:
1, 5
3, 4
1, 2
2, 4
The voice recorder records on four different channels the following information: 1- aural warnings 2- radio communications 3- conversations between the crew members through the cockpit interphone 4- announcements to the passengers. The combination regrouping all the correct statements is:
1, 3
1, 2, 3, 4
1, 4
1, 2, 3
The flight data recorders must preserve the conversation and aural warnings of the last:
25 hours of operation
30 minutes of operation
flight
48 hours of operation
If a manifold pressure gauge consistently registers atmospheric pressure, the cause is probably:
ice in induction system.
too high float level.
fuel of too low volatility.
leak in pressure gauge line.
The pressure probe used to measure the pressure of a low pressure fuel pump is:
a) a Bourdon tube.
b) a bellows sensor.
c) an aneroid capsule.
d) a differential capsule.
The probe used to measure the air intake pressure of a gas turbine engine powerplant is:
an aneroid capsule.
a differential capsule.
a Bourdon tube.
a bellows sensor.
Among the following engine instruments, the one operating with an aneroid pressure diaphragm is the:
oil pressure gauge.
manifold pressure gauge.
fuel pressure gauge.
oil thermometer.
The manifold pressure gauge measures
absolute pressure
differential pressure
gauge pressure
relative pressure
A thermocouple type thermometer consists of:
two metal conductors of the same type connected at two points.
two metal conductors of different type connected at one point.
a Wheatstone bridge connected to a voltage indicator.
a single-wire metal winding.
The yellow sector of the temperature gauge corresponds to:
a frequent operating range.
a normal operating range.
an exceptional operating range.
a forbidden operating range.
The total air temperature (TAT) is always :
lower than Static Air Temperature (SAT) depending on the Calibrated Air Speed (CAS).
higher than Static Air Temperature (SAT) depending on the Calibrated Air Speed (CAS).
higher than Static Air Temperature (SAT) depending on the altitude.
lower than Static Air Temperature (SAT) depending on the altitude
The measurement of the turbine temperature or of the EGT (Exhaust Gas Temperature) is carried out at the :
high pressure chamber intake.
combustion chamber outlet.
combustion chamber intake.
high pressure turbine outlet.
The airplane outside air temperature "probe" measures the:
"total" air temperature minus compressibility effects in order to obtain the static temperature.
"static" air temperature minus kinetic heating effects in order to obtain the total temperature.
"total" air temperature minus kinetic heating effects in order to obtain the static temperature.
"static" air temperature minus compressibility effects in order to obtain the total temperature.
The main advantage of a ratiometer-type temperature indicator is that it:
can operate without an electrical power supply.
is simple.
carries out an independent measurement of the supply voltage.
is very accurate.
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 junction is maintained constant.
cold junction is maintained constant.
cold junction is maintained at 15 °C.
hot junction is maintained at 15 °C.
The measurement of exhaust gas temperature (EGT) is normally based upon the principle of:
voltage generation in a thermocouple
expansion of a liquid in a capillary
the tension in a helical bimetallic spring
expansion of a solid
The disadvantage of an electronic rpm indicator is the:
necessity of providing a power supply source.
generation of spurious signals at the commutator.
influence of temperature on the indication.
high influence of line resistance on the indication.
The signal supplied by a transmitter fitted with a 3-phase AC generator, connected to RPM indicator, is:
an AC voltage varying with the RPM; the indicator rectifies the signal via a diode bridge and is provided with a voltmeter
a DC voltage varying with the RPM; the indicator is a plain voltmeter with a rev/min. scale
an AC voltage, the frequency of which varies with the RPM; the indicator converts the signal into square pulses which are then counted
a three-phase voltage, the frequency of which varies with the RPM; the indicator is provided with a motor which drives a magnetic tachometer
The signal supplied by a transmitter fitted with a magnetic sensor, connected to an RPM indicator is:
a) a three-phase voltage frequency varies with the RPM; the indicator is provided with a motor which drives a magnetic tachometer
b) an AC voltage, the frequency of which varies with the RPM; the indicator converts the signal into square pulses which are then counted
c) a DC voltage varying with the RPM; the indicator is a simple voltmeter with a rev/min. scale
d) an AC voltage varying with the RPM; the indicator rectifies the signal via a diode bridge and is provided with a voltmeter
The red pointer which is normally on the red line on the EGT (Exhaust Gas Temperature) indicators:
shows the limit value not to be exceeded.
moves when the corresponding value is exceeded and remains positioned at the maximum value that has been reached.
allows the display of the parameter value to be adopted during take-off.
shows the vibration level of the engine under consideration.
The advantages of single-phase A.C. generator tachometer are: 1- the suppression of spurious signals due to a D.C. generator commutator 2- the importance of line resistance on the information value 3- the independence of the information in relation to the airborne electrical power supply 4- the ease of transmission of the information. The combination representing all the correct statements is:
a) 2, 4.
b) 1, 2, 3, 4.
c) 2, 3, 4.
d) 1, 3.
When compared with the volumetric fuel flowmeter, the mass fuel flowmeter takes into account the fuel:
temperature.
density.
pressure.
dielectric constant.
A paddle-wheel placed in a the fuel circuit of a gas turbine engine initially measures:
mass flow by a tally of the impulses
volumetric flow by a tally of the impulses
volumetric flow by measure of a voltage proportional to the rotational speed
mass flow by measure of a voltage proportional to the rotational speed
The principle of capacity gauges is based on the:
capacitance variation by the volume measurement carried out on the sensor.
current variation in the Wheatstone bridge.
capacitance variation of a given capacitor with the type of dielectric.
flow rate and torque variation occurring in a supply line.
The disadvantages of an "electric" fuel (float) gauge are: 1- the design is complex 2- the indications are influenced by the airplane attitude variations 3- the indications are influenced by the accelerations 4- the indications are influenced by temperature variations 5- that an alternative current supply is necessary. The combination regrouping all the correct is:
a) 2, 3, 4, 5
b) 1, 2, 3, 4
c) 2, 3, 4
d) 1
The basic principle used for measuring a quantity of fuel in a transport airplane equipped with "capacitor" gauges is that the:
internal resistance of a capacity depends on the nature of the dielectric in which it is immersed.
capacity of a capacitor depends on the nature of the dielectric in which it is immersed.
capacity of a capacitor depends on the distance between its plates.
electromotive force of a capacity depends on the nature of the dielectric in which it is immersed.
The gauge indicating the quantity of fuel measured by a capacity gauging system can be graduated directly in weight units because the dielectric constant of fuel is:
twice that of air and varies directly with density.
the same as that of air and varies directly with density.
twice that of air and varies inversely with density.
the same as that of air and varies inversely with density.
The quantity of fuel in the tanks is measured by capacitor type contents gauges. The working principle of these sensors is to measure the:
charge of condensers
di-electric resistivity of the fuel
height of the fuel
volume of the fuel
Torque can be determined by measuring the:
oil pressure at the fixed crown of an epicycloidal reducer of the main engine gearbox.
phase difference between 2 impulse tachometers attached to a transmission shaft.
frequency of an impulse tachometer attached to a transmission shaft.
quantity of light passing through a rack-wheel attached to a transmission shaft.
The principle of detection of a vibration monitoring system is based on the use of:
2 accelerometers.
2 high and low frequency amplifiers.
2 high and low frequency filters.
a frequency converter.
In an engine vibration monitoring system for a turbojet any vibration produced by the engine is:
inversely proportional to engine speed.
amplified and filtered before being fed to the cockpit indicator.
directly proportional to engine speed.
fed directly to the cockpit indicator without amplification or filtering.
A vibration indicator receives a signal from different sensors (accelerometers). It indicates the:
vibration amplitude at a given frequency
acceleration measured by the sensors, expressed in g
vibration frequency expressed in Hz
vibration period expressed in seconds
In a modern airplane equipped with an ECAM (Electronic centralized aircraft monitor), when a failure occurs in a circuit, the centralized flight management system: releases an aural warning, lights up the appropriate push-buttons on the overhead panel, displays the relevant circuit on the system display, processes the failure automatically. The combination re-grouping all the correct statements is:
1, 3, 4.
1, 2, 3.
3, 4.
1, 2.
The signal supplied by a transmitter fitted with a magnetic sensor, connected to an RPM indicator is:
three-phase voltage frequency varies with the RPM; the indicator is provided with a motor which drives a magnetic tachometer
AC voltage, the frequency of which varies with the RPM; the indicator converts the signal into square pulses which are then counted
DC voltage varying with the RPM; the indicator is a simple voltmeter with a rev/min. scale
AC voltage varying with the RPM; the indicator rectifies the signal via a diode bridge and is provided with a voltmeter
The requirement to carry a GPWS (Ground Proximity Warning System) concerns
aeroplanes which are, depending on their age, weight and passenger capacity: 1-
turboprop-powered; 2- piston-powered; 3- jet-powered. The combination regrouping all the
correct statements is:
3
1
1, 2, 3
1, 3
The red pointer which is normally on the red line on the EGT (Exhaust Gas Temperature) indicators:
shows the limit value not to be exceeded.
moves when the corresponding value is exceeded and remains positioned at the maximum value that has been reached.
allows the display of the parameter value to be adopted during take-off.
shows the vibration level of the engine under consideration.
