Worksheetsinstruments
Total questions: 59
Worksheet time: 30mins
which of the following are typical AP engaged modes during the cruise phase?
Roll : LNAV
Pitch : V/S
Roll : TOGA
Pitch : TOGA
Roll : LNAV
Pitch : VNAV
Roll : LOC
Pitch : G/S
The result of performing the first intergration to the output from the East/West acceleration of an INS when engaged in NAV mode is
Aircraft’s longitude
change in longitude
velocity along the local parallel of latitude
departure
with TCAS II , when a corrective resolution is generated
the IAS must be modified without delay
the heading must be modified without delay
the vertical spped must be modified without delay
no action is required
The measurement of SAT directly is not possible for Aircraft traveling fast because
The airlaw causes too much cooling of the sensing probe
the effects of adiabatic compression and frictional heating
the boundary layer around the aircraft gets very turbulent
most temperature sensors have a low Kr
In an autopilot system, the flight path modes are
1. Pitch attitude hold
2. IAS and Mach number hold
3. Attitude hold
4. Glude slope intercept and track
the combination regrouping all the correct statements is :
3
2,3,4
4
1,2,3,4
The aural alert(s) associated with the mode 2 of the GPWS is (are) :
1. ‘TERRAIN’
2. ‘SINKRATE’
3. ‘TOO LOW TERRAIN’
4. ‘PULL UP’
1,4
3
3,4
2,4
when flying level in the cruise the __ holds altitude and the __ holds the speed
autothrottle , autothrottle
autopilot, autothrottle
autopilot, autopilot
autothrottle, autopilot
the rigidity of a gyro is improved by
increasing the RPM and concentrating the mass on the periphery of the rotor
decreasing the RPM and concentrating the mass on the periphery of the rotor
decreasing the RPM and concentrating the mass at the hub of the rotor
increasing the RPM and concentrating the mass at the hub of the rotor
at high latitude, the magnetic compass becomes unreliable because
the magnetic pole is oscillating
the variation is changing too fast
the magnetic field is too strong
the directive force is too week
which of the following describes magnetic variation?
It is because by the difference in position of the geographical North Pole and the magnetic North Pole
it varies inversely with aircraft’s bank angle
It caused by the inclination of the Earth’s magnetic field lines
It varies proportionally with aircraft’s bank angel
Hard iron magnetism in aircraft
is permanent in nature
changes with aircraft heading
it easily corrected for by degaussing
is the same in all aircraft of the same type
aircraft is heading 225*C , Deviation 4*E, HDG 223*T which of the following is true ?
Variation is 6*W with TN East of CN
Variation is 2*E with MN East of CN
Variation is 6*E with MN East of TN
Variation is 2*W with CN East of MN
when flying from a sector of warm air into one of colder air , the altimeter will
show the actual height above ground
underestimate
overestimate
be just as correct as before
the purpose of auto trim function in autopilot is to
help autopilot compensates for crosswind
trim throttles to obtain smooth engine power variation
control elevator trim tab in order to relieve elevator load
tell the pilot when elevator trimming is required
On the display of a TCAS II , the traffic being the cause of a resolution advisory (RA) is represented by
A red solid square
A white or cyan solid lozenge
An amber solid circle
A white or cyan empty lozenge
when accelerating on a westerly heading in the northern hemisphere, the compass card of a direct reading magnetic compass will turn
clockwise giving an apparent turn towards the South
Anti-clockwise giving an apparent turn towards the South
Clockwise giving an apparent turn towards the North
Anti-clockwise giving an apparent turn towards the North
in case of static blockage, the airspeed indicator
over-reads in climb and under-reads in descent
under-reads in climb and over-reads in descent
under-reads in descent only
over-reads in clb only
a synchroscope is used on aircraft to
automatically synchronise the RPM of each engine
Monitor the vibration of each engine
Allow pilot to set several engines to the same speed
achieve optimum control of on-board voltages
during a heading capture mode , the autopilot gives a bank attitude input
Always proportional to the aircraft indicated airspeed
equal to 30*
proportion to the deviation between the selected heading and the current heading but not exceeding a given value
equal to 20*
a pilot wishes to turn right onto a southerly heading with a rate 1 turn at a latitude of 30*N . Using a direct reading compass and assuming liquid swirl is negligible, to achieve this, he must stop the turn on an approximate compass heading of
200*
210*
160*
150*
The ADC uses the following parameters as input data
Mach number, barometric altitude, CAS
Static pressure, pitot pressure, RAT
Dynamic pressure, static pressure, TAT, EGT
TAS, barometric altitude, SAT
The VSI reads :
the differential pressure between the static pressure and pitot pressure
only the outside static pressure
the differential pressure between the capsule pressure and outside static pressure
the differential pressure between the capsule pressure and case pressure
the automatic synchronisation function of an autopilot control system
1. operates only whenthe autopilot is engaged
2. prevents the aircraft control system from jerking when disengaging the autopilot
3. 2. prevents the aircraft control system from jerking when engaging the autopilot
the combination that regroups all of the correct statements is:
3
1,2
1,2,3
1,3
The operating principal of an electronic torque meter is:
increase in power causes twisting of the torque shaft
increase in power causes expansion of the torque shaft
Axial thrust movement is generated when helical cut gears are use to transfer power from shaft to another
Axial thrust movement is generated when cylindrical cut gears are use to transfer power from shaft to another
The duration of a FMS navigation database loaded before expiring is
3 months
15 days
2 months
28 days
which of the following is/are parameters recorded in the Flight Data Recorder?
pressure altitude
propulsive thrust on each engine
radio navigation information displayed to flight crew
all of the above
the flight director command bars provide the pilot with corrections to apply to
pitch attitude only
pitch and/or roll attitude
pitch and/or roll attitude and yaw
roll attitude only
by intergrating fuel flow with respect to time we can obta
the cross section of the fuel line
the diameter of the fuel line
the volume or mass of fuel consumed
the fuel pressure
the Decision Height (DH) warning light comes on ưhen an aircraft:
Descends below a pre-set barometric altitude
passes over the outer marker
descends below a pre-set radio altitude
passes over the ILS inner marker
the two main sources of information used to calculate turbojet thrust are the :
N1 or EPR
high pressure turbine rotation speed or EPR
N1 or total pressure at the high pressure compressor outlet
N1 or the total pressure at the low pressure turbine outlet
The Mach trim system
compensates for the forward movement of the CP due to shockwave formation
Is operational at low subsonic speeds
compensates for the rearward movement of the CP due to shockwave formation
controls the aircraft in roll
when an aircraft has turned 270* with a constant attitude and bank, the pilot observed the following on a air-driven artificial horizon:
Too much nose up and bank too high
Too much nose up and bank correct
attitude and bank are correct
Too much nose up and bank too low
The auto-throttle enables to hold
1. True airspeed
2. Mach number
3. Indicated airspeed
4. N1 thrust
the combination regrouping all the correct statements is
1,2,4
1,2,3,4
2,3,4
1,2,3
The sensor(s) feeding the EPR indicator is (are) :
temperature probes, one located upstream from the compressor inlet, and another downstream from the turbine outlet
Pressure probes, one located upstream from the compressor inlet, and another downstream from the turbine outlet
tachometer located on the shaft of the N1 compressor
tachometer located on the shaft of the high pressure compressor
the yaw damper system acts on:
the rudder and the ailerons if necessary
the rudder and the speed brakes if necessary
the rudder and the roll trim if necessary
the rudder only
on a modern aircraft, the flight director modes are displayed on the :
acontrol panel of the flight director only
upper strip of the PFD
upper strip of the EICAS
upper strip of the ND
the dashpot assembly in an IVSI is used to alter
Case pressure to reduce lag
Capsule pressure to reduce lag
Case pressure to reduce pressure error
Capsule pressure to reduce pressure error
what is the meaning of number “ 4 “ displayed on a jet engine vibration indicator
4 Hz
It is the relative amplitude vibration
4% or 4 Hz , depending on the aircraft type
4%
If only a single A/P is used to clumb, cruise and approach; following of an inner loop component
It is fail safe and will disengage
It is fail operational and will not disengage
It is fail soft and will not disengage
It is fail passive and will redundancy
The alternate static source of a light non-pressurised aircraft is located in the flight deck. when used:
1. the airspeed indicator tends to under-read
2. the airspeed indicator tends to over-read
3. the altimeter tends to under-read
4. the altimeter tends to over-read
the combination that regroups all of the correct statements is
2,3
1,4
1,3
2,4
regarding a dual FMS architecture, during normal operations
captain’s and first officer’s FMS operate completely separately with no synchronisation
Each has separate inputs, but information is synchronised through a common bus
One FMS is switched off and used only if the other fails
Dual FMS system operates under a Master-Slave arrangement
due to rotation of the Earth, the apparent drift of a vertical axis gyroscopes at a latitude of 30*N is
2*/hr clockwise
7.5*/hr clockwise
15*/hr anti-clockwise
apparent drift is not applicable
the purpose of having a vibrating device within a servo-assisted altimeter is to
Reduce the effect of friction on the linkages
quickly dampen any oscillations
reduce the hysteresis effect
inform the crew of altimeter failure
An autopilot system
must provide automatic landing function
must provide automatic take-off function
must provide at least aircraft guidance function for
must provide at least aircraft stabilisation function
the spin axis of the gyro un an altitude indicator is
tied in two vertical planes
tied in vertical plane
maintained horizontal by gravity
tied to the horizontal plane
If, in the event of a failure, the approach, flare and landing can be completed by the remaining part of the automatic system, such an automatic landing system is considered as
Fail-hard
Fail- soft
Fail - operational
Fail - passive
which is true about the latitude nut?
in the NH, the nut is wound in to precess the gyro anti-clockwise
in the NH, the nut is wound out to precess the gyro anti-clockwise
in the SH, the nut is wound out to precess the gyro anti-clockwise
in the SH, the nut is wound out to precess the gyro clockwise
During a descent at constant IAS below the tropopause in ISA condition
Mach number and TAS decrease
Mach number and TAS increase
Mach number decrease and TAS increases
Mach number increase and TAS decreases
the disadvantage of a float type duel gauge are
1. The design is complex
2. the indications are influenced by the aircraft attitude variations
3. the indications are influenced by the acceleration
4. the indications are influenced by temperature variations
the combination regrouping all the correct statements is :
2,3,4
2,3
1
1,2,3,4
if warning, caution, or advisory lights are installed in the cockpit, they must, unless otherwise approved by the Authority , be red for
Advisory lights
caution lights
warning lights
none of the above
as a result of failure of the central air data computer (CADC) , the inertial navigation system (INS) will no longer provide information about :
the ground speed
the drift
the wind direction and speed
the time to next waypoint
an aeroplane performing emergency descent from FL390 to FL100 at maximum speed. The limit(s) is(are)
Mmo only during all the descent
Initially Mmo, then Vmo below a given flight level
Vmo only during all the descent
Initially Vmo, then Mmo below a given flight level
The radio altimeter supplies data to the following system(s)
1. Altitude alert system
2. TCAS
3. GPWS
4. Automatic landing system
the combination that regroups all the correct statements is
1,4
3,4
2,3,4
3
One of the errors unique to a ring laser gyroscope occurs at low input rotation rates tending towards zero when a phenomenon known as “lock-in” is experienced. What is the name of the technique, affected by means of a piezo-electric motor, that is use to prevent this error ?
zero drop
beam lock
cavity rotation
dither
a slaved directional gyro derives its directional signal from
the flux value
The ADC
A direct reading magnetic compass
the flight director
the radio altimeter
1. operates in the 1,600-1,660 kHz range
2. operates in the 4,200-4,400 kHz range
3. measures frequency difference
4. measures amplitude difference
the combination regrouping all the correct statements is :
2,3
1,3
2,4
1,4
In an IRS
accelerometer and platform are both strapped down
the accelerometer are strapped down but the platform is gyro-stabilised
accelerometer and platform are both gyro-stabilised
the platform is strapped down but the accelerometers are gyro-stabilised
the FWS generates an advisory message if
immediate recognition and corrective or compensatory action by the crew is required
immediate crew awareness is required and subsequent crew action will be required
crew awareness is required and subsequent crew action may be required
crew awareness is required and corrective or compensatory action by the crew is required
the most common system used to monitor turbine EGT is the
bimetallic metal consisting of Brass and Invar
expansion type using mercury
hot and cold junctions consisting of Alumel and Chromel
single junction Mercury Oxide reference electrode
