Instrument Question Bank

8/12/2019 Instrument Question Bank

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FLIGHT INSTRUMENT

001.In a standard atmosphere and at the sea level, the calibrated airspeed (CAS) is:

A) higher than the true airspeed (TAS)

B) independent of the true airspeed (TAS)C)equal to the true airspeed (TAS)

D) lower than the true airspeed (TAS)

002.A pitot tube covered by ice which blocks the ram air inlet will affect the following

instrument(s):

A) vertical speed indicator onlyB)airspeed indicator onlyC) altimeter only

D) airspeed indicator, altimeter and vertical speed indicator

003.A pitot blockage of both the ram air input and the drain hole with the static port open causes

the airspeed indicator to:

A)react like an altimeterB) freeze at zeroC) read a little high

D) read a little low

004.The pressure measured at the forward facing orifice of a pitot tube is the:

A)total pressure

B) static pressureC) dynamic pressure

D) total pressure plus static pressure

005.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:

A) calculating the ambient static pressure, allowing for the altitude and QNHadjusting the instruments

B) descending as much as possible in order to fly at a pressure as close to

1013.25hPa as possibleC) slightly opening a window to restore the ambient pressure in the cabinD)breaking the rate-of-climb indicator glass window


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006.The atmospheric pressure at FL70 in a "standard + 10" atmosphere is:

A) 942.13hPaB)781.85hPa

C) 644.41hPa

D) 1013.25hPa

007.On board an aircraft the altitude is measured from the:

A) temperature altitudeB)pressure altitudeC) density altitude

D) standard altitude

008.The use of the TCAS (Traffic Collision Avoidance System) for avoiding an aircraft in

flight is now general. TCAS uses for its operation:

A)the replies from the transponders of other aircraftB) both the replies from the transponders of other aircraft and the ground-

based radar echosC) the echos of collision avoidance radar system especially installed on

boardD) the echos from the ground air traffic control radar system


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009.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...

A)at high speed, the non-compensated altimeter will indicate a higheraltitude

B) there will be no difference between them if the air data computer (ADC)is functioning normally

C) ATC will get an erroneous altitude report SSRD) at high speed, the non-compensated altimeter will indicate a lower

altitude

010.The pressure altitude is the altitude corresponding:

A) in ambiant atmosphere, to the pressure Ps prevailing at this point

B) in ambiant atmopsphere, to the reference pressure Ps

C) in standard atmosphere, to the reference pressure PsD)in standard atmosphere, to the pressure Ps prevailing at this point

011.The altimeter consits of one several aneroid capsules located in a sealed casing. The

pressure in the aneroid capsule (i) and casing (ii) are respectively:

A) (i) static pressure at time t (ii) static pressure at time t- tB)(i) vacuum (or a very low pressure) (ii) static pressureC) (i) static pressure (ii) total pressure

D) (i) total pressure (ii) static pressure

012.The altitude indicated on board an aircraft flying in an atmosphere where all atmosphere

layers below the aircraft are warm is:

A) lower than the real altitudeB)higher than the real altitudeC) the same as the real altitudeD) equal to the standard altitude

013.The density altitude is:

A) the temperature altitude corrected for the difference between the real

temperature and the standard temperatureB) the pressure altitude corrected for the density of air at this point

C) the pressure altitude corrected for the relative density prevailing at thispoint

D)the altitude of the standard atmosphere on which the density is equal tothe actual density of the atmosphere


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014.In case of accidental closing of an aircraft's left static pressure port (rain, birds), the

altimeter:

A)overreads the altitude in case of a sideslip to the left and and displays thecorrect information during symmetric flight

B) keeps on providing reliable reading in all situationsC) underreads the altitude

D) overreads the altitude in case of a side-slip to the right and displays thecorrect information during symmetric flight

015.The altimeter is fed by:

A) dynamic pressureB)static pressure

C) differential pressure

D) total pressure

016.The error in altimeter readings caused by the variation of the static pressure near the source

is known as:

A) hysteresis effectB)position pressure error

C) instrument errorD) barometric error

017.If the static source of an altimeter becomes blocked during a descent the instrument will:

A) under-readB)continue to display the reading at which the blockage occured

C) gradually indicate zeroD) indicate a height equivalent to the setting on the milibar subscale

018.The primary factor which makes the servo-assisted altimeter more accurate than the simple

pressure altimeter is the use of:

A) more effective temperature compensating leaf springsB) a sub-scale logarithmic functionC)an induction pick-off deviceD) combination of counters/pointers


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019.If the static source to an altimeter becomes blocked during a climb, the instrument will:

A) over-readB)continue to indicate the reading at which the blockage occured

C) under-read by an amount equivalent to the reading at the time that the

instrument became blockedD) gradually return to zero

020.At sea level, on a typical servo altimeter, the tolerance in feet from indicated must not

exceed:

A) +/- 30ft

B) +/- 70ftC) +/- 75ftD)+/- 60ft

021.The altitude indicated on board an aircraft flying in an atmopshere where all the atmosphere

layers below the aircraft are cold is:

A) equal to the standard altitude

B) higher than the real altitudeC)lower than the real altitude

D) the same as the real altitude

022.When flying from a sector of warm air into one of colder air, the altimeter will:

A) underread

B) be just as correct as beforeC) show the actual height above groundD)overread

023.The hysteresis error of an altimeter varies substantially with the:

A) static temperature

B)time passed at a given altitude

C) mach number of the aircraftD) aircraft altitude


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024.The purpose of the vibrating device of an altimeter is to:

A) reduce the hysteresis effectB) inform the crew of failure of the instrumentC)reduce the effect of friction in the linkages

D) allow damping of the measurement in the unit

025.The QNH is by definition the value of the:

A)altimeter setting so that the needles of the altimeter indicate the altitude

of the location for which it is givenB) atmospheric pressure at the sea level of the location for which it is given

C) atmospheric pressure at the level of the ground overflown by the aircraft

D) altimeter setting so that the needles indicate zero when the aircraft is onground at the location for which it is provided

026.The limits of the white scale of an airspeed indicator are:

A) VSI for the lower limit and VLE for the upper limit

B) VSO for the lower limit and VLE for the upper limitC)VSO for the lower limit and VFE for the upper limit

D) VSI for the lower limit and VFE for the upper limit

027.If the static source to an airspeed indicator (ASI) becomes blocked during a descent the

instrument will:

A) continue to indicate the speed applicable to that at the time of the

blockage

B) read zeroC)over-read

D) under-read

028.When climbing at a constant Mach number below the tropopause, in ISA conditions, the

Calibrated Airspeed (CAS) will:

A) increase at an exponential rateB) increase at a linear rateC)decrease

D) remain constant


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029.For a constant Calibrated Airspeed (CAS) and a level flight, a fall in ambient temperature

will result in a:

A) higher True Air Speed (TAS) due to an decrease in air densityB) lower True Air Speed (TAS) due to an decrease in air density

C) higher True Air Speed (TAS) due to an increase in air densityD)lower True Air Speed (TAS) due to an increase in air density

030.When descending through an isothermal layer at a constant Calibrated Airspeed (CAS), the

True Airspeed (TAS) will:

A)decreaseB) remain constant

C) increase at a linear rate

D) increase at an exponential rate

031.A leak in the pitot total pressure line of a non-pressurized aircraft to an airspeed indicator

would cause it to:

A)under-readB) under-read in a climb and over-read in a descentC) over-read

D) over-read in a climb and under-read in a descent

032.The airspeed indicator circuit consists of pressure sensors. The pitot tube directly supplies:

A) the total pressure and the static pressureB) the dynamic pressure

C) the static pressureD)the total pressure

033.With a pitot probe blocked due to ice build up, the aircraft airspeed indicator will indicate in

descent a:

A) increasing speed

B) fluctuating speedC)decreasing speedD) constant speed


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034.The limits of the green scale of an airspeed indicator are:

A)VS1 for the lower limit and VNO for the upper limitB) VSO for the lower limit and VNO for the upper limit

C) VS1 for the lower limit and VLO for the upper limit

D) VS1 for the lower limit and VNE for the upper limit

035.With a constant weight, irrespective of the airfield altitude, an aircraft always takes off at

the same:

A) equivalent airspeedB) ground airspeedC)calibrated airspeedD) true airspeed

036.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:

A) initially by the VMO, then by the MMO below a certain flight level

B) by the MMOC) by the VMO in still air

D)initially by the MMO, then by the VMO below a certain flight level

037.All the anemometers are calibrated according to:

A) Bernoulli's limited formula which considers the air as an uncompressed

fluidB)St-Venant's formula which takes into account the air compressibility

C) Bernoulli's limited formula which takes into account the aircompressibility

D) St-Venant's formula which considers the air as an uncompressible fluid

038.The limits of the yellow scale of an airspeed indicator are:

A) VFE for the lower limit and VNE for the upper limitB) VLO for the lower limit and VNE for the upper limit

C) VLE for the lower limit and VNE for the upper limitD)VNO for the lower limit and VNE for the upper limit


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039.VNO is the maximum speed:

A) with flaps extended in landing positionB)not to be exceeded except in still air and with caution

C) which must never be exceeded

D) at which the flight controls can be fully deflected

040.The airspeed indicator of a twin-engined aircraft comprises different sectors and color

marks. The blue line corresponds to the:

A) speed not to be exceeded, or VNEB) minimum control speed, or VMC

C) maximum speed in operations, or VMOD)optimum climbing speed with one engine inoperative, or Vy

041.VFE is the maximum speed:

A) at which the flaps can be operatedB) with the flaps extended in take-off positionC)with the flaps extended in a given positionD) with the flaps extended in landing position

042.VLE is the maximum:

A) speed at which the landing gear can be operated with full safety

B) speed authorized in flightC) speed with flaps extended in a given position

D)flight speed with landing gear down

043.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) increases abruptly towards VNEB) decreases abruptly towards zero

C) increases steadilyD)decreases steadily


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044.VNE is the maximum speed:

A) with flaps extended in landing positionB) not to be exceeded except in still air and with caution

C) at which the flight controls can be fully deflected

D)which must never be exceeded

045.The calibrated airspeed (CAS) is obtained by applying to the indicated airspeed (IAS):

A) an antenna and compressibility correction

B) a compressibility and density correctionC)an instrument and position/pressure error correction

D) and instrument and density correction

046.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:

A)increases steadilyB) decreases steadily

C) decreases abruptly towards zeroD) increases abruptly towards VNE

047.The velocity maximum operating (VMO) is a speed expressed in:

A) true airspeed (TAS)

B)calibrated airspeed (CAS)C) equivalent airspeed (EAS)

D) computed airspeed (COAS)

048.VLO is the maximum:

A) flight speed with landing gear down

B) speed with flaps extended in a given positionC)speed at which the landing gear can be operated with full safety

D) cruising speed to to be exceeded except in still air with caution


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049.During a straight and uniform climb, the pilot maintains a constant calibrated airspeed

(CAS):

A) the Mach number is constant and the true airspeed (TAS) is constantB) the Mach number is increases and the true airspeed (TAS) is constant

C)the Mach number is increases and the true airspeed (TAS) increasesD) the Mach number is constant and the true airspeed (TAS) decreases

050.A VMO-MMO warning device consists of an alarm connected to:

A) a barometric aneroid capsule and an airspeed sensor subjected to adynamic pressure

B) a barometric aneroid capsule and an airspeed sensor subjected to a staticpressure

C)a barometric aneroid capsule subjected to a static pressure and an

airspeed sensor subjected to a dynamic pressureD) a barometric aneroid capsule subjected to a dynamic pressure and anairspeed sensor subjected to a static pressure

051.If the outside temperature at 35000ft is -40C the local speed of sound is:

A) 686ktB)596kt

C) 247ktD) 307kt

052.At a constant calibrated airspeed (CAS), the Mach number:

A) remains unchanged when the outside temperature decreasesB) remains unchanged when the outside temperature increasesC)increases when the altitude increasesD) decreases when the altitude increases

053.Indication of Mach number is obtained from:

A)indicated speed and altitude using a speed indicator equipped with analtimeter type aneroidB) indicated speed (IAS) compared with true airspeed (TAS) from the air

data computer

C) a kind of echo sound comparing velocity of sound with indicated speedD) an ordinary airspeed indicator scaled for Mach number instead of knots


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054.The Mach number is the:

A)true airspeed (TAS) divided by the local speed of soundB) corrected airspeed (CAS) divided by the local speed of sound

C) equivalent airspeed (EAS) divided by the local speed of sound

D) indicated airspeed (IAS) divided by the local speed of sound

055.The principle of the Mach indicator is based on the computation of the ratio:

A)(Pt-Ps) to Ps

B) (Pt-Ps) to PtC) (Pt+Ps) to Ps

D) Pt to Ps

056.At a constant Mach number, the calibrated airspeed (CAS):

A)decreases when the altitude increases

B) remains unchanged when the outside temperature increasesC) remains unchanged when the outside temperature decreases

D) increases when the altitude increases

057.The Mach number is:

A) the ratio of the indicated airspeed to the sonic velocity at the altitude

considered

B)the ratio of the aircraft true airspeed to the sonic velocity at the altitudeconsidered

C) a direct function of temperature; it varies in proportion to the square root

of the absolute temperatureD) the ratio of the aircraft conventionnal airspeed to the sonic velocity at the

altitude considered

058.Sound propagates through the air at a speed which only depends on:

A) density

B)temperatureC) temperature and the pressureD) pressure


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059.The velocity of sound at the sea level in a standard atmosphere is:

A) 1059ktB) 332ktC)661kt

D) 644kt

060.Machmeter readings are subject to:

A)position pressure error

B) setting errorC) temperature error

D) density error

061.The reading of a Mach indicator is independent of:

A) the total pressure

B) the static pressureC) the differential pressure measurement

D)the outside temperature

062.The operating principle of the vertical speed indicator (VSI) is based on the measurement of

the rate of change of:

A) Dynamic pressure

B) Total pressureC) Kinetic pressure

D)Static pressure

063.The response time of a vertical speed detector may be increased by adding a:

A) second calibrated port

B)correction based on an accelometer sensorC) bimetallic strip

D) return spring


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064.The vertical speed indicator of an aircraft flying at a true airspeed of 100kt, in a descent

with a slope of 3 degrees, indicates:

A) -150ft/minB) -300ft/min

C) -250ft/minD)-500ft/min

065.The vertical speed indicator (VSI) is fed by:

A) differential pressureB) total pressureC)static pressureD) dynamic pressure

066.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:

A) 2, 3, 4B) 1, 2, 3, 4

C) 1, 2, 3

D)1, 3, 4

067.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:

A) Tt = Ts (1 - 0.2 x M 2)

B) Tt = Ts (1 + 0.2Kr x M 2)C)Tt = Ts (1 + 0.2M 2)D) Tt = Ts / (1 + 0.2Kr x M 2)


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068.An Air Data Computer (ADC):

A) is an auxiliary system that provides altitude information in the event thatthe static source is blocked

B) converts air data measurements given by ATC from the ground in order

to provide correct altitude and speed informationC)transforms air data measurements into electric impulses driving servo

motors in instruments

D) measures position error in the static system and transmits thisinformation to ATC to provide correct altitude reporting

069.Cruising at FL390, M.84 is found to give a TAS of 499kt. The ISA deviation at this level

will be:

A) -19.

B)+17.C) -17.D) +19.

070.Compressibility error in the ASI is normally corrected by:

A)Use of the navigation computerB) Use of a calibration card placed next to the instrument

C) Accurate calibration of the instrumentD) The error is insignificant and can be ignored

071.Turbulent flow around a pressure head will cause:

A) an increase in the dynamic pressure.B) density error.

C) 95% increase in manoeuvre induced error.D)approximately 95% of the position error.

072.Dynamic pressure is given by:

A) The static energy formula P1V1 = P2V2B)The kinetic energy formula: 1/2 density x V2C) The kinetic energy formula P1V1 = P2V2

D) The static energy formula: 1/2 density x V2


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073.The advantages of an ADC over a traditional pitot - static system are:

position and compressibility correction.

reduced lag

ability to supply many instruments

ability to act as an altimeter following failure.

A) 1, 3 & 4B) 2, 3 & 4C)1, 2 & 3D) 1, 2 & 4

074.A servo altimeter has a quoted accuracy of 1 mb at mean sea level. The accuracy in the

standard atmosphere is:

A) +- 50 ft at 20 000 ft and +- 90 ft at the tropopause

B) +- 50 ft at 10 000 ft and +- 100 ft at 40 000 ftC)+- 27 ft at MSL and +- 50 ft at 10 000 ftD) +- 30 ft at 20 000 ft and +- 100 ft at 20 000 ft

075.VNO is the maximum speed:

A) at which the flight controls can be fully deflected.

B) with flaps extended in landing position.C)not to be exceeded except in still air and with caution.D) which must never be exceeded.

076.An is aircraft flying at a TAS of 1100 knots at FL 650. A change in 0.1M causes a change in

TAS of 57 knots.

The temperature deviation at FL 650 assuming an ISA atmosphere is:

A) +5B) +2.5C) -5D)-2.5

077.An aircraft is passing 6,500 ft in a descent when the static line becomes blocked. The

altimeter then reads:

A) more than 6,500 ftB) less than 6,500 ftC) zero

D)6,500 ft


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078.How many diaphragms are present in a basic Mach meter?

A) Four.B)Two.

C) One.

D) Three.

079.When an altimeter is used for SSR it is always referenced to:

A)1013.25 hPa

B) QNHC) QFE

D) The pressure setting in use

080.Aircraft with pressurized cabin in flight:

When switching to the alternate static pressure source, the pointer of the Vertical Speed

Indicator:

A) indicates a descent, then settles down and reads incorrectlyB) indicates a slight continuous descent

C) indicates correctlyD)indicates a climb, then settles down and reads incorrectly

081.The errors to which the machmeter is subject are:

A)instrument error, position error.B) instrument error, position error, compressibility error and manoeuvre

induced error.C) instrument error, position error, barometric error, temperature error and

manoeuvre induced error.D) instrument error, position error, density error and manoeuvre induced

error.

082.Pressure error in an altimeter arises because:

A)The true external static pressure is not accurately transmitted to theinstrument

B) The true external pitot pressure is not accurately transmitted to the

instrumentC) The true external dynamic pressure is not accurately transmitted to the

instrumentD) The true external kinetic pressure is not accurately transmitted to the

instrument


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083.The airspeed indicator is calibrated to:

A) ISA at 36,000 ftB) the full ISAC)ISA at mean sea level

D) ISA at the height the aircraft is flying

084.Given:

M: Mach number

Ts: static temperature

Tt: total temperature

Which of the following statements is correct?

A) Ts = Tt x (0.2M2)

B)Ts = Tt / (1+0.2M2)C) Ts = Tt x (1+0.2M2)

D) Ts = Tt / (0.2M2)

085.As an airplane climbs higher, the true airspeed for a given indicated airspeed will:

A)IncreaseB) Vary depending on the actual value of the indicated airspeed and the

angle of attack

C) Remain the same

D) Decrease

086.Which of the following instruments require pitot and static pressure inputs?

A) Airspeed indicator, vertical speed indicator, altimeter.B)Airspeed indicator and machmeter.C) Airspeed indicator only.

D) Airspeed indicator, machmeter and vertical speed indicator.

087.An aircraft is flying straight and level, over a warm air mass. The altimeter reading will be:

A) oscillating around the correct height

B)less than the real heightC) greater than the real height

D) correct


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088.The difference between static air temperature and total air temperature is known as:

A)the ram riseB) hot ramp radiation

C) the recovery factor

D) corrected outside air temperature

089.When descending through an isothermal level the TAS will .... (i), the CAS .... (ii) and the

LSS will .... (iii):

A) i decrease ii decrease iii remain constantB) i increase ii increase iii decreaseC)i remain constant ii increase iii remain constantD) i remain constant ii decrease iii increase

090.If the static line to the ASI becomes blocked during a climb, the ASI reading will:

A) remain fixed.B) progressively overread.C)progressively underread.D) increase, no matter what the actual airspeed is.

091.An aircraft is flying at FL 390, temperature -56.5 C at Mach 0.85. The TAS of the aircraft

is:

A) 561B) 472C)485D) 476

092.The temperature at the airport is 23 C, what is the local speed of sound:

A) 644 knots

B) 694 knots

C)671 knots

D) 616 knots


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093.What does a vertical speed indicator actually measure?

A) The rate of temperature and altitude change.B) The rate of altitude change.C)The rate of pressure change.

D) The rate of temperature change.

094.EAS is:

A) IAS corrected for compressibility

B)CAS corrected for compressibilityC) CAS corrected for position error

D) IAS corrected for instrument error only

095.For an altimeter, pressure fluctuations at the static vent cause:

A) Temperature error

B) Hysteresis errorC)Position error

D) Barometric error

096.The combined Machmeter / ASI is subject to the following errors:

A) instrument, pressure and temperature only

B) those of the Machmeter only

C)position, density, instrument, compressibility, manoeuvre inducedD) instrument and compressibility only

097.A temperature sensor having a recovery factor of 0.75 indicates 30 C. Static Air

Temperature (SAT) is 25 C.

How high is the Ram-rise?

A) 6.7 C.

B) 40 C.

C) 18.8 C.

D)5 C.


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098.An Air Data Computer (ADC):

A) Measures position error in the static system and transmits thisinformation to ATC to provide correct altitude reporting

B) Converts air data measurements given by ATC from the ground in order

to provide correct altitude and speed informationC) Is an auxiliary system that provides altitude information in the event that

the static source is blockedD)Transforms air data measurements into electric impulses driving servo

motors in instruments

099.What corrections must be applied to indicated airspeed to produce true airspeed?

A) Correction for altitude and wind.B) Correction for heading and altitude.

C)Correction for altitude and temperature.D) Correction for wind and temperature.

100.An increase of 0.15 Mach results in an increase of 93 kt TAS of an aircraft. The local speed

of sound is:

A) 560 ktB)620 kt

C) 685 ktD) 580 kt

101.An aircraft is in level flight at FL100 over a mountain range, which extends up to 2.400

metres AMSL. If the regional QNH is 998 hPa (use 30 ft/hPa), what is the approximate terrain

clearance?

A) 2.581 feet.B)1.681 feet.C) 450 feet.

D) 7.869 feet.

102.The Airspeed Indicator measures:

A) Differential pressure changesB)Differential pressure

C) Static pressure changesD) Static pressure


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103.An aircraft flies an altitude of 3500 feet from A, elevation 700 feet QNH 1015 mb to B,

elevation 1120 feet QNH 992 mb. Assuming the altimeter sub-scale is not changed, the aircraft

will arrive over B at a height of:

A) 3500 feet

B) 2670 feetC)1690 feet

D) 2810 feet

104.The Mach number is:

A) the ratio of the indicated airspeed to the sonic velocity at the altitudeconsidered.

B)the ratio of the aircraft true airspeed to the sonic velocity at the altitude

considered.

C) the ratio of the aircraft conventional airspeed to the sonic velocity at thealtitude considered.

D) a direct function of temperature ; it varies in proportion to the square

root of the absolute temperature.

105.Calibrated air speed is:

A)IAS plus instrument error correctionB) IAS plus density error correction

C) IAS plus compressibility correction

D) IAS plus the pressure error

106.CAS is IAS corrected for:

A) compressibility.B)position error.

C) instrument error.D) density error.

107.Change of temperature as an aircraft climbs or descends:

A) will affect VSI readings whenever actual temperature lapse rate differsfrom the standard atmosphere temperature lapse rate.

B) has no effect on the VSI readings, as only static pressure is used in thisinstrument.

C) must be corrected using a computer or correction tables.D)is compensated at the metering unit by means of a capillary and orifice.


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108.The ISA temperature and pressure for 18 000 ft are:

A) -12.7 C and 595.2 hPa respectivelyB)-20.7 C and 506 hPa respectively

C) -12.7 C and 506 hPa respectively

D) -20.7 C and 595.2 hPa respectively

109.The principle of operation of a servo-assisted pressure altimeter is that:

A)static pressure changes are converted via an E- and I-bar transducer into

electrical signal which is used, via a follow-up system, to move a digitalcounter and pointer system

B) static pressure enters an aneroid capsule causing it to expand

C) static and pitot pressure are compared with the resultant pressure beingused to drive the counter and pointer system

D) static pressure is used in the same way as a simple altimeter except thatseveral capsules are used

110.When flying from low pressure to high pressure, the barometric error of an altimeter will

cause the instrument to:

A)underread the true altitude of the aircraft.

B) indicate a higher altitude than the correct one.C) indicate the true altitude.

D) overread the true altitude of the aircraft.

111.VFE is the maximum speed:

A) with the flaps extended in take-off position.B) at which the flaps can be operated in turbulence.C)with the flaps extended in a given position.

D) with the flaps extended in landing position.

112.Compared to the VSI what errors are eliminated by the IVSI?

A)lagB) temperature

C) pressureD) turning


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113.If the pitot tube is clogged, which instrument(s) is/are affected?

A) Altimeter only.B) Altimeter and airspeed indicator.C)Airspeed indicator only.

D) Vertical speed indicator only.

114.We are maintaining a constant flight level. That means:

A) the outside air pressure is constant if the temperature remains constant.

B) the altitude is constant when the sea-level pressure is constant.C) the altitude above sea level is constant.

D)the outside air pressure is constant.

115.The vertical speed indicator indications may be in error for some seconds after starting

or finishing a climb or descent. The error is a result of:

A) a combination of time lag and instrument error.

B) manoeuvre induced errors only.C)a combination of time lag and manoeuvre induced errors.

D) a combination of position error and manoeuvre induced errors.

116.During a steady climb the pitot head becomes totally blocked by ice. As the climb continues

the indications of the machmeter will:

A) progressively under indicate the Mach numberB) stick at the Mach number at the time of blockage

C) go to zero and stay thereD)increase no matter what the actual Mach number

117.During a steady climb the pitot head becomes totally blocked by ice. As the climb continues

the indications of the machmeter will:

A) progressively under indicate the Mach numberB) stick at the Mach number at the time of blockage

C) go to zero and stay thereD)increase no matter what the actual Mach number


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118.Density varies:

A) Directly with temperature and pressureB)Directly with pressure and inversely with temperature

C) Inversely with pressure and directly with temperature

D) Inversely with temperature and pressure

119.The Mach number is a function of the:

A) humidity of the air.

B)Absolute temperature of the air.C) relative air temperature.

D) Isobaric gradient of the fluid.

120.The reason for having a square-law compensation in the airspeed-indicator mechanism is:

A) The differential pressure decreases with the square of the airspeed

B) The ram air pressure decreases with the square-root of the airspeedC) The ram air pressure increases with the square-root of the airspeed

D)The differential pressure increases with the square of the airspeed

121.Total Air Temp is always... than Static Air Temp and the difference varies with...

A) colder, CAS.

B) warmer, altitude.

C)warmer, TAS.D) colder, altitude.

122.Indicated airspeed corrected for position error is:

A)Calibrated airspeed.

B) Ground speed.C) True air speed.D) Equivalent air speed.

123.The vertical speed indicator VSI is fed by:

A) dynamic pressure.B) differential pressure.C)static pressure.D) total pressure.


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124.Given:

Ts: the static air temperature (SAT)

Tt: the total air temperature (TAT)

Kr: the recovery coefficient

M: the Mach number

A)Tt = Ts(1+0.2 x Kr x M2)B) Tt = Ts/(1+0.2 x Kr x M2)

C) Tt = Ts(1-0.2 x M2)D) Tt = Ts(1+0.2 x M2)

125.Compressibility Error requires a .... (i) correction because it is .... (ii) of ....(iii) pressure. It

gives .... (iv):

A) (i) positive (ii) an increase (iii) dynamic (iv) TAS

B) (i) positive (ii) a decrease (iii) static (iv) TASC) (I) negative (ii) a decrease (iii) static (iv) EASD)(i) negative (ii) an increase (iii) dynamic (iv) EAS

126.Dynamic pressure is:

A) Static pressure minus pitot pressureB)Pitot pressure minus static pressure

C) Pitot pressure plus static pressureD) Density and static pressure

127.If the static vent becomes blocked during climb:

A) the VSI will stop at the rate of climb of the aircraft at the time of

blockage.B)the VSI will return to zero.

C) the VSI will indicate an increasing rate of climb.D) the VSI will indicate a decreasing rate of climb.

128.A pitot tube covered by ice which blocks the ram air inlet will affect the following

instrument (s) :

A) vertical speed indicator only.

B) airspeed indicator, altimeter and vertical speed indicator.C) altimeter only.D)airspeed indicator only.


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129.The velocity maximum operating (V.M.O.) is a speed expressed in :

A) equivalent airspeed (EAS).B) true airspeed (TAS).C)calibrated airspeed (CAS).

D) computed airspeed (COAS).

130.The static pressure error of the static vent on which the altimeter is connected varies

substantially with the:

A) deformation of the aneroid capsuleB) aircraft altitude

C) static temperatureD)Mach number of the aircraft

131.The airspeed indicator of an aircraft is provided with a moving red and white hatched

pointer. This pointer indicates the:

A)maximum speed in VMO operation versus altitudeB) speed indicated on the autothrottle control box versus altitude

C) maximum speed in VMO operation, versus temperatureD) speed indicated on the autothrottle control box, versus temperature

132.In An Air Data Computer (ADC), aeroplane altitude is calculated from:

A)Measurement of absolute barometric pressure from a static source on thefuselage

B) Measurement of outside air temperature (OAT)C) The difference between absolute and dynamic pressure at the fuselage

D) Measurement of elapsed time for a radio signal transmitted to the ground

surface and back

133.Today's airspeed indicators (calibrated to the Saint-Venant formula), indicate, in the absence

of static (and instrumental) error :

A) The true airspeedB) The airspeed, whatever the altitude

C)The conventional airspeed (CAS) in all casesD) The equivalent airspeed, in all cases


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134.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


A) 2, 3, 4

B) 2, 3, 5C)1, 4

D) 1, 2, 3, 4, 5

135.The diagram in the annex 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:

A)1B, 2C, 3AB) 1B, 2A, 3C

C) 1C, 2B, 3AD) 1A, 2B, 3C


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136.The basis properties of a gyrospace are:

1 The gyro's weight

2 The rigidity in space

3 The inertia

4 The high RPM

5 The precession


A) 1, 3, 5

B) 2, 3, 5C)2, 5

D) 3, 4

137.Compared with a conventional gyro, a laser gyro:

A) consumes a lot of powerB) has a fairly long starting cycleC) is influenced by temperatureD)has a longer life cycle

138.In the building principle of a gyroscope, the best efficiency is obtained through the

concentration of the mass:

A) close to the axis and with a low rotation speedB) on the periphery and with a low rotation speed

C) close to the axis and with a high rotation speedD)on the periphery and with a high rotation speed

139.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 45N, this reference

turns by...

A) 15/hour to the right

B) 7.5/hour to the leftC)10.5/hour to the right

D) 7.5/hour to the right


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140.A laser gyro consists of:

A) a gyro with 2 degrees of freedomB)a laser generating two light waves

C) 2 electrodes (anodes+cathodes)

D) two moving cavities provided with mirrors

141.The directional gyro axis no longer spins about the local vertical when it is located:

A) on the North pole

B) in the latitude 30C) in the latitude 45

D)on the equator

142.The maximum directional gyro error to the earth rotation is:

A) 90/hour

B) 180/hourC)15/hour

D) 5/hour

143.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


A)1, 4

B) 2, 4C) 1, 3

D) 2, 3

144.For an aircraft flying a true track of 360 between the 005S and 005N parallels, the

precession error of the directional gyro due to apparent drift is equal to:

A)0/hour

B) +5/hour

C) -5/hourD) depends only on the aircraft's ground speed


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145.An airborne instrument, equipped with a gyro with 2 degrees of freedom and a horizontal

spin axis is:

A) a turn indicatorB) an artificial horizon

C)a directional gyroD) a flux gate compass

146.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...

A) shows itself by an apparent rotation of the horizontal axis of thegyroscope which seems to turn at 15 per hour to the right in the

northern hemisphereB)is dependent on the ground speed of the aircraft, its true track and the

average latitude of the flightC) is at its greatest value when the aircraft follows a meridional trackD) is, in spite of this, insignificant and may be neglected

147.The gimbal error of the directional gyro is due to the effect of:

A) an apparent weight and an apparental vertical

B) too slow precission on the horizontal gimbal ringC)a bank or pitch attitude of the aircraft

D) the aircraft's track over the earth

148.The directional gyro axis spins about the local vertical by 15/hour:

A) on the equator

B) in the latitude 45C) in the latitude 30D)on the North pole


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149.The characteristics of the directional gyro (DG) used in a gyro stabilised compass system

are:

A) two degrees of freedom, whose axis aligned with the vertical to thelocation is maintained in this direction by an erecting system

B) one degree of freedom, whose vertical axis, aligned with the real verticalto the location is maintained in this direction by an automatic erecting

systemC)two degrees of freedom, whose horizontal axis corresponding to the

reference direction is maintained in the horizontal plane by an automatic

erecting systemD) one degree of freedom, whose horizontal axis is maintained in the

horizontal plane by an automatic erecting system

150.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


A) 2, 5, 6

B)1, 3, 4, 6C) 1, 3, 4D) 1, 2, 3, 4, 5, 6

151.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


A)1, 2, 3, 5

B) 2, 3, 5C) 3, 4, 5

D) 1, 2, 4, 5


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152.The pendulum type detector system of the directional gyro feeds:

A) a nozzle integral with the outer gimbal ringB)a levelling erection torque motor

C) a torque motor on the sensitive axis

D) 2 torque motors arranged horizontally

153.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


A) 2, 3, 5B)1, 3, 5C) 1, 4D) 2, 5

154.Heading information given by a gyro platform, is given by a gyro at:

A) 1 degree-of-freedom in the vertical axisB)2 degrees-of-freedom in the horizontal axis

C) 2 degrees-of-freedom in the vertical axis

D) 1 degree-of-freedom in the horizontal axis

155.The gyromagnetic compass torque motor:

A) feeds the error detector systemB) is fed by the flux valve

C) causes the heading indicator to precessD)causes the directional gyro unit to precess

156.Heading information from the gyromagnetic compass flux gate is transmitted to the:

A) amplifier

B) erecting systemC)error detectorD) heading indicator


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157.The heading information originating from the gyromagnetic compass flux valve is sent to

the:

A) heading indicatorB) erector system

C)error detectorD) amplifier

158.The input signal of the amplifier of the gyromagnetic compass resetting device originates

from the:

A) flux valveB) directional gyro erection deviceC)error detector

D) directional gyro unit

159.A slaved directional gyro derives it's directional signal from:

A)the flux valveB) the air-data-computer

C) a direct reading magnetic compassD) the flight director

160.A failed RMI rose is locked on 090 and the ADF pointer indicates 225. The relative

bearing to the station is:

A) 225B) 315

C) Impossible to read, due to failure RMID)135

161.A Stand-by-horizon or emergency attitude indicator:

A) is automatically connected to the primary vertical gyro if the alternatorfails

B)contains its own separate gyroC) only works if there is a complete electrical failure

D) is fully independent of external energy resources in an emergencysituation


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162.Among the flight control instruments, the artificial horizon playes 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)

A)two degrees of freedom, whose axis is oriented and continouslymaintained to local vertical by an automatic erecting system

B) two degrees of freedom, whose horizontal axis corresponding to a

reference direction is maintained in a horizontal plane by an automaticerecting system

C) one degree of freedom, whose horizontal axis is maintained in ahorizontal plane by an automatic erecting system

D) one degree of freedom, whose vertical axis oriented in the direction of

the real vertical to the location is maintained in this direction by anautomatic erecting system

163.When an aircraft has turned 90 degrees with a constant attitude and bank, the pilot observes

the following on a classic artificial horizon:

A) attitude and bank correctB) too much nose-up and bank correct

C) too much nose-up and bank too highD)too much nose-up and bank too low

164.Following 180 stabilized turn with a constant attitude and bank, the artificial horizon

indicates:

A) too high pitch up and correct bankingB) too high pitch up and too high bankingC)too high pitch-up and too low bankingD) attitude and banking coorect

165.When an aircraft has turned 360 degrees with a constant attitude and bank, the pilot

observes the following on a classic artificial horizon:

A) too much nose-up and bank correctB) too much nose-up and bank too high

C) too much nose-up and bank too lowD)attitude and bank correct


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166.The diagram which shows a 40 left and 15 nose down attitude is number

A)1B) 4

C) 3

D) 2

167.A gravity erector system is used to correct the errors on:

A) a gyromagnetic compassB) a turn indicator

C) a directional gyroD)an artificial horizon


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168.During an acceleration phase at constant attitude, the resetting principle of the artificial

horizon results in the horizon bar indicating a:

A) nose-down followed by a nose-up attitudeB) nose-down attitude

C)nose-up attitudeD) constant attitude

169.When an aircraft has turned 270 degrees with a constant attitude and bank, the pilot

observes the following on a classic artificial horizon:

A) too much nose-up and bank correctB)too much nose-up and bank too high

C) attitude and bank correct

D) too much nose-up and bank too low

170.A gravity type erector is used in a vertical gyro device to correct errors on:

A) a directional gyro unitB)an artificial horizon

C) a gyromagnetic indicatorD) a turn indicator

171.An aircraft is flying at a 120kt true airspeed (VV), in order to achieve a rate 1 turn, the pilot

will have to bank the aircraft at an angle of:

A)18B) 36

C) 12D) 30


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172.The diagram representing a left turn with insufficient rudder is:

A)4B) 3

C) 1

D) 2

173.The rate turn 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


A) 2, 5B)1, 3C) 1, 6

D) 1, 3, 4

174.In a Turn-indicator, the measurement of a rate-of-turn consists for:

A) high bank angles, in measuring the roll rate

B) high bank angles, in measuring the yaw rateC) low bank angles, in measuring the roll rate

D)low bank angles, in measuring the yaw rate


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175.In a turn at constant rate, the turn indicator reading is:

A) proportional to the aircraft true airspeedB) proportional to the aircraft weightC)inversely proportional to the aircraft true airspeed

D) independent to the aircraft true airspeed

176.An airborne instrument, equipped with a gyro with 1 degree of freedom and a horizontal

spin axis is a:

A) fluxgate compassB) gyromagnetic compassC)turn indicatorD) directional gyro

177.A turn indicator is an instrument which indicates rate of turn.

Rate of turn depends on:

1 bank angle

2 aeroplane speed

3 aeroplane weight


A) 1, 2, 3B) 1, 3

C) 2, 3

D)1, 2

178.When, in flight, the needle of a needle-and-ball indicator is on the left and the ball on the

right, the aircraft is:

A)turning left with not enough bankB) turning left with too much bankC) turning right with not enough bankD) turning right with too much bank

179.When, in flight, the needle of a needle-and-ball indicator is on the right and the ball on the

left, the aircraft is:

A) turning left with not enough bankB) turning left with too much bankC) turning right with too much bank

D)turning right with not enough bank


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180.When, in flight, the needle and ball of a needle-and-ball indicator are on the right, the

aircraft is:

A) turning left with too much bankB)turning right with too much bank

C) turning right with not enough bankD) turning left with not enough bank

181.When, in flight, the needle and ball of a needle-and-ball indicator are on the left, the aircraft

is:

A) turning right with not enough bankB) turning left with not enough bank

C) turning right with too much bankD)turning left with too much bank

182.On the ground, during a left turn, the turn indicator indicates:

A) needle in the middle, ball to the leftB)needle to the left, ball to the right

C) needle in the middle, ball to the rightD) needle to the left, ball to the left

183.On the ground, during a right turn, the turn indicator indicates:

A) needle in the middle, ball to the rightB)needle to the right, ball to the left

C) needle in the middle, ball to the leftD) needle to the right, ball to the right


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184.Under normal operating conditions, when an aircraft is in 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


A) 2, 4

B) 3, 4C)1, 3

D) 1, 2

185.A turn indicator is built around a gyroscope with:

A)1 degree of freedom

B) 3 degrees of freedomC) 0 degree of freedom

D) 2 degrees of freedom

186.The rate-of-turn is the:

A) pitch rate in a turnB)change-of-heading rate of the aircraft

C) aircraft speed in a turnD) yaw rate in a turn

187.While 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:

A)with damping and a period of about 84 minutes

B) without damping and a period of about 84 minutesC) without damping and a period of about 84 seconds

D) with damping and a period of 84 seconds


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188.The vertical reference unit of a three-axis data generator is equipped with a gyro with:

A) 1 degree of freedom and horizontal spin axisB) 2 degrees of freedom and horizontal spin axisC)2 degrees of freedom and vertical spin axis

D) 1 degree of freedom and vertical spin axis

189.The heading reference unit of a three-axis data generator is equipped with a gyro with:

A) 2 degrees of freedom and vertical spin axis

B) 1 degree of freedom and horizontal spin axisC) 1 degree of freedom and vertical spin axis

D)2 degrees of freedom and horizontal spin axis

190.In order to align a strapdown inertial unit, it is required to insert the local geographical

coordinates. This is necessary to:

A) determine magnetic or true headingB) re-erect laser gyrosC)position the computing trihedron with reference to earthD) check operation of laser gyros

191.An artificial horizon with an electrical driven gyroscope has greatly reduced take-off errors.

This is because:

A) the fast erection switch is used to overcome topple by increasing theerection rate to a high value

B)the gyro has greater rigidity, is less bottom heavy and there is a linearaccelerometer cut-out switch fitted

C) the gyro has greater rigidity, is less bottom heavy and there is a roll cut-out switch fitted

D) it is fitted with a roll cut-out switch and a linear cut-out switch

192.Rigidity in a gyroscope is:

A) a way to express the stability of the inner and outer gimbal rings.B)the tendency it has to remain in its plane of rotation and resist attempts

to alter its position.

C) to what extremes the flight attitudes might be before the gyro topples.D) the reaction 90 in the direction of rotation when applying force to the

spinning wheel.


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193.The basic properties of a gyroscope are:

The gyro's weight

The rigidity in space

The inertia

The high RPM

The precession

A) 1, 3, 5B)2, 5C) 3, 4D) 2, 3, 5

194.While flying, a red flag labelled " HDG" appears in the indicator (HSI) of a Slaved Gyro

Compass System. This indicates that:

A) The flux valve has detected an error between the actual aircraft headingand the pre-selected heading

B) The autopilot has detected an error between the actual aircraft headingand the pre-selected heading

C) None of the above

D)The flux valve is not supplying reliable information to the compasssystem

195.The latitude nut of the direction indicator is on the .... (i) gimbal and this causes the gyro to

precess around its .... (ii) axis:

A) (i) inner (ii) horizontalB)(i) inner (ii) vertical

C) (i) outer (ii) verticalD) (i) outer (ii) horizontal

196.The torque motor of a slaved gyro compass:

A) precesses the gyro in the vertical plane.

B) moves the heading pointer.

C) moves the Selsyn stator.D)precesses the gyro in the horizontal plane.


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197.In order to align a strapdown inertial unit, it is requited to insert the local geographical

coordinates. This is necessary to:

A)Position the computing trihedron with reference to earthB) Check operation of laser gyros

C) Determine magnetic or true headingD) Re-erect laser gyros

198.Following 180 stabilized turn with a constant attitude and bank, the artificial horizon

indicates:

A)too high pitch-up and too low banking.B) too high pitch up and too high banking.

C) too high pitch-up and correct banking.

D) attitude and banking correct.

199.While accelerating on take-off, what would be the expected indications on an electrically

driven Attitude Indicator?

A)a climbing turn to the leftB) a descending turn to the leftC) a climbing turn to the right

D) none of the above - it will indicate correctly

200.Air-driven gyro rotors are prevented from spinning too fast by the:

A) pressure reducing valveB) electronic speed regulator moduleC)vacuum relief valveD) pressure outflow valve

201.An aircraft is flying at a TAS of 270 knots. What AOB will give a rate 1 turn:

A) 30B) 15

C) 17D)34


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202.Why is an INS platform virtually unusable at very high latitudes?

A) The value of earth rate affecting the E/W accelerometer is a componentdependent on the sine Lat. At high latitudes this component is nearly zero

and makes alignment to magnetic north virtually impossible

B) The value of earth rate affecting the E/W accelerometer is a componentdependent on the sine Lat. At high latitudes this component is nearly zeroand makes alignment to true north virtually impossible

C)The value of earth rate affecting the E/W accelerometer is a componentdependent on the cosine Lat. At high latitudes this component is nearly

zero and makes alignment to true north virtually impossibleD) The value of earth rate affecting the E/W accelerometer is a component

dependent on the cosine Lat. At high latitudes this component is nearlyzero and makes alignment to magnetic north virtually impossible

203.In a turn and slip indicator, the gyro is spinning at a greater speed than normal. What willthe effect be on the indicated rate of turn?

A)It will overread.B) It will cause more precision and rigidity.C) It will be more accurate than usual.

D) It will underread.

204.What are the advantages of a laser gyro compared to a conventional gyro?

A) uses more power.B) takes longer to set up/ spin up.C)has a longer cycle life.D) takes longer to align.

205.The principle of operation of the turn and slip indicator is best described as:

A) a space gyro which uses the force of precession against a spring to give areading of the aircraft rate of turn

B)a single gimbal gyroscope in which a spring, opposing the primaryprecession, in turn produces a secondary precession equal to the aircraft

rate of turnC) an earth gyro in which a calibrated spring ensures the tilt of the gyro is

proportional to the aircraft rate of turnD) a single gimbal gyroscope whose primary precession is opposed by a

spring which, in turn, produces a second precession equal and opposite tothe aircraft rate of turn


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206.The inertial platform in a north-referenced inertial navigation system is torqued to perform

like a Schuler pendulum, so that when the platform moves over the earth:

A)the platform remains level and aligned regardless of any aircraftaccelerations

B) gyro drift errors are cancelled outC) answers b and c are correct

D) the platform will always oscillate with respect to true north

207.The triangular cavity in a RLG is filled with which combination of gases:

A) Helium and argon

B) Hydrogen and argonC) Hydrogen and neonD)Helium and neon

208.The inner gimbal assembly of an artificial horizon is pivoted .... (i) in the .... (ii):

A)(i) to give freedom (ii) pitch plane

B) (i) laterally (ii) caseC) (i) longitudinally (ii) rolling plane

D) (i) longitudinally (ii) outer gimbal

209.The position accuracy of an RLG INS is:

A) 1 NM/hrB) 5 NM/hr

C)2 NM/hr

D) 10 NM/hr

210.What is the maximum drift of a gyro, due to earth rate:

A) 180 deg per hour.B)15 deg per hour.

C) 5 deg per hour.

D) 90 deg per hour.


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211.With regard to the turn indicator, the spring:

A)Produces a secondary precession equal to yawB) Directly balances yaw

C) Gives a linear relationship between extension and secondary force

D) Produces a secondary precession that opposes yaw

212.A space gyro has .... (i) gimbal rings with .... (ii) planes of freedom:

A)(i) 3 (ii) 3

B) (i) 2 (ii) 3C) (i) 3 (ii) 2

D) (i) 2 (ii) 2

213.Laser gyros are used in an IRS. Why must accurate Lat & Long be inserted?

A) to compensate for aircraft movement

B)to determine the computed trihedronC) to check the function of the laser gyros

D) to determine magnetic north

214.In a left turn while taxiing, the correct indications are:

A) Needle right, ball right.B)Needle left, ball right.

C) Needle left, ball left.D) Needle right, ball left.

215.A 2 axis gyro measuring vertical changes will have:

A)two degrees of freedom vertical axis.

B) one degree of freedom horizontal axis.C) one degree of freedom vertical axis.D) two degrees of freedom horizontal axis.


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216.Which of the following are errors of a DGI:

earth rate

transport wander

banking when pitched up

annual movement of poles

mechanical problems

A) 3, 4, & 5B) all 5C) 2, 3, & 5D)1, 2, 3, & 5

217.When turning left on the ground the turn and slip indicator:

A) will not indicate on the ground

B) will show a skidC) will show a left bank and slipD)will show a left bank and skid

218.Inside an artificial horizon:

A) the rotor axis is kept level by a calibrated spring attached to the outer

ring and the instrument case.B)the inner ring is pivoted laterally inside the outer ring and the outer ring

is pivoted longitudinally inside the case.

C) the inner ring is tied to the vertical by a control system.D) there is only one gimbal ring.

219.The fundamental difference between an INS and an IRS is that:

A)The IRS is a strap down system with 3 accelerometers mounted 90 to

each otherB) The INS is a strap down system with 3 accelerometers mounted 90 to

each other

C) The IRS is a strap down system with 2 accelerometers mounted 90 to

each otherD) The INS is a strap down system with 2 accelerometers mounted 90 to

each other


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220.The purpose of the flux-valve is:

A) to measure the strength of the earth's magnetic field.B) to align the spokes with the earth's magnetic field in order to get

maximum voltage from the pick-up coils.

C) to provide flux for the automatic slaving system.D)to sense the direction of the earth's magnetic field relative to the

airplane.

221.A DGI has:

A) one degree of freedom & a vertical spin axis.

B) one degree of freedom & a horizontal spin axis.

C) two degrees of freedom & a vertical spin axis.D)two degrees of freedom & a horizontal spin axis.

222.The case of an air driven turn and balance indicator is leaking. A rate 1 turn of 360 will

take:

A) Two minutes exactlyB)Less than two minutes

C) None of the aboveD) More than two minutes

223.In a Gyro magnetic Compass the flux gate transmits information to the:

A) heading indicator.

B)error detector.

C) erecting system.D) amplifier.

224.Typical directional gyro indicator errors are:

A) instrument error, synchro error and wandering errors.

B) parallax errors and gimballing errors.

C) gimballing errors, position error and friction error.D)random wander, gimballing errors and apparent wander due to earth'srotation.


50/160

225.The flux valve in a RIMC:

A) has its own self exciter unit.B)is supplied with AC current.

C) is fed with DC current.

D) is made of hard-iron magnetic steel.

226.The sustained oscillation in the Ring Laser Gyro (RLG) is initially caused by:

A) the spontaneous return of photons to a higher energy level, which in turn

produces, excited neon atoms.B) the corner mirrors, which reflect the radiation energy, back to the

photons.

C)the gas (or plasma) inside the triangular cavity is ionised by the voltage,causing helium atoms to collide with and transfer energy to the neon

atoms.D) the pressure fluctuation in the high pressure mixture of helium and neon

gases in the triangular cavity.

227.What indications should you get from the turn-and-slip indicator during taxi?

A) the ball stays fixed in the centre position during the turn, and the needledeflects in the direction of the turn

B)the ball moves freely opposite the turn, and the needle deflects in the

direction of the turnC) the ball stays fixed in the centre position during the turn, and the needle

deflects in the opposite direction of the turnD) the ball moves freely in the direction of the turn, and the needle deflects

in the opposite direction of the turn

228.In a Slaved Gyro Compass System the output of the flux-valve is fed to:

A)the stator in the slaved gyro control.B) the slaving torque motor directly.

C) to the indicator.

D) to the power supply of the gyro unit.


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229.An INS with the accelerometers aligned N/S and E/W is limited to use at latitudes below

about 82 . This is because:

A) the correction for the Coriolis effect of earth rotation approaches infinityabove 82 lat

B)the functions of Secant Latitude and Tangent Latitude used for certaincorrections in the computer start to approach infinity and the computer

cannot handle the rapid changes involvedC) it loses horizontal reference as dip becomes largeD) at high speed on East or West tracks the rate of convergence is faster

than the azimuth motor can correct

230.The corrections fed to the platform gimbal motors of a north referenced inertial navigation

system during the ALIGN mode use inputs from:

A)the latitude setting, the accelerometersB) all the aboveC) the latitude setting, the longitude setting, the accelerometers

D) the longitude setting, the latitude setting, the air data computer

231.Erection systems are provided for the purpose of:

A)Erecting and maintaining the gyro in its vertical positionB) Aligning a directional gyro in its horizontal position

C) Aligning a directional gyro in its vertical position

D) Erecting and maintaining the gyro in its horizontal position

232.A directional gyro is:

a gyroscope free around two axis

a gyroscope free around one axis

capable of self- orientation around an earth-tied direction

incapable of self-orientation around an earth-tied direction

A) 2 - 4.B) 1 - 3.

C) 2 - 3.D)1 - 4.


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233.What is the Schuler period?

A) 21 minutes.B) 63 minutes.C)84 minutes.

D) 1 oscillation in azimuth.

234.Alignment of a RLG INS takes:

A) 84.4 minutes

B) 10 - 15 minutesC)Less than 10 minutes

D) 15 - 20 minutes

235.A longitude error in an INS will cause:

A) Will cause no problems at all

B) Will be corrected for once the E/W accelerometer has aligned to truenorth

C) A failure to alignD)Poor alignment and degraded accuracy

236.The control and display unit of an inertial navigation system indicates a position of 4810.9

N 00012.2 W on a ramp position 4807.5 N 00005.1 E. What is the radial error rate of the

system if it has been in NAV mode for 8 hours 20 minutes:

A)1.37 NM/hr

B) 14.3 NM/hrC) 11.42 NM/hr

D) 1.37 Km/hr

237.The directional gyro keeps its rotation axis aligned toward:

A) a point in space.

B) a point on the Earth's surface.

C) geographic North.D)magnetic North.


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238.What is the main cause of precession?

A)Bearing friction.B) Magnetic variation.

C) The Earth's rotation.

D) Magnetic declination.

239.The term 'toppling', when applied to gyros is:

A) gyroscopic precession.

B) real wander and apparent wander.C)wander in the vertical plane.

D) wander in the horizontal plane.

240.Deviation compensation in a flux gate compass is done:

A) By the pilot

B) Both mechanically and electronicallyC)Mechanically

D) Electronically

241.The acceleration errors of en electrical artificial horizon are reduced compared to those of

an air driven one by:

A)designing the gyro so that it is not pendulous

B) reducing the erection rate of the gyro assemblyC) the use of compensation stilts

D) spinning the electrical rotor slower

242.The maximum drift error sensed by an uncompensated DGI will be:

A) 30 deg per hour.

B) 45 deg per hour.C) 60 deg per hour.

D)15 deg per hour.


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243.A DGI is assumed to be frictionless. Its latitude nut is set for 56 N. The reading that you

would expect to see after flying West along the parallel of 48 N for 45 minutes at a TAS of 480

kts with a Wind velocity of 090/60 would be:

A) 261.3

B) 281.3C)278.5

D) 277.6

244.At a low bank angle, the measurement of rate-of-turn actually consists in measuring the :

A) angular velocity of the aircraftB) pitch rate of the aircraft

C) roll rate of the aircraftD)yaw rate of the aircraft

245.The compass heading can be derived from the magnetic heading by reference to a:

A) map showing the isoclinic linesB) deviation correction curveC)compass swinging curveD) map showing the isogonic lines

246.The quadrantal deviation of the magnetic compass is due to the action of:

A) the hard iron pieces and the soft iron pieces influenced by the hard ironpieces

B) the hard iron pieces influenced by the mild iron piecesC) the hard iron pieces influenced by the geomagnetic fieldD)the soft iron pieces influenced by the geomagnetic field

247.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) 170B)210C) 190

D) 150


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248.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) 190C) 170

D) 200

249.A pilot wishes to turn right 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


A) 015

B) 355

C)030D) 330

250.The quadrantal deviation of a magnetic compass is corrected by using:

A) pairs of permanent magnets

B) hard iron piecesC)soft iron pieces

D) magnetized needles

251.The purpose of compass swinging is to determine the deviation of a magnetic compass:

A) on a given heading

B)on any headingC) at a given latitude

D) at any latitude

252.In the northern hemisphere, during deceleration following a landing in an Easterly direction,

the magnetic compass will indicate:

A) a heading fluctuating about 090B) a constant headingC)an apparent turn to the South

D) an apparent turn to the North


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253.The magnetic heading can be derived from the true heading by means of a:

A) map showing the isoclinic linesB) deviation correction curve

C) compass swinging curve

D)map showing the isogonal lines

254.When turning onto a northerly heading the rose of a magnetic compass tends to

"undershoot"; when turning onto a southerly heading it tends to "overshoot":

1 these compass indications are less reliable in the northern hemisphere than in the southern

hemisphere

2 these compass oscillations following a lateral gust are not identical if the aircraft is heading

north or south

3 this behaviour is due to the mechanical construction of the compass

4 this behaviour is a symptom of a badly swung compass


A)2, 3

B) 2, 3, 4C) 1, 2, 4

D) 1, 3

255.Among the errors of a magnetic compass, are errors:

A) of parallax, due to oscillations of the compass rose

B)in North seeking, due to bank angle and magnetic headingC) due to cross-wind gusts particularly on westerly or easterly headings

D) due to Schler type oscillations

256.The purpose of a compass swing is to attempt to coincide the indications of:

A) compass north and lubber line

B) compass north and true northC)compass north and magnetic north

D) true north and magnetic north


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257.In a steep turn, the northerly turning error on a magnetic compass on the northern

hemisphere is:

A) equal to 180 on a 270 heading in a right turnB) none on a 270 heading in a left turn

C)equal to 180 on a 090 heading in a right turnD) none on a 090 heading in a right turn

258.Magnetic compass swinging is carried out to reduce as much as possible:

A)deviationB) regulation

C) variationD) acceleration

259.A flux valve senses the changes in orientation of the horizontal component of the earth's

magnetic field.

1 the flux valve is made of a pair of soft iron bars

2 the primary coils are fed A.C. voltage (usually 487.5Hz)

3 the information can be used by a "flux gate" compass or a directional gyro

4 the flux gate valve casing is independent on the aircraft three inertial axis

5 the accuracy on the value of the magnetic field indication is less than 0.5%


A) 1, 4, 5

B) 3, 5C) 1, 3, 4, 5D)2, 3, 5

260.A pilot wishes to turn right on to a northerly heading with 20 bank at a latitude of

40North. Using a direct reading compass, in order to achieve this he must stop the turn on to an


A) 350B) 010

C)330D) 030


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261.In the Northern hemisphere, during deceleration following a landing in a Westerly direction,


A) an apparent turn to the NorthB)an apparent turn to the South

C) a heading fluctuating about 270D) no apparent turn

262.In the Southern hemisphere, during deceleration following a landing in a Westerly direction,


A) a heading fluctuating about 270B) an apparent turn to the SouthC)an apparent turn to the North

D) no apparent turn

263.During deceleration following a landing in Northerly direction, the magnetic compass will

indicate:

A) a heading fluctuating about 360B) an apparent turn to the WestC)no apparent turn

D) an apparent turn to the East

264.The fields affecting a magnetic compass originate from:

1 magnetic masses

2 ferrous metal masses

3 non ferrous metal masses

4 electrical currents


A) 1, 3, 4

B) 1, 2, 3, 4C) 1, 2, 3

D)1, 2, 4

\


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265.In the Southern hemisphere, during deceleration following a landing in a Easterly direction,


A) an apparent turn to the SouthB) no apparent turn

C) a heading fluctuating about 090D)an apparent turn to the North

266.An aircraft takes-off on a runway with an alignment of 045. The isogonic line on the area

chart indicates 0. The compass deviation is 0. On a take-off with zero wind, the northerly

turning error:

A)is such that the compass will indicate a value noticeable below 045B) will be nulC) is such that the compass will indicate a value noticeable above 045

D) will be nul if the wings are kept level

267.During deceleration following a landing in a Southerly direction, the magnetic compass will

indicate:

A) an apparent turn to the West

B) an apparent turn to the EastC) a heading fluctuating about 180

D)no apparent turn

268.Variation is defined as the angle between:

A)TN and MN.

B) MN and CN.C) TN and CN.

D) CN and the longitudinal axis of the aircraft.

269.A compass swing is used to:

A) get true north and lubber line aligned.

B) align compass north with true north.C) align magnetic north with true north.D)align compass north with magnetic north.


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270.In a standby direct reading compass there is:

A) a non-pendulously mounted magnet system.B) a low magnetic moment system, either of circular or bar configuration.

C) a single pendulously mounted bar magnet.

D)a circular magnet or pair of bar magnets pendulously mounted.

271.What should be the indication on the magnetic compass when rolling into a standard rate

turn to the right from a south heading in the Northern Hemisphere?

A)The compass will indicate a turn to the right, but at a faster rate than isactually occurring.

B) The compass will indicate the approximate correct magnetic heading ifthe roll into the turn is smooth.

C) The compass will remain on south for a short time, then gradually catch

up to the magnetic heading of the airplane.D) The compass will indicate a turn to the left.

272.Aircraft magnetism:

A) varies with aircraft heading and latitudeB)varies with latitude but does not vary with aircraft headingC) does not vary with aircraft heading or latitude

D) does not vary with aircraft latitude but does vary with aircraft heading

273.The directive force of the earth's magnetic field:

A) increases as the magnetic variation increases.

B) increases as magnetic latitude increases.C)is greatest at the magnetic equator.

D) varies with the heading of the aircraft.

274.The purpose of the Annunciator unit of the Remote Indicating compass is to:

A) advise if the gyro is subject to excessive wander

B) show whether the compass is operating either in the GYRO or COMPASSmodeC)indicate that the gyro is synchronised with the detector unit

D) display the serviceability of the compass


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275.When turning from 060 to 320 in the Northern Hemisphere the direct reading compass

will .... (i) causing an .... (ii) indication of the turn. Liquid Swirl will .... (iii) the error:

A) (i) under read (ii) over (iii) increaseB)(i) over read (ii) under (iii) increase

C) (i) under read (ii) over (iii) decreaseD) (i) over read (ii) under (iii) decrease

276.In the Northern Hemisphere, a magnetic compass will normally indicate a turn towards

North if:

A) a right turn is entered from an east heading.B) a left turn is entered from a west heading.C)an aircraft is accelerated while on an east or west heading.

D) an aircraft is decelerated while on an east or west heading.

277.Which of the following statements are correct:

A) Dip is proportional to HB)Dip is inversely proportional to H

C) Dip decreases with increased in latitudeD) Dip is inversely proportional to Z

278.An aircraft turns left from 045 to 315 in the Southern Hemisphere. The magnets turn (i)

.... and liquid swirls (ii) ... causing an error.

A) (i) anti-clockwise (ii) clockwiseB)(i) clockwise (ii) anti-clockwise

C) (i) clockwise (ii) clockwiseD) (i) anti-clockwise (ii) anti-clockwise

279.If the CH = 220 , var. = E12, dev. = W2, what is the corresponding TH?

A) TH = 206 .B) TH = 210 .

C)TH = 230 .D) TH = 234 .


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280.The deviating effect of vertical soft iron .... (i) with decrease of magnetic latitude, due to the

.... (ii) of H and the .... (iii) of Z:

A) (i) increases (ii) decrease (iii) increaseB) (i) decreases (ii) increase (iii) increase

C) (i) increases (ii) decrease (iii) decreaseD)(i) decreases (ii) increase (iii) decrease

281.When accelerating on a westerly heading in the Northern Hemisphere the needle of the DIC

will:

A) Turn clockwise giving an apparent turn towards southB)Turn anti-clockwise giving an apparent turn towards north

C) Turn clockwise giving an apparent turn towards north

D) Turn anti-clockwise giving an apparent turn towards south

282.An aircraft is fitted with a direct reading magnetic compass. Upon landing in a northerly

direction the compass will indicate:

A) a turn towards East.B) an oscillation to its North alignment.C) a turn towards West.

D)no change.

283.With reference to the flux valve of a remote indicating compass:

A)the flux valve is fixed to the aircraft and so turns with the aircraft tomeasure the angle between the aircraft and the earth's magnetic field.

B) the flux valve is pendulously mounted and so it is not subject to oraffected by the earth's magnetic field.

C) the flux valve is not subject to acceleration errors.D) the flux valve is pendulously mounted and is free to turn to remain

aligned with the earth magnetic field.

284.During a sustained turn... the nearer magnetic pole, the effect of liquid swirl will... compass

turning error.

A)towards; increase.

B) away from; not affect.C) away from; increase.D) towards; not affect.


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285.The principal advantage of a gyromagnetic compass (slaved gyro compass) is:

A) None of the aboveB)It combines the north-seeking ability of the magnetic compass with the

stability of the direction indicator

C) It does not have to be aligned with the northD) It does not precess

286.A remote indicating compass has usually less deviation error than a panel mounted compass

because:

A) the indication system consists of toroidal-wound coils forming a

Magnesyn system with little interference.B) it is carrying a well damped floating magnet.

C) it receives a higher flux-density from the earth's magnetic field.

D)it is normally mounted in a part of the airplane where magneticinterference is minimal.

287.In a standby compass the magnet system is immersed in a transparent liquid. The purpose of

this liquid is to:

A) increase sensitivity, reduce liquid swirl.

B) increase sensitivity at high latitudes, lubricate bearings.C)increase sensitivity, increase aperiodicity.

D) increase sensitivity, decrease aperiodicity.

288.The " sensor part" of the flux-valve is:

A) Separate GPS signal receiverB)The three pick-up coilsC) The two pick-up coils

D) Separate electronic magnetic compass

289.In the Southern hemisphere, during deceleration following a landing in an Easterly

direction, the magnetic compass will indicate :

A) a heading fluctuating about 090.B)an apparent turn to the North.C) no apparent turn.

D) an apparent turn to the South.


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290.During the approach, a crew reads on the radio altimeter the value of 650ft. This is an

indication of the true:

A) height of the aircraft with regard to the runwayB) altitude of the aircraft

C) height of the aircraft with regard to the ground at any timeD)height of the lowest wheels with regard to the ground at any time

291.The operating frequency range of a low altitude radio altimeter is:

A)4200MHz to 4400MHzB) 5400MHz to 9400MHz

C) 2700MHz to 2900MHzD) 5GHz

292.The low-altitude radio altimeters used in precision approaches:

1 operate in the 1540- 1660MHz range

2 are of the pulsed type

3 are of the frequency modulation type

4 have an operating range of 0 to 5000ft

5 have a precision of +/-2 ft between 0 and 5000ft


A) 3, 4B) 1, 2, 5

C) 2, 3, 4D)3, 5

293.The data supplied by a radio altimeter:

A)indicates the distance between the ground and the aircraftB) concerns only the decision heightC) is used only by the radio altimeter indicatorD) is used by the automatic pilot in the altitude hold mode

294.Modern low altitude radioaltimeters emit waves in the following frequency band:

A)SHF (Super High Frequency)B) HF (High Frequency)

C) VLF (Very Low Frequency)D) UHF (Ultra High Frequency)


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295.For most radio altimeters, when a system error occurs during approach the...

A) DH lamp flashes red and the audio signal soundsB) Audio warning signal sounds

C) DH lamp flashes red

D)Height indivation is removed

296.The Decision Height (DH) warning light comes on when an aircraft:

A)descends below a pre-set radio altitude

B) passes over the ILS inner markerC) descends below a pre-set barometric altitude

D) passes over the outer marker

297.The operation of the radio altimeter of a modern aircraft is based on:

A)frequency modulation of the carrier wave

B) pulse modulation of the carrier waveC) a combination of frequency modulation and pulse modulation

D) amplitude modulation of the carrier wave

298.A radio altimeter can be defined as a:

A) ground radio aid used to measure the true height of the aircraftB)self-contained on-board aid used to measure the true height of the

aircraftC) 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

299.In low altitude radio altimeters, the height measurement (above the ground) is based upon:

A) a pulse transmission, for which time between transmission and receptionis measured on a circular scanning screen

B) a wave transmission, for which the frequency shift by DOPPLER effect

after ground reflection is measuredC)a frequency modulation wave,

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Instrument Question Bank