Instrumentation Test Astana +

Rate of turn is affected by: 1. Aircraft speed 2. Angle of bank 3. Aircraft weight. 1 & 2. None of the above. 2 & 3. 1 & 3.

Which of the following correctly describes the gyroscope of a rate of turn indicator? 1. 1 degree of freedom 2. 2 degrees of freedom 3. Its frame is held by two springs 4. Its spin axis is parallel to the pitch axis 5. The spin axis is parallel to the yaw axis 6. The spin axis is horizontal. 1, 3 & 6. 1 & 2. 1, 4 & 5. 1, 3 & 5.

Why must an autopilot be synchronized when you wish to disconnect?. To allow automatic pitch trimming to reset. To secure against abrupt changes in aircraft attitude. To ensure fail-operational landings can continue safely. To allow for FD coupling.

To improve the horizontality of a compass, the magnet assembly is suspended from a point. Varying with magnetic latitude. Below the centre of gravity. On the centre line of the magnet. Above the centre of gravity.

An aircraft is descending at a constant Mach number. If the aircraft is descending through an inversion layer, the CAS will: Decrease. Increase. Remain constant. Decrease then decrease more slowly.

Concerning a fuel gauge system, the most relevant fuel parameter is: Density. Mass. Volume. Permittivity.

During an autoland the caption LAND 2 is illuminated. The system is: Fail-passive. Fail-active or fail-operational. Requiring a crew input. Approaching decision height.

In a turbine engine, what is the parameter N1, which is used to represent thrust?. NI refers to the rotational speed of the high speed spool which consists of the high pressure compressor and the high pressure turbine. N1 refers to the rotational speed of the low speed spool which consists of the fan, the low pressure compressor and the low pressure turbine. N1 is the ratio of the turbine discharge and the compressor inlet pressure. The indication is usually calibrated in percent RPM.

On a turn and slip indicator, needle to the left and ball to the right indicates: Left turn too much bank. Right turn not enough bank. Left turn not enough bank. Right turn too much bank.

For a capacitance type fuel indication system what indication would you expect in case of failure?. A sudden full deflection of the fuel gauge towards empty. A red flag in the gauge. A progressive deflection of the gauge to full. A frozen fuel level indication.

The ability of a gyroscope to indicate aircraft heading is based on it having: One degree of freedom in the vertical axis. Two degrees of freedom in the horizontal. One degree of freedom in the horizontal. Two degrees of freedom in the vertical axis.

An IRS differs from an INS in that it: Has a longer spin-up (is not affected by vertical accelerations due to gravity). Does not experience Schuler errors as accelerometers are strapped down and not rotated by a feedback loop. Has a shorter spin-up time and suffers from laser lock. Does not need to correct for coriolis and central acceleration).

Which of the following are modes of the GPWS? 1. Excessive sink rate 2. Altitude loss after take-off or go-around 3. Excessive glide slope deviation 4. High climb rate 5. Flaps in the incorrect position 6. High altitude descent 7. Stall. 3, 4, 5 & 6. 2, 3, 5 & 7. 1, 2, 3 & 5. 1, 2, 3 & 7.

The usual sequence of events for an ILS is to capture the LOC before the G/S. Many modern systems automatically inhibit the G/S from engaging until the LOC is engaged. Arming the APPROACH mode well above the normal G/S intercept altitude can lead to?. An increase in altitude. An airspeed reduction. A false glide path. A premature descent.

In a Schuler tuned INS, the largest unbounded errors are: Due to acceleration errors. Track errors due to initial misalignment. Created at the first stage of integration. Due to real wander of the platform gyroscopes.

What are the advantages of an IRS compared to an INS?. Reduce spin-up time and accuracy not adversely affect by "g". Increase accuracy and a dither motor to prevent "lock-out". Reduce spin-up time and a dither motor to prevent "lock-out". Insensitively to "g" and reduced wander of the gyroscope.

What errors can the Air Data Computer correct for? 1. Instrument error & ram rise 2. Compressibility & density error 3. Lag & density error 4. Position & temperature error 5. Temperature & instrument error 6. Manoeuvre error & ram rise 7. Manoeuvre & position errors. 3 & 7. 2 & 4. 3 & 5. 1 & 6.

Which of the following is the FMS normal operating condition in the cruise?. V NAV only. L NAV and V NAV. L NAV or V NAV. L NAV only.

The period of validity of an FMS data base is: 56 days. varies depending on the area of operational cover. 28 days. one week.

Can an FMS receive position inputs from the GPS system, if installed?. Yes. No, GPS is considered too inaccurate and unsecure for this. Yes but only for horizontal position data, not vertical position data. Yes, but only if a dual GPS system is installed.

In a solid state gyroscope the purpose of the dither motor is to: Overcome laser lock. Compensate for transport wander. Enhance the acceleration of the gyro at all rotational rates. Stabilize the laser frequencies.

What would the compass heading be given a true heading of 247° in an area where the variation is 8°W and a compass deviation of 11°E?. 266°. 244°. 255°. 247°.

Hydraulic pressure for flight deck indications is measured by: A diaphragm connected to an accumulator. A transducer connected to an indirect indicator. An aneroid capsule connected to a direct indicator. A bellows connected to a bourdon tube.

What are the colours used on an EFIS display to show a tuned navigation aid and an airport?. Green & cyan. Green & white. White & yellow. White & magenta.

What is used for EGT measurement?. Helical bimetallic strips. Thermistors. Radiation pyrometry. Thermo EMF thermocouples.

What must the pilot be particularly careful about in the current situation?. The autopilot could capture the localiser before the glideslope and commence a turn outside of the protected area. The flight director is in heading mode, but the autopilot is in VOR/LOC. The autopilot could capture the glideslope before the localiser and commence descent outside of the protected area. The flight director is in VOR/LOC, but the autopilot is in heading mode.

How is the reading of the Airspeed Indicator (ASI) affected when ice blocks the static air ports?. The Airspeed Indicator shows an increase in speed with a decrease in altitude. The Airspeed Indicator no longer indicates any change in speed. The Airspeed Indicator shows a decrease in speed with a decrease in altitude. The on board emergency system switches automatically to the standby static pressureport.

The rigidity (gyroscopic interia) of a gyroscope may be increased by: Increasing the speed of rotation and increasing the mass of the rotor. Decreasing the speed of rotation and increasing the speed of the rotor. Increasing the speed of rotation and decreasing the mass of the rotor. Increasing the number of gimbals and decreasing the number of planes of rotation.

The local speed of sound at mean sea level at ISA -10°C is: 680 kt. 661 kt. 673 kt. 650 kt.

The angle formed between the directive force and the total magnetic force is called: Isoclinal. Variation. Deviation. Dip.

The rate of turn indicator is a very useful gyroscopic instrument. When used in conjunction with the attitude indicator it provides: Rate of turn about the yaw axis. Angle of bank. Rate of climb. Rate of turn athwartships.

A jetengine vibration meter is indicating 4. What is the unit of this indication?. Hz. No units are specified. hPa. m/s.

At 200 ft on an autoland: The ROLL OUT mode is engaged in the Roll channel and the G/S mode is engaged in pitch. The LOC mode is engaged in the roll channel and the G/S mode is engaged in pitch. The LOC mode is engaged in the roll channel and the FLARE mode is engaged in the pitch channel. The autothrottle is maintaining the speed and the pitch channel is maintaining the height.

Given the following, which formula is correct? P = engine power T = torque n = RPM TAS = true airspeed GS = ground speed. P=T/n. P=T x n. P=T x TAS. P=T x GS.

An autopilot delivers roll commands to the ailerons to achieve a bank angle: Set bank of 30 degrees. Set bank of 25 degrees. Proportional to the deviation from the desired heading, but not exceeding a specified maximum. Proportional to TAS, but below a specified maximum.

Concerning the thrust measurement, the N1 is defined as the: First stage compressor speed. High pressure shaft speed. Low pressure shaft speed. Second stage compressor speed.

The true altitude of an aircraft in flight is shown from: Pressure altitude. Temperature altitude. The standard atmosphere. Density altitude.

The measurement of the turbine temperature or of the EGT is carried out at the: Outlet of the combustion chamber. Outlet of the high pressure stage of the turbine. Inlet of the high pressure chamber. Inlet of the combustion chamber.

If only a single A/P is used to climb, cruise and approach, following a failure: It is fail-passive with redundancy. It is fail-operational and will not disconnect. It is fail-safe and will disconnect. It is fail-soft and will not disconnect.

An aircraft that is assessed as not being a threat would be indicated on a TCAS system as: A solid white or cyan diamond. A hollow white or cyan diamond. A solid yellow circle. A solid red square.

If a constant CAS is maintained under normal conditions in the climb what happens to the Mach No ?. It will decrease in an isothermal layer. It will decrease. It will increase. It will remain constant.

You are flying at a constant FL290 and constant Mach number. The total temperature increases by 5°. The CAS will: Increase by 10 kt. Decrease by 10 kt. Remain approximately constant. Will increase or decrease depending on whether you are above or below ISA.

If the total pressure sensor supply line leaks, and with the drain element blocked, in a non-pressurized aircraft this will cause the ASI to: Under-read in the climb and over-read in the descent. Over-read. Under-read. Over-read in the climb and under-read in the descent.

An aircraft maintaining a constant CAS and altitude is flying from a cold airmass into warmer air. The effect of the change of temperature on the speed will be: EAS will decrease. TAS will increase. CAS will increase. TAS will decrease.

The gravity erecting device on a vertical gyro is used on which instrument?. Artificial horizon. Directional gyro unit. Turn indicator. Gyromagnetic device.

Which of the following parameters, as an input to the Air Data Computer, is used for calculating TAS?. Static Air Temperature. True Altitude. Density Altitude. Total Air Temperature.

To obtain heading information from a gyro stabilized platform, the gyros should have: 2 degrees of freedom and a vertical axis. 1 degree of freedom and a horizontal axis. 1 degree of freedom and a vertical axis. 2 degrees of freedom and a horizontal axis.

In what range is GPWS operative?. 3000 - 0 ft. 2450 - 0 ft. 3000 - 50 ft. 2450 - 50 ft.

A factor giving an error on a direct indicating compass would be: Parallax due to oscillations of the compass rose. Crosswinds - particularly on east/west headings. Turning through east/west headings. Acceleration on east/west headings.

Regarding magnetism, which of the following statements is correct? 1. Lines of flux run from blue pole to red pole 2. Like poles repel 3. Unlike poles repel 4. Like poles attract 5. Unlike poles attract. 1, 3 & 4. 1, 2 & 5. 1, 3 & 5. 2 & 5.

Using a classic attitude indicator, an aircraft performs a turn through 270° at a constant angle of bank and rate of turn. The indication is: Nose up bank left. Bank and pitch correct. Nose up wings level. Nose up bank right.

Under conditions determined by the International Standard Atmosphere, at MSL true airspeed: Equals CAS. Is less than CAS. Is indeterminate due to the variation in temperature. Is greater than CAS.

During a CAT I ILS approach, height is indicated by: Marker. GPS. Barometric. Radio altimeter.

When the autothrust part of the flight guidance system is in speed mode, the thrust is: Constant in order to maintain the target engine speed for a given thrust setting. Constant in order to maintain the best rate of climb speed. Varied in order to maintain a selected vertical airspeed. Varied as required to maintain the selected airspeed or Mach number.

An aircraft that is assessed as Proximate Traffic would be indicated on a TCAS system as: . .

A solid state gyro is: An earth gyro. A tied gyro. A rate sensor. A rate gyro.

The magnetic heading reference unit has a precession rate of: 3°/min. 1°/min. 5°/min. 2°/min.

A flight is performed with a higher Cost Index at a given mass. Which of the following will occur?. A better maximum range. A lower cruise Mach number. A higher cruise Mach number. A better long range.

With the aircraft weight constant but variations in airfield altitude, take-off will always be at a constant: Calibrated airspeed. Equivalent airspeed. Ground speed. True airspeed.

What correction is given by TCAS?. Contact ATC on receipt of a resolution advisory. Climb or descend at 500 ft/min. Climb or descend. Turn left or right.

The EADI and the EHSI of an EFIS installation are also referred to by the manufacturers as: Navigation display and primary display respectively. EICAS and ECAM respectively. Primary display and navigation display respectively. ECAM and EICAS respectively.

WXR display is on: A special screen. The captain's CRT only. On both the captain's and co-pilot's CRTs. The co-pilot's CRT only.

Which of the following will affect a direct reading compass? 1. Ferrous metals 2. Non-ferrous metals 3. Electrical equipment. 1 & 3. all 3. 1 only. 1 & 2.

When accelerating on a northerly heading what does the direct reading magnetic compass indicate?. North. A turn to the west. A turn to the east. No change.

Where an alternate static source is fitted, use of this source usually leads to: No change in position error. A temporary increase in lag error. An increase in position error. A lower pressure error than with normal sources.

On an electronic attitude director indicator (EADI) radio altitude is displayed: Digitally between 2500 ft and 100 ft. Digitally between 2500 ft and 1000 ft and thereafter as an analogue/digital display. On an analogue scale below 2500 ft. As an analogue display between 2500 ft and 1000 ft and thereafter as a digital display.

If the RPM of the rotor in a turn and slip indicator is higher than normal, the turn indicator will: Indicate correctly. Under-read the correct rate of turn. Not indicate due to the increased rigidity. Over-read the correct rate of turn.

An aircraft fly into a colder airmass. This will cause the altimeter to: Under-read. Over-read. The indication will depend on the hemisphere of operation. Read the correct altitude.

An aircraft is travelling at 120 kt, what angle of bank would be required for a rate one turn?. 12°. 30°. 35°. 19°.

The outputs of a flux valve are initially sent to: A compass card. An error detector. An amplifier. A feedback loop.

Which of the following are inputs to the central processing unit of the GPWS? 1. Flaps 2. Landing gear 3. Glide slope 4. Unusual attitudes 5. Radio altimeter 6. VOR. 1, 2 & 6. 1, 2, 3, 4 & 5. 1, 2, 3 & 5. 1, 2, 4 & 5.

Why is there a vibration device in a pressure altimeter? 1. To prevent hysteresis 2. To prevent lag in a mechanical system 3. To keep pilots happy during long flights 4. To prevent icing 5. To overcome dither. 2, 3 & 5. 1, 2 & 4. 1, 2 & 3. 1 & 2.

The rigidity of a gyroscope can be improved by: Decreasing the angular momentum and concentrating the mass on the periphery of the rotor. Increasing the angular momentum and concentrating the mass on the periphery of the rotor. Increasing the angular momentum and concentrating the mass at the hub of the rotor. Decreasing the angular momentum and concentrating the mass at the hub of the rotor.

With reference to the flux valve of a remote indicating compass: The flux valve is fixed to the aircraft and so turns with the aircraft to measure the angle between the aircraft and the earth's magnetic field. The flux valve is pendulously mounted and so it is not subject to or affected by the earth's magnetic field. The flux valve is pendulously mounted and is free to turn to remain aligned with the earth magnetic field. The flux valve is not subject to acceleration errors.

The output of a double integration N/S is: Distance. Velocity. Longitude. Departure.

The errors associated with the directional indicator are: 1. Earth rate 2. Transport wander 3. Banking when pitched up 4. Annual movement of the poles 5. Mechanical problems. 1, 2 & 3. 1, 2, 3, 4 & 5. 1, 2, 4 & 5. 1, 2, 3 & 5.

Total air temperature is _____ than static air temperature and the difference varies with _____: Warmer CAS. Warmer altitude. Colder CAS. Colder altitude.

In an IRS: Accelerometers and gyros are both strapped down. The accelerometers are strapped down but the platform is gyro-stabilized. Accelerometers and gyros are both gyro-stabilized. The platform is strapped down but the accelerometers are gyro-stabilized.

An aircraft in the northern hemisphere lands and decelerates on a westerly heading. The compass will indicate: A turn south. No turn will be indicated. An oscillation. A turn north.

In FMS fitted aircraft the main interface between pilot and system will be provided by: The flight control unit. The flight management source selector. The multi-purpose control and display unit. The automatic flight control system.

A blockage occurs in the ram air source and the drain-hole. The ASI in a non-pressurized aircraft will: Act like an altimeter. Read a little high. Freeze at zero. Read a little low.

The purpose of the Flight Director (FD) is to... Give a visual indication of the Flight Mode Annunciator (FMA). Help the crew with attitude control and guidance tasks. Repeat the flight control orders of the opposite crew member. Enable the crew to cross-check autopilot orders.

What is density altitude?. The indicated altitude when the altimeter setting is set to, 1013hPa. Pressure altitude corrected for Total Air Temperature. Pressure altitude corrected for the prevailing temperature. Temperature altitude.

During descent through a block of airspace of constant temperature and while flying at a constant Mach No. will cause the CAS to: Decrease. Increase at a rate of 1.9871000 ft. Increase. Remain constant.

Sound is propagated at a velocity which is dependent upon: Static pressure. Density. Barometric pressure. Temperature.

The use of autopilot can lead to a loss of situational awareness and the comprehension of the implication of the used mode. How can you mitigate these risks?. Ask the colleague to take over. Apply Standard Operating Procedures and follow/respect the call-outs. Advise ATC as they will always assist you. Disconnect the AP and fly manually.

The combined Machmeter/ASI is subject to the following errors: Those of the machmeter only. Position, density, instrument, compressibility, manoeuvre induced. Instrument, pressure and temperature only. Instrument and compressibility only.

When measuring different pressures (low/med/high) which of the following has the three types of sensing devices in ascending order of pressure measurement? 1. Bourdon tube 2. Bellows type 3. Aneroid capsule. 3, 2 & 1. 1, 3 & 2. 1, 2 & 3. 2, 3 & 1.

An inertial reference system is aligned when turned on so as to: Establish magnetic north. Calculate the computed trihedron with reference to the earth. Establish true and magnetic north. Establish position relative to true and magnetic north.

The turn coordinator and ball of a turn coordinator are both to the left of the datum. This indicates: A right turn with too little bank. A right turn with too much bank. A left turn with too little bank. A left turn with too much bank.

A modern radio altimeter uses the frequency band: VHF 30 - 300 MHz. SHF 3000 MHz - 30 GHz. UHF 300 MHz - 3 GHz. HF 3 MHz - 30 MHz.

If an aircraft, fitted with a DRMC, takes off on a westerly heading, in the northern hemisphere, the DRMC will indicate: No turn. Oscillates about west. A turn to south. A turn to the north.

What does the white arc on a temperature scale indicate?. Normal operating temperature. Minimum temperature. Never exceed. Maximum start and acceleration temperature.

In an inertial-lead VSI the source of the most pronounced error is: Steep turn. Missed approach maneuver. Position. Instrument.

Altitude select and altitude hold are examples of: Inner loop functions in pitch. Interlocking functions. Manometric functions from the Air Data Computer. Outer loop functions in roll.

An aircraft taking off from an airfield with QNH set in the altimeter has both static vents blocked by ice. As the aircraft climbs away the altimeter will: Read the height of the aircraft above the airfield. Show only a very small increase in height. Read the airfield elevation. Indicate the aircraft height AMSL.

A rate integrating gyroscope is used in: 1. inertial attitude system 2. automatic flight control systems 3. inertial navigation systems 4. rate of turn indicators. 1 & 3. 1, 2, 3. 1, 3 & 4. 1 & 2.

If the TAS at 40000 ft is 450 kt the Mach No. is: 0.825. 0.815. 0.76. 0.784.

A gravity-erecting device is utilized in: A directional gyroscopic indicator. A turn and slip. A vertical speed indicator. An artificial horizon.

Given the following parameters, in a capacitance fuel gauge, the correct formula is: (A= area of plates, D = distance between plates, E = dielectric permittivity). Capacitance =E x D x A. Capacitance =E x A/D. Capacitance =A x D/E. Capacitance =E x D/A.

Given the following information calculate the instrument error of a preflight altimeter check: • Aerodrome elevation: 235 ft • Apron elevation: 225 ft • Height of altimeter above apron: 20 ft • Altimeter reading with QFE set 40 ft. +30 ft. +10 ft. +20 ft. +40 ft.

VLO is defined as: The maximum speed at which to fly with the landing gear retracted. The maximum speed at which the landing gear may be retracted or extended. The minimum speed at which to fly with the landing gear extended 1 Mark. The maximum speed at which to fly with the landing gear extended.

"LOC ARMED" lights up on the FMA part of the PFD, this means: Localizer beam captured. Localizer beam armed and awaiting capture. Localizer alarm is on. a/c is on localizer centre line.

An aircraft in the northern hemisphere makes an accurate rate one turn to the left. If the initial heading was 070°, after 20 seconds of the turn the direct reading magnetic compass should read. Less than 010°. 350°. Less than 350°. More than 010°.

On a standard 2-dot EHSI in the en route mode each dot represents: 10 NM. 2 NM. 5 NM. 1 NM.

A VMO/MMO alerting system contains a barometric aneroid capsule: And an airspeed capsule subjected to dynamic pressure. Which is subjected to static pressure and an airspeed capsule which is subjected to dynamic pressure. And an airspeed capsule subjected to static pressure. Which is subjected to dynamic pressure and an airspeed capsule which is subjected to static pressure.

Wind information can be displayed in an EFIS system in which of the following modes?. Full ILS full VOR map plan. Full nav full ILS map centre map. Map centre map plan full ILS. Plan map expanded ILS full VOR.

A radio altimeter is: Aircraft based and measures true altitude. Aircraft based and measures true height. Ground based and measures true altitude. Ground based and measures true height.

The EPR (Engine Pressure Ratio) is: The ratio of the turbine outlet total pressure to the compressor inlet total pressure. The ratio of the turbine outlet total pressure to the ambient total pressure. The difference between the compressor inlet total pressure and the turbine outlet total pressure. The ratio of the compressor outlet total pressure to the compressor inlet total pressure.

The definition of torque is: force x distance x RPM. force x distance / RPM. force / RPM. force x distance.

True heading can be converted into magnetic heading using a compass and: A map with isobars. A map with isoclinal lines. A map with isogonal lines. A deviation card.

Select the correct statement. EAS = IAS corrected for position error. EAS = CAS corrected for compressibility error. CAS = TAS corrected for density error. TAS = EAS corrected for compressibility error.

What is the speed of sound at 30000 ft and -40°C?. 661 kt. 595 kt. 562 kt. 590 kt.

In which of the following modes may information from the AWR be displayed? 1. Plan 2. Expanded ILS 3. Map 4. Full nav 5. Full ILS 6. Expanded NAV 7. Full VOR 8. Expanded VOR 9. Centre map. 2, 3, 5, 7 & 9. 1, 3, 7, 8 & 9. 2, 6, 8 & 9. 1, 2, 4 & 7.

Since this is a combination of both instruments, the Machmeter/ASI is subjected to the 5 errors mentioned above. In the ILS mode, one dot on the lateral deviation scale on the EHSI indicates: 2°. 2 NM. 1 NM. 1°.

Which answer is an expression of pressure?. Force per unit area. Force times area. Force per unit volume. Force per unit volume.

An aircraft is travelling at 100 kt forward speed on a 3° glide slope. What is its rate of descent?. 500 ft/sec. 500 ft/min. 250 ft/min. 300 ft/min.

What is another name for fail-active?. Fail-soft. Fail-safe. Fail-passive. Fail-operational.

The amber ALERT sign on an INS control and display unit: Illuminates steadily for 2 minutes before reaching the next waypoint. Starts flashing 2 minutes before reaching the next waypoint and goes out at 30 seconds to run. Illuminates steadily after passing a waypoint in manual mode, until the next leg is programmed in. Illuminates if power from the aircraft bus bar has been lost and the system is operating on standby battery.

During an approach to autoland at 1500 feet. Offline channels are manually engaged, flare mode is armed. Localizer is controlling the roll channel, off line channels are automatically engaged and flare mode is armed. Localizer is controlling the roll channel, stabilizer is trimmed nose up and roll out is armed. Provided both localizer and glide slope signals are valid LAND 3 will engage.

A compass swing is used to: Align compass north with magnetic north. Align magnetic north with true north. Align compass north with true north. Get true north and the lubber line aligned.