Vibration is indicated in the cockpit as ? [ Students VFR ]

Question 56-1 : A direct reading a frequency proportional to the speed of the motor inversely proportional to the speed of the motor

exemple 156 A direct reading. — Revised ecqb03 july 2016 ..the engine vibration monitoring on a turbojet engine indicates any vibration resulting from an imbalance on the rotation parts of the engine .the gas turbine aircraft engine vibration indicating system features include engine c s rotation frequency measurement with two independent measuring channels vibration level measurement with multiple engine mounted piezoelectric sensors using digital broadband filters on each vibration sensor or digital monitoring narrow band filters on c s main harmonics frequencies as well as a comparison of measured and extreme limits of vibration 'excessive vibration' and 'vibration limit' signals formed when limits are exceeded . 1029. no specific unit is displayed for a vibration monitoring system A direct reading.

Given .p = power.t = torque.omega = angular velocity.the correct relationship is ?

Question 56-2 : P = t x omega t = p x omega p = t² x omega t = p / omega

exemple 160 P = t x omega — P = t x omega

The magnitude of a torque is defined as ?

Question 56-3 : Force times its lever arm force times its moment force times its area force per unit of volume

exemple 164 Force times its lever arm. — Force times its lever arm.

The operating principle of an electronic torque meter is ?

Question 56-4 : As power is increased the torque shaft twists as power is decreased the torque shaft twists as power increases the torque shaft lengthens as power increases the torsion shaft shrinks

exemple 168 As power is increased, the torque shaft twists. — As power is increased, the torque shaft twists.

If the outside temperature at 35 000 feet is 40°c the local speed of sound is ?

Question 56-5 : 595 kt 247 kt 307 kt 686 kt

exemple 172 595 kt. — Admin .lss varies with the square root of absolute temperature .formula lss = 39 x square root of oat+273 .lss = 39 x square root of 233.lss = 595 kt 595 kt.

The error in altimeter readings caused by the variation of the static pressure ?

Question 56-6 : Position error barometric error instrument error hysteresis effect

exemple 176 Position error. — Variation of the static pressure near the source is known as position error .barometric error is caused by setting the wrong number in the altimeter window .instrument error is caused by the imperfections of manufacture .hysteresis errors are caused by the irregular elasticity of the capsule Position error.

If the static source of an altimeter becomes blocked during a descent the ?

Question 56-7 : Continue to display the reading at which the blockage occurred gradually indicate zero under read indicate a height equivalent to the setting on the millibar subscale

If the static source to an altimeter becomes blocked during a climb the ?

Question 56-8 : Continue to indicate the reading at which the blockage occurred over read under read by an amount equivalent to the reading at the time that the instrument became blocked gradually return to zero

exemple 184 Continue to indicate the reading at which the blockage occurred. — Continue to indicate the reading at which the blockage occurred.

If the static source to an airspeed indicator asi becomes blocked during a ?

Question 56-9 : Over read read zero continue to indicate the speed applicable to that at the time of the blockage under read

. 959.the asi is a sensitive differential pressure gauge which measures and promptly indicates the difference between pitot total pressure and static pressure total pressure static pressure = dynamic pressure .these two pressures are equal when the aircraft is parked on the ground in calm air .when the aircraft moves through the air the pressure on the pitot line becomes greater than the pressure in the static lines this difference in pressure is registered by the airspeed pointer on the face of the instrument .thus while descending the total pressure increases* and the static pressure from the static source does not your airspeed indicator will over read .*while descending density increases so total pressure increases

A leak in the pitot total pressure line of a non pressurized aircraft to an ?

Question 56-10 : Under read over read over read in a climb and under read in a descent under read in a climb and over read in a descent

exemple 192 Under-read. — .airspeed indicator asi .the asi is a sensitive differential pressure gauge which measures and promptly indicates the difference between pitot impact/dynamic pressure and static pressure these two pressures are equal when the aircraft is parked on the ground in calm air when the aircraft moves through the air the pressure on the pitot line becomes greater than the pressure in the static lines this difference in pressure is registered by the airspeed pointer on the face of the instrument which is calibrated in miles per hour knots nautical miles per hour or both . 980 ..airspeed indication on the airspeed indicator is .total pressure static pressure = dynamic pressure .therefore with a leak in the pitot total pressure line it is similar to a reduction of speed a reduction of the relative flow entering in the pitot tube the airspeed indicator will under read Under-read.

Machmeter readings are subject to ?

Question 56-11 : Position pressure error density error temperature error setting error

exemple 196 Position pressure error. — Admin .machmeter errors .mach number is proportional to the ratio of pitot pressure to static pressure ie to pt ps /ps and this is exaclty what the machmeter measures thus any non standard temperature or density do not affect the accuracy of the machmeter and the only error worth considering is the pressure position error in addition to the usually small instrument error .a mach meter can be considered accurate to within +/ 0 01 mach in the normal operating range or to within +/ 0 02 at the limits of that range Position pressure error.

Vno is the maximum speed ?

Question 56-12 : Not to be exceeded except in still air and with caution which must never be exceeded at which the flight controls can be fully deflected with flaps extended in landing position

exemple 200 Not to be exceeded except in still air and with caution. — Not to be exceeded except in still air and with caution.

Vne is the maximum speed ?

Question 56-13 : Which must never be exceeded not to be exceeded except in still air and with caution at which the flight controls can be fully deflected with flaps extended in landing position

exemple 204 Which must never be exceeded — Which must never be exceeded

Vlo is the maximum ?

Question 56-14 : Speed at which the landing gear can be operated with full safety flight speed with landing gear down speed with flaps extended in a given position cruising speed not to be exceeded except in still air with caution

exemple 208 Speed at which the landing gear can be operated with full safety. — Speed at which the landing gear can be operated with full safety.

The position error of the static vent on which the altimeter is connected ?

Question 56-15 : Mach number of the aircraft static temperature deformation of the aneroid capsule flight time at high altitude

exemple 212 Mach number of the aircraft. — .the pressure errors on a pitot/static systems vary with aircraft speed but specifically with mach number Mach number of the aircraft.

The density altitude is ?

Question 56-16 : The altitude of the standard atmosphere on which the density is equal to the actual density of the atmosphere the temperature altitude corrected for the difference between the real temperature and the standard temperature the pressure altitude corrected for the relative density prevailing at this point the pressure altitude corrected for the density of air at this point

exemple 216 The altitude of the standard atmosphere on which the density is equal to the actual density of the atmosphere. — .the density altitude is the altitude in the standard atmosphere at which prevailing density occurs meaning your real altitude from the effects of height temperature and humidity and is used to establish performance as it is a figure that expresses where your machine thinks it is as opposed to where it actually is The altitude of the standard atmosphere on which the density is equal to the actual density of the atmosphere.

The response time of a vertical speed detector may be decreased by adding a ?

Question 56-17 : Correction based on an accelerometer sensor bimettalic strip return spring second calibrated port

exemple 220 Correction based on an accelerometer sensor. — Admin .on a vertical speed indicator the pointer takes a few seconds to steady because of the time taken to build up a steady pressure difference on climb or descent there will also be a time lag on levelling out because of the time .to overcome the problem of lag the instantaneous vertical speed indicator i v s i incorporates an accelerometer sensor which responds quickly to a change of altitude .the figure below shows an ivsi at the beginning of a descent . 988.the piston in the vertical acceleration pump immediately rises in the cylinder and causes a temporary increase of pressure in the capsule the capsule expands and the pointer will give an instant indication of descent .as the initial acceleration is turned into a steady rate of descent the piston will slowly descend to its original position but by this time the correct differential pressure between the capsule and the case will have been set up and the correct rate of descent will continue to be shown Correction based on an accelerometer sensor.

The pressure altitude is the altitude corresponding ?

Question 56-18 : In standard atmosphere to the pressure ps prevailing at this point in ambiant atmosphere to the pressure ps prevailing at this point in standard atmosphere to the reference pressure ps in ambiant atmosphere to the reference pressure ps

exemple 224 In standard atmosphere, to the pressure ps prevailing at this point. — The altimeter is calibrated to standard atmosphere conditions .it is nothing more than a barometer which measures atmospheric pressure and relates it to the altitude at which that pressure is found in a standard atmosphere in a standard atmosphere the pressure at 5000 feet is 850 hpa so if the static pressure ps is 850 hpa the altimeter tells you that you are 5000 feet and this is your pressure altitude In standard atmosphere, to the pressure ps prevailing at this point.

The atmospheric pressure at fl 70 in a 'standard + 10' atmosphere is ?

Question 56-19 : 781 85 hpa 942 13 hpa 1 013 25 hpa 644 41 hpa

exemple 228 781.85 hpa. — Admin .7000 ft / 28 ft par hpa = 250 hpa.pressure at mean sea level msl in international standard atmosphere is 1013 25 hpa .1013 25 250 = 763 25.this answer is close to 781 85 hpa .lucastefanon .fl 70 ==> 770 hpa.true altitude .7x4x10= 280 ft.280/27=10 5 hpa.as it's warmer then must be added so .770+10 5= 780 5 which i think it's more precise value respect to the answer 781.85 hpa.

Sound propagates through the air at a speed which only depends on ?

Question 56-20 : Temperature temperature and the pressure pressure density

The velocity of sound at the sea level in a standard atmosphere is ?

Question 56-21 : 661 kt 1059 kt 644 kt 332 kt

exemple 236 661 kt. — Admin .the velocity of sound varies only with temperature .s = 39 x sqrt °kelvin.to get kelvin add 273 to the centigrade +15°c + 273 = 288°k.s = 39 x sqrt 288°k = 660 8 kt .sqrt square root 661 kt.

The limits of the yellow scale of an airspeed indicator are ?

Question 56-22 : Vno for the lower limit and vne for the upper limit vlo for the lower limit and vne for the upper limit vle for the lower limit and vne for the upper limit vfe for the lower limit and vne for the upper limit

exemple 240 Vno for the lower limit and vne for the upper limit. — Img1034. Vno for the lower limit and vne for the upper limit.

The limits of the green scale of an airspeed indicator are ?

Question 56-23 : Vs1 for the lower limit and vno for the upper limit vs0 for the lower limit and vno for the upper limit vs1 for the lower limit and vne for the upper limit vs1 for the lower limit and vlo for the upper limit

exemple 244 Vs1 for the lower limit and vno for the upper limit. — Img1034 Vs1 for the lower limit and vno for the upper limit.

The limits of the white scale of an airspeed indicator are ?

Question 56-24 : Vso for the lower limit and vfe for the upper limit vsi for the lower limit and vfe for the upper limit vso for the lower limit and vle for the upper limit vsi for the lower limit and vle for the upper limit

exemple 248 Vso for the lower limit and vfe for the upper limit. — Img1034.white scale vso to vfe fe from flap extended .green scale vs without flaps to vno .yellow scale vno to vne .red line vne speed of never exceed Vso for the lower limit and vfe for the upper limit.

The reading of a mach indicator is independent of ?

Question 56-25 : The outside temperature the static pressure the total pressure the differential pressure measurement

exemple 252 The outside temperature. — The mach number is a function of p s /s.where p = total pressure pitot .s = static pressure .indications on the mach indicator will vary with p s and p s which is the differential pressure measurement .tas will vary with temperature but not the mach indicator The outside temperature.

After an aircraft has passed through a volcanic cloud which has blocked the ?

Question 56-26 : Decreases steadily increases abruptly towards vne increases steadily decreases abruptly towards zero

exemple 256 Decreases steadily. — Franck .the asi air speed indicator is provided by the pitot and static vent the pitot is blocked so the asi is going to react like an altimeter Decreases steadily.

The principle of the mach indicator is based on the computation of the ratio ?

Question 56-27 : Pt ps /ps pt ps /pt pt/ps pt + ps /ps

exemple 260 (pt - ps)/ps — Admin .pt total pressure.ps static pressure.dynamic pressure = pt ps.mach number is proportional to dynamic pressure/static pressure (pt - ps)/ps

The mach number is the ?

Question 56-28 : True airspeed tas divided by the local speed of sound corrected airspeed cas divided by the local speed of sound indicated airspeed ias divided by the local speed of sound equivalent airspeed eas divided by the local speed of sound

exemple 264 True airspeed (tas) divided by the local speed of sound — True airspeed (tas) divided by the local speed of sound

Given . ts the static temperature sat . tt the total temperature tat . kr the ?

Question 56-29 : Tt = ts 1+0 2 m² tt = ts 1 0 2 m² tt = ts 1+0 2 kr m² tt = ts/ 1+0 2 kr m²

exemple 268 Tt = ts(1+0.2 m²) — Admin .this question is a little bit tricky .if you add the recovery coefficient to the formula you will have exactly the 'total temperature' without you only have an approximation Tt = ts(1+0.2 m²)

A blocked pitot head with a clear static source causes the airspeed indicator to ?

Question 56-30 : React like an altimeter read like a vertical speed indicator operate normally freeze at zero

exemple 272 React like an altimeter. — React like an altimeter.

Given .m is the mach number.ts is the static temperature.tt is the total ?

Question 56-31 : Ts = tt / 1+0 2 m² ts = tt 1+0 2 m² ts = tt 0 2 m² ts = tt/ 0 2 m²

exemple 276 Ts = tt /(1+0.2. m²) — Ts = tt /(1+0.2. m²)

The airspeed indicator of a twin engine aircraft comprises different sectors ?

Question 56-32 : Optimum climbing speed with one engine inoperative or vy speed not to be exceeded or vne minimum control speed or vmc maximum speed in operations or vmo

exemple 280 Optimum climbing speed with one engine inoperative, or vy — Optimum climbing speed with one engine inoperative, or vy

The mach number is ?

Question 56-33 : The ratio of the aircraft true airspeed to the sonic velocity at the altitude considered a direct function of temperature it varies in proportion to the square root of the absolute temperature the ratio of the indicated airspeed to the sonic velocity at the altitude considered the ratio of the aircraft conventional airspeed to the sonic velocity at the altitude considered

exemple 284 The ratio of the aircraft true airspeed to the sonic velocity at the altitude considered — Admin .mach number formula .m = tas/a. a= local speed sound The ratio of the aircraft true airspeed to the sonic velocity at the altitude considered

In an adc air data computer the altitude is computed from ?

Question 56-34 : Measurement of barometric pressure from a static source on the fuselage static pressure the difference between absolute and dynamic pressure at the fuselage measurement of outside air temperature oat measurement of elapsed time for a radio signal transmitted to the ground surface and back

exemple 288 Measurement of barometric pressure from a static source on the fuselage (static pressure). — Measurement of barometric pressure from a static source on the fuselage (static pressure).

Indication of mach number is obtained from ?

Question 56-35 : Indicated speed and altitude using a speed indicator equipped with an altimeter type aneroid an ordinary airspeed indicator scaled for mach numbers instead of knots a kind of echo sound comparing velocity of sound with indicated speed indicated speed ias compared with true air speed tas from the air data computer

exemple 292 Indicated speed and altitude using a speed indicator equipped with an altimeter type aneroid. — Admin .the mach meter modifies the output from an airspeed capsule by using an altimeter aneroid capsule Indicated speed and altitude using a speed indicator equipped with an altimeter type aneroid.

The altimeter consists of one or several aneroid capsules located in a sealed ?

Question 56-36 : I vacuum or a very low pressure ii static pressure i static pressure at time t ii static pressure at time t dt i total pressure ii static pressure i static pressure ii total pressure

exemple 296 (i) vacuum (or a very low pressure) (ii) static pressure — (i) vacuum (or a very low pressure) (ii) static pressure

In case of accidental closing of an aircraft's left static pressure port rain ?

Question 56-37 : Overreads the altitude in case of a sideslip to the left and displays the correct information during symmetric flight underreads the altitude overreads the altitude in case of a side slip to the right and displays the correct information during symmetric flight keeps on providing reliable reading in all situations

exemple 300 Overreads the altitude in case of a sideslip to the left and displays the correct information during symmetric flight. — Amassa .with a side slip to the left pressure will increase on the left side of the aircraft and decrease on the right .if both static ports are open the pressures are compensated this is why two static ports are used .so a lower static pressure will be sensed and the altimeter will overread the aircraft's altitude Overreads the altitude in case of a sideslip to the left and displays the correct information during symmetric flight.

The vertical speed indicator vsi is fed by ?

Question 56-38 : Static pressure dynamic pressure total pressure differential pressure

exemple 304 Static pressure — Static pressure

The altimeter is supplied with ?

Question 56-39 : Static pressure dynamic pressure total pressure differential pressure

exemple 308 Static pressure. — Static pressure.

Total air temperature tat is ?

Question 56-40 : Higher or equal to static air temperature sat depending on mach number and sat lower than static air temperature sat depending on altitude and sat higher or equal to static air temperature sat depending on altitude and sat lower than static air temperature sat depending on mach number and sat

exemple 312 Higher or equal to static air temperature (sat) depending on mach number and sat. — Admin .tat = sat 1 + 0 2 x kr x m² . sat the static temperature in kelvin. tat the total temperature in kelvin. kr the recovery coefficient. m the mach number.if mach is 0 sat = tat .if sat is 0 tat = sat .absolute zero in kelvin is almost impossible to reach but from the formula tat will be 0 if sat is 0 Higher or equal to static air temperature (sat) depending on mach number and sat.

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