Measurements of Air Data Parameters Flashcards
If the outside temperature at 35 000 feet is -40°C, the local speed of sound is:
595 kt.
The error in altimeter readings caused by the variation of the static pressure near the source is known as:
position error.
If the static source of an altimeter becomes blocked during a descent the instrument will:
continue to display the reading at which the blockage occurred
If the static source to an altimeter becomes blocked during a climb, the instrument will:
continue to indicate the reading at which the blockage occurred
If the static source to an airspeed indicator (ASI) becomes blocked during a descent the instrument will:
over-read
When climbing at a constant Mach number through an isothermal layer, the CAS:
decreases.
A leak in the pitot total pressure line of a non-pressurized aircraft to an airspeed indicator would cause it to:
under-read.
Machmeter readings are subject to:
position error
The most significant advantages of an air data computer (ADC) are: 1. Position error correction 2. Hysteresis error correction 3. Remote data transmission capability 4. Gimballing errors correction The combination regrouping all the correct statements is:
1,3
VNO is the maximum speed:
not to be exceeded except in still air and with caution.
VNE is the maximum speed:
which must never be exceeded
VLO is the maximum :
landing gear operating speed.
The purpose of the vibrating device of an altimeter is to:
reduce the effect of friction in the linkages.
The response time of a vertical speed detector may be increased by adding a:
correction based on an accelerometer sensor.
The pressure altitude is the altitude corresponding :
in standard atmosphere, to the pressure Ps prevailing at this point
The atmospheric pressure at FL 70 in a “standard 10” atmosphere is:
782 hPa.
Sound propagates through the air at a speed which only depends on:
temperature.
The velocity of sound at the sea level in a standard atmosphere is:
661 kt.
During a climb at a constant CAS below the tropopause in standard atmosphere:
TAS and Mach number increase.
The limits of the yellow scale of an airspeed indicator are:
VNO for the lower limit and VNE for the upper limit
The limits of the white scale of an airspeed indicator are:
VSO for the lower limit and VFE for the upper limit
The maximum operating speed VMO is expressed in:
CAS or EAS.
The reading of a Mach indicator is independent of:
the outside temperature
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:
decreases steadily
The principle of the Mach indicator is based on the computation of the ratio :
(Pt - Ps)/Ps
The Mach number is the:
TAS divided by the local speed of sound.
A blocked pitot head with a clear static source causes the airspeed indicator to:
react like an altimeter.
A pitot tube covered by ice which blocks the ram air inlet will affect the following instrument (s):
airspeed indicator only.
VFE is the maximum speed:
with the flaps extended in a given position.
The airspeed indicator of a twin-engine aircraft comprises different sectors and colour marks. The blue line corresponds to the:
optimum climbing speed with one engine inoperative, or VY
The Mach number is:
the ratio of the aircraft true airspeed to the sonic velocity at the altitude considered
In An Air Data Computer (ADC), aeroplane altitude is calculated from:
Measurement of barometric pressure from a static source on the fuselage
Indication of Mach number is obtained from:
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 casing. The pressures in the aneroid capsule (i) and casing (ii) are respectively:
(i) vacuum (or a very low pressure) (ii) static pressure
In case of accidental closing of an aircraft’s left static pressure port (rain, birds), the altimeter:
overreads the altitude in case of a sideslip to the left and displays the correct information during symmetric flight.
The autothrottle : 1- enable to catch and to maintain the N1 RPM 2- enable to catch and to maintain the N2 RPM 3- enable to catch and to maintain an airplane indicated airspeed (IAS) 4- is always engaged automatically at the same time as the autopilot The combination regrouping all the correct statements is:
1, 3
The automatic power control system (autothrottle) of a transport airplane has the following mode(s) : 1- capture and holding of speeds 2- capture and holding of Mach number 3- capture and holding of flight angle of attack 4- capture and holding of N1 or EPR (Engine Power Ratio) 5- capture and holding of flight paths The combination regrouping all the correct statements is :
1, 2, 4
After having programmed your flight director, you see that the indications of your ADI (Attitude Director Indicator) are as represented in diagram N°1 of the appended annex. On this instrument, the command bars indicate that you must bank your airplane to the left and :
increase the flight attitude until the command bars recentre on the symbolic airplane.
Among the following functions of an autopilot, those related to the airplane guidance are: 1- pitch attitude holding 2- horizontal wing holding 3- indicated airspeed or Mach number holding 4- altitude holding 5- VOR axis holding 6- yaw damping The combination regrouping all the correct statements is:
3, 4, 5.
Among the following functions of an autopilot, those related to the aeroplane stabilization are: 1 - pitch attitude holding 2 - IAS or Mach number holding 3 - horizontal wing holding 4 - VOR radial holding The combination that regroups all of the correct statements is:
1, 3.
