Measurements of Air Data Parameters 2 Flashcards
An aeroplane is cruising at FL 220. The auto-throttle maintains a constant CAS. If the OAT decreases, the Mach number:
remains constant.
An aeroplane is cruising at FL 190. The auto-throttle maintains a constant CAS. If the OAT decreases, the Mach number:
remains constant.
An aeroplane is in steady descent. The auto-throttle maintains a constant calibrated airspeed. If the total temperature remains constant, the Mach number:
decreases.
The FMS provides the following functions: 1- vertical flight plan management 2- fuel management 3- lateral flight plan management 4- terrain awareness and warning The combination which regroups all of the correct statements is:
1, 2, 3.
An aeroplane is in steady cruise at flight level 270. The auto-throttle maintains a constant calibrated airspeed. If the static air temperature increases, the Mach number:
remains constant.
An aeroplane is in steady cruise at flight level 270. The auto-throttle maintains a constant calibrated airspeed. If the static air temperature decreases, the Mach number:
remains constant.
An aeroplane is in steady climb. The auto-throttle maintains a constant calibrated airspeed. If the total temperature remains constant, the Mach number:
increases.
When descending at a constant CAS through an isothermal layer, the Mach number:
decreases.
When climbing at a constant CAS through an isothermal layer, the Mach number:
increases.
The vertical speed indicator (VSI) is fed by:
static pressure
The operating principle of the vertical speed indicator (VSI) is based on the measurement of the rate of change of:
static pressure
An air data computer: 1. supplies the ground speed and the drift (angle) 2. determines the total temperature and the true altitude 3. receives the static pressure and the total pressure 4. supplies the true airspeed to the inertial unit 5. determines the Mach number, the outside (static) air temperature The combination regrouping all the correct statements is:
3, 4 and 5
An aircraft is descending from FL 390 to ground level at maximum speed. The limits in speed will be:
initially the MMO, then the VMO below a certain flight level.
An airspeed indicator displays:
IAS.
At a given altitude, the hysteresis error of an altimeter varies substantially with the:
time passed at this altitude.
Below the tropopause, when descending at a constant CAS:
Mach number decreases and the velocity of sound increases.
The CAS is obtained from IAS by correcting for the following errors: 1 - position 2 - compressibility 3 - instrument 4 - density The combination regrouping all the correct statements is:
1, 3.
CAS is equal to:
IAS corrected for position and instrument errors.
Concerning the airspeed indicator, IAS is:
the indicated reading on the instrument.
Considering a flight director of the “command bars” type: 1 - the vertical bar is always associated with the roll channel 2 - the vertical bar may be associated with the pitch channel 3 - the horizontal bar may be associated with the roll channel 4 - the horizontal bar is always associated with the pitch channel The combination regrouping all the correct statements is:
1, 4.
Considering an airspeed indicator, a second stripped needle, if installed, indicates:
maximum operating speed (VMO ).
Considering the relationship between CAS and EAS:
EAS is always lower than or equal to CAS.
Due to its conception, the altimeter measures a:
pressure altitude
During a category III automatic approach, the position signals in the vertical plane under 200 ft are based on:
a radio altimeter.
During a final approach, the flight director system is engaged in the LOC mode (holding of Localizer axis). The position of the vertical command bar indicates:
the correction on the bank to be applied to join and follow the Localizer axis.
During descent, the total pressure probe of the airspeed indicator becomes blocked. In this case: 1 - IAS becomes greater than CAS 2 - IAS becomes lower than CAS 3 - maintaining IAS constant, VMO may be exceeded 4 - maintaining IAS constant, aircraft may stall The combination regrouping all the correct statements is:
2, 3.
For the same TAS, when pressure altitude decreases below the tropopause:
Mach number decreases.
For the same TAS, when pressure altitude increases below the tropopause:
Mach number increases.
Given: Pt = total pressure Ps = static pressure Dynamic pressure is:
Pt - Ps
Given: Pt = total pressure Ps = static pressure Pd = dynamic pressure:
Pt = Pd + Ps
Given: Pt = total pressure Ps = static pressure Pso = static pressure at sea level. The CAS is a function of:
Pt - Ps
Given: Pt = total pressure Ps = static pressure Pso = static pressure at sea level. Dynamic pressure is:
Pt - Ps
TAS can be obtained from the following data:
EAS and density altitude.
If an aircraft maintaining a constant CAS and flight level is flying from a cold air mass into warmer air:
TAS increases.
If an aircraft maintaining a constant CAS and flight level is flying from a warm air mass into colder air:
TAS decreases.
If OAT decreases when at a constant Mach number:
TAS decreases.
If OAT decreases when at a constant TAS:
Mach number increases.
If OAT decreases whilst maintaining a constant CAS and flight level:
Mach number remains constant.
If OAT increases when at a constant Mach number:
TAS increases.
If OAT increases when at a constant TAS:
Mach number decreases.
