Measurement And Air Data Parameters 3 Flashcards
If OAT increases whilst maintaining a constant CAS and flight level:
Mach number remains constant.
If, with the automatic flight control system (AFCS) engaged, the pilot presses the force trim release button to allow a manual input to the flight controls:
the spring units will become ineffective.
In standard atmosphere, when descending at constant CAS:
TAS decreases.
In the absence of position and instrument errors, CAS is equal to:
IAS.
In the absence of position and instrument errors, IAS is equal to:
CAS.
In the absence of position and instrument errors:
IAS = CAS.
The automatic synchronisation function of an autopilot control system: 1 - operates only when the autopilot is engaged 2 - prevents the aircraft’s control system from jerking when disengaging the autopilot 3 - prevents the aircraft’s control system from jerking when engaging the autopilot The combination regrouping all the correct statements is:
3
The command bars of a flight director:
may be displayed when flying manually.
The compressibility correction to CAS to give EAS: 1 - may be positive 2 - is always negative 3 - depends on Mach number only 4 - depends on pressure altitude only The combination regrouping all the correct statements is:
2, 3.
The parameter that determines the relationship between EAS and TAS is:
density altitude.
True Air Speed (TAS) is obtained from Equivalent Air Speed (EAS) by correcting for:
density error.
True Air Speed (TAS) is obtained from Indicated Air Speed (IAS) by correcting for the following errors: 1 - instrument 2 - position 3 - compressibility 4 - density The combination regrouping all the correct statements is:
1, 2, 3, 4.
When climbing at a constant CAS in a standard atmosphere: 1 - TAS decreases 2 - TAS increases 3 - Mach number increases 4 - Mach number decreases The combination regrouping all the correct statements is:
2, 3.
When descending at a constant Mach number:
CAS increases.
When flying in cold air (colder than standard atmosphere), indicated altitude is:
higher than the true altitude.
When flying in cold air (colder than standard atmosphere), the altimeter will:
overestimate.
When flying in warm air (warmer than standard atmosphere), indicated altitude is:
lower than the true altitude.
With EAS and density altitude, we can deduce:
TAS.
With EAS and pressure altitude (Zp), we can deduce:
CAS.
During a climb, the total pressure probe of the airspeed indicator becomes blocked; if the pilot maintains a constant indicated airspeed, the true airspeed:
decreases until reaching the stall speed.
An airspeed indicator includes a capsule; inside this capsule is:
total pressure and outside is static pressure.
An aircraft is equipped with one altimeter that is compensated for position error and another one altimeter that is not. Assuming all other factors are equal, during a straight symmetrical flight:
the greater the speed, the greater the error between the two altimeters.
An aneroid capsule: 1 - measures differential pressure 2 - measures absolute pressure 3 - is used for low pressure measurement 4 - is used for very high pressure measurement The combination regrouping all the correct statements is:
2, 3.
An altimeter contains one or more aneroid capsules. Inside these capsules is:
a very low residual pressure and outside is static pressure.
As a result of the failure of the central air data computer (CADC), the inertial navigation system (INS) will no longer provide information about:
the wind direction and speed.
An outer loop Automatic Flight Control System (AFCS), is a system which:
contains a parallel actuator which provides control through 100% of the control range and moves both the control inputs and the cockpit control stick.
The “guidance” functions of a autopilot consist in:
monitoring the movements of the centre of gravity in the three dimensions of space.
The altimeter of your aircraft indicates 10000 ft with a subscale-setting of 1013,25 mb. OAT is +5°C. The pressure altitude of the aircraft is:
10000 ft.
The altimeter indicates true altitude:
in standard atmosphere only.
The maximum TAS is obtained at:
the Flight Level at which simultaneously CAS = VMO and M = MMO.
The input data of an ADC are: 1 - OAT 2 - TAT 3 - static pressure 4 - total pressure The combination regrouping all the correct statements is:
2, 3, 4.
During a final approach, if the flight director system is engaged in the G/S mode (holding of ILS Glide Slope), the position of the horizontal command bar indicates:
the correction on the pitch to be applied to join and follow the ILS Glide Slope.
Given: Mach number M = 0.70 measured impact temperature = - 48 °C the recovery factor (Kr) of the temperature probe = 0.85 The OAT is:
- 65 °C
During a descent at a constant Mach number below the tropopause in ISA conditions:
IAS and TAS increase.
During a descent at a constant Mach number below the tropopause in ISA conditions:
CAS and TAS increase.
During a descent at a constant IAS below the tropopause in ISA conditions:
Mach number and TAS decrease.
During a climb at a constant Mach number below the tropopause in ISA conditions:
IAS and TAS decrease.
If the pitot tube ices up during a flight, the affected equipment(s) is (are): 1 - the altimeter 2 - the variometer 3 - the airspeed indicator The combination regrouping all the correct statements is:
3.
If, during a descent:
- the pneumatic altimeter reading is constant
- the vertical speed indicator shows zero
- the IAS is increasing
the most likely explanation is that:
the static ports are completely blocked.
If the pitot tube becomes blocked during a descent, the airspeed indicator:
under-reads.
