Measurements And Air Data Parameters 4 Flashcards
Given: Pt: total pressure Ps: static pressure Pd: dynamic pressure The altimeter is fed by:
Pt-Pd.
A dynamic pressure measurement circuit is constituted of the following pressure probes:
total pressure and static pressure.
The QNH is by definition the value of the:
altimeter setting so that the altimeter, on the apron of the aerodrome for which it is given, reads the elevation.
When climbing at a constant Mach number:
CAS decreases.
The pressure capsule of an airspeed indicator is sensitive to the difference:
(Total Pressure - Static Pressure), called Dynamic Pressure.
When descending at a constant CAS:
EAS increases.
When climbing at a constant Mach number through an isothermal layer, the CAS:
decreases.
When climbing at a constant CAS:
EAS decreases.
VFE is the maximum speed:
with the flaps extended.
The yaw damper affects:
rudder only.
During a climb at a constant Mach number below the tropopause in ISA conditions:
CAS and TAS decrease.
A vertical speed indicator measures the difference between:
the instantaneous static pressure and the static pressure at a previous moment.
At flight level and mach number constant, if OAT increases, the CAS:
remains constant.
A temperature sensor has a recovery factor of 0,95. The temperature measured is equal to:
static air temperature (SAT) + 95% of the ram rise.
At flight level and mach number constant, if OAT decreases, the CAS:
remains constant.
Automatic Flight Control System (AFCS) series actuator is:
displayed in the cockpit as a function of input and output signals.
The altimeter of your aircraft indicates 15000 ft with a subscale-setting of 1013,25 mb. OAT is -21°C. The pressure altitude of the aircraft is:
15000 ft.
The altimeter of your aircraft indicates 11000 ft with a subscale-setting of 1013,25 mb. QNH is 1023 hPa. OAT is +3°C. The pressure altitude of the aircraft is:
11000 ft.
The altimeter of your aircraft indicates 12000 ft with a subscale-setting of 1013,25 mb. QNH is 999 hPa. The pressure altitude of the aircraft is:
12000 ft
The altimeter of your aircraft indicates 17000 ft with a subscale-setting of 1013,25 mb. QNH is 1031 hPa. The pressure altitude of the aircraft is:
17000 ft.
The altimeter of your aircraft indicates 16000 ft with a subscale-setting of 1013,25 mb. QNH is 993 hPa. OAT is -3°C. The pressure altitude of the aircraft is:
16000 ft.
The altimeter is subject to static pressure error. This error results from:
incorrect pressure sensing caused by disturbed airflow around the static ports.
The yaw damper system sends a motion order to the rudder if the yawing rate of the aircraft:
is not constant.
The yaw damper system is operative:
during manual or automatic flight.
Below the tropopause with no temperature inversion, when climbing at constant Mach number:
TAS decreases.
Below the tropopause, with no temperature inversion, when descending at constant Mach number:
TAS increases.
An aeroplane is in a steady climb. The auto-throttle maintains a constant Mach number. If the total temperature remains constant, the calibrated airspeed:
decreases.
An airplane is in steady cruise at flight level 290. The auto-throttle maintains a constant Mach number. If the total temperature decreases, the calibrated airspeed:
remains constant.
An airplane is in steady cruise at flight level 290. The auto-throttle maintains a constant Mach number. If the total temperature increases, the calibrated airspeed:
remains constant.
In a standard atmosphere and at the sea level, the calibrated airspeed (CAS) is:
equal to the true airspeed (TAS).
The parameter that determines the relationship between EAS and TAS is:
density altitude.
With CAS and pressure altitude, we can deduce:
EAS.
Speed of sound is proportional to:
the square root of the absolute temperature.
During a climb, if the total pressure head is rapidly clogged up by ice, the sensed total pressure remains constant and:
the static pressure decreases, implying an increasing IAS.
The Static Air temperature (SAT) is:
he ambiant outside air temperature
The limits of the green scale of an airspeed indicator are:
VS1 and VNO.
Concerning the pitot and static system, the static pressure error varies according to:
1 - altimeter setting
2 - speed
3 - angle of attack
The combination that regroups all of the correct statements is:
2 and 3.
The alternate static source is used:
when the static ports become blocked.
The machmeter is subject to position error. This error varies according to:
1 - angle of attack
2 - OAT
3 - TAS
The combination that regroups all of the correct statements is:
1, 3.
The data output from the ADC are: 1- Barometric altitude 2- Mach number 3- CAS 4- TAS 5- SAT The combination that regroups all of the correct statements is:
1, 2, 3, 4, 5.
