Measurements And Air Data Parameters 4

Question 1

Given: Pt: total pressure Ps: static pressure Pd: dynamic pressure The altimeter is fed by:

Answer 1

Pt-Pd.

Question 2

A dynamic pressure measurement circuit is constituted of the following pressure probes:

Answer 2

total pressure and static pressure.

Question 3

The QNH is by definition the value of the:

Answer 3

altimeter setting so that the altimeter, on the apron of the aerodrome for which it is given, reads the elevation.

Question 4

When climbing at a constant Mach number:

Answer 4

CAS decreases.

Question 5

The pressure capsule of an airspeed indicator is sensitive to the difference:

Answer 5

(Total Pressure - Static Pressure), called Dynamic Pressure.

Question 6

When descending at a constant CAS:

Answer 6

EAS increases.

Question 7

When climbing at a constant Mach number through an isothermal layer, the CAS:

Answer 7

decreases.

Question 8

When climbing at a constant CAS:

Answer 8

EAS decreases.

Question 9

VFE is the maximum speed:

Answer 9

with the flaps extended.

Question 10

The yaw damper affects:

Answer 10

rudder only.

Question 11

During a climb at a constant Mach number below the tropopause in ISA conditions:

Answer 11

CAS and TAS decrease.

Question 12

A vertical speed indicator measures the difference between:

Answer 12

the instantaneous static pressure and the static pressure at a previous moment.

Question 13

At flight level and mach number constant, if OAT increases, the CAS:

Answer 13

remains constant.

Question 14

A temperature sensor has a recovery factor of 0,95. The temperature measured is equal to:

Answer 14

static air temperature (SAT) + 95% of the ram rise.

Question 15

At flight level and mach number constant, if OAT decreases, the CAS:

Answer 15

remains constant.

Question 16

Automatic Flight Control System (AFCS) series actuator is:

Answer 16

displayed in the cockpit as a function of input and output signals.

Question 17

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:

Answer 17

15000 ft.

Question 18

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:

Answer 18

11000 ft.

Question 19

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:

Answer 19

12000 ft

Question 20

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:

Answer 20

17000 ft.

Question 21

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:

Answer 21

16000 ft.

Question 22

The altimeter is subject to static pressure error. This error results from:

Answer 22

incorrect pressure sensing caused by disturbed airflow around the static ports.

Question 23

The yaw damper system sends a motion order to the rudder if the yawing rate of the aircraft:

Answer 23

is not constant.

Question 24

The yaw damper system is operative:

Answer 24

during manual or automatic flight.

Question 25

Below the tropopause with no temperature inversion, when climbing at constant Mach number:

Answer 25

TAS decreases.

Question 26

Below the tropopause, with no temperature inversion, when descending at constant Mach number:

Answer 26

TAS increases.

Question 27

An aeroplane is in a steady climb. The auto-throttle maintains a constant Mach number. If the total temperature remains constant, the calibrated airspeed:

Answer 27

decreases.

Question 28

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:

Answer 28

remains constant.

Question 29

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:

Answer 29

remains constant.

Question 30

In a standard atmosphere and at the sea level, the calibrated airspeed (CAS) is:

Answer 30

equal to the true airspeed (TAS).

Question 31

The parameter that determines the relationship between EAS and TAS is:

Answer 31

density altitude.

Question 32

With CAS and pressure altitude, we can deduce:

Answer 32

EAS.

Question 33

Speed of sound is proportional to:

Answer 33

the square root of the absolute temperature.

Question 34

During a climb, if the total pressure head is rapidly clogged up by ice, the sensed total pressure remains constant and:

Answer 34

the static pressure decreases, implying an increasing IAS.

Question 35

The Static Air temperature (SAT) is:

Answer 35

he ambiant outside air temperature

Question 36

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

Answer 36

VS1 and VNO.

Question 37

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:

Answer 37

2 and 3.

Question 38

The alternate static source is used:

Answer 38

when the static ports become blocked.

Question 39

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:

Answer 39

1, 3.

Question 40

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:

Answer 40

1, 2, 3, 4, 5.