Measurements of Air Data Parameters

Question 1

If the outside temperature at 35 000 feet is -40°C, the local speed of sound is:

Answer 1

595 kt.

Question 2

The error in altimeter readings caused by the variation of the static pressure near the source is known as:

Answer 2

position error.

Question 3

If the static source of an altimeter becomes blocked during a descent the instrument will:

Answer 3

continue to display the reading at which the blockage occurred

Question 4

If the static source to an altimeter becomes blocked during a climb, the instrument will:

Answer 4

continue to indicate the reading at which the blockage occurred

Question 5

If the static source to an airspeed indicator (ASI) becomes blocked during a descent the instrument will:

Answer 5

over-read

Question 6

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

Answer 6

decreases.

Question 7

A leak in the pitot total pressure line of a non-pressurized aircraft to an airspeed indicator would cause it to:

Answer 7

under-read.

Question 8

Machmeter readings are subject to:

Answer 8

position error

Question 9

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:

Answer 9

1,3

Question 10

VNO is the maximum speed:

Answer 10

not to be exceeded except in still air and with caution.

Question 11

VNE is the maximum speed:

Answer 11

which must never be exceeded

Question 12

VLO is the maximum :

Answer 12

landing gear operating speed.

Question 13

The purpose of the vibrating device of an altimeter is to:

Answer 13

reduce the effect of friction in the linkages.

Question 14

The response time of a vertical speed detector may be increased by adding a:

Answer 14

correction based on an accelerometer sensor.

Question 15

The pressure altitude is the altitude corresponding :

Answer 15

in standard atmosphere, to the pressure Ps prevailing at this point

Question 16

The atmospheric pressure at FL 70 in a “standard 10” atmosphere is:

Answer 16

782 hPa.

Question 17

Sound propagates through the air at a speed which only depends on:

Answer 17

temperature.

Question 18

The velocity of sound at the sea level in a standard atmosphere is:

Answer 18

661 kt.

Question 19

During a climb at a constant CAS below the tropopause in standard atmosphere:

Answer 19

TAS and Mach number increase.

Question 20

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

Answer 20

VNO for the lower limit and VNE for the upper limit

Question 21

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

Answer 21

VSO for the lower limit and VFE for the upper limit

Question 22

The maximum operating speed VMO is expressed in:

Answer 22

CAS or EAS.

Question 23

The reading of a Mach indicator is independent of:

Answer 23

the outside temperature

Question 24

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:

Answer 24

decreases steadily

Question 25

The principle of the Mach indicator is based on the computation of the ratio :

Answer 25

(Pt - Ps)/Ps

Question 26

The Mach number is the:

Answer 26

TAS divided by the local speed of sound.

Question 27

A blocked pitot head with a clear static source causes the airspeed indicator to:

Answer 27

react like an altimeter.

Question 28

A pitot tube covered by ice which blocks the ram air inlet will affect the following instrument (s):

Answer 28

airspeed indicator only.

Question 29

VFE is the maximum speed:

Answer 29

with the flaps extended in a given position.

Question 30

The airspeed indicator of a twin-engine aircraft comprises different sectors and colour marks. The blue line corresponds to the:

Answer 30

optimum climbing speed with one engine inoperative, or VY

Question 31

The Mach number is:

Answer 31

the ratio of the aircraft true airspeed to the sonic velocity at the altitude considered

Question 32

In An Air Data Computer (ADC), aeroplane altitude is calculated from:

Answer 32

Measurement of barometric pressure from a static source on the fuselage

Question 33

Indication of Mach number is obtained from:

Answer 33

Indicated speed and altitude using a speed indicator equipped with an altimeter type aneroid

Question 34

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:

Answer 34

(i) vacuum (or a very low pressure) (ii) static pressure

Question 35

In case of accidental closing of an aircraft’s left static pressure port (rain, birds), the altimeter:

Answer 35

overreads the altitude in case of a sideslip to the left and displays the correct information during symmetric flight.

Question 36

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:

Answer 36

1, 3

Question 37

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 :

Answer 37

1, 2, 4

Question 38

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 :

Answer 38

increase the flight attitude until the command bars recentre on the symbolic airplane.

Question 39

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:

Answer 39

3, 4, 5.

Question 40

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:

Answer 40

1, 3.