INST-SB-MODULE3

INST-SB-MODULE3

1. The Decision Height (DH) warning light comes on when an aircraft:

a) passes over the ILS inner marker.
b) passes over the outer marker.
c) descends below a pre-set radio altitude.
d) descends below a pre-set barometric altitude.

2. If a manifold pressure gauge consistently registers atmospheric pressure, the cause is probably;

a) leak in pressure gauge line.
b) too high float level.
c) fuel of too low volatility.
d) ice in induction system.

3. The operation of the radio altimeter of a modern aircraft is based on:

a) frequency modulation of the carrier wave.
b) amplitude modulation of the carrier wave.
c) a combination of frequency modulation and pulse modulation.
d) pulse modulation of the carrier wave.

4. An airborne instrument, equipped with a gyro with 2 degrees of freedom and a horizontal spin axis is: NB: the degree(s) of freedom of a gyro does not take into account its rotor spin axis.

a) a directional gyro
b) an artificial horizon
c) a turn indicator
d) a fluxgate compass

5. An airborne instrument, equipped with a gyro with 1 degree of freedom and a horizontal spin axis is a: NB: the degree(s) of freedom of a gyro does not take into account its rotor spin axis.

a) turn indicator
b) fluxgate compass
c) directional gyro
d) gyromagnetic compass

6. In a turn at a constant angle of bank, the turn indicator reading is:

a) proportional to the aircraft weight
b) independent to the aircraft true airspeed
c) proportional to the aircraft true airspeed
d) inversely proportional to the aircraft true airspeed

7. At a low bank angle, the measurement of rate-of-turn actually consists in measuring the:

a) roll rate of the aircraft.
b) yaw rate of the aircraft.
c) pitch rate of the aircraft.
d) bank of the aircraft.

8. The rate-of-turn is the:

a) pitch rate in a turn
b) yaw rate in a turn
c) change-of-heading rate of the aircraft
d) aircraft speed in a turn

9. On the ground, during a right turn, the turn indicator indicates:

a) needle to the right, ball to right
b) needle in the middle, ball to right
c) needle to the right, ball to left
d) needle in the middle, ball to left

10. On the ground, during a left turn, the turn indicator indicates:

a) needle in the middle, ball to the right
b) needle to the left, ball to the left
c) needle to the left, ball to the right
d) needle in the middle, ball to the left

11. When, in flight, the needle and ball of a needle-and-ball indicator are on the left, the aircraft is:

a) turning right with too much bank
b) turning left with too much bank
c) turning left with not enough bank
d) turning right with not enough bank

12. When, in flight, the needle and ball of a needle-and-ball indicator are on the right, the aircraft is:

a) turning left with not enough bank
b) turning right with not enough bank
c) turning right with too much bank
d) turning left with too much bank

13. When, in flight, the needle of a needle-and-ball indicator is on the right and the ball on the left, the aircraft is:

a) turning right with not enough bank
b) turning right with too much bank
c) turning left with too much bank
d) turning left with not enough bank

14. When, in flight, the needle of a needle-and-ball indicator is on the left and the ball on the right, the aircraft is:

a) turning right with too much bank
b) turning left with not enough bank
c) turning left with too much bank
d) turning right with not enough bank

15. In an engine vibration monitoring system for a turbojet any vibration produced by the engine is:

a) fed directly to the cockpit indicator without amplification or filtering.
b) directly proportional to engine speed.
c) amplified and filtered before being fed to the cockpit indicator.
d) inversely proportional to engine speed.

16. Which one of the following statements is true with regard to the operation of a Mach trim system:

a) It only operates above a pre-determined Mach number.
b) It operates to counteract the larger than normal forward movements of the wing centre of pressure at high subsonic airspeeds.
c) It only operates when the autopilot is engaged.
d) It operates over the full aircraft speed range.

17. A closed loop control system in which a small power input controls a much larger power output in a strictly proportionate manner is known as:

a) a servomechanism.
b) a feedback control circuit.
c) an amplifier.
d) an autopilot.

18. In order to measure temperature the cylinder head temperature (CHT) gauge utilises a:

a) bourdon tube.
b) ratiometer circuit.
c) thermocouple consisting of two dissimilar metals.
d) wheatstone bridge circuit.

19. If an EPR is set at a constant barometric pressure, with an increasing OAT, the thrust

a) decreases.
b) remains constant
c) varies according to the characteristics of the engine
d) increases

20. The yaw damper system controls:

a) the rudder, with the angular rate about the yaw axis as the input signal.
b) the ailerons, with Mach Number as the input signal.
c) the ailerons, with the angular rate about the yaw axis as the input signal.
d) the rudder, with Mach Number as the input signal.

21. Considering an airspeed indicator, a second stripped needle, if installed, indicates:

a) maximum operating speed (VMO).
b) never-exceed speed (VNE).
c) never-exceed speed (VNE) or maximum operating speed (VMO), depending on which is the higher.
d) never-exceed speed (VNE) or maximum operating speed (VMO), depending on which is the lowest.

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

a) minimum control speed, or VMC
b) maximum speed in operations, or VMO
c) speed not to be exceeded, or VNE
d) optimum climbing speed with one engine inoperative, or Vy

23. The RPM indicator (or tachometer) of a piston engine can include a small red arc within the arc normally used (green arc) In the RPM range corresponding to this small red arc the:

a) propeller generates vibration, continuous rating is forbidden
b) rating is the maximum possible in continuous mode
c) rating is the minimum usable in cruise
d) propeller efficiency is minimum at this rating

24. TCAS 2 (Traffic Collision Avoidance System) uses for its operation:

a) the replies from the transponders of other aircrafts.
b) the echoes of collision avoidance radar system especially installed on board.
c) the echoes from the ground air traffic control radar system.
d) both the replies from the transponders of other aircraft and the ground-based radar echoes.

25. The Mach number is:

a) a direct function of temperature ; it varies in proportion to the square root of the absolute temperature
b) the ratio of the indicated airspeed to the sonic velocity at the altitude considered
c) the ratio of the aircraft true airspeed to the sonic velocity at the altitude considered
d) the ratio of the aircraft conventional airspeed to the sonic velocity at the altitude considered

26. Mach Trim is a device to compensate for:

a) the effects of fuel transfer between the main tanks and the tank located in the horizontal tail
b) backing of the aerodynamic centre at high Mach numbers by moving the elevator to noseup
c) weight reduction resulting from fuel consumption during the cruise
d) the effects of temperature variation during a climb or descent at constant Mach

27. When available, the yaw damper indicator supplies the pilot with information regarding the:

a) rudder displacement by the rudder pedals
b) rudder position
c) yaw damper action on the rudder
d) yaw damper action only on the ground

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

a) The difference between absolute and dynamic pressure at the fuselage
b) Measurement of absolute barometric pressure from a static source on the fuselage
c) Measurement of elapsed time for a radio signal transmitted to the ground surface and back
d) Measurement of outside air temperature (OAT)

29. Indication of Mach number is obtained from:

a) A kind of echo sound comparing velocity of sound with indicated speed
b) Indicated speed (IAS) compared with true air speed (TAS) from the air data computer
c) Indicated speed and altitude using a speed indicator equipped with an altimeter type aneroid
d) An ordinary airspeed indicator scaled for Mach numbers instead of knots

30. 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 :

a) the greater the speed, the lower the error between the two altimeters.
b) the greater the speed, the greater the error between the two altimeters.
c) the lower the speed, the greater the error between the two altimeters.
d) the error between the two altimeters does not depend on the speed.

31. A Stand-by-horizon or emergency attitude indicator:

a) Is automatically connected to the primary vertical gyro if the alternator fails
b) Contains its own separate gyro
c) Is fully independent of external energy resources in an emergency situation
d) Only works of there is a complete electrical failure

32. Mode "Localizer ARM" active on Flight Director means:

a) System is armed for localizer approach and coupling will occur upon capturing centre line
b) Coupling has occurred and system provides control data to capture the centreline
c) Localizer is armed and coupling will occur when flag warning disappears
d) Localizer ALARM, making localizer approach not authorized

33. The purpose of Auto Throttle is:

a) automatic shut down of one engine at too high temperature
b) to deactivate manual throttles and transfer engine control to Auto Pilot
c) to maintain constant engine power or airplane speed
d) to synchronize engines to avoid "yawing"

34. The purpose of Auto Trim function in autopilot is to:

a) control elevator trim tab in order to relieve elevator load
b) trim throttles to obtain smooth engine power variation
c) help Auto Pilot compensate for crosswind influence
d) tell the pilot when elevator trimming is required

35. The altitude alerting system:

a) alerts the flight crew upon approaching a pre-selected altitude.
b) generates a signal once the aircraft is steady at the pre-selected altitude.
c) alerts the flight crew in case of ground proximity.
d) alerts the flight crew in case of an autopilot disengagement.

36. The signal supplied by a transmitter fitted with a magnetic sensor, connected to an RPM indicator is:

a) an AC voltage, the frequency of which varies with the RPM; the indicator converts the signal into square pulses which are then counted
b) an AC voltage varying with the RPM ; the indicator rectifies the signal via a diode bridge and is provided with a voltmeter
c) a three-phase voltage frequency varies with the RPM; the indicator is provided with a motor which drives a magnetic tachometer
d) a DC voltage varying with the RPM ; the indicator is a simple voltmeter with a rev/min. scale

37. A vibration indicator receives a signal from different sensors (accelerometers). It indicates the:

a) vibration period expressed in seconds
b) vibration frequency expressed in Hz
c) acceleration measured by the sensors, expressed in g
d) vibration amplitude at a given frequency

38. 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:

a) (i) total pressure (ii) static pressure
b) (i) vacuum (or a very low pressure) (ii) static pressure
c) (i) static pressure at time t (ii) static pressure at time t - dt
d) (i) static pressure (ii) total pressure

39. Concerning the TCAS (Traffic Collision Avoidance System):

a) In one of the system modes, the warning: "TOO LOW TERRAIN" is generated
b) Resolution Advisory (RA) must not be followed without obtaining clearance from ATC
c) No protection is available against aircraft not equipped with a serviceable SSR transponder
d) In one of the system modes, the warning: "PULL UP" is generated

40. The TCAS 2 (Traffic Collision Avoidance System) gives avoidance resolutions:

a) in horizontal and vertical planes
b) based on speed control
c) only in the vertical plane
d) only in the horizontal plane

41. In the event of a conflict, the TCAS 2 (Traffic Collision alert and Avoidance System) presents warnings to the crew such as:

a) "Glide Slope"
b) "Too low terrain"
c) "Climb" or "Descent"
d) "Turn left" or "Turn right"

42. The principle of the TCAS (Traffic Collision Avoidance Systems) is based on the use of:

a) air traffic control radar systems
b) F.M.S. (Flight Management System)
c) airborne weather radar system
d) transponders fitted in the aircraft

43. In the absence of position and instrumental errors, IAS is equal to:

a) KAS
b) EAS
c) CAS
d) TAS

This is more feedback!

This is the feedback!

Data Base Login Information: Please make
sure that you enter your name before
submitting your results.

My Name
*Enter your name here