Download - 239463141 Aircraft Instrmnt System Docx

8/11/2019 239463141 Aircraft Instrmnt System Docx

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1. Inertial navigational system (INS) calculate velocity and distance by using;A. two seismic pendulous and a gyro platform.B. the formula, acceleration and velocity.C. accelerometers and gyros on a platform.

2. The output from INS computer are;A. true heading, time and distance.B. magnetic heading, time and distance.C. present position and navigational data position.

3. INS component that serve as a communication link between the pilot and thenavigational unit computer is the;A. Control Display Unit (CDU)B. Mode Selector Unit (MSU)C. Navigational Unit (NU)

4. INS compensation signals that keep the platform level to the earth at all times isfrom the;A. two gyros.B. two accelerometer.C. INS computer.

5. Ring laser gyro consists of ;A. two anodes and one cathodeB. two anodes and one mirrorC. one anode and two cathodes

6. Lift transducer or detector on a stall warning system is merely a ;A. a limit switch move by air pressureB. a precision switch activated by movement of vaneC. a stick shaker attached to control column

7. Indication of an impending stall on a reed type stall warning system is by;A. the loudness of sound produced by the reedB. vibrating the control columnC. actuating a precision switch when stagnation point is displaced

8. An angle of attack system will provide aircrews with AOA indication and stall warningby sensors fitted;

A. at a stagnation point on an aircraft leading edgeB. at the fuselage below the flight deckC. at the control column transducer

9. Angle of attack indicator scale are calibrated;A. degrees of angle of attackB. stall angle of attack


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C. percent of stall-speed angle of attack

10. GPWS system detect the closeness of aircraft to terrain is through the;

A. Radio altimeterB. Air data computerC. HF/VOR signal

11. GPWS mode 5 (too much deviation below the glideslope) warning is;A. GPWS red light and computer generated voiceB. G/S red light and auralC. G/S amber light and aural

12. The GPWS provides various warning, caution and advisory level alerts whenoperating below what altitude?

A. 2450 feet radio altitude.B. 1500 feet radio altitude.C. 2450 feet barometric altitude.

13. GPWS mode 7 is of the windshear warning and the warning is of;A. GPWS red light and computer generated voiceB. windshear red light and auralC. aural warning only

14. On the GPWS control panel, the self test switch can conducted;A. on groundB. in-flightC. on ground and in-flight

15. Which GPWS warning can be disable if the pilot decided to silence the warning;A. Mode 1, 2, 3, & 4B. Mode 5C. Mode 6 & 7

16. Which warning mode of the GPWS that provide a call out warning only;A. Mode 1, 2, 3, & 4B. Mode 5C. Mode 6

17. Freely suspended magnet will align itself to the earths;A. North and south poles.B. Geographical north and south poles.C. Magnetic north and south poles.

18. A magnetic compass or standby compass is a;


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A. Slave compass.B. Direct reading compass.C. Remote reading compass.

19. What is adjusted in a magnetic compass to correct for deviation?

A. The strength of the compass magnet is varied.B. The compass magnets are moved either closer together or further apart.C. Compensating magnets are rotated to cancel the interfering magnetic

field.20. When swinging a magnetic compass, the compensators are adjusted to correct for;

A. magnetic variation.B. compass card oscillations.C. magnetic influence deviation.

21. Maximum allowable deviation on a magnetic compass if it is not use as a primaryheading is;

A. 3 deg.B. 5 deg.C. 10 deg.

22. An aircraft magnetic compass is swung to up-date the compass correction cardwhen;

A. aircraft is schedule for a long route.B. equipment is added that could effect compass deviation.C. after completion of maintenance work.

23. Typical FDR system consists of digital flight data recorder (DFDR), digital flight dataacquisition unit (DFDAU), flight recorder control panel, test connector with test plugand;A. FDR computerB. accelerometerC. warning annunciator

24. What is the function of the DFDAU?A. collect all aircraft systems informationB. convert analogue signal to binary digitC. records analogue, synchro and VOR signal to FDR

25. DFDAU received aircraft parameters are of analogue, discrete or binary digit fromthe;

A. FDR computerB. FDR control panelC. aircraft systems

26. Ground testing or fault isolation on the FDR system can be carried out from;A. Digital flight data acquisition unit (DFDAU)


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B. Digital flight data recorder (DFDR)C. Flight data control panel

27. Mandatory requirement for aircraft parameters to be recorded are 10 hours forhelicopters and aircrafts is;

A. 24 hoursB. 25 hoursC. 26 hours

28.The FDR system has three automatic switch ON methods and one manual methodof switch ON from the;

A. digital flight data recorder (DFDR).B. digital flight data acquisition unit (FDAU).C. FDR control panel.

29.Electronic flight instrument system (EFIS) displays aircrafts primary flight displaythrough the;

A. attitude director indicatorB. horizontal situation indicatorC. control display unit

30. A unit that act as an interface between components of an EFIS system is the;A. symbol generatorB. data busC. display controller

31. EFIS that uses an inclinometer to indicates a skid or a slip of an aircraft during a turnare fitted to the;

A. attitude director indicatorB. horizontal situation indicatorC. control display unit

32. EFIS uses _________ to transfer digital data between aircraft electronic systems.A. ARINC 429B. ARINC 629C. ARINC 573

33. Engine indicating and crew alerting system (EICAS) displays alert messages on the;A. Main EICASB. Secondary EICASC. Auxiliary EICAS

34. Advisory messages are level C message and displayed in amber with aural warningas;

A. Siren soundB. Owl soundC. None


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35. Central maintenance system (CMS) can be found under;

A. ATA 31B. ATA 34C. ATA 45

36. Most commonly use method to access to the central maintenance computer isthrough the;

A. line replacement unit (LRU)B. integrated display unit (CDU)C. multi-function display unit (MFD)

37. Ground test can be perform through the central maintenance computer (CMC)interface, by using the control display unit (CDU) or through the;

A. LRU (Start up BITE)B. LRU (Interruptive BITE)

C. LRU (Continuous BITE)

38. Central maintenance system considered the EICAS warning, caution and advisorymessages as;

A. Flight deck effects (FDE)B. Level A alert messageC. Flight phase logic

39. The central maintenance computer (CMC) are located at the;A. cockpit centre consoleB. main equipment centre (MEC)C. maintenance access terminal (MAT)

40. One of these measuring elements is used to measure atmospheric pressure;A. aneroid capsuleB. bellowC. bourdon tube

41. When setting the barometric scale counters of an altimeter to the atmosphericpressure prevailing at a particular airport, the corresponding Q code is known as;

A. QFEB. QNEC. QNH

42. What is the relationship between the resistance of a temperature bulb and thetemperature?

A. Resistance decreases with temperature.B. Resistance increases with temperature.C. There is no change of resistance with temperature.


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43. Synchronous data-transmission system is;A. an analogue systemB. a digital systemC. a remote position indicating system

44. On a Turn and Slip Indicator, the inclinometer is used to indicate;A. turn and bankB. roll and pitchC. skid and slip

45. As the speed of a gyroscope rotor increases, the rate of precession for a giventorque;

A. remain constant.B. decreases.C. increases.

46.Which instruments are connected to an aircrafts pitot static system?A. VSI, ASI, AltimeterB. VSI, ASI, Radio AltimeterC. VSI, ASI, Cabin Altimeter

47. A constant leak on a pitot static system on a pressurized aircraft will make analtimeter reading;

A. under readB. over readC. no change

48. What kind of probe is used in an electronic fuel quantity systems?A. Capacitance typeB. Resistance typeC. Magnetic type

49. Pilot will monitor engine condition in RPM by referring to;A. Engine pressure ratio indicator.B. Tachometer indicator.C. Manifold pressure gauge.

50. The common system used to measure engine speed of a piston engine eithermechanical or electrical is the;

A. flexible drive shaftB. drag cup principleC. four stroke engine