Vayudoot Aviation

1. What is the first page on an FMS CDU?

PRE-START.

INDEX.

TAKE-OFF.

IDENT

2. when Initial position is put into an INS system?

It rejects initial latitude errors, but accepts initial longitude errors.

It accepts both longitude and latitude errors.

It rejects initial longitude errors, but will accept latitude errors.

It rejects initial latitude or longitude errors.

3. The control and display unit of an inertial navigation system indicates a position of 4810.9° N 00012.2° W on a ramp position 4807.5°N 00005.1°E. What is the radial error rate of the system if it has been in NAV mode for 8 hours 20 minutes?

11.42 Nm/hr.

1.37 Km/hr.

14.3 Nm/hr.

1.37 Nm/hr.

4. In an INS a TAS input is ?

Required for polar navigation.

Not required.

Required for great circle navigation.

Required in order to provide a wind velocity read out.

5. A cost index is?

An FMS output code.

A fixed code giving best fuel efficiency for each route.

A fixed code giving the best fuel efficiency for each aircraft type.

An FMS input code telling the FMS the required balance between optimising fuel costs and sector time.

6. The sequences for switching on INS is?

Off, On, Align, Standby.

Off, Align, Standby, Nav.

Off, Align, On, Standby.

Off, Standby, Align, Nav.

7. The selection on an IRS mode panel are used in the following order?

OFF STBY ALIGN ATT NAV.

OFF ALIGN STBY ATT NAV.

OFF ALIGN STBY NAV ATT.

OFF STBY ALIGN NAV ATT.

8. The vertical reference unit of a three axis data generator is equipped with a gyro with?

1 degree of freedom and a horizontal spin axis .

2 degrees of freedom and a vertical spin axis .

2 degrees of freedom and a horizontal spin axis .

1 degree of freedom and a vertical spin axis .

9.
The diagram below shows a gyro-stabilised platform . 1 is a........ gyro gimbal and 2 is a ...... gimbal?

Pitch Roll.

Roll Pitch.

Roll yaw.

10. The position accuracy of an RLG INS is ?

1 nm/hr.

10 nm/hr.

2 nm/hr.

5 nm/hr.

11. During initial alignment the IRS must be given coordinates to?

Input initial heading information.

Establish true magnetic north.

Establish the trihedron with reference to the earth.

Test the accuracy and serviceability of the laser ring gyros.

12. The correct latitude must be put into INS?

Because small latitude errors will not be detected but will cause unbounded errors during the subsequent flight.

Because it cannot detect latitude. changes.

Large latitude errors will be undetected but cause large errors during the subsequent flight.

Because it cannot detect initial latitude.

13. Where would a rate integrating gyro be used? 1. Turn and slip indicators. 2.Servo stabiliser mechanisms. 3. Autopilots. 4. Inertial attitude units 5. Inertial navigation units.

3, 4, 5

2, 4, 5.

1, 2, 3, 4.

4, 5

14. The Schuler period is?

22 minutes.

66 minutes.

1 oscillation in azimuth.

84 minutes.

15. What would be the FMC displayed position in an aircraft equipped with a twin inertial system and DME?

The mean of the radio fix position and the primary inertial position.

The mean between the radio fix and the mean of the two inertial positions.

The mean of the two inertial positions.

Identical to the primary inertial system position.

16. In an INS which is Schuler tuned , the largest unbounded errors are?

Due to the output of the first stage integrators.

Track errors due to initial platform misalignment.

Due to accelerometer errors.

Due to the real wander of the platform gyroscopes.

17. To obtain heading information from a gyro-stabilised platform, the gyros should be?

1 degrees of freedom and a vertical axis.

2 degree of freedom and a vertical axis.

2 degree of freedom and a horizontal axis.

1 degree of freedom and a horizontal axis.

18. The errors of an INS fall into three categories?

Bounded, unbounded and accelerometer.

Coriolis, unbounded and inherent.

Bounded, unbounded and velocity.

Bounded, unbounded and inherent.

19. Ring laser gyros use dither motors to?

Level and align the gyros.

Prevent unbounded errors.

Prevent lock in of the laser beams.

Reduce random wander.

20. What happens If an FMC operating in VNAV and LNAV modes reaches a waypoint beyond which no route has been input?

The autopilot will disconnect and a warning will be sounded and illuminated on EICAS/ECAM.

The system reverts to heading mode.

The aircraft returns to the previous waypoint.

The aircraft circles the waypoint until commanded to do otherwise.

21. The flight control unit in an FMS?

Control vertical flight paths

Controls only heading.

Control all flight paths.

Controls lateral flight paths.

22. The JAR 25 standard colour for an FMS active planned route is?

Red

Cyan

White.

Magents

23. with reference to Inertial Navigation Systems, the functions of the integrator are? 1. At the second stage integration to suppress unbounded errors (when in nav mode). 2. At the first stage of integration to convert accelerations with respect to time, into speed, (when in nav mode.) 3. At the second stage of integration to convert speed with respect to time, into distance gone, (when in nav mode). 4. To align the platform (when in level and align modes)

Only statements 1,2 and 3, are correct

Only statements 2,3 and 4 are correct.

Only statements 2 and 3 are correct.

All of the above statements are correct.

24. While inertial platform system is operating on board an aircraft , it is necessary to use a device with the following characteristics, in order to keep the vertical line with the pendulous system?

With damping and a period of about 84 seconds.

Without damping and a period of about 84 seconds.

Without damping and a period of about 84 minutes.

With damping and a period of about 84 minutes.

25. In an IRS system?

Both the platform and accelerometers are strapped down

Both the platform and accelerometers are gyro-stabilised.

The platform is gyro-stabilised but the accelerometers are strapped down.

The platform is strapped down but the accelerometers are gyro-stabilised.

26. The triangular cavity in a RLG is filled with which combination of gasses?

Hydrogen and neon

Hydrogen and argon.

Helium and argon.

Helium and neon.

27. Valid FMS CDU waypoint entries include? 1. Runway number 2. Navaid limitations. 3. Airport ICAO identifier. 4.Navaid identifier 5. Waypoint name 6. Country code

2, 3, 4, 6.

1, 3, 4, 5.

1, 4, 5, 6.

1, 2, 3, 4.

28. A rate Integrating gyro is used in ?

Inertial navigation system.

Flight Director.

Artificial horizon.

Turn and slip Indicator.

29. A longitude error in an INS will cause

Will be corrected for once the E/W accelerometer has aligned to true north

Will cause no problems at all.

A failure to align.

Poor alignment and degraded accuracy.

30. Why is the Inertial strapdown unit in an IRS programmed with coordinates during alignment?

To establish the trihedron with reference to the earth.

To functionally test the ring laser gyroscopes.

To compensate for earth rotation errors.

To establish magnetic north and true north.

31. The fundamental difference between INS and IRS is that?

The IRS is a strap down system with 3 accelerometers mounted at 90° to each other.

The INS is a strap down system with 3 accelerometers mounted at 90° to each other.

The IRS is a strap down system with 2 accelerometers mounted at 90° to each other.

The INS is a strap down system with 2 accelerometers mounted at 90° to each other.

32. Why is an INS platform virtually unusable at very high latitudes?

The value of the earth rate affecting the E/W accelerometer is a component dependent on the sine lat. At high latitudes this component is nearly zero and makes alignment to true north virtually impossible.

The value of the earth rate affecting the E/W accelerometer is a component dependent on the sine lat. At high latitudes this component is nearly zero and makes alignment to true magnetic virtually impossible.

The value of the earth rate affecting the E/W accelerometer is a component dependent on the cosine lat. At high latitudes this component is nearly zero and makes alignment to magnetic north virtually impossible.

The value of the earth rate affecting the E/W accelerometer is a component dependent on the cosine lat. At high latitudes this component is nearly zero and makes alignment to true north virtually impossible.

33. Integration of a yaw rate signal?

Gives heading.

Gives yaw displacement.

Gives yaw acceleration rate.

Gives track.

34. Which of the following is closest to the Schuler period?

84 minutes.

84 seconds.

48 seconds.

48 minutes.

35. In an INS the gyros should ..... be strap down. In an IRS the gyros should ..... be strapped down?

always never.

never always.

always always.

never never

36. The inputs to the FMS include? 1. Air data computer information 2. Route data. 3.Radio aids information. 4.Power pland data. 5.Operating data

1, 2, 3, 4.

1, 2, 3, 4, 5.

2, 3, 4, 5.

1, 3, 4, 5.

37. The Inputs to an FMS Include? 1. Operating data. 2. Terminal data. 3. Air data 4. Route data 5.Engine data 6. Radio aids data.

2, 3, 4, 5.

3, 4, 5, 6.

1, 2, 3, 4.

All of the above.

38. The product of the first integration of the E/W acceleration sensed by an INS system is?

Speed along the local parallel.

Departure.

Speed along the local horizontal

Distance.

39. An INS in the ALIGN mode will?

Accept an error of 10° longitude but not one of 10°of latitude in the inserted initial position.

Accept an error of 10° latitude and 10°of longitude of the inserted position.

Accept an error of 10° latitude but not an error of 10° longitude of the inserted initial position.

Not accept an error on 10° latitude and 10° longitude of the inserted initial position.

40. With reference to an FMS, what does the term managed guidance mean?

The term managed guidance is not related to FMS.

The autopilot gives commands to the FMC.

The INS gives commands to the autopilot.

The FMC gives commands to the autopilot

41. An INS with the accelerometers aligned N/S and E/W is limited to use at latitudes below about 82°. This is because?

It loses horizontal reference as dip becomes large.

At high speed on East or West tracks the rate of convergency is faster than the azimuth motor can correct.

The functions of secant latitude and tangent latitude used in certain corrections in the computer start to approach infinity and the computer cannot handle the rapid changes involved.

The correction for the Coriolis effect of the earth rotation approaches infinity above 82° latitude.

42. Modern systems employ ring laser gyros because they offer?

More rapid alignment.

Longer life.

Lower electrical power requirements.

More rapid run up.

43. The fundamental difference between INS and IRS is that?

Bounded, unbounded and velocity.

Coriolis, unbounded and inherent.

Bounded, unbounded and accelerometer.

Bounded, unbounded and inherent.

44. IRS is different from INS in that it?

It suffers laser lock but spins up faster.

Its strapped down accelerometers are not rotated with the aircraft and hence do not suffer schuler errors.

It is not affected by vertical accelerations due to gravity, but it requires a longer spin-up time.

It requires no corrections for central accelerations or Coriolis effects.

45. When using an INS platform Coriolis affects?

Neither a, nor b.

The E/W accelerometer.

The N/S accelerometer.

Both a, and b.

46. At the second state of integration E/W speed is converted into E/W distance gone. To convert this departure into change of longitude it has to?

Be multiplied by the secant of latitude.

Be multiplied by the Cosine of latitude.

Be divided by the tangent of latitude.

Be divided by the secant of latitude.

47. The amber ALERT light on an INS control and display unit?

Flashes for 2 minutes before reaching the next waypoint.

Illuminates if power from the aircraft bus bar has been lost and the system is operating on standby battery.

Illuminates steadily after passing a waypoint in manual mode, until the next leg is programmed in.

Illuminates steadily for 2 minutes before reaching the next waypoint.

48. Heading information given by a gyro platform is given by a gyro with?

2 degrees of freedom in the vertical axis.

1 degrees of freedom in the horizontal axis.

3 degrees of freedom in the vertical axis.

3 degrees of freedom in the horizontal axis.

49. Alignment of a RLG INS takes?

Less than 10 minutes.

84.4 minutes.

15 to 20 minutes.

10 to 15 minutes.

50. What is the Schuler period?

48 minutes.

84 minutes.

48 seconds.

84 seconds.

Question Bank

Questions for KW INSTRUMENTS INS/IRS/FMS