Vayudoot Aviation

1. A gyro is said to drift when its spin axis moves in the ?

Neither, because its definition is not related to these

Vertical

Horizontal and vertical

Horizontal

2. In which IRS mode does gyro-compassing take place?

ON

ALIGN

ATT

NAV

3. Which of the following statements is true of a Ring Laser Gyro?

It doesn't suffer from 'lock in' and is unaffected by the earth's gravitational force

It is not necessarily fixed to true north and is quick to erect

It is fixed to true north and is quick to erect

It is not necessarily fixed to the true north but takes long time to erect

4. On the IRS, selection of ATT mode gives attitude?

Heading and groundspeed

Only

And heading

Altitude and heading

5. In a laser reference system (IRS), as compared to a gyro reference system (INS)

Accelerometers and platform are both gyro-stabilsed

Accelerometers and platform are both strapped down

The platform is strapped down but the accelerometers are gyro-stabilsed

The accelerometers are strapped down but the platform is gyro stabilised

6. Weather radar Displays are available on the Boeing 737-400 EFIS EHSI, when the system is set to?

MAP, FULL VOR/ILS, FULL NAV

MAP, EXPVOR/ILS EXP NAV

MAP, PLAN, EXP VOR/ILS

MAP, PLAN, FULL VOR/ILS

7. In order to maintain an accurate vertical using a pendulous system, an aircraft Inertial platform incorporates a device?

With damping and a period of 48.4 MIN

With damping and a period of 84.4 SEC.

With damping and a period of 48.4 SEC

With damping and a period of 84.4 MIN

8. Alignment of INS and IRS equipments can take place in which of the following modes?

ALIGN only

ALIGN and ATT

NAV and ALIGN

ATT and ALIGN

9. An aircraft equipped with an Inertial Navigation System (INS) files with INS 1 coupled with autopilot. Both Inertial navigation systems are navigating from waypoint A to B. The Inertial systems 'Central Display Units (CDU) show? XTK on INS 1 = 0 XTK on INS 2 = 15L (XTK = cross track) What can be deduced from this information?

Only Inertial navigation system No. 2 is drifting

Only Inertial navigation system No. 1 is drifting

The autopilot is unserviceable in NAV mode

At least one of the Inertial navigation systems is drifting

10. Gyro - compassing in an INS?

It is not possible in flight because the gyros cannot differentiate between acceleration due to aircraft movement and initial alignment errors.

Is not possible in flight as the gyros can differentiate between acceleration due to aircraft movement and Initial alignment errors.

Is possible in flight as the gyros can differentiate between acceleration due to aircraft movement and initial alignment errors.

d. Is possible in flight as he gyros cannot differentiate between acceleration due to aircraft movement and Initial alignment error.

11. After an IRS has lost its position mid-flight it must?

Be turned OFF

Not be used in NAV mode

Have a new position inserted

Be selected to ALIGN and then to NAV

12. What is the purpose of the plezo-electric motor in an IRS system?

Dither

Shudder

Vibrate

Shake

13. What output is calculated by double integration of output from the east/west accelerometer of an inertial navigation system (INS) when the system is engaged in the NAV mode?

Distance east/west

Vehicle longitude

Distance north/south

Velocity east/west

14. What is produced by double Integration of the output from the east/west accelerometer of an inertial navigation system (INS) when it is in the NAV MODE?

Velocity east/west

Distance east/west

Vehicle longitude

Distance north/south

15. In an Inertial Navigation System (INS), Ground Speed (GS) is calculated?

By Integrating gyro precession in N/S and E/W directions respectively.

From TAS and WN from RNAV data

By integrating measured acceleration

From TAS and WN from Air Data Computer (ADC)

16. The platform of an Inertial navigation system (INS) is maintained at right angles to the local vertical by applying corrections for the effects of?

Aircraft manoeuvres, earth rotation, transport wander and coriollis

Gyroscopic Inertia, earth rotation and real drift

Movement in the yawing plane, secondary procession and pendulous oscillation

Vertical velocities, earth procession, centrifugal forces and transport drift

17. How long does it take to align an IRS (Laser Ring Gyros)?

10 minutes

5 minutes

15 minutes

1 minute

18. The period of validity of an FMS database is?

56 days

Variable

28 days

One week

19. What do you call a system of gyros and accelerometers that is fixed to the aircraft?

Fixed

Strapdown

Stabilised

Laser

20. Which FMC/CDU page normally appears on initial power application to the B737-400 Electronic Flight Instrument System?

RTE

PERF INIT

POS INIT

IDENT

21. If an INS temporarily loses its power supply in flight?

It must be switched off for the remainder of the flight

It will be usable only in the NASV mode

It can only be used for attitude reference

It will functions normally

22. How is the FMC position produced?

The average of the IRS position

Half way between the IRS and radio navigation positions

Computer generated from the radio navigation positions

Computer generated from the IRS and radio navigation positions

23. How long does it take to align an IRS (Laser Ring Gyros)?

10 minutes

15 minutes

1 minute

5 minute

24. In which IRS mode does gyro-compassing takeplace?

ON

NAV

ATT

ALIGN

25. The latest point at which an INS or IRS may be selected to NAV mode is?

Immediately prior to push back or taxi from the gate

At the holding point

On operation of TOGA switch when opening the throttles for the take-off

After passengers and freight are aboard

26. Which of the following lists the first three pages of the FMC/CDU normally used to enter data on initial start-up of the B737-400 Electronic Flight Instrument System?

IDENT - POS INIT - RTE

RTE - POS INT - IDENT

PERF INIT - POD IDENT - INIT

POS INIT - IDENT - RTE

27. Which mode selection on the CDU of an INS is required to display Initial Great Circle track?

DSRTK/STS

XTK/TKE

HDG/DA

TK/DS

28. An Inertial Navigation System (INS), calculates Ground Speed (GS)?

From TAS and WN from Air Data Computer (ADC)

By integrating gyro precession in N/S and E/W directions respectively

From TAS and WN from RNAV data

By integrating measured acceleration

29. What is the source of magnetic variation information in a Flight Management System (FMS)?

Magnetic variation is calculated by each IRS based on the respective IRS position and the aircraft magnetic heading

The FMS calculates MH and MT from the FMC position

Magnetic variation information is stored in each IRS memory; it is applied to the true heading calculated by the respective IRS

The main directional gyro, which is coupled to the magnetic sensor (flux valve) positioned in the wingtip

30. What are the positions (in the order left to right) on the Boeing 737-400 IRS Mode Selector Unit (MSU)?

OFF ALIGN NAV ATT

OFF STBY ATT NAV

OFF STBY ALIGN NAV

OFF STBY NAV ATT

31. Some Inertial reference systems are known as 'strapdown'

The system is mounted on a stabilised platform

The accelerometers are fixed but the gyros are stable

The gyros are fixed but the accelerometers are stable

The system is mounted and fixed to the aircraft strap

32. In what formats can created waypoints be entered into the scratch pad of the B737-400 FMS?

Place Bearing/Distance, Place Distance/Place Distance, Along-Track Displacement, Latitude and Longitude

Place Bearing/Distance, Place Bearing/Place Bearing, Along-Track Displacement, Latitude and Longitude

Place Bearing/Distance, Place Bearing/Place Bearing, Across-Track Displacement, Latitude and Longitude

Place, Place Bearing/Distance, Along-Track Displacement, Latitude and Longitude

33. Gyro drift occurs when the spin axis moves in the?

Horizontal

Vertical

Neither, because its definition is not related to these axes

Horizontal and vertical

34. What do the sensors of an INS measure?

The horizontal component of the earth's rotation

Velocity

Acceleration

Precession

35. In an Inertial Navigation System(INS), the output of the first stage North/South integrator is?

Latitude

Groundspeed

Change of latitude

Velocity along the local meridian

36.
Which white EFIS symbol below represents the aircraft?

D

A

B

C

37.
Which Cyan symbol below represents an off-route waypoint?

D

B

A

C

38. From what information is the FMC position calculated?

Computer generated from the radio navigation positions

The average of the IRS positions

Half way between the IRS and radio navigation positions

Computer generated from the IRS and radio navigation positions

39. In which IRS mode does gyro-compassing take place?

ATT

NAV

ON

ALIGN

40. What is the period of validity of an FMS databse?

Variable

28 days

56 days

One week

41. On the IRS, selection of ATT mode gives attitude?

Only

Heading and groundspeed

And heading

Altitude, and heading

42. In a ring laser gyro, the purpose of the dither motor is to

Compensate for transport wander

Stabilise the laser frequencies

Enhance the accuracy of the gyro at all rotational rates

Overcome laser lock

43. Some inertial reference systems are known as 'strapdown'. This means

The gyros are fixed but the accelerometers are stabilised

The accelerometers are fixed but the gyros are stabilised

The system is mounted on a stabilised platform

The system is mounted and fixed to the aircraft structure

44. Some Inertial reference and navigation system are known as "strapdown". This means that?

The gyroscopes and accelerometers become part of the unit's fixture to the aircraft structure.

The accelerometers are fixed to the aircraft structure but the gyros are stabiised.

The gyros are stabilised but the accelerometers are fixed to the aircraft structure.

The indicator units are strapped to the aircraft structure.

45. What information is required by the FMS to enable it to calculate groundspeed?

Input from ADC of TAS and wind velocity

Input of heading from either the IRS or gyro compass, TAS from ADC and wind velocity from selected meterological data

Input from IRS

Input from DME with change of range integrated with respect to time

46. Double Integration of the output from the east/west accelerator navigation system(INS) in the NAV MODE given

Velocity east/west

Distance north/south

Distance east/west

Vehicle longitude

47. When initial position is put into a B737-400 FMS, the system?

Rejects initial latitude error, but it will accept longitude error

Cannot detect input errors, and accepts whatever is put in

Rejects initial latitude or longitude error

Rejects initial longitude error, but it will accept latitude error

48. An IRS differs from an INS in that it?

Has a longer spin-up time and is not affected by vertical accelerations due to gravity

Has a shorter spin-up time and suffers from laser lock

Does not experience Schuler errors as accelerometers are strapped down

Does not need to correct for coriolis and central acceleration

49. What will be the effect if the crew of an aircraft switch off the power to his IRS whilst in flight, before switching it back on a few seconds later?

It must be re-aligned whilst in flight

It cannot be used and must be shut down or the gyros will topple

It cannot be used for navigation, but can be used to provide attitude information

The system will operate normally

50. Which of the following statements is true of a Ring Laser Gyro?

It is not necessarily fixed to true north but takes along time to erect

It is not necessarily fixed to true north and is quick to erect

It is fixed to true north and is quick to erect

If doesn't suffer from 'lock in' and is unaffected by the earth's gravitational force

Question Bank

Questions for INS/IRS/FMS