1) A force re-balance accelerometer in an IN system has the acceleration force balanced by a Report

constant force

linear force

non-linear force

2) An accelerometer in an IN system must be able to detect accelerations down to Report

10⁶ g.

10² g.

10³ g.

3) A laser gyro output is Report

directly proportional to frequency addition

directly proportional to angular turning rate

inversely proportional to angular turning rate

4) In an IN system, Coriolis effect is the result of Report

gyro wander

platform misalignment

the effect of the earth's rotation on a stable platform

5) The Inertial Navigation System computes distance from acceleration by Report

two successive integrations

a single integration

a differential followed by an integration

6) Coriolis effect is corrected for by Report

re-aligning the stable platform

adding a correction term to the accelerometer outputs

torquing the gyros

7) In an IN system, the output of the accelerometer is linear because of a Report

pendulous suspension

linear spring

force balance system

8) The three accelerometers on a stable platform are mounted Report

orthogonally

120 degrees apart

parallel to each other

9) In an IN system, the purpose of the stable platform is to Report

provide attitude reference

prevent unwanted acceleration affecting the accelerometers

stop the gyros from toppling

10) The type of gyro generally used in an IN system is a Report

rate gyro

rate integrating gyro

displacement gyro

11) Earth rate is approximately Report

5 degrees per hour

15 degrees per hour

84 degrees per hour

12) In a gimbal system, the stable platform is the Report

azimuth gimbal

roll gimbal

pitch gimbal

13) To prevent gimbal lock on the stable platform it is normal to use Report

a pitch gimbal

four gimbals

three gimbals

14) When the inertial platform is torqued to perform like a Schuler pendulum Report

the platform rotates with respect to the aircraft

the platform remains fixed with respect to the local vertical

the platform oscillates with respect to the local vertical

15) A Schuler pendulum has a period of oscillation of Report

8.4 minutes

84.4 seconds

84.4 minutes

16) An IN system requires data from the Report

air data computer

Doppler system

satellites

17) When in manual mode, the C.D.U. alert lamp of the IN system will flash Report

when an error is detected

thirty seconds before a track change is required.

two minutes before the next waypoint

18) TK (cross track) is the Report

perpendicular distance from the desired track.

angle in degrees that aircraft track is left or right of desired track

actual track across the earth's surface

19) The output of an INS can be fed to Report

attitude indicators

vertical speed indicators

altimeters

20) The three accelerometers on a strapdown platform are mounted Report

90⁰ to each other

120⁰ apart

parallel to each other

EASA Questions Module 11 Set 8: Navigation

Set 1: Theory of flight

Set 2: Airframe Structures

Set 3: Aeroplanes-Fuselage

Set 4: Cabin Pressurisation

Set 5: Instruments

Set 6: Avionic system

Set 7: Avionic system

Set 8: Navigation

Set 9: Electrical Power

Set 10: Electrical System

Set 11: Battery

Set 12: Equip & Furnishing

Set 13: Fire Protection

Set 14: Fuel Systems

Set 15: Hydraulic Power

Set 16: Ice & Rain

Set 17: Flight Controls

Set 18: Flight Controls_1

Set 19: Landing Gear

Set 20: Lights

Set 21: Oxygen

Set 22: Pneumatic

Set 23: Water & Waste