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CPL Test Series
Question Bank
Questions for INERTIAL NAVIGATION SYSTEM (INS)
Answer the following questions
Test Mode
Training Mode
1. INS errors are classified as “Bounded errors” and “Unbounded errors”
A “Bounded error” is an error that is “tied” to the real wander rates of the gyros on the platform.
An “Unbounded error” is an error that increases with time, an example being the distance gone error due to a ground speed error.
A “Bounded error” is an error that is subject to sudden unpredictable random changes. Most notable during pitching manoeuvres and when raising or lowering flap and U/C.
An “Unbounded error” is an error that increases with time, an example being an increasing ground speed error due to the platform not being levelled correctly.
2. During initialisation of an INS the aircraft must not be moved until
The gyros and accelerometers are in the “null” position.
The ramp position has been inserted and checked.
The platform is levelled.
The green “ready NAV” light has been illuminated and the mode selector switch has been set to the “NAV” position
3. With reference to Inertial Navigation Systems, the functions of the integrators are: i) at the second stage of integration to suppress unbounded errors (when in the NAV mode). ii) at the first stage of integration to convert acceleration, with respect to time, into speed, (when in NAV mode). iii) at the second stage of integration to convert speed, with respect to time, into distance gone, (when in the NAV mode). iv) to align the platform (when in the level and align modes).
only (ii), (iii) and (iv) of the above statements are true.
only (i), (ii) and (iii) of the above statements are true.
all the above statements are true.
only (ii) and (iii) of the above statements are true.
4. Two checks that can be carried out to check that two selected sequential waypoints have been entered correctly are:
select DIS/TIME and check that the distance agrees with the distance on the flight plan; select DSR.TK/STS and check that the track agrees with the flight plan track for the leg.
select DIS/TIME and check that the distance agrees with the distance on the flight plan; then check that the time agrees with the flight plan time for the leg
select DIS/TIME and check that the distance agrees with the distance on the flight plan; select HDG/DA and check that the heading agrees with the flight plan heading for the leg.
select DSR.TK/STS and check that the status is less than 4; select DIS/TIME and check that the time agrees with the flight plan time.
5. In an INS the E/W accelerations are converted into an E/W speed (kt) at the first stage of integration and into E/W distance gone (nm) at the second stage of integration. This gives
departure which is multiplied by Sine of the present latitude to obtain d'long (min) which is used to automatically up-date the present longitude.
departure which is multiplied by Secant of the present latitude to obtain d'long (min) which is used to automatically up-date the present longitude.
d'long (min) which is used to automatically up-date the present longitude.
departure which is multiplied by Cosine of the present latitude of obtain d'long (min) which is used to automatically up-date the present longitude.
6. The computer of a north referenced Inertial Navigation System (INS) in flight, provides compensation for:
coriolis, real wander, apparent wander, transport wander.
aircraft manoeuvres, real wander, apparent wander, transport wander.
transport wander, apparent wander, coriolis, magnetic variation.
earth rotation, transport wander, coriolis.
7. The amber ALERT light on an INS control and display unit
illuminates if power from the aircraft bus bar has been lost and the system is operating on standby battery.
start flashing 2 minutes before reaching the next waypoint and goes out at 30 seconds to run.
illuminates steadily after passing a waypoint in manual mode, until the next leg is programmed in.
illuminates steadily 2 minutes, in AUTO mode, before reaching the next waypoint.
8. At the second stage of integration E/W speed is converted into E/W distance gone. To convert this departure into change of longitude is has to
be multiplied by Secant of the latitude
be divided by Tangent of the latitude.
be divided by Secant of the latitude.
be multiplied by Cosine of the latitude.
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