OPERATOR’S MANUAL
CMA-9000 FLIGHT MANAGEMENT SYSTEM
INERTIAL NAVIGATION MODE
The is used in combination with an inertial navigation/reference system meeting the requirements of FAA AC
25-4 and/or 14 CFR Part 121 Appendix G. Subject to a time limitation for the inertial navigation mode.
A. ACCURACY
The inertial drift rate model used for assessment of current inertial navigation accuracy assumes a 2
nautical miles per hour drift rate in the cross-track direction after the FMS is placed in the inertial navigation
mode. The inertial navigation mode in RNP airspace is time limited based on the current RNP. In Terminal
phase of flight the inertial navigation mode must not be used more than 30 minutes after it is placed in the
inertial navigation mode. In Enroute phase of flight, its usage can be extended to 60 minutes. The Inertial
navigation mode is not available for the approach mode.
B. INTEGRITY
This provides an indication of the inertial position integrity by monitoring inertial navigation accuracy and IRS
data output validity status. Based on typical MTBF values of the inertial sensor, the FMS has a probability
of misdetection by hardware of a failure condition that would cause the inertial position to be outside the
containment limit of an order of magnitude of 10
-4
per flight hour.
This probability is improved when a mixed inertial position is computed using 3 IRS sensors.
C. CONTINUITY
Based on typical values of MTBF of the inertial sensor, the FMS meets the 10
-4
per flight hour continuity
requirement.
Page 15-5
August 17, 2010
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