OPERATOR’S
MANUAL
CMA-9000 FLIGHT MANAGEMENT SYSTEM
Page 1-3
November 19, 2009
NAVIGATION MODES
The CMA-9000 FMS is providing a Military or Civil configuration option; integrity monitoring and resulting
consequences as required by TSO-C115b, AC20-130A and DO-236A are the main differences between the two
options.
CIVIL NAVIGATION MODE
When in the civil navigation option, the sensor navigation solutions will be assumed not to have integrity unless
proven otherwise. The navigation modes selection logic is geared to safety (integrity) and the CMA-9000 FMS
may force mode transitions to remain in a navigation mode with integrity, thereby also preventing unnecessary
alarms from being raised. This configuration option is intended to fully comply with TSO-C115, AC20-130A and
the integrity requirement of DO-236A.
The CMA-9000 FMS will determine integrity, availability and accuracy for each navigation mode solution.
A navigation solution will be available if sufficient data required to compute the solution is received from the
sensor source and no critical failures are detected. For each navigation solution, a horizontal position sensor
value, Navigation Performance (NP), will be determined. The probability of the error exceeding the NP
containment value will be no more than 10
-5
per hour for the variables monitored. For some navigation solutions,
insufficient data may not ensure that the required probability is always met. In this case, when in the military
navigation option, the CMA-9000 FMS will nevertheless compute a NP value using the available data. In this
same case, when in the civil navigation option, the CMA-9000 FMS will make the NP value unavailable.
When in the civil navigation option, a navigation solution will be deemed to have integrity if:
•
The solution’s NP value is less than the active error limit and,
•
For some sensors where the NP does not include all the necessary variables to ensure the required
probability is always met, other criteria ensuring integrity are met. If integrity can never be assured, the
CMA-9000 FMS will declare the navigation solution for a specific sensor never having integrity. The error
limit can be configured to either Phase of Flight (POF) or Required Navigation Performance (RNP).
All accuracy-based transitions will use the 95% probability error statistics and will include a hysteresis value of
100m, except for the transition from GPS to INS/GPS sensor and the transition from VOR/DME with integrity to
DME/DME with integrity. The transitions for these two cases will be done without hysteresis. This is also
applicable when the navigation sensor cross-check is configured.
In a configuration with multiple FMSs, a
hysteresis of 100m will also be applied when switching from a sensor to another identical sensor but from a
different FMS.
The CMA-9000 FMS has the following navigation modes: Hybrid GPS/INS, GPS (or cGPS), mGPS, DME/DME,
VOR/DME/TACAN, hybrid INS/DVS, Inertial, Doppler, KALMAN and Dead-Reckoning (DR). The availability of
specific navigation modes depends on the equipment configuration.
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