Esterline CMA-9000 - Gps Navigation Mode; Accuracy; Integrity; Continuity

OPERATOR’S MANUAL
CMA-9000 FLIGHT MANAGEMENT SYSTEM
PERFORMANCE, MONITORING AND ALERTING
When configured to ANP/HIL=1.0, the ANP presented to the aircrew on the PROGRESS page represents the
99.999% probable radial position estimation error (PEE).
The FMS monitors the ANP and generates the “CHECK ANP” CDU alert message when the ANP exceeds the
current RNP.
NOTE: That the condition has to be present for 3 seconds before the message is displayed.
In GPS mode, the FMS activates the INT (integrity) lamp when the HIL exceeds the current RNP.
GPS NAVIGATION MODE
A. ACCURACY
When installed in accordance with the Installation Manual, the GPS navigation mode exceeds the 95% 2D
accuracy requirements of AC20-130A. A typical 95% probable position estimation radial error is 0.04 nm.
B. INTEGRITY
GPS-based position integrity is the GPS HIL computed by the Receiver Autonomous Integrity Monitor
(RAIM) function of the integrated GPS Sensor Module. HIL is expressed in nautical miles and represents the
radius of a circle centered around the estimated GPS position, such that the probability that the aircraft’s
true position lies within the circle is 99.999% when no satellite failure exists and 99.9% under all conditions
of satellite failure.
This exceeds the 10
-5
per flight hour requirement for containment integrity for RNP operations as defined in
RTCA-DO-236B/DO-283A.
C. CONTINUITY
Based on typical values of the Mean Time Between Failures (MTBF) of the GPS receiver and on the
industry-accepted failure rate of the GPS satellites (10
-5
/hour/satellite), the FMS meets the 10
-4
per flight
hour continuity requirement.
Page 15-3
August 17, 2010
DRAFT