Esterline CMA-9000 - Inertial Navigation Mode

OPERATOR’S MANUAL
CMA-9000 FLIGHT MANAGEMENT SYSTEM
INERTIAL NAVIGATION MODE
The purpose of the FMS/inertial sensors interface is to provide a stand-alone inertial navigation mode for use
when stand-alone GPS navigation and radio navigation are not possible.
Reversion to the inertial navigation mode is automatic upon loss of GPS and radio navigation.
Depending on the inertial sensors installed in the aircraft, the FMS will receive and process inertial data which
may include position, ground speed, altitude, E-W and N-S inertial velocities, baro-inertial altitude, true and
synthetic magnetic heading, status and maintenance data.
The inertial navigation mode is based on the FMS-calculated mixed inertial position, track and ground speed.
The mixed inertial position is computed as a weighted average of all operational inertial sensor positions.
When in GPS or DME navigation mode, each FMS calculates a bias vector between its system position and the
mixed inertial position.
When the inertial navigation mode becomes active, the mixed inertial position is corrected with the bias vector in
order to prevent large FMS position change.
The actual navigation performance (ANP) of the mixed inertial position is derived from the inertial drift rate, the time
elapsed since inertial navigation mode became active, and the system ANP when the inertial navigation mode
became active. The FMS computes an inertial ANP based on a drift rate of 2 nautical miles per hour of inertial
navigation.
1. Display the IRS STATUS 1/X page by pressing [INIT REF], <NAV STATUS> (LSK 5R) and <IRS> (LSK
4R).
LASEREF_V installation:
1R
2R
3R
4R
5
R
IRS1 STATUS 1/X
POSITION
N45
o
34.25 W122
o
45.12
MODE
NAV
HDG/DA TK/GS
060
o
/ R99
o
045
o
/140KT
PITCH/ROLL ALT
D15
o
/ R10
o
5000FT
VERT SPD
+175
FT/MIN START TEST>
<NAV STATUS ACCURACY>
1L
2L
3L
4L
5L
6L
6R
Page 12-7
August 17, 2010
DRAFT