Table of Contents
5.
System Limits
This section describes limits of the flight guidance system's major
functions, which are referred to throughout Section 6, Modes of
Operation.
ATTITUDE DIRECTOR INDICATOR (ADI) COMMAND
CUE
The cue rolls or pitches to indicate an attitude that will accomplish a
smooth transition to the desired flight path.
If the information required to fly the flight path becomes invalid, the
mode requiring the information will deselect.
GLIDESLOPE CAPTURE
The following conditions are required for glideslope capture:
D
Glideslope is valid
D
Glideslope is armed
D
The localizer mode is captured
D
Glideslope deviation is less than two dots
D
Either of the following is satisfied
— The vertical beam sensor is tripped, or
— Glideslope deviation is less than 20 mV.
GLIDESLOPE GAIN PROGRAMMING
Gain programming starts after the vertical beam sensor trips. The gain
is programmed as a function of radio altitude. If the radio altimeter is
invalid, gain programming occurs at glideslope capture and is controlled
by a height–above–runway estimator. The value estimated is a function
of glideslope capture, glideslope track, and middle marker.
If radio altitude or total air temperature is lost, data is degraded.
A28–1146–134
REV 1 Jan/03
R
PRIMUS
1000 Integrated Avionics System
System Limits
5-1
- Quick Links:
- The Primus R 1000 Integrated Avionics...
Hide quick links:
Table of Contents
Troubleshooting
