Honeywell PRIMUS 1000 - AP Disconnect Switch; Autopilot Power-Up Test; FGS Caution and Advisory Messages; Pitch Wheel and Turn Knob Controls

PRIMUSr 1000 Integrated Avionics System
A28--1146--112--00
6-5
Flight Guidance System (FGS)
Remote Autopilot Switches and Annunciators
D Pitch Wheel and Turn Knob Controls -- Refer to the autopilot
controller section (page 6--6), for a description of the PITCH wheel
and TURN knob controls.
D AP Disconnect Switch --TheAP disconnect switch is mountedon
the control wheel. When pushed, it disconnects the autopilot and
yaw damper.
D TCS Button -- The TCS button is mounted on the control wheel.
When pushed, the pilot can change aircraft attitude, altitude,
airspeed, and/or vertical speed, without permanently disengaging
the autopilot.
D GA(Go--Around) Button--Thego--aroundbuttonislocatedonthe
throttle. Under normal conditions, if the autopilot is engaged, it
remains engaged and the AFCS commands coupled go--around
minimumspeedholdfunctionforthecommandbars.Ifonlytheflight
director is available, a fixed pitch of 8° nose--up is commanded.
Autopilot Power--Up Test
When the autopilot is powered up, it performs a self--test on the servo
circuits, and the autopilot control and disconnect paths.
FGS Caution and Advisory Messages
The engine instrument and crew alerting system (EICAS) displays
messages that relate to the FGS. Table 6--2 contains the red warning
FGS messages that are shown on the EICAS. Table 6--3 contains all
the FGS amber caution messages.
Message Description
AUTOPILOT FAIL Autopilot has disengaged and
indicates failed.
PIT TRIM 1 INOP Main pitch trim is inoperative.
PIT TRIM 2 INOP Backup pitch trim is inoperative.
Red (Warning) Flight Guidance System Messages
Table 6--2