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re-engaged. If light remains on, MACH TRIM
TEST/ON/OFF switch must be set to OFF.
SERVO MONITOR QSTAJBAjpMTN
PITCH
YAW
ROLL
J
YD INOP SWITCH/LIGHT
Amber YD INOP light comes on if a yaw
damper channel fails. When pressed, the light
is reset.
MACH
TRIM
INOP
YD INOP
YD FAIL
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MACH TRIM
TEST,
ON
OFF
MACH TRIM TEST/ON/OFF SWITCH
Three-position, spring-loaded switch.
ON—Mach trim is engaged.
TEST-When held at TEST, the NUP STAB
pointer on the control surface trim indicator
moves up. When released, the MACH TRIM
INOP light comes on, the MASTER CAUTION/
RESET switch/lights flash and the FLT CONT
light on the 10-channel system annunciator
comes on.
YD FAIL LIGHT
Red YD FAIL light flashes if there is a channel
failure which the autopilot and stability
augmentation monitors can not identify. Light
can not be reset.
DISENGA
Y/D DISENGA PUSHBUTTON
When pressed, disengages yaw damper.
I
Stability Augmentation Control Panel SECTION 4
Figure 2 Page 6
Oct 03/83
canaaair
chanenQer
OPERATING MANUAL
Failure of a Mach trim channel is indicated when the amber MACH TRIM INOP
switch/light on the stability augmentation control panel comes on. To
alert the pilots immediately of this condition, the red MASTER/CAUTION
PRESS TO RESET switch/light flashes and FLT CONT light on the master
caution system annunciator panel comes on. The Mach trim can be re-engaged
by pressing the MACH TRIM INOP switch/light if the failure was momentary.
If the failure persists the Mach trim system must be disengaged by
switching the MACH TRIM TEST/ON/OFF switch to OFF.
To test the Mach trim system, the MACH TRIM TEST/ON/OFF switch is held in
the TEST position and the NUP STAB (nose up pointer, stabilizer) pointer on
the control surface trim indicator moves up. When the switch is released,
the MACH TRIM INOP switch/light comes on, the red MASTER/CAUTION PRESS TO
RESET light flashes and FLT CONT light on the master caution system
annunciator panel comes on.
6. FLIGHT DIRECTOR COMPONENTS
A. Attitude Director Indicator
The ADI is an integrated attitude director indicator which displays pitch
and roll attitude, flight director commands, glideslope deviation,
localizer deviation, radio altitude, rate-of-turn, speed command,
appropriate flags, inclinometer, attitude self-test switch, and mode
annunciation.
B. Horizontal Situation Indicator
The HSI is an integrated horizontal situation indicator that displays
heading, course deviation, vertical deviation, ADF or NAV bearing, selected
heading, selected course with digital read-out, DME distance, waypoint
alert light and appropriate annunciators and flags. The indicator also
provides heading and course error signals to the flight director computer.
C. Remote Heading and Course Select Controller
The remote heading and course select controller contains a HEADING control,
a COURSE 1 control and a COURSE 2 control. The HEADING control drives both
the pilot's and copilot's HSI heading bugs. The COURSE 1 control drives
the pilot's HSI course select pointer and the COURSE 2 control drives the
copilot's HSI course select pointer.
D. Flight Director Mode Selector
The flight director mode selector contains the mode select switch/lights
for selecting flight director path modes.
SECTION 4
Page 7
Oct 03/83
cacnhaadnaeinr tjer
OPERATING MANUAL
E. Flight Director Computer
The flight director computer contains all computation and mode selection
electronics for flight director flight path modes.
F. Rate Gyro
The rate gyro drives the rate-of-turn display on the ADI and provides a
damping input to the stability augmentation system.
G. Vertical Gyro
The vertical gyro provides roll and pitch data to the ADI, flight director
computer, autopilot and weather radar.
H. Directional Gyro
The directional gyro provides heading data to the HSI, radio magnetic
indicator, autopilot, and VHF navigation system.
I. Instrument Comparator
The instrument comparator compares information from the pilot's and
copilot's instruments and VHF navigation receivers. Roll and pitch
attitude, heading, glideslope and localizer deviation are also monitored.
A visual warning is provided if a difference exists between any of the
compared signals.
J. Touch Control Steering
Touch Control Steering (TCS) allows the pilot to momentarily take control
of the aircraft without disengaging the autopilot. When the TCS button on
either control wheel is pressed, the servo clutches disengage to allow the
　
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