Textron Aviation Cessna 172S NAV III Skyhawk SP, Information Manual

Page: 340 / 490

SECTION 9 - SUPPLEMENTS CESSNA
SUPPLEMENT 3 MODEL 172S NAV III
KAP 140 AUTOPILOT
U.S.
FAA APPROVED
GENERAL
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Internal computer logic prevents the autopilot or MET system from
engaging until the KAP 140 autopilot computer has successfully
completed the preflight self-test sequence and has determined the
system is operating correctly. The preflight self-test will automatically
start when the AVIONICS switch (BUS 2) is set to the ON position.
The KAP 140 autopilot will disengage if any of the following conditions
occur:
1. Internal autopilot system malfunction.
2. Autopilot computer monitor detects either roll axis (
R ) or pitch
axis ( P ) malfunction annunciation.
3. Pitch accelerations larger than +1.4g or -0.6g caused by a servo
malfunction. The pilot cannot maneuver the airplane and cause
this condition, although some turbulence can.
4. DC electric turn coordinator malfunction.
5. The A/P DISC/TRIM INT switch on the left control wheel is
pushed.
The AVIONICS switch (BUS 2) supplies electrical power to the AUTO
PILOT circuit breaker from AVIONICS BUS 2. The AVIONICS switch
(BUS 2) can also de-energize the KAP 140 autopilot or MET system in
an emergency.
The following circuit breakers energize and supply protection for the
KAP 140 autopilot:
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LABEL FUNCTIONS
AUTO PILOT A pullable circuit breaker on the AVIONICS BUS 2
energizes the KAP 140 autopilot computer and the
roll, pitch and pitch trim servos.
WARN A pullable circuit breaker on the CROSSFEED BUS
supplies power for the PITCH TRIM annunciation
on the Garmin G1000 PFD.
172SPHAUS-S3-01
S3-6
For
Training
Purposes
Only