Section III. NAVIGATION
The navigation equipment group provides the
pilot and copilot with instrumentation required to
establish and maintain an accurate flight course and
position, and to make an approach on instruments
under instrument meteorological conditions. The
determining attitude, position, destination range and
bearing, heading reference, and groundspeed.
3A-14. AUTOMATIC FLIGHT CONTROL SYSTEM
a. Description. The automatic flight control
system provides fully digital, dual channel, fail passive
operation in flight director, autopilot, yaw damper, and
The pilot can couple the left or right EFIS to
either automatic flight control system for control of the
The dual flight control computers provide digital
processing of heading, navigation, and air data
information to satisfy the pilot's requirements. The
data is presented to the pilots on the altitude and
vertical speed indicators and EFIS indicators.
The flight control system displays heading,
barometric altitude, selected alert altitude, radio
altitude, short and long range navigation, course
deviation, glideslope deviation, to-from indication,
VOR/DME distance information. Display of weather
radar and lightning sensor system information on the
EHSI is also provided.
Lighted annunciators denote selected flight
mode, altitude alert, decision height, and go-around
mode engagement. Pitch, roll steering commands,
and heading are displayed on the Electronic Attitude
Display Indicators (EADI).
The pilot's and copilot's symbol generators are
the focal point of information flow in the systems. The
symbol generator converts information to video and
deflection formats required by the EADI and EHSI
displays, and provides analog steering information to
the flight director/autopilot interfaces.
When engaged and coupled to the flight director
commands, the flight control system will control the
aircraft using the same commands displayed on the
EADI. When engaged and not coupled to the flight
director commands, manual pitch and roll commands
may be inserted using the Control Wheel Steering
(CWS) switch on the pilot's or copilot's respective
control wheel or the autopilot pitch wheel and turn
knob located on the pedestal extension.
The digital automatic flight control system
consists of the following components:
1. Two autopilot/flight director computers
2. Two air data computers (KDC 481).
3. Two altitude and vertical speed indicators
4. Five primary servos (KSA 470). They are
aileron, rudder, elevator, rudder trim, and
5. One autopilot controller (KMC 440).
6. Two autopilot monitors (KMC 440).
7. Two gyro adapters (KDA 430).
8. Two vertical gyros (KVG 350).
9. Two directional gyros (KCS 305).
10. Two rate turn gyros (KRG 332).
11. Two mode selectors (KMS 446).
12. Two EHSI (ED-551A).
13. Two EADI (ED-551A).
14. Two EFIS control panels (CP-467).
(KCP 420). The autopilot/flight director computers
provide all flight director and autopilot command
computations as well as safety monitoring functions.
The computers are fully digital and employ dual
channels for command computation. Each calculation
is computed separately and simultaneously by each
channel, with the results compared for consistency by
a third channel devoted to system monitoring. The
computers are fail passive to prevent the possibility of
servo overcontrol by both disengaging the affected
servo motor clutch and shutting off motor drive power