automatically resynchronize to the vertical mode.
Example: with IAS mode selected, the pilot may press
the TCS push button and manually change airspeed.
Once trimmed at the new airspeed, the TCS push
button is released and the autopilot will hold this
airspeed. If a large pitch attitude change is made, the
pilot should trim the aircraft normally before releasing
the TCS button.
changing of the autopilot regardless of
which pilot has control of the autopilot.
However, use of the TCS will cancel the
other pilot's flight director GA mode.
The OBS/LEG, SNS, and MOD keys will
cause the control display to immediately
However, the system will not actually
activate the new operational status for a
period of 1 second. Repeated presses of
these keys during this 1-second period will
reset the delay back to 1 second.
Automatic navaid selection does not occur
when operating the system in AUTO/ LEG,
VOR or TACAN, RNV APR. The pilot must
waypoint in the reference name field of
each waypoint page. This reference navaid
is the particular navaid which the VOR
navigation receiver and DME will be turned
to when this waypoint is activated.
Shutdown Procedure. ON/OFF rocker
switch Press lower half.
3B-26. FLIGHT MANAGEMENT SYSTEM (KNS-660)
System (FMS) is an integrated, long range, multi-
sensor flight management system. It may be used to
manage the entire range of navigational functions
navigation, instrument approaches, and frequencies.
The FMS serves as a computer processor/display for
inputs from a choice of sensors such as VOR/DME,
GPS, or TACAN. Navigation sensors may be selected
separately or blended within the computer. It provides
for manual operation to selected waypoints or
navigation throughout a complete flight plan. The FMS
consists of a cockpit-mounted Control Display Unit
(CDU), a remote mounted navigation computer, and
an "H" field antenna. Refer to Figure 3B-18 for an
illustration of the CDU. The FMS calculates its present
position in terms of latitude and longitude coordinates.
The flight's destination must be inserted into the FMS
in a latitude and longitude format or in a format that
the FMS can convert to latitude and longitude, such as
ICAO identifiers of navaids, airports, or intersections.
The FMS can use navigation inputs from VOR,
DME, TACAN, and GPS navaids. In addition the
system uses aircraft heading and altitude inputs.
The FMS system is protected through a
5-ampere circuit, breaker placarded FMS, located on
the overhead circuit breaker panel, Figure 2-16,
b. Data Base . The FMS incorporates a self-
contained data base. This data base consists of an
extensive library of navigation data that is loaded into
the system at the time of manufacture. This data is
updated by means of a 3 ½-inch diskette using the
data loader in the pedestal extension every 28 days.
The diskette contains updated worldwide navigation
data that is broken down into the following 10
navigational elements for each of these 10 regions:
(a) Navaids (VORTAC's, VOR/DME's,
VOR's, ILS/DME's, DME's, and TACAN's).
runway that is at least 4,000 feet in length.
runway that is at least 3,000 feet in length.
(d) Runway thresholds.
(e) Outer markers.
(f) High altitude waypoints.
(g) Low altitude waypoints.
(h) DP/STAR waypoints.
(i) Approach intersections.