TM 55-1510-215-10
The vertical trim switch is used to adjust the selected
because of back force generated by
altitude up or down at a constant rate of approximately
the elevator downsprings or pilot
600 fpm without disengaging the mode.
induced forces.
The ALT HOLD mode is cancelled by automatic
WARNING
Glideslope capture, selection of ALT ARM/GO-AROUND
modes, or deselecting FD.
If the AUTOPILOT circuit breaker is
(11) Control wheel steering (CWS). When the
pulled,
the
red
TRIM
failure
autopilot is engaged, CWS provides the pilot with the
annunciator light on the autopilot
capability for manual maneuvering of the aircraft without
annunciator panel will be disabled
the need to disengage and reengage the autopilot, or
and only the aural alert will sound if
reselect any modes of operation. CWS is engaged by
an electric trim malfunction occurs.
continuous pressure on the CWS button, located on
If the aural alert sounds pull the
either the pilot's or copilot's control wheel. Operation of
ELECT TRIM circuit breaker and
the CWS button causes immediate release of autopilot
accomplish inflight trimming with the
servos allowing the pilot to assume manual control.
manual trim wheel.
Upon release of the CWS button, the autopilot will
reassume control of the aircraft to the original lateral,
1. AVIONICS MASTER switch - ON.
and existing vertical commands.
2. Flight director switch - Press on.
Since all engaged modes remain coupled during
CAUTION
operation of the CWS switch, their annunciator displays
will continue to show on the mode annunciator panel.
Prior to autopilot engagement insure
c. Operating Procedures.
that command V-bar commands are
satisfied.
WARNING
3. Autopilot switch (AP) - ON.
4. Autopilot modes - As required.
Insure that the autopilot has been
disengaged and check that the
d. Shutdown Procedures.
aircraft manual trim indicator is set to
1. Flight director switch - Disengage.
the takeoff position before takeoff.
2. AVIONICS MASTER switch - OFF.
Operating the autopilot on the ground
may cause the autotrim to run
Section IV. TRANSPONDER AND RADAR
3-28. Transponder (KT 76A).
(b) SBY position. The unit should be
placed in SBY after engine start for warm up. It takes
approximately 47 seconds for the transponder to warm
identification, position tracking , altitude reporting, and
up and become operational.
emergency tracking device. The unit receives, decodes,
(c) ON position. When the transponder
and responds to interrogations by search radar. The
is in the ON position the unit is operating in mode A.
range of the set is normally limited to line-of-sight. The
Mode A provides for normal operation without altitude
transponder is protected by a 3-ampere circuit breaker,
reporting.
placarded XPDR 1, located on the right subpanel. The
(d) ALT
position.
When
the
associated antenna is shown in figure 2-1.
transponder is in the ALT position the unit is operating in
b. Controls and Functions.
mode C (altitude reporting). Mode C provides for normal
operation along with altitude reporting. The aircraft
(1) Function selector switch.
Provides for
altitude is automatically reported to the ground controller
selection of OFF, SBY, ON, ALT, and TST positions.
in increments of 100 feet from minus 1000 feet up to
(a) OFF position. Removes power from
63,000 feet.
the unit.
(e) TST position. When the function
selector switch is held in the TST position the reply
annuniator should illuminate and remain illuminated until
Change 5 3-31
