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at the actuator control rod, thus uncoupling the autopilot
from the ACL system.U pon ACL engagementt,h e par-
._ ~.^_
allel actuator centers itself automatically as a function
_..
of stick position, pitch rate.,a ndp itch attitude.C oupling
with the aircraft out of trim or in a climb or descentw ill
result in improper centering of the parallel actuator and
decreaseda ctuatora uthority in one direction. This will
greatly increaset he probability of uncoupling during the
approach since the actuator may command the control
system against the physical stop in the direction of reduced
authority and disconnect the force link. Similarly,
it is possible for the force link to disconnect during pilot
OBC iflongitudinal trim is not properly set prior to OBC
commencement. Once the force link is disconnected,
farther mode I or mode IA approachesw ill be impossible
until the force link is reset by maintenance.
2-113 ORIGINAL
. It is absolutely imperative that the aircraft
be trimmed hands-off in level, on-speed,
wings-level flight with landing checks
complete prior to coupling in order to
achieve proper centering of the pitch parallel
actuator. Engagement of ACL in any
other flight condition will seriously degradem
ode VIA flight characteristicsa nd
may result in a force link disconnect. The
recommended method for coupling is to
engage ACL after 1.5 to 30 seconds of
flight in the landing configuration with
AFCS attitude and altitude hold engaged
to utilize the AFCS automatic pitch trim
system.
. OBC commencement with less than 3”
noseup trim with flaps down or less than
zero degrees with flaps up may result in a
force link disconnect when the stick hits
the forward stick stop during the pitchparallel
actuator checks.
2.24.3.3 Automatic Pitch Trim. Automatic pitch
trim is used in all autopilot pitch modes to trim the
aircraft in order to minimize. pitch transients when disengaging
autopilot functions. The pitch servo position
is monitored to drive the aircratl pitch ttim motor at
one-tenth manual trim rate. The pilot manual trim button
on the control stick is inoperative during all autopilot
operations.
2.24.3.4 AFCS Emergency Disengage. Operation
of the autopilot emergencyd isengagep addleo n the control
stick (Figure 2-68), disengages the autopilot and
DLC. All autopilot switches will retum to OFF. The
pitch and roll SAS servosa re disengagedw hile the paddle
is held depressedD. epressingthepaddlew ith weight
on wheels reverts throttle system from the AUTO or
BOOST mode to the MAN mode only while depressed
Depressingt he paddled isengagesth ep itch and roll SAS
servos and causes the pitch and roll SAS switches to
move to OFF. The yaw SAS switch is not affected by
operationo f the autopilot emergency disengagep addle
and will remain ON.
Note
The AUTO PILOT light may or may not illuminate
when the autopilot is disengagedw ith
the autopilot emergencyd isengagep addle.
2.24.4 Pilot Relief and Guidance Modes
2.24.4.1 Control Stick Steering. With the autopilot
engagedt,h e aircraft may be maneuveredu sing control
stick steering. In control stick steering mode, the
AFCS automatically synchronizes to the new attitude.
2.24.4.2 Attitude Hold. Attitude. hold is selected by
setting the AUTOPILOT ENGAGE switch to ENGAGE.
To change attitude, use control stick steering. Reengagement
is achieved by releasing pressure on the stick. The
autopilot will hold pitch attitudes up to *30” and bank
anglesu p to %60”.I nertial measuremenut nit failure will
cause mode disagreement and the engage switch will
return off. The mode may be reengaged using the
SAHRS as a reference.
2.24.4.3 Heading Hold. Heading (HDG) hold is
engaged by setting the HDG-OFF-GT switch to HDG.
AAer maneuvering the aircrafi to the desired reference
headiig, release the control stick at a bank angle of less
than i5O. The autopilot will then hold the aircraft on the
desired heading. Heading reference is obtained t?om the
SAHRS via the converter interface unit.
2.24.4.4 Ground Track. To engage ground track, set
the HDG-OFF-GT switch to GT. When the A/P REF
advisory legend (on upper left side of the MFD) appears,
press the nosewheel steering pushbutton on the control
stick grip. When the A/P REF legend goes off, the mode
is engaged.
Disengagemenwt ill occur if more than l-1/2 pounds
lateral stick force is applied and will be indicated by the
A/p REF legend. The ground-track mode may be reengaged
by releasing the stick force and pressing the nosewheel
　
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本文鏈接地址：F-14D 飛行手冊(cè) Flight Manual 1(117)