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is monitored to provide failure detection and automatic
shutdown of a malfunctioning actuator channel. PITCH
STAR and ROLL STAB caution lights notify the pilot
of a malfunction. The remaining functional channel will
continue to provide half authority for the pitch and roll
axes.A utopilot modes may be engageableb ut will have
reduced authority.
ORIGINAL 2-110
NAVAIR 01.Fl4AAD-I
Figure 2-68. AFCS Controls and hiicato~ (Sheet 1 of 3)
2-111 ORIGINAL
NAVAIR Ol-IWAAD-1
NOMENCLATURE FUNCTION
0
PITCH STAB AUG Engages dual-channel pitch stability augmentation. Solenoid held in ON.
engage switch Spring-loaded to OFF
0
ROLL STAB AUG Engages dual-channel roll stability augmentatlon. Solenoid held in ON.
engage switch Sprlng-loaded to OFF
@ YA$TAB AUG engage Engages three-channel yaw stability augmentation.
@
AUTOPILOT ENGAGE - Engages autopilot. PITCH, ROLL, and YAW SAS must be
ENGAGE-OFF switch engaged. No wanup required. Engages attitude hold.
Requires weight off wheels.
OFF - Dlsengages autopilot.
0
HDG-OFF-GT switch HDG - Autopllot will lock on constant aircraft heading when aircraft is
less than f5 degrees roll.
OFF -
GTDisengages
heading hold and ground track.
Selects autopilot ground tracking computed at time of
engagement using inertial navigation system (INS) data.
Engaged by nosewheel steering pushbutton
@ ALT-OFF switch ALT - Autopilot will maintain barometric altitude. Engaged by
nosewheel steering pushbutton.
OFF - Disengages altitude mode.
0 VEC/PCD-OFF-ACL VEC/PCD - Autopilot roll axis commands steer aircraft using data link
SignSIS for VSCtOrlng. If the preclslon course direction (PCD)
discrete is present both roll and pitch axis commands are
used. Engaged by nosewheel steering pushbutton,
OFF - Disengages VEC/PCD and ACL modes.
ACL - Autopilot will accept data link signals for carrier landing, using
spollers for roll and parallel servo for pitch. Only pitch
commands are transmitted to stick movement. Engaged by
nosewheel steerlng pushbutton.
@ ACLS/AP caution light Autopilot and automatic carrier landlng system (ACLS) mode disengaged.
ORIGINAL
Figure 2-68. AFCS Controls and Indicators (Sheet 2 of 3)
2-112
NOMENCLATURE
@
A/P CPLR advisory
legend on MFD
010 zMFi advisory legend
0
PITCH STAB 1 and
PITCH STAB 2 caution
0 ROLL STAB 1 and ROLL
STAB 2 caution Iiqhts
0
YAW STAB OP and YAW
STAB OUT caution lights
@
AUTO PILOT caution
light
0 Autopilot reference and
nosewheel steering
63 Autopilot emergency
disengage paddle
FUNCTION
lndlcates the aircraft can be coupled to the ACL system for a mode I or mods
IA approach. A/P CPLR legend remains In conjunction with the CMD CTRL
legend after coupling Is accomplished.
AutopIlot mode is selected but Is not engaged. (Except attitude and heading
hold.)
One light, illuminated channel inoperative. Single channel 53% loss of
authority. Both lights Illuminated, indicates PITCH STAB failure.
One light lllumlnated channel Inoperative. Single channel, 50% loss of
authority. Both lights Illuminated, Indicates ROLL SAS failure.
I OP- One channel Inoperatlve.
NAVAIR 0%Fl4AAD-1
OUT- Two channels inoperative. Yaw stabilization inoperative.
Indicates failure of one or more of pllot relief modes
Engages the ALT, GT, ACL or VEC/PCD autopilot mode selected. Autopilot
must be engaged and compatible autopilot modes selected. Requires weigh
off wheels.
t
Disengages all aulopllot modes and releases all autopilot switches.
Disengages the pitch and roll servos and causes the pitch and roll SAS
switches to move to OFF. The yaw channels in either case are not affected.
Figure 2-68. AFCS Controls and Indicators (Sheet 3 of 3)
the three yaw channels is inoperative. Full authority is
The YAW STAB OP caution light indicates one of
retained.
Taxiing with one engine shut down and the
HYD TRANSFER PUMP off may ill&-
nate the pitch, roll, and/or yaw caution lights.
2.24.3.2 AFCS Pitch Parallel Actuator. The AFCS
pitch parallel actuator is a single-channel electrohydraulic
servoactuatotrh at providesa utomatic longitudinal
control during mode I and mode IA ACLS
approachesP. itch commands receivedb y the data link
are supplied to the parallel actuator via the AFCS pitch
computer. As a safety feature, the parallel actuator system
contains a mechanical force link that is designed to
excessive torte (greater than YU pounds) 1s encounterea
disconnect the actuator from the control system when
　
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