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to voice radio commands from the final controller
to keep the aircraft on the proper glideslope. From
the radar azimuth and elevation displays, the final controller
determinest he aircrafiposition withrespectto the
desired glidepath and gives guidance to the pilot.
17.1.4 Flight Director. The pilot flies the aircraftso
that the FPM stays inside the flight director symbol
on the HUD. The flight director symbol provides
glideslope and centerline steering information computed
by the mission computer using navigation system
parameters and data-link information from the
SPN-42/46 ACLS system. The box with the three dots
provides the pilot with optimal glidepath intercept and
following when the flightpath marker is inside the
flight director box and the three dots are aligned with
the wings and the tail of the flightpath marker. The
horizontal deviation of the flight director symbol from
the FPM represents the error between the commanded
and actual bank angle. The. vertical deviation represents
the error between the commanded vertical rate.
The flight director symbol also rotates an amount corresponding
to the error between the bank command
and the bank attitude to give an indication of the size
of the bank correction required (primarily usefirl for
following large bank commands during centerline
captures). The vertical deviation is scaled on the HUD
17-l ORIGINAL
NAVAIR 0%Fl4AAD-1
so that it gives an indication of the vertical flightpath
angle correction required.
17.2 AIRCRAFT SUBSYSTEMS
Mode I (automatic) landings are possible only if the
ACLS installation, including data link, AFCS, radar
beacon and augmentor, inertial navigation system,
and ACLS displays (MFD and/or HUD) are all fully
operational. The approach power compensator should
be used during the coupled portion of the approach.
Mode II (manual) landings can be made using displayed
crosspointer information from either the data
link or the AN/ARA-63 receiver decoder, or both
(providing dual displays).
17.2.1 Data Link. Data-link (link 4A) messagesa re
received and transmitted by a UHF frequency-shift-keymodulated
radio link. Data link receives control messagesi
n serial form from the NTDS and processese ach
messagea s necessary.F or ACL, the position error information
is furnished to the MFD and/or HUD ACL
steeringi ndicator, discretem essagesa ppearo n MFDs 1
and 3, and control information is provided for the AFCS.
Reply messages are transmitted to the NTDS with detailed
information on aircraft heading, speed, altitude,
Ihe1 quantity, weapons, stores, and autopilot status.
The shipboard data link continuously transmits a universal
test message and a monitor control message.
When in operation, the UTM or MCM is used by the
aircraft as a self-test feature. The aircraft data-link system
self-test is performed by selecting AWL steering on
the MFD. Only the pilot can deselect AWL steering
from the MFD VDI format once selected.
Note
AWL steering is only available in the TLN
mode. In A/A and A/G, the AWL pushbutton
selection on the MFD VDI format is
removed.
17.2.2 Automatic Flight Control System. The
AFCS performs two functions: stability augmentation
and autopilot.
Stability augmentation (STAB AUG) provides added
stability to the aircraft and is, in general, necessary for
effective aircraft control.
The autopilot ACL mode can be engaged only after
engaging all STAB AUG axes and then by placing the
AUTO PILOT ENGAGE switch in ON. Selection of
ACL on the AFCS control panel arms the mode and
displays the A/P REF advisory on the pilot MFD No. 1.
A/P REF indicates that an AFCS pilot relief mode has
beens elected( in this case,A CL), but not engaged.T he
pilot engages ACL through the reference engage switch
on the stick grip, at which time the A/P REF advisory
goes out.
Note
If a pitch parallel actuator force link disconnect
occurs prior to an ACLS approach, the
A/P REF advisory may go out when coupling
is attempted, but the aircraft will not respond
to SPN-42 commands and the aircraft will
uncouple when the first pitch commands are
received.
Following ACL engagement, the pilot can take control
of the aircraft by simply overriding the data-link
commandsw ith his control stick. This causesim mediate
disengagement, and the AFCS will again revert to
STAB AUG. Refer to paragraph 2.24.4.7, Automatic
Carrier Landing, for further information on ACL.
17.2.3 Radar Beacon (ANIAPN-164). The radar
beacon enhances aircraft tracking (range and accuracy)
　
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