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UP PERIOD.
d. POWER SWITCN STBY OR PWR
I). MODE awITCH.. .ACLS
\ v- &MILE DME FIX 1,200 FEET
CCCE NGAGED
AFCSANADL TITVDHE OLD ACQUISITION WINDOW
FINAL REPORT
FEET--112MILE
REPORT: “SIDE NUMBER
COMMANDCONTROL” ’ 170° RADIAL
\
1 70° RADIAL \
La* I,““” I-CSI
TOUCHDOWN -?!A
TOUCHDOWN
1. APC DISENGAGES
AUTOMATICALLY.
2. SELECT MRT BOTH
THROTTLES AND
RETRACT SPEEDBRAKES.
3. ANTlClPATE BOLTER.
BDLTRl?tWAVRDFF
PROCERDASINCU
CAaR Ill Pm-raw.
Figure 17-4. ACLS Mode I and II Approaches
ORIGINAL
NAVAIR Ql-F14AAD-1
ofhis intentions. The ground controller will then disable
the flight director commands and enable the autopilot
commands. Until this is done, the pilot will not have
the capability to couple the autopilot to the ACLS
commands. The only information that is displayed on
the HUD during Mode I approachesis the ACLS tadpole
situation information and the ILS needles situation
information.
17.4.4 Landing Phase. As the aircraft continues its
approach and passes through the 4-nm ACLS radar acquisition
window, a smooth transition, not requiring pilot
action, occurs. If tacan information has previously
been selected (for the approach phase), the pilot could
use this information to land. Assume, however, that
AWL. has been selected, ILS and ACL information is
being displayed on the HUD and VDI.
At the radar acquisition window, the AIKSPN-42 radar
acquires the aircrag with the aid of the airborne radar
beacon augmentor, and the system automatically sends
a discrete indicating radar lock-on that illuminates the
ACL READY advisory. Transmission of vertical and
lateral glidepath errors and flight director commands,
derived by the AN/SPN42/46 radar, commences. The
glidepath error signals drive the ACL tadpole on the
VDI and HUD. The flight director symbol is selected for
display by boxing the FLT DIR pushbutton on the AWL
VDI MFD format. ‘Ihe flight director display information
is computed by the mission computer using navigation
system parameters and data-link information, if
desired. If the pilot intends to make a Mode I approach,
he must advise the ground controller of his intentions.
The ground controller will then disable the flight directorcommands
and enable the autopilot commands. Until
this is done, the pilot will not have the capability to
couple the autopilot to the ACLS commands. The only
information that is displayed on the HUD during Mode
I approachesis the ACLS tadpoles ituation information
and the ILS needles situation information.
The HUD and VDI symbology has thus been determined
for the landing phase and no further pilot selection
is required (unless a system malfunction occurs).
The mode of operation for this phase of the landing is a
function of the type of equipment used. In particular,
there are thnx modes of landing applicable: Mode I,
Mode II, and Mode III.
17.4.4.1 Mode I Landing Sequence
Note
Refer to paragraph 2.24.4.7, Automatic Carrier
Landing (ACL), for further information
on ACL.
The landing system (CATCC) (Figure 174) generates
a coupter availabre discrete that illuminates the A/P
CPLR advisory and indicates that the pilot has the option
of coupling the AFCS to data-link commands of pitch
and bank. At this time, the aircraft should be in a landing
configuration with APC, DLC, AFCS, and altitude hold
engaged.
Note
TheradarshouldbeinSTY orPULSEsearch
to avoid beaconi nterferencep roblems.
The AFCS should be armed in the ACL relief mode
with the A/P REF advisory on, indicating that a pilot
reliefmode (in this case,A CL) hasb eens electedb ut not
engagedT. he pilot can couple the AFCS to the datal ink
by means of the autopilot engage button on his control
stick, at which time, ifthe AFCS is functioningproperly
and the ACL interlock is true, the AP REF advisory will
go out. The pilot should report coupled; at which time,
the controller will send a discrete command control message
that illuminates the CMD CONTROL advisory.
The NTDS begins transmitting data-link and pitch and
bank commands to the aircraft. The autopilot (AFCS)
actuates the appropriate control surface to execute the
desired command, while the autothrottle (APC) maintains
approach angle of attack by controlling the throttle
setting.
Whenever the aircrafi exceeds the Mode I flightpath
control envelope, the system automatically sends a signal
to uncouple the AFCS (A/P CPLR advisory goes
　
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本文鏈接地址：F-14D 飛行手冊 Flight Manual 2(148)