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aircrew should ensuret hat both beacon antennasa rc in
good repair and not painted. The receive antenna is located
on the lower starboard fuselage just aft of the
radome and is mounted flush with the fuselage. The
transmit antenna is a blade antenna located on the aft
portion of the chin dome (IKTV pod). Poor condition
of these antennas will seriously degrade beacon performance
and will result in degraded tracking capability
by the ANEPN-42 system.
17.4.2 Poststart Checks. Following start, the aircrew
should verify proper operation of the beacon and
data-link systems along with associated lights and advisories
and indications by performing the prescribed
built-in tests. In addition, the pitch parallel actuator
should be checked during OBC to make sure that the
force link is not totally or partially disconnected.I f any
of these systems are not functioning properly, a coupled
approach will not be possible.
17.4.3 Approach Phase. In ACL, the purpose of
the approach phase is to get the aircraft to the acquisition
window (Figure 174). At the marshaling area, some 20
miles astern of the carrier, the abaft about to land are
stacked according to fuel status and other relevant parameters
that determine landing priority, the ILS
(AN/AKA-63) systemi s energized,a ndt he properc hannel
and displays are selected. The pilot, in concurrence
with the controller, has the option ofchoosing from three
display submodes to aid him in reaching the radar acquisition
window:
1. Data-link vector
2. Tacan
3. AWL.
All are directly selectable on the VDI format of the
MPD. Switching between submodes requires a choice
between DATA LINK, TACAN, and AWL steering. If
a submode selected becomes invalid, the steering information
will cease.T he oilothas the oution of reaelectinn
will also info& thd &crew of invalid~s&ing
During the letdown from marshaling, an ANEPN-42
channel is assigned to the aircratl and a computer program
of aircraft control parameters is selected. A datalink
discrete message (the first of a series to be
transmitted), LANDING CHBCK, is sent to the aircraft
to initiate communications with CATCC and to indicate.
to the pilot that an ANjSPN-42 channel is available. The
aircraft will usually already be in a landing configuration
upon receipt of LANDING CHECK.
17.4.3.1 Data-Link Vector Approach. When
DATA LINK is selected, the DiL vector display is added
to the basic landing display. Command heading relative
to the heading tane is added to the HUD and VID disolav
and iefi side of the MI display. Data-link vector information
is available only for the approach phase (i.e., to
the radar acquisition window). When the aircraft is vectored
(D/L vector commands) to the acquisition window,
the pilot has to make a new submode selection for
the descent phase. This is not the case with the tacan
submode, as tacan information is available throughout
landing, from marshaling to touchdown.
17.4.3.2 Tacan Approach. The course deviation
indicator is used for tacan deviation along with a manually
set command heading indicator on both the HUD
and VDI display.
17.4.3.3 AWL Approach. ILS information from
the ANEPN-41 is available during both the approach
anddescentphase.SelectionofAWLontheVDIdisplay
enables vertical and lateral glideslope enor display. Final
determination of the AWL&CD mode is governed
by the ILS/ACL selection, which provides for separate
HUD and VDI selection. Additionally, the pilot may
independently select HUD flight director for display by
boxing the FLT DIR pushbutton on the AWL MI.
The normal ACLS approach mode will display the
ACL tadpoles ituation information, the ILS needless ituation
information, and the ACL flight director steering
information on the HUD. If the pilot intends to make a
Mode I approach, he must advise the ground controller
ORIGINAL 17-10
NAVAIR 01.F14AAD-1
BEFORE REACHING 6-MlLE DME FIX
MARSHAL PLATFORM 5.000 FEET
1. ARAa3 SET 4. AFCS STAB AM 1. SLOW DESCENT TO 2,000 ft,min
2. Plum DISPLAY CONTROL PANEL a, PITCH ON 2. AlRSPEED 250 KNOTS
a. MODE . . ,... ., TLN Il. ROLL ON 3. REPORT:
b. HUDDECLUTTER NORM c. YAW ON a. MODEX
c. WDAWL AWL b. PLATFORM
d. “DIMODE .,..,.,....... AWL
DEPARTING MARSHAL IO-MILE DME FIX 1,200 FEET
1. DESCENT AT 4.000 ‘thin AND 250 1. AFT-154 STaYORPWR
KNOTS 2. REPORT:
3. APN-la4 2. REPORT: 8. MODEX
1. MODE awITCH.. .NOT ACLS a MODEX b. I&MILE GATE
b. POWER SWITCH .STBY b. COMMENCINO 3. TRANSlTlON TO LANDING CONFlG
c. ALLOW 6 MINUTE WARM. c. STATE
　
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本文鏈接地址：F-14D 飛行手冊 Flight Manual 2(147)