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not concurrent releases (incompatible) or an avionic equipment processor OFP is incompatible with
MC OFPs. The incompatible OFP(s) are indicated by a line drawn through the OFP ident. If the MC
OFPs are incompatible a line is drawn through both MC OFP idents.
2.21.6.2.3 OVRD Button. The override option allows the pilot to override the software configuration
logic when the software country ID codes do not agree with the aircraft country ID codes.
2.21.6.3 INS Terminal Data. INS terminal data can be obtained if at least one update has been
performed after flight with the parking brake on. Terminal data is displayed by selecting the following
options in sequence: MENU, BIT, MAINT, INS, and POST. Note the PER (performance error rate)
and navigation time on the FLIGHT 1, POST 1 display (see figure 2-58). Select the POST option again
and note the velocity on the FLIGHT 1, POST 2 display. Turn the INS mode selector knob to OFF.
With GPS operating, if the aircraft is flown with IAF selected, the performance error rate does not
include the time flown in the AINS mode.
Figure 2-57. CONFIG Display (Sample)
A1-F18EA-NFM-000
I-2-173 ORIGINAL
Figure 2-58. INS Postflight Data Display
A1-F18EA-NFM-000
I-2-174 ORIGINAL
2.22 JOINT HELMET MOUNTED CUEING SYSTEM (JHMCS)
The JHMCS allows the aircrew to target and employ existing SRMs and High Off-Boresight
(HOBS) weapons, such as the AIM-9X, and cue the radar, FLIR, and other sensors. When using
JHMCS to employ HOBS weapons, the aircrew can slave/acquire and shoot targets beyond the gimbal
limits of the aircraft radar and designate ground targets. The main display provides a monocular 20°
field of view that is visible in front of the pilot's right eye.
2.22.0.1 Helmet-Vehicle Interface (HVI) Connectors. The HDU is connected to the aircraft by the
HVI, which consists of three connectors. These connectors are the Quick Disconnect Connector (QDC),
In-Line Release Connector (IRC), and Helmet Release Connector (HRC). See figure 2-59.
The QDC is the primary disconnect for ejection, and both normal and emergency ground egress. The
QDC can be manually disconnected for normal egress by pushing a button on top of the QDC and
separating the top half. During an ejection or emergency egress the QDC is disconnected via an aircraft
mounted lanyard when a force of 18 to 25 pounds is applied. When the QDC is not connected, the
aircraft QDC should be properly stowed in its receptacle. When the QDC is not properly connected and
the system is on, an HMD advisory is generated.
· Low voltage is present on the exposed QDC pins when the HMD
control knob is not in OFF. To prevent a minor electrical shock from
contact with exposed pins, ensure the HMD control knob is OFF
whenever the QDC is disconnected.
· To prevent damage to the QDC and aircraft components, make sure
the aircraft QDC is properly stowed in its receptacle when not mated
to the pilot's QDC.
The IRC is a back up disconnect which functions in the event of QDC failure. The IRC is attached
to the left aft console and requires a force of 50 to 90 pounds to disconnect.
The HRC allows the cable to disconnect should the helmet be lost during ejection. The HRC
connects to the left shoulder harness and requires a force of 50 to 90 pounds to disconnect.
A1-F18EA-NFM-000
I-2-175 CHANGE 1
Figure 2-59. Helmet-Vehicle Interface (HVI) Connections
A1-F18EA-NFM-000
I-2-176 CHANGE 1
2.22.1 HMD Off/Brightness Control. The HMD OFF/BRIGHTNESS control replaces the MAPGAIN
switch on the map gain/spin recovery panel. This rotary switch removes and applies power to the
HMD, and adjusts helmet CRT display brightness. See figure 2-60.
2.22.2 HUD Video Record Panel. A switch has been added to the HUD video record panel so that
HMD or LDDI can be selected while the other switch is used to select HUD or RDDI for video
recording. See figure 2-60 for modified video record panels.
2.22.3 Cautions/Advisories. When the MC detects a software configuration conflict while on the
ground, the MC displays a SW CONFIG caution and displays a line through the HMD S/W
configuration line on the configuration display. A FCP HMD advisory is reported if the respective
HMD connector is not connected, the QDC is not properly secured to the hip mount, coarse alignment
is invalid or has not been performed, or if the Removable Optics Module Assembly (ROMA) is not
connected.
Figure 2-60. HMD Controls
A1-F18EA-NFM-000
I-2-177 CHANGE 1
2.22.4 Configuration Check. When the JHMCS system is turned on, the MC provides the EU with
the aircraft make, model, and tail number.
2.22.5 Built-In Test (BIT). The JHMCS BIT system includes automated start-up BIT (SBIT) and
　
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本文鏈接地址：NATOPS Flight Manual 飛行手冊 1(120)