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remaining two require pilot corrective action. In all
degraded modes there will be a loss of some operational
capability, as described in paragraphs thru 4.25.5.
442 Change 3
WARNING
TM 1-1520-236-10
PNVS turret motion maybe limited to 75 degrees left
Figure 4-16. TADS/PNVS Equipment Data
Table 4-14. PNVS Equipment Data
Parameter Function
Normal Azimuth +90 degrees/
Operating Range -90 degrees
Azimuth Stow Position -118 degrees. or greater
Elevation Operating +20 degrees/
Range -45 degrees
Field of View 30 degrees vertical/
40 degrees horizontal
Maximum Slew Rate 120 degrees per second
4.25.1 PNVS Electrical Power. The PNVS receives
115 vac power from the No. 1 essential ac bus and 28
vdc power from the No. 3 essential dc bus through the
PNVS AC and PNVS DC circuit breakers on the pilot
overhead circuit breaker panel. The PNVS is continuously
monitored by FD/LS which will illuminate the
PNVS caution light segment for a PNVS malfunction.
The on command DD/LS test (test 09-PNVS) will fault
isolate to the LRU.
4.25.2 TADS Electronic Unit Failure. In the event of a
TADS Electronic Unit (TADS computer) failure, the
PNVS will be placed in the direct mode automatically
by the fire control system. The PNVS turret will be directly
driven by the IHADSS sight electronics unit.
and 75 degrees right in azimuth; turret motion may be
erratic beyond the 75 degree azimuth position. The
message PNVS...DIRECT will be displayed in the
sight status block of the pilot’s high action display. No
corrective action is required by or available to the pilot.
4.25.3 Symbol Generator Failure. In the event of a
symbol generator failure, the fire control system will
automatically command the IHADSS display electronics
unit to display PNVS FLIR 2 on the pilot/CPG
HDU. The PNVS will continue to function normally;
however, the video displayed to the pilot will not have
symbology. VDU video will blank and the recorder will
be inoperative. Additionally, the CPG will receive
TADS FLIR 2 video on the ORT. No corrective action is
required by or available to the pilot.
If night or simulated night NOE,
reaction to the following malfunctions
must be immediate, exit of the
NOE environment maybe required.
4.25.4 PNVS FLIR or Turret Failure. In the event of a
failure of the PNVS FLIR or turret assembly, the pilot
must place the NVS switch on the collective switchbox
(figs 2-11 and 2-12) in the TADS position. TADS will be
slaved to the pilot helmet LOS and moded to WFOV
FLIR. Normally, this action will provide useable TADS
video to the pilot. However, in some cases, the TADS
FLIR video may be scrambled following loss of the
PNVS FLIR video. If this should occur, reselect PNVS
on the pilot’s collective NVS switch and then select
TADS. The out-of-synch video will be corrected. The
slew rates of the TADS turret are noticeably slower
than those of the PNVS and some gain and level adjustment
may be required to obtain optimum image quality.
4.25.5 IHADSS Failure. In the event of an IHADSS
failure, either inability to command the PNVS turret or
loss of video on the HDU, the pilot must first exit the
NOE environment. and then set the VDU control
switch to PLT (fig 4-2) and the ACQ SEL switch to
NVS FXD. This configuration will allow the pilot to fly
a fixed panel mounted display. Terrain flight capability
will be directly dependent on pilot proficiency.
4.26 WEAPONS SYMBOLOGY.
The weapons symbology is displayed to the CPG on the
video from the selected sight. The symbology is shown
in figure 4-17. Refer to table 4-15 for symbol definition.
4-43
TM 1-1520-238-10
Fig. 4-17 Ref No.
M
A
B
K
Figure 4-17. Weapons Symbology Modes
Table 4-15. Weapons Symbology Definitions
Symbol Name
LOS Reticle
Alternate Sensor
Bearing
Lubber Line
Cueing Dots
Description
Represents the line-of-sight of the crewmember selected sight.
The reticle will flash whenever the selected sight LOS is invalid
or has failed. The reticle will also flash whenever the
"ACTIONED" weapon is in a NO-GO state. The High Action
Display will prompt the crewmember for the appropriate
condition.
Indicates to the crewmember the other crewmember sensor
relative bearing with respect to helicopter center line.
Index indicates helicopter magnetic heading.
Indicates cued direction for target acquisition. All four dots
present and flashing indicate IHADSS boresight is required.
4-44
TM 1-1520-238-10
　
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