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when the HARS inertial platform has gone into the free inertial mode if
MUX switch is in SEC.
8 Heading Scale Helicopter magnetic heading scale.
9 Cued LOS Reticule A virtual reticule indicating the cued LOS to the appropriate crew
member. Used with the cueing dots.
10 Missile Constraints Indicates the required orientation to align the helicopter into constraints
for Hellfire missile engagements. When all constraints for the mode of
engagement are satisfied, the box will go from ’dashed’ to ’solid’.
11 Radar Altitude A digital display of radar altitude. Displays in 1-foot increments to 50 feet
and in 10-foot increments above 50 feet.
12 Rate of Climb An analog display of rate of climb moving along the left side of the
vertical scale. Tick marks designate 500 and 1000 fpm rates of climb or
descent.
13 Radar Altitude A vertical scale for the analog display of radar altitude. Tick marks
Vertical Scale designate 10-foot increments from 0 to 50-feet, and 50-foot increments
from 50 to 200 feet. The scale is blanked when radar altitude is greater
than 200 feet.
14 Radar Altitude An analog display of radar altitude moving within the vertical scale; also
Vertical Tape blanked above 200 feet.
15 Skid/Slip Lubber Represent the limits for ’ball centered’ flight.
Lines
16 Skid/Slip Ball Indicates the amount of skid or slip the helicopter is experiencing.
17 Cued LOS DOT Indicates the cued LOS location within the field of regard. The cued LOS
DOT will flash when the HARS inertial platform has gone into the free
inertial mode.
18 Field of View Represents the instantaneous FOV of the crewmember sensor within the
field of regard.
19 Sensor Field of Represents the total gimbal limits possible for the respective crew
Regard member sensor.
20 High Action Display Refer to paragraph 4.28.
4-4 Change 3
TM 1-1520-238-10
Table 4-1. Flight Symbology Definitions - continued
Fig. 4-1
Ref No.
21
22
23
24
25
26
Symbol Name Description
Rocket Steering Indicates the required orientation to align the helicopter into constraints
Cursor for 2.75 inch FFAR rocket engagements. During fixed or flight stow
rocket delivery, a broken I beam will appear.
Hover Position Box Displays helicopter relative position when bob-up mode is selected and
represents an 8 foot square. Maximum displacement is 48 feet laterally or
longitudinally. The Hover Position Box drifts while in a stationary hover.
A drift of 6 feet the first minute is possible, and as much as 23 feet after 5
minutes when using EGI with GPS keyed tracking 4 or more satellites. If
these conditions are not met, a drift of 21 feet per minute is possible.
Head Tracker Indicates the pilot head position relative to the center line of the
helicopter. This is a virtual symbol whose range of display is 30 degrees
vertically and 40 degrees horizontally about the nose of the helicopter.
When CPG selects PLT/GND ORIDE and SIGHT SEL NVS, this symbol
indicates his head position.
Airspeed A digital display of true airspeed when the ADSS is turned on or not
failed. If the ADSS is OFF or failed, display is ground speed in knots from
the doppler navigation system. Range is 0 to 200, omnidirectional.
Horizon Line Indicates pitch and roll attitude of the helicopter.
Engine Torque Indicates the engine torque output by the engines. The magnitude is the
larger of the two engine torque values. If a greater than 12% torque split
occurs between engines, the displayed torque value will flash. At an
engine torque value of 98% or higher, a box around the torque value
flashes to indicate an impending engine torque limit. Symbolic torque
value maximum is 120%.
4.4 VIDEO DISPLAY UNIT (VDU).
The VDU (fig 4-2) is located in the pilot vertical instrument
panel (fig 2-9). The basic configuration has a red
night filter which is stored in a bracket on top of the
unit. The -3 configuration VDU has a gray night filter
which is stored in a protective pouch on top of the unit.
The red and gray filters are used on evening and night
flights to provide a display which does not affect the pilot
night vision. The VDU has the capability of displaying
the video from either the pilot or CPG selected sensors
independent of the IHADSS. This permits the pilot
to have a simultaneous display of the PNVS video on
the HMD and CPG video on the VDU. In the event of
pilot HDU failure, a limited night terrain flight capability
is available by selecting PLT on the VDU and placing
the PNVS in the NW FXD position. The VDU receives
28 vdc power from the No. 2 essential dc bus and
　
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