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3.18.2 Controls and Functions. Controls for the mag-netic compass set are on the front panel of the unit. The function panel of each control is as follows:
CONTROL  FUNCTION
Null Meter  Moves left (+) or right (v) of center to indicate misalignment (synchronization) of the AN/ASN-
43.

Mode Selector Selects either magnetically (SLAVED-SLAVED or FREE gyro operation FREE) of the AN/ASN-43.
Null Control  Is manually pressed and turned to
PUSH-TO-SET  null the annunciator, thereby synchronizing (electrically and mechanically aligning) the AN/ ASN-43. Turns compass card of HSI for alignment.
3.18.3 Operation.
3.18.4 Starting Procedure.
1.
Mode selector -As desired.

2.
Null control -Push, and turn in direction indi-cated by null meter (+ or v) until annunciator is centered. In SLAVED mode, during normal operation, the annunciator will oscillate slightly about the center position; however, during cer-

tain helicopter maneuvers the annunciator will move off center.
3. HSI -check to see that HSI heading agrees with a known magnetic heading.

3.19 ELECTRONIC NAVIGATION INSTRUMENT DISPLAY SYSTEM.
The instrument display system provides displays for navigation and command signals on a vertical situation in-dicator (VSI) and a horizontal situation indicator (HSI) for pilot visual reference. The system consists of the two VSIs and two HSIs on the instrument panel. The system has a common command instrument system processor (CISP), two HSI/VSI mode select panels, and one CIS mode select panel.
3.19.1 Vertical Situation Indicator. The VSI (Figure 3-29), provides a cockpit display of the helicopter’s pitch, roll attitude, turn rate, slip or skid, and certain navigational information. It accepts command instrument system proces-sor signals and displays the .ight command information needed to arrive at a predetermined point. The system also monitors and displays warnings when selected navigation instrument readings lack reliability. The VSI is composed of a miniature airplane, four warning indicator .ags ATT, GS, NAV and CMD, two trim knobs ROLL and PITCH, a bank angle scale, a bank angle index on the spheroid, a turn rate indicator and inclinometer, pitch and roll com-mand bars, collective position pointer, a course deviation pointer, and a glide slope deviation pointer. Refer to Chap-
ter 2, Section XIV for a description of the attitude indicat-
ing system, and turn and slip indicator. The gyro erect switch (Figure 2-7) supplies a fast erect signal to the pilot and copilot displacement gyros, thereby considerably re-ducing the time required for the gyros to reach full operat-ing RPM. The pilot and copilot’s displacement gyros sup-ply pitch and roll attitude signals to the vertical situation indicators, automatic .ight control system, and the Doppler/ GPS navigation system. Power to operate the VSI is pro-vided from the No. 2 ac primary bus through circuit break-ers marked VSI PLT, CPLT.
3.19.1.1 Steering Command Bars and Pointer. The roll and pitch command bars and the collective position pointer operate in conjunction with the command instru-ment system processor (CISP) and the command instru-ment system/mode selector (CIS MODE SEL). Selection of HDG on the CIS MODE SEL panel provides a display of a roll signal by the roll command bar (Figure 3-29). The pitch command bar and the collective position pointer are out of view, and the CMD .ag is held from view. Selecting the CIS MODE SEL switch NAV and the MODE SEL switch VTAC ILS, the roll command bar will display roll commands from the CISP. If an ILS (LOC) frequency is tuned in, the pitch command bar and the collective com-mand pointer will also display CISP signals. If a VOR/ TACAN frequency is tuned-in, the pitch command bar and collective position pointer will be held from view. The CMD warning .ag will be held from view, indicating that the CISP functional integrity is being monitored. Refer to Figure 3-31 for VSI indications in other switch positions.
　
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