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(b) The digital displays indicate between 0
and 3 feet.
(c) LO caution light is on.
(d) Low altitude warning (”ALTITUDE LOW,
TOO LOW”) is heard in the headset.
(e) HI caution light is off.
(f) Off flag not in view.
b. Testing.
(1) Press and hold the PUSH-TO-TEST knob to
actuate the PUSH-TO-TEST condition. Verify the following:
(a) OFF flags not in view.
(b) Pointers indicate between 900 feet and
1,100 feet.
(c) Digital displays read between 900 feet
and 1,100 feet.
(d) LO caution light is off
(e) HI caution light is on.
(f) The high altitude warning “ALTITUDE
HIGH, CHECK ALTITUDE”, is audible (Full volume) at 10
seconds intervals throughout the test. Verify that the
voice warning audio is discernable by all active crew
members.
(2) Release the PUSH-TO-TEST knob. Check
that all indications return to those specified in step a. (2).
(a) Momentarily press the PUSH-TO-TEST
knob once and verify the message is at 1/2 volume.
(b) Momentarily press the PUSH-TO-TEST
a second time and verify the warning message is OFF.
(c) Pointers indicate between 900 feet and
1,100 feet.
NOTE
The LO caution light may appear to go out.
However, the light will be visible with night
vision goggles. In bright daylight, it may be
necessary to shade the indicator to verify operation
of the dimming control.
(3) Rotate the RAD ALT dimming control from
BRT to DIM. Check that the digital display dims and goes
out. Check that the LO caution light dims but does not go
out completely.
c. Inflight operation.
TM 1-1520-240-10
2-14-6
CAUTION
When operating over dense foliage, the
radar altimeters will indicate the altitude to
the tops of the trees. When operating over
sparse foliage, the altimeters may indicate
the altitude between the ground and about
half the average tree height, depending on
ground speed. When external cargo is carried,
the radar altimeter may occasionally
indicate the distance between the bottom
of the helicopter and the load.
(1) Set RAD ALT dimming control to desired
digital display light level.
(2) Set HI and LO indexes as desired. If the
helicopter exceeds one of these indexes, an aural warning
message will be heard at full volume initially, but the
volume level can be decreased by one-half (1/2) by
pressing the PUSH-TO-TEST once or inhibited by pressing
PUSH-TO-TEST a second time. If HI or LO indexes
are not desired, set the LO index at 0 feet or the HI index
above 1,500 feet.
2-14-15. VERTICAL SPEED Indicator.
Two VERTICAL SPEED indicators are in the instrument
panel (fig. 2-1-7 and 2-1-9). They indicate the rate of
climb based on the rate of change of atmospheric pressure.
The indicator is a direct-reading pressure instrument
requiring no electrical power for operation.
2-14-16. Attitude Indicator.
Two attitude indicators are on the instrument panel (fig.
2-1-7 and 2-1-9). The attitude indicators have been specifically
tailored for the flight characteristics of a helicopter
by the inclusion of an electrical trim capability in the
roll axis in addition to the standard pitch trim. Normal
flight attitudes of helicopters, defined by fixed amounts of
roll as well as pitch, are easily trimmed into this indicator,
and optimum operation of the helicopter in an attitude
such as hover is facilitated. Degrees of pitch and roll are
indicated by movement of a universally mounted sphere
painted optical black and light gray to symbolize earth
and sky, with a horizon line separating the two colores.
To adjust the miniature aircraft in relation to pitch, use the
lower knob. The pitch adjustment range is about 5
nose
up and 10
nose down minimum. To compensate attitude
in the roll axis, use the upper knob. The roll adjustment
range is about 8
minimum in either direction.
NOTE
Rapid rotation of the pitch and roll trim knobs
on the attitude indicator may cause abrupt
pitch and roll attitude changes with AFCS on.
The indicator incorporates integral lighting. The pilot and
copilot attitude indicators should erect within 90 seconds
after electrical power is applied. Power to operate the
attitude indicator gyros is supplied by the No. 1 and No.
2 AC bus through the NAV PILOT VGI and NAV COPLT
VGI circuit breakers on the No. 1 and No.2 PDP.
2-14-17. Pilot and Copilot Attitude Indicator (VGI)
Switch.
A VGI switch is on the instrument panel below each attitude
indicator (fig. 2-1-7 and 2-1-9). The switch is labeled
NORM and EMER. When the switch is at NORM, each
　
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