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breaker panel.
f. CPG Remote Attitude indicator. The CPG remote
attitude indicator (RAI) displays helicopter attitude
from information obtained from the heading and
attitude reference system (HARS). The indicator can
display 360° of roll and ± 90° of pitch. HARS input
drives roll and/or pitch servos, which results in the appropriate
roll or pitch of the artificial horizon. If HARS
input ceases or becomes unreliable, 28-vdc power will
cause an OFF flag to appear at the window on the left
side of the instrument face. A pitch trim knob at the
lower right corner may be turned to adjust the pitch of
the artificial horizon relative to the fixed aircraft reference
symbol. The RAI receives 115 vac from the No. 1
essential ac bus through the ATTD IND circuit breaker
on the CPG No. 1 circuit breaker panel.
g. Clock. The clock combines the features of a
standard clock and a stopwatch by displaying normal
and elapsed time in hours, minutes, and seconds. Once
wound, the clocks will run for eight days. The elapsedtime
pushbutton control is on the upper right corner of
the case. The clock is wound and set with a knob at the
lower left corner of the case.
2.50.2 Pilot Flight instruments. The flight instruments
in the pilot instrument panel (fig 2-9) are the
video display unit, standby magnetic compass, free air
temperature gage, accelerometer, and radar altimeter.
a. Video Display Unit (VDU). The VDU is a multipurpose
instrument that provides the pilot with flight,
navigation, and targeting information. A turn-and-slip
indicator is located below the face of the cathode ray
tube. The signals for the turn rate indicator are provided
by the DASE.
b. Standby Magnetic Compass. The standby
magnetic compass is attached to the pilot glareshield.
Primary heading information is taken from the horizontal
situation indicator, which is discussed in Chapter
3, Section III.
2-76
TM 1-1520-238-10
c. Free Air Temperature (FAT indicator. The FAT
indicator (fig 2-11) is a self-contained unit mounted to
the bulkhead adjacent to, and left of, the pilot PWR
quadrant. A probe extends through the airframe to
sense outside free air temperature. The dial, marked
FREE AIR, indicates in degrees Celsius (°C).
d. Accelerometer. The accelerometer measures
the g-forces during flight.
e. Radar Altimeter. For description refer to paragraph
3.18.
2.50.3 CPG Flight Instruments. The flight instruments
unique to the CPG instrument panel (fig 2-10)
are the radio magnetic indicator, airspeed indicator,
and altimeter.
a. Radio Magnetic Indicator (RMI). The RMI, located
at the bottom center of the CPG right instrument
cluster, displays magnetic heading and ADF bearing to
a selected station. The ADF will be discussed in Chapter
3 in conjunction with direction finder set AN/
ARN-89 or the AN/ARN-149. Magnetic heading is provided
through a synchro signal from the
heading/attitude reference set (HARS) to a heading
servo that positions the heading compass card within
the instrument. When the HARS is aligning or failed, a
heading warning signal will cause the OFF flag (right
center on the instrument face) to appear. Internal power
to the RMI is provided by 115 vac 400 Hz input power.
2.51 PITOT-STATIC SYSTEM.
Electrically-heated pitot tubes are installed at the outboard
leading edge of both wings. Two associated static
ports are installed flush with the fuselage: one on the
right, and one on the left. The right wing pitot tube supplies
ram air to the pilot airspeed indicator, and the left
wing pitot tube supplies ram air to the CPG airspeed
indicator. The static port on the right side of the fuselage
provides static air pressure to the pilot barometric
altimeter, rapid response vertical speed indicator, air
speed indicator, No. 2 airspeed transducer, and the air
data processor. The static port on the left side of the fuselage
provides static air pressure to the CPG barometric
altimeter, rapid response vertical speed indicator,
airspeed indicator, and No. 1 airspeed transducer.
2.52 PILOT AND CPG MASTER CAUTION PANEL.
The master caution panels (fig 2-43), located at the center
of the pilot and right center of the CPG glareshield
(fig 2-9 and 2-10), are identical. When the PRESS TO
TEST pushbutton is pressed, all caution/warning
lights in that crew station illuminate. All segments
have two lamps so that failure of a single lamp will produce
only a dimming effect. If a segment fails to light, it
indicates either the failure of both lamps or a defective
　
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