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to channel 3 which is split into sections A and B. A:
to the avionics lights; B: to the ASN 128 panel lights.
The L CSL controls the circuit breaker and collective
stick grip lights.
C. Emergency Floodlight System. The emergency
floodlight system is installed under the glareshields
of the pilot and CPG instrument panels. Power for the
emergency floodlight system is emergency bus 28 vdc
power through the UTIL SEC circuit breaker on the pilot
overhead circuit breaker panel and the UTIL SEC
LT circuit breaker on the CPG main circuit breaker
panel (fig 2-40). Operation of the emergency floodlight
system is controlled by the FLOOD three-position
toggle switch on the pilot and CPG INTR LT control
panel. When the switch is positioned to the BRT position,
it turns on the blue green secondary lights to the
brightest level. When in the dim position, the secondary
lighting is dimmed.
d. Utility Light. A detachable utility light with a
coiled extension cord is located to the left of the pilot
and CPG seats. The utility light provides emergency
red or white lighting in case instrument panel lighting
fails. The light is operated by an OFF BRT rheostat
switch integral with the light. Rotating the front section
of the light selects white flood or red flood. The utility
light receives 28 vdc from the emergency dc bus
through the UTIL SEC LT circuit breaker on the pilot
overhead circuit breaker panel and the UTIL SEC LT
circuit breaker on the CPG No. 1 circuit breaker panel.
e. Dimming, MASTER CAUTION Panel, and Caution/
Warning Panel Advisory Segment Lights. Dimming
of all caution/warning lights is controlled by the
INST control on both the pilot and CPG INTR LT control
panels for the respective crew station. When the
INST control is is in the OFF position, caution/warning
lights are bright; any other position will cause the
respective lights to go to a preset dim condition.
2-75
TM 1-1520-236-10
Section XIV. FLIGHT INSTRUMENTS
2.50 FLIGHT INSTRUMENTS.
The instruments discussed in this section are, for the
most part, those that directly measure flight performance.
Caution, warning, audio systems, and some
flight instruments are common to both crew stations.
The instruments are grouped as common, pilot, and
CPG flight instruments.
2.50.1 Common Flight instruments. The flight
instruments found in both the pilot instrument panel
(fig 2-9) and the CPG instrument panel (fig 2-10) are
the pressure (barometric) altimeter, instantaneous vertical
speed indicator, airspeed indicator, attitude indicator,
and the clock.
a. Pilot Barometric Altimeter. The pilot has an
AAU-32/A encoding barometric altimeter. This altimeter
is the same as the CPG’s except the AAU-32/A interfaces
with the IFF for Mode C operation.
b. CPG Barometric Altimeter. The CPG has an
AAU-31/A barometric altimeter. The altimeter is graduated
in 50-foot increments and marked at 100-foot
intervals (0 - 9 x 100). Just left of center is a 100-foot
drum and a 1000-foot drum to supplement the scale
pointer. The scale window, at the lower right section of
the instrument face, indicates barometric pressure setting
in inches of mercury. It is adjustable by use of the
barometric pressure set knob on the lower left corner of
the indicator case. Maximum allowable altimeter error
is 70 feet.
c. Verticai Speed indicator (VSI). The VSI measures
the rates of change in static air pressure resulting
from climbs and descents. An adjustment screw on
the lower left corner is used to zero the pointer, if necessary,
prior to flight.
d. Airspeed indicator. The airspeed indicator
measures the difference between pitot pressure and
static pressure. Instrument range markings and limitations
are contained in Chapter 5, Section II, System
Limits. At low airspeeds and high power settings,
indicated airspeeds may be unreliable and fluctuate
greater than 10 KIAS.
e. Pilot Standby Attitude indicator. The pilot
standby attitude indicator provides an independent
display of helicopter attitude. The indicator can display
360° of roll and ± 85° of pitch. A PULL TO CAGE knob
at the lower right corner has two functions. Pulling it
out with power applied to the instrument will cage the
motor-driven internal gyroscope and level the background
horizon line to 0° in pitch and roll. The knob
may be turned to adjust the pitch of the artificial horizon
relative to the fixed aircraft symbol. The indicator
receives 28 vdc from the emergency dc bus through the
STBY ATTD circuit breaker on the pilot overhead circuit
　
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