TM 1-1510-262-10
AVIONICS
SECTION I. GENERAL
3-1. INTRODUCTION.
Except for mission avionics, this chapter covers all avionics equipment installed in the RC-12X aircraft. It provides a
brief description of the equipment, the technical characteristics, and locations. It covers systems and controls, and
provides the proper techniques and procedures to be employed when operating the equipment. For more detailed
operational information consult the vendor manuals.
3-2. AVIONICS EQUIPMENT CONFIGURATION.
The aircraft avionics covered consists of three groups of electronic equipment. They are grouped by functionality:
communications, navigation, or transponder/radar.
a. The communication group consists of the intercom system, UHF transceivers (HAVE QUICK), VHF-FM trans-
ceiver (SINCGARS), VHF-AM transceivers, Advanced Communications System, Radio Control Unit (RCU), and an
emergency locator transmitter (ELT).
b. The navigation group consists of the following components; VOR/localizer/glideslope/marker beacon re-
ceivers, automatic direction inder receiver (ADF), inertial navigation system (INS), TACAN receiver, a global posi-
tioning system (GPS/WAAS), radio altimeter system, dual attitude heading reference system (AHRS), dual Flight
Management System (FMS), Electronic Standby Instrument System (ESIS), and a digital integrated light control
system.
c. The transponder and radar group consists of weather radar, lightning sensor system, transponder, and trafic
collision and avoidance system (TCAS). The transponder and radar group includes identiication, position, emer-
gency tracking system, and a radar and lightning sensor system to locate potentially dangerous weather areas.
For additional operational details to operate equipment controlled by aircraft survivability equipment/avionics control
system (ASE/ACS), refer to Chapter 4.
3-3. POWER SOURCE.
a. DC Power. DC power for the avionics equipment is provided from four sources: the aircraft battery, left and
right generators, and external power. Power is routed through two 50-ampere circuit breakers to the avionics power
relay, which is controlled by the AVIONICS MASTER POWER switch, located on the overhead control panel (Fig.
2-13). Individual system circuit breakers and the associated avionics buses are shown in igure 2-12, 2-34 through
NOTE
If the AVIONICS MASTER POWER switch fails to operate, power to the individual avionics circuit
breakers can be provided by pulling the 5-ampere circuit breaker, placarded AVIONICS MASTER
CONTR, located on the overhead circuit breaker panel (Fig. 2-12).
(1) AVIONICS MASTER POWER switch. A switch placarded AVIONICS MASTER POWER ON EXT
PWR , located on the overhead control panel (Fig. 2-13) controls power to the #1 and #2 avionics buses.
(a) OFF. In the aft (off) position, power from the 5-ampere circuit breaker placarded AVIONICS MASTER
PWR , located on the overhead circuit breaker panel (Fig. 2-12), energizes the avionics relay, removing power from
the avionics buses.
(b) ON. With the switch in the ON (center) position, the avionics power relay is de-energized and power
is applied through the 35-ampere AVIONICS MASTER PWR #1 and #2 circuit breakers to the individual avionics
circuit breakers on the overhead circuit breaker panel (Fig. 2-12).
(c) External power (EXT PWR). When the switch is in the EXT PWR (forward) position, external power
may be applied to the avionics buses. The avionics system is automatically isolated from DC GPU power. Setting
