AIRCRAFT AND SYSTEMS DESCRIPTION AND OPERATION
Section I. AIRCRAFT
The purpose of this chapter is to describe the
aircraft and its systems and controls which contribute to
the physical act of operating the aircraft. It does not
contain descriptions of avionics or mission equipment
covered elsewhere in this manual. This chapter also
contains the emergency equipment installed. This
chapter is not designed to provide instructions on the
complete mechanical and electrical workings of the
various systems; therefore, each is described only in
enough detail to make comprehension of that system
sufficiently complete to allow for safe and efficient
The RC-12P and RC-12Q are pressurized, low
wing, all metal aircraft and are powered by two PT6A-67
turboprop engines (fig. 2-1 and 2-2). The aircraft have
all-weather capability. Distinguishable features of the
aircraft are the slender, streamlined engine nacelles,
four-bladed propellers, aft rotating boom antenna,
mission antennas, wing tip pods, stabilons, T-tail, and a
ventral fin below the empennage. The RC-12Q aircraft
is distinguished by the large SATCOM radome located
on top of the fuselage.
RC-12P Basic Mission. The basic mission
of the aircraft is radio reconnaissance.
RC-120 Basic Mission. The basic mission
of the aircraft is Direct Air to Satellite Relay (DASR)
Cabin entrance is made through a stair-type door
aft of the wing on the left side of the fuselage (fig. 2-1
and 2-2). The interior configuration of the aircraft is
shown in figure 2-3 and 2-4.
Overall aircraft dimensions are shown in
GROUND TURNING RADIUS.
Minimum ground turning radius of the aircraft is
shown in figure 2-6.
Takeoff. Maximum gross takeoff weight is
Landing. Maximum gross landing weight
is 15,675 pounds.
Maximum Ramp Weight. Maximum ramp
weight is 16,620 pounds.
Maximum Zero Fuel Weight. Maximum
zero fuel weight is 13,100 pounds.
EXHAUST AND PROPELLER DANGER AREAS.
Exhaust and propeller danger areas to be avoided
by personnel while aircraft engines are being operated
on the ground are depicted in figure 2-7. Distance to be
maintained with engines operating at idle are also
shown. Temperature and velocity of exhaust gases at
varying locations aft of the exhaust stacks are shown for
maximum power. The danger area extends to 40 feet aft
of the exhaust stack outlets. Distance to be maintained
with engines operating at idle and propeller danger
areas are also shown.
LANDING GEAR SYSTEM.
The retractable tricycle landing gear is electrically
controlled and hydraulically actuated. The landing gear
are extended and retracted by a hydraulic power pack,
located in the left wing center section, forward of the
main spar. The power pack consists primarily of a
hydraulic pump, a 28 VDC motor, a gear selector valve
and solenoid, a two section fluid reservoir, filter screens,
a gear-up pressure-switch and a low fluid level sensor.
Engine bleed air, regulated to 18 to 20 PSI, is plumbed
into the power pack reservoir and the system fill
reservoir to prevent cavitation of the pump. The fluid
level sensor activates an amber caution annunciator,
caution/advisory annunciator panel, whenever the fluid
level in the power pack. is low. The annunciator is
tested by pressing the HYD FLUID SENSOR TEST
switch located on the pilot's subpanel (fig. 2-8).
Power for the hydraulic power pack is supplied through
the landing gear motor relay and a 60-ampere circuit
breaker located under the floorboard forward of the main
spar. The motor relay is energized by power furnished
through the 2-ampere LANDING GEAR CONTROL
circuit breaker located on the overhead circuit breaker
panel (fig. 2-9). The power pack motor is protected by a
time delay module which senses operation voltage
through a 5-ampere circuit breaker. Both are located
beneath the aisleway floorboards, forward of the main