TM 1-1510-262-10
AIRCRAFT AND SYSTEMS DESCRIPTION AND OPERATION
SECTION I.
AIRCRAFT
2-1. INTRODUCTION.
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 contains descriptive information and does not describe procedures for operation of the
aircraft. These procedures are contained within appropriate chapters in the 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 suficiently complete to allow for its safe and eficient operation.
2-2. GENERAL.
The RC-12X is a pressurized, low wing, all metal aircraft, powered by two PT6A-67 turboprop engines (Fig. 2-17
and Fig. 2-18), having all weather capability. Distinguishable features of the aircraft are the slender, streamlined
engine nacelles, four-bladed propellers, an aft rotating boom antenna, mission antennas, wing tip pods, stabilons,
a T-tail, and a ventral in below the empennage. The basic mission of the aircraft is radio reconnaissance. Cabin
entrance is accomplished through a stair-type door (Fig. 2-15) aft of the wing on the left side of the fuselage. The
interior coniguration is shown in igure 2-6.
2-3. EMERGENCY SYSTEMS
Emergency Equipment information is located in Chapter 9.
2-4. DIMENSIONS.
Overall aircraft dimensions are shown in igure 2-7.
2-5. GROUND TURNING RADIUS.
Minimum ground turning radius of the aircraft is shown in igure 2-8.
2-6. MAXIMUM WEIGHTS.
This information is presented for basic aircraft description purposes; Chapter 5 contains the controlling aircraft limi-
tations.
a. Takeoff. Maximum gross takeoff weight is 16,500 pounds.
b. Landing. Maximum gross landing weight is 15,675 pounds.
c. Maximum Ramp Weight. Maximum ramp weight is 16,620 pounds.
d. Maximum Zero Fuel Weight. Maximum zero fuel weight is 13,100 pounds.
2-7. EXHAUST AND PROPELLER DANGER AREAS.
Danger areas to be avoided by personnel while aircraft engines are being operated on the ground are depicted in
igure 2-9. Distances 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
