TM 1-1510-218-10
2-1
CHAPTER 2
AIRCRAFT AND SYSTEMS DESCRIPTIONS 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
and
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 system is described only in
enough detail to make comprehension of that system
sufficiently complete to allow for its safe and efficient
operation.
NOTE T2
C-12T2 aircraft incorporate Aviator Night
Vision Imaging (ANVIS) compatible interior
lighting in the following areas: all cockpit,
except emergency lighting; all cabin lights,
except reading, spar cover, no smoking,
fasten seat belt, and emergency lighting.
2-2. GENERAL.
The C-12 is a pressurized, low wing, all metal
aircraft, powered by two PT6A turboprop engines and
has all-weather capability. Refer to Figure 2-1, Sheets
1 through 3, and Figure 2-2. Distinguishable features
of the aircraft are the slender, streamlined engine
nacelles, square-tipped wing and tail surfaces, a T-tail
and dual aft body strakes below the empennage. The
basic mission of the aircraft is to provide a transport
service supporting staff in the conduct of command
and control functions, administration, liaison, and
inspection. Cabin entrance is made through a stair-
type door on the left side of the fuselage. The pilot
and copilot seats are separated from the cabin by a
removable partition. Table 2-1 lists main differences
between models.
2-3. DIMENSIONS.
Overall aircraft dimensions are shown in Figure
2-3, Sheets 1 and 2.
2-4. GROUND TURNING RADIUS.
Minimum ground turning radius of the aircraft is
shown in Figure 2-4.
Table 2-1. Main Differences Between Models
ITEM
C-12C
C-12D
C-12T1/T2
Wing span
54 ft. 6 in.
55 ft. 6.5 in.
55 ft. 6.5 in.
Ground turning radius
39 ft. 10 in.
40 ft. 4 in.
40 ft. 4 in.
Cargo door
Not installed
Height – 52 in.
Width – 52 in.
Height – 52 in.
Width – 52 in.
Engines
PT6A -41
PT6A -41 D1
PT6A -42 D2
PT6A -42
Oxygen system
Passenger masks stowed
for use
Auto-deployment system
Auto-deployment system
Landing/taxi lights
Located on nose gear
Located on nose gear
Located on nose gear
High flotation landing gear Not installed
Installed
Installed
Hydraulic landing gear
Not installed
Installed D2
Installed
ANVIS lighting
Not installed
Not installed
Installed T2
