AIRCRAFT AND SYSTEMS DESCRIPTIONS AND OPERATION
Section I. AIRCRAFT
The purpose of this chapter is to describe the
aircraft and its systems and controls that 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
pressurized, low wing, all metal aircraft and are
powered by two PT6A-42 turboprop engines. The
aircraft has all-weather capability. Distinguishable
features of the aircraft are the slender, streamlined
engine nacelles, four-blade propellers, T-tail, and dual
aft body strakes. The basic mission of the aircraft is to
provide scheduled or unscheduled air transportation of
passengers and / or cargo in any area of the world.
Cabin entrance is made through a stair-type door aft of
the wing on the left side of the fuselage. Refer to
Figure 2-1, Sheets 1 through 6, for illustrations of the
general exterior arrangement for C-12R, C-12T3, and
2-4. GROUND TURNING RADIUS.
Minimum ground turning radius of the aircraft is
shown in Figure 2-3.
2-5. MAXIMUM WEIGHTS.
a. Operations At Or Below 12,500 Pounds.
(1) Takeoff. Maximum Gross Takeoff Weight
(GTOW) is 12,500 pounds.
(2) Landing. Maximum gross landing weight
is 12,500 pounds.
(3) Maximum Ramp Weight. Maximum ramp
weight is 12,590 pounds.
(4) Maximum Zero Fuel Weight. Maximum
zero fuel weight is 11,000 pounds.
(a) At least 75% of total missions shall be
flown at altitudes above 5,000 feet above ground level
when operating at or below 12,500 pounds GTOW.
(b) At least 50% of total missions shall be
flown at altitudes above 10,000 feet above ground
level when operating at or below 12,500 pounds
b. Operations Over 12,500 Pounds Gross
Artificial stall warning systems may only
provide a 1 to 5 knot stall warning.
Maximum GTOW charts must be strictly
followed in the event of an engine failure.
Raisbeck Engineering dual aft body strakes and
engine ram air recovery system with PT6A-42 engines.
(b) Landing. Maximum landing weight is
12,500 pounds, unless required by an emergency. If it
is necessary to land with a weight over 12,500 pounds,
the landing shall be made on a smooth, paved runway
at a sink rate of 500 feet per minute or less, if possible.
(c) Altitude and Flight Duration. All
missions with over 12,500 pounds GTOW shall be
planned and flown at or above 10,000 feet above
ground level and be a minimum of 60 minutes in