TM 1-1510-225-10 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 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 operation. 2-2.  GENERAL. The C-12R, C -12T3, and C-12F3 are 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 C-12F3 aircraft.   2-3.  DIMENSIONS. Overall aircraft dimensions are shown in Figure 2-2. 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. (5)   Altitude. (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 GTOW. b.  Operations    Over    12,500    Pounds    Gross Takeoff Weight. (1)   Requirements. Artificial  stall  warning  systems  may  only provide a 1 to 5 knot stall warning. CAUTION Maximum   GTOW   charts   must   be   strictly followed in the event of an engine failure. (a)  Aircraft shall be equipped with 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 WARNING