TM 1-1510-225-10 5-14 Table 5-3.  Generator Load Limits MINIMUM GAS GENERATOR RPM – N₁ GENERATOR LOAD WITHOUT AIR CONDITIONING WITH AIR CONDITIONING * T3  F3 0% to 75% 58% 62%            75% to 80% 60% 62% R  0% to 80% 61% 62%     80% to 85% 65% 65% * Right engine only Section IV.  LOADING LIMITS 5-17.  CENTER OF GRAVITY LIMITATIONS. Center   of   gravity   limits   and   instructions   for computation  of  the  center  of  gravity  are  contained  in Chapter  6.    The  center  of  gravity  range  will  remain within     limits,     providing     the     aircraft     loading     is accomplished according to instructions in Chapter 6. 5-18.  WEIGHT LIMITATIONS. The  ability  to  experience  loss  of  engine power and successfully stop, continue the takeoff,   or   climb,   before   or   after   gear retraction, is not assured for all conditions. Thorough     mission     planning     must     be accomplished  prior  to  takeoff,  by  analysis of  maximum  takeoff  weight  permitted  by takeoff  distance,  accelerate-stop,  positive one   engine   inoperative   climb   at   lift   off, accelerate-go,  takeoff  climb  gradient,  and climb performance.  This data will describe performance capabilities for critical mission decisions. a.  Operations   At   Or   Below   12,500   Pounds Gross Takeoff Weight (GTOW). (1)  Takeoff.      Maximum   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 GTOW. (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.        All    missions    with    over 12,500 pounds GTOW shall be  planned  and flown  at or above 10,000 feet above ground level. WARNING WARNING