TM 1-1510-223-10 ONE-ENGINE-INOPERATIVE MAXIMUM CRUISE POWER 1700 RPM ISA -20°C WEIGHT® 16,000 POUNDS 14,000 POUNDS TORQUE FUEL TOTAL TORQUE FUEL TOTAL PRESSURE PER FLOW FUEL PER FLOW FUEL ALTITUDE IFAT FAT ENGINE PER FLOW IAS TAS ENGINE PER FLOW IAS TAS ENGINE ENGINE FEET °C °C PERCENT LBS/HR LBS/HR KTS KTS PERCENT   LBS/HR    LBS/HR KTS KTS 0 -3 -5 83 626 626 150 148 83 625 625 155 152 2000 -7 -9 83 605 605 148 150 83 604 604 153 155 4000 -11 -13 83 588 588 147 153 83 587 587 152 158 6000 -15 -17 83 575 575 144 155 83 574 574 150 161 8000 -19 -21 83 564 564 141 157 83 563 563 148 163 10,000 -22 -25 83 554 554 139 159 83 553 553 145 166 12,000 -26 -29 83 545 545 136 160 83 544 544 143 168 14,000 -30 -33 83 538 538 132 161 83 537 537 141 171 16,000 -34 -37 83 532 532 129 163 83 531 531 139 174 18,000 -38 -41 83 529 529 125 163 83 527 527 136 176 20,000 -42 -47 --- --- --- --- --- 79 502 502 128 172 22,000 -46 -49- --- --- --- --- --- 74 470 470 117 164 24,000 --- --- --- --- --- --- --- --- --- --- --- --- 26,000 --- --- --- --- --- --- --- --- --- --- --- --- 28,000 --- --- --- --- --- --- --- --- --- --- --- --- 28,000 --- --- --- --- --- --- --- --- --- --- --- --- 29,000 --- --- --- --- --- --- --- --- --- --- --- --- 31,000 --- --- --- --- --- --- --- --- --- --- --- --- 33,000 --- --- --- --- --- --- --- --- --- --- --- --- 35,000 --- --- --- --- --- --- --- --- --- --- --- --- BT03639 NOTE During  operations  with  ice  vanes  extended,  torque  will  decrease  approximately  7 percentage  points  (E.  G.,  67%  7  percentage  points  =  60%),  fuel  flow  will  decrease approximately 25 LBS/HR/ENG, and true airspeed will be reduced approximately 15 knots. Figure 7-128.  One Engine Inoperative Max Cruise Power at 1700 RPM - ISA -20 °C (Sheet 1 of 2)  IR Change 2  7-205