TM 1-1510-223-10 ONE-ENGINE INOPERATIVE MAXIMUM CRUISE POWER 1700 RPM SA -10°C WEIGHT® 12,000 POUNDS 10,000 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 7 5 83 651 651 164 164 83 650 650 167 166 2000 4 1 83 632 632 163 167 83 631 631 166 170 4000 0 -3 83 614 614 161 170 83 614 614 164 173 6000 -4 -7 83 598 598 159 173 83 598 598 162 177 8000 -8 -11 83 584 584 157 176 83 583 583 160 180 10,000 -12 -15 83 571 571 155 179 83 571 571 158 183 12,000 -16 -19 83 560 560 152 182 83 559 559 156 186 14,000 -20 -23 83 552 552 150 186 83 551 551 154 190 16,000 -23 -27 81 531 531 146 186 81 532 532 150 192 18,000 -27 -31 77 504 504 140 185 77 505 505 145 192 20,000 -31 -35 73 478 478 134 184 74 480 480 140 191 22,000 -36 -39 68 448 448 127 180 69 450 450 134 189 24,000 -40 -43 63 418 418 118 174 64 420 420 127 186 26,000 -44 -47 58 386 386 105 162 59 391 391 119 182 28,000 -48 -50 --- --- --- --- --- 54 361 361 111 176 29,000 -50 -52 --- --- --- --- --- 52 347 347 106 172 31,000 --- --- --- --- --- --- --- --- --- --- --- --- 33,000 --- --- --- --- --- --- --- --- --- --- --- --- 35,000 --- --- --- --- --- --- --- --- --- --- --- --- BT055906 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 7-131.  One Engine Inoperative Max Cruise Power at 1700 RPM - ISA -10 °C (Sheet 2 of 2)  CA 7-212  Change 2