TM 1-1510-223-10 ONE-ENGINE-INOPERATIVE MAXIMUM CRUISE POWER 1700 RPM ISA  -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 83 627 627 158 158 83 627 627 160 160 2000 3 1 83 609 609 156 161 83 608 608 159 164 4000 0 -3 83 592 592 154 164 83 591 591 158 167 6000 -4 -7 83 577 577 153 167 83 577 577 156 170 8000 -8 -11 83 565 565 151 170 83 564 564 154 173 10,000 -12 -15 83 553 553 149 173 83 552 552 152 177 12,000 -16 -19 83 543 543 147 176 83 543 543 150 180 14,000 -20 -23 83 536 536 145 179 83 536 536 148 183 16,000 -24 -27 83 529 529 142 181 82 531 531 146 186 18,000 -28 -31 79 503 503 136 180 79 504 504 141 186 20,000 -32 -35 75 477 477 130 178 75 479 479 136 186 22,000 -36 -39 70 447 447 122 174 70 449 449 129 183 24,000 -40 -43 64 416 416 112 166 65 419 419 122 180 26,000 -44 -47 58 384 384 97 151 60 389 389 115 176 28,000 -48 -50 --- --- --- --- --- 55 360 360 106 169 29,000 --- --- --- --- --- --- --- --- --- --- --- --- 31,000 --- --- --- --- --- --- --- --- --- --- --- --- 33,000 --- --- --- --- --- --- --- --- --- --- --- --- 35,000 --- --- --- --- --- --- --- --- --- --- --- --- BT03642 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 7-130.  One Engine Inoperative Max Cruise Power at 1700 RPM - ISA -10 °C (Sheet 2 of 2)   IR 7-210  Change 2