TM 1-1510-223-10 MAXIMUM CRUISE POWER 1700 RPM ISA + 10°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 30 25 83 640 1280 216 222 83 640 1280 218 224 2000 26 21 83 620 1240 214 226 83 620 1240 216 228 4000 22 17 83 602 1204 212 231 83 601 1202 214 232 6000 18 13 83 585 1170 210 235 83 585 1170 211 237 8000 14 9 83 572 1144 208 240 83 572 1144 209 242 10,000 11 5 83 563 1126 205 245 83 563 1126 207 247 12,000 7 1 80 534 1068 200 246 80 535 1070 202 248 14,000 3 -3 76 503 1006 193 245 76 504 1008 196 248 16,000 -1 -7 72 474 948 187 245 72 474 948 189 248 18,000 -5 -11 68 446 892 180 244 68 447 894 183 248 20,000 -9 -15 64 422 844 173 243 64 422 844 176 247 22,000 -13 -19 60 397 794 165 240 60 398 796 170 246 24,000 -17 -23 56 373 746 157 237 57 374 748 162 244 26,000 -21 -27 52 349 698 149 233 53 350 700 155 242 28,000 -26 -30 49 326 652 138 226 49 328 656 147 238 29,000 -28 -32 47 315 630 133 221 47 317 634 142 235 31,000 -33 -36 42 291 582 117 204 43 294 588 132 228 33,000 -36 -40- --- --- --- --- --- 39 270 540 119 215 35,000- --- --- --- --- --- --- --- --- --- --- --- --- BT055939 NOTE During operations with ice vanes extended, torque will decrease approximately 10 percentage points (E.  G., 64% - 10 percentage points = 54%), fuel flow will decrease approximately 35 LBS/HR/ENG, and true airspeed will be reduced approximately 20 knots. Figure 7-51.  Maximum Cruise Power at 1700 RPM - ISA +10 °C (Sheet 1 of 2)  CA Change 2  7-71