TM 1-1510-223-10 MAXIMUM CRUISE POWER 1700 RPM ISA + 30°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 50 45 81 634 1268 214 227 81 635 1270 215 228 2000 46 41 79 605 1210 210 229 79 605 1210 211 231 4000 42 37 77 576 1152 205 231 77 576 1152 207 233 6000 38 33 74 547 1094 201 233 74 548 1096 203 235 8000 34 29 72 519 1038 196 235 72 519 1038 198 237 10,000 30 25 69 491 982 191 237 69 492 984 193 239 12,000 26 21 66 461 922 186 237 66 461 922 188 239 14,000 22 17 62 432 864 180 237 62 433 866 182 240 16,000 18 13 58 403 806 173 236 58 403 806 175 239 18,000 14 9 53 373 746 164 232 53 373 746 167 236 20,000 10 5 49 347 694 157 230 49 348 696 160 235 22,000 6 1 46 327 654 150 229 47 328 656 155 234 24,000 2 -3 44 308 616 144 227 44 308 616 148 234 26,000 -2 -7 41 290 580 137 225 41 290 580 143 233 28,000 -6 -10 39 273 546 130 222 39 274 548 137 232 29,000 -8 -12 37 265 530 126 220 38 266 532 133 231 31,000 -12 -16 34 247 494 117 213 35 249 498 126 228 33,000 -17 -20 31 227 454 104 199 32 229 458 118 222 35,000 --- --- --- --- --- --- --- --- --- --- --- --- BT0559314 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 7-55.  Maximum Cruise Power at 1700 RPM - ISA +30 °C (Sheet 2 of 2)  CA 7-80  Change 2