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 83 623 1246 209 222 83 623 1246 210 223 2000 46 41 83 603 1206 207 226 83 603 1206 208 227 4000 42 37 81 576 1152 203 229 82 576 1152 204 230 6000 38 33 79 547 1094 198 230 79 547 1094 200 232 8000 34 29 76 519 1038 193 232 76 519 1038 195 234 10,000 30 25 72 491 982 188 233 72 491 982 190 235 12,000 26 21 68 460 920 182 233 68 461 922 184 235 14,000 22 17 64 431 862 176 232 65 432 864 178 235 16,000 18 13 60 402 804 168 230 60 402 804 171 234 18,000 14 9 54 372 744 160 226 54 372 744 163 230 20,000 10 5 50 346 692 152 224 50 347 694 156 228 22,000 6 1 47 327 654 146 222 47 327 654 150 228 24,000 2 -3 44 307 614 139 220 45 308 616 144 227 26,000 -2 -7 42 289 578 133 218 42 290 580 138 226 28,000 -6 -10 39 273 546 126 215 39 274 548 132 225 29,000 -8 -12 38 264 528 122 213 38 265 530 129 224 31,000 -12 -16 35 246 492 113 205 35 248 496 122 220 33,000 -16 -20 --- --- --- --- --- 32 228 456 113 214 35,000 -20 -24 --- --- --- --- --- 29 209 418 103 204 BT03290 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 7-54.  Maximum Cruise Power at 1700 RPM - ISA +30 °C (Sheet 2 of 2)  IR 7-78  Change 2