TM 1-1510-223-10 MAXIMUM CRUISE POWER 1700 RPM ISA 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 19 15 83 613 1226 211 213 83 613 1226 212 214 2000 15 11 83 599 1198 209 217 83 598 1196 210 218 4000 12 7 83 584 1168 206 221 83 583 1166 208 223 6000 8 3 83 569 1138 204 225 83 568 1136 206 227 8000 4 -1 83 556 1112 202 229 83 555 1110 204 231 10,000 0 -5 83 544 1088 200 234 83 544 1088 202 236 12,000 -4 -9 83 534 1068 198 239 83 534 1068 200 241 14,000 -7 -13 83 527 1054 196 244 83 527 1054 198 246 16,000 -11 -17 81 509 1018 191 245 81 509 1018 193 248 18,000 -15 -21 76 481 962 184 245 77 481 962 187 248 20,000 -19 -25 72 455 910 177 244 72 456 912 181 248 22,000 -23 -29 68 430 860 170 242 68 430 860 174 247 24,000 -27 -33 64 404 808 163 240 64 405 810 167 246 26,000 -31 -37 59 378 756 154 236 59 379 758 159 243 28,000 -36 -40 54 351 702 144 230 55 352 704 151 239 29,000 -40 -44 49 324 648 133 220 52 339 678 146 236 31,000 -42 -46 47 311 622 126 213 48 313 626 136 229 33,000 -46 -50 --- --- --- --- --- 43 288 576 125 219 35,000 --- --- --- --- --- --- --- --- --- --- --- --- BT03283 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 7-48.  Maximum Cruise Power at 1700 RPM - ISA (Sheet 1 of 2)   IR Change 2  7-65