TM 1-1510-224-10 MAXIMUM CRUISE POWER 1700 RPM ISA +30°C WEIGHT® 12,000 POUNDS 10,000 POUNDS PRESSURE ALTITUDE IOAT OAT TORQUE PER ENGINE FUEL FLOW PER ENGINE TOTAL FUEL FLOW IAS TAS TORQUE PER ENGINE FUEL FLOW PER ENGINE TOTAL FUEL FLOW IAS TAS FEET °C °C PERCENT LBS/HR LBS/HR KTS KTS PERCENT LBS/HR LBS/HR KTS KTS 0 50 45 82 636 1272 227 240 82 636 1272 228 241 2000 46 41 80 606 1212 222 242 80 606 1212 223 243 4000 43 37 78 577 1154 218 244 78 577 1154 219 246 6000 39 33 75 549 1098 213 246 75 549 1098 214 248 8000 35 29 73 521 1042 208 248 73 521 1042 210 250 10,000 31 25 70 494 988 203 250 70 494 988 205 252 12,000 27 21 67 463 926 197 251 67 463 926 199 253 14,000 23 17 63 434 868 191 251 63 435 870 193 254 16,000 19 13 59 405 810 183 249 59 405 810 186 253 18,000 15 9 54 374 748 174 245 54 375 750 177 249 20,000 11 5 50 349 698 167 243 50 350 700 170 248 22,000 7 1 47 329 658 160 242 47 330 660 164 248 24,000 3 -3 44 309 618 153 240 44 309 618 158 247 26,000 -1 -7 42 291 582 146 238 42 291 582 152 246 28,000 -5 -10 39 275 550 140 236 39 276 552 146 246 29,000 -7 -12 38 266 532 136 234 38 268 536 142 245 31,000 -12 -16 35 248 496 126 227 35 250 500 135 242 33,000 -16 -20 32 228 456 114 214 32 231 462 126 236 35,000 -20 -24 - - - - - - - - - - - - - - - 29 211 422 116 227 BT05215 NOTE During  operations  with  ice  vanes  extended,  torque  will  decrease  approximately 12%,  fuel  flow  will  decrease  approximately  8%,  and  true  airspeed  will  be  reduced by approximately 15 knots. Figure 7-46.  Maximum Cruise Power at 1700 RPM - ISA +30°C (Sheet 2 of 2) 7-71