TM 1-1510-224-10 MAXIMUM CRUISE POWER 1700 RPM ISA +37°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 57 52 74 607 1214 217 232 74 607 1214 218 234 2000 53 48 72 577 1154 213 235 72 577 1154 215 237 4000 49 44 70 549 1098 209 238 70 549 1098 211 239 6000 45 40 68 522 1044 205 240 69 522 1044 206 242 8000 42 36 66 496 992 200 242 67 496 992 202 244 10,000 38 32 64 469 938 195 243 64 469 938 197 246 12,000 34 28 60 437 874 189 243 61 438 876 191 246 14,000 30 24 57 408 816 182 243 57 409 818 185 246 16,000 26 20 53 380 760 175 241 54 380 760 178 245 18,000 22 16 49 351 702 167 229 49 352 704 170 243 20,000 18 12 45 326 652 159 235 46 326 652 163 241 22,000 13 8 42 305 610 151 232 43 306 612 156 239 24,000 9 4 39 284 568 143 228 39 285 570 149 236 26,000 5 0 37 267 534 136 225 37 268 536 142 235 28,000 1 -3 35 254 508 129 222 35 255 510 137 235 29,000 -1 -5 34 247 494 125 221 34 249 498 134 235 31,000 -5 -9 32 231 462 116 212 32 233 466 127 232 33,000 -9 -13 - - - - - - - - - - - - - - - 29 215 430 118 224 35,000 -13 -17 - - - - - - - - - - - - - - - 26 196 392 106 212 BT05213 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 7-47.  Maximum Cruise Power at 1700 RPM - ISA +37°C (Sheet 2 of 2) 7-73