TM 1-1510-224-10 MAXIMUM CRUISE POWER 1700 RPM ISA +20°C WEIGHT® 12,000 POUNDS 10,000 POUNDS PRESSURE ALTITUDE IFAT FAT 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 40 35 83 638 1276 229 238 83 637 1274 230 239 2000 36 31 83 617 1234 226 243 83 616 1232 227 244 4000 33 27 83 598 1196 224 247 83 597 1194 225 249 6000 29 23 83 582 1164 222 253 83 581 1162 223 254 8000 25 19 82 560 1120 218 256 82 561 1122 220 258 10,000 21 15 78 531 1062 213 258 78 532 1064 215 260 12,000 17 11 75 501 1002 207 259 75 501 1002 209 261 14,000 13 7 70 469 938 200 258 70 470 940 202 260 16,000 9 3 66 440 880 193 257 66 441 882 195 260 18,000 5 -1 62 414 828 186 257 62 415 830 189 260 20,000 1 -5 58 389 778 179 256 58 389 778 182 260 22,000 -3 -9 55 366 732 172 255 55 366 732 176 259 24,000 -7 -13 51 343 686 165 253 51 343 686 169 259 26,000 --11 -17 48 322 644 158 251 48 323 646 162 258 28,000 -15 -20 45 303 606 151 249 45 304 608 156 256 29,000 -17 -22 43 294 588 147 247 43 294 588 152 256 31,000 -21 -26 40 273 546 138 242 40 275 550 145 253 33,000 -25 -30 36 252 504 127 233 37 254 508 136 241 35,000 -30 -34 32 230 460 114 218 33 233 466 127 241 BT058686 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 7A-45.  Maximum Cruise Power at 1700 RPM - ISA +20°C (Sheet 2 of 2) 7A-69