TM 1-1510-224-10 MAXIMUM CRUISE POWER 1700 RPM ISA +20°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 40 35 83 639 1278 229 239 83 639 1278 231 240 2000 37 31 83 618 1236 227 243 83 618 1236 228 245 4000 33 27 83 599 1198 225 248 83 599 1198 226 250 6000 29 23 83 583 1166 223 253 83 583 1166 224 255 8000 25 19 82 561 1122 219 257 82 561 1122 220 258 10,000 21 15 78 531 1062 214 258 78 532 1064 215 260 12,000 17 11 75 501 1002 208 259 75 501 1002 210 262 14,000 13 7 70 469 938 200 258 70 470 940 202 261 16,000 9 3 66 440 880 193 258 66 441 882 196 261 18,000 5 -1 62 414 828 187 258 62 415 830 189 261 20,000 1 -5 58 389 778 180 257 58 389 778 183 261 22,000 -3 -9 55 366 732 173 256 55 366 732 176 260 24,000 -7 -13 51 343 686 166 254 51 344 688 169 259 26,000 -11 -17 48 322 644 159 252 48 323 646 163 258 28,000 -15 -20 45 303 606 151 250 45 304 608 156 257 29,000 -17 -22 43 294 588 148 248 43 294' 588 153 257 31,000 -21 -26 40 274 548 139 243 40 275 550 145 254 33,000 -25 -30 36 252 504 129 235 37 254 508 137 249 35,000 -30 -34 33 231 462 115 221 33 233 466 128 242 BT05217 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 7-45.  Maximum Cruise Power at 1700 RPM - ISA +20°C (Sheet 2 of 2) 7-69