TM 1-1510-224-10 MAXIMUM RANGE POWER 1500 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 39 35 76 574 1148 211 220 74 567 1134 211 220 2000 36 31 72 536 1072 204 220 70 530 1060 205 220 4000 32 27 68 501 1002 198 219 67 496 992 199 220 6000 28 23 65 468 936 192 220 64 464 928 193 220 8000 24 19 62 438 876 186 220 60 433 866 187 221 10,000 20 15 58 408 816 180 219 57 404 808 181 221 12,000 16 11 56 384 768 175 220 55 378 756 176 221 14,000 12 7 52 357 714 167 217 51 355 710 170 221 16,000 8 3 49 336 672 161 217 48 331 662 163 219 18,000 4 -1 46 313 626 154 215 45 308 616 157 218 20,000 0 -5 44 295 590 148 214 42 287 574 151 217 22,000 -4 -9 42 279 558 142 213 40 270 540 145 216 24,000 -8 -13 41 269 538 139 215 38 254 508 139 215 26,000 -12 -17 41 262 524 136 218 35 237 474 132 212 28,000 -16 -20 41 258 516 133 221 33 223 446 126 210 29,000 -18 -22 41 257 514 132 224 33 218 436 123 210 31,000 -22 -26 - - - - - - - - - - - - - - - 33 214 428 120 213 33,000 -26 -30 - - - - - - - - - - - - - - - 33 215 430 120 220 35,000 -29 -34 - - - - - - - - - - - - - - - 34 217 434 120 228 BT058716 NOTE During  operations  with  ice  vanes  extended,  torque  will  decrease  approximately 10%,  fuel  flow  will  decrease  approximately  5%,  and  true  airspeed  will  be  reduced by approximately 10 knots. Figure 7A-69.  Maximum Range Power at 1500 RPM - ISA +20°C (Sheet 2 of 2) 7A-109