TM 1-1510-224-10 MAXIMUM CRUISE POWER 1700 RPM ISA +10°C WEIGHT® 16,000 POUNDS 14,000 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 30 25 83 635 1270 227 233 83 635 1270 229 235 2000 26 21 83 615 1230 225 237 83 615 1230 227 239 4000 22 17 83 597 1194 223 242 83 597 1194 224 243 6000 19 13 83 581 1162 220 246 83 581 1162 222 248 8000 15 9 83 568 1136 218 251 83 567 1134 220 253 10,000 11 5 83 559 1118 216 257 83 559 1118 218 259 12,000 7 1 81 536 1072 212 259 81 537 1074 214 262 14,000 3 -3 77 506 1012 205 259 77 506 1012 207 262 16,000 -1 -7 73 476 952 198 258 73 477 954 201 262 18,000 -5 -11 69 448 896 190 257 69 449 898 194 262 20,000 -9 -15 65 424 848 183 256 65 424 848 187 261 22,000 -13 -19 61 399 798 175 254 61 400 800 180 260 24,000 -17 -23 57 374 748 167 251 57 375 750 172 258 26,000 -21 -27 53 351 702 158 246 53 352 704 164 255 28,000 -25 -30 49 328 656 148 239 50 329 658 156 251 29,000 -27 -32 47 316 632 142 234 48 318 636 151 249 31,000 -31 -36 35 248 496 125 225 44 296 592 141 241 33,000 -36 -40 --- --- --- --- --- 40 272 544 128 229 35,000 --- --- --- --- --- --- --- --- --- --- --- --- BT058687 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-44.  Maximum Cruise Power at 1700 RPM - ISA +10°C (Sheet 1 of 2) 7A-66