TM 1-1510-223-10 LOITER POWER 1700 RPM ISA -10°C WEIGHT® 12,000 POUNDS 10,000 POUNDS TORQUE FUEL TOTAL TORQUE FUEL TOTAL PRESSURE PER FLOW FUEL PER FLOW FUEL ALTITUDE IFAT FAT ENGINE PER FLOW IAS TAS ENGINE PER FLOW IAS TAS ENGINE ENGINE FEET °C °C PERCENT LBS/HR LBS/HR KTS KTS PERCENT   LBS/HR    LBS/HR KTS KTS 0 6 5 25 393 786 124 126 23 383 766 124 126 2000 3 1 26 376 752 124 129 24 366 732 124 129 4000 -1 -3 26 359 718 124 133 24 349 698 124 133 6000 -5 -7 27 343 686 124 137 24 333 666 124 137 8000 -9 -11 27 328 656 124 141 25 317 634 124 141 10,000 -13 -15 27 314 628 124 146 25 303 606 124 146 12,000 -17 -19 28 300 600 124 150 26 289 578 124 150 14,000 -21 -23 29 288 576 124 155 26 277 554 124 155 16,000 -24 -27 29 277 554 124 160 27 266 532 124 160 18,000 -28 -31 30 267 534 124 165 28 255 510 124 165 20,000 -32 -35 31 259 518 124 171 28 248 496 124 171 22,000 -36 -39 31 253 506 124 176 29 241 482 124 176 24,000 -39 -43 32 249 498 124 182 29 236 472 124 182 26,000 -43 -47 32 244 488 124 189 30 232 464 124 189 28,000 -47 -50 33 241 482 124 195 30 228 456 124 195 29,000 -49 -52 33 240 480 124 199 31 226 452 124 199 31,000 -52 -56 34 242 484 124 206 31 224 448 124 206 33,000 -56 -60 35 247 494 124 213 32 227 454 124 213 35,000 -60 -64 37 251 502 124 221 33 231 462 124 221 BT055948 NOTE During  operations  with  ice  vanes  extended,  torque  will  decrease  approximately  7 percentage points (E.G., 67% - 7 percentage points = 60%), fuel flow will decrease approximately 20 LBS/HR/ENG, and true airspeed will be reduced approximately 20 knots. Figure 7-110.  Loiter Power at 1700 RPM - ISA -10°C (Sheet 2 of 2)   CA Change 2  7-175