TM 1-1510-223-10 LOITER POWER 1700 RPM ISA -10°C WEIGHT® 16,000 POUNDS 14,000 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 30 418 836 124 126 28 405 810 124 126 2000 3 1 31 402 804 124 129 28 388 776 124 129 4000 -1 -3 31 386 772 124 133 29 372 744 124 133 6000 -5 -7 32 370 740 124 137 29 356 712 124 137 8000 -9 -11 32 355 710 124 141 30 341 682 124 141 10,000 -13 -15 33 341 682 124 146 30 326 652 124 146 12,000 -17 -19 34 327 654 124 150 31 313 626 124 150 14,000 -21 -23 35 315 630 124 155 32 300 600 124 55 16,000 -24 -27 36 304 608 124 160 32 290 580 124 160 18,000 -28 -31 36 296 592 124 165 33 280 560 124 165 20,000 -32 -35 37 289 578 124 171 34 273 546 124 171 22,000 -36 -39 38 284 568 124 176 34 268 536 124 176 24,000 -39 -43 38 280 560 124 182 35 263 526 124 182 26,000 -43 -47 39 278 556 124 189 36 260 520 124 189 28,000 -47 -50 41 283 566 124 195 36 258 516 124 195 29,000 -49 -52 41 285 570 124 199 37 260 520 124 199 31,000 -52 -56 43 290 580 124 206 38 264 528 124 206 33,000 -56 -60 44 296 592 124 213 39 269 538 124 213 35,000 -60 -64 --- --- --- --- --- 41 274 548 124 221 BT055945 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 1 of 2)  CA 7-174  Change 2