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 32 414 828 124 126 30 401 802 124 126 2000 3 1 33 398 796 124 129 30 385 770 124 129 4000 -1 -3 33 382 764 124 133 31 369 738 124 133 6000 -5 -7 34 367 734 124 137 31 354 708 124 137 8000 -9 -11 35 353 706 124 141 32 340 680 124 141 10,000 -13 -15 35 340 680 124 146 32 326 652 124 146 12,000 -17 -19 36 327 654 124 150 33 314 628 124 150 14,000 -21 -23 37 316 632 124 155 34 302 604 124 155 16,000 -24 -27 38 307 614 124 160 34 292 584 124 160 18,000 -28 -31 38 299 598 124 165 35 284 568 124 165 20,000 -32 -35 39 294 588 124 171 36 278 556 124 171 22,000 -36 -39 40 289 578 124 176 36 273 546 124 176 24,000 -39 -43 41 286 572 124 182 37 270 540 124 182 26,000 -43 -47 42 287 574 124 189 38 266 532 124 189 28,000 .47 -50 43 292 584 124 195 39 268 536 124 195 29,000 -49 -52 44 295 590 124 199 39 270 540 124 199 31,000 -52 -56 45 300 600 124 206 41 274 548 124 206 33,000 -56 -60 --- --- --- --- --- 42 280 560 124 213 35,000 --- --- --- --- --- --- --- --- --- --- --- --- BT03603 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/HRIENG, and true airspeed will be reduced approximately 20 knots. Figure 7-109.  Loiter Power at 1700 RPM - ISA -10°C (Sheet 1 of 2)   IR 7-172  Change 2