TM 1-1510-223-10 LOITER POWER 1700 RPM ISA -30°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 -14 -15 28 386 772 124 121 26 378 756 124 121 2000 -18 -19 28 369 738 124 125 26 360 720 124 125 4000 -21 -23 28 352 704 124 128 26 343 686 124 128 6000 -25 -27 28 336 672 124 132 26 327 654 124 132 8000 -29 -31 29 321 642 124 136 27 312 624 124 136 10,000 -33 -35 29 306 612 124 140 27 297 594 124 140 12,000 -37 -39 30 293 586 124 144 27 284 568 124 144 14,000 -41 -43 30 282 564 124 149 28 272 544 124 149 16,000 -45 -47 31 272 544 124 153 28 262 524 124 153 18,000 -48 -51 31 263 526 124 158 29 253 506 124 158 20,000 -52 -55 32 255 510 124 163 29 245 490 124 163 22,000 -56 -59 33 252 504 124 169 30 239 478 124 169 24,000 -60 -63 33 248 496 124 174 31 235 470 124 174 26,000 -63 -67 34 246 492 124 180 31 232 464 124 180 28,000 -67 -70 34 243 486 124 186 32 230 460 124 186 29,000 -69 -72 34 242 484 124 190 32 229 458 124 190 31,000 -73 -76 35 242 484 124 196 32 227 454 124 196 33,000 -77 -80 36 247 494 124 203 33 229 458 124 203 35,000 -80 -84 -37 251 502 124 210 34 233 466 124 210 BT03600 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 7-105.  Loiter Power at 1700 RPM - ISA -30°C (Sheet 2 of 2)  IR Change 2  7-165