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 25 390 780 124 121 23 381 762 124 121 2000 -18 -19 26 371 742 124 125 24 362 724 124 125 4000 -21 -23 26 353 706 124 128 24 344 688 124 128 6000 -25 -27 26 337 674 124 132 24 328 656 124 132 8000 -29 -31 27 321 642 124 136 25 312 624 124 136 10,000 -33 -35 27 306 612 124 140 25 297 594 124 140 12,000 -37 -39 28 292 584 124 144 25 283 566 124 144 14,000 -41 -43 28 280 560 124 149 26 270 540 124 149 16,000 -45 -47 29 269 538 124 153 26 259 518 124 153 18,000 -48 -51 30 260 520 124 158 27 249 498 124 158 20,000 -52 -55 31 251 502 124 163 27 241 482 124 163 22,000 -56 -59 31 246 492 124 169 28 234 468 124 169 24,000 -60 -63 32 242 484 124 174 29 229 458 124 174 26,000 -63 -67 32 239 478 124 180 29 225 450 124 180 28,000 -67 -70 32 236 472 124 186 30 223 446 124 186 29,000 -69 -72 32 235 470 124 190 30 321 442 124 190 31,000 -73 -76 33 234 468 124 196 30 220 440 124 296 33,000 -77 -80 34 237 474 124 203 31 220 440 124 203 35,000 -80 -84 35 241 482 124 210 32 224 448 124 210 BT055942 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 7-106.  Loiter Power at 1700 RPM - ISA -30°C (Sheet 2 of 2)   CA Change 2  7-167