TM 1-1510-223-10 LOITER POWER 1700 RPM ISA -20°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 -4 -5 28 388 776 124 123 26 379 758 124 123 2000 -7 -9 28 371 742 124 127 26 362 724 124 127 4000 -11 -13 28 354 708 124 131 26 345 690 124 131 6000 -15 -17 29 338 676 124 135 26 329 658 124 135 8000 -19 -21 29 324 648 124 139 27 314 628 124 139 10,000 -23 -25 29 309 618 124 143 27 300 600 124 143 12,000 -27 -29 30 296 592 124 147 28 287 574 124 147 14,000 -31 -33 30 285 570 124 152 28 275 550 124 152 16,000 -34 -37 31 275 550 124 157 29 265 530 124 157 18,000 -38 -41 32 267 534 124 162 29 256 512 124 162 20,000 -42 -45 32 261 522 124 167 30 249 498 124 167 22,000 -46 -49 33 256 512 124 173 30 244 488 124 173 24,000 -50 -53 34 252 504 124 178 31 239 478 124 178 26,000 -53 -57 34 249 498 124 185 32 236 472 124 185 28,000 -57 -60 35 247 494 124 191 32 233 466 124 191 29,000 -59 -62 35 246 492 124 194 32 232 464 124 194 31,000 -63 -66 36 247 494 124 201 33 230 460 124 201 33,000 -66 -70 37 251 502 124 208 34 233 466 124 208 35,000 -70 -74 38 256 512 124 216 35 238 476 124 216 BT03602 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 7-107.  Loiter Power at 1700 RPM - ISA -20°C (Sheet 2 of 2)   IR Change 2  7-169