TM 1-1510-223-10 LOITER POWER 1700 RPM ISA -200C 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 25 391 782 124 123 23 382 764 124 123 2000 -7 -9 26 373 746 124 127 24 364 728 124 127 4000 -11 -13 26 356 712 124 131 24 346 692 124 131 6000 -15 -17 26 339 678 124 135 24 330 660 124 135 8000 -19 -21 27 324 648 124 139 25 314 628 124 139 10,000 -23 -25 27 309 618 124 143 25 299 598 124 143 12,000 -27 -29 28 295 590 124 147 26 285 570 124 147 14,000 -31 -33 28 283 566 124 152 26 273 546 124 152 16,000 -34 -37 29 272 544 124 157 27 262 524 124 157 18,000 -38 -41 30 263 526 124 162 27 252 504 124 162 20,000 -42 -45 30 256 512 124 167 28 244 488 124 167 22,000 -46 -49 31 250 500 124 173 28 238 476 124 173 24,000 -50 -53 32 246 492 124 178 29 233 466 124 178 26,000 -53 -57 32 242 484 124 185 30 229 458 124 185 28,000 -57 -60 33 239 478 124 191 30 226 452 124 191 29,000 -59 -62 33 238 476 124 194 30 225 450 124 194 31,000 -63 -66 33 236 472 124 201 31 222 444 124 201 33,000 -66 -70 35 241 482 124 208 31 222 444 124 208 35,000 -70 -74 36 246 492 124 216 32 227 454 124 216 BT055944 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 7-108.  Loiter Power at 1700 RPM - ISA -20°C (Sheet 2 of 2)   CA Change 2  7-171