TM 1-1510-223-10 LOITER POWER 1700 RPM ISA -10°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 6 5 27 390 780 124 126 26 380 760 124 126 2000 3 1 28 373 746 124 129 26 364 728 124 129 4000 -1 -3 28 357 714 124 133 26 347 694 124 133 6000 -5 -7 29 342 684 124 137 27 332 664 124 137 8000 -9 -11 29 328 656 124 141 27 318 636 124 141 10,000 -13 -15 30 314 628 124 146 27 304 608 124 146 12,000 -17 -19 30 301 602 124 150 28 291 582 124 150 14,000 -21 -23 31 290 580 124 155 28 279 558 124 155 16,000 -24 -27 31 279 558 124 160 29 269 538 124 160 18,000 -28 -31 32 271 542 124 165 30 259 518 124 165 20,000 -32 -35 33 264 528 124 171 30 252 504 124 171 22,000 -36 -39 33 259 518 124 176 31 247 494 124 176 24,000 -39 -43 34 255 510 124 182 31 243 486 124 182 26,000 -43 -47 35 251 502 124 189 32 239 478 124 189 28,000 -47 -50 35 249 498 124 195 32 235 470 124 195 29,000 -49 -52 35 248 496 124 199 33 234 468 124 199 31,000 -52 -56 37 253 506 124 206 33 234 468 124 206 33,000 -56 -60 38 257 514 124 213 35 238 476 124 213 35,000 -60 -64 39 262 524 124 221 36 243 486 124 221 BT03604 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 7-109.  Loiter Power at 1700 RPM - ISA -10°C (Sheet 2 of 2)  IR Change 2  7-173