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 37 35 27 410 820 124 132 25 397 794 124 132 2000 33 31 27 394 788 124 126 25 380 760 124 136 4000 29 27 28 376 752 124 140 26 364 728 124 140 6000 25 23 28 359 718 124 145 26 349 698 124 145 8000 21 19 29 342 684 124 149 27 332 664 124 149 10,000 17 15 29 326 652 124 154 27 316 632 124 154 12,000 14 11 30 311 622 124 159 27 301 602 124 159 14,000 10 7 30 300 600 124 164 28 290 580 124 164 16,000 6 3 31 290 580 124 170 28 279 558 124 170 18,000 2 -1 31 279 558 124 175 29 268 536 124 175 20,000 -2 -5 32 270 540 124 181 30 259 518 124 181 22,000 -5 -9 33 265 530 124 187 30 252 504 124 187 24,000 -9 -13 34 261 522 124 194 31 246 492 124 194 26,000 -13 -17 35 258 516 124 201 32 242 484 124 201 28,000 -16 -20 35 257 514 124 208 32 240 480 124 208 29,000 -18 -22 36 257 514 124 212 33 240 480 124 212 31,000 -22 -26 37 258 516 124 220 33 240 480 124 220 33,000 -26 -30 --- --- --- --- --- 34 241 482 124 228 35,000 --- --- --- --- --- --- --- --- --- --- --- --- BT0559412 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 7-116.  Loiter Power at 1700 RPM - ISA +20°C (Sheet 2 of 2)  CA Change 2  7-187