TM 1-1510-223-10 MAXIMUM CRUISE POWER 1700 RPM ISA +10°C WEIGHT® 16,000 POUNDS 14,000 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 29 25 83 619 1238 209 215 83 619 1238 211 216 2000 25 21 83 599 1198 207 219 83 599 1198 208 220 4000 22 17 83 581 1162 205 223 83 580 1160 206 225 6000 18 13 83 565 1130 202 227 83 565 1130 204 229 8000 14 9 83 553 1106 200 232 83 553 1106 202 234 10,000 10 5 83 545 1090 198 237 83 545 1090 200 239 12,000 7 1 83 533 1066 196 241 83 534 1068 198 243 14,000 3 -3 78 502 1004 189 240 78 503 1006 191 243 16,000 -1 -7 74 473 946 182 239 74 473 946 185 243 18,000 -5 -11 69 445 890 175 238 70 446 892 178 242 20,000 -9 -15 65 420 840 168 236 66 421 842 171 241 22,000 -14 -19 61 396 792 160 234 61 397 794 165 239 24,000 -18 -23 57 372 744 152 230 57 373 746 157 237 26,000 -22 -27 53 348 696 143 225 53 349 698 150 234 28,000 -26 -30 49 325 650 133 217 50 327 654 141 230 29,000 -28 -32 47 314 628 127 212 48 316 632 137 227 31,000 -31 -36- --- --- --- --- --- 44 293 586 127 219 33,000 -36 -40 --- --- --- --- --- --- --- --- --- --- 35,000 -40 -44 --- --- --- --- --- --- --- --- --- --- BT03285 NOTE During operations with ice vanes extended, torque will decrease approximately 10 percentage points (E.  G., 64% 10 percentage points = 54%), fuel flow will decrease approximately 35 LBS/HR/ENG, and true airspeed will be reduced approximately 20 knots. Figure 7-50.  Maximum Cruise Power at 1700 RPM - ISA +10 °C (Sheet 1 of 2)  IR Change 2  7-69