TM 1-1510-223-10 MAXIMUM CRUISE 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 30 25 83 639 1278 219 225 83 639 1278 220 226 2000 26 21 83 619 1238 217 229 83 619 1238 218 230 4000 22 17 83 601 1202 215 234 83 600 1200 216 235 6000 18 13 83 584 1168 203 239 83 584 1168 214 240 8000 15 9 83 571 1142 211 244 83 571 1142 212 245 10,000 11 5 83 563 1126 209 244 83 562 1124 210 250 12,000 7 1 80 535 1070 204 249 80 535 1070 205 252 14,000 3 -3 76 504 1008 198 250 76 504 1008 200 253 16,000 -1 -7 72 475 950 192 251 72 475 950 194 254 18,000 -5 -11 68 447 894 185 251 68 448 896 188 254 20,000 -9 -15 64 423 846 179 251 65 423 846 182 254 22,000 -13 -19 61 399 798 173 251 61 399 798 175 254 24,000 -17 -23 57 374 748 166 250 57 375 750 169 254 26,000 -21 -27 53 351 702 159 248 53 352 704 163 253 28,000 -25 -30 49 329 658 152 246 50 329 658 156 252 29,000 -27 -32 48 318 636 148 244 48 319 638 152 251 31,000 -31 -36 44 295 590 140 240 44 296 592 145 248 33,000 -35 -40 40 273 546 130 234 40 274 548 137 244 35,000 -40 -44 36 250 500 119 223 37 251 502 128 238 BT0559310 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 7-51.  Maximum Cruise Power at 1700 RPM - ISA +10 °C (Sheet 2 of 2)  CA 7-72  Change 2