TM 1-1510-223-10 MAXIMUM CRUISE 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 39 35 83 622 1244 210 220 83 622 1244 212 221 2000 36 31 83 601 1202 208 224 83 601 1202 209 225 4000 32 27 83 581 1162 206 228 83 581 1162 207 230 6000 28 23 83 565 1130 204 233 83 565 1130 206 235 8000 24 19 83 552 1104 202 238 83 552 1104 204 239 10,000 21 15 81 529 1058 198 240 81 529 1058 200 242 12,000 17 11 77 498 996 192 241 77 498 996 194 243 14,000 13 7 71 466 932 185 239 71 466 932 186 241 16,000 9 3 67 437 874 178 238 67 438 876 180 241 18,000 5 -1 63 411 822 171 238 63 412 824 174 241 20,000 1 -5 59 386 772 165 236 59 386 772 167 240 22,000 -3 -9 55 363 726 158 235 55 364 728 161 239 24,000 -8 -13 51 340 680 151 233 51 341 682 155 238 26,000 -12 -17 48 320 640 144 231 48 320 640 148 237 28,000 -16 -20 45 301 602 137 228 45 302 604 142 236 29,000 -18 -22 43 291 582 133 226 43 292 584 139 235 31,000 -22 -26 40 271 542 125 221 40 272 544 132 232 33,000 -26 -30 36 250 500 114 212 37 251 502 123 227 35,000 -30 -34 --- --- --- --- --- 33 230 460 114 220 BT03288 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 7-52.  Maximum Cruise Power at 1700 RPM - ISA +20 °C (Sheet 2 of 2)  IR 7-74  Change 2