TM 1-1510-223-10 MAXIMUM CRUISE POWER 1700 RPM ISA 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 19 15 83 612 1224 213 215 83 612 1224 214 216 2000 15 11 83 598 1196 212 220 83 598 1196 213 221 4000 12 7 83 583 1166 209 224 83 583 1166 211 225 6000 8 3 83 568 1136 207 228 83 568 1136 209 230 8000 4 -1 83 555 1110 205 233 83 555 1110 207 234 10,000 0 -5 83 544 1088 203 238 83 543 1086 205 239 12,000 -3 -9 83 533 1066 201 243 83 533 1066 203 244 14,000 -7 -13 83 527 1054 200 248 83 526 1052 201 250 16,000 -11 -17 81 510 1020 195 251 81 510 1020 197 253 18,000 -15 -21 77 481 962 189 251 77 482 964 191 253 20,000 -19 -25 73 456 912 183 251 73 456 912 185 254 22,000 -23 -29 68 431 862 177 251 68 431 862 179 254 24,000 -27 -33 64 405 810 170 250 64 406 812 172 254 26,000 -31 -37 60 380 760 163 248 60 380 760 166 253 28,000 -35 -40 55 353 706 155 246 55 354 708 159 251 29,000 -37 -42 53 340 680 151 244 53 341 682 155 249 31,000 -41 -46 48 315 630 143 239 49 316 632 147 246 33,000 -45 -50 44 290 580 133 233 44 291 582 139 242 35,000 -50 -54 39 264 528 123 224 40 266 532 130 236 BT03284 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/HRIENG, and true airspeed will be reduced approximately 20 knots. Figure 7-48.  Maximum Cruise Power at 1700 RPM - ISA (Sheet 2 of 2)   IR 7-66  Change 2