TM 1-1510-225-10 7-54 MAXIMUM CRUISE POWER 1700 RPM ISA + 10 °C NOTES: IOAT, TORQUE, AND FUEL FLOW BASED ON 12,000 POUNDS. TO OBTAIN FUEL FLOW PER ENGINE, DIVIDE  THE TOTAL FUEL FLOW  VALUE FOR THE CORRESPONDING ALTITUDE BY TWO. AIRSPEED ~ KNOTS PRESSURE ALT IOAT    OAT TORQUE PER ENGINE TOTAL FUEL FLOW 13,000 LB 12,000 LB 11,000 LB 10,000 LB FEET ° C ° C FT-LB % LB/HR IAS TAS IAS TAS IAS TAS IAS TAS SL 30 25 2230 100 952 233 238 234 239 235 240 236 241 2000 27 21 2230 100 924 231 243 232 244 233 145 234 246 4000 23 17 2230 100 898 229 247 230 249 231 250 232 251 6000 19 13 2230 100 874 226 252 227 253 228 255 229 256 8000 15 9 2230 100 848 224 257 225 258 226 259 227 261 10,000 12 5 2230 100 826 221 262 222 263 224 265 225 266 12,000 8 1 2230 100 804 219 267 220 269 221 270 222 271 14,000 4 -3 2230 100 790 216 272 217 273 219 275 220 276 16,000 0 -7 2230 100 778 213 277 214 278 216 280 217 282 18,000 -3 -11 2141 96 740 206 277 209 279 210 281 211 283 20,000 -7 -15 2052 92 706 200 277 202 280 204 282 205 285 22,000 -11 -19 1940 87 672 192 276 195 279 197 282 199 285 24,000 -15 -23 1806 81 628 184 273 187 277 189 281 191 284 26,000 -20 -27 1695 76 580 175 268 178 274 181 278 184 282 28,000 -24 -31 1561 70 536 164 262 169 269 172 274 175 279 29,000 -26 -32 1494 67 514 158 257 163 265 167 271 171 277 31,000 -30 -36 1360 61 474 145 245 153 257 158 265 162 272 33,000 -35 -40 1249 56 434 – – – – – – 140 245 148 258 153 267 35,000 -41 -44 1093 49 388 – – – – – –     – – –     – – – 134 245 142 259 Figure 7-50.  Maximum Cruise Power, 1700 RPM, ISA + 10 °C