TM 1-1510-225-10 7-53 MAXIMUM CRUISE POWER 1700 RPM ISA 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 20 15 2230 100 946 235 236 236 237 237 238 238 239 2000 16 11 2230 100 920 232 240 234 241 235 242 235 243 4000 13 7 2230 100 892 230 245 231 246 232 247 233 248 6000 9 3 2230 100 866 228 249 229 251 230 252 231 253 8000 5 -1 2230 100 844 225 254 226 255 228 257 228 258 10,000 1 -5 2230 100 822 223 259 224 260 225 262 226 263 12,000 -2 -9 2230 100 800 220 264 222 266 223 267 224 286 14,000 -6 -13 2230 100 786 218 269 219 271 221 272 222 274 16,000 -10 -17 2230 100 776 215 274 216 276 218 277 219 279 18,000 -13 -21 2230 100 772 212 278 213 281 215 282 217 284 20,000 -17 -25 2141 96 734 205 279 207 281 209 283 210 285 22,000 -21 -29 2029 91 698 199 274 200 281 202 284 204 286 24,000 -25 -33 1896 85 652 191 276 193 280 195 283 197 286 26,000 -29 -37 1762 79 604 181 272 184 277 187 280 189 284 28,000 -34 -41 1628 73 558 171 266 175 272 178 277 181 281 29,000 -36 -42 1561 70 536 166 263 170 269 173 275 176 279 31,000 -40 -46 1427 64 494 154 253 159 262 164 270 167 275 33,000 -45 -50 1316 59 452 137 235 148 253 154 262 158 270 35,000 – – –     – – – – – – – – – – – – – – – – – –     – – –     – – –     – – – – – –     – – –     – – – Figure 7-49.  Maximum Cruise Power, 1700 RPM, ISA