TM 1-1510-225-10 7-43 NORMAL CRUISE POWER 1700 RPM ISA + 20 °C NOTE:    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 40 35 2230 100 958 323 241 233 242 234 243 235 244 2000 37 31 2230 100 932 229 245 231 247 232 248 233 249 4000 33 27 2230 100 94 227 250 228 251 229 252 230 253 6000 29 23 2230 100 878 225 255 226 256 227 257 228 258 8000 25 19 2230 100 854 222 260 223 261 224 262 225 263 10,000 22 15 2230 100 832 220 265 221 266 222 268 223 269 12,000 18 11 2208 99 806 216 269 218 271 219 272 220 274 14,000 14 7 2219 95 762 210 269 212 271 213 273 215 274 16,000 10 3 2029 91 722 203 269 205 272 207 274 209 276 18,000 6 -1 1940 87 682 197 269 199 272 201 275 202 277 20,000 2 -5 1873 84 654 191 270 194 273 195 276 197 279 22,000 -2 -9 1874 80 624 184 270 187 274 189 277 919 280 24,000 -6 -13 1673 75 582 175 266 179 271 182 275 184 279 26,000 -10 -17 1539 69 536 165 260 170 266 173 271 176 275 28,000 -14 -21 1405 63 492 153 250 159 259 163 265 167 271 29,000 -17 -22 1338 60 472 145 242 153 254 158 262 162 268 31,000 -21 -26 1227 55 432 – – – – – – 140 242 149 255 153 263 33,000 -25 -30 1115 50 400 – – – – – –     – – –     – – – 136 243 143 258 35,000 -29 -34 1026 46 368 – – – – – –     – – –     – – –     – – – – – – 131 244 Figure 7-39.  Normal Cruise Power, 1700 RPM, ISA + 20 °C