TM 1-1510-225-10 7-42 NORMAL CRUISE POWER 1700 RPM ISA + 10 °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 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 2163 97 756 210 273 212 275 213 277 215 279 18,000 -4 -11 2052 92 714 203 273 205 275 207 277 208 279 20,000 -8 -15 1962 88 680 197 273 199 276 201 278 202 281 22,000 -12 -19 1851 83 648 189 271 192 275 194 278 196 281 24,000 -16 -23 1739 78 604 181 268 184 273 186 276 189 280 26,000 -20 -27 1606 72 558 171 263 175 269 178 273 180 277 28,000 -24 -31 1472 66 512 160 256 165 263 169 269 172 274 29,000 -26 -32 1405 63 492 154 251 160 259 164 266 167 271 31,000 -31 -36 1293 58 452 139 234 149 251 154 260 158 267 33,000 -36 -40 1160 52 414 – – – – – – 133 234 143 251 149 261 35,000 -40 -44 1070 48 380 – – – – – –     – – –     – – – 128 233 138 251 Figure 7-38.  Normal Cruise Power, 1700 RPM, ISA + 10 °C