TM 1-1510-225-10 7-66 NORMAL CRUISE POWER 1800 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 31 25 2230 100 990 238 244 239 245 240 246 241 246 2000 27 21 2230 100 962 236 248 237 249 238 250 239 251 4000 23 17 2230 100 936 234 253 235 254 236 255 237 256 6000 19 13 2230 100 910 231 258 232 259 233 260 234 261 8000 16 9 2230 100 886 229 263 230 264 231 265 232 266 10,000 12 5 2230 100 862 226 268 228 269 229 270 230 272 12,000 8 1 2230 100 840 224 273 225 275 226 276 227 277 14,000 4 -3 2163 97 802 218 275 220 277 221 278 222 280 16,000 0 -7 2052 92 756 212 275 213 277 215 279 216 281 18,000 -4 -11 1962 88 714 205 275 207 277 208 280 210 281 20,000 -7 -15 1873 84 682 199 275 201 278 203 281 204 283 22,000 -11 -19 1784 80 648 191 275 194 278 196 281 198 283 24,000 -15 -23 1673 75 606 183 272 186 276 188 279 191 282 26,000 -20 -27 1539 69 560 174 267 177 272 180 277 183 280 28,000 -24 -31 1405 63 514 163 260 167 267 171 272 174 277 29,000 -26 -32 1360 61 494 149 247 162 263 166 270 170 275 31,000 -31 -36 1227 55 454 133 229 150 253 156 263 161 270 33,000 -36 -40 1115 50 414 – – – – – – 135 237 145 254 151 264 35,000 -40 -44 1026 46 380 – – – – – –     – – –     – – – 130 237 140 254 Figure 7-62.  Normal Cruise Power, 1800 RPM, ISA + 10 °C