TM 1-1510-225-10 7-67 NORMAL CRUISE POWER 1800 RPM ISA + 20 °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 41 35 2230 100 994 237 246 238 247 239 248 240 249 2000 37 31 2230 100 968 235 251 236 252 237 253 237 254 4000 33 27 2230 100 940 232 255 233 257 234 258 235 259 6000 29 23 2230 100 914 230 261 231 262 232 263 233 264 8000 26 19 2230 100 890 227 266 228 267 230 268 230 269 10,000 22 15 2208 99 862 224 270 225 271 227 273 228 274 12,000 18 11 2096 94 806 217 270 219 271 220 273 221 275 14,000 14 7 2007 90 762 211 270 213 273 214 274 215 276 16,000 10 3 1918 86 722 205 271 207 273 208 276 210 277 18,000 6 -1 1851 83 682 198 271 200 274 202 276 204 279 20,000 2 -5 1784 80 656 193 273 195 276 197 279 199 281 22,000 -1 -9 1717 77 626 187 273 189 277 191 280 193 283 24,000 -6 -13 1606 72 584 178 270 181 274 184 278 186 282 26,000 -10 -17 1472 66 538 168 264 172 270 175 274 178 279 28,000 -14 -21 1338 60 494 155 253 161 263 165 269 169 274 29,000 -17 -22 1271 57 472 147 245 155 257 160 266 164 272 31,000 -21 -26 1160 52 434 – – – – – – 142 245 150 258 155 266 33,000 -25 -30 1026 46 380 – – – – – –     – – –     – – – 137 245 145 259 35,000 -29 -34 982 44 368 – – – – – –     – – –     – – –     – – – – – – 132 246 Figure 7-63.  Normal Cruise Power, 1800 RPM, ISA + 20 °C