TM 1-1510-225-10 7-44 NORMAL CRUISE POWER 1700 RPM ISA + 30 °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 51 45 2230 100 964 231 243 231 244 232 245 233 246 2000 47 41 2230 100 936 228 248 229 249 230 250 231 251 4000 43 37 2230 100 910 226 252 227 254 228 255 229 256 6000 39 33 2230 100 882 223 257 224 259 225 260 226 261 8000 36 29 2230 100 858 221 262 222 264 223 265 224 266 10,000 32 25 2163 97 818 216 264 217 266 219 268 220 269 12,000 28 21 2074 93 764 209 264 211 266 212 268 214 270 14,000 24 17 1985 89 724 203 265 205 267 206 269 208 271 16,000 20 13 1896 85 686 196 265 198 268 200 270 202 272 18,000 16 9 1806 81 650 190 265 192 268 194 271 197 273 20,000 12 5 1762 79 626 185 266 187 270 189 273 191 276 22,000 8 1 1717 77 602 179 267 182 271 184 275 186 278 24,000 4 -3 1583 71 560 169 262 173 268 176 272 179 276 26,000 0 -7 1472 66 516 159 255 164 262 168 268 171 273 28,000 -4 -11 1338 60 474 147 244 153 255 158 263 162 269 29,000 -7 -12 1293 58 454 137 232 147 250 153 259 157 266 31,000 -12 -16 1160 52 414 – – – – – – 131 231 142 250 148 260 33,000 -16 -20 1048 47 382 – – – – – –     – – –     – – – 126 230 137 251 35,000 -20 -24 959 43 350 – – – – – –     – – –     – – –     – – – – – – 121 230 Figure 7-40.  Normal Cruise Power, 1700 RPM, ISA + 30 °C