TM 1-1510-225-10 7-40 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 10 5 2230 100 940 236 233 237 234 238 235 239 236 2000 6 1 2230 100 914 234 238 235 239 236 240 237 240 4000 3 -3 2230 100 888 232 242 233 243 234 244 235 245 6000 -1 -7 2230 100 862 229 247 231 248 232 249 232 250 8000 -5 -11 2230 100 840 227 251 228 253 229 254 230 255 10,000 -9 -15 2230 100 818 225 256 226 257 227 259 228 260 12,000 -12 -19 2230 100 800 222 261 223 262 225 264 226 265 14,000 -16 -23 2230 100 786 220 266 221 268 222 269 223 270 16,000 -20 -27 2230 100 776 217 271 218 273 220 274 222 276 18,000 -24 -31 2230 100 768 214 276 216 278 217 279 218 281 20,000 -27 -35 2141 96 734 208 276 210 279 211 281 213 283 22,000 -31 -39 2052 92 698 201 276 203 279 205 281 207 284 24,000 -35 -43 1918 86 652 193 274 195 277 197 280 199 283 26,000 -40 -47 1784 80 606 184 270 187 274 189 278 191 281 28,000 -44 -51 1650 74 558 174 265 177 270 180 275 183 278 29,000 -46 -52 1583 71 534 168 261 172 267 176 272 179 277 31,000 – – –     – – – – – – – – – – – – – – – – – –     – – –     – – –     – – – – – –     – – –     – – – 33,000 – – –     – – – – – – – – – – – – – – – – – –     – – –     – – –     – – – – – –     – – –     – – – 35,000 – – –     – – – – – – – – – – – – – – – – – –     – – –     – – –     – – – – – –     – – –     – – – Figure 7-36.  Normal Cruise Power, 1700 RPM, ISA – 10 °C