TM 1-1510-218-10 7A-55 MAXIMUM CRUISE POWER 1700 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 % LB/HR IAS TAS IAS TAS IAS TAS IAS TAS SL 40 35 100 958 323 241 233 242 234 243 235 244 2000 37 31 100 932 229 245 231 247 232 248 233 249 4000 33 27 100 904 229 250 228 251 229 252 230 253 6000 29 23 100 878 225 255 226 256 227 257 228 258 8000 25 19 100 854 222 260 223 261 224 262 225 263 10,000 22 15 100 832 220 265 221 266 222 268 223 269 12,000 18 11 100 810 217 270 218 271 220 273 221 274 14,000 14 7 98 780 212 272 214 274 215 276 217 278 16,000 10 3 94 744 206 273 208 275 210 278 211 279 18,000 6 -1 91 708 200 274 202 276 204 279 206 281 20,000 3 -5 87 678 194 274 196 277 198 280 200 283 22,000 -1 -9 83 646 187 274 190 278 192 281 995 284 24,000 -6 -13 78 604 179 271 182 275 185 279 187 283 26,000 -10 -17 72 558 169 265 173 271 176 276 179 280 28,000 -14 -21 66 514 157 257 162 264 167 271 170 276 29,000 -16 -22 60 472 151 251 157 260 162 268 165 273 31,000 -21 -26 55 434 133 230 146 251 152 261 156 269 33,000 -26 -30 49 392 – – – – – – 128 229 141 252 147 262 35,000 -29 -34 46 368 – – – – – – – – – – – – – – – – – – 136 252 Figure 7A-51.  Maximum Cruise Power, 1700 RPM, ISA + 20 C