TM 1-1510-218-10 7-67 MAXIMUM CRUISE POWER 1900 RPM ISA NOTE: 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 FUEL FLOW TOTAL @12,000 LB @11,000 LB @10,000 LB FEET ° C ° C % LB/HR IAS TAS IAS TAS IAS TAS SL 21 15 100 1016 246 247 247 248 248 249 2,000 17 11 100 988 244 252 245 253 245 253 4,000 13 7 100 962 241 256 242 257 243 258 6,000 9 3 100 940 239 261 240 262 241 263 8,000 6 -1 100 922 237 267 237 268 268 269 10,000 2 -5 100 904 234 272 235 273 236 274 12,000 -2 -9 100 890 232 277 233 279 234 280 14,000 -5 -13 99 874 229 282 530 284 231 285 16,000 -9 -17 93 820 221 281 222 283 223 284 18,000 -13 -21 87 768 213 280 214 282 216 283 20,000 -17 -25 81 714 204 277 206 280 207 282 22,000 -21 -28 75 666 196 275 198 278 200 280 24,000 -26 -32 70 618 186 271 189 275 191 278 26,000 -30 -36 64 572 178 266 180 271 183 275 28,000 -34 -40 59 530 167 261 171 266 174 271 29,000 -36 -42 57 510 162 257 166 264 170 269 31,000 -40 -46 52 472 151 249 156 259 161 264 33,000 -45 -50 47 434 137 235 145 248 151 258 35,000 --- --- --- --- --- --- --- --- --- --- Figure 7-63.  Maximum Cruise Power, 1900 RPM - ISA