TM 1-1510-218-10 7-69 MAXIMUM CRUISE POWER 1900 RPM ISA + 20 °C 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 41 35 100 1030 243 252 244 253 245 254 2,000 37 31 100 1004 241 257 241 258 242 259 4,000 33 27 100 976 238 262 239 263 240 264 6,000 30 23 100 952 236 267 237 268 238 269 8,000 26 19 400 930 233 272 234 274 235 275 10,000 22 18 96 882 227 274 228 275 230 276 12,000 18 11 91 834 220 274 222 275 223 277 14,000 14 7 86 784 213 274 215 276 216 277 16,000 10 3 82 736 206 273 208 275 210 277 18,000 6 -1 77 690 199 272 201 274 203 277 20,000 2 -5 72 646 191 270 193 273 195 276 22,000 -2 -8 67 604 182 267 185 271 188 274 24,000 -6 -12 62 564 174 263 177 268 180 272 26,000 -10 -16 58 524 164 258 168 264 171 269 28,000 -14 -20 53 486 154 251 159 258 163 265 29,000 -16 -22 51 468 148 246 153 255 158 262 31,000 -21 -26 46 432 134 232 143 246 148 255 33,000 -26 -30 42 396 --- --- 129 231 138 247 35,000 --- --- --- --- --- --- --- --- --- --- Figure 7-65.  Maximum Cruise Power, 1900 RPM - ISA + 20 °C