TM 1-1510-218-10 7-70 MAXIMUM CRUISE POWER 1900 RPM ISA + 30 °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 51 45 100 1036 242 255 242 256 243 257 2,000 47 41 100 1008 239 259 240 260 241 261 4,000 43 37 98 964 234 262 235 263 236 264 6,000 40 33 96 924 230 265 231 266 232 268 8,000 36 29 92 880 225 267 226 268 227 270 10,000 32 25 88 834 219 268 220 270 221 271 12,000 28 21 84 786 212 268 214 270 215 272 14,000 24 17 80 738 205 267 207 270 208 272 16,000 20 13 75 694 198 367 200 269 201 272 18,000 16 9 71 652 190 265 193 269 195 271 20,000 12 5 66 608 183 263 185 267 188 270 22,000 8 2 62 570 175 261 178 265 180 269 24,000 4 -2 58 532 166 257 170 262 173 267 26,000 0 -6 54 496 156 251 161 258 165 164 28,000 -5 -10 50 462 146 243 152 253 156 260 29,000 -7 -12 48 444 140 237 147 249 152 257 31,000 -11 -16 43 410 123 218 135 238 142 250 33,000 --- --- --- --- --- --- --- --- --- --- 35,000 --- --- --- --- --- --- --- --- --- --- Figure 7-66.  Maximum Cruise Power, 1900 RPM - ISA + 30 °C