TM 1-1510-218-10 7-68 MAXIMUM CRUISE POWER 1900 RPM ISA + 10 °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 31 25 100 1024 244 250 245 251 246 251 2,000 27 21 100 998 242 254 243 255 244 256 4,000 23 17 100 972 240 259 241 260 241 261 6,000 20 13 100 948 237 264 238 265 239 266 8,000 16 9 100 926 235 270 236 271 237 272 10,000 12 5 100 908 233 275 234 276 235 277 12,000 8 1 99 882 229 279 230 280 231 282 14,000 5 -3 93 830 222 279 223 280 224 282 16,000 1 -7 88 778 214 278 216 280 217 281 18,000 -3 -11 82 730 206 277 208 279 209 281 20,000 -8 -15 77 682 198 275 200 277 202 280 22,000 -12 -18 72 238 189 272 192 275 194 278 24,000 -16 -22 66 592 180 268 183 272 186 275 26,000 -20 -26 61 550 171 263 174 268 177 272 28,000 -24 -30 56 512 161 257 165 263 169 269 29,000 -29 -32 54 492 155 253 160 260 164 266 31,000 -30 -36 49 454 144 242 150 253 155 261 33,000 -35 -40 45 418 126 221 138 242 147 254 35,000 -40 -44 38 380 --- --- 121 222 133 243 Figure 7-64.  Maximum Cruise Power, 1900 RPM - ISA + 10 °C