TM 1-1510-218-10 7-66 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 11 5 100 1010 248 244 248 245 249 246 2,000 7 1 100 984 245 249 246 250 247 250 4,000 3 -3 100 960 213 254 244 254 245 255 6,000 -1 -7 100 936 243 258 242 259 242 260 8,000 -4 -11 100 916 238 268 239 264 240 265 10,000 -8 -15 100 900 236 269 237 270 238 271 12,000 -12 -19 100 890 234 274 235 275 236 276 14,000 -15 -23 100 880 261 280 232 281 233 282 16,000 -19 -27 98 856 227 283 228 284 229 286 18,000 -23 -31 91 798 218 281 220 283 221 284 20,000 -27 -35 85 740 210 279 211 281 213 283 22,000 -31 -38 79 690 201 276 203 279 205 281 24,000 -35 -42 73 642 192 273 195 276 197 279 26,000 -40 -46 67 594 183 269 186 273 188 276 28,000 -44 -50 62 550 173 264 177 269 179 273 29,000 -46 -52 59 530 168 261 172 266 275 271 31,000 --- --- --- --- --- --- --- --- --- --- 33,000 --- --- --- --- --- --- --- --- --- --- 35,000 --- --- --- --- --- --- --- --- --- --- Figure 7-62.  Maximum Cruise Power, 1900 RPM, ISA – 10 °C