TM 1-1510-218-10 7-71 MAXIMUM CRUISE POWER 1900 RPM ISA + 37 °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 58 52 95 1012 236 252 237 253 238 254 2,000 54 48 93 970 232 255 233 256 234 257 4,000 50 44 91 928 228 258 229 259 230 260 6,000 46 40 90 890 224 261 225 262 226 264 8,000 43 36 87 848 219 263 220 265 221 266 10,000 39 32 84 502 213 264 214 266 216 268 12,000 35 28 80 756 206 264 208 266 210 268 14,000 31 22 75 710 199 263 201 266 203 268 16,000 27 18 71 666 192 262 194 265 196 268 18,000 23 14 67 624 184 260 187 264 189 267 20,000 19 10 62 584 176 258 179 262 182 266 22,000 15 7 59 546 168 255 172 260 175 264 24,000 11 3 55 510 160 250 164 257 167 262 26,000 6 -1 51 474 150 244 155 252 159 259 28,000 2 -5 47 442 138 234 146 146 151 254 29,000 0 -7 45 426 132 227 141 242 146 252 31,000 -5 -11 41 394 --- --- 128 229 137 244 33,000 --- --- --- --- --- --- --- --- --- --- 35,000 --- --- --- --- --- --- --- --- --- --- Figure 7-67.  Maximum Cruise Power, 1900 RPM - ISA + 37 °C