TM 1-1510-223-10 ONE-ENGINE-INOPERATIVE MAXIMUM CRUISE POWER 1700 RPM ISA WEIGHT® 12,000 POUNDS 10,000 POUNDS TORQUE FUEL TOTAL TORQUE FUEL TOTAL PRESSURE PER FLOW FUEL PER FLOW FUEL ALTITUDE IFAT FAT ENGINE PER FLOW IAS TAS ENGINE PER FLOW IAS TAS ENGINE ENGINE FEET °C °C PERCENT LBS/HR LBS/HR KTS KTS PERCENT   LBS/HR    LBS/HR KTS KTS 0 17 15 83 627 627 157 160 83 627 627 160 163 2000 13 11 83 611 611 155 163 83 611 611 158 166 4000 10 7 83 595 595 153 165 83 595 595 156 169 6000 6 3 83 580 580 151 168 83 579 579 154 172 8000 2 -1 83 566 566 149 171 83 566 566 153 175 10,000 -2 -5 83 554 554 147 174 83 553 553 151 178 12,000 -6 -9 83 544 544 145 178 83 544 544 149 182 14,000 -10 -13 80 522 522 140 178 81 523 523 145 183 16,000 -14 -17 76 493 493 134 176 76 495 495 140 182 18,000 -18 -21 72 468 468 128 174 72 470 470 134 181 20,000 -22 -25 68 443 443 121 170 68 445 445 129 180 22,000 -26 -29 63 416 416 112 164 64 419 419 122 178 24,000 -30 -33 59 388 388 100 153 60 393 393 116 175 26,000 -34 -37 --- --- --- --- --- 55 366 366 107 169 28,000 -38 -40 --- --- --- --- --- 51 339 339 97 159 29,000 -40 -42 --- --- --- --- --- 48 324 324 89 150 31,000 --- --- --- --- --- --- --- --- --- --- --- --- 33,000 --- --- --- --- --- --- --- --- --- --- --- --- 35,000 --- --- --- --- --- --- --- --- --- --- --- --- BT03644 NOTE During  operations  with  ice  vanes  extended,  torque  will  decrease  approximately  7 percentage points (E.  G., 67% 7 percentage points = 60%), fuel flow will decrease approximately 25 LBS/HR/ENG, and true airspeed will be reduced approximately 15 knots. Figure 7-132.  One Engine Inoperative Max Cruise Power at 1700 RPM - ISA (Sheet 2 of 2)    IR 7-214  Change 2