TCDS E-288

Page No. 1 2 Rev. No. 1 1 DEPARTMENT OF COMMERCE CIVIL AERONAUTICS ADMINISTRATION E-288 Revision 1 FAIRCHILD FT-101E May 1, 1956 AIRCRAFT ENGINE SPECIFICATION Engines of models described herein conforming with this specification and approved data on file with the Civil Aeronautics Administration are rated as airworthy for use in certificated aircraft in accordance with pertinent aircraft specifications and the manufacturer's installation, operation, repair and overhaul instructions. Manufacturer Fairchild Engine Division Fairchild Engine and Airplane Corporation Deer Park, New York Model FT-101E Type - Turbojet Single-stage, mixed flow compressor Single-stage, axial flow turbine 1 annular combustion chamber Ratings Maximum continuous static thrust, lbs., rpm, altitude 900-15,100-S.L. Takeoff static thrust (5 minutes), lbs., rpm, altitude 1000-15,780-S.L. Fuel control Woodward type 1374 Fuel (MIL-F-5572) Aviation Gasoline Oil (MIL-L-7808A) Esso Turbo 15 Accessory housing oil capacity, pts. .75 Engine oil mist lubricator capacity, pts. .85 Principal Dimensions Length overall, in. 90.4 Diameter, in. 24.3 Weight (dry), lbs. 380 Center of gravity, in. aft of trunnion 10.5 Ignition General Laboratories type 19800 with two igniters and a dual ignition coil Certification basis Type Certificate No. 288 Production basis Pending NOTE 1. Maximum permissible temperatures are as follows: Turbine outlet gas temperatures, Takeoff, 1325°F Maximum continuous, 1290°F Transient, 1440°F for three seconds maximum. Bearing temperatures (recommended limits) Turbine bearing outer race, 300°F Compressor bearing outer race, 150°F NOTE 2. Fuel pump inlet pressure limits: Minimum at pump inlet, 15 psia Operating gage pressures, 14 to 50 psi "psi" = lbs./sq.in. "psia" = lbs./sq.in. absolute. E-288 2 NOTE 3. These ratings are based upon the following conditions: Compressor inlet air, 59°F and 29.92 in.Hg. dry Jet nozzle area, 118 sq.in. Turbine outlet gas temperature, 1220°F No turbine air bleed NOTE 4. Oil supply level in both the accessory drive section and the oil mist lubricator must be checked frequently when on the ground, to insure an adequate quantity since no provision is made for indicating oil pressure, or temperature or quantity while in operation. NOTE 5. The following accessory drive provisions are available: Speed Ratio to Torque (in.lb.) Overhang Drive Rotation* Turbine Shaft Continuous Static (in.lb.) Tachometer C .269 15 70 10.7 Fuel pump C .227 50 600 134.0 Starter CC .440 500 2200 187.0 *C-Clockwise **CC-Counter Clockwise NOTE 6. The following accessories are provided with the engine at weight increase indicated: Accessory Weight Tachometer Generator 2 lbs. *Starter (Jack & Heintz - D62) 25 lbs. *Starter (Jack & Heintz - D62-1) 22 lbs. Power control actuator 2 lbs. Accessory section fairing 5 lbs. Electrical conduit 5 lbs. *Optional NOTE 7. This engine has no provision for anti-icing the inlet and has not been tested to determine the extent to which flights in icing weather will adversely affect engine output. .....END.....