TCDS E-142

Page No. 1 2 Rev. No. 3 3 FEDERAL AVIATION AGENCY E-142 Revision 3 Pratt & Whitney WASP S3H1-G R-1340-59 February 1, 1974 AIRCRAFT ENGINE SPECIFICATION Engines of models described herein conforming with this specification and approved data on file with the Federal Aviation Agency meet the minimum standards for use in certificated aircraft in accordance with pertinent aircraft specifications and applicable portions of the Civil Air Regulations provided they are installed, operated, and maintained as prescribed by the approved manufacturer's manuals and other approved instructions. Manufacturer Pratt & Whitney Aircraft Division of United Aircraft Corporation East Hartford, Connecticut Model Wasp S3H1 R-1340-59 Type 9RA 3:2 reduction gearing - - Rating (Impeller gear ratio) 10:1 - - Maximum continuous, hp., rpm, in.Hg., at: Critical altitude (ft.) 550-2200-32.5-5000 - - Sea level pressure altitude (ft.) 550-2200-34.0-S.L. - - Takeoff (5 minutes), hp., rpm, in.Hg., at: Critical altitude (ft.) 600-2250-35.5-3000 - - Sea level pressure altitude (ft.) 600-2250-36.0-S.L. - - (See Note 4 for additional rating.) Fuel (minimum grade aviation gasoline) 80/87 - - Lubricating oil See P&WA Service Bulletin No. 1183 - - Bore and stroke, in. 5.75 X 5.75 - - Displacement, cu. in. 1344 - - Compression ratio 6:1 - - Weight (dry), lb. 930 950 Propeller shaft, SAE No. 40 - - Carburetion Stromberg NA-Y9B, NA-Y9C or NA-Y9H with 2-3/4 in. venturi Strromberg NA-Y9E1 Ignition, Dual Scintilla SB9R magnetos Scintilla SB9RN-4 Timing, °BTC 25 - - Spark plugs See P&WA Service Bulletin No. 1175 - - Notes 1, 2, 3, 4, 7 1, 2, 3, 6, 7 Certification basis Type Certificate No. 142 Production basis Production Certificate No. 2 E-143 2 NOTE 1. Maximum permissible temperatures are as follows: Cylinder Head Cylinder Barrel Oil Inlet S3H1-G 500°F. 300°F. 200°F. R-1340-59 500°F. 335°F. 200°F. NOTE 2. Fuel and oil pressure limits: S3H1-G R-1340-59 Fuel pressure (psi) 3-6 3-5 Oil pressure (psi) 70-90 70-90 NOTE 3. The following accessory drives are provided: Direction of Rotation (Clockwise or Counter- Speed Ratio (Times Crankshaft Maximum Torque (in. lb.) **Maximum Overhang Clockwise) Speed) Cont. Static (in.-lb.) Starter CC 1.0 2300 10,000 180 Generator C 1.5 100 300 183 Generator (opt. S3H1-G) C 2.0 140 900 183 (Std. R-1340-59) Fuel pump CC 1.0 150 450 10 Aux. accessory CC 1.0 *150 450 10 Tachometer R.H. C .5 15 45 10 L.H. CC .5 15 45 10 Goverrnor C 1.144 60 250 - Vacuum pump C 1.5 *100 300 10 *Maximum combined drive load of vacuum pump and fuel pump must not exceed 150 in.-lb. **Maximum allowable accessory moments in in.-lb., provided no destructi ve accessory drive or mounting pad forces resulting from accessory vibration are present. Early Wasp engines incorporate tongue and groove vacuum and fuel pump drives. All later engines have spline type drives. NOTE 4. (a) Ratings are based upon the best power mixture strength and 450°F cylinder head temperature. (b) With the use of grade 91/96 fuel, the following ratings may be used: Maximum continuous, hp, rpm, in.Hg., at: Critical altitude (ft.) 550-2200-33.0-4500 Sea level pressure altitude (ft.) 550-2200-34.0-S.L. Takeoff (one minute), hp, rpm, in.Hg., at: Critical altitude (ft.) 600-2250-36.0-2300 Sea level pressure altitude (ft.) 600-2250-36.5-S.L. NOTE 5. Deleted February 1, 1974. NOTE 6. Eligible with rear crankcase section fabricated from aluminum alloy instead of magnesium alloy at a weight increase of 12 lbs. NOTE 7. R-1340-59 is the same as S3H1-G except for carburetor setting and dry weight. .....END.....