TCDS E-129

Page No. 1 2 Rev No. 8 8 Reformatted 11/93. FEDERAL AVIATION ADMINISTRATION E-129 Revision 8 Pratt & Whitney Wasp S1H1 S1H1-G S1H2 S1H4 S1H5-G (See Note 11) S3H2 R-1340-61 February 1, 1974 AIRCRAFT ENGINE SPECIFICATION No. E-129 Engines of models described herein conforming with this specification and approved data on file with the Federal Aviation Administration 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 S1H1, S1H2 S1H4 S1H1-G R-1340-61 S3H2 Type 9RA Direct drive - - 3.2 reduction gearing - - Direct drive Rating (Impeller gear ratio) 12:1 - - - - - - 10:1 Maximum continuous hp, rpm, in.Hg., at: Critical altitude (ft.) 550-2200-33.0-8000 - - - - - - 550-2200-32.5-5000 Sea level, pressure altitude 550-2200-35.0-S.L. - - - - - - 550-2200-34.0-S.L. Takeoff (five minutes), hp, rpm, in.Hg. 660-2250-36.5 - - - - - - 600-2250-36.0 (See NOTE 10) Fuel (Minimum grade av. gas) 80/87 - - - - - - - - Lubricating oils 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), lbs. 865, 868 879 930 950 878 Propeller shaft, SAE No. 40 - - - - - - - - Carburetion Stromberg NA-Y9E1 carburetor - - - - - - - - Ignition, dual Scintilla SB9-RN-4 magnetos - - - - - - Scintilla SB9R Ignition timing, °BTC 25 - - - - - - - - Spark plugs See P&WA Service Bulletin No. 1175 - - - - - - - - NOTES 1, 2, 3, 4, 5, 6, 7, 10 1, 2, 3, 5, 7 1, 2, 3, 4, 6, 10 1, 2, 3, 6 1, 2, 3, 5, 7 "- -" indicates "same as preceding model." "__" indicates "does not apply." NOTE 1. Maximum permissible temperatures are as follows: Cylinder Head (Well type thermocouple) Cylinder Barrel Oil Inlet 500°F 335°F 200°F E-129 Page 2 NOTE 2: Fuel and oil pressure limits: Fuel pressure (psi) 3-6 Oil pressure (psi) 70-90 Except R-1340-61, 3-5 NOTE 3. The following accessory drives are provided: Direction of Speed Ratio Maximum Torque Rotation (Clockwise (Times crank- (in.-lb.) **Maximum overhang or Counter-clockwise) shaft speed) Continuous Static (in.-lb.) Starter CC 1.0 2300 10000 180 Generator C 1.5 100 300 183 Generator (opt) C 2.0 140 500 183 (Except R-1340-61) 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 Governor C 1.144 60 250 - - Vacuum Pump C 1.5 *100 300 10 *Maximum combined drive load of Vacuum Pump must not exceed 150 in. lb. **Maximum allowable accessory moments in inch pounds, provided no destructive accessory drive or mounting pad forces resulting from accessory vibration are present. Early Wasp Engines incorporate tongue and groove fuel and vacuum pump drives. All later engines have spline type drives. NOTE 4. Eligible with an automatic power and mixture control with the NA-Y9C carburetor at a weight increase of 12 lbs. NOTE 5. Incorporates both 9th and 4-1/2 order dynamic dampers. NOTE 6. Eligible with rear crankcase section fabricated from aluminum alloy instead of magnesium alloy at a weight increase of 13 lbs. NOTE 7. The S1H2, S3H2 and S1H4 engines are approved for helicopter application and operation. The S1H2 and S3H2 differ principally from the S1H1 in having a modified lubrication system and a new carburetor adapter. These modifictions were made in order to enable these engines to operate properly when mounted at an upward angle of 45° from the horizontal position. The S1H4 engine is the same as the S1H2 engine except that it incorporates the oil scavenging provisions of the R-1340-55 engine and a carburetor elbow to permit operation in a vertical attitude. R-1340-61 is the same as S1H1-G except for dry weight. NOTE 8. Deleted April 16, 1959. NOTE 9. Deleted February 1, 1974. NOTE 10. (a) Ratings are based upon the best power mixture strength and 400°F cylinder head temperature. (b) A takeoff manifold pressure at 38.0" Hg. may be used with grade 91/96 fuel for S1H1 and S1H1-G engines. NOTE 11. The approval for Models S1H2-G and S1H5-G has expired. None of these engines were manufactured. -- END --