TCDS E-247

Page No. 1 2 3 Rev No. 8 8 8 FEDERAL AVIATION AGENCY E-247 Revision 8 PRATT & WHITNEY Wasp Major TSB3-G VSB11-G (See NOTE 5) B5, B6, B7, B13, CB2, B14 March 21, 1960 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 aproved manufacturer's manuals and other approved instructions. Manufacturer Pratt & Whitney Aircraft Division of United Aircraft Corporation East Hartford, Connecticut Model Wasp Major TSB3-G B5 CB2 B6 Type 28EA, reduction gearing .375:1 - - - - - - Rating (Also see NOTE 9) (With low imp. gear ratio) 6.375:1 - - - - - - Max. continuous, ip, rpm, in.Hg., at: Critical alt. (ft.) 2800-2550-53.0-1200 2850-2550-54.0-300 - - 2650-2550-50.0-2800 Sea level press. alt. 2800-2550-53.5-S.L. 2850-2550-54.5-S.L. - - 2650-2550-50.5-S.L. Takeoff (5 min.), hp, rpm,in.Hg., at: (dry) - - - - - - Critical alt. (ft.) (app. 1000 ft. below S.L.) - - - - 3000-2700-56.0-1300 Sea level press. alt. 3250-2700-60-0 S.L. - - - - 3000-2700-56-0-S.L. (with anti-det. inj.) Critical alt. (ft.) (app. 1500 ft. below S.L.) - - - - 3250-2700-56.5-500 Sea level pressure, altitude 3500-2700-60.0 S.L. - - - - 3250-2700-56.5-S.L. (With high imp. gear ratio)     Max. continuous, hp, rpm, in.Hg., at: Critical alt. (ft.)     Fuel (min. grade aviation gasoline) 108/135 - - - - 100/130 Lubricating oils See P&WA Service Bulletin No. 1183 - - - - - - Bore and stroke, in. 5.75 X 6.00 - - - - - - Displacement, cu. in. 4363 - - - - - - Compression ratio 6.70:1 - - - - - - Weight (dry), lbs. 3450 3584 3670 3450 Center of gravity location (dry) Fwd of rear face of blower suction, in. 29.3 29.0 - - 29.3 Above propeller shaft C.L., in. 0.0 - - - - - - Propeller shaft, SAE No. 60A - - - - - - Carburetion Stromberg PR-3008-3 - - - - - - Ignition, dual 7 Scintilla D4NM-2 high tension eng. 4 Scintilla S14NM-15 low tension eng. - - 7 Scintilla D4NM-2 high tension eng. Ignition timing, °BTC 20 - - - - - - (20° manual cruise) - - - - (25° manual cruise) Spark plugs See Note 10 - - - - - - NOTES 1,2,3,4,6,7,8,10 1,2,3,4,6,7,8,10 1,2,3,4,6,7, 8,9,10 1,2,3,4,6,7,10 "- -" indicates "same as preceding model." "" indicates "does not apply." E-247 2 Model Wasp Major B7 B13 B14 Type 28EA, reduction gearing .375:1 .425:1 - - Rating (With low imp. gear ratio) 6.375:1 6.95:1 - - Max. continuous, ip, rpm, in.Hg., at: Critical alt. (ft.) 2650-2550-50.0-2800 2650-2550-49.5-6500 - - Sea level press. alt. 2650-2550-50.5-S.L. 2650-2550-51.0-S.L. - - Takeoff (5 min.), hp, rpm,in.Hg., at: (dry) - - - - Critical alt. (ft.) 3000-2700-56.0-1300 3250-2700-60.0-2200 3250-2700-61.0-1700 Sea level press. alt. 3000-2700-56.0-S.L. 3250-2700-60.5-S.L. 3250-2700-61.5-S.L. (with anti-det. inj.) Critical alt. (ft.) 3250-2700-56.5-500 3500-2700-60.5-1300 3500-2700-61.5-3000 Sea level pressure, altitude 3250-2700-56-5-S.L. 3500-2700-60.5-S.L. 3500-2700-62.0-S.L. (With high imp. gear ratio)  9.07:1 - - Max. continuous, hp, rpm, in.Hg., at: Critical alt. (ft.)  2300-2550-50.0-18300 2300-2550-52.5-10000 2000-2550-43.5-23850 2000-2550-46.5-10000 Fuel (min. grade aviation gasoline) 100/130 115/145 108/135 Lubricating oils See P&WA Service Bulletin No. 1183 - - - - Bore and stroke, in. 5.75 X 6.00 - - - - Displacement, cu. in. 4363 - - - - Compression ratio 6.70:1 - - - - Weight (dry), lbs. 3584 3555 - - Center of gravity location (dry) Fwd of rear face of blower suction, in. 29.0 27.8 - - Above propeller shaft C.L., in. - - - - - - Propeller shaft, SAE No. 6OA - - - - Carburetion Stromberg PR-3008-3 - - Ignition, dual 4 Scintilla S14RN-15 low tension eng. 7 Scintilla D14RN-2 high tension eng. - - Ignition timing, °BTC (25° manual cruise) (20° manual cruise) - - (manual or normal??) Spark plugs See NOTE 10 - - - - NOTES 1,2,3,4,6,7,10 1,2,4,5,10 - - "- -" indicates "same as preceding model." "" indicates "does not apply." Certification basis Type Certificate No. 247 Production basis Production Certificate No. 2 NOTE 1. Maximum permissible cylinder head, barrel, and oil inlet temperatures, 480 °F, 325°F, and 212 °F, respectively, except CB2 which has maximum permissible cylinder head temperature of 510 °F. The cylinder head temperature is measured wit h a well-type thermocouple. NOTE 2. The following accessory provisions are available: Max. Torque (in. lbs.) Max. Overhang Rotation* Speed** Continuous Static (ibs. in.) Starter C 3.0  12000 300 Generator (3 provided) C 3.0 500 2200 350 Fuel pump CC .80 50 600  Propeller governor (B13 only) CC .956 125 825  Propeller governor (B3-0, B5) CC .984 125 1300  Propeller governor (B6, B7, CB2 & modified B3-G***) CC .964 125 825  Power takeoff (on rear face and is optional) C 3.0 1500 5400 75 *C - Clockwise, viewing pad. CC - Counter clockwise, viewing pad. **Speed - Times crankshaft speed. ***Applies only to TSB3-G engines incorporating strengthened pinion cage hubs for use with Curtiss Electric propellers. 3 E-247 NOTE 3. The TSB3-G, B5, B6, B7 and CB2 engines are eligible for use with a turbosupercharger. Accordingly, the ratings listed above are based on 100 °F carburetor air temperature with 31 in.Hg. exhaust back pressure for sea level ratings and standard atmospheric exhaust back pressures for altitude ratings. To maintain "Maximum Continuous" power under conditions with higher carburetor air temperature and/or higher exhaust back pressure, the manifold pressure may be increased up to a maximum of 56 in.Hg. for the TSB3-G, B6, and CB2 and to 53 in.Hg. for the B5 and B7 to compensate for loss of power provided neither 43 in. (abs.) Hg. exhaust back pressure nor 130 °F carburetor air temperature is exceeded. NOTE 4. The takeoff rating for the TSB3-G, B5, B5, B7 and CB2 engines with anti-detonant injection is eligible when the engines are equipped with water injection regulator no. 106455. Anti-detonant fluid of 12.8 lbs/min. are required at 3500 BHP and 11.8 lbs/min. at 3250 BHP. This fluid may be composed of any of the following solutions by volume: 1. Methyl Alcohol 50%, water 50% 2. Methyl Alcohol 60%, water 40% Per Pratt & Whitney Specification 509 3. Methyl Alcohol 25%, Ethyl alcohol 25%, Water 50% 4. Methyl Alcohol 60%, water 40% anticorrosion oil 1%, per British Specification D-Eng. R.D. 2470, dated January 8, 1946. NOTE 5. Specifications formerly listed for Model VSB11-G have been omitted since all of these engines have been converted to Model B13 engines. En gines Nos. P774 to 777, P811 to 817, P916, 917, 920 to 924 differ from other B13 engines in that they incorporated originally, early design types of the following parts: Cylinder heads; main oil pump; ignition harness; intake valves; guides, washers, and cam follower rollers. NOTE 6. (a) The B5 engine is identical to the single-speed, single-stage TSB3-G engine except for the fuel used, and the power ratings. (b) The B6 engine is a conversion model from the TSB3-G, and incorporates essentiall y a new power section, nose section (including torquemeter and reduction gears), and low tension ignition system. TSB3-G cylinders, supercharger, and rear sections are retained. (c) The B7 engine is identical to the B6 engine except for the fuel used and the power ratings. (d) The CB2 engine is a further modified version of the B6 engine, incorporating "C" type cylinders with improved cooling provisions. (e) The B14 is similar to the B13 except for the fuel used and the power ratings. NOTE 7. A manifold pressure regulator may be employed at an additional weight of 12 lbs. NOTE 8. Ignition timing may be manually advanced to 28 ° BTC for cruise operation. NOTE 9. The CB2 engine is eligible for operation on grade 100/130 fuel at the following reduced ratings: HP RPM HP ALT. Maximum continuous Critical altitude 2650 2550 50.0 3000 S.L. pressure, altitude 2650 2550 50.5 S.L. Takeoff (dry) Critical altitude 3000 2700 56.0 1700 S.L. pressure, altitude 3000 2700 56.0 S.L. Takeoff (with anti-detonant injection) Critical altitude 3250 2700 56.5 900 S.L. pressure, altitude 3250 2700 56.5 S.L. NOTE 10. The following spark plugs are approved on these engines: AC 161, 171, 181, 261, 271, 281 BG 240, 245, 340, 341, 345, 346, RB19R-2, RB27R, RB27R-1, RB39R. Champion REA32N, REB32N, RHA32N, RHB32N, RHA32E, RHB32E, R37S-1, REA37N, REB37N, RHA37N, RHB37N, RHA37E, RHB37E, R56S, R111, R115 .....END.....