# TCDS E-231: Pratt & Whitney Division - Type: Type certificate data sheet - Status: Current - Holder: Pratt & Whitney Division - Revision: 11 - Revised: October 31, 1978 - Product: Engine - Data sheet PDF: https://openairdocs.org/files/sha256/e6/84/e684bd837dab5f237f0d05c7c678af7013cb85ee19a3fc5d3734d7586083c951 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/28543F501B3E3CEE8525670D0060471A.0001 - Page: https://openairdocs.org/tcds/E-231 ## Models (7) As the data sheet lists them. - Double Wasp CA5 - Double Wasp CA15 - Double Wasp CA17 - Double Wasp R2800-97 - Double Wasp CA19 - Double Wasp CA18 - Double Wasp CA3 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text "- -" Indicates "Same as preceding model." "" Indicates "Does not apply." Page No. 1 2 3 4 Rev. No. 11 11 11 11 Reformatted 11/94 FEDERAL AVIATION ADMINISTRATION E-231 Revision 11 PRATT & WHITNEY Double Wasp CA15, CA3 Double Wasp CA17, CA5 Double Wasp CA18, CA19, R2800-97 October 31, 1978 TYPE CERTIFICATE DATA SHEET NO. E-231 Engines of models described herein conforming with this specification and approved data on file with the Federal Aviation Administration are rated as airworthy for use in certificated aircraft in accordance with pertinent aircraft specifications and applicable portions of the Civil Air Regulations and Federal Aviation Regulations provided they are installed, operated and maintained as prescribed by the approved manufacturer' manuals and other approved instructions. Manufacturer Pratt & Whitney Aircraft Division of United Aircraft Corporation East Hartford, Connecticut Models Double Wasp CA15 CA3 CA17 Type 18RA 20:9 reduction gearing - - - - Rating (With low impeller gear ratio) 7.29:1 - - - - Max. cont., hp, rpm, in. Hg. at: Rated pressure altitude (ft.) 1900-2600-46.5-4900 - - - - Sea level pressure alt. 1900-2600-47.5-S.L. - - - - or 1800-2600-44.0-6500 - - - - 1800-2600-45.0-S.L. - - - - Takeoff (5 min.), hp, rpm, in. Hg. at: (dry) - - - - Critical altitude 2100-2800-52.5-3400 - - 2300-2800-58.0-700 Sea level 2100-2800-53.5-S.L. - - 2300-2800-58.0-S.L. (with anti-detonant injection) Critical altitude 2400-2800-56.0-1000 - - - - Sea level 2400-2800-56.5-S.L. - - - - (With high impeller gear ratio) 9.45:1  9.45:1 Max. cont., hp, rpm, in. Hg. at: Rated pressure alt. (ft.) 1600-2600-45.0-16200  1700-2600-48.0-14800 Low critical pressure alt. (ft.) 1600-2600-46.5-10000  1700-2600-48.5-8000 Takeoff (5 min.), hp, rpm, in. Hg. at: (with anti-detonant injection) High critical pressure alt. (ft.)   2000-2600-54.0-11000 Low critical pressure alt. (ft)   2000-2600-54.5-8000 Fuel (Min. octane aviation gasoline) Grade 100/130, 100LL - - Grade 115/145 Lubricating oils See P&WA Service - - - - Bulletin No. 1183 Bore and stroke, inches 5.75 x 6.00 - - - - Displacement, cu. in. 2804 - - - - Compression ratio 6.75:1 - - - - Weight (dry), lbs. 2360 2327 2360 C.G. location (dry) Fwd. of mounting lug rear edge, in. 11.8 - - - - Above prop. shaft C.L., in. .2 - - - - Propeller shaft, SAE No. 60A - - - - Carburetion Stromberg PR-58E-4,-5 - - Stromberg PR-58E-5 Ignition, dual (see NOTE 5) Scintilla or General Electric Ignition timing, °BTC 20 (35 in automatic or 25 manual for cruise advance) - - - - Spark plugs See NOTE 9 - - - - E-231 2 Models Double Wasp CA5 CA18, R2800-97 CA19 Type 18RA 20:9 reduction gearing - - - - Rating (With low impeller gear ratio) 7.29:1 - - - - Max. cont., hp, rpm, in. Hg. at: Rated pressure altitude (ft.) 1900-2600-46.5-4900 - - - - Sea level pressure alt. 1900-2600-47.5-S.L. - - - - or 1800-2600-44.0-6500 - - - - 1800-2600-45.0-S.L. - - - - Takeoff (5 min.), hp, rpm, in. Hg. at: (dry) - - - - Critical altitude 2300-2800-58.0-700 2100-2800-52.5-3400 2300-2800-58.0-700 Sea level 2300-2800-58.0-S.L. 2100-2800-53.5-S.L. 2300-2800-58.0-S.L. (with anti-detonant injection) Critical altitude 2400-2800-56.0-1000 - - - - Sea level 2400-2800-56.5-S.L. - - - - (With high impeller gear ratio)  9.1:1 - - Max. cont., hp, rpm, in. Hg. at: Rated pressure alt. (ft.)  1675-2600-47.0-13500 1800-2600-50.0-11500 Low critical pressure alt. (ft.)  1675-2600-49.0-8000 1800-2600-51.0-8000 Takeoff (5 min.), hp, rpm, in. Hg. at: (with anti-detonant injection) (with anti-detonant injection) High critical pressure alt. (ft.)  1900-2600-49.0-10900 2100-2600-54.0-7700 Low critical pressure alt. (ft)  1900-2600-49.5-8000 2100-2600-54.0-7700 Fuel (Min. octane aviation gasoline) Grade 115/145 Grade 100/130, 100LL Grade 115/145 Lubricating oils See P&WA Service - - - - Bulletin No. 1183 Bore and stroke, inches 5.75 x 6.00 - - - - Displacement, cu. in. 2804 - - - - Compression ratio 6.75:1 - - - - Weight (dry), lbs. 2327 2360 2360 C.G. location (dry) Fwd. of mounting lug rear edge, in. 11.8 - - - - Above prop. shaft C.L., in. .2 - - - - Propeller shaft, SAE No. 60A - - - - Carburetion Stromberg PR-58E-5 - - - - Ignition, dual (see NOTE 5) Scintilla or General Electric Ignition timing, °BTC 20 (35 in automatic or 25 manual for cruise advance) - - - - Spark plugs See NOTE 9 - - - - "- -" Indicates "Same as preceding model." "" Indicates "Does not apply." Certification basis Type Certificate No. 231 Production basis Production Certificate No. 2 NOTE 1. Maximum permissible cylinder head, cylinder barrel and oil inlet temperatures are 500°F, 350°F, and 212°F respectively. The cylinder head temperature is measured with a well type thermocouple. NOTE 2. Pressure limits - normal operation Max. Min. Fuel pressure, p.s.i. 25 21 Oil pressure, p.s.i. 100 60 3 E-231 NOTE 3. The following accessory drives are provided: Maximum Torque (in. lbs.) Max. Overhang Rotation * Speed * Continuous Static Moment, lb. in. Starter C 1.000  30000 340 Generator C 3.033 600 3000 300 Fuel pump CC 0.864 355 1380 10 Vacuum or hydraulic pumps (2 provided) C 1.400 250 2250 50 Power take-off C 1.400 1300 12000 300 Propeller governor CC 0.964 125 825  "C" - Clockwise viewing pad "CC" - Counterclockwise "Speed" - Times crankshaft speed NOTE 4. Models CA3, CA15 and CA18 are similar respectively to models CA5, CA17 and CA19 except for the fuel used, carburetor setting and power rating. All engines incorporate a built-in torquemeter. NOTE 5. The takeoff ratings using anti-detonant injection are permissible when the engine is equipped with a P&W water regulator (whose detail settings are suitable for the desired wet ratings) at an additional weight of 13 lb. ADI fluid flow is 9.2 lb. min. in low blower (2400 bhp), 7.9 lb./min. in high blower for the CA17 (2000 hp) and the CA19 (2100 hp); 7.8 lb./min. in high blower (1900 bhp) for the CA18. The ADI fluid may be composed of any one of the following solutions of volume: Methyl Alcohol 50%, water 50% ) Per Pratt & Whitney Methyl Alcohol 60%, water 40$ ) Specification 509 Methyl Alcohol 25%, Ethyl Alcohol 25%, water 50% ) Methyl Alcohol 60 parts, water 40 parts, Anticorrosion oil one part (per British Specification D-Eng. R.D. 2470, dated 1-8-46). NOTE 6. The following ignition systems are eligible: High Tension - Scintilla with one DF-18LN dual magneto, two high tension distributors and harness. - General Electric, with S18RG-PIA combined magneto-distributor units and P18HG-9 harness. Low Tension - Scintilla with one DLN-10 dual magneto, two low-tension distributors, harness, and cylinder head mounted ignition coils. Weight decrease with this system is 10 lb. NOTE 7. These engines are eligible for operation on Grade 91/96 fuel in low blower at the following reduced ratings: HP RPM MP ALTITUDE Maximum continuous 1300 2600 32.5 15,000 Maximum continuous 1300 2600 35.5 S.L. Takeoff 1350 2800 34.0 15,300 Takeoff 1350 2800 37.0 S.L. NOTE 8. Engines having the symbols "NH" following the engine serial numbers have no propeller oil transfer bearing in the nose section making it impossible to utilize a hydraulically controllable propeller. NOTE 9. The following spark plugs are approved on these engines: AC 161, 165, 171, 175, 181, 261, 265, 271, 273, 275, 281. BG 240, 245, 340, 341, 345, 346, RB19R -2, RB21R-1, RB27R, RB27R-1, RB39R. Champion C34S, R33S*, R37S-1, R56S, R103*, R111, R115, R214D, RC34S, RC35S, REA29N*, REA32N, REA37N, REB29N*, REB32N, REB37N, RHA29E*, RHA29N*, RHA32E, RHA32N, RHA37E, RHA37N, RHB29E*, RHB29N*, RHB32E, RHB32N, RHB37E, RHB37N. Lodge RS19-2R. *May be used in rear position of both front and rear rows but not in front of either row. E-231 4 NOTE 10. Engines incorporating the original CA type crankshaft with the heavyweight front damper and lightweight rear damper will be identified by having the suffix "H" added to the engine model designation listed on the nameplate. Example: Double Wasp CA15H. The CB type crankshaft with two lightweight dampers will require no change in the engine model designation for identification of the crankshaft. NOTE 11. The military R2800-97 engine is identical to the Double Wasp CA18 and is eligible for use in certificated aircraft; however, when used civilly the engine name plate should be revised to include the corresponding civil model designation and Type Certificate No. .....END..... ``` ## ADs (5, in force first) - [AD 48-22-01](https://openairdocs.org/ad/48-22-01): Water-Alcohol Injection System · Pratt & Whitney Division Double Wasp CA15, Double Wasp CA17, Double Wasp CA18 and 8 more - [AD 49-40-02](https://openairdocs.org/ad/49-40-02): Thrust Plate · Pratt & Whitney Division Double Wasp CA15, Double Wasp CA18, Double Wasp CA3 and 2 more - [AD 51-05-01](https://openairdocs.org/ad/51-05-01): Power Measurements · Pratt & Whitney Division Double Wasp CA15, Double Wasp CA17, Double Wasp CA18 and 4 more - [AD 56-03-02](https://openairdocs.org/ad/56-03-02): Derichment Valve Cover · Pratt & Whitney Division Double Wasp CA15, Double Wasp CA17, Double Wasp CA18 and 8 more - [AD 56-06-02](https://openairdocs.org/ad/56-06-02): Cylinder Flange Attaching Stud · Pratt & Whitney Division Double Wasp CA15, Double Wasp CA17, Double Wasp CA18 and 115 more ## STCs approved under this data sheet (4) - [STC SE01966WI](https://openairdocs.org/stc/SE01966WI): Use of GAMI G100UL High Octane Unleaded Avgas in spark ignition piston aircraft engines. General Aviation Modifications Inc. - [STC SE1047NE](https://openairdocs.org/stc/SE1047NE): Replacment of Pratt & Whitney intermediate supercharger shaftgears P/N's 145860 and 145861 with Windsor Aerospace P/N's WA-145860 and WA-145861, respectively.. Windsor Gear and Drive Inc - [STC SEW-8](https://openairdocs.org/stc/SEW-8): Modification to push rod housing assemblies.. National Aircraft Sales, Inc - [STC SEW-3](https://openairdocs.org/stc/SEW-3): Modification of crankshafts and reidentification according to their respective counterweight dampers.. National Aircraft Sales, Inc --- OpenAirDocs.org is an independent research project of [Contrail Labs](https://contraillabs.com/). It is not affiliated with the FAA or the NTSB. Source documents are U.S. government works in the public domain.