# TCDS TC 5E-2: Pratt & Whitney Division - Type: Type certificate data sheet - Status: Current - Holder: Pratt & Whitney Division - Revision: 0 - Product: Engine - Data sheet PDF: https://openairdocs.org/files/sha256/a9/7c/a97ce912786a8556d55b9f52e36a438d67d4b856e72c69961cf320ad3c360e96 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/557844629A50A6388525676A006740C9.0001 - Page: https://openairdocs.org/tcds/TC%205E-2 ## Models (1) As the data sheet lists them. - Military R-1340 Series ## What the data sheet says This is OCR from the scanned FAA data sheet. OCR can misread letters and numbers. ```text MODEIS: Pratt & Whitney Millrary Models R-1340 series 1,C. NUMBER: 5E-2 Military model SR-1340-E R-1340-19 R-1340-22 R-1340-29 R-1340-36, R-1340-AN-2 R-1 340-51M1. -40,-47,-49, Type - 9RA Direct drive Geared 3: 2 Direct drive 13: 2 for -53 only) Corresponding certif- icated wasp model S1D1 -53 None None S3H1 S3H1G S1H2 Ratings: hp, Ipm. Critical altitude in.Hg.. at: 550-2200- ERFERR (It.) 33-5000 542-2200- -33-S.L. 550-2200- 34 Fuel 80 octane aviation 5.75 × 5.75 1344 weight 6:1 715 5437:1 (See NOTE 5) (See NOTE 5) (See NOTE 5) SAE No. 30 40 30 40 Carburetor 10:1 NA-YSC 14:1 NA-Y7B NA-Y9B NA-Y 9E1 12: 1 NA-Y9E1 VAG-9D VAG-9 Scintilla SBORN S B9 -RN-4 magnetos SB9R or Bosch SB9RU2 Ignition timing, degrees BTC 27 25 25 Hydraulic propeller None IWO Constant TWO Non e provision position speed position (except for - 4911) NOTE 1. Maximum permissible temperatures are as follows: Cylinder head cylinder barrei 2il inlet R-1340-E, - 19. - 36. -49M1 -51, - 51M 129 5o degrees F 35 degrees F 200 degrees F R-1340-24, - 35 degrees F 200 degrees F NOTE 2. Pressure limits - normal operation: Maximur Minimum oil pressure Fuel fressure 90 psi 6 psi. 73 psi. psi. NOIE 3. The following accessory drives are provided: Direction of Rotatior. Speed Ratio Maximum Maximum** (Clockwise or Torque (in. ibs.) Over hang Counter-Clockwise) Crankshaft Speed) Continuous (in. 1bs.) Starter cc 2300 10000 180 100 300 183 Generator (optional) 150 900 183 Fuel pump 450 10 Auxiliary Accessory 1. 0 150* 450 10 Tachometer R.H. L.H. cc 10 Vacuum pump c 100* 300 10 Early wasp engines incorporate tongue and groove fuel and vacuum pump drives. when incorporated in certificated aircraft, the engine name-plate should re stamped, "CAA 3pec. No. 5E-2." thin metal plate attached beneath he exist eaten are tate i the forman me be stand or dain this information on the When a new model designation is required because of changes to the engine, the new designation should be added to the name-plate. NOTE 5. The following engines incorporate the additional detailed characteristics: Similar Certificated R-1340 Model wt. dry, 1ts. Characteristics - 36 865 1bs. with magnesium S3H1 Incorporates spline type vacuum and fuel pump rear section eligible at the 550 Ihp rating 878 1bs. with aluminum maximum continuous and take-off with 80 octane rear section able, the next higher grade 91/96 should te fuel. when the 80/87 grade fuel is not avail- used with the 600 khp rating. -40 865 1bs. with magnesium S3H2 Similar to -36 except dry weight. Engine is rear section designed for operation with the crankshaft in 878 1ks. with aluminum a position approximately 45 degrees to the horizontal in helicopters. This has beer. accomplished ty a means of a special carturetor adapter and revisions to the engine lubricating system. Only the forged nose case, P/N 37902, is to be used on the helicopter engines. -47 865 1bs. with magnesium S3H1 Similar to -36 except engines incorporates tongue rear section type vacuum and fuel pump drives. 878 1bs. with aluminum rear section -49 865 lbs. with magnesium S3H1 Similar to -36. rear section 878 1bs. with alumirum rear section -49M1 865 1bs. with magnesium S3H1 Similar to -36 ard -40 except for dry weight. rear section 878 its. with alumirum rear section -51 865 lbs. with magnesium S3H1 Similar to -36. rear section 878 1ts. with alumirum rear section - 5141 865 1bs. with magnesium S1H2 Similar to -36 except with 12:1 ratio flower. rear section 878 1bs. with alumirum rear section S1H1-G Similar to -AV-2 except with 12:1 ratio blower. 868 S1H2 Similar to -40 except for dry weight and 12:1 ratio blower. -AN-1 865 lbs. with magnesium S3H1 Similar to -36 except engine No. P326794 modified rear section to included (1) 12:1 ratio tlower parts used in 878 lbs. wtth aluminum Civil wasp S1H1 engines, (2) provision for rear section hydromatic propeller, (3) the S1H1 caburetor settings, and is similar to the S1H1 model and has the same ratings as the -AN-2 Similar to -36, except for dry weight. NOTE 6. The following spark plugs are approved on these engines: HSR-86; Autolite SH-2K, 390, 2239N, - 2039, 2215E, "1750025 ``` ## ADs (3, in force first) - [AD 99-11-02](https://openairdocs.org/ad/99-11-02): Cylinders Inspections · Pratt & Whitney Division Military R-1340 Series, Wasp R-1340-59, Wasp R-1340-61 and 7 more. Effective Jul 19, 1999 - [AD 96-15-02](https://openairdocs.org/ad/96-15-02): Crankshaft counterweight · Pratt & Whitney Division Military R-1340 Series, Wasp S1H1, Wasp S1H1-G and 2 more. Effective Aug 12, 1996 - [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 (3) - [STC SE04651CH](https://openairdocs.org/stc/SE04651CH): To allow use of l00R grade aviation fuel meeting Swift Fuel, LLC specification SPEC-l00R-22. Swift Fuels LLC - [STC SE5189NM](https://openairdocs.org/stc/SE5189NM): Installation of chip detector light system.. A & L Aircraft Parts Inc - [STC SE01200LA](https://openairdocs.org/stc/SE01200LA): Installation of Pratt & Whitney R-2800 engine cylinder assemblies on altered P&WA R-1340 engine models. Aircraft Cylinder & Turbine 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.