# TCDS E-265: Neptune Aviation Service Inc. - Type: Type certificate data sheet - Status: Current - Holder: Neptune Aviation Service Inc. - Revision: 9 - Revised: August 8, 2012 - Product: Engine - Certification basis: CAR 13 - Registered aircraft: 2, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/d9/c7/d9c7b42b83c5fb64aa0367e8d65db1993601301e4159fb7737b2f774ffa70aad - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/94DED2C51637150486257A54005C823C.0001 - Page: https://openairdocs.org/tcds/E-265 ## Models (4) As the data sheet lists them. - J34-WE-34 - W-340 - J34-WE-36 - 24C4D-1 ## What the data sheet says From the PDF's text layer, line by line; tables lose their columns. The PDF is the record. ```text Page No. 1 2 3 Rev. No. 9 8 8 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E-265 Revision 9 Westinghouse 24C4D-1 J34-WE-34 J34-WE-36 W-340 August 8, 2012 TYPE CERTIFICATE DATA SHEET NO. E-265 Engines of models described herein conforming with this data sheet (which is a part of type certificate No. E-265) and other approved data on file with the Federal Aviation Administration meet the minimum standards for use in certificated aircraft in accordance with pertinent aircraft data sheets 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. Type Certificate Holder Neptune Aviation Services, Inc. 2 Corporate Way Missoula, Montana 59808 Type Certificate Holder Record Neptune, Inc. 5225 Hwy 10 West, Box 17 Missoula, MT 59802 Steward-Davis, Inc. 3200 Cherry Avenue Long Beach, California Model 24C4D-1 J34-WE-34, -1, -2 W-340, -1, -2 Type - Turbojet Axial flow, eleven stage compressor; double annular combustion chamber, two stage turbine - - - - Ratings Maximum continuous static thrust, lb., rpm, at sea level 2650 - 11800 - - 3000 - 12000 Takeoff static thrust (5 minutes), lb., rpm, at sea level 3250 - 12500 - - 3400 - 12500 Fuel control Holley B5805 - - Holley PB5805 Fuel Aviation gasoline (MIL-F-5572) Aviation gasoline (MIL-F- 5572) JP-3 (MIL-F-5624) - - - - Oil (MIL-O-6801) grade 1010 - - - - Principal dimensions Length overall, in. 120 (with exhaust nozzle) - - 111.5 (less exhaust nozzle) Height, in. 35.2 - - - - Weight (dry), lb. (with single lever control, all accessory drives, engine lubrication systems, but less generator, hydraulic pump and tachometer generator) 1233 1233 1184 C.G. location fwd of rear engine mount, in. 11 11 8 Ignition Two igniter (P/N 62G488) and two ignition coils (P/N 23F856) - - Scintilla TLN-10 ignition and two igniters (P/N 64G876) or Scintilla TLN-10 ignition unit and two igniters (P/N 64G876) NOTES 1,2,3,4,5,6,7,11 1,2,3,4,5,6,7,8,9,10,11 1,2,3,4,5,6,7,10,11,12,13 "- -" indicates "same as preceding model." "—" indicates "does not apply.' Certification basis Regulations & Amendments Model Date of Application Date Type Certificate No. 265 Issued CAR 13 effective 8-1-41 as amended by 13-1 24C4D-1 4-28-50 5-19-50 CAR 13 effective 6-16-56 W-340 (J34-WE-36) 4-18-55 8-10-56 CAR 13 effective 6-15-56 as amended by 13-1, 13-2, , 13-3 J34-WE-34 4- 3-58 9-19-60 NOTE 1. Maximum permissible temperat ure limits: Model Model Model Measured exhaust gas temperatures 24C4D-1 J34-WE-34 W-340 Takeoff 1260°F* 1260°F* * Maximum continuous 1175°F* 1175°F* * Oil inlet temperature 190°F 190°F 210°F Turbine inlet temperature 1490°F 1490°F 1525°F *Each W-340 engine and any engine model having Engine Bulletin No. 294 incorporated will have individual turbine outlet temperature maximum va lues corresponding to the maximum turbine inlet temperature for takeoff on a 100°F. day. Ma ximum continuous power is obtained at maximum continuous rpm with the exhaust nozzle set for a 100°F. day and the gas outlet temperature resulting, although this temperature will be lower than at takeoff. NOTE 2. Fuel and oil inlet pressure limits: 24C4D-1 J34-WE-34 W-340 Fuel: Minimum at fuel line connection to engine 10 p.s.i.g. - - - - Operating fuel inlet gage pre ssure 20 ± 10 p.s.i.g. - - - - Oil: Minimum at oil line connection to engine 4 p.s.i.a. - - - - Operating oil gage pressure 20 - 170 p.s.i. - - 120 ± 35 p.s.i. 20 p.s.i. (idle) "p.s.i.a." means lb. per sq. in. absolute "p.s.i.g." means lb. per sq. in. gage NOTE 3. The engine ratings are based on static sea level conditions of 59°F, 29.92 in. Hg. and dry air using no air bleed or power to drive aircraft acce ssories, with limiting gas temperatures as in Note 1, and jet nozzle sizes as follows: 24C4D-1, J34-WE-34 W-340 173 ± 5 sq. in. tabbed to size corresponding to 1490°F. or T.O. turbine inlet temperature on a hot day (100°F). 185 ± 5 sq. in. tabbed to size corresponding to 1525°F. for T.O. turbine inlet temperature on a hot day (100°F.) NOTE 4. The following accessory drive provisions are available: Rotation* Speed (Ratio to Turbine) Cont. Torque (in.-lb.) Static Torque (in.-lb.) Maximum Overhang (in.-lb.) Starter (W-340) C 1.0 ** 6000 300 Starter (24C4D & J-34-WE34) C 1.0 470 5400 300 Generator (W-340) C .667 500 2200 400 Generator (24C4D & J-34-WE34) C .669 500 2200 400 Hydraulic pump (W-340) CC .264 2500 75 Hydraulic pump (All) CC .264 600 1650 75 Hydraulic pump (W-340) CC .667 35 600 75 Tachometer (24C4D & J34-WE34) CC .3364 7 50 Tachometer (W-340) CC .3364 15 70 *C - Clockwise; CC - counter clockwise **1200 in.-lb. at 1500 rpm NOTE 5. All models are equipped w ith Type E-2 electric starter at the additional weight of 41 lb. NOTE 6. Models 24C4D and J34-WE-34 have no provisions for anti-icing the engine inlet and are not approved for use in icing conditions. Model W-340 is satisfactory for operation in icing conditions. NOTE 7. These engines must be installed with suitable compressor section external armor to preclude possible secondary damage in the event of compressor blade failure. NOTE 8. The use of 5% alcohol in fuel is approved for the J34-WE-34 engine. NOTE 9. Military model J34-WE-34 engines produced by the Aviation Gas Turbine Division, Westinghouse Electric Corporation and built to Westinghouse Pa rts Lists 58J59-1, -2, -3, -4, -6, -9, -11, -14, and -17 are eligible. Engines built to Westinghouse Parts Lists 43J745-2 and -3 are eligible if modified to the 58J59-1 configuration by incorporating the engine bulletins listed in Table II, Setion II of T.O. AN 02B-110ABA-3 dated 1 April 1957. All J34 models must have Engine Bulletins 124 and 129 incorporated. NOTE 10 The J34-WE-34-1, J34-WE-36-1 and the W340-1 engines incorporate Steward-Davis accessory gear box drive shaft SDD-472. The -2 engines incorporate Steward-Davis accessory gear box drive shaft SDD-410A. NOTE 11. These engines must comply with Steward-Da vis, Inc. Service Bulletin No. 215 Revision "A" dated August 1, 1964, or later FAA approve d revision, before eligible for installation on certificated aircraft. NOTE 12. The model W-340 engine is de fined by Westinghouse Drawing 103T850. NOTE 13. Military model J34-WE-36 engines produced by the Aviation Gas Turbine Division, Westinghouse Electric Corporation and built to Westinghouse Parts List 58J300-24 are eligible with the same ratings and limitations which apply to the civil model W-340. ....END..... ``` ## ADs None name its models. ## Registered aircraft by registry model (OpenAirDocs) - [Anzani W-3](https://openairdocs.org/engine/anzani-w-3-series): 2 aircraft (registry code 04702) - [Westinghse 24C4D-1](https://openairdocs.org/engine/westinghse-24c4d-1): 0 aircraft (registry code 65501) - [Westinghse J34-WE-34](https://openairdocs.org/engine/westinghse-j34-we-34): 0 aircraft (registry code 65503) - [Westinghse W-340](https://openairdocs.org/engine/westinghse-w-340): 0 aircraft (registry code 65506) --- 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.