# TCDS E-249: DeVore Aviation Corporation - Type: Type certificate data sheet - Status: Current - Holder: DeVore Aviation Corporation - Revision: 19 - Revised: October 12, 1972 - Product: Engine - Certification basis: CAR 13 - Data sheet PDF: https://openairdocs.org/files/sha256/25/fa/25fa51a4ac8725cd9d5c5fda897cf2a575cf62ae30336d71146a66192e3e99bb - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/3777FAF966B2A6DC8525670C00504B1A.0001 - Page: https://openairdocs.org/tcds/E-249 ## Models (1) As the data sheet lists them. - 15KS-1000-A1 ## 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. 2 Rev No. 19 19 Reformatted 12/93. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E-249 Revision 19 DEVORE 15KS-1000-A1 12 October 1972 TYPE CERTIFICATE DATA SHEET NO. E-249 Engines of models described herein conforming with this data sheet (which is part of Type Certificate No. 249) 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/ Federal Aviation Regulations, provided they are installed, operated and maintained as prescribed by the approved Type Certificate holder's manuals and other approved instructions. Type Certificate Holder DeVore Aviation Service Corp. Roslyn Heights, New York 11577 Model 15KS-1000-A1 Type Cylindrical case, self-contained, solid propellant, reloadable, electrically fired Thrust characteristics (nominal value) Temperature of Propellant -65°F (-53.9°C) 60°F (15.5°C) 140°F (60°C) Thrust lb. 815 1062 1320 Duration, second 18.0 14.0 11.5 Ignition lag, second 0.21 0.11 0.09 Nominal Rated Thrust, Lb. at sea level and 35°F propellant temperature 1,000 Nominal Rated Impulse lb.-second 15,000 Maximum usable Impulse, lb.-second 14,400 Temperature Range Operating -75°F (-59.4°C) to 140°F (60°C) Storage -75°F (-59.4°C) to 160°F (71.1°C) Altitude Limit Operating 42,000 ft. above mean sea level Storage 35,000 ft. above mean sea level Fuel (Propellant) Solid Aeroplex AN-583AF - smokeless Ignition Recommended Current 25 ampere at 12 or 24 volt Duration of Interval 0.5 second maximum Principal Dimensions of Case, in. Diameter 10.30 Length, over-all 33.45 Weights, Lb. Loaded (charged) 144 Empty (expended) 72 Notes 1 through 7 E-249 2 Certification basis: Engine Model Application Date TC E-249 Cancelled CAR 13 effective 1 August 1941 12AS-1000D-5 - 13 September 1946 and special conditions Rocket Engine Type Certificate ER-1 12AS-1000D-5 - 15 October 1947 Rocket Engine Type Type Certificate No. Certificate ER-1 E-249 issued to cancelled replace Rocket Engine Type Certificate ER-1 14AS-1000D-5 - 8 October 1948 12AS-1000D-5 cancelled and redesig- nated 14AS-1000D-5 14AS-1000D-5 - cancelled 5 July 1955 14AS-1000-G1 2 April 1953 cancelled 5 July 1955 CAR 13 effective 5 March 1952 15KS-1000-A1 24 June 1955 5 July 1955 CAR 13-1 effective 16 May 1953 (Navy Desig. CAR 13-2 effective 18 May 1954 Mark 6 Mod 1) and special conditions consisting of tests described in Aero-Jet- General Corporation Letter No. 300-3905 dated 15 December (Deleted Navy 1954 to the Bureau of Aeronautics, Designation U.S. Department of the Navy 26 June 1964) Production basis: None NOTE 1: Engines and igniters shall only be rebuilt by the Type Certificate holder or his authorized sources. NOTE 2: All 15KS-1000-A1 JATO installations are to be basically in accordance with the engineering criteria in Aerojet-Bristol-DeVore Report No. 981. Each new type installation shall be reviewed and concurred in by DeVore or its authorized representative and approved by the Federal Aviation Administration or by the Civil Aviation Authority of the country involved. NOTE 3. Maximum storage period is four years from stenciled shipping date. Temperature storage limits are -75°F (-59.4°C) minimum, 160°F (71.1°C) maximum. NOTE 4. 15KS-1000-A1 rocket engines may be carried on an aircraft ready for operation for a maximum of 1000 hours cumulative flying time or 24 months, whichever occurs first; however, this maximum may be extended up to 1600 hours provided that the increases are in increments and are accomplished in accordance with procedures approved by the Chief, Aircraft Engineering Branch, FAA Eastern Region. These allowances are in addition to the four year storage period. NOTE 5. It is suggested that the rocket engines be fired just prior to normal removal, for time, for pilot familiarization and checkout. NOTE 6. The "Temperature of Propellant" is the temperature of the propellant mass. This temperature approximates the average of the temperatures to which the rocket engine has been exposed in the previous 24-hour period. NOTE 7. Thrust and Impulse of this rocket engine increase slightly with increase in altitude. See 15KS-1000-A1 and 15KS-1000-A1(B) Aircraft Rocket Engines Operation and Service Instructions, STM-159 Revised. ....END.... ``` ## ADs None name its models. --- 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.