European Aviation Safety Agency EASA TYPECERTIFICATE DATA SHEET Number: E.219 Issue : 01 Date : 09 January 2013 Type : series engines s B BS List of effective Pages: Page 1 2 3 4 5 6 Issue 1 1 1 1 1 1
TCDS E.219 series engines page 2/6 Issue 01, 09 January 2013 s:, B, BS,, Intentionally left blank
TCDS E.219 series engines page 3/6 Issue 01, 09 January 2013 s:, B, BS,, I. General 1. Type / s /, BS,, 2. Type Certificate Holder Kleinmotoren GmbH Stuttgarter Straße 41 71069 Sindelfingen Germany EASA ADOAP: AP 136 3. Manufacturer Kleinmotoren GmbH Stuttgarter Straße 41 71069 Sindelfingen Germany 4. Certification Application Date 02 June 1982 Note: The application was made to LBA Germany before EASA had been established according to German national procedures. 5. Certification Date 02 June 1983 EASA TCDS replaces LBA TCDS 4603. II. Certification Basis 1. Airworthiness Standards JAR22 Change 2 September 13. 1982, Subpart H 2. Special Conditions 3. Deviations 4. Equivalent Safety Finding 5. Environmental Protection Requirements: (not required for piston engines) III. Technical Characteristics 1. Type Design Definition Type Design Definition in accordance with parts list 20 00 350 of 10 August 1987 for B, also applicable for (*)
TCDS E.219 series engines page 4/6 Issue 01, 09 January 2013 s:, B, BS,, (*) = or l ater approved revisions 2. Description Twostroke, twocylinder aircooled inline engine with contactless magneto ignition. Displacement: 431 cm³ Bore / stroke: 70mm / 56mm * B and BS** * Compression ratio 1:10 1:10 1:12 1:12 Gear ratio 1:2,1 1:2,3 1:1,56 Starter SJCE Mod. 102 SJCE Mod. 101 Or Or United Tech. United Tech. 107728Mo 30 sm SMH12A 104 Generator Ducati 435.03.0600 Fuel Pump Bing 80203A * no throttle control, no engine starter, no generator; ** no fuel pump; see also VI, No. 5. 3. Equipment As stated in the type definition parts list. 4. Dimensions B and BS Bing 80203A Bing 80203A Overall Length mm 480 405 472 620 Overall Height mm 383 506 575 524 Width mm 216 290 259 240 5. Dry Mass Mass kg complete with exhaust system B and BS 17 26 25 23,5 6. Ratings (*with muffler) Takeoff Power 19,6 (*15,3) KW at 5500 rpm Max. Continuous Power 19,6 (*15,3) KW at 5500 rpm B and BS 17 KW at 6300 rpm 17 KW at 6300 rpm 22 KW at 6500 rpm 20 KW at 6100 rpm 22 KW at 6500 rpm 22 KW at 6500 rpm
TCDS E.219 series engines page 5/6 Issue 01, 09 January 2013 s:, B, BS,, Note: The performance value specified above corresponds to minimum values defined under the conditions of ICAO or ARDC standard atmosphere. 7. Control System: The engine models, are equipped with dual diaphragm carburettors without throttle control, an additional fuel pump and a contactless magneto ignition. The engine model B is equipped with dual diaphragm carburettors and a contactless magneto ignition. For the definition of the BS see VI, No. 5. The engine model is equipped with two diaphragm carburettors, an additional fuel pump and a contactless magneto ignition. 8. Fluids: See Operation and Maintenance Manual for approved fluids. 9. Aircraft Accessory Drives: IV. Operational Limitations 1. Temperature Limits Maximum Cyl. Head Temperature* * see note 4 B and BS C 275 275 275 275 2. Maximum/ Minimum Speeds: B and BS Minimum Cont. Speed * 2000 rpm 3000 rpm * Max.Take off and Cont. 5500 rpm 6300 rpm 6100 rpm 6500 rpm Speed Maximum Speed 6500 rpm 6500 rpm 6500 rpm 6600 rpm * not possible, no throttle control 3. Pressure Limits: Fuel supply pressure min. 0,2 bar; max. 0,4 bar. 4. Oil Consumption and Capacity Limits: See engine manual V. Operational and Service Instructions Manual for the engine (Handbuch für den Motor) Type 01, Issue 1 24.05.1983 (*) B and BS Type B, Issue 1 20.08.1987 (*) Type C, Issue 1 27.04.1989 (*) Type, Issue 1
TCDS E.219 series engines page 6/6 Issue 01, 09 January 2013 s:, B, BS,, (*) = or later approved revisions 30.07.2001 (*) VI. Notes 1. The manufacturer documents recorded in this TCDS are binding in the specified issue or later approved revisions. 2. The suitability and allowable operating ranges of an engine for use in a specific aircraft/propeller combination are to be demonstrated during the aircraft certification. 3. For the permitted engine operating hours refer to the relevant operating instructions. 4. The maximum permissible Cylinder Head Temperature was increased to 275 C for all models with a Nonsignificant major change, EASA approved 21. September 2005, Nr. EASA.E.C.01026. 5. B: The deviations of the BS are defined as follows: The engine model BS is equipped with a single float type carburettor and a contactless magneto ignition. 1. Operational limitations Takeoff Power: 17 KW at 5500 rpm Max. Continuous Power: 17 KW at 5500 rpm Maximum Speed: 6500 rpm Minimum Cont. Speed: 2000 rpm 2. Equipment Fuel pump: Bing 80203A Carburettor: Bing 842 The width is increasing to 405 mm. All other technical data is identical to the model solo B. Operating instructions: engine manual BS, Issue 1, 12.06.1991 (or later approved revisions). Both models are used for pusherconfiguration engine installations only.