TCDS E00058NE

U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E00058NE TCDS NUMBER E00058NE REVISION: REVISION 4* DATE: October 11, 2016 BRP-Rotax GmbH & Co KG MODELS: ROTAX 914 F2 914 F3 914 F4 Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00058NE) 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 Federal Aviation Regulations, provided they are installed, operated, and maintained as prescribed by the approved manufacturer's manuals and other approved instructions. TYPE CERTIFICATE (TC) HOLDER BRP-Rotax GmbH & Co KG Rotaxstrasse 1 A-4623 Gunskirchen, Austria TYPE CERTIFICATE HOLDER RECORD Bombardier- Rotax GmbH transferred TC E00058NE to BRP--POWERTRAIN GMBH & CO KG on December 18, 2003 I. MODELS 914 F2 914 F3 914 F4 TYPE For models 914 F2 and 914 F4: Four cylinders, horizontally opposed, four stroke engine with turbosupercharger and electronic turbocharger control unit, reduction gear driven, liquid cooled cylinder heads, ram air cooled cylinders, dry sump pressure lubrication, vacuum pump, optional. For Model 914 F3: Instead of the optional vacuum pump, a hydraulic constant speed propeller control is mounted. RATINGS Takeoff power (5 min.): (sea level pressure altitude) (see notes 12 & 13.) Max. continuous power: (sea level pressure altitude) 84.5 kW/115 HP at 5,800 rpm 73.5 kW/100 HP at 5,500 rpm - - - - - - - - OIL pressure: Normal operating range 2.0 - 5 bar (29 to 73 psi), with maximum cold start value of 7 bar (102 psi), and minimum value of 1.5 bar (22 psi) - (see Note 2.). Max. oil-inlet temperature (° C): Max. cylinder-head temperature (° C): 130 135 - - - - - - - - Max. coolant temperature (° C) (engine type designation extended with suffix -01) 120 - - - - COOLANT temperature: Monitored via cylinder head temperature, otherwise monitored via coolant temperature for engine type designation extended with suffix -01 specification: See Note 7 for a reference to coolant specifications (ref. Operator's Manual). FUEL pressure: (see note 2) (at inlet to carburetor) Minimum: airbox pressure plus 0.15 bar (2.1 psi) Maximum: airbox pressure plus 0.35 bar (5.0 psi) Normal: airbox pressure plus 0.25 bar (3.6 psi) specification: See NOTE 5 OIL, Lubrication: Maximum capacity: 3.0 L (3.17 qts) See Note 7 for a reference to oil specifications (reference Operator's Manual). * PAGE 1 2 3 4 5 REV. 4 0 3 3 3 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" INDICATES "DOES NOT APPLY" NOTICE: ALL PAGES ARE REFORMATTED. SIGNIFICANT CHANGES, IF ANY ARE BLACK-LINED IN THE LEFT MARGIN. TCDS E00058NE PAGE 2 I. MODELS (Continued) 914 F2 914 F3 914 F4 CARBURETOR 2 x Bing constant pressure carburetors, type 64/32, main nozzle 160, cylinders 1 & 3 164, cylinders 2 & 4 FUEL PUMP 2 x Electrical Pierburg fuel pumps - Rotax P/N 996 735 IGNITION SYSTEM Ignition timing Rotax dual magneto high-voltage condenser ignition, contactless SMD type. 26° BTDC for circuit A, and 22° BTDC for circuit B. SPARK PLUGS ND X27EPR-U9, Rotax part number 897257 ALTERNATOR, external Nippondenso F3A with integrated regulator. P/N 887251 (OPTIONAL - see Note 8) GENERATOR, integrated Ducati, permanent magnet single phase generator with external rectifier regulator. STARTER Nippondenso ferrite type 12V / 0.6 kW, engagement via reduction gear and freewheel. VACUUM PUMP Airborne 211 CCW, including drive. (OPTIONAL) - see Note 9. ENGINE SPEED MEASUREMENT (rpm) Electronic tachometer connector and optional mechanical tachometer drive WEIGHT (dry) (see Note 4.) 74.7 kg (164.7 lbs) 77.4 kg (170.6 lbs) 74.7 kg (164.7 lbs) DISPLACEMENT 1211 cm3 (73.9 in3) - - - - BORE 79.5 mm (3.13 in.) - - - - STROKE 61 mm (2.40 in.) - - - - COMPRESSION RATIO 9.0 : 1 - - - - PROPELLER ROTATION CCW - - - - PROPELLER FLANGE P.C.D. 75 mm, 80 mm, and 4 inch diameter for fixed propeller P.C.D. 75 mm, 80 mm, and 4 inch diameter with drive for hydraulic gov. for constant speed propeller P.C.D. 75 mm, 80 mm, 4 inch diameter prepared for hydraulic gov. for constant speed propeller GEAR REDUCTION RATIO (crankshaft to prop) 2.4286 : 1 - - - - PROPELLER CONTROL --- adapter and drive for hydraulic constant speed propeller --- GOVERNOR (see Note 10.) --- Woodward 210 786, (Rotax P/N 886735) or McCauley type DFCU 290D17B/T2 (Rotax P/N 888507). --- OPERATING INSTRUCTIONS For models 914 F2, F3 and F4: Operator's Manual for Rotax engine type 914 F, latest revision (see Note 7. of this Data Sheet). TCDS E00058NE PAGE 3 CERTIFICATION BASIS 14-CFR, part 33, Airworthiness Standards: Aircraft Engines, effective February 1, 1965, as amended by 33-1 through 33-15, inclusive, including Federal Aviation Administration Special Condition, NPRM Doc. 24922, Notice 92-14. DATE OF DATE TC ISSUED MODEL APPLICATION OR REVISED 914 F2 February 16, 1994 December 4, 1998 914 F3 February 16, 1994 December 4, 1998 914 F4 February 16, 1994 December 4, 1998 The Austrian aviation authority, Austro Control GmbH (ACG), originally type certificated this engine. The FAA validated this product under U.S. Type Certificate Number E00058NE. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of ACG. IMPORT REQUIREMENTS To be considered eligible for installation on United Sates registered aircraft, each new engine to be exported to the United States with ACG or EASA airworthiness approval shall have a Joint Airworthiness Authority (JAA) or EASA Form 1, Authorized Release Certificate. The JAA or EASA Form 1 should state that the engine conforms to the type design approved under the U.S. Type Certificate E00058NE, is in a condition for safe operation and has under gone a final operational check. NOTES NOTE 1. Temperature Limits (maximum permissible): Cylinder head: 135oC Coolant: 120oC (for engine type designation extended with suffix -01) Oil inlet: 130oC NOTE 2. Pressure Limits: Fuel Pressure at inlet to Carburetor: 0.15 bar (2.2 psi) - minimum 0.35 bar (5.0 psi) - maximum The fuel pressure must not exceed 0.35 bar (5.0 psi) to ensure not to override the float valve in the carburetor. Oil Pressure: Normal operation: 2.0 bar - 5.0 bar (29 - 73 psi) above 3500 RPM Idling: 0.8 bar (11.6 psi) - minimum at high oil temperature Starting & warm-up: 7 bar 102 psi) - maximum NOTE 3. Accessory Drive Mounting Provisions: Accessory 914 F2 914 F3 914 F4 Rotation, facing drive pad Speed Ratio, to crankshaft Maximum Torque Overhung moment (max.) Starter * * * CW 25.25 : 1 0.5 Nm --- Alternator ** ** ** CCW 1.24 : 1 1.6 Nm --- Vacuum pump ** --- ** CCW 0.54 : 1 0.9 Nm 0.4 Nm Governor --- * --- CCW 0.54 : 1 1.8 Nm 1.04 Nm Tachometer ** ** ** CW 0.25 : 1 --- --- Water pump * * * CCW 0.87 : 1 0.5 Nm Oil pump * * * CCW 0.50 : 1 0.7 Nm --- "---" Indicates "does not apply" "*" Standard feature "**" Optional feature "CW" Clockwise "CCW" Counter clockwise TCDS E00058NE PAGE 4 NOTE 4. Engine weight is defined as the following configurations: 914F2/914F4: 74.7 kg (164.7 lbs), with ignition unit and generator, carburetor, oil tank and electric starter, engine mount, turbosupercharger and turbocharger control unit, muffler, fuel pumps and alternator, but without the radiator. 914F3: 77.4 kg (170.6 lbs), with propeller flange P.C.D. 75/80 mm / 4”, drive and adapter for hydraulic governor for constant speed propeller, governor and alternator. Alternator (external): 3.0 kg (6.61 lbs). Center of Gravity (CG): Reference the 914F Installation Manual, latest revision (see NOTE 7). NOTE 5. Fuel Specifications (see Operator’s Manual as defined in NOTE 7): • 100LL AVGAS in accordance with American Society for Testing & Materials (ASTM) D910. • Automotive gasoline, unleaded regular, minimum RON 95, in accordance with ASTM D4814. NOTE 6. Model Description: F2 Basic model; 4-stroke, 4 cylinder horizontally opposed, turbosupercharger and electronic turbosupercharger control unit, one central camshaft, push-rods, overhead valves, liquid cooled cylinder heads, ram air-cooled cylinders, dry sump forced lubrication, dual breakerless capacitive discharge ignition, two constant depression carburetors, two electrical fuel pumps, fixed pitch propeller configuration, drive output via reduction gear with integrated shock absorber and overload protection, electric starter, integrated DC generator, steel exhaust system, vacuum pump drive (optional), and external alternator (optional). F3 Same as F2, except; additional drive and adapter for hydraulic governor propeller shaft for constant speed propeller with governor installed. F4 Same as F3, except; fixed pitch propeller, prepared for installation of hydraulic governor for constant speed propeller (without drive, adapter and governor). 914 F2/3/4 engine Same as described above, except; engine temperature measurement methods have been type designation amended from CHT (cylinder head temperature) and CT (coolant temperature) to only CT extended with (coolant temperature). Therefore only the coolant temperature limit applies. For further suffix -01 details refer to Service Bulletins SB-914-047 and SB-914-049 (respectively latest revision). NOTE 7. Operating and Service Instructions: • Operator’s Manual for Rotax 914F Aircraft Engine - Part Number OM-914 (all models) • Installation Manual for Rotax 914F Aircraft Engine - Part Number IM-914 (all models) • Maintenance Manual Line for Rotax 914F Aircraft Engine - Part Number MML-914 (all models) • Maintenance Manual Heavy for Rotax 914F Aircraft Engine - Part Number MMH-914 (all models) • Overhaul Manual for Rotax 914F Aircraft Engine - Part Number OHM-914 (all models) • Overhaul Manual Appendix for Rotax 914F Aircraft Engine - Part Number OHMA-914 (all models) NOTE 8. Generator and Alternator Operation: The optional external alternator was certified with the engine under 14-CFR, part 33, using some of the standards specified in Aerospace Standard AS 8020. Compliance to the AS 8020 standard for parallel operation of the optional external alternator and integrated internal generator has been demonstrated. NOTE 9. Vacuum Pump: During 14-CFR, part 33 certification of the 914 F series engine, compliance for the vacuum pump has only been shown to the attachment requirements of 14-CFR, part 33.25. TCDS E00058NE PAGE 5 NOTE 10. Governor: During 14-CFR, part 33 certification of the 914 F series engine, compliance for the Woodward hydraulic governor has been shown to the attachment requirements of 14-CFR, part 33.25, and in lieu of 14-CFR, part 35.42 (as required by part 33.19(b)), JAR-E (b)(1)(ii) was used for governor functional testing. NOTE 11. Engine Attitude: The 914 F2/F3/F4 model engines have been certified up to a maximum 40 degree bank angle, with no loss of lubrication capability of the dry sump system. See Rotax 914 F Operator's Manual, section 7, titled, Operating Instructions. NOTE 12. Critical Altitude: Five minute takeoff power is limited to a critical altitude of 8000 feet (2450 meters). NOTE 13. Takeoff Power: Five minute takeoff rated horsepower is 84.5 kW/115 HP when the single channel digital turbocharger control unit (TCU) is operable. Available takeoff power is limited to 66.1 kW/90 HP if the TCU fails prior to or during takeoff roll, unless the waste gate lockout switch is engaged and manifold pressure is assured just prior to takeoff roll. Therefore, aircraft installation that require more than 66.1 kW/90 HP for safe takeoff must have procedures requiring waste gate lockout engagement prior to every takeoff. NOTE 14. Overhaul: The Rotax 914F series engine must be overhauled in accordance with the approved overhaul manual. NOTE 15. NOTE 16. Engine Certification: Type Certificate E00058NE applies to Rotax 914 F2, 914 F3 and 914 F4 engines which are in compliance with the following Bombardier-Rotax mandatory Technical Bulletins: Technical Bulletin Numbers 914-03, 914-04, 914- 05, 914-07, 914-08, 914-12 and 914-13. Engines with serial numbers 4.420.200 and higher incorporated these Technical Bulletins at the time they were manufactured by Bombardier-Rotax. Each of the documents listed below must state that it is approved by the European Aviation Safety Agency or, for approvals made before September 28, 2003, by Austro Control GmbH. Any such documents, including those approved under a delegated authority, are accepted by the FAA and are considered FAA approved. ● Service bulletins, ● Structural repair manuals, ● Vendor manuals, ● Aircraft flight manuals, ● Overhaul and maintenance manuals These approvals pertain to the type design only. ---THE END---