# TCDS E00051EN: BRP-Rotax GmbH & Co KG - Type: Type certificate data sheet - Status: Current - Holder: BRP-Rotax GmbH & Co KG - Revision: 9 - Revised: March 2, 2026 - Product: Engine - Certification basis: Part 33 - Registered aircraft: 2,228, by the registry models matched to it (OpenAirDocs) - Data sheet PDF: https://openairdocs.org/files/sha256/f9/66/f966ad424a4066a6f93415550d357c2eb8fa876eda176d8d560f53fce6a35392 - FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID162918864420260303164002.0001 - Page: https://openairdocs.org/tcds/E00051EN ## Models (14) As the data sheet lists them. - 912 S3 - 912 F3 - 912 S2 - 912 F4 - 912 F2 - 912 S4 - 915 iSc2 C24 - 915 iSc3 C24 - 912 iSc2 Sport - 912 iSc3 Sport - 916 iSc2 A - 916 iSc3 A - 916 iSc2 C24 - 916 iSc3 C24 ## 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 1 2 3 4 5 6 7 8 9 10 11 REV. 9 9 8 9 9 9 9 9 9 9 8 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" "---" INDICATES "DOES NOT APPLY" NOTICE: SIGNIFICANT CHANGES, IF ANY ARE BLACK-LINED IN THE LEFT MARGIN. U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E00051EN TCDS NUMBER E00051EN REVISION: 9 DATE: March 2, 2026 BRP-Rotax GmbH & Co KG MODELS: ROTAX 912 F2 912 F3 912 F4 912 S2 912 S3 912 S4 915 iSc2 C24 915 iSc3 C24 912 iSc2 Sport 912 iSc3 Sport 916 iSc2 A 916 iSc3 A 916 iSc2 C24 916 iSc3 C24 Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00051EN) 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 BRP-Rotax GmbH & Co KG on June 15, 2016 BRP--POWERTRAIN GMBH & CO KG on December 18, 2003 Bombardier- Rotax GmbH (Name changes of TC Holder) I. MODELS, 912 series 912 F2 912 F3 912 F4 912 S2 912 S3 912 S4 TYPE (See NOTE 5) Four cylinder, horizontally opposed, four stroke engine, reduction gear driven, liquid cooled cylinder head's, ram air cooled cylinders, dry sump pressure lubrication, dual magneto high-voltage condenser ignition, contactless, two constant depression carburetors, electric starter, generator, fuel pump, vacuum pump. RATINGS Takeoff power (5 min.) : (sea level pressure altitude) Max. continuous power : (sea level pressure altitude) 59.6 kW(81 HP) at 5,800 rpm 58 kW(79 HP) at 5,500 rpm - - - - - - - - 73.5 kW(99 HP) at 5,800 rpm 69 kW(93 HP) at 5,500 rpm - - - - - - - - FUEL For specifications see Operators Manual OIL For specifications see Operators Manual CAPACITY Maximum: 0.79 Gal / 3.0 L Minimum: 0.66 Gal / 2.5L COMSUMPTION LIMIT 0.016 Gal / 0.06 L per hour FUEL PUMP Mechanical pump ENGINE SPEED MEASUREMENT (rpm) Electronic tachometer connector and optional mechanical tachometer drive WEIGHT (dry) (See NOTE 11) 57.1 kg (125.9 lbs) 59.8 kg (131.8 lbs) 57.1 kg (125.9 lbs) 58.3 kg (128.5lbs) 61 kg (134.5 lbs) 58.3 kg (128.5 lbs) DISPLACEMENT 1211 cm3 (73.9 in3) - - - - 1352 cm 3 (82.5 in 3) - - - - TCDS E00051EN PAGE 2 I. MODELS – 912 series(Continued) 912 F2 912 F3 912 F4 912 S2 912 S3 912 S4 BORE 79.5 mm (3.13 in.) - - - - 84 mm (3.3 in.) - - - - STROKE 61 mm (2.40 in.) - - - - 61 mm (2.40 in.) - - - - COMPRESSION RATIO 9.0 : 1 - - - - 10.5:1 - - - - 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 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, and 4 inch diameter with drive for hydraulic gov. for constant speed propeller GEAR REDUCTION (crankshaft to prop) 2.2727: 1 - - - - 2.4286:1 - - - - PROPELLER CONTROL --- --- adapter and drive for hydraulic constant speed propeller --- --- adapter and drive for hydraulic constant speed propeller II. MODELS, 915 iSc series 915 iSc2 C24 915 iSc3 C24 TYPE (See NOTE 5) Four cylinder horizontally opposed, four stroke piston engine with liquid cooled cylinder heads, ram-air cooled cylinders, dry sump forced lubrication, turbocharger with intercooler, exhaust system, controlled by a dual channel Full Authority Digital Engine Control (FADEC) system for ignition and injection and a regulator type with a 28V System Interface for power exchange to and from a 28V aircraft system. The engine is equipped with a reduction gear box with integrated torsion shaft, dampening clutch and overload protection clutch to reduce the crankshaft speed to the designed propeller shaft speed. RATINGS Takeoff power (5 min.) : (sea level pressure altitude) Max. continuous power : (sea level pressure altitude up to critical altitude of 15000 ft /4572 m) 104 kW(139.5 HP) at 5,800 rpm 99 kW(132.8 HP at 5,500 rpm FUEL See Operators Manual: FUEL PUMP Electrical fuel pump (not engine type design) OIL For specifications see Operators Manual CAPACITY Maximum: 0.79 Gal / 3.0 L Minimum: 0.66 Gal / 2.5L COMSUMPTION LIMIT 0.016 Gal / 0.06 L per hour ENGINE SPEED MEASUREMENT (rpm) Electronic tachometer connector WEIGHT (dry) (See NOTE 11) 85.3 kg (188.1 lbs) 85.9 kg (189.4 lbs) DISPLACEMENT 1352 cm 3(82.5 in 3) - - BORE 84 mm (3.31 in.) - - STROKE 61 mm (2.40 in.) - - COMPRESSION RATIO 8.2:1 - - PROPELLER ROTATION CCW - - TCDS E00051EN PAGE 3 II. MODELS, 915 iSc series (cont.) 915 iSc2 C24 915 iSc3 C24 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 GEAR REDUCTION (crankshaft to prop) 2.5454 : 1 - - PROPELLER CONTROL --- Adapter and drive for hydraulic constant speed propeller III. MODELS, 912 iSc series 912 iSc2 Sport 912 iSc3 Sport TYPE (See NOTE 5) The engine is a 4 cylinder horizontally opposed, 4-stroke piston engine with liquid cooled cylinder heads, ram-air cooled cylinders, dry sump forced lubrication, 2 electrical fuel pumps, exhaust system and it is controlled by a dual channel Full Authority Digital Engine Control (FADEC) system for ignition and injection. The engine is equipped with a reduction gear box with integrated shock absorber (dog clutch type) and overload protection to reduce the crankshaft speed to the designed propeller shaft speed. RATINGS Takeoff power (5 min.) : (sea level pressure altitude) Max. continuous power : (sea level pressure altitude) 73.5 kW(99 HP) at 5,800 rpm 72 kW(96.6 HP) at 5,500 rpm FUEL See Operators Manual: FUEL PUMP Dual Electrical fuel pumps OIL For specifications see Operators Manual CAPACITY Maximum: 0.79 Gal / 3.0 L Minimum: 0.66 Gal / 2.5L COMSUMPTION LIMIT 0.016 Gal / 0.06 L per hour ENGINE SPEED MEASUREMENT (rpm) Electronic tachometer connector WEIGHT (dry) (See NOTE 11) 63.6 kg (140.2 lbs) 64.4 kg (142 lbs) 1 External alternator 3.0 kg (6.61 lbs) - - DISPLACEMENT 1352 cm 3(82.5 in 3) - - BORE 84 mm (3.31 in.) - - STROKE 61 mm (2.40 in.) - - COMPRESSION RATIO 10.8:1 - - 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 GEAR REDUCTION (crankshaft to prop) 2.4286 : 1 - - PROPELLER CONTROL --- Adapter and drive for hydraulic constant speed propeller TCDS E00051EN PAGE 4 IV. MODELS, 916 iSc series 916 iSc2 A 916 iSc3 A 916 iSc2 C24 916 iSc3 C24 TYPE (See NOTE 5) Four cylinder horizontally opposed, four stroke piston engine with liquid cooled cylinder heads, ram-air cooled cylinders, dry sump forced lubrication, turbocharger with intercooler, exhaust system, controlled by a dual channel Full Authority Digital Engine Control (FADEC) system for ignition and injection. The engine is equipped with a reduction gear box with integrated torsion shaft, dampening clutch and overload protection clutch to reduce the crankshaft speed to the designed propeller shaft speed and an adjustable exhaust system. Four cylinder horizontally opposed, four stroke piston engine with liquid cooled cylinder heads, ram-air cooled cylinders, dry sump forced lubrication, turbocharger with intercooler, exhaust system, controlled by a dual channel Full Authority Digital Engine Control (FADEC) system for ignition and injection and a regulator type with a 28V System Interface for power exchange to and from a 28V aircraft system. The engine is equipped with a reduction gear box with integrated torsion shaft, dampening clutch and overload protection clutch to reduce the crankshaft speed to the designed propeller shaft speed and an adjustable exhaust system. RATINGS Takeoff power (5 min.) : (sea level pressure altitude) Max. continuous power : (sea level pressure altitude) 117 kW(160 HP) at 5,800 rpm 101 kW(137 HP) at 5,500 rpm FUEL See Operators Manual: FUEL PUMP Electrical fuel pump (not engine type design) OIL For specifications see Operators Manual CAPACITY Maximum: 0.79 Gal / 3.0 L Minimum: 0.66 Gal / 2.5L COMSUMPTION LIMIT 0.016 Gal / 0.06 L per hour ENGINE SPEED MEASUREMENT (rpm) Electronic tachometer connector WEIGHT (dry) (See NOTE 11) 85.8 kg (189.2 lbs) 86.4 kg (190,5 lbs) 86.5 kg (190.7 lbs) 87.1 kg (192,0 lbs) DISPLACEMENT 1352 cm3(82.5 in 3) BORE 84 mm (3.31 in.) STROKE 61 mm (2.40 in.) COMPRESSION RATIO 8.2 : 1 PROPELLER ROTATION CCW PROPELLER FLANGE P.C.D. 80 mm, and 4 inch diameter for fixed propeller P.C.D. 80 mm, and 4 inch diameter with drive for hydraulic gov. for constant speed propeller P.C.D. 80 mm, and 4 inch diameter for fixed propeller P.C.D. 80 mm, and 4 inch diameter with drive for hydraulic gov. for constant speed propeller GEAR REDUCTION (crankshaft to prop) 2.5454 : 1 PROPELLER CONTROL --- Adapter and drive for hydraulic constant speed propeller --- Adapter and drive for hydraulic constant speed propeller TCDS E00051EN PAGE 5 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 912 F2 November 18, 1993 February 2, 1995 912 F3 November 18, 1993 February 2, 1995 912 F4 November 18, 1993 February 2, 1995 912 S2 December 28, 1998 August 12, 1999 912 S3 December 28, 1998 August 12, 1999 912 S4 December 28, 1998 August 12, 1999 14-CFR, part 33, Airworthiness Standards: Aircraft Engines, effective February 1, 1965, as amended by 33-1 through 33-34, inclusive. 915 iSc2 C24 October 4, 2021 November 23, 2021 915 iSc3 C24 October 4, 2021 November 23, 2021 14-CFR, part 33, Airworthiness Standards: Aircraft Engines, effective February 1, 1965, as amended by 33-1 through 33-34, inclusive. 912 iSc2 Sport November 3, 2022 March 27, 2023 912 iSc3 Sport November 3, 2022 March 27, 2023 14-CFR, part 33, Airworthiness Standards: Aircraft Engines, effective February 1, 1965, as amended by 33-1 through 33-34, inclusive. 916 iSc2 A March 24, 2025 March 2, 2026 916 iSc3 A March 24, 2025 March 2, 2026 916 iSc2 C24 March 24, 2025 March 2, 2026 916 iSc3 C24 March 24, 2025 March 2, 2026 The Austrian aviation authority, Austro Control GmbH (ACG), originally type certificated the 912 engines. The FAA validated this product under U.S. Type Certificate Number E00051EN. 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 E00051EN, is in a condition for safe operation and has under gone a final operational check. NOTES NOTE 1 ENGINE RATINGS The power ratings for the 915 iSc C24 series, 916 iSc A series and 916 iSc C24 series for Take-off Power and Maximum Continuous Power have been determined without accessories (such as governor,etc.) NOTE 2 TEMPERATURE LIMITS Models 912 F2 / F3/ / F4 912 S2 / S3/ / S4 915 iSc2 C24 915 iSc3 C24 912 iSc2 Sport 912 iSc3 Sport 916 iSc2 A 916 iSc3 A 916 iSc2 C24 916 iSc3 C24 Max. oil-temperature at inlet ( C) / ( F) 140/284 130/266 130/266 120/248 Max. cylinder-head temperature ( C) / ( F) 150/302 135/275 Not Applicable Not Applicable Max. coolant temperature ( C) / ( F) 120/248 (engine type designation extended with suffix -01) 120/248 120/248 Monitored via cylinder head temperature, otherwise monitored via coolant temperature for engine type designation extended with suffix -01 TCDS E00051EN PAGE 6 NOTE 3 FUEL AND OIL PRESSURE LIMITS Models 912 F2 / F3 / F4 / S2 / S3 / S4 915 iSc2 C24 915 iSc3 C24 916 iSc2 A 916 iSc3 A 916 iSc2 C24 916 iSc3 C24 912 iSc2 Sport 912 iSc3 Sport Fuel Pressure 0.15 bar (2.18 psi) – minimum 2.9 bar/42.0 psi 2.8 bar/40.61 psi 0.50 bar (7.25 psi) – maximum 3.2 bar/46.41 psi 3.2 bar/46.41 psi At inlet to carburetor. The delivery pressure of a fuel pump connected in series (backing pump) must not exceed 0.3 bar (4.4 psi) to ensure not to override the float valve in the carburetor. Models 912 F2 / F3 / F4 / S2 / S3 / S4 / 915 iSc2 C24 / 915 iSc3 C24 / 912 iSc2 Sport / 912 iSc3 Sport / 916 iSc2 A / 916 iSc3 A / 916 iSc2 C24 / 916 iSc3 C24 Oil Pressure normal operating range above 3500 rpm: 2.0 bar –5.0 bar (29-72.5 psi)* idling: 0.8 bar (11.6 psi) – minimum** starting & warm-up: 7 bar (101.5 psi) – maximum For 912F up to engine Number 4412.764: *normal operation: 1.5 bar –5.0 bar (22-73 psi) **idling: 1.5 bar (22 psi) - minimum NOTE 4. ACCESSORY DRIVE PROVISIONS LIMITS Accessory 912 F2 912 F3 912 F4 Rotation, facing drive pad Speed Ratio to crankshaft i=2.2727 /i=2.4286 ** Maximum Torque Overhung moment (max.) Vacuum pump ** --- ** CCW 0.585 : 1 0.548:1** 0.1 Nm/ 0.4 Nm Governor drive --- * --- CCW 0.585 : 1 0.548:1** 2.0 Nm 1.04 Nm Tachometer drive ** ** ** CW 0.25 : 1 --- --- "---" indicates "does not apply" "*" standard feature "**" optional feature "CW" clockwise "CCW" counter clockwise Accessory 912 S2 912 S3 912 S4 Rotation, facing drive pad Speed Ratio, to crankshaft i=2.4286 Maximum Torque Overhun g moment (max.) Vacuum pump ** --- ** CCW 0.548:1 0.9 Nm2 0.4 Nm Governor drive --- * --- CCW 0.548:1 1.8 Nm 1.04 Nm Tachometer drive ** ** ** CW 0.25 : 1 --- --- "---" indicates "does not apply" "*" standard feature "**" optional feature "CW" clockwise "CCW" counter clockwise TCDS E00051EN PAGE 7 NOTE 4. ACCESSORY DRIVE PROVISIONS LIMITS (Continued) Accessory 915 iSc2 C24 915 iSc3 C24 Rotation, facing drive pad Speed Ratio, to crankshaft i = 2.5454 Maximum Torque Overhung moment (max.) Vacuum pump ** --- CCW 0.518 : 1 0.9 Nm 0.4 Nm Governor --- * CCW 0.518 : 1 1.8 Nm 1.04 Nm "---" indicates "does not apply" "*" standard feature "**" optional feature "CW" clockwise "CCW" counter clockwise Accessory 912 iSc2 Sport 912 iSc3 Sport Rotation, facing drive pad Speed Ratio, to crankshaft i = 2.4286 Maximum Torque Overhung moment (max.) Vacuum pump ** --- CCW 0.548 : 1 0.9 Nm 0.4 Nm Governor --- * CCW 0.548 : 1 1.8 Nm 1.04 Nm "---" indicates "does not apply" "*" standard feature "**" optional feature "CW" clockwise "CCW" counter clockwise Accessory 916 iSc2 A 916 iSc2 C24 916 iSc3 A 916 iSc3 C24 Rotation, facing drive pad Speed Ratio, to crankshaft i = 2.4286 Maximum Torque Overhung moment (max.) Vacuum pump --- --- CCW 0.518 : 1 0.9 Nm 0.4 Nm Governor --- * CCW 0.518 : 1 1.8 Nm 1.04 Nm "---" indicates "does not apply" "*" standard feature "**" optional feature "CW" clockwise "CCW" counter clockwise NOTE 5. MODEL DESCRIPTION: 912 F2 Basic model; four stroke, four cylinder horizontally opposed, 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, mechanical fuel pump, fixed pitch propeller configuration, drive output via reduction gear with integrated shock absorber and overload protection, electric starter, integrated AC generator, vacuum pump drive (optional), external generator (optional). 912 F3 Same as described for F2, except; additional drive and adapter for hydraulic governor, hydraulic governor and propeller shaft for constant speed propeller 912 F4 Same as F3 except; fixed pitch propeller, prepared for hydraulic governor for constant speed propeller (without drive, adapter and governor). TCDS E00051EN PAGE 8 NOTE 5. MODEL DESCRIPTION (Continued) 912 S2 Similar to F2 in I above, except; increased displacement and horsepower, and larger reduction gearbox. 912 S3 Same as S2 except; additional drive and adapter for hydraulic governor, hydraulic governor and propeller shaft for constant speed propeller. 912 S4 Same as S3 except; fixed pitch propeller, prepared for hydraulic governor for constant speed propeller (without drive, adapter and governor). 912 F2/3/4 engine, and 912 S2/3/4 engine type designation extended with suffix -01 Same as described above, except; engine temperature measurement methods have been amended from CHT (cylinder head temperature) and CT (coolant temperature) to only CT (coolant temperature). Therefore only the coolant temperature limit applies. For further details refer to Service Bulletins SB-912-066 and SB-912-068 (respectively latest revision). 915 iSc2 C24 Four cylinder horizontally opposed, four stroke piston engine with liquid cooled cylinder heads, ram- air cooled cylinders, dry sump forced lubrication, turbocharger with intercooler, exhaust system, controlled by a dual channel Full Authority Digital Engine Control (FADEC) system for ignition and injection and a regulator type with a 28V System Interface for power exchange to and from a 28V aircraft system. The engine is equipped with a reduction gear box with integrated torsion shaft, dampening clutch and overload protection clutch to reduce the crankshaft speed to the designed propeller shaft speed. 915 iSc3 C24 Same as described for 915 iSc2 C24, except; additional drive and adapter for hydraulic governor propeller shaft for constant speed propeller 912 iSc2 Sport Four cylinder horizontally opposed, four stroke piston engine with liquid cooled cylinder heads, ram- air cooled cylinders, dry sump forced lubrication, 2 electrical fuel pumps, exhaust system, controlled by a dual channel Full Authority Digital Engine Control (FADEC) system for ignition and injection. The engine is equipped with a reduction gear box with integrated shock absorber (dog clutch type) and overload protection to reduce the crankshaft speed to the designed propeller shaft speed. 912 iSc3 Sport Same as described for 912 iSc2 Sport, except; additional drive and adapter for hydraulic governor propeller shaft for constant speed propeller 916 iSc2 A Four cylinder horizontally opposed, four stroke piston engine with liquid cooled cylinder heads, ram- air cooled cylinders, dry sump forced lubrication, turbocharger with intercooler, exhaust system, controlled by a dual channel Full Authority Digital Engine Control (FADEC) system for ignition and injection. The engine is equipped with a reduction gear box with integrated torsion shaft, dampening clutch and overload protection clutch to reduce the crankshaft speed to the designed propeller shaft speed and an adjustable exhaust system. 916 iSc3 A Same as described for 916 iSc2 A, except; additional drive and adapter for hydraulic governor propeller shaft for constant speed propeller 916 iSc2 C24 Four cylinder horizontally opposed, four stroke piston engine with liquid cooled cylinder heads, ram- air cooled cylinders, dry sump forced lubrication, turbocharger with intercooler, exhaust system, controlled by a dual channel Full Authority Digital Engine Control (FADEC) system for ignition and injection and a regulator type with a 28V System Interface for power exchange to and from a 28V aircraft system. The engine is equipped with a reduction gear box with integrated torsion shaft, dampening clutch and overload protection clutch to reduce the crankshaft speed to the designed propeller shaft speed and an adjustable exhaust system. 916 iSc3 C24 Same as described for 916 iSc2 C24, except; additional drive and adapter for hydraulic governor propeller shaft for constant speed propeller NOTE 6 TYPICAL AIRCRAFT ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES, WITH AIRCRAFT LEVEL REQUIREMENTS, PROVIDED AS PART OF ENGINE TYPE DESIGN: Not applicable TCDS E00051EN PAGE 9 NOTE 7 AIRCRAFT ACCESSORIES, COMPONENTS, OR SYSTEM ASSEMBLIES INSTALLED ON THE ENGINE BUT ARE NOT PROVIDED AS PART OF ENGINE TYPE DESIGN Not applicable NOTE 8 SPECIAL ANTI-ICING OR DE-ICING REQUIREMENTS Not applicable NOTE 9 ENGINE MOUNT SYSTEM PROVISIONS See Installation and Maintenance Manuals NOTE 10 POWER BOOST, INJECTION OR AUGMENTATION SYSTEMS AND LIMITS AS APPLICABLE The 915 iSc C24 series, 916 iSc A series and 916 iSc C24 series engines are equipped with a turbocharger with intercooler. NOTE 11 SPECIAL INSTALLATION REQUIREMENTS Engine weight is defined as the following configurations: 912 F2 / F4/ S2 / S4: With ignition unit and internal generator, carburetors, overload clutch, oil tank and electric starter, but without the muffler and radiator. 912 F3 / S3: As above and with propeller flange P.C.D. 75/80 mm / 4", drive and adapter for hydraulic governor for constant speed propeller. Alternator (external): 3.0 kg (6.6 lbs). 915 iSc2 C24 With base engine with gearbox and turbocharger, cooling air baffle,wiring harness, sensors, intermediate flange with overboost valve, air hose and clamps, magneto valve block with holes, ECU, fuse box, 28V AC/DC converter, oil tank, intercooler, exhaust system. Without fuel pumps assy, radiator, oil cooler governor and governor drive. 915 iSc3 C24 As 915 iSc2 C24 but w ith governor drive. 912 iSc2 Sport With electric system: wiring harness ECU, fuse box and start relay. With oil tank. Without engine suspension frame, exhaust system, fuel pumps assy., cooling baffle radiator, oil cooler, governor and governor drive. 912 iSc3 Sport As 912 iSc2 Sport but w ith governor drive 916 iSc2 A With base engine with gearbox and turbocharger, cooling air baffle, wiring harness, sensors, intermediate flange with overboost valve, air hose and clamps, magneto valve block with hoses, ECU, fusebox, oil tank, intercooler, exhaust system Without fuel pumps assy., radiator and oil cooler, governor and governor drive. 916 iSc3 A As 916 iSc2 A but with governor drive 916 iSc2 C24 With base engine with gearbox and turbocharger, cooling air baffle, wiring harness, sensors, intermediate flange with overboost valve, air hose and clamps, magneto valve block with hoses, ECU, fusebox, 28V AC/DC converter, oil tank, intercooler, exhaust system Without fuel pumps assy., radiator and oil cooler, governor and governor drive. 916 iSc3 C24 As 916 iSc2 C24 but with governor drive TCDS E00051EN PAGE 10 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 external alternator and internal generator has not been demonstrated. Vacuum Pump: The propeller shaft driven vacuum pump is optional for the 912 F2/S2/F4/S4 series engine models, and not applicable, nor available, for the 912 F3/S3 series engine model. During 14-CFR, Part 33 certification of the 912 series engine models, compliance for the vacuum pump has only been shown to the attachment requirements of 14-CFR, Part 33.25. Governor: During 14-CFR, Part 33 certification of the 912 series engine models, compliance for the 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. The 912 iSc Sport series, 915 iSc C24 series, 916 iSc A series and 916 iSc A series engines are not approved for Time Limited Dispatch. All engine systems and equipment must be functional prior to aircraft take-off. Any detected engine system or equipment failure must be corrected before next flight. For special instructions, see applicable Operation & Maintenance Manual. NOTE 12 MANUFACTURER’S SERVICE BULLETINS OR OTHER INSTRUCTIONS Each of the documents listed below must state that it is approved by the European Union 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. NOTE 13 SPECIAL OPERATING PROCEDURES OR LIMITATIONS Not applicable NOTE 14 SPECIAL REPAIR OR OVERHAUL LIMITATIONS The Rotax 912, 915 and 916 series engines must be overhauled in accordance with the approved overhaul manuals. NOTE 15 APPLICABLE MANUALS Description 912 F2 / F3/ / F4 / S2 / S3 /S4 915 iSc2 C24 915 iSc3 C24 912 iSc2 Sport 912 iSc3 Sport 916 iSc2 A 916 iSc3 A 916 iSc2 C24 916 iSc3 C24 Operators Manual OM-912 OM-915 iA/C24 OM-912i OM-916 i A/C24 Installation Manual IM-912 IM-915 iA/C24 IM-912i IM-916 i A/C24 Maintenance Manual-Line MML-912 MML-915 iA/C24 MML-912i MML-916 i A/C24 Maintenance Manual-Heavy MMH-912 MMH-915 iA/C24 MMH-912i MMH-916 i A/C24 Overhaul Manual OHM-912 OHM-915 iA/C24 OHM-912i OHM-916 i A/C24 Overhaul Manual Appendix OHMA-912 OHMA-915 iA/C24 OHMA-912i OHMA-916iA/C24 Illustrated Parts Catalog IPC-912 IPC-915 iSc C24 IPC-912i IPC-916 i A/C24 TCDS E00051EN PAGE 11 NOTE 16 IMPORT REQUIREMENTS STATEMENT FOR FOREIGN MANUFACTURED ENGINES See import requirements above. Refer to the applicable bilateral agreement to verify eligibility for import into the United States of both new and used aircraft based on the scope of the agreement, to identify any required statements by the exporting authority on the export certificate of airworthiness (or equivalent document) , and for procedures for coordinating exceptions to conformity statements on these documents. Refer to FAA Order 8130.2 , Airworthiness Certification of Aircraft , for requirements for issuance of an airworthiness certificate for imported aircraft. NOTE 17 LIFE LIMITED PART INFORMATION Not applicable NOTE 18 MILITARY MODEL INFORMATION Not applicable NOTE 19 HORIZONTAL OR VERTICAL INSTALLATION (ROTORCRAFT) Not applicable NOTE 20 CENTER OF GRAVITY TABULATION (IF NOT SHOWN IN BODY OF TCDS) Reference the Installation Manual, latest revision NOTE 21 VIBRATION DAMPER PROVISION LIMITATIONS Not applicable ---END--- ``` ## ADs (22, in force first) - [AD 2026-16-11](https://openairdocs.org/ad/2026-16-11): Reciprocating Engine Front Section · BRP-Rotax 912 F2, 912 F3, 912 F4 and 16 more. Effective Aug 28, 2026 - [AD 2026-04-02](https://openairdocs.org/ad/2026-04-02): Turbine Engine Reduction Gear · BRP-Rotax 915 iSc2 C24 and 915 iSc3 C24. Effective Mar 19, 2026 - [AD 2025-15-03](https://openairdocs.org/ad/2025-15-03): Reciprocating Engine Oil System · BRP-Rotax 912 iSc2 Sport, 912 iSc3 Sport, 915 iSc2 C24 and 1 more. Effective Aug 6, 2025 - [AD 2023-17-13](https://openairdocs.org/ad/2023-17-13): Reciprocating Engine Front Section · BRP-Rotax 912 F2, 912 F3, 912 F4 and 16 more. Effective Sep 20, 2023 - [AD 2019-10-04](https://openairdocs.org/ad/2019-10-04): Reciprocating Engine Cylinder Section · BRP-Rotax 912 F2, 912 F3, 912 F4 and 6 more. Effective Jul 10, 2019 - [AD 2016-23-04](https://openairdocs.org/ad/2016-23-04): Carburetor floats · BRP-Rotax 912 F2, 912 F3, 912 F4 and 6 more. Effective Dec 7, 2016 - [AD 2016-13-04](https://openairdocs.org/ad/2016-13-04): Engine coolant temperature limit · BRP--POWERTRAIN 912 F2, 912 F3, 912 F4 and 6 more. Effective Jul 27, 2016 - [AD 2013-15-19](https://openairdocs.org/ad/2013-15-19): Excessive oil consumption · BRP--POWERTRAIN 912 F2, 912 F3, 912 F4 and 6 more. Effective Aug 27, 2013 - [AD 2012-16-13](https://openairdocs.org/ad/2012-16-13): Pressure side fuel hose · BRP--POWERTRAIN 912 F2, 912 F3, 912 F4 and 3 more. Effective Sep 10, 2012 - [AD 2012-04-03](https://openairdocs.org/ad/2012-04-03): Oil pump attachment bolts · BRP--POWERTRAIN 912 S2, 912 S3 and 914 F2. Effective Mar 16, 2012 - [AD 2011-25-02](https://openairdocs.org/ad/2011-25-02): Crankshaft · BRP--POWERTRAIN 912 F2, 912 F3, 912 F4 and 6 more. Effective Dec 22, 2011 - [AD 2011-12-04](https://openairdocs.org/ad/2011-12-04): Washers · Bombardier-Rotax 912 F3, 912 S2, 912 S3 and 4 more. Effective Jun 27, 2011 - [AD 2010-20-23](https://openairdocs.org/ad/2010-20-23): Engine crankcase · Bombardier-Rotax 912 F2, 912 F3, 912 F4 and 6 more. Effective Nov 8, 2010 - [AD 2010-18-14](https://openairdocs.org/ad/2010-18-14): Fuel pressure · Bombardier-Rotax 912 F2, 912 F3, 912 F4 and 3 more. Effective Oct 13, 2010 - [AD 2005-01-14](https://openairdocs.org/ad/2005-01-14): Valve train on all engines · BRP--POWERTRAIN 912 F2, 912 F3, 912 F4 and 6 more. Effective Feb 15, 2005 - [AD 2002-19-09](https://openairdocs.org/ad/2002-19-09): Fuel pump assembly · BRP--POWERTRAIN 912 F2, 912 F3, 912 F4 and 3 more. Effective Oct 10, 2002 - [AD 2002-16-07](https://openairdocs.org/ad/2002-16-07): Valve Spring Retainers · BRP--POWERTRAIN 912 F2, 912 F3, 912 F4 and 6 more. Effective Sep 3, 2002 - [AD 98-15-16](https://openairdocs.org/ad/98-15-16): Fuel Pump · BRP--POWERTRAIN 912 F2, 912 F3 and 912 F4. Effective Aug 7, 1998 - [AD 2025-07-02](https://openairdocs.org/ad/2025-07-02) (historical): Reciprocating Engine Oil System · BRP-Rotax 912 iSc2 Sport, 912 iSc3 Sport, 915 iSc2 C24 and 1 more. Effective Apr 21, 2025 - [AD 2013-07-12](https://openairdocs.org/ad/2013-07-12) (historical): Cylinder heads · BRP--POWERTRAIN 912 F2, 912 F3, 912 F4 and 6 more. Effective Apr 30, 2013 - [AD 2002-21-16](https://openairdocs.org/ad/2002-21-16) (historical): Valve train · Bombardier-Rotax 912 F2, 912 F3, 912 F4 and 6 more. Effective Oct 28, 2002 - [AD 2002-16-26](https://openairdocs.org/ad/2002-16-26) (historical): Engine crankcase · Bombardier-Rotax 912 F2, 912 F3, 912 F4 and 3 more. Effective Sep 16, 2002 ## Registered aircraft by registry model (OpenAirDocs) - [Rotax 912 IS](https://openairdocs.org/engine/rotax-912-is-series): 875 aircraft (registry code 55593) - [Rotax 915 IS](https://openairdocs.org/engine/rotax-915-is-series): 393 aircraft (registry code 55620) - [Rotax 912S](https://openairdocs.org/engine/rotax-912s-series): 335 aircraft (registry code 55570) - [Rotax 912](https://openairdocs.org/engine/rotax-912-series): 299 aircraft (registry codes 55569, 55606) - [Rotax 916 IS](https://openairdocs.org/engine/rotax-916-is-series): 118 aircraft (registry code 55622) - [Rotax 912S3](https://openairdocs.org/engine/rotax-912s3): 95 aircraft (registry code 55594) - [Rotax 912ISC](https://openairdocs.org/engine/rotax-912isc-series): 66 aircraft (registry code 55591) - [Rotax 915 series](https://openairdocs.org/engine/rotax-915-series): 41 aircraft (registry code 55619) - [Rotax 912F3](https://openairdocs.org/engine/rotax-912f3): 6 aircraft (registry code 55601) ## STCs approved under this data sheet (2) - [STC SE02352CH](https://openairdocs.org/stc/SE02352CH): Installation of Challenger cleanable oil filter assembly. Challenger Aviation Products Inc. - [STC SE01966WI](https://openairdocs.org/stc/SE01966WI): Use of GAMI G100UL High Octane Unleaded Avgas in spark ignition piston aircraft engines. General Aviation Modifications 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.