TCDS E9EA

PAGE 1 2 3 4 5 6 7 8 REV. 13 11 11 11 13 10 12 11 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. U.S. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION TYPE CERTIFICATE DATA SHEET E9EA TCDS NUMBER E9EA REVISION: 13* DATE: April 30, 2013 Franklin Sp. z.o.o. MODELS: FRANKLIN 6A-350-C1 6A-350-D1 6A-350-C1R 6A-350-C1A 6A-350-D1A 6A-350-C1L 6A-350-C2 6A-350-D1B 6A-350-C2A 6V-350-A 6A-350-D 6V-350-B Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E9EA) 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 Franklin Sp. z.o.o. Ul. Chelmińska 208 86-300 Grudziądz Poland TYPE CERTIFICATE (TC) HOLDER RECORD WSK-PZL-RZESZOW transferred TC E9EA to Franklin Sp. z.o.o. on August 17, 2006 I. MODELS 6A-350-C1 6A-350-C1A 6A-350-C2 6A-350-C2A 6A-350-C1R, -C1L TYPE 6OA Horizontally-Mounted Direct Drive RATINGS Maximum Continuous hp, r.p.m., at: Sea level pressure altitude Takeoff hp, r.p.m., full throttle at: Sea level pressure altitude 220-2800 220-2800 - - - - 215-2800 215-2800 212-2800 212-2800 205-2800 205-2800 FUEL (See Note 13) Minimum grade aviation gasoline 100/130 - - - - - - - - OIL GRADE (See Note 13) above 40øF ambient air temp. below 40øF ambient air temp. all ambient air temp. SAE 50 SAE 30 SAE 15W50 SAE 20W50 - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - - TCDS E9EA PAGE 2 I. MODELS (Continued) 6A-350-C1 6A-350-C1A 6A-350- C2 6A-350- C2A 6A-350-C1R/C1L COMPRESSION Bore and stroke, in. Displacement, cu. in. Compression ratio 4.625 x 3.5 350 10.5:1 - - - - - - - - - - - - - - - - - - - - - - - - WEIGHT (DRY) (lb) 325 334 325 328 330 CENTER OF GRAVITY (in) (with all accessories) Forward from rear face of crankcase Above C.L. of crankshaft 10.0 2.0 8.0 0.31 10.0 2.0 7.2 0.3 - - - - DRIVE SHAFT END Integral flange, six 1/2 in. holes on 4 in. circle - - - - - - - - CARBURETION Marvel Schebler MA4-5, MA-5, Bendix PS5BD MA-5 - - - - - - IGNITION (dual) Bendix-Scintilla S6RN-21 Slick 6399 - - - - - - - - - - - - S6RN-21 (C1R) S6LN-1227 (C1L) - - (C1R only) TIMING, øBTC 28 - - - - - - See NOTE 12 SPARK PLUGS AC 273, Champion RHB32E, RHB32N, RHB33E, RHB36P, RHB36W - - - - - - - - OIL SUMP CAPACITY, QT. 8.8 - - - - - - - - USEABLE OIL, QT. (starting with full tank) See NOTE 3 (c) 6.8 (d) 5.8 - - - - - - - - - - - - - - - - NOTES 1-3, 5, 7-10, 13, 14 1-3, 5, 7, 9,10, 13, 14 - - - - 1-3, 7, 9-14 TCDS E9EA PAGE 3 II. MODELS 6A-350-D 6A-350-D1 6A-350-D1A 6A-350-D1B TYPE 6OA Horizontally-Mounted Direct Drive RATINGS Maximum Continuous hp, r.p.m., at: Sea level pressure altitude Takeoff hp, r.p.m., full throttle at: Sea level pressure altitude 235-3200 235-3200 200-3200 200-3200 230-3200 230-3200 220-3000 220-3000 FUEL (See Note 13) Minimum grade aviation gasoline 100/130 80/87 100/130 - - OIL GRADE (See Note 13) above 40øF ambient air temp. below 40øF ambient air temp. all ambient air temp. SAE 50 SAE 30 SAE 15W50 SAE 20W50 - - - - - - - - - - - - - - - - - - - - - - - - COMPRESSION Bore and stroke, in. Displacement, cu. in. Compression ratio 4.625 x 3.5 350 10.5:1 - - - - - - - - - - - - - - - - - - WEIGHT (DRY) (lb) 304 - - - - - - CENTER OF GRAVITY (in) (with all accessories) Forward from rear face of crankcase Below C.L. of crankshaft 7.2 .67 8.0 - - - - - - 7.3 - - DRIVE SHAFT END Integral flange, eight 5/16 in. threaded holes on 3-3/16 in. circle - - - - - - CARBURETION Marvel Schebler MA-5 - - - - - - IGNITION (dual) Bendix-Scintilla S6RN-21 Slick 6399 - - - - - - - - - - - - TIMING, øBTC 28 - - - - - - SPARK PLUGS AC 273, Champion RHB32E, RHB32N, RHB33E, RHB36P, RHB36W - - - - - - OIL SUMP CAPACITY, QT. 8.8 - - - - - - USEABLE OIL, QT. (starting with full tank) See NOTE 3 (c) 6.8 (d) 5.8 - - - - - - - - - - - - NOTES 1-4, 6, 7, 9, 10, 13 - - - - - - III. MODELS 6V-350-A, -B TYPE 6OA Vertically-Mounted Direct Drive TCDS E9EA PAGE 4 RATINGS Maximum Continuous hp, r.p.m., at: Sea level pressure altitude Takeoff hp, r.p.m., full throttle at: Sea level pressure altitude 235-3200 235-3200 FUEL (See Note 13) Minimum grade aviation gasoline 100/130 OIL GRADE (See Note 13) above 40øF ambient air temp. below 40øF ambient air temp. all ambient air temp. SAE 50 SAE 30 SAE 15W50 SAE 20W50 COMPRESSION Bore and stroke, in. Displacement, cu. in. Compression ratio 4.625 x 3.5 350 10.5:1 WEIGHT (DRY) (lb) 308 CENTER OF GRAVITY (in) (with all accessories) Above rear face of crankcase From crankshaft C.L. forward carburetor 6.8 2.0 DRIVE SHAFT END Integral flange, eight 5/16 in. threaded holes on 3-3/16 in. circle CARBURETION MA-5AA IGNITION (dual) Bendix Scintilla S6RN-21 Slick 6399 TIMING, øBTC 28 SPARK PLUGS AC 273, Champion RHB32E, RHB32N, RHB33E, RHB36P, RHB36W OIL SUMP CAPACITY, QT. 10.0 USEABLE OIL, QT. (starting with full tank) See NOTE 3 (a) 6.0 (b) 8.0 NOTES 1-4, 6, 7, 9, 10, 13 TCDS E9EA PAGE 5 CERTIFICATION BASIS CAR 13, effective June 15, 1956, as amended by 33-1 to 13-6, inclusive. The 6A-350-C1R and 6A-350-C1L engine models comply with Federal Aviation Regulation Part 33, effective February 1, 1965, including amendments 33-1 to 33-14, inclusive, for sections 33.17, 33.19, 33.23, 33.25, 33.27, 33.35, 33.43, and 33.49. Type Certificate E9EA issued/revised: Date of Date TC Model Application Issued/Revised 6V-350-A, -B 03/27/62 10/12/64 6A-350-D 03/15/65 07/29/65 6A-350-C1 06/04/63 12/01/65 6A-350-C2 06/04/63 03/11/66 6A-350-D1 01/17/66 04/07/66 6A-350-D1A 05/22/67 07/26/67 6A-350-C2A 04/15/68 10/04/68 6A-350-C1A 11/11/68 11/21/68 6A-350-D1B 03/21/72 05/12/72 6A-350-C1R 09/30/92 12/8/94 6A-350-C1L 09/30/92 12/8/94 Reissued to PEZETEL 08/01/79 Reissued to WSK "PZL-RZESZOW" 11/05/81 Reissued to WSK "PZL-RZESZOW" SA 12/8/94 Reissued to Franklin Sp. z.o.o. 04/30/13 The General Inspectorate of Civil Aviation of Poland originally type certificated this engine. The FAA validated this product under U.S. Type Certificate Number E9EA. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of Poland. PRODUCTION BASIS 1. Production Certificate No. 9 for U.S. production. There will be no further production of engines or replacement parts under this production certificate. 2. FAR 21.500 for production of engines or replacement parts under this type certificate by WSK "PZL-RZESZOW" SA under control of the Republic of Poland General Inspectorate of Civil Aviation (GICA). Parts produced under either production basis are eligible to be used interchangeably. IMPORT REQUIREMENTS To be considered eligible for installation on U.S. registered aircraft, each new engine to be exported to the United States with the General Inspectorate of Civil Aviation of Poland or EASA airworthiness approval shall have a Joint Aviation Authorities (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 E9EA, is in a condition for safe operation and has undergone a final operational check. Additional guidance is contained in FAA Advisory Circular 21-23, Airworthiness Certification of Civil Aircraft, Engines, Propellers, and Related Products, imported into the United States. TCDS E9EA PAGE 6 NOTES NOTE 1. Maximum permissible temperatures (øF): Cylinder head 390 (bayonet thermocouple) Cylinder base 315 Oil inlet All models except 6A-350-C1R/C1L 235 6A-350-C1R/C1L 230 NOTE 2. Fuel pressure limits (p.s.i.): Min Max All models except 6A-350-C1R/C1L Inlet to carburetor 0.5 6.0 6A-350-C1R/C1L Inlet to fuel pump 1.4 8.5 Oil pressure limits (p.s.i.): Idle Normal Operation Inlet to engine All models except 6A-350-C1R/C1L 25 55-80* 6A-350-C1R/C1L 25 55-81.2* *50 p.s.i. instead of 55 p.s.i. with external filter NOTE 3. 6V Model Engines (Vertical) (a) With crankshaft flange tilted 15ø from vertical in the direction of the oil pan. (b) With crankshaft flange tilted 15ø from vertical in the direction of the crankcase cover. 6A Model Engines (Horizontal) (c) 15ø Nose down (d) 20ø Nose up NOTE 4. The following accessory drives are provided: ACCESSORY Type of Drive Pad Rotation Facing Drive Pad Speed Ratio to Crankshaft Max. Torque (in. lb.) Cont. Static Maximum Overhang Moment (in. lb.) Starter Generator Tachometer Fuel Pump Special Special AND 10005 AND 10000 (modified) CC CC CC CC 11.44:1 1.50:1 0.50:1 1.50:1 140 25 2 5 300 70 6 600 90 75 3 7 "C" - Clockwise facing engine drive pad, "CC" - counter clockwise facing engine drive pad TCDS E9EA PAGE 7 NOTE 5. The following accessory drives are provided: ACCESSORY Type of Drive Pad Rotation Facing Drive Pad Speed Ratio to Crankshaft Max. Torque (in. lb.) Cont. Static Maximum Overhang Moment (in. lb.) Starter Alternator Tachometer Fuel Pump or Fuel Pump (See Note 14) Propeller Governor Vacuum Pump Special Belt AND 10005 Diaphragm Special AND 20010 AND 20000 CC CC CC Plunger CC CC C 11.44:1 1.60:1 0.50:1 1.65:1 1.65:1 0.847:1 0.847:1 140 100 7 100 100 125 125 450 800 50 800 800 825 825 90 --- 5 30 50.6 25 25 "C" - clockwise facing engine drive pad, "CC" - counter clockwise facing engine drive pad NOTE 6. These engines are approved for helicopter application. NOTE 7. Power tolerance for production engines is +4%, -3% of the nominal rating.. NOTE 8. When the MA4-5 carburetor is used on the 6A-350-C1 for improved acceleration the takeoff and Max. Continuous ratings are 215 hp. at 2800 r.p.m. NOTE 9. The above models incorporate additional characteristics as follows: Model Characteristics 6A-350-C1A Same as -C1 except for geared starter located over the top of the crankcase. 6A-350-C2 Same as -C1 except for induction system piping. 6A-350-C2A Same as -C2 except for modified mounts and induction system piping. 6A-350-C1R Same as -C1 except for new starter, alternator, and voltage regulator to be compatible with 12 volt system; modified starter gear and damper assembly; new propeller shaft seal and speed governor; relocated starting injectors; and oil sump modification. 6A-350-C1L Same as -C1R except for new starter, magnetos, propeller speed governor, camshaft, and oil pump drive gear to be compatible with engines opposite direction of rotation. 6A-350-D1 Differs from -D also in location of the carburetor. 6A-350-D1A Has -D1 carburetor location; otherwise same as -D. 6A-350-D1B Derated D1A with crankshaft torsional damper. 6V-350-B Same as -A except for zone pipes, oil tank and other external hardware. TCDS E9EA PAGE 8 NOTE 10. Service Bulletins, structural repair manuals, vendor manuals, aircraft flight manuals, and SERVICE INFORMATION: Each of the documents listed below must state that it is approved by the European Aviation Safety Agency (EASA) or, for approvals made before September 28, 2003 by the General Inspectorate of Civil Aviation of Poland. 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, and • Overhaul and maintenance manuals. These approvals pertain to the type design only. NOTE 11. The following accessory drives are provided: ACCESSORY Type of Drive Pad Direction of Rotation Facing Engine Drive Pad Model C1R Model C1L Speed Ratio to Crankshaft Max. Torque (in. lb.) Cont. Static Maximum Overhang Moment (in. lb.) Starter Alternator Tachometer Fuel Pump or Fuel Pump (See Note 14) Propeller Governor Vacuum Pump Special Belt AND 10005 Diaphragm Special AND 20010 AND 20000 CC CC CC Plunger CC CC C C C C Plunger C C CC 11.44:1 2.40:1 0.50:1 1.65:1 1.65.1 0.847:1 0.847:1 140 100 7 10010 0125 125 450 800 50 800 800 825 825 90 --- 5 30 50.6 25 25 NOTE 12. NOTE 13. NOTE 14. Ignition advance angle is individually adjusted for each engine in the range 28-32 BTC. This angle is marked on the nameplate and recorded in engine document. Fuels and oils that meet the following specifications and the specified grades are acceptable for all engine models. Fuel - ASTM-D-910, M1L-G-5572, DERD 2485, AIR 3401, GOST 1012-72. Oil - SAE-J-1966(M1L-L-6082), DERD 2472, or SAE-J-22851(M1L-L-22851), DERD 2450. Engine Serial Numbers xxxxx130 and above incorporate slide vane fuel pump drive instead of diaphragm pump drive. The serial number of these engines incorporates letter “S”. When slide vane fuel pump drive is installed in service, the suffix “/S” is affixed to the serial number. Fuel pump PLL-7-6R (WSK Part No 26.11.8300) is approved for 6A-350-Cxx engines (excluding 6A- 350-C1L). Fuel pump PLL-7-6L (WSK Part No 26.11.8310) is approved for 6A-350-C1L Engine. These pumps comply with Federal Aviation Regulation Part 33, effective February 1, 1965, including amendments 33-1 to 33-5. ---THE END---