TCDS E5EA

* PAGE 1 2 3 4 REV. 5 5 4 4 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 E5EA TCDS NUMBER E5EA REVISION: 5* DATE: April 30, 2013 Franklin Sp. z.o.o. MODELS: FRANKLIN 6AS-335-A 6AS-335-B Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E5EA) 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. U l . C h e l m i ńska 208 86-300 Grudzi ądz Poland TYPE CERTIFICATE (TC) HOLDER RECORD WSK-PZL-RZESZ OW transferred TC E5EA to Franklin Sp. z.o.o. on August 17, 2006 I. MODELS 6AS-335-A 6AS-335-B TYPE 6HOA Horizontally-Mounted Di rect Drive Turbosupercharged RATINGS Maximum Continuous hp, r.p.m., in. Hg. at: Critical pressure altitude, ft. Sea level pressure altitude Takeoff (5 min.) hp, r.p.m., in. Hg. at: Critical pressure altitude, ft. Sea level pressure altitude 240-3200-40.0-15,000 240-3200-37.5-S.L. 260-3200-41.0-10,000 260-3200-41.0-S.L. 240-3200-42.0-15,000 240-3200-38.0-S.L. 260-3200-43.0-10,000 - - FUEL Minimum grade aviation gasoline 100/130 - - LUBRICATING OIL (Engine and Turbo) MIL-L-6082 or MIL-L-22851 - - OIL GRADE above 40øF ambient air temp. below 40øF ambient air temp. SAE 50 SAE 30 - - - - COMPRESSION Bore and stroke, in. Displacement, cu. in. Compression ratio 4.5 x 3.5 335 7.0:1 - - - - - - WEIGHT (DRY) (lb) 358 - - TCDS E5EA PAGE 2 I. MODELS (Continued) 6AS-335-A 6AS-335-B CENTER OF GRAVITY (in) (with all accessories) Forward from rear face of crankcase Above C.L. of crankshaft 8.5 5.0 - - - - DRIVE SHAFT END SAE ARP 502, six 1/2 in. bolts on 4 in. circle - - CARBURETION Marvel-Schebler MA-5 Marvel-Schebler MA6 TURBOSUPERCHARGER AiResearch TE 0634 - - IGNITION Bendix S6RN-21 - - TIMING, øBTC 30 - - SPARK PLUGS Champion RHB32E or RHB32N - - OIL SUMP CAPACITY, QT. 8.8 - - USEABLE OIL, QT. (starting with full tank) 15ø nose down 20ø nose up 6.8 5.8 - - - - NOTES 1-6, 8 1-8 CERTIFICATION BASIS CAR 13, effective June 15, 1956, as amended by 13-1 to 13-5, inclusive, for 6AS-335-A engine model. CAR 13, effective June 15, 1956, as amended by 13-1 to 13-6, inclusive, for 6AS-335-B engine model. Date of Date TC Model Application Issued/Revised 6AS-335-A 03/15/63 04/14/64 6AS-335-B 11/30/64 02/23/65 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. April 30, 2013 The General Inspectorate of Civil Aviation of Poland originally type certificated this engine. The FAA validated this product under U.S. Type Certificate Number E5EA. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of Poland. PRODUCTION BASIS 1. Production Certifi cate 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 re placement 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 E5EA, 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 E5EA PAGE 3 NOTES NOTE 1. Maximum permissible temperatures (øF): Cylinder head 390 (bayonet thermocouple) Cylinder base 315 Oil inlet 235 Carburetor inlet air 225 NOTE 2. Fuel pressure limits: M a x M i n Inlet to fuel pump 14 p.s.i. 12 p.s.i. Oil pressure limits: Idle - - 25 p.s.i. Normal operation - - 55-80 p.s.i. Exhaust back pressure limit (max.): 45 in. Hg. (measured 9 in. to rear of No. 1 cylinder) NOTE 3. 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 Max. Overhang Moment (in-lb.) Starter Generator Tachometer Fuel Pump Special Special AND 10005 AND 10000 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 "CC" - counter clockwise facing engine drive pad NOTE 4. These engines are approved for helicopter application and operation in a horizontal mount installation. NOTE 5. These engines are equipped with an AiRe search model TE0634 turbosupercharger, which meets the containment requirements of CAR 13.116 and does not require external protection. Performance data on the above engines are presented in Franklin Curve Numbers PE-4112, 4113 and 4114. NOTE 6. Power tolerance for production engine s is +4%, -3% of the nominal rating. NOTE 7. The 6AS-335-B differs from the -A in car buretor location and induction system piping.. TCDS E5EA PAGE 4 NOTE 8. 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. ---THE END---