TCDS E24EA

* PAGE 1 2 3 4 REV. 6 6 5 5 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 E24EA TCDS NUMBER E24EA REVISION: 6* DATE: April 30, 2013 Franklin Sp. z.o.o. MODELS: FRANKLIN 2A-120-A 2A-120-B 2A-120-C 2A-120-D Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E24EA) 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 E24EA to Franklin Sp. z.o.o. on August 17, 2006 I. MODELS 2A-120-A 2A-120-B 2A-120-C 2A -120-C1 2A-120-D TYPE 2HOA Horizontally-M ounted 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 60-3200 60-3200 - - - - - - - - - - - - - - - - FUEL Minimum grade aviation gasoline 100/130 - - - - - - - - LUBRICATING OIL 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 4.625 x 3.5 117 8.5:1 - - - - - - - - - - - - - - - - - - - - - - - - TCDS E24EA PAGE 2 I. MODELS (Continued) 2A-120-A 2A -120-B 2A-120-C 2A-120-C1 2A-120-D WEIGHT (DRY) (lb) 133 126 133 - - 129 CENTER OF GRAVITY (in) (with all accessories) Forward from rear face of crankcase Above C.L. of crankshaft 1.49 .05 3.44 1.2 below 1.68 .05 - - - - 3.29 .57 below PROPELLER SHAFT SAE No. 2, six 3/8 in. bolts on 4.75 in. circle - - - - SAE No. 2, six 3/8 in. bolts on 4.75 in. circle and six M8 bolts on 3.98 in. circle (simultaneously) - - CARBURETION Marvel-Schebler MA-3A - - - - - - - - IGNITION (dual) Slick 2070 - - - - - - - - TIMING, øBTC 36 - - - - - - - - SPARK PLUGS AC 273, Champion RHB32E, RHB36D, RHB36W - - - - - - - - OIL SUMP CAPACITY, QT. 2.5 - - 4 - - - - USEABLE OIL, QT. (starting with full tank) 15ø nose down 20ø nose up 2.2 2.3 - - - - 2.0 2.8 - - - - - - - - NOTES 1-6 - - - - 1-2, 4-7 1-6 CERTIFICATION BASIS FAR Part 33, effective February 1, 1965, as amended by 33-1 to 33-3, inclusive. Type Certificate E24EA issued/revised: Date of Date TC Model Application Issued/Revised 2A-120-A 09/23/70 04/26/71 2A-120-B 09/23/70 01/29/71 2A-120-C 02/09/72 07/26/72 2A-120-D 02/09/72 07/26/72 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 E24EA. Effective September 28, 2003, the European Aviation Safety Agency (EASA) began oversight of this product on behalf of Poland. TCDS E24EA PAGE 3 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 insta llation on U.S. registered aircraft, each new engine to be exported to the United States with 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 E24EU, 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. NOTES NOTE 1. Maximum permissible temperatures (øF): Model 2A-120-A, B, C, D Model 2A-120-C1 Cylinder head 400 (bayonet thermocouple) 395 (bayonet thermocouple) Cylinder base 320 320 Oil inlet 285 260 NOTE 2. Fuel pressure limits: Pressure Feed Gravity Feed Inlet to fuel pump 6 p.s.i. (max) 5" fuel (min) Oil pressure limits: Idle 25 p.s.i. Normal operation 55-95 p.s.i. NOTE 3. The following accessory drives are pr ovided (2A-120-B, -D has tachometer only): 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 Special Belt AND 10005 Diaphragm CC CC CC Plunger 11.44:1 1.08:1 0.50:1 1.08:1 140 70 7 100 450 800 50 800 90 60 5 30 "C" - clockwise facing engine drive pad, "CC" - counter clockwise facing engine drive pad NOTE 4. Power tolerance for production engine s is +4%, -0% of the nominal rating. TCDS E24EA PAGE 4 NOTE 5. The following engines incorporate the additional detailed characteristics: 2A-120 Model Characteristics -A Basic model. -B Similar to -A but does not incorporate starter, alternator or fuel pump. -C Similar to -A except for increased oil sump capacity and revised induction system. -D Similar to -C but does not incorporate starter, alternator or fuel pump. -C1 Similar to -C1 except for a modified lubrication system. NOTE 6. 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 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 7. 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 Vacuum Pump or Hydraulic pump Special Belt AND 10005 Diaphragm AND 20000 CC CC CC Plunger CC 11.44:1 1.08:1 0.50:1 1.08:1 1.08:1 140 70 7 100 125 450 800 50 800 570 90 60 5 5 25 CC" - counter clockwise facing engine drive pad ---THE END---