TCDS E-228

DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION O-435, -A, -A2 O-435-B (O-435-5) O-435-C (O-435-1) O-435-C1 (O-435-11) O-435-C2 (O-435-13) O-435-K O-435-K1 (O-435-4) E-228 Revision 17 Lycoming Engines GO-435 GO-435-C2 (O-435-17) GO-435-C2A, -C2A2 GO-435-C2B, -C2B1, -C2B2 GO-435-C2C, -C2D, -C2E GO-435-D1 June 23, 2010 TYPE CERTIFICATE DATA SHEET NO. E-228 Engines of models described herein conforming with this data sheet (which is a part of type certificate No. E-228) 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 Civil Air Regulations provided they are installed, operated and maintained as prescribed by the approved manufacturer's manuals and other approved instructions. Type Certificate Holder Lycoming Engines An Operating Division of AVCO Corporation Williamsport, Pennsylvania 17701 Type Certificate Holder Record Lycoming Division AVCO Corporation., Williamsport, PA. transferred TC 284 to Lycoming Engines, An Operating Division of AVCO Corporation on June 23, 2010 Model Lycoming O-435 O-435-B O-435-A2 O-435-K, K1 O-435-A Type 6H0A - - - - - - - - Reduction gearing ratio Direct Drive - - - - - - - - Rating Max. continuous, hp., r.p.m., S.L. pressure altitude 175-2300-S.L. 235-3000-S.L. 225-3000-S.L. 240-3000-S.L. (-K) 250-3200-S.L. (K1) 190-2550-S.L. Takeoff, 5 min., hp., r.p.m. at full throttle 175-2300 235-3000 225-3000 - - 190-2550 Fuel (Min. grade aviation gasoline) 73 100 91/98 - - 80 Lubricating oil Lycoming Spec. No. 301-G* - - - - - - - - Bore and stroke, in. 4.875 x 3.875 - - - - - - - - Displacement, cu. in. 434 - - - - - - - - Compression ratio 6.25:1 7.5:1 - - 7.3:1 6.5:1 Weight (dry), lb. 347 362 365 405 348 (with -8 mag.) 342 (with -20 mag.) C.G. location (dry) Fwd. of rear mounting face, in. 10.6 - - — 10.9 — From prop. shaft C.L., in. 0.5 below - - — 0.3 below — C.G. location (with starter and generator) Fwd. of rear mounting face, in. 8.9 — 9.6 — 9.6 Below prop. shaft C.L., in. 0.5 — 0.6 — 0.6 Propeller shaft, SAE No. 20 20 (See NOTE 5) 20 - - - - * See latest edition of Lycoming Service Instruction 1014 Page No. 1 2 3 4 5 6 Rev. No. 17 17 17 16 16 17 Model Lycoming (cont'd) O-435 O-435-B O-435-A2 O-435-K, K1 O-435-A Carburetion MA-4* MA-4-5* - - - - MA-4-5* or PS-5C# Ignition, dual SF6LN-8 Magnetos+ SF6LN-8+ or Edison- Splitdorf SF6L-D SF6LN-8+ - - SF6LN-8+ or S6LN-20+ Ignition timing, °BTC 25 - - - - - - 20 Spark plugs See NOTE 12 - - - - - - - - Oil sump cap., qts. (wet sump) 12 - - - - - - - - Usable oil sump cap., qts. (wet sump) 9-1/4 - - - - - - - - NOTES 1,2,3,6,7,8, 12 1,2,3,4,5,6,7,8 ,12 1,2,3,6,7,12 1,2,3,4, 6,7,10,12 1,2,3,6,7,12 Model Lycoming O-435-C1 O-435-C, -C2 GO-435 GO-435-C2, -C2A, -C2A2, -C2B, -C2B1, -C2B2, -C2C, -C2D, -C2E GO-435-D1 Type 6H0A - - - - - - - - Reduction gearing ratio Direct Drive - - .642 - - - - Rating Max. continuous, hp., r.p.m., S.L. pressure altitude 175-2300-S.L. - - 210-3000-S.L. 240-3000-S.L. or 245-3100-S.L. - - Takeoff, 5 min., hp., r.p.m. at full throttle 175-2300 - - 210-3000 260-3400 - - Fuel (Min. grade aviation gasoline) 80 80 - - (See NOTE 9) - - Lubricating oil Lycoming Spec. No. 301-G** - - - - - - - - Bore and stroke, in. 4.875 x 3.875 - - - - - - - - Displacement, cu. in. 434 - - - - - - - - Compression ratio 6.25:1 - - - - 7.3:1 - - Weight (dry), lb. 366 356 (-C) 368 (-C2) 407 438 (C2A) 432 (C2A2) 430 (C2B) 422 (C2, C2C) 420 (C2D, C2E) 458 C.G. location (dry) Fwd. of rear mounting face, in. 10.2 10.6 (-C) 10.2 (-C2) 11.0 20.0 (C2A) 19.70 (C2A2) 19.30 (C2) 19.4 (C2B, C2C, C2D) 19.08 (C2E) 8.9 From prop. shaft C.L., in. 0.5 be low - - 0.7 below 0.04 right (C2A, C2A2) 0.41 below (C2A2) 0.05 left (C2B, C2C, C2D) 0.5 below (C2, C2A, C2B, C2C, C2D, C2E) .03 below .13 left ** See latest edition of Lycoming Service Instruction 1014 *Volare formerly PAC, formerly Marvel-Schebler # PAC formerly Bendix + TCM formerly Bendix-Scintilla Model Lycoming O-435-C1 O-435-C, -C2 GO-435 GO-435-C2, -C2A, -C2A2, -C2B, -C2B1, -C2B2, -C2C, -C2D, -C2E GO-435-D1 C.G. location (with starter and generator) Fwd. of rear mounting face, in. 8.9 — — 10.0 (-A2) — Below prop. shaft C.L., in. 0.5 — — 0.4 (-A2) — Propeller shaft, SAE No. 20 - - - - 20 (See NOTE 5) 20 Carburetion MA-4* MA-4SPA* MA-4-5* MA-4-5* or PS-5BD# - - Ignition, dual SF6LN-8 Magnetos+ SF6LN-8+ or Edison- Splitdorf SF6LN-8+ or S6LN-50+, -51+ or S6LN-20+, -21+ S6RN-50+,-51+ Ignition timing, °BTC 25 - - 25 - - - - Spark plugs See NOTE 12 - - - - - - - - Oil sump cap., qts. (wet sump) 12 - - - - - - - - Usable oil sump cap., qts. (wet sump) 9-1/4 - - - - - - - - NOTES 1,2,3,4,6,7,12 1,2,3, 4,6,7,12 1,2,3,4,6,7,8,1 1, 12 1,2,3,5,6,7,8,9,11, 12 1,2,3,7,9,11, 12 "- -" indicates "same as preceding model" "—" indicates "does not apply" *Volare formerly PAC, formerly Marvel-Schebler #PAC formerly Bendix + TCM formerly Bendix-Scintilla Certification basis Date Type Certificate Regulation & Amendments Model Date of Application E-228 Issued/Revised CAR 13 As Amended to November 15, 1940 O-435 February 11, 1942 O-435-A July 18, 1941 February 11, 1942 CAR 13 Effective August 1, 1941 O-435-B August 25, 1942 October 7, 1943 O-435-5 August 25, 1942 October 7, 1943 O-435-C December 3, 1942 January 11, 1943 O-435-1 January 11, 1943 O-435 Canceled February 25, 1944 GO-435 August 12, 1944 August 30, 1944 O-435-C1 March 14, 1946 January 2, 1948 O-435-11 March 14, 1946 January 2, 1948 O-435-C2 October 9, 1947 January 2, 1948 O-435-13 October 9, 1947 January 2, 1948 O-435-A2 January 10, 1949 October 19, 1949 GO-435-A2 July 14, 1949 October 19, 1949 GO-435-C2 July 14, 1949 October 19, 1949 O-435-B Canceled November 2, 1950 GO-435 Canceled November 2, 1950 CAR 13 Effective August 1, 1949 GO-435-C2A July 18, 1950 January 2, 1951 As Amended By 13-1 O-435-A3 September 28, 1950 January 5, 1951 O-435-K January 12, 1951 January 24, 1951 O-435-4 January 12, 1951 March 30, 1951 13-1 and 13-2 O-435-K1 March 19, 1951 March 30, 1951 CAR 13 Effective March 5, 1952 GO-435-C2B October 30, 1952 November 6, 1952 As Amended By 13-1 GO-435-C2C Se ptember 25, 1953 November 24, 1953 GO-435-D1 September 25, 1953 O-435-17 December 18, 1953 December 30, 1953 GO-435-C2D March 19, 1954 July 20, 1954 O-435-A3 Canceled February 8, 1955 GO-435-A2 Canceled February 8, 1955 Date Type Certificate Regulation & Amendments Model Date of Application E-228 Issued/Revised As Amended by 13-1 (cont'd) GO-435-C2A Canceled February 8, 1955 13-1 and 13-2 GO-435-C2B1 January 11, 1955 February 8, 1955 GO-435-C2A Reinstated July 15, 1955 GO-435-C2B2 February 7, 1956 February 28, 1956 GO-435-C2C Canceled July 5, 1956 GO-435-C2D Canceled July 5, 1956 CAR 13 Effective June 15, 1956 GO-435- C2E August 22, 1956 September 27, 1956 As Amended By 13-1 GO-435-C2A2 October 24, 1957 November 1, 1957 Production basis Production Certificate No. 3 NOTE 1. Maximum permissible temperatures are as follows: Models Cylinder Head Cylinder Barrel Oil Inlet Spark Plug Gasket Well Type Thermocouple Thermocouple O-435-B 540°F 515°F 325°F 225°F O-435, -A, -A2, -C, -C1, -C2; GO-435 525°F 500°F 325°F 225°F GO-435-C2, -C2B, -C2B1, -D1; O-435-A3, -K, -K1, -C2D, -C2A, -C2A2 — 475°F 325°F 225°F NOTE 2. Minimum (p.s.i.) Maximum (p.s.i.) Fuel pressure limits - Marvel carburetor Fuel pressure limits - Bendix carburetor Oil pressure limits - (Normal operation) 0.5 9.0 60.0 5.0 15.0 85.0 NOTE 3. The above models incorporate add itional different characteristics as follows: O-435-A Similar to O-435. Incorporates provisions for automotive type accessories. O-435-B Similar to O-435-A except compression ra tio higher ratings and provisions for AN type accessories. O-435-C Similar to O-435A. Has provisions for AN type accessories. O-435-C1 Similar to O-435-C. Has revised type valv es, valve guides, and accessory case with generator and starter drive only. O-435-C2 Similar to O-435-C1 except has provisions for O-435-C accessories carburetor. GO-435-C2A2 Similar to GO-435-C2B2 except incorporates a dry sump and does not have provisions for hydraulic propeller control or governor. GO-435-C2A Similar to GO-435-C2A2 except incorporates S6LN-20, -21 magnetos. O-435-A2 Similar to O-435-B. Has redesigned improve d crankcase, cylinders, valves and valve seats, exhaust valve guides and rocker shaft bushing. Also, O-435-A2 has provisions for automotive type accessories. O-435-K Similar to O-435-A2 except incorpor ates GO-435-C2 accessory case and crankcase. O-435-K1 Similar to O-435-K except maximum conti nuous rating increased and generator pad omitted. GO-435 Similar to O-435-C. Incorporates six 3rd order crankshaft torsional vibration dampers and reduction gearing. GO-435-C2 Similar to GO-435. Incorporates improved crankcase and cylinder assembly. NOTE 3. (cont'd) GO-435-C2B Similar to GO-435-C2 except has pr ovisions for hydraulic propeller and governor. GO-435-C2B1 Similar to GO-435-C2B except incorpor ates dual generator and vacuum pump drive. GO-435-C2B2 Similar toGO-435-C2B except incorporates S6LN-20, -21 magnetos. GO-435-C2E Similar to GO-435-C2 except incorporates S6LN-20, -21 magnetos. GO-435-D1 Similar to GO-435-C2B except incorporat es dry sump and crosswise accessory drives. NOTE 4. Military models O-435-1, O-435-4, O-435-5, O-435-11, O-435-13, and O-435-17 are identical to the corresponding civil designated engines. When installed in certificated aircraft, the corresponding commercial model designations and type certificate Nos. should be added to the engine data plate. NOTE 5. Model O-435-B, Serial No. 103-12, incorporates a special short crankshaft Part No. 66510 with a detachable flanged propeller hub, Part No. 66511. Model GO-435-C2D incorporates a flanged type propeller shaft with 4-7/8" diameter flange and 4" diameter bolt circle. NOTE 6. Deleted. (Accessories such as generators, fuel pumps, etc., previously listed in NOTE 6 are satisfactory for continued use with these engines. Accessories of these types are not integral engine accessories and therefore are not evaluated for approval during engine certification testing. The airworthiness of such accessories is substantiated during aircraft-installation system approval. The suitability of the accessory to the engine mounting provisions as described in NOTE 7 of this data sheet must be determined when processing such approvals.) NOTE 7. The following accessory drive provisions are available: Drive O-435-A2 O-435- C O-435-C1 O-435- C2 GO-435-C2A GO-435- C2A2 O-435-K, -K1 GO-435-C2 GO-435-C2B GO-435-C2B2 GO-435-C2C GO-435-C2D GO-435- C2B1 GO-435-D1 Starter X Starter X X X X X X Starter X Generator X Generator X X Generator X X X** Generator X Generator X Generator X Fuel Pump X Fuel Pump X X X X X X Fuel Pump X Vacuum Pump X Vacuum Pump X X X X X Vacuum Pump X Vacuum Pump X Tachometer X X Tachometer X X X X X X X Hydraulic Pump X Prop. Governor X X X Dual Drive: Prop Governor X X Vacuum Pump X X Drive Rotation Facing Pad Drive Ratio Max. Torque (in. -lb.) Max. Overhang Moment (in. -lb.) Cont Static Starter C 13.462:1 - 240 150 Starter C 1.000:1 - 3000 80 Starter 1.000:1 - 12000 300 Generator CC 1.857:1 30 65 175 Generator CC 1.385:1 175 500 200 Generator C 1.250:1 175 500 200 Generator C 2.577:1 90 250 200 Generator C 2.600:1 500 2200 400 Generator C 2.569:1 90 250 200 Fuel Pump Plunger Operated .500:1 - - 10 Fuel Pump C 1.000:1 50 450 10 Fuel Pump CC .803:1 25 450 25 Vacuum Pump C 1.292:1 60 175 25 Vacuum Pump C 1.333:1 100 800 25 Vacuum Pump C 1.219:1 200 800 25 Vacuum Pump C 1.250:1 100 800 25 Tachometer CC .500:1 7 50 5 Tachometer C .500:1 7 50 5 Hydraulic Pump C 1.083:1 300 1650 75 Prop. Governor C .801:1 125 825 - Dual Drive: Prop Governor CC 1.013:1 50 450 25 Vacuum Pump CC 1.013:1 50 450 25 (Or Total of 100 -C2 & -C2E) Also the Hartzell "I" Drive, P/N C192 weighing 3 lbs. is an approved dual drive unit for installation on this drive with the following provisions: Vacuum Pump Provision (Optional) Hydraulic Pump Provision (Optional) Maximum weight, lbs. 4.5 Maximum weight, lbs. 2.4 Maximum overhand moment, in.-lbs. 11.2 Maximum overhang moment, in.-lbs. 7.0 Maximum continuous torque, in.-lbs. 16.0 Maximum continuous torque, in.-lbs. 17.5 Hartzell Propeller Company, Installation Instruction No. 2 dated May 4, 1951, explains details for accomplishing installation of the C192 "T" Drive. *C = Clockwise, CC = Counter Clockwise. **Omitted from -K1. NOTE 8. Approval of the following models have been canceled. No engines of the following models manufactured after the date shown or with serial numbers higher than those listed below are eligible for use in certificated aircraft: Model Date Serial No. O-435 2-25-44 493-8 O-435-B 11-2-50 157-12 GO-435 11-2-50 105-13 GO-435-C2C, -C2D 7-5-56  No engines of the following models ar e in operation in this country: O-435-A3 GO-435-A2 NOTE 9. Marvel MA-4-5 carburetor with setting 10-3391-1 may be used with either 80/87 or 91/98 grade fuel, but with setting 10-3391 only 91/98 grade fuel should be used. Either 80/87 or 91/98 grade fuel may be used with Bendix PS-5BD carburetor. NOTE 10. The O-435-K1 engine has been approve d specifically for helicopter installation. NOTE 11. The GO-435 series engines incorporate crankshafts with six 3rd order torsional vibration dampers unless a "-6" follows the model designation. Engines so designated have five 3rd order and one 6th order torsional dampers. NOTE 12. Spark plugs: See latest revision of Lycomi ng Service Instruction No. 1042 for approved equipment. ....END....