TCDS E-229

Page No. 1 2 3 4 5 Rev. No. 14 14 13 14 14 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E-229 Revision 14 AVCO Lycoming 0-290, -A, -AP, -B (0-290-1), -C (0-290-3), -CP, -D (0-290-11), -D2, -D2A, -D2B, -D2C January 31, 2020 TYPE CERTIFICATE DATA SHEET NO. E-229 Engines of models described herein conforming with this data sheet (which is a part of type certificate No. 229) and other approved data on file with the Federal Aviation Agency, 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 Division AVCO Corporation Williamsport, Pennsylvania 17701 Model Lycoming 0-290 0-290-A, -AP 0-290-B 0-290-C, -CP Type 4H0A Direct Drive - - - - - - - - - - - - Rating Max. continuous, hp., r.p.m., Sea level pressure altitude 125-2450-S.L. 125-2600-S.L. 125-2600-S.L. - - Takeoff, hp., r.p.m. , at full throttle 125-2450 1250-2600 or 130-2800 (5 min.) 130-2800 (5 min.) - - Fuel (Minimum grade aviation gasoline)* 73 - - - - - - Bore and stroke, in. 4.875 x 3.875 - - - - - - Displacement, cu. in. 269 - - - - - - Compression ratio 6.25:1 6.5:1 - - - - Weight (dry), lbs. 244 251 (with SR4L-8 or N-8 magnetos); 245 (with N-20 or N-21 magnetos) 247 238 C.G. location (dry) Fwd. of mounting face, in. 7.0 — 7.0 - - From front face of rear propeller mounting flange, in. — — — — Off propeller shaft C.L., in. .3 (Above) — .2 .1 (Below) C.G. location (with all accessories) Fwd. of mounting face, in. 5.1 4.7 — — From front face of rear propeller mounting flange, in. — — — — Off propeller shaft C.L., in. .3 (Above) .6 (Below) — — Propeller shaft (see NOTE 4) Integral flanged hub 8-3/8 bolts 5-1/4 circle - - - - - - or SAE spline type No. 10 - - - - - - Carburetion MA-3 MA-3SPA MA-3SPAA MA-3SPA "- - indicates "same as preceding model." "—" indicates "does not apply." * For alternate fuel grades, see latest revision of Lycoming Service Instruction 1070. E-229 2 Model Lycoming (cont'd) 0-290 0-290-A, -AP 0-290-B 0-290-C, -CP Ignition, Dual+ TCM● SF4L-8 or SF4LN-8 magnetos SF4L-8, SF4LN-8, -20 or -21 SF4L-8 or SF4LN-8 - - Ignition timing, °BTC 25 20 - - - - Spark plugs See NOTE 8 - - - - - - Oil sump capacity, Qts. 8 - - - - - - Usable oil sump capacity, Qts. 6 - - - - - - NOTES 1,2,3,4,5,6,8 - - - - - - Model Lycoming 0-290D 0-290-D2, -D2A 0-290-D2B 0-290-D2C Type 4HOA Direct Drive - - - - - - - - - - - - Rating Max. continuous, hp., r.p.m., Sea level pressure altitude 125-2600-S.L. 135-2600-S.L. - - - - Takeoff, hp., r.p.m. , at full throttle 130-2800 (5 min.) 140-2800 (5 min.) - - - - Fuel (Minimum grade aviation gasoline)* 80 80/87 - - - - Bore and stroke, in. 4.875 X 3.875 - - - - - - Displacement, cu. in. 269 - - - - - - Compression ratio 6.5:1 7.5:1 7.00:1 - - Weight (dry), lbs. 230 233 (-D2) 236 (-D2A) 236 235 C.G. location (dry) Fwd. of mounting face, in. — — — — From front face of rear propeller mounting flange, in. 15.1 - - - - — Off propeller shaft C.L., in. .7 .1 (Right) - - - - - - - - — — C.G. location (with all accessories) Fwd. of mounting face, in. — — — — From front face of rear propeller mounting flange, in. 14.21 - - — 14.21 Off propeller shaft C.L., in. 1.27 (Below) .06 (Right) - - - - — — 1.27 (Below) .06 (Right) Propeller shaft (see NOTE 4) Integral flanged hub Flange type SAE 2 - - - - - - or SAE spline type No. — — — — Carburetion MA-3SPA - - - - - - Ignition, Dual+ S4LN-20 (Right), S4LN-21 (Left) - - - - S4LN-204 S4LN-200 Ignition timing, °BTC 25 18 25 25 Spark plugs See NOTE 8 - - - - - - Oil sump capacity, Qts. 8 - - - - - - Usable oil sump capacity, Qts. 6 - - - - - - NOTES 1,2,3,4,5,8 1,2,3,4,5,6,7,8 1,2,3,4,5,7,8 - - "- - indicates "same as preceding model." "—" indicates "does not apply." * For alternate fuel grades, see latest revision of Lycoming Service Instruction 1070. ● Teledyne (TCM formally Scintilla) +For alternate ignition systems, see latest revision of Lycoming Service Instruction 1443. 3 E-229 CERTIFICATION BASIS Regulation & Amendments Model Date of Application Date Type Certificate No. 229 Issued/Revised CAR 13 Effective August 1, 1941 As Amended by 13-1 CAR 13 Effective March 5, 1952 As Amended By 13-1 & 13-2 CAR 13 Effective June 15, 1956 As amended by 13-1 13-2 & 13-3 0-290-A 0-290 0-290-C 0-290-B 0-290-AP, -CP 0-290-D 0-290-D2 0-290-A, -AP, -B, -C, -CP 0-290-D2A 0-290-D2B 0-290-D2A 0-290-11 0-290-D2C March 18, 1942 June 15, 1942 November 23, 1942 November 28, 1942 July 17, 1944 July 22, 1949 June 28, 1950 March 31, 1953 September 23, 1954 December 6, 1957 April 17, 1961 July 27, 1942 July 27, 1942 January 22, 1943 January 22, 1943 July 21, 1944 December 13, 1949 May 1, 1952 Canceled Nov 2, 1950 April 20, 1953 September 30, 1954 Canceled July 5, 1956 January 6, 1958 May 8, 1961 Production basis Production Certificate No. 3 NOTE 1. Maximum permissible temperatures are as follows: Model Cylinder head (Spark plug washer thermocouple) Cylinder head (Well- type thermocouple) Cylinder barrel Oil Inlet 0-290 only 0-290-A, -AP, -B, -C, -CP 0-290-D, -D2, -D2A, -D2B, -D2C 550°F 525°F 525°F 525°F 500°F 500°F 300°F 325°F 325°F 200°F 220°F 245°F NOTE 2. Minimum Maximum Fuel pressure limits 0.5 p.s.i. 6.0 p.s.i. Oil pressure limits (Normal operation) 60 p.s.i. 90 p.s.i. (Idling 25 p.s.i.) (Starting and warm-up) 100 p.s.i. NOTE 3. Deleted. Accessories such as generators, starters, fuel and vacuum pumps, etc. previously listed in NOTE 3 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 approvals. The suitability of the accessory to the engine mounting provisions as described in NOTE 4 of this data sheet must be determined when processing such approvals. E-229 4 NOTE 4. The following accessory drive provisions are available. Engine Model Drive O-290, -C, -CP O-290- A, -AP O-290-B O-290-D, -D2, -D2a, -D2b, -D2C *Direction of Rotation Facing Engine Pad Speed X Crankshaft RPM Maximum Torque (in. -lb.) Cont. Static Maximum Overhang Moment (in. -lb.) Starter■ Yes Yes C 1.000:1 — 3000 80 Starter■ Yes C 13.500:1 — 240 150 Starter■ Yes CC 13.556:1 — 450 150 Generator■ Yes CC 1.385:1 175 500 200 Generator■ Yes CC 1.500:1 30 65 175 Generator■ Yes C 1.250:1 175 500 200 Generator■ Yes C 1.910:1 60 120 175 Generator■ Yes C 2.500:1 60 120 175 Tachometer Yes Yes C 0.500:1 20 60 5 Tachometer Yes Yes C 0.500:1 7 50 5 Fuel Pump Yes C 1.000:1 50 450 10 Fuel Pump Yes Yes Plunger Operated 0.500:1 — — 10 Vacuum Pump Yes C 1.333:1 50 450 25 Vacuum Pump Yes C 1.292:1 60 175 25 Vacuum Pump Yes C 1.000:1 50 450 25 Vacuum Pump Yes CC 1.300:1 70 450 25 Hydraulic Pump Yes C 1.333:1 50 450 25 Fuel Pump 0-290-D2B, -D2C C 1.000:1 25 450 25 Propeller Governor or Fuel Pump 0-290-D2A C C .866:1 .866:1 125 125 825 825 25 25 *C - Clockwise, CC - Counter-Clockwise ■ These accessories are optional, see latest revision of Lycoming Service Instruction 1154 for the approved alternates. NOTE 5. The above engines incorporate the following detailed differences: (a) Includes Model 0-290-A engine, Serial No. 107-6, with ratings, temperature limits, compression ratio, carburetor, and ignition timing the same as for Model 0-290. (b) Serial No. suffix "S" identifies engines incorporating No. 10 spline crankshaft. 0-290-C engines, Nos. 568-6 to 597-6 inclusive, originally incorporated the 6 bolt propeller flange. Propellers having at least a 4- 3/4 in. thick hub are required with these crankshafts. (c) Models 0-290-AP and 0-290-CP, similar respectively to Models 0-290-A and 0-290-C, incorporate provisions for absorbing the propeller thrust in both tractor and pusher type aircraft. (d) Military Models 0-290-1, 0-290-3 and 0-290-11 are identical respectively to 0-290-B, 0-290-C and 0-290-D. When they are installed in certificated aircraft, the corresponding commercial model designation and Type Certificate No. 229 should be added to the engine nameplate. (e) Model 0-290-D similar to Model 0-235-C1 except for 0-290-A cylinder, piston and connecting rod assemblies, reinforced crankcase and crankshaft and is eligible for both tractor and pusher type installations. (f) Model 0-290-D2 similar to Model 0-290-D except crankcase, higher compression ratio, hydraulic tappets, camshaft, intake valves and associated parts. (g) Model 0-290-D2A similar to Model 0-290-D2 except has provisions for controllable propeller and propeller governor or alternate fuel pump. (h) Model 0-290-C Serial No. 1446-6 has been modified in accordance with C.E. Wilson Drawing #2 to incorporate revised generator and magneto drive gears. With this modification, the engine is restricted to 125 hp. at 2600 r.p.m. for takeoff and maximum continuous. (i) Model 0-290-D2B similar to 0-290-D2 except for compression ratio, ignition timing and propeller governor provisions. (j) Model 0-290-D2C similar to 0-290-D2B except has retard breaker magnetos S4LN-204, -200. 5 E-229 NOTE 6. The approvals for the following models have expired. No engines of these models manufactured after the indicated date or with a higher Serial No. are eligible is certificated aircraft: Model Serial No. Date 0-290 872-6 2-25-44 0-290-B 1448-6 7-10-45 0-290, -A, -AP, -C, -CP 2070-6 3-10-50 0-290-D2A 5720-21 10-15-53 NOTE 7. Model 0-290-D2 is approved for horizontal mounted helicopter application at the following ratings: Maximum continuous hp., r.p.m., sea level pressure altitude 135-2600-S.L. Takeoff hp., r.p.m., full throttle 135-2600 NOTE 8. Spark Plugs: See latest revision of Lycoming Service Instruction No. 1042 for approved equipment. ....END....