TCDS E-237

P a g e N o . 1 2 3 R e v . N o . 1 11 11 0 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E-237 Revision 11 Jacobs-Page R-755A1 R-755A2 R-755A2M R-755A2M1 R-755B1 R-755B2 R-755B2M R-755E January 2, 2002 TYPE CERTIFICATE DATA SHEET NO. E-237 Engines of models described herein conforming with this data sheet (which is a part of Type Certificate No. E-237) 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 Air Repair, Inc. 920 Airport Service Road Cleveland, Mississippi 38732 Type Certificate Holder Record: Air Repair, Inc. assumed ownership of this type certificate from Jacobs Service Company, 4305 Saturn Way, Chandler, Arizona 85334 on January 2, 2002. Model R-755A1, R-755A2, R-755B1, R-755B2, R-755A2M, R-755A2M1 R-755B2M R-755E Type - 7RA Direct Drive - - .649:1 Rating Max. continuous, hp, rpm, at: Sea level pressure altitude (ft.) 300-2200-S.L. 275-2200-S.L. 350-2500-S.L. Takeoff (5 min.), hp, rpm at: Sea level pressure altitude (ft.) 300-2200 275-2200 350-2500 full throttle Fuel (minimum grade aviation gasoline) 80 - - 91 Bore and stroke in. 5.25 X 5.00 - - - - Displacement, cu. in. 757 - - - - Compression ratio 6:1 - - 6.5:1 Weight (dry), lb. 505 (A1), 511 (A2) 505 (B1), 511 (B2) 600 504 (A2M & A2M1) 504 (B2M) C.G. location (dry) Fwd. of mounting face, in. 6:9 - - 7.4 Below propeller shaft, in. 0.2 - - - - Propeller shaft end, SAE No. Spline 20 - - 30 Carburetion Stromberg NA-R7A - - - - Carburetor setting 482-12 - - 482-11 Ignition, dual Combination Scintilla Combination Scintilla Combination Scintilla VMN7-DF5 magneto VMN7-DF5 magneto VMN7-DF5 magneto and and Scintilla WL7A and Scintilla WL7A Scintilla WL7A battery battery ignition unit battery ignition unit ignition unit (R-755A1, R-755A2), (R-755B1, B2), dual Dual Scintilla VMN7- Scintilla VMN7-DF5 DF5 magnetos magnetos (B2M). (R-755A2M, R-755A2M1) E-237 Page 2 of 3 Ignition, timing °BTC 31 - - 30 Spark plugs See Note 7. - - - - NOTES 1,2,3,4,5,6,7 1,2,4,5,6,7 - - "- -" indicates "same as preceding model." "—" indicates "does not apply." Certification Basis Regulations & Amendments Model Date of Application Date Type Certificate E-237 issued/revised CAR 13 effective Aug 1, 1941 R-755A1, A2 R-755E May 23, 1945 June 28, 1947 August 20, 1945 April 1, 1949 As amended by 13-1 & 13-2 R-755B1 and B2 January 24, 1952 March 6, 1952 CAR 13 effective June 15, 1956 As amended by 13-1, 13-2 & 13-3 R-755A2M, B2M, R-755A2M1 July 14, 1961 December 1, 1961 July 26, 1961 July 17, 1962 November 3, 2001 TC Holder transfer January 2, 2002 Production basis The manufacturer no longer holds a production certificate for engines under this certificate as of February 20, 1957; therefore, each engine produced is subject to a detailed inspection for workmanship and conformity with the approved data by an FAA representative. In addition, the engine must have a satisfactory run-in including at least five hours at rated power and speed. Upon satisfactory completion of the above, the FAA representative shall tag the engine with Tag Form FAA-186 NOTE 1. Maximum permissible temperatures: Cyl. Head Cyl. Base Oil Inlet All except R-755E 500°F 300°F 200°F R-755E 460°F 300°F 190°F NOTE 2. Pressure limits for normal operation: Fuel inlet 2.5 to 4 p.s.i. (pressure feed) 1.0 p.s.i. (gravity feed with carburetor setting revised for corrected float level or different size float needle and seat) NOTE 3. Models R-755A1 and A2 eligible with aluminum rear and front crankcases and main bearing plate replacing the magnesium parts with possible weight increase of 11 lbs. NOTE 4. Models R-755A2, otherwise similar to Model R-755A1, has provision for hydraulically operated constant speed or two position propellers. Model R-755A2M similar to R-755A2 except for dual magneto ignition system. Model R-755A2M1 similar to R-755A2M except has provisions for propeller governor drive and propeller governor oil transfer rings in nose case. Model R-755B1 and B2 respectively, similar to R-755A1 and A2 except for crankcase, cylinders and oil sump strainer. Model R-755B2M similar to R-755B2 except for dual magneto ignition system. Model R-755E incorporates the following redesigned and new features not incorporated in the R-755A models: Heavier cylinder heads, propeller reduction gearing, silver master rod bearing, new design crankcase with 3-1/2 order torsional vibration dampers, and new ratings. Page 3 of 3 E-237 NOTE 5. Accessories such as generators, starters, fuel and vacuum pumps, etc., previously listed in NOTE 5 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 air- worthiness of such accessories is substantiated during aircraft installation system approvals. The suitability of the accessory to the engine mounting provisions as described in NOTE 6 must be determined when processing such approvals. NOTE 6. The following accessory drive provisions are available on all models: Direction of Maximum Torque (in.-lb.) Maximum Overhang Moment Drive Rotation Drive Ratio Continuous Static (in.-lb.) Starter CC 1.5 :1 — 5500 150 Generator CC 1.4 :1 50 300 110 Fuel pump (rear crankshaft) C 1 :1 20 150 6 Tachometer CC .5 :1 — — — *Vacuum pump CC 1 :1 or .875:1 30 200 8 *Propeller governor CC 1 :1 30 200 13 *Hydraulic pump CC 1 :1 or .875:1 30 200 6 *Fuel pump CC 1 :1 30 200 3 Propeller governor C 1 :1 50 200 13 (R-755A2M1 model only) All directions of rotation are given facing engine drive flange. *Accessories marked with an asterisk are mounted on accessory drive unit. The total continuous torque taken off all the drives on the accessory drive unit should not exceed 70 inch-pounds. NOTE 7. The following spark plugs are approved on these engines: AC S-86R, SR-83P, HSR-83P Autolite SH-2K, SH-2M, SH-20, SH-20A, 18A-1 BG RB485S Champion C27, C27S, D4IN, ED4IN, EM4IN, M4IN, RC26S, RED39N, REM39N, REM40E, RHD39N, RHM39N, RHM40E, M42E, EM42E, REM39P, RHM38P ....END....