TCDS E-270

Page No. 1 2 Rev No. 5 5 Reformatted 12/93. DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION E-270 Revision 5 WRIGHT Double Row Cyclone 956C18CA1 975C18CB1 December 28, 1983 TYPE CERTIFICATE DATA SHEET NO. E-270 Engines of models described herein conforming with this specification and approved data on file with the Civil Aeronautics Administration and Federal Aviation Administration are rated as airworthy for use in certificated aircraft in accordance with pertinent aircraft specifications and the manufacturer's installation, operation, repair and overhaul instructions. Manufacturer Curtiss Wright/Marquette Inc. Fountain Inn, S.C. Model Double Row Cyclone 956C18CA1 975C18CB1 Type 18RA 16:7 Reduction gearing - - Rating (with low impeller gear ratio) 6.46:1 - - Max. continuous, hp, rpm, in.Hg., at: Critical altitude (ft.) 2300-2600-45.5-6300 2400-2600-46.0-5300 Sea level pressure altitude 2300-2600-47.0-S. L. 2400-2600-47.5-S. L. Take-off (5 min.), hp, rpm, in.Hg., at: Critical altitude (ft.) 2700-2900-52.5-5100 2800-2900-52.5-4500 Sea level pressure altitude 2700-2900-54.0-S. L. 2800-2900-54.0-S. L. (With high impeller gear ratio) 8.67:1 - - Max. continuous, hp, rpm, in.Hg., at: Critical altitude (ft.) 2000-2600-46.5-15,800 2000-2600-46.0-16,000 Low critical pressure altitude (ft.) 2000-2600-48.0-10,700 2000-2600-47.5-10,800 Fuel (Minimum grade aviation gasoline) 115/145 115/145 (See NOTE 6 for 100/130) Bore and stroke, in. 6.125 X 6.312 - - Displacement, cu. in. 3350 - - Compression ratio 6.70:1 - - Weight (dry), lbs. 2945 3065 C.G. location (dry) From crankcase mounting pad counterbore, in. 13.50 - - From thrust nut face, in. 30.64 - - Above propeller shaft, in. 0.2 - - Propeller shaft, SAE No. 60 - - Fuel injection model Bendix Stromberg PR-58-P3 Bendix Stromberg PR-58-S2 master control with two or PR-58-P3 master control direct injection pumps with two direct injection pumps Ignition, Dual Scintilla, DLN-9 magneto - - Timing, °BTC 25 (35 in cruising) - - NOTES 1, 2, 3, 4, 5 1, 2, 3, 4, 5, 6 "- -" indicates "same as preceding model" "" indicates "does not apply" Certification basis Type Certificate No. 270 Production basis Production Certificate No. 8 E-270, Rev 5 Page 2 NOTE 1. Maximum permissible temperatures are as follows: Head (Well Type Thermocouple) Barrel Oil Inlet 475° (500° for T.O. only) 350° 220° NOTE 2. Fuel and oil pressure limits: Oil pressure (psi) Rear Pump 70 ± 5 Fuel pressure (psi) 25 ± 1 NOTE 3. The following accessory drives are provided: Rotation* Speed* Maximum Torque (lbs. in.) Maximum Bending Moment (in. lbs.) Continuous Static Starter C 1.000 - 36000 350 Generator and accessory (2) C 3.110 1500 6600 400 Fuel pump (2) CC 1.000 25 450 15 Hydraulic pump C 1.400 600 2700 350 Vacuum pump (2) C 1.400 250 1650 75 Tachometer (2) 1C 0.500 22 50 15 1CC Propeller governor C 0.857 125 825 30 *"C" - Clockwise viewing drive pad "CC" - Counter clockwise Speed - Times crankshaft rpm NOTE 4. These engines incorporate torquemeters, provisions for crankcase mounting and double-acting hydraulic propeller provisions. NOTE 5. The ratings of these engines are based on standard conditions of temperature and barometric pressure (60°F and 29.92 in.Hg. at sea level) and 80% relative humidity. If corrected to dry standard air conditions, the rated powers would be increased approximately 2.5% at sea level to 0.4% at 15,000 feet for equal manifold pressure settings. NOTE 6. The 97C18CB1 engine is eligible for use with grade 100/130 fuel at the following ratings: With low impeller rear ratio: Max. continuous, hp, rpm, in.Hg., at: Critical altitude (ft.) - 2150-2600-40.5-8700 Sea level - 2150-2600-43.0-S. L. Take-off (5 min.), hp, rpm, in.Hg. at: Critical altitude (ft.) - 2350-2600-45.0-5900 Sea level - 2350-2600-46.5-S. L. With high impeller gear ratio: Max. continuous, hp, rpm, in.Hg., at: Critical altitude (ft.) - 1800-2600-41.0-18,800 Low critical pressure altitude (ft.) - 1800-2600-42.0-14,000 ....END....