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Lambert Aircraft Engine Corp The Major Lambert / R-266
The Lambert R-266 features a solid master connecting rod and two piece crankshaft. A two piece magnesium alloy crankcase, split on the cylinder centreline, is held together with ten bolts. The front section carries the front main ball-bearing and thrust ball-bearing. The inlet passage and valve lifter guides are cast in the rear section.
Cylinder barrels are nickel semi-steel castings. Removable cylinder hads of aluminium alloy with exhaust and inlet ports toward the rear, are held in place with four long studs which run through the crankcase. Enclosed valve actuating mechanism is at the rear of the cylinders.
Accessories and their drives are grouped at the rear making for easy cowling.
Equipment incules a propeller hub, exhaust ring, carburettor air heater and muffler, tool kit, and instruction and parts book.
Type: 5 cylinder air cooled, fixed radial
Dept of Commerce Rating: 90 hp at 2375 rpm
Displacement: 266
Compression ratio: 5.55-1
Bore: 4 1/4 in
Stroke: 3 3/4 in
Length: 30 3/8 in
Diameter: 33 in
Weight: 214 lb
Fuel consumption: not more than .55 lb/hp/hr
Oil consumption: not more than .025 lb/hp/hr
Lubrication: Pressure and dry sump
Ignition: Dual Scintilla
Carburation: Stromberg NAR 3
Spark plugs: 2 per cylinder Champion

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