Patent ID: 8668481

Claim:
A pump assembly ( 1 ), in particular for lubrication in helicopters ( 16 ), comprising : a drive shaft ( 3 ) extending along a longitudinal axis ( 4 ); a casing ( 2 ) comprising : a) a lateral wall ( 8 ) defining an intake port ( 38 ) and a delivery port ( 40 ); b) a rear wall ( 9 ) and front wall ( 12 ) opposite each other and crosswise to said longitudinal axis ( 4 ), said front wall ( 12 ) having an axial hole ( 13 ) fitted through with said drive shaft ( 3 ); pumping means ( 34 ) housed in said casing ( 2 ), said pumping means comprising two rotary pumps ( 34 ); a transmission ( 66 ) that splits the motion of said drive shaft ( 3 ) between said rotary pumps ( 34 ), wherein said transmission ( 66 ) is housed in a compartment ( 49 ) of said casing ( 2 ) and comprises two driven gears ( 69 ) respectively operating said rotary pumps ( 34 ); and a disk ( 51 ) housed in a fixed position in said compartment ( 49 ) coaxially with said drive shaft ( 3 ), wherein said disk ( 51 ) supports an axial end of said drive shaft ( 3 ) and has two through holes ( 77 ) aligned with and larger than said driven gears ( 69 ).