Mechanical override for electronic fuel control on a piston engi

Internal-combustion engines – Engine speed regulator – Having condition responsive means with engine being part of...

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123396, 123400, 123198D, 74479, 74625, F02D 4122

Patent

active

046431489

ABSTRACT:
This invention discloses apparatus for controlling the throttle of an aircraft engine so that it is either in the fully automatic electronic fuel control mode or in the completely manual mode while using a single throttle lever. In the event of a power failure in the aircraft, automatic reversion to the manual throttle control mode of operation is provided. The apparatus for achieving this consists of an outer housing shell having a lever arm extending radially therefrom, the outermost end of the lever arm being pinned to a source of translational motion such as provided by a push rod attached to the manual throttle lever. Within one end of the outer housing shell there is an output spool having on its outward facing end a boring sized to accommodate the throttle shaft of the engine fuel metering system. An input spool is mounted for rotation within the second end of the outer housing shell. The outward facing end of the input spool is secured by a shaft to the electronic fuel control equipment. An electrically powered solenoid mounted on the outer housing shell so that its plunger faces radially inward interfaces with a spring loaded transverse pin within the apparatus to selectively lock the rotation of the output spool to the rotation of the input spool for providing control of the throttle by the automatic fuel control equipment. Loss of aircraft electric power or deactivation of the solenoid automatically locks the output spool to the outer housing shell thereby enabling manual throttle control.

REFERENCES:
patent: 3120845 (1964-02-01), Horner
patent: 3292453 (1966-12-01), Recknagel
patent: 4401077 (1983-08-01), Earl
patent: 4548176 (1985-10-01), Ishida et al.

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