Push button reconfiguration for rudder pedal

An aircraft rudder control system comprising:

• a first rudder pedal adjustment system including:
• a rudder pedal actuatable to control movement of a rudder of an aircraft;
• a support frame component;
• a rudder pedal arm spring-biased and rotatably attached to the support frame component, wherein the rudder pedal is attached to the rudder arm;
• a pin;
• a pin receiving component attached to or integrally formed with the support frame component and having two or more openings or receptacles configured to selectively receive the pin, such that while the pin is received in any of the two or more openings or receptacles, the rudder pedal arm is prevented from rotating;
• a first lever pivotally attached to the rudder pedal arm and having a first end portion fixed to the pin and a second end portion spring-biased away from the rudder pedal arm, wherein the first lever is pivotally attached to the rudder pedal arm between the first end portion and the second end portion;
• a second lever having a third end portion and a fourth end portion and being pivotally attached to a portion of the rudder pedal arm between the third end portion and the fourth end portion, wherein the third end portion of the second lever is located between the first end portion and the rudder pedal arm;
• and
• a solenoid configured to draw the fourth end portion of the second lever toward the solenoid in response to activation of the solenoid, thus pivoting the second lever to raise the third end portion which lifts the first end portion of the first lever away from the rudder pedal arm, thereby withdrawing the pin from the pin receiving component and freeing the rudder pedal arm to be rotatably repositioned by user foot actuation.

An aircraft rudder control system comprising:

• a first rudder pedal adjustment system and a second rudder pedal adjustment system, wherein each of the first rudder pedal adjustment system and the second rudder pedal adjustment system comprise:
• a rudder pedal actuatable to control movement of a rudder of an aircraft;
• a support frame component;
• a rudder pedal arm spring-biased and rotatably attached to the support frame component and integrally comprising a solenoid support structure, wherein the rudder pedal is attached to the rudder pedal arm, wherein a pin hole is formed through the rudder pedal arm;
• a pin actuatable into and at least partially through the pin hole of the rudder pedal arm and out of the pin hole of the rudder pedal arm;
• a pin receiving component attached to or integrally formed with the support frame component and having two or more openings or receptacles configured to selectively receive the pin, such that while the pin is received in any of the two or more openings or receptacles, the rudder pedal arm is prevented from rotating;
• a first lever pivotally attached to the rudder pedal arm and having a first end portion fixed to the pin and a second end portion spring-biased away from the rudder pedal arm, wherein the first lever is pivotally attached to the rudder pedal arm between the first end portion and the second end portion;
• a second lever having a third end portion and a fourth end portion and being pivotally attached to the solenoid support structure between the third end portion and the fourth end portion, wherein the third end portion of the second lever is located between the first end portion and the rudder pedal arm without blocking a travel path of the pin through the pin hole;
• a solenoid is attached to the solenoid support structure and is configured to draw the fourth end portion of the second lever toward the solenoid in response to activation of the solenoid, thus pivoting the second lever to raise the third end portion which lifts the first end portion of the first lever, thereby withdrawing the pin from the pin receiving component and freeing the rudder pedal arm to be rotatably repositioned by user foot actuation;
• and
• a remote button or switch configured to selectively activate and deactivate the solenoid.