Aircraft control surface actuation systems and methods
Aircraft control surface actuation systems and methods are described herein. An example control surface actuation system includes an interface cable, a test interface, and a controller. The test interface is to be disposed in an electrical equipment (EE) bay of an aircraft and operatively coupled to an actuator associated with a control surface of the aircraft. The interface cable is to be connected between the test interface and the controller, and the controller is to transmit a signal via the interface cable to the test interface to control the actuator.
1. A control surface actuation system comprising:
an interface cable;
a test interface to be disposed in an electrical equipment (EE) bay of an aircraft, the test interface to be electrically coupled to an actuator or a valve associated with the actuator, the actuator associated with a control surface of the aircraft; and
a controller, the interface cable to be connected between the test interface and the controller, the controller to transmit a control signal via the interface cable and the test interface to activate and control the actuator.
2. The control surface actuation system of claim 1 , wherein the control surface is a spoiler.
3. The control surface actuation system of claim 1 , wherein the test interface is contained in a housing and includes an interface cable connector to be electrically coupled to the interface cable and an actuator line connector to be electrically coupled to an actuator line electrically coupled to the actuator or the valve associated with the actuator, the interface cable connector disposed on a first side of the housing and the actuator line connector disposed on a second side of the housing opposite the first side.
4. The control surface actuation system of claim 3 , wherein the housing of the test interface has a size substantially matching a size of a Spoiler Control Electronics (SCE) box, and wherein the housing is to be disposed in a slot in the EE bay designated for the SCE box.
5. The control surface actuation system of claim 1 , wherein the controller includes a control panel having a switch that is moveable between a first position and a second position, the controller to transmit the control signal when the switch is in the first position and not transmit the control signal when the switch is in the second position.
6. The control surface actuation system of claim 5 , wherein the control panel includes a master drive switch that is moveable between an ON position and an OFF position, and wherein the controller only transmits the control signal when the switch is in the first position and the master drive switch is in the ON position.
7. The control surface actuation system of claim 5 , wherein the test interface is to be operatively coupled to a plurality of actuators associated with a plurality of control surfaces of the aircraft, and wherein the control panel includes a plurality of switches corresponding to one or more of the plurality of actuators.
8. The control surface actuation system of claim 7 , wherein the plurality of switches are arranged in an order that matches a layout of the plurality of control surfaces.
9. The control surface actuation system of claim 7 , wherein at least one of the plurality of switches controls multiple ones of the actuators.
10. The control surface actuation system of claim 5 , wherein the control panel includes a light, and wherein the light is to be activated when the switch is in the first position.
11. The control surface actuation system of claim 1 , wherein the controller includes a power cord to be connected to a power source and a battery to provide backup power.
12. The control surface actuation system of claim 11 , wherein the controller includes a speaker to generate an audible alert when the controller receives backup power from the battery.
13. The control surface actuation system of claim 11 , wherein the controller includes a battery test button to test an amount of charge in the battery.
14. A method comprising:
inserting a test interface into an electrical equipment (EE) bay of an aircraft;
connecting an actuator line to the test interface, the actuator line is operatively coupled to an actuator associated with a control surface of the aircraft;
connecting an interface cable between the test interface and a controller; and
operating a switch of the controller to generate a control signal, the control signal transmitted via the interface cable and the test interface to activate and control the actuator.
15. The method of claim 14 , further including, prior to operating the switch of the controller, connecting the controller to an external power source.
16. The method of claim 14 , wherein inserting the test interface includes inserting the test interface into a slot in the EE bay designated for a Spoiler Control Electronics (SCE) box.
17. The method of claim 14 , wherein the control surface is a spoiler.
18. A controller comprising:
a housing;
an interface cable connector disposed on a side of the housing, the interface cable connector to be operatively coupled to a plurality of control surface actuators associated with a plurality of control surfaces of an aircraft; and
a control panel disposed in the housing, the control panel having a plurality of switches corresponding to respective ones of the control surface actuators to enable an operator to control movement of the control surfaces, the plurality of switches arranged in an order that matches a layout of the plurality of control surfaces.
19. The controller of claim 18 , wherein the housing includes a lid that is moveable between an open position in which the control panel is exposed and a closed position in which the control panel is covered.
20. The controller of claim 19 , wherein the lid includes a transparent panel to enable the operator to view the control panel through the lid when the lid is in the closed position.