Test device for the detection of the recovery effort by a secondary flight ordering actuator, and associated test method

• US 8,702,034 B2
• Filed: 12/08/2010
• Issued: 04/22/2014
• Est. Priority Date: 12/08/2009
• Status: Active Grant

• Current Assignee: Goodrich Actuation Systems SAS (Rtx Corporation)
• Original Assignee: Goodrich Actuation Systems SAS (Rtx Corporation)
• Inventors: Moulon, Thomas, Turpin, Pierre
• Primary Examiner(s): Caputo, Lisa
• Assistant Examiner(s): DUNLAP, JONATHAN M
• Application Number:
  US12/962,883
• Publication Number:
  US 20110132106A1
• Time in Patent Office: 1,231 Days
• Field of Search: 738/623.81, 244 992- 994
• US Class Current: 244/99.2
• CPC Class Codes: B64C 9/02 Mounting or supporting thereof
• CPC Class Codes: B64F 5/60 Testing or inspecting aircraft components or systems
• CPC Class Codes: Y10T 29/49826 Assembling or joining

Abstract

The disclosure relates to a device for testing means of detecting the loading of the secondary path of a flight control actuator of the type including a primary path and a secondary path able to take up the effort of the primary path in the event of a breakdown of the latter, wherein a tool is able to press against at least one zone of at least one element of the secondary path, as well as a lever arm which by tilting allows the tool to press against the zone so that it exerts a traction and/or compression force on the secondary path, the lever arm being mounted pivotingly on a support able to be fastened on a structure that is mechanically independent of the secondary path.

Claims

1. A testing device for testing means of detecting loading of a secondary path of a flight control actuator,

the flight control actuator comprising a primary path and a secondary path able to take up the effort of the primary path in the event of a breakdown of the latter, the testing device comprising:

a tool operably pressing against at least one zone of at least one element of the secondary path,

and a lever arm which by tilting allows the tool to press against the zone so that it exerts at least one of a fraction and compression force on the secondary path,

the lever arm being mounted pivotingly on a support operably fastened on a structure that is mechanically independent of the secondary path.

2. The device according to claim 1, wherein the tool operably clamps at least one zone of at least one element of the a top fastener of the secondary path.

3. The device according to claim 2, wherein the tool comprises a set including two plates connected by two clamping screws, operably clamping around an area of an element of the top fastener of the secondary path.

4. The device according to claim 3, wherein the tool has a U-shaped element wherein a stop is received, the stop terminating the arm forming a lever at its end opposite its grasping end, the stop pressing against at least one of the two inside flanks of the U-shaped element during the tipping of the lever arm in at least one direction, and making it possible to apply a force in at least one direction on the secondary path.

5. The device according to claim 4, wherein the support comprises a vice operably placed on a piece of one of the primary path and the structure of an aircraft.

6. The device according to claim 3, wherein the support comprises a vice operably placed on a piece of one of the primary path and the structure of an aircraft.

7. The device according to claim 2, wherein the tool has a U-shaped element wherein a stop is received, the stop terminating the arm forming a lever at its end opposite its grasping end, the stop pressing against at least one of the two inside flanks of the U-shaped element during the tipping of the lever arm in at least one direction, and making it possible to apply a force in at least one direction on the secondary path.

8. The device according to claim 7, wherein the support comprises a vice operably placed on a piece of one of the primary path and the structure of an aircraft.

9. The device according to claim 2, wherein the support comprises a vice operably placed on a piece of one of the primary path and the structure of an aircraft.

10. The device according to claim 1, wherein the tool has a U-shaped element wherein a stop is received, the stop terminating the arm forming a lever at its end opposite its grasping end, the stop pressing against at least one of the two inside flanks of the U-shaped element during the tipping of the lever arm in at least one direction, and making it possible to apply a force in at least one direction on the secondary path.

11. The device according to claim 10, wherein the support comprises a vice operably placed on a piece of one of the primary path and the structure of an aircraft.

12. The device according to claim 1, wherein the support comprises a vice operably placed on a piece of one of the primary path and the structure of an aircraft.

13. A testing method for testing a detector which operably detects loading of a secondary path of a flight control actuator, the flight control actuator comprising a primary path and a secondary path operably taking up the effort of the primary path in the event of a breakdown of the latter, the method further comprising:

exerting at least one of a traction and compression force on the secondary path by a tool to press against at least one zone of at least one element of the secondary path, as well as by a lever arm which by tilting allows the tool to press against the zone in order that it exerts the at least one of the traction and compression force on the secondary path,

pivoting the lever arm on a support operably fastened on a structure that is mechanically independent of the secondary path.

14. The method according to claim 13, further comprising:

fastening the support of the lever arm on a structure that is mechanically independent of the secondary path, and fastening the tool around a zone of an element of the top fastener of the secondary path, and clamping around the zone with the tool.

15. The method according to claim 14, further comprising:

a prior step of loosening a spring box and a nut, in order to prevent mechanical friction for allowing reset of the detector of the loading of the secondary path, and a step of retightening the spring box and the nut at the end of the test.

16. The method according to claim 13, further comprising a prior step of loosening a spring box and a nut, in order to prevent mechanical friction for allowing reset of the detector of the loading of the secondary path, and a step of retightening the spring box and the nut at the end of the test.

17. An apparatus comprising:

(a) a detector operably detecting a loading of a secondary path of a flight control actuator, the flight control actuator comprising a primary path and the secondary path acting as a backup to the primary path;

(b) a tester operably testing the detector, the tester further comprising;

a member operably pressing against at least one portion of the secondary path;

an arm causing the member to apply a force in at least one direction against the portion when the arm is moved; and

a removable support mechanically independent from the secondary path, the arm being movably mounted to the support.

18. The device according to claim 17, wherein the portion operably clamps at least one zone of at least one element of a top fastener of the secondary path.

19. The device according to claim 17, wherein the tester has a U-shaped element wherein a stop is received, the stop terminating the arm at its end opposite its grasping end, the stop pressing against at least one of the two inside flanks of the U-shaped element during the tipping of the arm in at least one direction, and making it possible to apply a force in at least one direction on the secondary path.

20. The device according to claim 17, wherein the removable support comprises a vice operably placed on a piece of one of the primary path and the structure of an aircraft.