Automatic heating test device for 737NG aircraft atmosphere data sensor

Abstract

The utility model relates to the technical field of airplane function testing devices, in particular to an automatic heating testing device for a 737NG airplane atmosphere data sensor, which comprises a shell, and a testing socket, a testing plug, a first switch and a second switch are fixedly mounted on the shell. The first switch is provided with a first terminal and a second terminal, and the second switch is provided with a third terminal and a fourth terminal. The F12 contact of the test plug built-in integrated block B area and the F12 contact of the test socket built-in integrated block B area are connected with a first wiring terminal through wires, and the second wiring terminal is connected with a first grounding wire. The testing device can control GND / OPEN signals on specific nodes on a circuit, and is simple to manufacture, low in cost, stable and reliable.

Description

Technical Field

[0001] The utility model relates to the technical field of aircraft function test devices, in particular to an automatic heating test device for an atmospheric data sensor of a 737NG aircraft. Background Art

[0002] The atmospheric data sensor is used to measure the surrounding atmospheric static pressure and total pressure and then convert them into flight parameters such as aircraft altitude and airspeed. In order to prevent the atmospheric data sensor from icing when flying at high altitude, the atmospheric data sensor heating function can work automatically when the engine is running.

[0003] According to the current valid aircraft maintenance manual AMM 30-31-00-750-801, the test of the automatic heating function of the atmospheric data sensor requires starting the aircraft engine or connecting an external special device (ARINC 600 breakout box, SPL-1930) to provide the aircraft system with an engine running signal as a necessary condition for completing the test. The former has high requirements for the parking space and staff qualifications, and the engine ground test has a greater safety risk, which requires unbearable time and labor costs in actual production, especially in line maintenance; the latter requires the purchase of expensive equipment available abroad (ARINC 600 breakout box, SPL-1930, with a total value of about 200,000 yuan).

[0004] The role of the ARINC 600 breakout box, SPL-1930 in this test is to control the GND / OPEN signal on a specific node on the circuit to simulate the engine start / stop state. According to the comments of AMM 30-31-00-750-801, the purpose of this device is only to protect the wiring terminals to the greatest extent, and the test can be completed without using this device. Utility Model Content

[0005] The main purpose of the utility model is to provide a 737NG aircraft atmospheric data sensor automatic heating test device to solve the problem of how to realize low-cost GND / OPEN signals on specific nodes on the control circuit in the 737NG aircraft atmospheric data sensor automatic heating test in the above-mentioned prior art.

[0006] In order to achieve the above-mentioned purpose, the utility model provides an automatic heating test device for an atmospheric data sensor of a 737NG aircraft, comprising a shell, on which a test socket, a test plug, a first switch and a second switch are fixedly installed, the test socket and the test plug are both ARINC600 standard parts, the part number of the test socket is NIC66J33C17AA0, and the part number of the test plug is NIC66K33C17AA0, and a plurality of contacts corresponding to each other are arranged on the test socket and the test plug; the first switch is provided with a terminal 1 and a terminal 2 which can be connected and disconnected to each other, and the second switch is provided with a terminal 3 and a terminal 4 which can be connected and disconnected to each other; the F12 contact of the built-in integrated block B area of ​​the test plug and the F12 contact of the built-in integrated block B area of ​​the test socket are both connected to the terminal 1 through a wire, and the terminal 2 is connected to the ground wire 1; the F12 contact of the built-in integrated block E area of ​​the test plug and the F12 contact of the built-in integrated block E area of ​​the test socket are both connected to the terminal 3 through a wire, and the terminal 4 is connected to the ground wire 2; the remaining contacts of the test plug and the test socket are connected to each other through wires.

[0007] Furthermore, one end of the grounding wire 1 away from the first switch and one end of the grounding wire 2 away from the second switch are both connected with a wire clamp; by providing the wire clamp, the wire clamp is clamped on the grounding post of the aircraft electronic frame when in use to achieve grounding.

[0008] Furthermore, the second terminal and the grounding wire are plug-connected, as well as the fourth terminal and the grounding wire are plug-connected.

[0009] The utility model provides an automatic heating test device for an atmospheric data sensor of a 737NG aircraft, which can realize a GND / OPEN signal on a specific node on a control circuit in an automatic heating test of an atmospheric data sensor of a 737NG aircraft, and has the advantages of simple manufacturing, low cost, stability and reliability. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] The drawings in the specification, which constitute a part of the present application, are used to provide a further understanding of the present invention. The illustrative embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation on the present invention.

[0011] Figure 1 It is a structural schematic diagram of an embodiment;

[0012] In the figure: 1. test socket; 2. test plug; 3. first switch; 4. second switch; 5. housing; 6. grounding wire 1; 7. grounding wire 2; 8. wire clamp. DETAILED DESCRIPTION

[0013] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application can be combined with each other. The present utility model will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0014] like Figure 1 As shown, according to an embodiment of the utility model, a 737NG aircraft atmospheric data sensor automatic heating test device is provided, comprising a shell 5, on which a test socket 1, a test plug 2, a first switch 3 and a second switch 4 are fixedly mounted, the test socket 1 and the test plug 2 are both ARINC600 standard parts, the part number of the test socket 1 is NIC66J33C17AA0, the part number of the test plug 2 is NIC66K33C17AA0, and more than 300 one-to-one corresponding contacts are arranged on the test socket 1 and the test plug 2 (only some contacts are shown in the figure); the first switch 3 is provided with a terminal 1 and a terminal 2 that can be connected and disconnected to each other, and the second switch 4 is provided with a terminal 3 and a terminal 4 that can be connected and disconnected to each other; the F12 contact of the built-in integrated block B area of ​​the test plug 2 and the F12 contact of the built-in integrated block B area of ​​the test socket 1 are both connected to the terminal 1 through a wire, and the terminal 2 is connected to the ground wire 1 6; the F12 contact of the built-in integrated block E area of ​​the test plug 2 and the test socket 1 The F12 contacts in the E area of ​​the built-in integrated block are all connected to the wiring terminal 3 through a wire, and the wiring terminal 4 is connected to the ground wire 2 7.

[0015] The end of the grounding wire 1 6 away from the first switch 3 and the end of the grounding wire 2 7 away from the second switch 4 are both connected to a wire clamp 8; by setting the wire clamp 8, the wire clamp 8 is clamped on the grounding post of the aircraft electronic frame when in use to achieve grounding.

[0016] The connection terminal 2 is plugged in with the grounding wire 1 6 and the connection terminal 4 is plugged in with the grounding wire 2 7 .

[0017] When using the above test device to perform the automatic heating test of the atmospheric data sensor of the 737NG aircraft, firstly clamp the wire clamp 8 on the grounding stake of the aircraft electronic frame to achieve grounding, and then perform the following steps: Step 1, confirm that the PROBE HEAT A and B switches on the cockpit windshield / pitot heating control panel are in the AUTO position;

[0018] Step 2: Confirm that the external protective covers of the atmospheric data sensors (including the captain's side pitot tube, the co-pilot's side pitot tube, the spare pitot tube, the angle of attack wind vane, and the total temperature probe) have been removed;

[0019] Step 3. Confirm that the following eight indicators on the cockpit windshield / pitot heating control panel are lit: CAPTPITOT, L ELEV PITOT, L ALPHA VANE, TEMP PROBE, F / O PITOT, R ELEV PITOT, RALPHA VANE and AUX PITOT;

[0020] Step 4, test the automatic heating function when PROBE HEAT A and B are in AUTO position:

[0021] a.DEU 1 is plug-connected to the aircraft. DEU 1 is provided with a socket identical to test socket 1, and the aircraft is provided with a plug identical to test plug 2. Remove DEU 1 according to AMM31-62-21-000-801;

[0022] b. Plug the test socket 1 of the test device into the plug on the aircraft for plugging with DEU 1;

[0023] c. Plug the removed DEU 1 into the test plug 2 of the test device according to AMM31-62-21-000-801;

[0024] d. Close the first switch 3;

[0025] e. Confirm that the following eight indicators on the cockpit windshield / pitot heating control panel are off: CAPT PITOT, L ELEV PITOT, L ALPHA VANE, TEMP PROBE, F / O PITOT, R ELEV PITOT, R ALPHA VANE and AUX PITOT;

[0026] f. Disconnect the first switch 3;

[0027] g. Confirm that the following eight indicators on the cockpit windshield / pitot heating control panel are lit: CAPT PITOT, LELEV PITOT, L ALPHA VANE, TEMP PROBE, F / O PITOT, R ELEV PITOT, R ALPHA VANE and AUX PITOT;

[0028] h. Close the second switch 4;

[0029] i. Confirm that the following eight indicators on the cockpit windshield / pitot heat control panel are off: CAPT PITOT, L ELEV PITOT, L ALPHA VANE, TEMP PROBE, F / O PITOT, R ELEV PITOT, R ALPHA VANE and AUX PITOT.

[0030] j. Disconnect the second switch 4;

[0031] k. Confirm that the following eight indicators on the cockpit windshield / pitot heated control panel are illuminated: CAPT PITOT, LELEV PITOT, L ALPHA VANE, TEMP PROBE, F / O PITOT, R ELEV PITOT, R ALPHA VANE and AUX PITOT.

[0032] l. Remove DEU 1 according to AMM31-62-21-000-801;

[0033] m. Remove the test device;

[0034] n. Install DEU 1 according to AMM31-62-21-000-801;

[0035] Step 5, restore the aircraft to a usable state.

[0036] Note:

[0037] During the test, keep personnel and equipment away from the captain's side pitot tube, co-pilot's side pitot tube, spare pitot tube, angle of attack wind vane and total temperature probe; otherwise, these components may heat up and scald personnel or damage equipment.

[0038] The above description is only the preferred embodiment of the utility model, and is not intended to limit the utility model. For those skilled in the art, the utility model can have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the utility model shall be included in the protection scope of the utility model.

Claims

1. An automatic heating test device for an air data sensor of a 737NG aircraft, comprising a housing (5), characterized in that: A test socket (1), a test plug (2), a first switch (3) and a second switch (4) are fixedly mounted on the housing (5); the test socket (1) and the test plug (2) are both ARINC600 standard parts; the part number of the test socket (1) is NIC66J33C17AA0; the part number of the test plug (2) is NIC66K33C17AA0; the test socket (1) and the test plug (2) are provided with a plurality of contacts in one-to-one correspondence; the first switch (3) is provided with a first terminal and a second terminal that can be connected and disconnected to each other; the second switch ( 4) is provided with a terminal 3 and a terminal 4 which can be connected and disconnected to each other; the F12 contact of the built-in integrated block B area of ​​the test plug (2) and the F12 contact of the built-in integrated block B area of ​​the test socket (1) are both connected to the terminal 1 through a wire, and the terminal 2 is connected to the grounding wire 1 (6); the F12 contact of the built-in integrated block E area of ​​the test plug (2) and the F12 contact of the built-in integrated block E area of ​​the test socket (1) are both connected to the terminal 3 through a wire, and the terminal 4 is connected to the grounding wire 2 (7); the remaining contacts of the test plug (2) and the test socket (1) are connected one-to-one through wires.

2. The 737NG aircraft air data sensor automatic heating test device as claimed in claim 1, characterized in that: An end of the grounding wire 1 (6) away from the first switch (3) and an end of the grounding wire 2 (7) away from the second switch (4) are both connected to a wire clamp (8).

3. The 737NG aircraft air data sensor automatic heating test device as claimed in claim 1, characterized in that: The connection terminal 2 is plugged in to the grounding wire 1 (6) and the connection terminal 4 is plugged in to the grounding wire 2 (7).

Images