Airplane landing gear monitoring and alert system and method

Abstract

A landing gear monitoring and alert system includes a locking pin configured to be inserted into an aperture extending through a linkage mechanism of an extended landing gear assembly. When inserted into the aperture, the locking pin inhibits movement of the linkage mechanism to establish a locked state of the extended landing gear assembly. The system also includes a magnetic sensor and a communication module. The magnetic sensor is disposed proximate the aperture and is configured to sense a magnetic response indicative of the locking pin being disposed within the aperture. The magnetic sensor is configured to generate a sensor output indicative of the locking pin being disposed within the aperture. The communication module has a transmitter coupled to the magnetic sensor to receive the sensor output, and the communication module is configured to responsively transmit a signal indicative of the locking pin being disposed within the aperture.

Description

Technical Field

[0001] This disclosure relates generally to aircraft, and more specifically to aircraft landing gear monitoring and alarm systems and methods. Background Technology

[0002] Some aircraft include landing gear. During landing, the aircraft's landing gear contacts the surface of the airport runway to facilitate a smooth landing. Additionally, landing gear is used during taxiing to facilitate the aircraft's movement on the airport runway. Summary of the Invention

[0003] This disclosure describes an aircraft landing gear monitoring and warning system and method. The landing gear monitoring and warning system alerts the flight crew and ground personnel when a locking pin is positioned within a clearance of a linkage mechanism in an extended landing gear assembly. The locking pin inhibits movement of the linkage mechanism, thereby preventing the landing gear assembly from moving from the extended position to the retracted position. It is desirable to remove the locking pin from the clearance of the linkage mechanism before takeoff to allow the landing gear assembly to retract. Failure to do so may increase drag acting on the aircraft, thereby increasing fuel consumption. As a result, the aircraft may have to deviate from its flight plan to return to the airport to allow ground personnel to remove the locking pin from the clearance of the linkage mechanism. Such detours can result in financial losses for airlines in the form of airport parking fees, additional fuel costs, and unexpected departure delays. Therefore, it is desirable to develop a system and method for alerting the aircraft's ground personnel and flight crew when a locking pin is positioned within a clearance of a linkage mechanism in the landing gear assembly.

[0004] Currently disclosed aircraft landing gear monitoring and warning systems detect when a locking pin is positioned within a gap that extends through a linkage mechanism of the landing gear assembly in its extended position. Upon detecting a locking pin within the gap, the system alerts the flight crew and ground personnel that the pin is positioned within the gap extending through the linkage mechanism of the landing gear assembly, thereby allowing ground personnel to remove the locking pin from the gap before takeoff.

[0005] In some examples of this disclosure, the landing gear monitoring and warning system includes a locking pin configured to insert into an aperture extending through at least one linkage mechanism of the protruding landing gear assembly. When inserted into the aperture, the locking pin inhibits movement of the linkage mechanism to establish a locked state of the protruding landing gear assembly. The aircraft landing gear monitoring and warning system also includes a magnetic sensor disposed near the aperture and configured to sense a magnetic response indicating that the locking pin is positioned within the aperture to establish a locked state of the protruding landing gear assembly. The magnetic sensor is configured to generate a sensor output indicating that the locking pin is positioned within the aperture. Additionally, the aircraft landing gear monitoring and warning system includes a communication module with a transmitter. The transmitter is coupled to the magnetic sensor to receive the sensor output indicating that the locking pin is positioned within the aperture of the linkage mechanism. The communication module is configured to responsively transmit a signal indicating that the locking pin is positioned within the aperture to establish a locked state of the protruding landing gear assembly.

[0006] In some aspects of this disclosure, the landing gear monitoring and warning system may include a display device within the main field of view in the aircraft cockpit. The display device is configured to display information regarding the locking status of a locking pin positioned within an orifice to establish a locked position of the extended landing gear assembly, in response to a transmitted signal received by the display device via the aircraft's data network.

[0007] In this disclosure, the magnetic sensor may include a magnetic sensor-activated switch, wherein the magnetic sensor is configured to activate the magnetic sensor-activated switch when it magnetically senses that a locking pin is positioned within the aperture. The magnetic sensor-activated switch also provides a sensor output to a communication module.

[0008] In this disclosure, the linkage mechanism may include a pair of pivotally coupled link members. An aperture of the linkage mechanism extends through the pair of pivotally coupled link members. A locking pin is configured to be inserted into the aperture extending through the pair of pivotally coupled link members to inhibit movement of the pair of pivotally coupled link members relative to each other, thereby maintaining the pair of pivotally coupled link members in a fixed relationship with each other.

[0009] In some aspects of this disclosure, the communication module may include a microcontroller configured to receive sensor output from a magnetic sensor. The communication module may also include an integrated WiFi component configured to wirelessly transmit a signal indicating that a locking pin is positioned within an aperture in the linkage mechanism.

[0010] In this disclosure, the microcontroller may be a general-purpose host controller interface that transmits a signal indicating that the locking pin is positioned within the aperture via a general-purpose asynchronous transceiver.

[0011] In some aspects of this disclosure, the communication module may be configured to transmit a signal indicating that the locking pin is set in the orifice of the linkage mechanism to a handheld device of a ground crew member in response to receiving a sensor output indicating that the locking pin is set in the orifice.

[0012] In some aspects of this disclosure, the communication module may be configured to transmit a signal indicating that the locking pin is set in the orifice in response to: (a) receiving a sensor output indicating that the locking pin is set in the orifice; and (b) receiving flight phase information indicating the aircraft's taxiing motion.

[0013] In this disclosure, the landing gear monitoring and warning system may also include a display device within the main field of view in the aircraft cockpit. This display device is configured to display, on a summary page, information regarding the locking state of a locking pin positioned within an aperture in the linkage mechanism to establish a locked position of the extended landing gear assembly, in response to a signal received by the display device via the aircraft's data network.

[0014] This disclosure also describes a method for operating a landing gear monitoring and alarm system. In some aspects of this disclosure, the method includes monitoring a magnetic field near an aperture of a landing gear assembly. The landing gear assembly includes at least one linkage mechanism. An aperture extends through the linkage mechanism. The landing gear assembly includes a locking pin configured to insert into the aperture when the landing gear assembly is in an extended position to inhibit movement of the linkage mechanism and establish a locked state of the landing gear assembly in the extended position. The method further includes sensing a magnetic response indicating that the locking pin is positioned within the aperture to establish the locked state of the landing gear assembly in the extended position. Additionally, the method includes transmitting a signal indicating that the locking pin is inserted into the aperture to establish the locked state of the landing gear assembly in the extended position in response to sensing the magnetic response indicating that the locking pin is positioned within the aperture to establish the locked state of the landing gear assembly in the extended position.

[0015] In some aspects of this disclosure, the method may further include displaying information on the aircraft's display device regarding the locking pin being positioned within the aperture, in response to a transmitted signal received by the display device via the aircraft's data network. The display device has the primary field of view in the aircraft's cockpit.

[0016] In the currently disclosed method, sensing a magnetic response may include activating a magnetically activated switch when a locking pin is magnetically sensed to be positioned within the orifice, and transmitting a sensor output from the magnetically activated switch to a communication module of the landing gear monitoring and alarm system in response to the activation of the magnetically activated switch.

[0017] In the currently disclosed method, transmitting a signal indicating that the locking pin is inserted into the orifice may include wirelessly transmitting a signal indicating that the locking pin is inserted into the orifice.

[0018] In the currently disclosed method, transmitting a signal indicating that the locking pin is inserted into the orifice may include transmitting a signal indicating that the locking pin is inserted into the orifice via a universal asynchronous transceiver.

[0019] In the currently disclosed method, transmitting a signal indicating that the locking pin is inserted into the orifice may include transmitting a signal indicating that the locking pin is inserted into the orifice to a handheld device of ground crew in response to a magnetic response that senses the locking pin being positioned within the orifice to establish a locked state of the landing gear assembly in the extended position.

[0020] In the currently disclosed method, transmitting a signal indicating that the locking pin is inserted into the orifice may include a magnetic response in response to sensing that the locking pin is positioned within the orifice to establish a locked state of the landing gear assembly in the extended position, and receiving flight phase information indicating the aircraft's taxiing motion, transmitting a signal indicating that the locking pin is positioned within the orifice.

[0021] The currently disclosed method may also include displaying information about a locking pin disposed in the aperture on a summary page displayed by the display device in response to the display device receiving a transmitted signal via the aircraft's data network.

[0022] This disclosure also describes an aircraft including a fuselage and a landing gear assembly movable relative to the fuselage. The landing gear assembly has an extended position and includes at least one linkage mechanism and an aperture extending through the linkage mechanism. The landing gear assembly also includes a locking pin configured to insert into the aperture extending through the linkage mechanism. The locking pin, when inserted into the aperture, inhibits movement of the linkage to establish a locked state of the landing gear assembly in the extended position. The aircraft also includes a landing gear monitoring and warning system coupled to the landing gear assembly. The landing gear monitoring and warning system includes a magnetic sensor disposed near the aperture and configured to sense a magnetic response indicating that the locking pin is positioned within the aperture to establish a locked state of the landing gear assembly in the extended position. The magnetic sensor is configured to generate a sensor output indicating that the locking pin is positioned within the aperture. The landing gear monitoring and warning system also includes a communication module having a transmitter. The transmitter is coupled to the magnetic sensor to receive the sensor output indicating that the locking pin is positioned within the aperture. The communication module is configured to responsively transmit a signal indicating that the locking pin is positioned within the orifice, thereby establishing a locked state of the landing gear assembly in the extended position.

[0023] In some aspects of this disclosure, the aircraft may also include a cockpit and a display device disposed in the cockpit. The display device is within the cockpit's main field of view. Furthermore, the display device is configured to display information regarding the locking state of a locking pin disposed within an aperture to establish the landing gear assembly in the extended position, in response to a signal received by the display device via the aircraft's data network.

[0024] In some aspects of this disclosure, the aircraft's magnetic sensor may include a magnetic sensor-activated switch, wherein the magnetic sensor is configured to activate the magnetic sensor-activated switch when it magnetically senses that a locking pin is positioned within an aperture. The magnetic sensor-activated switch is also configured to provide a sensor output to a communication module.

[0025] The above features and advantages, as well as other features and advantages, of this teaching will become apparent when taken in conjunction with the accompanying drawings and according to the following specific embodiments of the mode for implementing this teaching. Attached Figure Description

[0026] The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments of the present disclosure and, together with the specification, serve to explain the principles of the present disclosure.

[0027] Figure 1 It is a schematic perspective view of an aircraft including the landing gear assembly and landing gear monitoring and alarm system.

[0028] Figure 2 yes Figure 1 A schematic perspective view of the landing gear assembly of the aircraft shown.

[0029] Figure 3 yes Figure 2 A schematic side view of a portion of the landing gear assembly shown.

[0030] Figure 4 yes Figure 3 The schematic exploded perspective view of the linkage mechanism of the landing gear assembly shown depicts locking pins spaced apart from orifices extending through the linkage mechanism.

[0031] Figure 5 yes Figure 1 A schematic perspective view of the cockpit of the aircraft shown.

[0032] Figure 6 yes Figure 1 The schematic front view of the aircraft's display equipment depicts an image 144 of an aircraft with landing gear assembly.

[0033] Figure 7 yes Figure 1 The diagram shows a schematic front view of the aircraft's instrument panel, including the landing gear lights.

[0034] Figure 8 yes Figure 1 The diagram shows a schematic front view of the aircraft's display equipment, including the engine indication and crew alert system (EICAS) pages.

[0035] Figure 9 yes Figure 1 The diagram shows a schematic block diagram of the aircraft's landing gear monitoring and alarm system.

[0036] Figure 10 It is an operation Figure 9 The flowchart shows a method for a landing gear monitoring and alarm system. Detailed Implementation

[0037] The foregoing details and the following specific implementation of certain embodiments will be better understood when read in conjunction with the accompanying drawings. As used herein, elements or steps referred to in the singular and preceding the words “a” or “an” should be understood to not necessarily exclude multiple elements or steps. Furthermore, reference to “an embodiment” is not intended to exclude the existence of other embodiments that also include the described features. Moreover, unless explicitly stated to the contrary, embodiments that “comprise” or “have” one or more elements having a particular property may include other elements that do not have that property.

[0038] refer to Figure 1 The aircraft 100 includes a fuselage 102 and two or more wings 104 coupled to the fuselage 102. In addition to the wings 104, the aircraft 100 also includes one or more landing gear assemblies 106 coupled indirectly or directly to the fuselage 102. As a non-limiting example, the aircraft 100 may include: two landing gear assemblies 106, each coupled below its respective wing 104; and a landing gear assembly 106 coupled to the nose 108 of the fuselage 102. Regardless of the number, each landing gear assembly 106 can be in a retracted position and an extended position relative to the fuselage 102 (e.g., Figure 1 The aircraft 100 moves between the landing gear assemblies (as shown). During landing and takeoff, each landing gear assembly 106 is in the extended position to facilitate movement of the aircraft 100 on the ground. When the aircraft 100 is in the air, the landing gear assemblies 106 are in the retracted position to minimize drag.

[0039] refer to Figures 2 to 4 Each of the landing gear assemblies 106 includes a shock absorber strut 110, one or more tires 112, and a shock absorber 113 coupled between the shock absorber strut 110 and the tires 112. The shock absorber 113 is movable relative to the shock absorber strut 110 to reduce movement on the landing gear assembly 106. In addition to the shock absorber 113, the landing gear assembly 106 may include one or more trunnions 114 coupled to the shock absorber strut 110 to allow the landing gear assembly 106 to move relative to the fuselage 102 ( Figure 1 The landing gear assembly 106 also includes a torque link 116 pivotally coupled to each other. The torque link 116 is connected to the shock strut 110 and the shock absorber 113 and allows the shock absorber 113 to move linearly relative to the shock strut 110 while preventing the shock absorber 113 and the shock strut 110 from rotating relative to each other.

[0040] The landing gear assembly 106 also includes at least one linkage mechanism 118 pivotally coupled to the shock absorber strut 110. The linkage mechanism 118 facilitates movement of the landing gear assembly 106 relative to the fuselage 102 between a retracted position and an extended position. To move the linkage mechanism 118, the landing gear assembly 106 includes an actuator 120. In the illustrated embodiment, the actuator 120 is a hydraulic actuator. However, it is contemplated that the actuator 120 could be another actuation system capable of moving the linkage mechanism 118. The actuator 120 may include an actuation cylinder 122 and a hydraulic line 125 in fluid communication with the actuation cylinder 122. The actuation cylinder 122 is connected to the linkage mechanism 118. Upon actuation, the actuator 120 moves the linkage mechanism 118 to move the landing gear assembly 106 between a retracted position and an extended position.

[0041] Linkage 118 includes a pair of pivotally coupled link members 124. In the illustrated embodiment, linkage 118 includes a first link member 124a and a second link member 124b pivotally coupled to each other. The first link member 124a may be referred to as a lower drag support, and the second link member 124b may be referred to as an upper drag support. Landing gear assembly 106 has an aperture 126 that extends through at least one linkage 118 when landing gear assembly 106 is in the extended position. Specifically, aperture 126 extends through a pair of pivotally coupled link members 124. In the illustrated embodiment, aperture 126 extends through the first link member 124a and the second link member 124b. Landing gear assembly 106 includes a locking pin 128 configured, sized, and shaped to insert into the aperture 126 extending through linkage 118. When inserted into the orifice 126, the locking pin 128 inhibits movement of a pair of pivotally coupled linkage members 124 to establish a locked state of the landing gear assembly 106 in the extended position. Specifically, when the locking pin 128 is inserted into the orifice 126, the pair of pivotally coupled linkage members 124 remain fixed to each other, thereby establishing a locked state of the landing gear assembly 106 in the extended position. In other words, when the locking pin 128 is inserted into the orifice 126, the first linkage member 124a and the second linkage member 124b are locked relative to each other, thereby preventing the landing gear assembly 106 from moving from the extended position to the retracted position. As a result, the landing gear assembly 106 is locked in the extended position. The landing gear assembly 106 may also include a marker 130 attached to the locking pin 128 to remind ground crew to remove the locking pin 128 from the orifice 126 before the aircraft 100 begins taxiing.

[0042] The landing gear assembly 106 may also include a locking hook 132 and a locking actuation lever 134 coupled to the locking hook 132 to lock the locking pin 128 in the orifice 126. When actuated by the actuator 120, for example, the locking actuation lever 134 drives the locking hook 132 toward the locking pin 128 to lock the locking pin 128 in the orifice 126.

[0043] refer to Figure 5 The aircraft 100 also includes a cockpit 136 within the nose 108 of the fuselage 102. The cockpit 136 includes one or more display devices 138 to visually provide information to the flight crew of the aircraft 100. The display devices 138 may be part of an instrument panel 140 of the aircraft 100, which may include analog instruments. As a non-limiting example, the display devices 138 may be liquid crystal displays (LCD) screens. Regardless of the type of display device 138 used, each of the display devices 138 is within the main field of view in the cockpit 136 of the aircraft 100, thereby allowing the flight crew to view the information output by the display devices 138. At least one of the display devices 138 is configured to respond to receiving a landing gear monitoring and alarm system 300 ( Figure 9 The information regarding whether the locking pin 128 is positioned within the orifice 126 to establish a locked state of the extended landing gear assembly 106 is displayed upon receiving a signal transmitted from the landing gear monitoring and alarm system 300, as discussed in detail below. Upon receiving a signal transmitted from the landing gear monitoring and alarm system 300, information regarding whether the locking pin 128 is positioned within the orifice 126 may be output on a summary page 142 of one of the display devices 138. As a limiting example, the display device 138 may be configured as a multifunction display (MFD), an electronic flight bag (EFB), or an illuminated symbol or text on the instrument panel 140.

[0044] refer to Figure 6 Display device 138, such as MFD or EFB, can display an image 144 of an aircraft 100 having landing gear assembly 106. In response to a signal received from landing gear monitoring and alarm system 300, display device 138 can, for example, change the color of the image 144 of landing gear assembly 106 (e.g., from black to red), which has a locking pin 128 disposed within a hole 126 in linkage mechanism 118. Furthermore, display device 138 can display a message 146 indicating that the locking pin 128 is disposed in the hole 126 of one or more of the landing gear assemblies 106. For example, in the depicted embodiment, message 146 shown in display device 138 indicates "nose-wheel pin engaged" to indicate that the locking pin 128 of the landing gear assembly 106 located in the nose 108 is disposed in the hole 126 of the landing gear assembly 106.

[0045] refer to Figure 7The display device 138 of the instrument panel 140 is configured to display illuminated text. Each display device 138 may correspond to one of the landing gear assemblies 106. For example, in the illustrated embodiment, the three display devices 138 include corresponding messages, namely, “nose landing gear,” “left landing gear,” and “right landing gear,” to indicate which landing gear assembly 106’s locking pin 128 is inserted into the hole 126. In this embodiment, the display device 138 is configured as an associated landing gear light 141 and may be located above the landing gear lowering and locking light 143. The display device 138 may respond to a landing gear monitoring and alarm system 300 ( Figure 9 One or more messages are received that illuminate the landing gear assembly 106, which still has the locking pin 128 in the insertion hole 126, as described in detail below.

[0046] refer to Figure 8 The display device 138 may include an Engine Indication and Crew Alarm System (EICAS) page 148. Upon receiving a signal from the landing gear monitoring and alarm system 300, the display device 138 displays information on the EICAS page 148 indicating that the locking pins 128 of one or more landing gear assemblies 106 are in the holes 126 of the linkage mechanism 118. For example, the display device 138 may display information in the form of a mark 150, such as “nose pin,” to indicate that the locking pin 128 in one of the landing gear assemblies 106 is still in the hole 126. By displaying the mark 150, “nose pin,” the display device 138 indicates that the locking pin 128 of the landing gear assembly 106 located in the nose 108 is inserted into the hole 126 of the linkage mechanism 118.

[0047] refer to Figure 9 The landing gear monitoring and warning system 300 monitors whether a locking pin 128 is positioned within an aperture 126 of at least one linkage mechanism 118. As described above, the locking pin 128 may extend through the aperture 126 through the linkage mechanism 118 (e.g., a first linkage member 124a and a second linkage member 124b) to establish a locked state of the extended landing gear assembly 106. The locking pin 128 can be considered part of the landing gear monitoring and warning system 300, which, when inserted into the aperture 126, inhibits movement of the linkage mechanism 118 to lock the landing gear assembly 106 in the extended position. Before the aircraft 100 takes off, the aperture 126 should be removed to allow the landing gear assembly 106 to move from the extended position to the retracted position. If the locking pin 128 is not removed, the landing gear monitoring and warning system 300 alerts the aircraft operators (e.g., flight crew and ground staff) that the locking pin 128 is positioned within the aperture 126 of the linkage mechanism 118.

[0048] The landing gear monitoring and alarm system 300 includes a magnetic sensor 302 disposed near the aperture 126. The magnetic sensor 302 is configured to sense a magnetic response indicating that the locking pin 128 is positioned within the aperture 126 of the linkage 118 to establish a locked state of the extended landing gear assembly 106. In other words, the magnetic sensor 302 senses disturbances and changes in the magnetic field near the aperture 126 of the linkage 118, such as intensity, direction, and flux, to determine whether the locking pin 128 is within the aperture 126 of the linkage 118. As a non-limiting example, the magnetic sensor 302 may be a Hall effect magnetic sensor. To calibrate the magnetic sensor 302, tests can be performed to sense the intensity, direction, or flux of the magnetic field near the aperture 126 when the locking pin 128 is inserted into the aperture 126 and when the locking pin 128 is not in the aperture 126. Based on this test, the magnetic sensor 302 determines whether the locking pin 128 is positioned within the aperture 126 of the linkage mechanism 118 in response to detecting the strength, direction, or flux of an identified magnetic field when the locking pin 128 is positioned within the aperture 126 during the test. In some embodiments, the magnetic sensor 302 includes a magnetic sensor-activated switch 304. The magnetic sensor 302 is configured to activate the magnetic sensor-activated switch 304 when magnetically sensing that the locking pin 128 is positioned within the aperture 126 of the linkage mechanism 118. In response to the activation of the magnetic sensor-activated switch 304, the magnetic sensor 302 generates and provides a sensor output. The sensor output indicates that the locking pin 128 is positioned within the aperture 126 of the linkage mechanism 118. The magnetic sensor 302 may also include a sensor communication module 306 configured to transmit the sensor output. The sensor communication module 306 of the magnetic sensor 302 can transmit the sensor output via wired or wireless means. In some embodiments, the sensor communication module 306 includes a transmitter configured to transmit wireless signals (e.g., wireless sensor output). As a non-limiting example, the sensor communication module 306 may be configured as a system-on-chip microcontroller including a built-in antenna capable of transmitting wireless signals, such as… and BLUETOOTH To minimize the size and cost of the landing gear monitoring and alarm system 300.

[0049] The landing gear monitoring and alarm system 300 also includes a communication module 308 that is wired or wirelessly connected to the magnetic sensor 302. The communication module 308 includes a transmitter 310 coupled to the magnetic sensor 302. Therefore, the communication module 308 is configured to receive sensor output from the magnetic sensor 302. As described above, the sensor output indicates that the locking pin 128 is disposed within the aperture 126 of the linkage mechanism 118. The communication module 308 is configured to responsively transmit a signal indicating that the locking pin 128 is disposed within the aperture 126 of the linkage mechanism 118, thereby establishing a locked state of the extended landing gear assembly 106. In other words, due to the transmitter 310, the communication module 308 is configured to transmit a signal indicating that the locking pin 128 is disposed within the aperture 126 of the linkage mechanism 118 in response to receiving a sensor output from the magnetic sensor 302, wherein the sensor output indicates that the locking pin 128 is disposed within the aperture 126 of the linkage mechanism 118. As a non-limiting example, the communication module 308 includes a microcontroller 312 configured to receive sensor output from the magnetic sensor 302. The communication module 308 may include an integrated Wi-Fi component 314 configured to wirelessly transmit a signal indicating that the locking pin 128 is positioned within the aperture 126 of the linkage mechanism 118, in order to minimize the size of the communication module 308. For example, the integrated Wi-Fi component 314 may include a built-in antenna integrated on the microcontroller 312, and the microcontroller 312 may be an integrated chip. The microcontroller 312 may be a universal host controller interface that transmits the signal indicating that the locking pin 128 is positioned within the aperture 126 of the linkage mechanism 118 via a universal asynchronous transceiver. The microcontroller 312 may be a universal host controller interface to minimize the power required to operate the microcontroller 312. Furthermore, the transmitter 310 may be a universal asynchronous transceiver to allow the magnetic sensor 302 and the communication module 308 to exchange data at their own speeds.

[0050] Communication module 308 communicates with the flight management system (FMS) 316 of aircraft 100. As a result, communication module 308 is configured to receive information from FMS 316 regarding the flight phase of aircraft 100. For example, FMS 316 may transmit flight phase information indicating the taxiing motion of aircraft 100 to communication module 308. In some embodiments, communication module 308 is configured to transmit a signal indicating that locking pin 128 is positioned within orifice 126 in linkage mechanism 118 in response to: (a) receiving a sensor output indicating that locking pin 128 is positioned within orifice 126; and (b) receiving flight phase information indicating the taxiing motion of aircraft 100 from FMS 316.

[0051] Communication module 308 communicates with at least one display device 138 via data network 318. Data network 318 may be a wired or wireless data network. As described above, display device 138 is within the main field of view in the cockpit 136 of aircraft 100 and is configured to receive a signal from communication module 308 indicating that locking pin 128 is disposed within a gap in linkage mechanism 118 to establish a locked state of the extended landing gear assembly 106. In response to receiving this signal from communication module 308, display device 138 is configured to display information regarding the locking state of locking pin 128 being disposed within gap 126 to establish a locked state of the extended landing gear assembly 106. Information regarding whether locking pin 128 is disposed within gap 126 may be output on a summary page 142 of one of display devices 138. Alternatively, display device 138 may display information on EICAS page 148 indicating that locking pin 128 of one or more of landing gear assemblies 106 is disposed within a gap 126 of linkage mechanism 118. Regardless of the configuration of the display device 138, the display device 138 can be considered as part of the landing gear monitoring and alarm system 300.

[0052] Upon receiving a sensor output from the magnetic sensor 302 indicating that the locking pin 128 is within the aperture 126, the communication module 308 is configured to transmit a signal indicating that the locking pin 128 is positioned within the aperture 126 of the linkage mechanism 118 to a ground crew handheld device 320. The ground crew handheld device 320 may be, for example, a mobile phone or any other suitable device capable of displaying information to the ground crew that the locking pin 128 is positioned within the aperture 126 of the linkage mechanism 118. After receiving this information on the ground crew handheld device 320, the ground crew can remove the locking pin 128 from the aperture 126 of the linkage mechanism 118. The communication module 308 can transmit the signal indicating that the locking pin 128 is positioned within the aperture 126 of the linkage mechanism 118 via the aircraft's onboard networking system (ONS) 322. The ONS 322 then transmits the signal via the airport wireless data network (e.g., airport...). The signal is transmitted from the network or Aircraft Communications Addressing and Reporting System (ACARS) 326 to the Airline Operations Control (AOC) server 324. The AOC server 324 then transmits the signal to the handheld device 320 of the ground crew.

[0053] Figure 10 This is a flowchart of a method 400 for operating the landing gear monitoring and alarm system 300. Method 400 begins at block 402 (i.e., the start block). Then, method 400 proceeds to block 404. In block 404, the landing gear monitoring and alarm system 300 monitors the magnetic field near the aperture 126 of one or more landing gear assemblies 106. For this purpose, the microcontroller 312 reads the sensor output from the magnetic sensor 302. Next, method 400 proceeds to block 406.

[0054] In block 406, microcontroller 312 determines whether the locking pin 128 is inserted into the aperture 126 of the linkage 118 by sensing a magnetic response indicating that the locking pin 128 is positioned within the aperture 126 of the linkage 118 to establish a locked state of the landing gear assembly 106 in the extended position. Sensing the magnetic response may require activating a magnetic sensor-activated switch 304 when the locking pin 128 is magnetically sensed to be positioned within the aperture 126. Additionally, sensing the magnetic response may require transmitting a sensor output from the magnetic sensor-activated switch 304 to the communication module 308 of the landing gear monitoring and alarm system 300 in response to the activation of the magnetic sensor-activated switch 304. Upon receiving the sensor output indicating that the locking pin 128 is positioned within the aperture 126 of the linkage 118, microcontroller 312 determines that the locking pin 128 is positioned within the aperture 126 of the linkage 118. If the locking pin 128 is not inserted into the orifice 126, method 400 proceeds to block 412, where the communication module 308 transmits a signal regarding the status of the locking pin 128. In this case, the signal indicates that the locking pin 128 is not positioned within the orifice of the linkage mechanism 118, and therefore, no alarm is activated. On the other hand, if the locking pin 128 is inserted into the orifice 126 as determined in block 406, method 400 continues to block 408.

[0055] In block 408, communication module 308 receives a signal from FMS 316 indicating the flight phase of aircraft 100. After block 408, method 400 proceeds to block 410.

[0056] In block 410, microcontroller 312 determines whether the flight phase has transitioned to taxiing based on signals received from FMS 316. If the flight phase of aircraft 100 has not yet transitioned to taxiing, method 400 proceeds to block 412. As described above, in block 412, microcontroller 312 transmits a signal indicating that locking pin 128 is not positioned within the orifice of linkage 118. After block 412, method 400 continues to block 416. In block 416, a signal indicating that locking pin 128 is not positioned within the orifice 126 of linkage 118 is transmitted to ONS 322. If the flight phase has transitioned to taxiing, as determined in block 410, method 400 proceeds to block 414.

[0057] At block 414, communication module 308 responds to: (a) a magnetic response that senses the locking pin 128 being positioned within the orifice 126 of linkage mechanism 118 to establish a locked state of the landing gear assembly in the extended position; and (b) receiving flight phase information indicating the taxiing motion of aircraft 100, and transmits a signal indicating that the locking pin 128 is inserted into the orifice 126 (i.e., an alarm signal). Following block 414, method 400 continues to block 416.

[0058] In block 416, communication module 308 transmits a signal indicating that locking pin 128 is inserted into aperture 126 to ONS 322 of aircraft 100. Alternatively, in block 416, a signal indicating that locking pin 128 is not inserted into aperture 126 is transmitted to ONS 322. Once locking pin 128 is removed from aperture 126 and is securely stored in the security locking pin box, a signal indicating that locking pin 128 is not inserted into aperture 126 can be transmitted to ONS 322. These signals can be transmitted wirelessly. After block 416, method 400 proceeds to block 418.

[0059] In block 418, a signal indicating that the locking pin 128 is inserted into the aperture 126 (i.e., an alarm signal) or a signal indicating that the locking pin 128 is not inserted into the aperture 126 is transmitted via AOC server 324 to display device 138 and handheld device 320 of ground crew. A signal indicating that the locking pin 128 is inserted into the aperture 126 (i.e., an alarm signal) is transmitted in response to sensing a magnetic response indicating that the locking pin 128 is positioned within the aperture 126 to establish a locked state of the landing gear assembly 106 in the extended position. Method 400 then proceeds to blocks 420, 422, and 424.

[0060] In each of blocks 420, 422, and 424, method 400 requires, in response to a transmitted signal received by the display device via the data network 318 of the aircraft 100, to display information on display device 138 of the aircraft 100 regarding the locking pin 128 being positioned within the aperture 126. As discussed above, display device 138 has the primary field of view in the cockpit 136 of the aircraft 100. In block 420, for some aircraft 100s, displaying information regarding the locking pin 128 being positioned within the aperture 126 requires illumination such as... Figure 7 The associated landing gear lights 141 are shown. These lights may be located above the landing gear down and lock lights 143. In box 422, for an aircraft 100 with EFB, a flashing warning may be displayed on display device 138. For example, an image 144 of the associated landing gear assembly 106 may change color (e.g., from black to red) to indicate which landing gear assembly 106 has a locking pin 128 disposed within the aperture 126, as shown. Figure 6As shown. Additionally, the display device 138 can display message 146 indicating that the locking pin 128 is disposed in a hole 126 in one or more of the landing gear assembly 106, as also shown. Figure 6 As shown. In box 424, for aircraft 100 with EICAS and MFD pages, a flashing alarm can be displayed on summary page 142 or another suitable page on display device 138 to indicate which landing gear assembly 106 is locked. For example, as Figure 8 As shown, the EICAS page 148 of display device 138 displays a message in red as a mark 150. Mark 150 indicates which landing gear assembly 106 is locked due to the locking pin 128 being located within the orifice 126 of linkage mechanism 118.

[0061] Furthermore, this disclosure includes embodiments pursuant to the following provisions:

[0062] Clause 1. A landing gear monitoring and alarm system (300), comprising:

[0063] A locking pin (128) is configured to be inserted into a hole (126) of at least one linkage (118) extending through the extended landing gear assembly (106), the locking pin inhibiting movement of at least one linkage (118) upon insertion to establish a locked state of the extended landing gear assembly (106).

[0064] A magnetic sensor (302) is disposed near the aperture (126) and configured to sense a magnetic response indicating that the locking pin (128) is disposed within the aperture (126) to establish a locked state of the extended landing gear assembly (106), and the magnetic sensor (302) is configured to generate a sensor output indicating that the locking pin (128) is disposed within the aperture (126); and

[0065] The communication module (308) has a transmitter (310) coupled to the magnetic sensor (302) to receive the sensor output indicating that the locking pin (128) is set in the aperture (126), and the communication module (308) is configured to responsively transmit a signal indicating that the locking pin (128) is set in the aperture (126) to establish a locked state of the extended landing gear assembly (106).

[0066] Clause 2. The landing gear monitoring and alarm system (300) as described in Clause 1 further includes a display device (138) in the main field of view in the cockpit (136) of the aircraft (100), the display device (138) being configured to display information regarding the locking state of the locking pin (128) being disposed in the orifice (126) to establish the extended landing gear assembly (106) in response to a transmitted signal received by the display device (138) via the data network (318) of the aircraft (100).

[0067] Clause 3. The landing gear monitoring and alarm system (300) according to Clause 1, wherein the magnetic sensor (302) includes a magnetic sensor activated switch (304), wherein the magnetic sensor (302) is configured to activate the magnetic sensor activated switch (304) and provide sensor output to the communication module (308) when magnetically sensing that the locking pin (128) is located in the aperture (126).

[0068] Clause 4. The landing gear monitoring and alarm system (300) according to Clause 1, wherein at least one linkage mechanism (118) includes a pair of pivotally coupled linkage members (124), an aperture (126) extending through the pair of pivotally coupled linkage members (124), and a locking pin (128) is configured to be inserted into the aperture (126) extending through the pair of pivotally coupled linkage members (124) to inhibit movement of the pair of pivotally coupled linkage members (124) relative to each other, thereby keeping the pair of pivotally coupled linkage members (124) in a fixed relationship with each other.

[0069] Clause 5. The landing gear monitoring and alarm system (300) according to Clause 1, wherein the communication module (308) includes a microcontroller (312) configured to receive sensor output from a magnetic sensor (302), and the communication module (308) includes an integrated WiFi component (314) configured to wirelessly transmit a signal indicating that the locking pin (128) is disposed within the aperture (126).

[0070] Clause 6. The landing gear monitoring and alarm system (300) as described in Clause 5, wherein the microcontroller (312) is a universal host controller interface that transmits a signal indicating that the locking pin (128) is positioned in the orifice (126) via a universal asynchronous transceiver.

[0071] Clause 7. The landing gear monitoring and alarm system (300) according to Clause 1, wherein the communication module (308) is configured to transmit a signal indicating that the locking pin (128) is set in the orifice (126) to a handheld device (320) of ground crew in response to receiving a sensor output indicating that the locking pin (128) is set in the orifice (126).

[0072] Clause 8. The landing gear monitoring and alarm system (300) according to Clause 1, wherein the communication module (308) is configured to transmit a signal indicating that the locking pin (128) is set in the orifice (126) in response to receiving a sensor output indicating that the locking pin (128) is set in the orifice (126) and receiving flight phase information indicating the taxiing motion of the aircraft (100).

[0073] Clause 9. The landing gear monitoring and alarm system (300) as described in Clause 1 further includes a display device (138) in the main field of view in the cockpit (136) of the aircraft (100), the display device (138) being configured to display on a summary page (142) information regarding the locking state of the locking pin (128) being disposed in the orifice (126) to establish the extended landing gear assembly (106) in response to a transmitted signal received by the display device (138) via the data network (318) of the aircraft (100).

[0074] Clause 10. A method (400) for operating a landing gear monitoring and alarm system (300), comprising:

[0075] The magnetic field near the aperture (126) of the landing gear assembly (106) is monitored. The landing gear assembly (106) includes at least one linkage (118), the aperture (126) extends through the at least one linkage (118), and the landing gear assembly (106) includes a locking pin (128) configured to be inserted into the aperture (126) when the landing gear assembly (106) is in the extended position to inhibit the movement of the at least one linkage (118) and establish a locked state of the landing gear assembly (106) in the extended position.

[0076] The sensing indicator locking pin (128) is disposed within the aperture (126) to establish a magnetic response that establishes a locked state of the landing gear assembly (106) in the extended position; and

[0077] In response to a magnetic response that indicates the locking pin (128) is positioned in the orifice (126) to establish a locked state of the landing gear assembly (106) in the extended position, a signal indicating that the locking pin (128) is inserted into the orifice (126) to establish a locked state of the landing gear assembly (106) is transmitted.

[0078] Clause 11. The method (400) according to Clause 10 further includes, in response to a transmitted signal received by the display device (138) via the data network (318) of the aircraft (100), displaying information on the display device (138) of the aircraft (100) that the locking pin (128) is disposed in the aperture (126), and the display device (138) having a primary view in the cockpit (136) of the aircraft (100).

[0079] Clause 12. The method (400) according to Clause 10, wherein sensing the magnetic response includes: activating a magnetic sensor activated switch (304) when magnetically sensing that the locking pin (128) is disposed in the aperture (126), and in response to activating the magnetic sensor activated switch (304), transmitting a sensor output from the magnetic sensor activated switch (304) to a communication module (308) of the landing gear monitoring and alarm system (300).

[0080] Clause 13. The method (400) according to Clause 10, wherein transmitting a signal indicating that the locking pin (128) is inserted into the aperture (126) includes wirelessly transmitting a signal indicating that the locking pin (128) is inserted into the aperture (126).

[0081] Clause 14. The method (400) according to Clause 10, wherein the transmission of the signal indicating that the locking pin (128) is inserted into the aperture (126) includes the transmission of the signal indicating that the locking pin (128) is inserted into the aperture (126) via a universal asynchronous transceiver.

[0082] Clause 15. The method (400) according to Clause 10, wherein transmitting the signal indicating that the locking pin (128) is inserted into the aperture (126) includes a magnetic response in response to sensing that the locking pin (128) is positioned in the aperture (126) to establish a locked state of the landing gear assembly (106) in the extended position, transmitting the signal indicating that the locking pin (128) is positioned in the aperture (126) to a handheld device (320) of the ground crew.

[0083] Clause 16. The method (400) according to Clause 10, wherein the signal indicating that the locking pin (128) is inserted into the aperture (126) includes a magnetic response in response to sensing that the locking pin (128) is disposed in the aperture (126) to establish a locked state of the landing gear assembly (106) in the extended position, and receiving flight phase information indicating the taxiing motion of the aircraft (100), the signal indicating that the locking pin (128) is disposed in the aperture (126).

[0084] Clause 17. The method (400) according to Clause 10 further includes, in response to the display device (138) receiving the transmitted signal via the data network (318) of the aircraft (100), displaying information about the locking pin (128) disposed in the aperture (126) on a summary page (142) displayed by the display device (138).

[0085] Clause 18. An aircraft (100), comprising:

[0086] Fuselage (102);

[0087] A landing gear assembly (106) movable relative to the fuselage (102), the landing gear assembly (106) having an extended position, the landing gear assembly (106) including at least one linkage mechanism (118) and an aperture (126) extending through the at least one linkage mechanism (118), the landing gear assembly (106) including a locking pin (128) configured to insert into the aperture (126) extending through the at least one linkage mechanism (118), the locking pin, upon insertion, inhibiting movement of the at least one linkage mechanism (118) to establish a locked state of the landing gear assembly (106) in the extended position; and

[0088] A landing gear monitoring and alarm system (300) coupled to the landing gear assembly (106) includes:

[0089] A magnetic sensor (302) is disposed near the aperture (126) and configured to sense a magnetic response indicating that the locking pin (128) is disposed within the aperture (126) to establish a locked state of the landing gear assembly (106) in the extended position; and the magnetic sensor (302) is configured to generate a sensor output indicating that the locking pin (128) is disposed within the aperture (126); and

[0090] The communication module (308) has a transmitter (310) coupled to the magnetic sensor (302) to receive a sensor output indicating that the locking pin (128) is set in the orifice (126), and the communication module (308) is configured to responsively transmit a signal indicating that the locking pin (128) is set in the orifice (126) to establish a locked state of the landing gear assembly (106) in the extended position.

[0091] Clause 19. The aircraft (100) as described in Clause 18 further includes a cockpit (136) and a display device (138) disposed in the cockpit (136), the display device (138) being within the main field of view in the cockpit (136), the display device (138) being configured to display information relating to a locking pin (128) disposed in an aperture (126) to establish a locking state of the landing gear assembly (106) in an extended position, in response to the display device (138) receiving a transmitted signal via the data network (318) of the aircraft (100).

[0092] Clause 20. The aircraft (100) according to Clause 18, wherein the magnetic sensor (302) includes a magnetic sensor activated switch (304), wherein the magnetic sensor (302) is configured to activate the magnetic sensor activated switch (304) when magnetically sensing that the locking pin (128) is disposed in the aperture (126), and to provide the sensor output to the communication module (308).

[0093] As used herein, a system, apparatus, structure, article, element, component, or hardware "configured" to perform a specified function is indeed capable of performing the specified function without any changes, rather than merely having the potential to perform the specified function after further modification. In other words, a system, apparatus, structure, article, element, component, or hardware "configured" to perform a specified function is specifically selected, created, implemented, utilized, programmed, and / or designed for performing the specified function. As used herein, "configured" means an existing feature of the system, apparatus, structure, article, element, component, or hardware that enables the system, apparatus, structure, article, element, component, or hardware to perform the specified function without further modification. For the purposes of this disclosure, a system, apparatus, structure, article, element, component, or hardware described as "configured" to perform a particular function may be additionally or alternatively described as "suitable" and / or "operably" to perform that function.

[0094] The illustrations of the embodiments described herein are intended to provide a general understanding of the structure of various embodiments. These illustrations are not intended to be a complete description of all elements and features of apparatuses and systems utilizing the structures or methods described herein. Many other embodiments will likely be apparent to those skilled in the art upon review of this disclosure. Other embodiments may be utilized and other embodiments may be derived from this disclosure, allowing structural and logical substitutions and changes to be made without departing from the scope of this disclosure. For example, the embodiments may be performed in a different order than that shown. Figure 4 The operations listed in method 400 may be performed simultaneously (or in combination), with two or more operations possible, or one or more operations may be omitted. For illustration, electric field strength data may be generated prior to the generation of an electric arc, such as simultaneously with the application of voltage to a corona generator. Therefore, this disclosure and the accompanying drawings should be considered illustrative rather than restrictive.

Claims

1. A landing gear monitoring and alarm system (300) for an aircraft, said landing gear monitoring and alarm system comprising: A locking pin (128) is configured to be inserted into a hole (126) of at least one linkage (118) extending through the extended landing gear assembly (106), the locking pin inhibiting movement of at least one of the linkages (118) upon insertion to establish a locked state of the extended landing gear assembly (106). A locking hook and a locking actuating rod, the locking actuating rod being connected to the locking hook and the at least one linkage member, wherein actuation of the locking actuating rod causes the locking hook to move to hook the locking pin, thereby locking the locking pin in the orifice, thereby inhibiting the movement of the at least one linkage mechanism and locking the protruding landing gear assembly in the locked state; A magnetic sensor (302), disposed near the aperture (126) and configured to sense a magnetic response indicating that the locking pin (128) is disposed within the aperture (126) to establish the locked state of the extended landing gear assembly (106), and the magnetic sensor (302) is configured to generate a sensor output indicating that the locking pin (128) is disposed within the aperture (126); and The communication module (308) has a transmitter (310) coupled to the magnetic sensor (302) to receive the sensor output indicating that the locking pin (128) is disposed in the aperture (126), and the communication module (308) is configured to responsively transmit a signal indicating that the locking pin (128) is disposed in the aperture (126) to establish the locking state of the extended landing gear assembly (106).

2. The landing gear monitoring and alarm system (300) of claim 1 further includes a display device (138) in the main field of view in the cockpit (136) of the aircraft (100), the display device (138) being configured to display information regarding the locking state of the locking pin (128) being disposed in the orifice (126) to establish the extended landing gear assembly (106) in response to a transmitted signal received by the display device (138) via the data network (318) of the aircraft (100).

3. The landing gear monitoring and alarm system (300) according to claim 1, wherein, The magnetic sensor (302) includes a magnetic sensor activated switch (304), wherein the magnetic sensor (302) is configured to activate the magnetic sensor activated switch (304) when magnetically sensing that the locking pin (128) is disposed in the aperture (126), and to provide the sensor output to the communication module (308).

4. The landing gear monitoring and alarm system (300) according to claim 1, wherein, At least one of the linkage mechanisms (118) includes a pair of pivotally coupled link members (124), the aperture (126) extending through the pair of pivotally coupled link members (124), and the locking pin (128) is configured to be inserted into the aperture (126) extending through the pair of pivotally coupled link members (124) to inhibit movement of the pair of pivotally coupled link members (124) relative to each other, thereby keeping the pair of pivotally coupled link members (124) in a fixed relationship with each other.

5. The landing gear monitoring and alarm system (300) according to claim 1, wherein, The communication module (308) includes a microcontroller (312) configured to receive the sensor output from the magnetic sensor (302), and the communication module (308) includes an integrated WiFi component (314) configured to wirelessly transmit a signal indicating that the locking pin (128) is positioned within the aperture (126).

6. The landing gear monitoring and alarm system (300) according to claim 5, wherein, The microcontroller (312) is a general host controller interface that transmits signals via a universal asynchronous transceiver indicating that the locking pin (128) is positioned within the aperture (126).

7. The landing gear monitoring and alarm system (300) according to claim 5, wherein, The communication module (308) is configured to transmit a signal indicating that the locking pin (128) is positioned in the aperture (126) to a handheld device (320) of ground crew in response to receiving a sensor output indicating that the locking pin (128) is positioned in the aperture (126).

8. The landing gear monitoring and alarm system (300) according to any one of claims 1 to 7, wherein, The communication module includes a microcontroller configured to determine whether a flight phase has transitioned to taxiing based on a signal from the flight management system and to respond when a transition to taxiing occurs. The communication module (308) is configured to transmit a signal indicating that the locking pin (128) is positioned in the orifice (126) in response to receiving a sensor output indicating that the locking pin (128) is positioned in the orifice (126) and receiving flight phase information indicating the taxiing motion of the aircraft (100).

9. The landing gear monitoring and alarm system (300) of claim 1, comprising an aircraft (100), the aircraft comprising: Fuselage (102); A landing gear assembly (106) movable relative to the fuselage (102), the landing gear assembly (106) having an extended position, the landing gear assembly (106) including at least one linkage mechanism (118) and an aperture (126) extending through at least one of the linkage mechanisms (118), the landing gear assembly (106) including a locking pin (128) configured to insert into the aperture (126) extending through at least one of the linkage mechanisms (118), the locking pin, upon insertion, inhibiting movement of at least one of the linkage mechanisms (118) to establish a locked state of the landing gear assembly (106) in the extended position; and The cockpit (136) and the display device (138) disposed in the cockpit (136), the display device (138) being within the main field of view of the cockpit (136), the display device (138) being configured to display information regarding the locking state of the locking pin (128) disposed in the aperture (126) to establish the landing gear assembly (106) in the extended position, in response to a transmitted signal received by the display device (138) via the data network (318) of the aircraft (100).

10. A method (400) for operating a landing gear monitoring and alarm system (300) in an aircraft, the method comprising: The magnetic field near the aperture (126) of the landing gear assembly (106) is monitored. The landing gear assembly (106) includes at least one linkage (118) through which the aperture (126) extends. The landing gear assembly (106) includes a locking pin (128) configured to be inserted into the aperture (126) when the landing gear assembly (106) is in the extended position to inhibit movement of at least one linkage (118) and establish a locked state of the landing gear assembly (106) in the extended position. A locking actuator is driven to cause a locking hook to engage the locking pin, thereby locking the locking pin in place and inhibiting the movement of at least one of the linkage mechanisms, thereby locking the landing gear assembly in the extended position. The sensing indicates the magnetic response of the locking pin (128) being disposed within the aperture (126) to establish the locking state of the landing gear assembly (106) in the extended position; and In response to sensing the magnetic response indicating that the locking pin (128) is disposed in the aperture (126) to establish the locking state of the landing gear assembly (106) in the extended position, a signal indicating that the locking pin (128) is inserted into the aperture (126) to establish the locking state of the landing gear assembly (106) is transmitted.

11. The method (400) of claim 10, further comprising, in response to a transmitted signal received by a display device (138) of the aircraft (100) via a data network (318) of the aircraft (100), displaying on the display device (138) information about the locking pin (128) being disposed in the aperture (126), and the display device (138) having a primary view in the cockpit (136) of the aircraft (100).

12. The method (400) according to claim 10, wherein, Sensing the magnetic response includes: activating a magnetic sensor activated switch (304) when the locking pin (128) is magnetically sensed to be disposed in the aperture (126), and in response to activating the magnetic sensor activated switch (304), transmitting a sensor output from the magnetic sensor activated switch (304) to the communication module (308) of the landing gear monitoring and alarm system (300).

13. The method (400) of claim 10, wherein transmitting a signal indicating that the locking pin (128) is inserted into the aperture (126) comprises wirelessly transmitting a signal indicating that the locking pin (128) is inserted into the aperture (126), or transmitting a signal indicating that the locking pin (128) is inserted into the aperture (126) via a universal asynchronous transceiver.

14. The method (400) according to claim 10, wherein, The communication module includes a microcontroller configured to determine whether a flight phase has transitioned to taxiing based on a signal from the flight management system. The transmission of a signal indicating that the locking pin (128) is inserted into the orifice (126) includes, when determining that the flight phase has transitioned to taxiing, transmitting the signal indicating that the locking pin (128) is positioned in the orifice (126) to establish the locking state of the landing gear assembly (106) in the extended position, and receiving flight phase information indicating the taxiing movement of the aircraft (100).

15. The method (400) according to any one of claims 10 to 14, further comprising, in response to a transmitted signal received by the display device (138) via the data network (318) of the aircraft (100), displaying information on a summary page (142) displayed by the display device (138) regarding the locking pin (128) being disposed within the aperture (126).

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