Landing configuration control system for amphibious aircraft based on three-position landing gear handle

Abstract

The present invention proposes a landing configuration control system for amphibious aircraft based on a three-position landing gear handle design. The control system primarily includes a crew operation module, a landing gear control module, a landing gear wheel actuation and positioning feedback system, a landing configuration determination module, an information display and warning module, and a configuration data module. This "human-centric" design preserves the operational habits of land-based aircraft. After takeoff, the landing gear handle is pulled to the "air" position; during landing, the handle is pulled to the "land" position; and during water contact, the handle is pulled to the "landing" position. This eliminates the need for the crew to separately operate an amphibious aircraft selector switch or equivalent component after takeoff and before landing, which incurs additional workload and attention. This improves the human factors design of the cockpit. Furthermore, without increasing workload, this design avoids the problem of configuration warning failures caused by the crew failing to operate the amphibious aircraft selector switch, thereby enhancing flight safety.

Description

Technical Field

[0001] The present invention relates to the field of control and regulation, and in particular to the control of the course, altitude or attitude of an aircraft. Background Art

[0002] Land-based aircraft landing gear is used for ground taxiing, takeoff, and landing. To reduce drag, the aircraft retracts the landing gear after takeoff and lowers it before landing to facilitate post-touchdown rollout. To ensure a safe landing, land-based aircraft crews must perform a quick checklist before landing. This involves the pilot and co-pilot making calls, repeating commands, and cross-checking to ensure the landing gear is extended during landing. This ensures the correct landing configuration and a safe, controllable flight. Furthermore, the aircraft is equipped with a landing configuration control system. This computer monitors information such as ground clearance, throttle angle, and flap position to determine the aircraft's configuration. It also monitors whether the landing gear is in the extended position. If the aircraft is low, the throttle is low, and the flaps are extended, the computer deems the aircraft in landing configuration. If the landing gear is not extended, a landing configuration warning signal is issued to the crew, prompting them to lower the landing gear as soon as possible to prevent human error.

[0003] Amphibious aircraft and conventional land-based aircraft are similar in design, but there is a significant difference in their operation. Amphibious aircraft are required to lower the landing gear when landing and retract the landing gear when landing on water. If the landing gear is not lowered when landing or not retracted when landing on water, dangerous or even catastrophic events may occur.

[0004] Similarly, in addition to the aforementioned operational requirements for crew cross-checks, amphibious aircraft must also assess the aircraft configuration and landing gear status. If the landing gear status is abnormal in the landing configuration, the crew should be provided with warnings such as "Landing configuration landing gear not extended" or "Water landing configuration landing gear not retracted" to prevent human errors due to omissions. Furthermore, due to the ability of amphibious aircraft to both land and water, to prevent human errors due to mode errors or negligence, the aircraft should also provide intuitive visual, auditory, or combined reminders of "landing mode" or "water landing mode."

[0005] Since the flight states of amphibious aircraft are similar when landing and landing on water, and the landing water and land environments are relatively similar, how to provide the crew with efficient "preparation for landing or landing on water information and related configuration warning information" has been a long-standing design problem. Existing aircraft, such as the Russian Be200ES, Canadian CL-415 series and other civil amphibious aircraft, all use manual operation buttons / knobs by the crew to pre-select the "landing or landing on water" selection switch before each landing, and provide the landing configuration control system with a manual input source as a judgment basis in advance (such as the method proposed in the literature "Chen Zhenxing, Wu Haiyan. Research on landing configuration warning of large civil amphibious aircraft [J]. Popular Science, 2014 (11): 96-97"); there are also considerations of using integrated avionics equipment, such as the patent "CN 109144079B, "A Landing Configuration Control System for Amphibious Aircraft Based on Integrated Avionics," proposes a design that combines an onboard terrain database and aircraft position information (such as inertial navigation and attitude and heading systems) to automatically determine the aircraft's impending landing or water landing environment. Among the aforementioned technologies, manually preselecting the landing or water landing switch by the crew is an acceptable design approach. However, in actual use, the preselection method, which requires operational confirmation for each takeoff and landing, has been reported by crews as requiring too many preselection operations and imposing an unacceptable workload. Furthermore, the single preselection confirmation method may lead to human errors such as omissions and pattern errors in subsequent multiple landing (landing gear handle down) / water landing (landing gear handle kept up) alternating operations. This requires additional attention from the crew, and human factor safety design is relatively rare. The use of integrated avionics automatic judgment methods places excessive demands on equipment reliability (e.g., very high requirements for land and water predictions for landings at land airports near waterfronts or artificial islands), safety (high accuracy requirements for forward and downward landing point predictions), and maintenance costs (terrestrial data requires monthly updates). The system design is also complex and difficult, and the crew is required to preselect the "landing or water" selection switch before each landing to activate the landing configuration control system, which also presents the problem of excessive crew operation and excessive workload. Due to its high technical requirements and overly complex design, this method has not been put into practical use. It is foreseeable that it will be difficult to implement in the future due to the constraints of the overall design technology and safety requirements of civil (manned) aircraft.

[0006] Taking a typical one-hour, on-site, round-trip takeoff and landing training (including approximately eight takeoffs and landings) at a typical land airport as an example, the configuration control technology used by existing amphibious aircraft and the configuration control technology based on integrated avionics equipment require a total of 32 operations / checks on the landing gear handle and land selector, while conventional land-based aircraft require a total of 16 operations. This shows that currently used solutions / unused methods require the crew to provide more attention and operation than the landing process of land-based aircraft. To address this problem, the present invention provides an amphibious aircraft landing configuration control system based on a three-position landing gear handle design, which can reduce the number of attention and operations to 16, reaching the same level as mainstream land-based aircraft. This clear and practical system design architecture significantly reduces the crew's operational burden and effectively improves flight safety. Summary of the Invention

[0007] The objects of the present invention are:

[0008] An embodiment of the present invention provides an amphibious aircraft landing configuration control system based on a three-position landing gear handle design, so as to at least solve the problems of cumbersome crew operations, excessive workload and the need for additional attention during the landing configuration confirmation process of an amphibious aircraft, and to provide a landing configuration control system that can improve flight safety, is simple for crew operations, and is designed to suit current reality.

[0009] The technical solution of the present invention is:

[0010] According to one embodiment of the present invention, a landing configuration control system for an amphibious aircraft based on a three-position landing gear handle design is provided, comprising: a crew operation module, a landing gear control module, a landing gear wheel actuation and positioning feedback module, a landing configuration determination module, an information display and warning module, a configuration data module, and corresponding procedures in a conventional quick checklist required to be executed by the crew during relevant aircraft phases.

[0011] The crew operation module includes at least one three-position landing gear handle device. Compared with the two-position landing gear handle device commonly used in land-based aircraft, this is a landing gear handle device with three stable parking positions and can be selected from three parking positions after being pulled up. In addition, three mode signals can be output at the corresponding stable positions. In this embodiment, the three mode signals respectively represent the configuration state that the aircraft is currently in or about to be in, representing "land", "air" or "water surface" respectively.

[0012] Optionally, the crew operating module includes an alarm suppression switch for suppressing the sound, light and other signals of the landing gear configuration alarm.

[0013] The landing gear control module is interconnected with the crew operation module, receives the mode signal provided by the three-position landing gear handle device, and after analysis and processing, sends the landing gear retraction and extension signal to the landing gear wheel actuation and in-position feedback system.

[0014] The landing gear wheel actuation and position feedback system is interconnected with the landing gear control module, receives the landing gear retraction and extension signal, and drives the landing gear wheels to retract / lower. After the wheels are in position, a retraction / lowering position signal can be obtained, and the signal is sent to the landing gear control module.

[0015] The landing configuration determination module is interconnected with the landing gear control module to receive the landing gear wheel retraction / detraction signals processed by the landing gear control module and the mode signal from the three-position landing gear handle. It is also interconnected with the configuration data module to receive aircraft configuration information. After analysis by the module itself, the aircraft configuration status is transmitted to the information display and warning module, providing visual information and audible and visual warnings to the crew.

[0016] Preferably, the landing configuration module receives warning suppression switch information. When the warning suppression switch is activated, the landing configuration module can suppress the sound and light signals of the configuration warning related to the landing gear.

[0017] The configuration data module at least includes the aircraft radio altitude signal.

[0018] Preferably, the aircraft configuration data includes airspeed, flap position, throttle lever position, engine throttle valve opening, water rudder position, wheel load signal, etc.

[0019] The information display and warning module includes a configuration information indication module and a configuration warning module, which are respectively used to indicate the current configuration information at appropriate locations and provide clear and direct warning information when the aircraft configuration is abnormal.

[0020] Optionally, the "land", "water surface" and "air" logos on the three-position landing gear handle device can be hollowed out and lit to serve as part of the configuration information indication module.

[0021] The corresponding inspection procedures of the flight phase quick checklist require the operation, reading and cross-checking of the landing gear handle position at least in the inspection procedures of necessary stages such as take-off, landing and before landing on the water.

[0022] According to another embodiment of the present invention, a landing configuration control system for an amphibious aircraft based on a three-position landing gear handle design is provided, comprising: a crew operation module, a landing gear control module, a landing gear wheel actuation and positioning feedback module, a landing configuration determination module, an information display and warning module, a configuration data module, and corresponding procedures in a quick checklist required to be executed by the crew during conventional aircraft-related phases.

[0023] Based on safety design and index allocation requirements, the landing configuration module bypasses the landing gear control module, and is interconnected with the crew operation module, landing gear wheel actuation and in-position feedback system, directly receiving the landing gear wheel retraction / lowering in-position signal and the mode signal provided by the three-position landing gear handle device.

[0024] The advantages and beneficial effects of the present invention are:

[0025] The present invention is "people-centered" and establishes a landing configuration control system for amphibious aircraft based on a three-position landing gear handle design. Compared with the operation process of land-based aircraft: after takeoff, the landing gear handle is pulled up to retract the landing gear; before landing, the landing gear handle is pulled up to lower the landing gear. If the handle is not lowered before landing, an alarm is issued. Through the present invention, the crew of an amphibious aircraft can retain the operating habits of a land-based aircraft, pull up the landing gear handle to the "air" position after takeoff, pull up the landing gear handle to the "land" position when landing, and pull up the landing gear handle to the "landing" position when landing on water. This eliminates the problem that the crew needs to separately operate the amphibious selection switch or equivalent components after takeoff and before landing of the amphibious aircraft, which requires additional workload and attention, thereby improving the level of human factor design in the cockpit; at the same time, without increasing the workload, the problem of the crew's omission of operating the amphibious selection switch, resulting in the failure of the configuration alarm, is avoided, thereby improving the level of flight safety; at the same time, the configuration information indication module and the setting of the quick checklist content of the corresponding flight phase provide the crew with clear aircraft landing configuration information through intuitive visual distinction of indications, as well as conventional operations, calls and cross-checks, thereby greatly reducing the possibility of mode selection errors; finally, the present invention has a clear and concise architecture, low design, manufacturing, training and maintenance costs, and practical design and application. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following briefly introduces the drawings required for use in the embodiments of the present invention. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative work.

[0027] Figure 1 This is a structural diagram of an amphibious aircraft landing configuration control system based on a three-position landing gear handle design provided by the present invention (Example 1).

[0028] Figure 1The invention comprises a crew operation module (1) (including a three-position landing gear handle device (8) and optionally a warning inhibition switch (9)), a landing gear control module (2), a landing gear wheel actuation and positioning feedback system (3), a landing configuration judgment module (4), an information display and warning module (5) (including a configuration information indication module (10) and a configuration warning module (11)), a configuration data module (6), and corresponding procedures (7) for calling, operating and cross-checking the landing gear in the flight phase quick checklist.

[0029] Figure 2 The present invention provides a flow chart of an amphibious aircraft landing configuration control system based on a three-position landing gear handle design.

[0030] Figure 3 This is a structural diagram of another amphibious aircraft landing configuration control system provided by the present invention based on a three-position landing gear handle design (Example 2).

[0031] Figure 3 In the invention, the crew operation module (1) (including a three-position landing gear handle device (8), optionally including a warning inhibition switch (9), a landing gear control module (2), a landing gear wheel actuation and positioning feedback system (3), a landing configuration judgment module (4), an information display and warning module (5) (including a configuration information indication module (10) and a configuration warning module (11)), a configuration data module (6), and corresponding procedures (7) for calling, operating and cross-checking the landing gear in the flight phase quick checklist. DETAILED DESCRIPTION

[0032] To make the purpose, technical solutions, and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making any creative work are within the scope of protection of the present invention.

[0033] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other, and the embodiments can refer to and quote each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0034] The present invention relates to the field of control and regulation, and in particular to the control of the course, altitude or attitude of an aircraft. The present invention proposes a landing configuration control system for an amphibious aircraft based on a three-position landing gear handle design, which mainly comprises a crew operation module (1) (including a three-position landing gear handle device (8) and optionally including an alarm suppression switch (9)), a landing gear control module (2), a landing gear wheel actuation and in-position feedback system (3), a landing configuration judgment module (4), an information display and alarm module (5) (including a configuration information indication module (10) and a configuration alarm module (11)), a configuration data module (6), and corresponding procedures (7) for calling, operating and cross-checking the landing gear in a quick checklist during the flight phase.

[0035] Example 1:

[0036] In this embodiment, a design of an amphibious aircraft landing configuration control system architecture based on a three-position landing gear handle is provided. Figure 1 As shown in the system flow chart Figure 2 As shown. As used below, the term "module" may be a combination of software and / or hardware that implements a predetermined function. The apparatus described in the embodiments is preferably implemented in software and hardware, but separate implementations of hardware or software are also possible and contemplated. The implementation includes the following steps:

[0037] See also Figure 1 During the takeoff phase of an amphibious aircraft, after the crew confirms a stable and positive ascent, they pull up and place the three-position landing gear handle device (8) in the crew operation module (1) to the "air" position according to the conventional operating habits of land-based aircraft and the (7) flight phase quick checklist. The landing gear control module (2) receives the signal, processes it, and transmits it to the landing gear wheel actuation and in-position feedback system (3), which controls the landing gear to the retracted state and maintains it. The landing gear retracted in-position signal is transmitted back to the landing gear control module (2).

[0038] The landing configuration judgment module (4) and the landing gear control module (2) are interconnected to receive a landing gear retracted position signal and a three-position landing gear handle position signal, and after processing, the received signals are displayed in the configuration information indication module (10) in the information display and warning module (5).

[0039] The landing configuration judgment module (4) receives data from the configuration data module (6). When the aircraft takes off from the ground for a period of time or at a certain height, if there is still no "air" position signal in the received three-position landing gear handle position, a landing gear configuration warning signal is sent to the configuration warning module (11) in the information display and warning module (5) to remind the crew to pull up the three-position landing gear handle and place it in the "air" position.

[0040] See also Figure 1 and Figure 2When the aircraft is ready to land, the crew operates the three-position landing gear handle device (8) in the crew operation module (1) according to the conventional operating habits of land-based aircraft and the (7) flight phase quick checklist. If landing, the aircraft is pulled up and placed in the "land" position. The landing gear control module (2) receives the signal, processes it and transmits it to the landing gear wheel actuation and in-position feedback system (3), controls the landing gear to be lowered and maintained, and the landing gear lowered in-position signal is transmitted back to the landing gear control module (2); if landing on water, the aircraft is pulled up and placed in the "water surface" position. The landing gear control module (2) receives the signal, processes it and transmits it to the landing gear wheel actuation and in-position feedback system (3), controls the landing gear to be maintained in the retracted state, and the landing gear retracted in-position signal is transmitted back to the landing gear control module (2).

[0041] 10) The configuration information indication module provides the crew with intuitive and necessary indications of the target configuration and current configuration status during flight.

[0042] The landing configuration judgment module (4) receives data from the configuration data module (6). When it is determined that the aircraft is about to land through the configuration data such as airspeed, radio altitude, flap position, throttle position, etc., if the received three-position landing gear handle position is still the "air" position signal, a landing gear configuration warning signal is sent to the information display and warning module (5) to remind the crew to operate the three-position landing gear handle to the landing configuration position, that is, the "land" or "water" position.

[0043] Optionally, an alarm suppression switch (9) is provided. In the landing configuration abnormality alarm or special mission mode, the crew can suppress the sound and light alarm signals emitted by the configuration alarm module (11) in the information display and alarm module (5) by pressing the alarm suppression switch (9).

[0044] Through the description of the above embodiments, those skilled in the art will clearly understand that the methods according to the above embodiments can be implemented using both software and hardware, or alternatively, using a pure hardware or pure software architecture, although in many cases the former is the preferred embodiment. Based on this understanding, some technical solutions of the present invention can enable the terminal device hardware to execute the methods described in various embodiments of the present invention in the form of software products, instructions in a storage medium, and the like.

[0045] Example 2:

[0046] In this embodiment, another amphibious aircraft landing configuration control system architecture design based on a three-position landing gear handle design is provided. This system architecture design is used to implement the above-mentioned embodiments and preferred implementation methods, and those that have been explained will not be repeated here.

[0047] There is no significant difference between this embodiment and embodiment 1 in crew operation. Unlike embodiment 1, the landing configuration judgment module (4) in this embodiment is directly interconnected with the crew operation module (1) and the landing gear wheel actuation and in-position feedback system (3), so that the system architecture design can adjust the safety level of the landing gear control module (2) and the landing configuration judgment module (4) in a targeted manner, ensuring that the overall safety and redundancy level of the system are satisfactory during the actual development process.

[0048] Through the description of the above implementation method, in a typical implementation process, the crew's operation of the landing gear handle during the take-off and landing of an amphibious aircraft is very similar, and the inspection and attention items during the operation process are consistent with the requirements of conventional land-based aircraft. Before landing, only the three-position landing gear handle needs to be pulled once, and no additional operations and precautions are required. The workload is reduced to the same level as that of mainstream land-based aircraft. At the same time, the configuration information indications and warnings are clear and concise, and easy for the crew to understand.

[0049] The present invention is "people-centered" and establishes a landing configuration control system for amphibious aircraft based on a three-position landing gear handle design, integrating the previous configuration judgment of amphibious aircraft using a separate amphibious selection device operation into the retraction and extension operation of the landing gear itself. Through the present invention, the crew of an amphibious aircraft can retain the operating habits of a land-based aircraft, pull up the landing gear handle to the "air" position after takeoff, pull up the landing gear handle to the "land" position when landing, and pull up the landing gear handle to the "landing" position when landing on water. This eliminates the problem that the crew needs to separately operate the amphibious selection switch or equivalent components after takeoff and before landing of the amphibious aircraft, which requires additional workload and attention, thereby improving the level of human factor design in the cockpit; at the same time, without increasing the workload, the problem of the crew's omission of operating the amphibious selection switch, resulting in the failure of the configuration alarm, is avoided, thereby improving the level of flight safety; at the same time, the configuration information indication module and the setting of the quick checklist content of the corresponding flight phase provide the crew with clear aircraft landing configuration information through intuitive visual distinction of indications, as well as conventional operations, calls and cross-checks, thereby greatly reducing the possibility of mode selection errors; finally, the present invention has a clear and concise architecture, low design, manufacturing, training and maintenance costs, and practical design and application.

[0050] It should be noted that the above process operations can be applied in combination to different degrees. For the sake of simplicity, the implementation methods of various combinations will not be described in detail. Technical personnel in this field can flexibly adjust the order of the above operating steps according to actual needs, or flexibly combine the above steps.

[0051] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, but the scope of protection of the present invention is not limited thereto. Any technician familiar with the field can easily think of various equivalent modifications or replacements within the technical scope disclosed by the present invention, and these modifications or replacements should all be covered by the scope of protection of the present invention.

Claims

1. A landing configuration control system for an amphibious aircraft based on a three-position landing gear handle, characterized in that: include: Crew operation module (1), landing gear control module (2), landing gear wheel actuation and positioning feedback system (3), landing configuration judgment module (4), information display and warning module (5), configuration data module (6), flight phase quick checklist (7), wherein: The crew operating module (1) comprises: a three-position landing gear handle device (8); The three-position landing gear handle device (8) serves as an input signal for the landing gear retraction and extension control of the landing gear control module (2) and the landing configuration judgment module (4), synchronously completing the landing gear retraction and extension control and providing a pre-set signal for the landing configuration control; The three-position landing gear handle device (8) includes three gear positions: "land", "air" and "water surface". The landing configuration judgment module (4) receives the "land", "air" or "water surface" gear position signal from the three-position landing gear handle device (8), and provides target and current configuration information in combination with the configuration data on the aircraft; When the lifting handle is placed in the "Land" position, the "Land" gear position sends a position signal, and the landing gear wheels are lowered and kept in place; When the lifting handle is placed in the "air" position, the "air" gear position sends a position signal, and the landing gear wheels are retracted and kept in place; When the lifting handle is placed in the "surface" position, the "surface" position sends a position signal, and the landing gear wheels are retracted and held in place; The alarm module (5) comprises: a configuration information indication module (10) and a configuration alarm module (11); A configuration information indication module (10) is used to provide the crew with intuitive and necessary indications of the target configuration and the current configuration status during flight; During the takeoff phase of the amphibious aircraft, the three-position landing gear handle device (8) in the crew operation module (1) is pulled up and placed in the "air" position based on the flight phase quick checklist (7); The landing gear control module (2) receives the signal, processes it and transmits it to the landing gear wheel actuation and position feedback system (3), controls the landing gear to be in the retracted state and maintains it, and transmits the landing gear retracted position signal back to the landing gear control module (2); The landing configuration judgment module (4) and the landing gear control module (2) are interconnected to receive a landing gear retracted position signal and a three-position landing gear handle position signal, and after processing, the received signals are displayed in the configuration information indication module (10) in the information display and warning module (5); The landing configuration judgment module (4) receives data from the configuration data module (6). When the aircraft takes off from the ground for a period of time or at a certain height, if the received three-position landing gear handle still does not have an "air" position signal, a landing gear configuration warning signal is sent to the configuration warning module (11) in the information display and warning module (5), issuing a warning to pull the three-position landing gear handle and place it in the "air" position.

2. The system according to claim 1, wherein: in: The flight phase quick checklist (7) includes: relevant data related to the call, operation and cross-check of the landing gear.

3. The system according to claim 1, wherein: in: When the aircraft is ready to land, the crew operates the three-position landing gear handle device (8) in the crew operation module (1) according to the conventional land-based aircraft operating habits and the (7) flight phase quick checklist: If landing, the aircraft is lifted and placed in the "land" position. The landing gear control module (2) receives the signal, processes it and transmits it to the landing gear wheel actuation and position feedback system (3), controls the landing gear to be lowered and held, and transmits the landing gear lowered position signal back to the landing gear control module (2); If the aircraft touches the water, it is lifted and placed on the "water surface" position. The landing gear control module (2) receives the signal, processes it and transmits it to the landing gear wheel actuation and in-position feedback system (3), controls the landing gear to remain in the retracted state, and the landing gear retracted in-position signal is transmitted back to the landing gear control module (2).

4. The system according to claim 1, wherein: in: The landing configuration judgment module (4) receives data from the configuration data module (6); When it is determined that the aircraft is about to land through configuration data such as airspeed, radio altitude, flap position, and throttle position, if the received three-position landing gear handle position is still the "air" position signal, a landing gear configuration warning signal is sent to the information display and warning module (5) to remind the crew to operate the three-position landing gear handle to the landing configuration position, that is, the "land" or "water" position.

5. The system according to claim 1, wherein: in: The unit operation module (1) further comprises: an alarm suppression switch (9); The alarm suppression switch (9) is used to suppress the sound and light alarm signals emitted by the configuration alarm module (11) in the information display and alarm module (5) in the landing configuration abnormality alarm or special mission mode.

6. The system according to any one of claims 1 to 5, characterized in that: in: The corresponding data for the flight phase quick checklist (7) include: When taking off an amphibious aircraft: put the landing gear handle in the "air" position, and the "landing gear air position" will be announced; When landing an amphibious aircraft: When the landing gear handle is placed in the "Land" position, the "Landing Gear Land Position" will be displayed; When an amphibious aircraft lands on water: the landing gear handle is placed in the "water surface" position and the "landing gear water surface position" is reported; When an amphibious aircraft is taxiing into water: the landing gear handle is placed in the "water surface" position and the "landing gear water surface position" is reported; When an amphibious aircraft is taxiing ashore: Put the landing gear handle in the "Land" position to display "Landing Gear Land Position".

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