A tire for an aeroplane with the tread (2) comprising two shoulder ribs (6) having an axial width L.sub.S, each shoulder rib (6) comprises cavities (8) that open onto the tread surface (3), forming an opening surface (81) inscribed in a circle of diameter D. These cavities (8) are distributed circumferentially at a circumferential spacing P and along a periodic curve (9) having a period T and an amplitude A. The circumferential spacing P between two consecutive cavities (8) is at most equal to 0.2 times the period T of the periodic curve (9), the period T of the periodic curve (9) is at most equal to the circumferential length L.sub.C of the contact patch (31), and the amplitude A of the periodic curve (9) is at most equal to 0.5 times the axial width L.sub.S of the shoulder rib (6).

A method, apparatus and system are disclosed in which an indication given by at least one tyre monitoring device is confirmed by input received from another source is disclosed. The method includes causing, by the control device, at least one tyre monitoring device mounted on a wheel to measure a tyre pressure and to indicate a status using an indicator provided on the tyre monitoring device; receiving, from the at least one tyre monitoring device, data representative of the status of the at least one tyre monitoring device; receiving input representative of the status indicated on the indicator of the at least one tyre monitoring device; comparing the received data representative of the status with the received input representative of the status; and taking action based on the result of the comparing.

A method of configuring a tire monitoring device is disclosed. The method includes, at the tire monitoring device: entering a configuration mode; responsive to entering the configuration mode, transmitting a first message to a second device, the message indicating that the second device should transmit configuration data to the tire monitoring device; receiving configuration data from the second device in response to the first message; and configuring the tire monitoring device based on the configuration data.

A method for initialising a tyre monitoring device including a wireless communication interface and tyre monitoring devices and systems using the method are disclosed. The method includes operating the tyre monitoring device in a first mode, in the first mode the tyre monitoring device is only responsive to an initialisation instruction received over the wireless communication interface from the second device; receiving an initialisation instruction over the wireless communication interface while operating in the first mode; and, responsive to the initialisation instruction, operating the tyre monitoring device in a second mode in which the tyre monitoring device is responsive to instructions received over the wireless communication interface. The first mode draws lower power than the second mode so power draw prior to initialisation, for example while storage awaiting use, is reduced.

An aircraft pneumatic tire includes a spirally wound belt layer in which a ribbon-shaped first strip material with a first belt cord including organic fibers and being covered with rubber is spirally wound; and zigzag belt layers in which a ribbon-shaped second strip material with a second belt cord including organic fibers and being covered with rubber extends and is wound in a circumferential direction while bending zigzag by being folded back at width directional end edges to an outer circumferential side of the spirally wound belt layers. The maximum width of the spirally wound belt layers is wider than the maximum width of the zigzag belt layers, and the width of the second strip material is wider than the width of the first strip material.

Tire for an aeroplane and, in particular, the crown thereof which comprises a tread (1), a textile crown reinforcement (2) and a textile carcass reinforcement (4). In order to optimize the number of landings, in the equatorial plane, the thickness (E1) of the tread is at least equal to 1.1 times the thickness of the working reinforcement and the thickness (E5) of the carcass is at least equal to 1.5 times the thickness (E3) of the working reinforcement, the reinforcing elements of the working layers (31, 32, 33) having a tenacity at least equal to 90 cN/tex.

An object is to, in an aircraft tire, promote heat dissipation from circumferential direction grooves of a tread and improve durability of the tire. Plural circumferential direction grooves (central side circumferential direction grooves (14), edge portion side circumferential direction grooves (16)) that extend in a tire circumferential direction are formed in a tread (12). In a tire circumferential direction cross-section, a groove bottom (18) of at least one of the circumferential direction grooves has a wave shape having amplitude in a tire radial direction.

An object is to make it make it possible to, before a protecting layer is exposed, visually recognize that a final stage of wear of a tread has been reached. A pneumatic tire (10) for an aircraft has: a carcass ply (12) that spans between a pair of bead portions; a belt layer (14) that is provided at a tire radial direction outer side of a crown portion (12A) of the carcass ply (12); a protecting layer (16) that is provided at a tire radial direction outer side of the belt layer (14); a tread (18) that is provided at a tire radial direction outer side of the protecting layer (16), and at which ribs (30, 32, 34) are demarcated and formed by circumferential direction grooves; and filaments (20) that are provided between the protecting layer (16) and the tread (18), or within the tread (18), that extend in a tire axial direction, and that are disposed with an interval therebetween in a tire circumferential direction.

An apparatus configured to determine the pressure of an aircraft tire at a reference temperature. The apparatus includes a processing system configured to: obtain a measured tire pressure and a measured temperature associated with the measured tire pressure; and determine a tire pressure at the reference temperature by adjusting the measured tire pressure using a predetermined temperature characteristic, a square root of the measured temperature and a square root of the reference temperature. The predetermined temperature characteristic is a gradient of the relationship between square root of temperature and tire pressure.

An aircraft tire comprises a tread (2), having an axial width L, which comprises a middle portion (3) having an axial width L.sub.C at least equal to 50% and at most equal to 80% of the axial width L of the tread and consisting of a middle rubber composition, and two lateral portions (41, 42), positioned axially on either side of the middle portion (3), each having an axial width (L.sub.S1, L.sub.S2) at least equal to 10% and at most equal to 25% of the axial width L of the tread and each consisting of a lateral rubber composition. The middle rubber composition comprises in particular from 25 to 85 phr of a tin-functionalized butadiene and styrene copolymer and from 15 to 75 phr of isoprene elastomer, and at least one lateral rubber composition is different from the middle rubber composition.