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公开(公告)号：EP4442566A1
公开(公告)日：2024-10-09
申请号：EP24165675.0
申请日：2024-03-22
摘要： A temporary pintle support 360 is provided which can attach between upper prongs 331, 332 of a landing gear, and which is arranged to hold pintle pins 370, 380 prior to installation of the landing gear assembly at an aircraft. The pintle support 360 is attached at the landing gear so as to align the pintle pins with their respective attachment bearings 340, 350 on each of the prongs. The pintle support may be removed once the pintle pins are fully inserted.
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公开(公告)号：EP4282752A2
公开(公告)日：2023-11-29
申请号：EP23175076.1
申请日：2023-05-24
发明人： BARSALI, Guilherme
摘要： A retractable landing gear assembly for an aircraft has a main strut (210) arranged to pivot between a retracted position and an extended position, and a sidestay (220) having an unfolded position and a folded position. A telescopic actuator (250) is coupled between the main strut (210) and the sidestay (220), so that when the actuator (250) has a first length the sidestay (220) locks the main strut (210) in the extended position, and when the actuator (250) has a second length the sidestay (220) is in the folded position and the main strut (210) is in the retracted position.
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公开(公告)号：EP4282752A3
公开(公告)日：2024-02-28
申请号：EP23175076.1
申请日：2023-05-24
发明人： BARSALI, Guilherme
摘要： A retractable landing gear assembly for an aircraft has a main strut (210) arranged to pivot between a retracted position and an extended position, and a sidestay (220) having an unfolded position and a folded position. A telescopic actuator (250) is coupled between the main strut (210) and the sidestay (220), so that when the actuator (250) has a first length the sidestay (220) locks the main strut (210) in the extended position, and when the actuator (250) has a second length the sidestay (220) is in the folded position and the main strut (210) is in the retracted position.
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公开(公告)号：EP4289726A1
公开(公告)日：2023-12-13
申请号：EP23178132.9
申请日：2023-06-07
摘要： A door fairing (300) for a retractable landing gear leg of an aircraft has an outer member (330) which covers a portion of a landing gear bay of the aircraft when the landing gear leg is retracted. An inner member (310) of the door fairing (300) is coupled to the outer member (330) via a number of configurable couplings (350, 360, 370, 380, 390) which allow adjustment of the position of the outer member (330) with respect to the inner member (310). The inner member (310) has mounting points (315, 320) for mounting the door fairing (300) to the landing gear leg. Prior to fitting the door fairing (300) at the aircraft, measured or derived dimensional parameters of the landing gear bay are used to adjust the configurable couplings (350, 360, 370, 380, 390) such that the door fairing (300) is preconfigured to fit the landing gear bay of the aircraft.
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公开(公告)号：EP4282767A1
公开(公告)日：2023-11-29
申请号：EP23175512.5
申请日：2023-05-25
摘要： A cradle (300) for supporting an aircraft landing gear assembly (360) includes a chassis for transporting the cradle (300) and an arm (330) movable between a stowed position and an elevated position (345) with respect to the chassis (310). The arm (330) has a set of clamps (350) for securing the landing gear assembly (360) to the cradle (300). In this way the landing gear assembly (360) is held securely in the stowed position for storage and transport, and held securely in the elevated position (345) for installation to an aircraft, such that damage to the landing gear assembly (360) during transportation and installation is minimised.
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