Abstract: A landing gear for an aircraft includes a shock absorber strut (1) with upper and lower telescoping portions (2, 3), the upper portion (2) being connectable to the airframe of the aircraft. An arm (4) extends fore and aft relative to the aircraft and carrying a landing wheel, (7, 71), and pivotally connects by a main pivot (5) to the lower portion (3) of the shock absorber strut. A load reacting unit (9) connects between the arm (4) and the shock absorber strut (1) for reacting to load applied between the arm and shock absorber strut on landing. An indicator (60) monitors the load applied to the load reacting unit (9) on landing. The load reacting unit (9) may be connected between a forward end of the arm (4) and the upper portion (2) of the shock absorber strut to make the gear act as a semi-levered landing gear. Alternatively, the load reacting unit (9) may be connected between the arm (4) and the lower portion (3) of the shock absorber strut to act as a pitch trimmer.

Abstract: A load indicator comprises a load bearing assembly of first and second load bearing members (23, 22) connected together to bear a lateral load applied to the first member (23), the first load bearing member defining a cavity (25) with the second load bearing member such that it is frangible above an indicator load, and the cavity (25) containing an indicator liquid which escapes from the cavity once the first load bearing member is fractured by said load. The load bearing members (22, 23) comprise cylindrical members arranged concentrically with the outer member (23) having a portion of reduced thickness to render it frangible and to define the cavity (25). The cavity (25) includes an internal volume within the second load bearing member (22). The load indicator may be configured as a load bearing pin to connect two components.

Abstract: An overload detecting assembly comprises a first load bearing member (10) adapted to flex laterally in response to a load to be monitored, a second load bearing member (11) spaced from the first under normal load conditions and which is contacted and loaded by the first load bearing member (10) when it is loaded beyond a load limit. Preferably, the first load bearing member (10) has a yield point below the load limit and takes a permanent set once the yield point has been exceeded. A lateral probe (18) cooperates with the first load bearing member as it moves towards the second load bearing member and in turn deflects an indicator member (20) which takes a permanent set when a yield point is exceeded. Ready inspection of the indicator member then reveals whether or not it has been bent.

Abstract: Aircraft landing gear includes a retractable housing comprising an upper leg (11); a lower leg (15) including a wheel axle (16) slidingly disposed within the upper leg (11) and resiliency biassed to an extended condition; a turning collar (18) rotatably disposed about the housing and having connection means for a drag stay (17); and a steering collar (19) operatively connected to a steering motor (41) and connected to the lower leg (15) by a torque link (21, 22); in which the turning collar (18) is provided with a cam surface (24) which cooperates in use with the torque link (21, 22) to maintain the lower leg (15) with the wheel in the fore-and-aft position when in the extended condition.

Abstract: Apparatus for monitoring a parameter associated with a structural component comprises a module (1) which is attachable to the structural component and which is associated with a sensor (2) for making measurements of said parameter. The module incorporates a power supply (7) for powering the apparatus; a memory (4) for storing data from the sensor, and a processor (3) to process measurement signals from the sensor (2) and to store data in said memory (4). A display (5) for displaying measurements made by the sensor (2) may also be provided. The processor may make use of an algorithm such as a rainflow counting algorithm to reduce data stored. For energy saving, the sensor (2) is only powered on as required to take a measurement. The sensor (3) is interfaced to the processor through a signal processing subsystem (6) consisting of an amplifier and A to D converter, and each is turned on and off as required to power the sensor (2) for measuring.

Abstract: A semi-levered landing gear for an aircraft comprises a main shock absorber strut (1) connected to the airframe; a bogie beam (4) extending fore and aft of the airframe with forward and aft wheels (J, T) and a main pivot connection (5) to the strut (1) between the forward and aft wheels (7, T) and an auxiliary actuator (49) connected between the strut (1) and the front of the bogie beam (4) at an auxiliary pivot (14). The auxiliary actuator (49) comprises a two stage telescopic hydraulic unit comprising a first stage piston and cylinder actuator (59, 63) and a second stage piston and cylinder actuator (56, 50) operating coaxially within an outer casing (50). A respective piston rod (65, 60) each extends from each end of the casing (50) and is connected to a respective one of said (strut 1) and bogie beam (4). The first stage actuator (59, 63) is operable to an extended position, and the second stage actuator (56, 60) is operable between a retracted position (FIG. 11) and an extended position (FIG.