A system for detecting a fault in a locking pin for use in an aircraft is described herein, said system comprising: said locking pin (120); means (160) for receiving a static air temperature; and a controller (150); wherein said locking pin (120) comprises an internal heater element (130) and at least one internal temperature sensor (140) provided therein, said system further comprising means for transmitting said measured temperature sensor information from said at least internal temperature sensor (140) and said static air temperature information to said controller (150), and wherein said controller (150) is configured to compare the static air temperature information with said locking pin temperature sensor information and determine if a difference between the measurements is above a static v. internal temperature threshold value. A system is also described herein for detecting a fault in a locking pin for use in an aircraft, said system comprising: said locking pin (120), wherein said locking pin (120) comprises an internal heater element (130) and at least two internal temperature sensors (140) provided therein, and a controller (150); wherein said controller (150) is configured to compare temperature information from a first of said at least two temperature sensors (140) with a temperature information from a second of said at least two temperature sensors (140), and wherein if said difference between said first and second sensors (140) is above an internal sensor comparison threshold, said controller (150) is configured to determine that at least one of said first and second temperature sensors (140) is faulty. Methods are also described herein.
ANTI-ICING AND DE-ICING HEATED LOCK PIN SYSTEM
ERWÄRMTES SCHLOSSSTIFTSYSTEM FÜR EISSCHUTZ UND ENTEISUNG
SYSTÈME DE GOUPILLE DE VERROUILLAGE CHAUFFÉE D'ANTIGIVRAGE ET DE DÉGIVRAGE
2023-04-19
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
European Patent Office | 2021
|NTIS | 1971