US 12,436,179 B2
Identifying fault in torque signal / torque sensor for aircraft system
Andrew Ghattas, La Prairie (CA); Michael P. Smith, Mississauga (CA); and Charles Bolon-Bruhn, Longueuil (CA)
Assigned to Pratt & Whitney Canada Corp., Longueuil (CA)
Filed by Pratt & Whitney Canada Corp., Longueuil (CA)
Filed on May 17, 2023, as Appl. No. 18/198,784.
Prior Publication US 2024/0385234 A1, Nov. 21, 2024
Int. Cl. G01R 29/26 (2006.01); B64D 45/00 (2006.01)
CPC G01R 29/26 (2013.01) [B64D 2045/0085 (2013.01)] 19 Claims
OG exemplary drawing
 
1. A method for operating an aircraft system, comprising:
rotating a shaft of an aircraft powerplant;
receiving, at a controller, a torque signal indicative of a torque applied to the shaft while the shaft is rotating;
determining, using the controller, a noise parameter indicative of noise in the torque signal;
identifying, using the controller, a fault in the torque signal when the noise parameter is equal to or greater than a threshold;
identifying, using the controller, a fault in a torque sensor when the fault in the torque signal is identified, wherein the torque signal is received from the torque sensor; and
signaling, using the controller, a user interface to provide notification of the identified fault in the torque signal.