US 12,351,328 B2
Methods and systems for operating an aircraft engine
Kasra Hamzehi, Richmond Hill (CA); Kulbir Singh Madhok, Montréal (CA); Michael Paul Smith, Mississauga (CA); and Dennis Deorajh, Caledon East (CA)
Assigned to PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed by PRATT & WHITNEY CANADA CORP., Longueuil (CA)
Filed on Dec. 9, 2021, as Appl. No. 17/546,171.
Prior Publication US 2023/0182914 A1, Jun. 15, 2023
Int. Cl. B64D 31/00 (2024.01); B64D 45/00 (2006.01); G07C 5/00 (2006.01)
CPC B64D 31/00 (2013.01) [B64D 45/00 (2013.01); G07C 5/008 (2013.01); B64D 2045/0085 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A method for operating an aircraft engine, comprising:
monitoring, by a health evaluation device, a health parameter for the aircraft engine received from a first instrument, the health evaluation device being communicatively coupled to a communication link established between a controller associated with the aircraft engine and a second instrument which monitors an operating condition of the aircraft and generates an operation parameter signal indicative of the operating condition of the aircraft engine;
comparing, by the health evaluation device, the health parameter to a predetermined threshold;
when the health parameter is below the predetermined threshold, causing, at the health evaluation device, the operation parameter signal to be transmitted from the second instrument to the controller via the communication link;
when the health parameter reaches the predetermined threshold, preventing, at the health evaluation device, the operation parameter signal from being transmitted from the second instrument to the controller, and transmitting to the controller, via the communication link, a fault signal to elicit a health response from the controller, the fault signal containing at least two mutually-exclusive fault codes, wherein each one of the two fault codes may occur individually based on the operating condition monitored by the second instrument, but where the two fault codes do not occur simultaneously based on the operating condition monitored by the second instrument, wherein a simultaneous transmission of the two mutually-exclusive fault codes indicates a cause related to the health parameter rather than a cause related to the operating condition.