Method for diagnosing faults in electronic fuel control systems

• US 4,557,141 A
• Filed: 09/19/1984
• Issued: 12/10/1985
• Est. Priority Date: 09/19/1984
• Status: Expired due to Term

• Current Assignee: Pratt & Whitney Canada Corporation (Rtx Corporation)
• Original Assignee: Pratt & Whitney Canada Corporation (Rtx Corporation)
• Inventors: Poirier, Roger, Hamill, Donald F.
• Primary Examiner(s): MYRACLE, JERRY
• Application Number:
  US06/652,016
• Time in Patent Office: 447 Days
• Field of Search: 73/117.2, 73/117.3, 73/118, 73/119 A
• US Class Current: 73/112.01
• CPC Class Codes: G01R 31/00 Arrangements for testing electric properties; Arrangements for locating electric faults; Arrangements for electrical testing characterised by what is being tested not provided for elsewhere measuring superconductive properties G01R33/1238; testing or measuring semiconductors or solid state devices during manufacture H01L22/00; testing line transmission systems H04B3/46
• CPC Class Codes: G01R 31/008 on air- or spacecraft, railway rolling stock or sea-going vessels

Abstract

A method of troubleshooting, with a test set, an electronic fuel control system in an aircraft includes disconnecting the electronic engine control after mechanical tests have verified that the faults do not exist in the hydromechanical unit or associated mechanical parts. The test set then delivers signals to the circuits of the fuel control system one at a time to uniquely and specifically identify the fault. With this method, the engine can be tested when it is in its static condition.

Claims

1. A method of troubleshooting, with a test set, a fuel control system in an aircraft which has interfacing connectors with an engine on one side and airframe instruments on the other side, a plurality of LRU'"'"'s in the engine, specific conductors connected, at one end thereof, to each LRU, the other end of said conductors forming an engine harness, said engine harness being split into an engine/airframe interface portion whose connectors are connected to separate positions of a multiposition interface plug, a mating multiposition interface receptacle being connected to said multiposition interface plug to airframe instruments;

said fuel control system comprising an electronic engine control (EEC);

said engine harness being further split into an EEC harness portion connected to a separate position of a multiposition EEC plug connected to a mating multiposition EEC receptacle mounted on said EEC;

a trim plug mounted on a mating trim plug receptacle on said EEC;

said test set comprising a first harness, respective connectors of said first harness being connected to a first test receptacle for mating engagement with said multiposition bulkhead plug, and other connectors of said first harness being connected to a first test plug for mating engagement with said mating multiposition bulkhead receptacle;

said test set further comprising a second harness, respective connectors of said second harness being connected to a second test receptacle for mating engagement with said multiposition EEC plug, and other connectors of said second harness being connected to a second test plug for mating engagement with said mating trim plug receptacle;

said method comprising;

disconnecting the mating multiposition bulkhead receptacle from said multiposition bulkhead plug and connecting said first test receptacle to said multiposition bulkhead plug and said first test plug to said mating multiposition bulkhead receptacle;

disconnecting said multiposition EEC plug from said mating multiposition EEC receptacle and connecting said second test receptacle to said multiposition EEC plug;

connecting said second test plug to said mating trim plug receptacle;

testing the circuits of said fuel control system one at a time by sending signals from said test set through said connectors of said first and second harness one at a time and receiving signals to determine if a fault exists in the respective circuits.

2. A method as defined in claim 1 wherein, if it is shown that a fault exists when a signal is sent through said first harness, through said first test receptacle, and through said multiposition bulkhead plug, then it is known that the fault exists either in a respective one of said LRU'"'"'s or in the connector leading to said respective LRU;

said method further comprising the step of testing said LRU and, if said respective LRU is found faulty, replacing said respective LRU;

or

if said respective LRU is not found faulty, then determining that the fault is in the connector leading to said respective LRU.

3. A method as defined in claim 1 wherein, if a fault is located when a signal is sent through said first harness through said first test plug through said mating multiposition bulkhead receptacle, then it is known that the fault exists either in a respective one of said airframe instruments or in the connector leading to said respective airframe instrument;

said method further comprising testing said respective airframe instrument and if said respective airframe instrument is found faulty replacing said respective airframe instrument;

or

if said respective airframe instrument is not found faulty, then determining that the fault is in the conductor leading to said respective airframe instrument.

4. A method as defined in claim 1, wherein said electronic fuel control system comprises a hydro-mechanical unit and wherein said method comprises, before making the connections as defined in claim 1, ascertaining that the said hydro-mechanical unit and associated parts are serviceable and if not, replacing the faulty unit or part;

or

if no faults are found in the hydro-mechanical unit and associated parts, conducting the test as defined in claim 1.