Abstract: The present invention provides airline mechanics with an electronic maintenance terminal (MT) that displays real time central maintenance computer (CMC) data screens. The invention provides the mechanic with the ability to access fault isolation manual (FIM) troubleshooting procedures via an internal software hot link between the CMC fault code and the FIM procedure. The FIM data is a subset of the electronic portable maintenance aid (PMA) data. In addition to faults the present invention also links flight deck effect (FDE) EICAS messages to FIM troubleshooting procedures.

Abstract: The present invention provides airline mechanics with an electronic maintenance terminal (MT) that displays real time central maintenance computer (CMC) data screens. The invention provides the mechanic with the ability to access fault isolation manual (FIM) troubleshooting procedures via an internal software hot link between the CMC fault code and the FIM procedure. The FIM data is a subset of the electronic portable maintenance aid (PMA) data. In addition to faults the present invention also links flight deck effect (FDE) EICAS messages to FIM troubleshooting procedures.

Abstract: A distributed BITE system for a digital avionic system. The avionic system comprises a plurality of LRUs and digital communication devices through which the LRUs can transmit and receive data in a predefined format comprising multiple bit communication words. The avionic system further includes an interface unit (12) and at least one distributed computer system (14, 16, 18). The interface unit includes a control/display unit (20) that comprises a display screen (22) and input device such as a keyboard (24, 26). The digital communication devices may include a first bus (40) through which the interface unit can transmit communication words to the distributed computer system, and a second bus (42, 44, 46) through which the distributed computer system can transmit communication words to the interface unit. The BITE system comprises a distributed BITE program (72, 74, 76) in the distributed computer system, and a passthrough program (78) in the interface unit.

Abstract: A vertical glide slope control system including a complementary filter. Complementary aircraft generated and processed signals are added to a glide slope error signal which may include distortions. The results of the summation are applied to a first order lag filter having a low breakpoint (i.e., a low-pass band). The low-pass band eliminates high frequency distortions contained in the glide slope error signal without loss of stability. Aircraft stability is not lost due to the inclusion of the complementary aircraft signals added prior to the passage of the signals through the first order lag filter.