A system, comprising: an input/output interface (300; 1003); a processor; a data storage comprising data modules (130; 132), each data module having links or references to other data modules; and a non-transitory computer-readable medium having instructions stored thereon that, when executed, cause the processor to: receive a fault code (102; 306a-c) associated with a first component of an aircraft; receive a data module (130; 132) associated with the first component based on the fault code (102; 306a-c); display on the input/output interface (300; 1003) the first component of the aircraft that is associated with the fault code (102; 306a-c); display on the input/output interface (300; 1003) a first and second hyperlinks (422; 430) associated with the first component; upon selection by a user of the first hyperlink display a physical layout of the aircraft in which the physical location of the first component is indicated; and upon selection by the user of the second hyperlink display a first wiring diagram of the aircraft in which the logical location of the first component is indicated, wherein the physical layout is displayed alternatively to the first wiring diagram. an input/output interface (300; 1003); a processor; a data storage comprising data modules (130; 132), each data module having links or references to other data modules; and a non-transitory computer-readable medium having instructions stored thereon that, when executed, cause the processor to: receive a fault code (102; 306a-c) associated with a first component of an aircraft; receive a data module (130; 132) associated with the first component based on the fault code (102; 306a-c); display on the input/output interface (300; 1003) the first component of the aircraft that is associated with the fault code (102; 306a-c); display on the input/output interface (300; 1003) a first and second hyperlinks (422; 430) associated with the first component; upon selection by a user of the first hyperlink display a physical layout of the aircraft in which the physical location of the first component is indicated; and upon selection by the user of the second hyperlink display a first wiring diagram of the aircraft in which the logical location of the first component is indicated, wherein the physical layout is displayed alternatively to the first wiring diagram. receive a fault code (102; 306a-c) associated with a first component of an aircraft; receive a data module (130; 132) associated with the first component based on the fault code (102; 306a-c); display on the input/output interface (300; 1003) the first component of the aircraft that is associated with the fault code (102; 306a-c); display on the input/output interface (300; 1003) a first and second hyperlinks (422; 430) associated with the first component; upon selection by a user of the first hyperlink display a physical layout of the aircraft in which the physical location of the first component is indicated; and upon selection by the user of the second hyperlink display a first wiring diagram of the aircraft in which the logical location of the first component is indicated, wherein the physical layout is displayed alternatively to the first wiring diagram.