Narrative:

While in cruise at FL380; we received an spda (secondary power distribution assembly) fail; fuel feed 1 fault; and APU fuel sov clsd EICAS messages. I transferred control of the aircraft to the first officer (first officer) [and] complied with QRH procedures. I contacted dispatch via ACARS and eventually did a conference call with maintenance control over arinc. Maintenance explained that we were having secondary power distribution issues. However; after about 20 minutes; we experienced additional electric buses issues; hydraulics and fuel pumps failures; fuel crossfeed system malfunctions; and fire system faults. On the electrical synoptic pages: AC bus 2; tru 2; dc bus 2 started to flash amber. Then it started affecting AC ess and dc ess 3 bus and bat 2. Then the APU start bus was showing that it was being energized by the batt 1. We lost the ability to fuel crossfeed. The valve would open and then close again with the switch selected to either fuel tank. Loss of both tank 1 and 2 fuel ejector pumps. AC electric 1 fuel pump took over but was turning on/off. AC electric 2 fuel pump showed offline as well as the #2 fuel ejector pump and that the dc fuel pump (which is used to supply fuel from the #2 tank to the APU was supplying fuel pressure to the #2 engine. As the captain and after discussing it with the first officer; I overrode the fuel pumps to force to the AC electric pumps to run continuously since the fuel ejector pumps were showing that they were failing; turning the backup AC pumps and then turning them off and on. I wanted to make sure we had positive fuel pressure to the engines. I conferred with dispatch and maintenance control over arinc again. We all concurred to divert to [a nearby alternate]. As we were turning final and intercepting the localizer; we received a fire protection fault message and the first officer lost ILS2. I took control of the aircraft; disconnected the autopilot and continued the landing visually. Landed under maximum landing weight. Failure of spda causing malfunctions and failures of other aircraft systems (fuel; fire; electrical; hydraulics and APU).

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Original NASA ASRS Text

Title: ERJ-190 Captain reported diverting to an alternate airport after experiencing multiple system failures associated with the loss of the Secondary Power Distribution Assembly (SPDA).

Narrative: While in cruise at FL380; we received an SPDA (Secondary Power Distribution Assembly) FAIL; FUEL FEED 1 FAULT; and APU FUEL SOV CLSD EICAS messages. I transferred control of the aircraft to the F/O (First Officer) [and] complied with QRH procedures. I contacted Dispatch via ACARS and eventually did a conference call with Maintenance Control over ARINC. Maintenance explained that we were having secondary power distribution issues. However; after about 20 minutes; we experienced additional electric buses issues; hydraulics and fuel pumps failures; fuel crossfeed system malfunctions; and fire system faults. On the ELECTRICAL synoptic pages: AC BUS 2; TRU 2; DC BUS 2 started to flash amber. Then it started affecting AC ESS and DC ESS 3 BUS and BAT 2. Then the APU START BUS was showing that it was being energized by the BATT 1. We lost the ability to fuel crossfeed. The valve would open and then close again with the switch selected to either fuel tank. Loss of both tank 1 and 2 fuel ejector pumps. AC electric 1 fuel pump took over but was turning on/off. AC electric 2 fuel pump showed offline as well as the #2 fuel ejector pump and that the DC fuel pump (which is used to supply fuel from the #2 tank to the APU was supplying fuel pressure to the #2 engine. As the Captain and after discussing it with the FO; I overrode the fuel pumps to force to the AC electric pumps to run continuously since the fuel ejector pumps were showing that they were failing; turning the backup AC pumps and then turning them off and on. I wanted to make sure we had positive fuel pressure to the engines. I conferred with Dispatch and Maintenance Control over ARINC again. We all concurred to divert to [a nearby alternate]. As we were turning final and intercepting the LOC; we received a FIRE PROTECTION FAULT message and the FO lost ILS2. I took control of the aircraft; disconnected the autopilot and continued the landing visually. Landed under maximum landing weight. Failure of SPDA causing malfunctions and failures of other aircraft systems (fuel; fire; electrical; hydraulics and APU).

Data retrieved from NASA's ASRS site and automatically converted to unabbreviated mixed upper/lowercase text. This report is for informational purposes with no guarantee of accuracy. See NASA's ASRS site for official report.