Patent ID: 9365293
Filing Date: 2016-06-14
CPC Classification: B64D,Y02T

Claim Text:
1. An aircraft system, comprising: a first bleed air system supplying bleed air to a first pack via a first line; a second bleed air system supplying bleed air to a second pack via a second line; a connection line coupled between the first line and the second line, the connection line including a bleed air valve; a common mixing chamber receiving air treated by the first and second packs; a first redundant valve system coupled in the first line downstream of the connection line and upstream of the first pack, the first redundant valve system including a first electrical flow control valve (EFCV), which only provides electrical flow control, and a first pneumatic flow control valve (PBV), which only provides pneumatic flow control, arranged for air flow control in a parallel connection, the EFCV comprising an electrically-controlled actuator unit and a flap unit which is set via a pressure membrane, and the PBV comprising a pneumatically-controlled actuator unit and a flap unit which is set via a pressure membrane; and a second redundant valve system coupled in the second line downstream of the connection line and upstream of the second pack, the second redundant valve system including a second EFCV, which only provides electrical flow control, and a second PBV, which only provides pneumatic flow control, arranged for air flow control in a parallel connection, wherein if the EFCV fails, the flap unit of the EFCV is closed and the PBV is opened.