SISTEMA ELECTRICO
FALLO DE LA BARRA AC 1
Loss of electrical bus BACKGROUND BACKGROUND
• Loss of AC1 bus & AC ESS bus due to: AC
1 bus fault And no manual action to transfer the power supply of AC ESS Bus from AC 1 to AC 2 Bus, by pressing the ALTN pushbutton.
• Consequences can be multiple : © AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Loss
of several displays Total loss of communication Loss of stand-by instruments lighting
5. Improvement of thebus Electrical Distribution System Loss of electrical
• The corrective action consists in replacing the crew action by an
Š AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
automatic switching of AC ESS, 3 seconds after the AC1 Bus is lost.
Mod 37317 / SB A320-24-1120 This modification is expected to be covered by an AD.
Corrective action for total loss of communication
• In addition to the automatic transfer, another modification has been introduced to ensure a continuous power supply of the digital AMU in case of total loss of DC ESS bus. of DC 1 Bus power supply of the Digital Audio Management Unit-AMU in addition to DC ESS Bus.
© AIRBUS S.A.S. All rights reserved. Confidential and proprietary document.
Introduction
Objective: To ensure Digital AMU availability in case of loss of DC ESS Bus. Mod 37782/ SB A320-23-1333
Corrective action forCockpit standby instrument 3. Improvement of the Lighting System lighting
•Interim solution: OEB 185/2
• Permanent solution:
Select
the Dome Light to DIM or BRT throughout flight. Dome Light may be selected OFF if during final approach and landing if deemed necessary.
CAPT
flood light located above standby instruments power from the HOT BUS in case of electrical loss. Cancels OEB 185/2.
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Objective: To ensure that the flight crew will be able to read the standby instrument indications
Mod 37329 &37330/ SB A320-33-1057 – MANDATORY AD 2007-0286 allows the stby instrument lihgting by the glareshield and aswell connection for the power supply thru the hot bus ( SB 33-1057).