A320 Architecture
Flight Control Law & Redundancy Analysis

A320 Fly-By-Wire Redundancy Explorer

Simulate multi-lane computer and hydraulic outages to observe real-time flight control reconfiguration, degradation pathways, and surface authority changes.

Open Comparison Tool
A320 Fly-By-Wire Computer and Surface Hierarchy Visual schematic showing inputs routing from Sidestick through ELAC, SEC, and FAC computers to hydraulic servos on the elevator, aileron, spoiler, and rudder. PILOT INPUT Sidestick & Pedals ELAC 1 & 2 Elevator & Aileron SEC 1, 2, 3 Spoiler & Elevator FAC 1 & 2 Yaw & Rudder Travel HYDRAULIC LOOPS GREEN (G) BLUE (B) YELLOW (Y) Elevators & THS Ailerons & Roll Spoilers Rudder & Yaw Trim
Interactive Reconfiguration Engine

Before vs. After Degradation Model

Baseline Nominal Condition

Full Fly-By-Wire flight envelope protection (Normal Law), autotrim active, full roll rate and structural limiting.

Evaluated Degradation State

Live computed law, active fallback pathways, and surviving aerodynamic surface authority.

Toggle Individual Hardware Channels
Normal Law Active

Normal Law

All flight control computers and all 3 hydraulic circuits are active. Full flight envelope protection, load alleviation, and automatic trim operate nominally.

  • Pitch: G-load command with autotrim and high/low angle of attack protection.
  • Roll: Rate command with bank angle limiting (67° max).
  • Yaw: Automatic Dutch roll damping and coordinated turn assistance.

System Availability Index

Computing Channels 7 / 7 Online
Hydraulic Pressure Circuits 3 / 3 Nominal
Fail-Operational Logic: Reconfiguration occurs automatically within milliseconds upon loss of cross-comparison validity.

Surface Actuator Authority

Nominal Degraded/Fallback Inoperative
ELAC Elevator & Aileron Computer
SEC Spoiler & Elevator Computer
FAC Flight Augmentation Computer
Green, Blue, Yellow Hydraulic Networks
Normal Law Protection Envelope
Alternate Law With Reduced Protections
Direct Law Surface Direct Proportionality
Mechanical Backup Pitch Trim & Rudder
ELAC Elevator & Aileron Computer
SEC Spoiler & Elevator Computer
FAC Flight Augmentation Computer
Green, Blue, Yellow Hydraulic Networks
Normal Law Protection Envelope
Alternate Law With Reduced Protections
Direct Law Surface Direct Proportionality
Mechanical Backup Pitch Trim & Rudder
Degradation Hierarchy

How Control Reconfiguration Occurs

The Fly-By-Wire system is engineered to protect structural integrity while preserving pilot control across sequential hardware losses.

When both ELACs fail, or when two hydraulic circuits lose nominal pressure, the system automatically transitions from Normal Law to Alternate Law. In Alternate Law, load factor demand is maintained in pitch, but high-angle-of-attack alpha protection and high-speed protection revert to stability warnings.

Operational Guidance & Pilot Reference

Flight Crew Training & Scenario Feedback

Architectural Physicality

Triple-Redundant Hydraulic Integration

Unlike pure mechanical linkages, each flight surface is powered by two or three independent hydraulic actuators receiving electrical command signals from discrete computer buses.

The system avoids common-mode failures by utilizing dissimilar microprocessors and distinct software code across the ELAC (Thomson-CSF) and SEC (SFENA) architectures.

Cockpit avionics and flight deck fly-by-wire controls
Training & Academic Scope

Explore Safely. Operate by the Book.

This interactive explorer is a simplified, non-authoritative educational model derived from public technical documentation. It omits specific sensor bus arbitration, airspeed schedule transitions, and certified flight manual revisions. It is not approved for flight crew certification or operational dispatch.

System State Reset

Return all modeled flight computers and hydraulic circuits to baseline operational configuration.

A320 Reconfiguration Diagnosis Report


    

      
      
    

  

  
  
  

  


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