ATR 42/72-600 Systems Guide — Chapter B: Integrated Systems

2026-06-23

Chapter B. INTEGRATED SYSTEMS (CONTINUED)¶

2. MULTI FUNCTION COMPUTER (MFC) (FCOM DSC 31, 42)¶

The Multi Function Computer (MFC) system consists of four independent modules divided into two pairs: MFC 1 (Modules 1A and 1B) and MFC 2 (Modules 2A and 2B). The system automates system management, controls operating logics, and coordinates cockpit panel interfaces.

2.1. MFC Modules Allocation and Architecture¶

MFC 1 (Modules 1A & 1B): Manages essential operations including forward cargo door control logic, engine starting authorization sequences, and primary landing gear positioning monitoring.
MFC 2 (Modules 2A & 2B): Handles flight control surveillance, environmental pack regulation parameters, and pneumatic cross-bleed valve auto-scheduling laws.

2.2. Operational Redundancy Logic¶

Cross-Module Monitoring: Within each pair, one module is active while the secondary module operates in active-standby. They continuously cross-check data paths.
Failure Reconfiguration: If a single module fails (e.g., MFC 1A), its twin module (MFC 1B) immediately assumes full processing overhead without operational loss.
Dual Module Loss: If an entire computer pair fails (both 1A and 1B), the affected systems revert to a degraded fallback mode or basic manual control backup paths.

3. MULTI PURPOSE COMPUTER (MPC) (FCOM DSC 31, 42)¶

The Multi Purpose Computer (MPC) centralizes data collection, flight data recording interfaces, and maintenance reporting protocols for the entire aircraft.

3.1. Main Computing Tasks¶

Flight Data Recording Control: Collects sensory data vectors across all aircraft systems and feeds them sequentially to the Digital Flight Data Recorder (DFDR) and Cockpit Voice Recorder (CVR).
Central Maintenance System (CMS): Gathers real-time fault codes and BITE (Built-In Test Equipment) messages during flight. This diagnostic history is accessible on the ground via the Multipurpose Control Display Unit (MCDU) or specialized service ports.
Engine Condition Monitoring (ECM): Monitors raw thermodynamic and structural performance values from the turboprop power plants to track performance degradation metrics over time.

4. SYSTEM SCHEMATIC ARCHITECTURE¶

  IMA & SYSTEM INTEGRATION TOPOLOGY
  ┌──────────────────────┐         ┌──────────────────────┐
  │   AIRCRAFT SENSORS   │         │  COCKPIT PANEL SWs   │
  │ (System Inputs/Data) │         │ (Manual Control Cmds)│
  └──────────┬───────────┘         └──────────┬───────────┘
             │                                │
             └───────────────┬────────────────┘
                             ▼
  ┌───────────────────────────────────────────────────────┐
  │              DATA CONCENTRATION MODULES               │
  │        (Input/Output Signal Processing Modules)       │
  └──────────┬─────────────────────────────────┬──────────┘
             │                                 │
             ▼                                 ▼
  ┌──────────────────────┐         ┌──────────────────────┐
  │   MFC MODULES 1 & 2  │         │     MPC COMPONENT    │
  │ (Automation/Logic)   │         │ (Recording/CMS/BITE) │
  └──────────┬───────────┘         └──────────┬───────────┘
             │                                 │
             └───────────────┬─────────────────┘
                             ▼
  ┌───────────────────────────────────────────────────────┐
  │                 FLIGHT WARNING SYSTEM                 │
  │        (FWC Processing & Visual/Aural Routing)        │
  └──────────────────────────┬────────────────────────────┘
                             ▼
  ┌───────────────────────────────────────────────────────┐
  │            ELECTRONIC FLIGHT INSTRUMENTS              │
  │      (EWD / MFD Displays & System Synoptics Pages)    │
  └───────────────────────────────────────────────────────┘