14.1 Airbus ECAM — Electronic Centralised Aircraft Monitoring

14.1 Airbus ECAM — Electronic Centralised Aircraft Monitoring

Current EASA Part-66 topic 5.15, Typical electronic / digital aircraft systems, is knowledge level 1 for categories A, B3, B1 and B2/B2L. The current Appendix I gives no system-by-system list; the pre-12 June 2024 detailed description explicitly included Electronic Centralised Aircraft Monitoring (ECAM) and associated Built-In Test Equipment (BITE). This section retains ECAM as a representative historical study example. This section covers how a typical Airbus installation organises the Engine/Warning Display (E/WD) and System Display (SD), and how advisory, caution and warning information is generated and inhibited by flight-phase logic. Exact ECAM action lines and Quick Reference Handbook drills belong on a type course, not in Module 5.

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What ECAM Provides

ECAM is the Airbus name for the centralised engine-indication, systems-synoptic and crew-alerting function. A typical glass-cockpit Airbus puts four jobs on two display units: primary and supporting engine parameters; aircraft-system synoptic pages; colour-coded crew alerts (warning, caution, advisory and memo); and a status summary of inoperative systems after a failure. The crew must see the engine state continuously, be pointed at the affected system when something fails, and not be flooded with every amber message during take-off and landing. For the maintenance engineer, a missing parameter, a stuck memo, a blank display or an unexpected inhibit is often the first evidence of a failed sensor, a failed warning computer, or a display-reversion event.

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Typical Computer Arrangement

Classroom teaching uses the A320-family split as the general arrangement. Later Airbus types keep the same ideas with different box names and display sizes. Processing is divided among specialised computers rather than placed in a single LRU.

Dual SDACs and dual FWCs mean a single computer failure should not remove both synoptic data and alerting. Three DMCs allow an EFIS DMC to be switched onto the ECAM displays if DMC 3 fails. Engine parameters originate mainly in Full Authority Digital Engine Control (FADEC) or Electronic Engine Control (EEC) channels as digital words; fire detection, some oil-quantity sensors and other independent loops arrive on separate paths (section 14.3).

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Engine/Warning Display (E/WD)

The upper ECAM display is the Engine/Warning Display. In normal operation it is the permanent engine and alert window, not a general systems page. Typical zones, from top to bottom, are the primary engine area (N1 or engine pressure ratio (EPR), exhaust gas temperature (EGT), N2 and fuel flow, with limit marks and the active thrust limit), fuel-on-board and slat/flap cues, and the memo, warning and caution field. Left-side columns list titles; some types add right-side action reminders. Module 5 requires recognition that this colour-coded field exists, not memorising type-course action lines.

Green memo messages (seat-belt signs, APU available, speed-brake extended) confirm a selected or automatic aircraft state and are not failures. Pulsing advisory behaviour around a parameter (often taught as level 1) marks a value drifting toward a limit. Cautions (amber, typically level 2) and warnings (red, typically level 3) occupy the same field at higher priority. Overflow indication and clear/recall logic step through a stack that is too long for one screen. Independent failures remain listed; purely consequential effects may be suppressed so the same failure is not repeated in several disguises.

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System Display (SD) and System Pages

The lower ECAM display is the System Display. It presents system synoptic pages and the status (STS) page rather than the permanent engine strip. A typical ECP allows the crew to call BLEED, PRESS, EL/AC, EL/DC, HYD, FUEL, APU, COND/AIR, DOOR/OXY, WHEEL, F/CTL, ENG and similar pages. Each page is a schematic of valves, pumps, buses, quantities, temperatures and pressures in the same red/amber/green/white language as the rest of the glass cockpit. The CRUISE page, when provided, is a condensed multi-system summary for the cruise phase.

Automatic page switching is part of the general arrangement: ENG during start or an engine-related failure; the affected synoptic after a system failure; DOOR or WHEEL on the ground or landing; STS after the operational failure drill is cleared. The SD is a context display. If the upper display fails, the E/WD image normally transfers onto the lower unit so that engine parameters and alerts are preserved; system pages then share an EFIS display via an ECAM/ND transfer switch.

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Advisory, Caution and Warning Levels

ECAM alerting is taught as a ranked set of levels. Colours, lights and sounds must match the level.

Red is never used for a routine memo. Amber is never used to mean normal. Green completed indications mean the item is in the expected state. Cyan or blue action titles and white page labels must not be confused with the red/amber/green safety language. The master-warning and master-caution captions are driven by the FWCs. Pressing the light silences or resets attention-getters; it does not repair the system and it does not erase BITE memory.

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Flight-Phase Inhibit as Typical Teaching

If every amber caution chimed at rotation, genuine red warnings could be missed. Flight-phase inhibit is FWC logic that uses airspeed, radio altitude, thrust-lever position, landing-gear discretes and similar inputs to defer selected caution-level messages during the most critical phases. Typical classroom teaching divides electrical power-up, engine start, take-off roll, climb, cruise, descent, approach, landing and post-landing into numbered phases, but the exact phase table is type-specific. During the take-off and landing inhibit windows many cautions are parked. Red warnings that protect against fire or similarly immediate hazards are generally not inhibited. After the window, previously inhibited cautions that are still present appear, often with the normal single chime. An engineer troubleshooting a missing amber message must ask whether the FWC considered the aircraft to be in an inhibit phase, not only whether a sensor failed.

[!WARNING] Do not treat ECAM as a type-course procedure trainer. Module 5 asks for general arrangement: E/WD versus SD, system pages, the warning/caution/advisory/memo hierarchy, and the existence of flight-phase inhibit. Precise inhibit speeds and ECAM action lines are aeroplane-specific.

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Associated BITE

ECAM computers include BITE. Power-up tests and continuous monitoring record faults against the SDAC, FWC, DMC and display-unit LRUs and usually report to a centralised maintenance computer or centralised fault-display system. Failures that affect the current flight appear as operational warnings or cautions. Lower-priority items may appear only on the STS page or only in the BITE readout. Using the E/WD as the maintenance manual is a category error. If the E/WD is blank but the SD is alive, suspect a display unit, DMC assignment or reversion. If system pages freeze while warnings still chime, suspect the SDAC path versus the FWC path. If a known amber failure is silent during take-off, check flight-phase inhibit before replacing sensors.