There are four basic modes to the ECAM system: flight  phase, advisory, failure related, and manual. The flight phase  mode is normally used. The phases are: preflight, takeoff,  climb, cruise, descent, approach, and post landing. Advisory  and failure–related modes will appear automatically as the  situation requires. When an advisory is shown on the primary  monitor, the secondary monitor will automatically display  the system schematic with numerical values. The same is true  for the failure-related mode, which takes precedent over all  other modes regardless of which mode is selected at the time  of the failure. Color coding is used on the displays to draw  attention to matters in order of importance. Display modes  are selected via a separate ECAM control panel shown in  Figure 10-121 . The manual mode of an ECAM is set by pressing one of the  synoptic display buttons on the control panel. This allows the  display of system diagrams. A failure warning or advisory  event will cancel this view.  [Figure 10-122] ECAM flight warning computers self-test upon startup. The  signal generators are also tested. A maintenance panel allows  for testing annunciation and further testing upon demand.  BITE stands for built-in test equipment. It is standard for  monitoring systems to monitor themselves as well as the  aircraft systems. All of the system inputs to the flight warning  computers can also be tested for continuity from this panel, as  well as inputs and outputs of the system data analog converter.  Any individual system faults will be listed on the primary  display as normal. Faults in the flight warning computers and  signal generators will annunciate on the maintenance panel.  [Figure 10-123]  Follow the manufacturer’s guidelines when  testing ECAM and related systems. as well as suggested action due to the failure. By performing  system monitoring automatically, the pilot is free to fly the  aircraft until a problem occurs.  Early ECAM systems only monitor airframe systems. Engine  parameters are displayed on traditional full-time cockpit  gauges. Later model ECAM systems incorporate engine  displays, as well as airframe.  An ECAM system has two CRT monitors. In newer aircraft,  these may be LCD. The left or upper monitor, depending  on the aircraft panel layout, displays information on system  status and any warnings associated corrective actions. This  is done in a checklist format. The right or lower monitor  displays accompanying system information in a pictorial  form, such as a diagram of the system being referred to on  the primary monitor. The ECAM monitors are typically powered by separate  signal generators. Aircraft data inputs are fed into two flight  warning computers. Analog inputs are first fed through a  system data analog converter and then into the warning  computers. The warning computers process the information  and forward information to the signal generators to illuminate  the monitors.  [Figure 10-120 ]  An engine indicating and crew alerting system (EICAS)  performs many of the same functions as an ECAM system. The  objective is still to monitor the aircraft systems for the pilot.  All EICAS display engine, as well as airframe, parameters.  Traditional gauges are not utilized, other than a standby  combination engine gauge in case of total system failure.  EICAS is also a two-monitor, two-computer system with  a display select panel. Both monitors receive information  from the same computer. The second computer serves as  a standby. Digital and analog inputs from the engine and  airframe systems are continuously monitored. Caution and  warning lights, as well as aural tones, are incorporated.  [Figure 10-124] 10-72 Engine Indicating and Crew Alerting System  (EICAS) Figure 10-119.  An EFIS EADI displays an airspeed scale to the  left of the horizon sphere and an altimeter and vertical speed scale  to the right. The slip indicator is the small rectangle under the  direction triangles at the top. This EFIS display presents all of the  flight information in the conventional cockpit basic T. 15 15000 FMS1 DTK 042 44.6NM BCE 3 N 33 30 6 E 12 15 200 4 2 1 1 2 4 000 28 900 800 29.92  IN 100 279 300 280 260 M.708 240 20 10 10 18000 LNV1 VALT Airspeed scale Digital airspeed readout Altitude scale Vertical speed scale Slip indicator