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If a display controller fails, the associated PFD and ND revert to the
following display source selections:
OPERATING MANUAL
2A-31-00 PRODUCTION AIRCRAFT SYSTEMS
Page 34
January 31/02
Revision 6
PFD: ND:
On-side IRS, DADC, RA & NAV MAP Format
RAD ALT Set = 200 On-side FMS
Bearing Pointers = AUTO ID WAYPT
BARO = IN
FD CMD = SC
If both display controllers fail, EICAS uses DAU 1A, DAU 2B and FWC 1.
Operation of the BARO knobs will be unaffected due to the direct
connection to their on-side DADC.
C. Display Units:
The six display units (Figure 17) are interchangeable, high resolution, eight
inch by eight inch cathode ray tubes. Driven by the symbol generators and
commanded by the display controllers, the display units are used by the
central display system to present air data and display information about the
airplane’s attitude, flight director, navigation, engines and aircraft systems.
Once power is applied, it takes approximately ten (10) minutes for full color
stabilization to take place.
Display units used as primary flight displays also present other data vital for
safe airplane operation such as the navigation data source, radio altitude,
course, heading and distance.
Display units used as navigation displays show navigation and flight plan
data from the navigation receivers, flight management system, and
weather radar in one of three desired formats:
• MAP: partial compass rose and range displays
• COMP: (compass) traditional HSI with 360° compass rose
• PLAN: “north up” representation of active flight plan
If the component providing data to the PFD or ND fails or provides invalid
data, a red X will appear on that portion of the PFD or ND. If a symbol
generator fails, a red X will appear across the entire display unit. If the
display unit goes blank, display unit failure should be suspected.
D. Display Power Panel:
The six display units are selected on and off in pairs using the PILOT,
EICAS and COPILOT switches on the display power panel (DISPLAYS
section of the cockpit overhead panel, Figure 14). All three switches are
guarded switches and when not selected on, an amber OFF legend is
displayed in the switch. Design of the panel is “fail-operational” in that the
affected display units will be powered should a failure occur within the
panel.
E. Display Unit Cooling:
Two fans are installed to provide circulation of cooling air to the display
units. On airplanes Serial Number (SN) 1000 through 1155 not having
Aircraft Service Change (ASC) 87, the cooling fans automatically start and
remain on any time electrical power is applied to the airplane, regardless of
whether the display units are on or off. The fans may be shut off, however,
by pulling the DISPLAYS FAN #1 and DISPLAYS FAN #2 circuit breakers
(copilot’s circuit breaker panel, D-5 and D-6, respectively).
On airplanes SN 1156 and subsequent and SN 1000 through 1155 having
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-31-00
Page 35
January 31/02
Revision 6
ASC 87, the display unit cooling fans (and also the display controllers) are
shut off when the airplane is on the ground and all three DISPLAYS
switches are selected OFF. When the airplane is airborne, the cooling fans
and display controllers are operational at all times. In addition to being able
to control the cooling fans without exercising the circuit breakers,
incorporation of ASC 87 eliminates the possibility of inadvertently operating
the display units without the cooling fans operating.
F. Display Brightness Panel:
DU brightness is controlled by the DISPLAY BRIGHTNESS panel located
on the cockpit center pedestal and shown in Figure 15. Three (3) dual
concentric potentiometers (knob sets consisting of an inner and outer
knob) are provided. Each knob set is dedicated to a pair of DUs: pilot’s,
EICAS and copilot’s. The inner and outer knobs control the DUs in the pair.
Display brightness is also controlled by a photo-electric sensor in each DU
that will automatically adjust display brightness based on ambient light
levels.
G. Display Switching and System Control Panel:
(See Figure 18 for SPZ-8000 and Figure 19 for SPZ-8400.)
The display switching and system control panel is located on the cockpit
overhead panel. It provides the flight crew with reversionary control of the
central display system in the event of display unit or symbol generator
failures. The control panel is divided into two sections, labeled DISPLAY
SWITCHING and SYMBOL GENERATOR CONTROL. The function of
each section is outlined as follows:
　
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