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types of information, a single SG can provide information to all six (6) DUs. In a single
SG configuration, however, the copilot’s displays will be a “repeater” of the pilot’s
displays and “same source” annunciations would appear on those displays, and the
pilot’s Display Controller would have command over all displays.
The SYMBOL GENERATOR CONTROL panel (lower section of the Reversionary
Controller), is located on the cockpit overhead panel. It consists of three (3) rotary
switches: PILOT, EICAS and COPILOT. Each switch has two (2) positions, Normal
(NORM) and Alternate (ALT). The PILOT switch has control over SG 1, the EICAS switch
has control over SG 3 and the COPILOT switch has control over SG 2, in that selection
of any of the three (3) switches to ALT commands the associated SG to shut down. In
addition, the proper information is re-routed from the remaining SGs to the respective set
of DUs. With all three (3) switches selected to ALT, all six (6) DUs would be blank (“Red
X’ed”), as all three (3) SGs would be shut down.
With all three (3) knobs selected to NORM, SG 1 is generating the PILOT displays, SG
3 is generating the EICAS displays and SG 2 is generating the COPILOT displays. If SG
1 should develop a failure, it will be necessary to rotate the PILOT control knob to ALT, in
which case SG 1 will shut down and SG 3 will pick up the PILOT displays, provided the
EICAS control knob is selected to NORM. If SG 3 should subsequently develop a fault,
it would be necessary to rotate the EICAS control knob to ALT, at which time SG 3 will be
shut down and SG 2 would be used for EICAS displays. The COPILOT displays would
become a repeater of the PILOT displays, also generated by SG 2.
The EICAS control knob in the NORM position uses SG 3 for EICAS displays. When the
EICAS control knob is selected to ALT, it will use SG 2, unless SG 2 has been
commanded to shut down (through selection of the COPILOT control knob to ALT), in
which case it will use SG 1. The COPILOT control knob in the NORM position uses SG
2 for COPILOT displays. When the COPILOT control knob is selected to ALT, it will use
SG 3, unless SG 3 has been commanded to shut down (through selection of the EICAS
control knob to ALT), in which case it will use SG 1 and provide the COPILOT display
with a “repeater” display of the PILOT displays.
The following table summarizes SG selection possibilities:
OPERATING MANUAL
05-18-00 EXPANDED ABNORMAL / EMERGENCY PROCEDURES
Page 2
May 30/02
Revision 7
Control Switch And Position Symbol Generator Used
PILOT EICAS COPILOT PILOT EICAS COPILOT
NORM NORM NORM 1 3 2
ALT NORM NORM 3 3 2
ALT ALT NORM 2 2 2R
k ALT k ALT k ALT Red X Red X Red X
j ALT j ALT j ALT 1 3 2
ALT NORM ALT 3 3 3R
NORM NORM ALT 1 3 3
NORM ALT NORM 1 2 2
NORM ALT ALT 1 1 1R
NORM = Normal
ALT = Alternate
R = Repeater of source in use by opposite side
k = SPZ-8000 equipped airplanes
j = SPZ-8400 equipped airplanes
05-18-30: Traffic and Collision Avoidance System (TCAS) Failure
1. Equipment Failure:
Should TCAS fail, a blue TCAS FAIL advisory message will be displayed on the
Crew Alerting System (CAS).
2. Circuit Protection:
TCAS components are protected by the TCAS circuit breaker located on the
Copilot’s Overhead Circuit Breaker Panel.
05-18-40: Enhanced Ground Proximity Warning System (EGPWS) Failure
1. Circuit Protection:
EGPWS components are protected by the EGPWS circuit breaker located on the
Copilot’s Overhead Circuit Breaker Panel.
05-18-50: DADC Failures
1. ″Flagged″ DADC Failures:
A ″flagged″ DADC failure is one where the failure is readily apparent, because of
the blue DADC 1 (or 2) FAIL advisory CAS message, and red ″X’s″ through all
four air data scales (airspeed, altitude, AOA, and vertical speed) of the PFD using
the failed DADC as its air data source, as selected on the display controllers.
Other confirmation of failure is as follows:
• Transponder indications
• AOA indexer failure
• Automatic cabin pressurization control problems and faulty guidance panel
indications (if operating on the failed DADC)
• EICAS message indicating that EPR is receiving pressure information from
the opposite DADC (EPR 1 - DADC 2 or EPR 2 - DADC 1)
If a ″flagged″ DADC failure has occurred, see Section 05-18-51.
OPERATING MANUAL
EXPANDED ABNORMAL / EMERGENCY PROCEDURES 05-18-00
Page 3
May 30/02
Revision 7
2. ″Unflagged″ DADC Failures:
An ″unflagged″ DADC failure will produce a blue DADC MISCOMPARE advisory
　
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