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- With both DU 3 and 4 inoperative, compact display of engine instruments
and CAS messages is displayed on DU 5.
Manual reversion with all six DU’s operative results in the blanking of the DU from which
information has been transferred and display of that data on the appropriate DU.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
3-92 FAA APPROVED
31 May 2000
3-18-20: Symbol Generator Failure:
Three (3) symbol generators (SG) are used to generate all information appearing on all six (6)
Display Units (DU’s). Each symbol generator can generate PFD, ND, EI, and CAS display
formats; switching determines which type of information is taken from a symbol generator for
presentation on the proper set of DU’s. Since any one symbol generator can generate all four (4)
types of information, a single symbol generator can power all six (6) DU’s, with the general
provision that the copilot’s displays will be a repeater of the pilot’s and "same source"
annunciations would appear on those displays, and that the pilot’s Display Controller would have
command over all displays.
The lower half of the Reversionary Controller provides for symbol generator control. It consists
of three (3) two-position (Normal (NORM) and Alternate (ALT)) Rotary switches, one each for
PILOT, EICAS, and COPILOT. The PILOT’S switch has control over SG 1; the EICAS switch
over SG 3, and the COPILOT’S switch over SG 2, in that ALT position commands that symbol
generator to shut down, as well as routing proper information from other symbol generators to
the respective set of DU’s. With all three (3) switches to ALT, all six (6) DU’s would lack
presentations, since all three (3) symbol generators would be commanded OFF.
With all three knobs in NORM, SG 1 is generating the pilot’s displays, SG 3 is generating the
EICAS displays, and SG 2 is generating the copilot’s displays. If SG 1 should develop a failure,
it will be necessary to rotate the pilot’s symbol generator control knob to the Alternate (ALT)
position, in which case SG 3 will pick up the pilot’s displays if the EICAS symbol generator
control knob is in NORM. If SG 3 should subsequently develop a fault, it would be necessary to
rotate the EICAS selector to ALT, at which time SG 3 would be shut down, SG 2 would be
utilized for EICAS displays, and the copilot’s displays would become repeaters of the pilot’s
displays, being powered also by SG 2.
The EICAS selector knob in NORM position utilizes SG 3 for EICAS displays, and in ALT will
use SG 2 , unless SG 2 has been commanded to shut down (by having placed copilot’s selector
switch to ALT), in which case it will use SG 1. The copilot’s selector knob in NORM utilizes SG
2 for the copilot’s displays, and in ALT will use SG 3 , unless SG 3 has been commanded to shut
down (by having positioned EICAS selector to ALT), in which case SG 1 will be used to provide
copilot’s displays, as repeaters of the pilot’s displays.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
FAA APPROVED 3-93
30 May 2002
The following table summarizes the Symbol Generator selection possibilities:
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
*ALT ALT ALT X X X
**ALT ALT 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 R = Repeater of source in use by opposite side
ALT = Alternate X = Red “X” displayed
* = SPZ 8000 equipped airplanes ** = SPZ 8400 equipped airplanes
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
3-94 FAA APPROVED
11 October 2001
3-18-30: Traffic and Collision Avoidance System (TCAS) Failure:
1. Equipment Failure
Should TCAS fail, a TCAS FAIL Blue Advisory Message will be displayed on the EICAS.
2. Circuit Protection
TCAS components are protected by the TCAS circuit breaker in the Copilot’s Overhead
Circuit Breaker Panel.
3-18-40: Enhanced Ground Proximity Warning System (EGPWS) Failure:
EGPWS components are protected by the EGPWS circuit breaker in the Copilot’s Overhead
Circuit Breaker Panel.
03-18-50: DADC Failures:
“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
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湾4飞机飞行手册AFM Gulfstream IV AIRPLANE FLIGHT MANUAL 1(73)
