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DAMPER FAILURE in this section. Observe Yaw Damper limitations in Section 1, Limitations.
Perform a normal approach and landing using normal procedures. After landing use brakes,
steering and left thrust reverser. The right thrust reverser is not operational for landing.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
3-88 FAA APPROVED
31 May 2000
3-17-50: Landing With Standby Electrical Power System Operating:
NOTE: If Standby Electrical Power is interrupted during the following steps, cycle the Standby
Electrical Power Switch OFF then ON.
1. Landing Gear..................................................................................................................DOWN
2. Flaps........................................................................................................ SET FOR LANDING
3. Emergency Batteries ............................................................................................................ ON
4. Ground Spoilers ..................................................................................................................OFF
5. Maintain 67% HP RPM until touchdown.
NOTE: Once the airplane is on the ground, there is no need to continue to maintain 67% HP
RPM. The Standby Electrical System should stay on line during normal taxi
maneuvers. If Standby Electrical Power is interrupted, cycle the Standby Electrical
Power Switch OFF then ON to regain power.
6. DO NOT Use Reverse Thrust.
7. On touchdown, manually deploy the flight spoilers at a slow rate (approximately 5 seconds).
8. Use normal braking to stop the airplane.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
FAA APPROVED 3-89
31 May 2000
3-18-00: INDICATING/RECORDING SYSTEM
3-18-10: Display Unit Failure:
The pilot’s flight instrumentation consists of two 8" x 8" CRT Display Units (DU 1 and DU 2).
DU 1 displays the pilot’s Primary Flight Display (PFD) and is used to present basic flight
attitude, air data, and flight director information. DU 1 is located directly in front of the pilot’s
yoke. DU 2 normally displays the pilot’s Navigation Display (ND) and is used to present radio
navigation information, weather radar, and FMS map/navigation information. DU 2 is located
inboard of DU 1.
The copilot’s flight instrumentation is similar, with DU 5 utilized for the Navigation Display
(ND), mounted inboard of DU 6, the copilot’s Primary Flight Display (PFD), mounted in front of
the copilot’s yoke.
Display Units 3 and 4, mounted vertically on the center-line of the cockpit instrument panel, are
utilized for Engine Instrument (EI) display and Crew Alerting System display (CAS); both,
together, comprise EICAS (Engine Instrument and Crew Alerting System).
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
3-90 FAA APPROVED
31 May 2000
For SPZ 8000 equipped airplanes
In the event of a Display Unit failure, the following switching options are available:
1. NORM - Normal presentation
2. PFD XFER - Display of PFD information on DU normally used as ND
3. ND OFF - Blanks the ND
EICAS switching options are:
1. NORM - Normal presentation
2. TOP CMPT - "Compacted" display of both engine instrumentation and flight crew alerting
messages on upper tube (DU 3).
3. BOT CMPT - "Compacted" display of both engine instrumentation and flight crew alerting
messages on lower tube (DU 4)
The display switching control panel (upper half of REVERSIONARY CONTROLLER) is in the
overhead panel, and consists of three (3) rotary knobs, one each for PILOT, EICAS, and
COPILOT, which permit selections listed above. There is no capability to transfer flight
information to the EICAS displays or vice versa.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
FAA APPROVED 3-91
31 May 2000
For SPZ 8400 equipped airplanes
In the event of Display Unit failure, automatic switching of displays occurs to the next available
DU.
Manual switching is also available with the following options:
PILOT DISPLAY (PFD AND ND)
1. NORM - Normal presentation
2. PFD - Display of PFD information on DU 2
3. ENG/EICAS - With DU 3 failed, Engine Data is displayed on DU 2.
- With both DU 3 and 4 inoperative, compact display of engine instruments
and CAS messages is displayed on DU 2.
COPILOT DISPLAY (PFD AND ND)
1. NORM - Normal presentation
2. PFD - Display of PFD information on DU 5
3. CAS/EICAS - With DU 4 inoperative, normal CAS display is displayed on DU 5.
　
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