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by illumination of the ANTI-SKID FAIL amber message on the EICAS.
There is no automatic reversion to auxiliary braking unless the combined/utility hydraulic system
fails.
If the anti-skid switch is left ON there may still be anti-skid protection on one pair of wheels
(inboard or outboard). With the anti-skid switch OFF all anti-skid protection is disabled.
Braking with the ANTI-SKID FAIL message illuminated should be performed using the ANTISKID
OFF BRAKING procedures defined in this section.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
FAA APPROVED 3-11
11 October 2001
3-02-50: Anti-Skid Off Braking (HMAB):
FOR AIRPLANES SN 1183, SN 1214 AND SUBS
With the anti-skid system failed or OFF, full braking performance is not available and stopping
distances are significantly increased. Applied brake pressure must be carefully controlled to
avoid locked wheels and blown tires.
TAKEOFF
During takeoff with ANTI-SKID inoperative or Selected OFF, wheel spindown function will be
functional.
Perform the following Steps for takeoff with the ANTI-SKID inoperative or OFF:
1. ANTI-SKID Switch ............................................................................................................OFF
2. Select Applied Brake Pressure Display on DU 4.
APPROACH AND LANDING
The following procedure should be used when braking with anti-skid inoperative.
1. ANTI-SKID Switch ............................................................................................................. ON
2. Select Applied Brake Pressure Display on DU 4.
3. Apply Maximum Reverse Thrust.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
3-12 FAA APPROVED
13 September 2000
4. Immediately upon landing or at takeoff abort, the pilot should smoothly apply brakes to
approximately 300 psi as advised by the copilot. In an anti-skid inoperative situation, the
pilot should devote his attention to airplane control and the copilot should monitor applied
brake pressure and advise the pilot of corrections needed to maintain 300 psi.
CAUTION: IT IS NORMAL FOR DECELERATION TO INCREASE AS THE STOP
PROGRESSES. IT IS EXTREMELY IMPORTANT TO MAINTAIN 300 PSI TO
AVOID LOCKED WHEELS AND BLOWN TIRES. THERE WILL BE A
SIGNIFICANT INCREASE IN LANDING DISTANCE WITH ANTI-SKID
INOPERATIVE.
NOTE: Brake pedal position in relation to brake pressure can be observed and practiced
airborne with the anti-skid system selected OFF, and the landing gear up or down.
An increase in landing distance will result if a landing rollout is made with anti-skid
inoperative. For landing distances with Anti-skid inoperative see Landing Field Length
Anti-Skid Inoperative Chart, Performance Section. Use of Reverse Thrust reduces
AFM landing distances.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
FAA APPROVED 3-13
31 May 2000
3-03-00: AUTO FLIGHT SYSTEM
3-03-10: Autopilot Malfunction:
If the Autopilot malfunctions, disengage Autopilot as follows:
1. Autopilot disengage button (on either pilots’ control wheel).................PRESS (Momentarily)
The Autopilot may also be disengaged by any of the following:
2. Autopilot "ON" Capsule (Guidance Panel) ................................................................... PRESS
3. Electric Elevator Trim Switch .................................................................................ACTUATE
4. Autopilot will disengage if either G/A button is pressed.
CAUTION: THE AUTOTHROTTLE, IF ENGAGED WHEN G/A BUTTON IS PRESSED,
WILL INCREASE POWER TO G/A EPR.
If a flight guidance computer fails, the second computer will continue to control airplane. A
failure of the second computer will disconnect the autopilot.
In the event that above methods fail, the autopilot may be overpowered by the pilot.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
3-14 FAA APPROVED
31 May 2000
3-03-20: Autothrottle Malfunction:
Disengage the Autothrottle as follows:
1. Activating either momentary action engage/disengage thumb lever located on the power
levers.
2. Activating either mechanical disengagement button located on the front of the power lever
knobs.
3. Deselecting the autothrottle ARM button on the Guidance Panel.
If the above methods fail, the autothrottle may be over powered by the pilot and will
automatically disengage. Override forces may be as high as forty (40) pounds.
A failure of either autothrottle control system will result in system disengagement. The opposite
　
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