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2. Aileron Control (Roll) ......................................................PULL Flight Power Shutoff Handle
3. Elevator Control (Pitch)....................................................PULL Flight Power Shutoff Handle
NOTE: Use only lateral and longitudinal trim after pulling Flight Power Shutoff Handle.
Disengage Yaw Damper. Return directional trim to the neutral position prior to
restoring hydraulic boost to flight control. If control is not regained in manual mode,
return hydraulic boost to flight controls.
If Yaw Damper disengages as result of pulling Flight Power Shutoff Handle, do not
attempt to reengage it until hydraulic pressure has been restored to Flight Controls.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 4
EMERGENCY
PROCEDURES
4-40 FAA APPROVED
11 October 2002
4-15-40: Stall Barrier Malfunction:
Malfunctions of the Stall Barrier (Control Column Pusher) System have been demonstrated
throughout the flight envelope. Negative acceleration resulting from unwanted control column
push has never exceeded an increment of one (1) g., which is well within structural envelope of
airplane. Altitude loss is minimal, providing prompt recovery action is initiated by the pilot. If
necessary, a stall barrier malfunction can be readily overridden by manual pilot control
(approximately 75 lbs. (334N)).
In the event of unwanted stall barrier actuation, the following procedure applies:
1. Autopilot Disengage Button ........................................................................PRESS and HOLD
2. Stall Barrier Switch.............................................................................................................OFF
3. Autopilot Disengage Button .....................................................................................RELEASE
4. Determine failed Stall Barrier System and disable by pulling the appropriate Stall Warning
Computer (STALL WARN COMPTR) circuit breaker on the copilot’s overhead CB panel.
5. Stall Barrier Switch............................................................................ ON (proceed with flight)
If stick pusher actuates in flight and cannot be partially restored using above procedures, it is
probable that a hydraulic malfunction has occurred in Stall Barrier System. In this event, it will
be necessary to continue flight with Stall Barrier System deactivated by leaving the Stall Barrier
Switch in OFF position.
4-15-50: Ground Spoiler Failure:
IN-FLIGHT
If the GND SPOILER warning message illuminates:
1. Ground Spoiler Arming Switch ..........................................................................................OFF
2. GND SPOILER Circuit Breaker...................................................................................... PULL
DURING LANDING
If NO GND SPOILER light illuminates (remains ON) after landing touchdown (GND
SPOILERS ARMED).
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 4
EMERGENCY
PROCEDURES
FAA APPROVED 4-41
11 October 2002
1. Speed Brakes..................................................................................DEPLOY IMMEDIATELY
NOTES: (1) Aircraft Configuration message may illuminate and warning tone may sound
momentarily.
(2) NO GND SPOILER light may light momentarily after touchdown during landing,
and then go out again, in less than one (1) second. This is the normal sequence of
events as the ground spoilers go through their automatic deployment process.
Wheel spin up logic should preclude this occurrence. If light remains ON after
touchdown, the above procedure applies.
4-16-00: FUEL SYSTEM
4-16-10: Fuel Leak In Flight:
A suspected fuel leak will most likely manifest itself as an increasing difference in fuel quantity
that can not be explained by normal differences in fuel flows between engines. It can also be
identified by fuel smell in the cabin, abnormally high fuel flow or fuel flow out of range
“ dashed” indications on one of the engines, or lateral trim changes
CAUTION: DO NOT PERFORM THIS PROCEDURE ON THE BASIS OF ERRATIC FUEL
GAUGE INDICATIONS ONLY OR DURING ASYMMETRIC TRIM
REQUIREMENTS FELT DURING ACCELERATING PHASES OF FLIGHT
SUCH AS INITIAL CLIMB OR NOSE HIGH OR NOSE LOW PITCH
ATTITUDES.
1. FUEL CROSSFLOW VALVE...................................................................................CLOSED
2. FUEL INTERTANK VALVE ....................................................................................CLOSED
3. FMS SINGLE ENGINE PERFORMANCE/RANGE..................................................CHECK
Monitor fuel tank quantities and lateral trim requirements. Identify leak by observing one wing
　
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