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2. Auxiliary Hydraulic Pump............................................................................. ON (If Required)
NOTE: Do NOT engage autopilot when using Emergency Flaps unless flap deflection is 10° or
greater.
3. Emergency Flap Switch ...............................................................................................EMERG
NOTE: Activating the Emergency Flap switch will cause Flap Input invalid message on FMS
CDU, the speed target will become invalid, VREF will no longer be displayed on the
Display Controller or PFD speed tape and the autothrottle will disengage.
4. Emergency Flap Control .................................................. PUSH or PULL (Extend or Retract)
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
3-76 FAA APPROVED
31 May 2000
When flaps attain desired position:
5. Emergency Flap Control ..........................................................................................NEUTRAL
CAUTION: IN ORDER TO GUARD AGAINST THE REMOTE POSSIBILITY OF
ASYMMETRY PROTECTION FAILURE WHEN USING EMERGENCY FLAP
CONTROL, OBSERVE THAT NO AIRPLANE ROLL IS PRESENT
INDICATING FLAP ASYMMETRY. IF ASYMMETRY IS INDICATED,
RETURN FLAPS TO THEIR PREVIOUSLY SELECTED POSITION.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
FAA APPROVED 3-77
13 September 2000
3-14-30: Partial Flaps Landings:
If landing at a reduced flap setting is unavoidable, plan a wide approach, select Airstart Ignition
ON, and observe VREF speed appropriate to configuration as shown in Performance Section. See
Performance Section for Landing Distances.
Landing with less than full flaps negates Ground Spoiler deployment as result of wheel spin-up
unless the Ground Spoiler Flap Override switch is selected ON before landing. Ground Spoiler
deployment as result of weight-on-wheels should be normal.
NOTE: Set Flap Override Switch to prevent nuisance message.
CAUTION: TIRE SPEED LIMITATIONS WILL BE EXCEEDED IF TOUCHDOWN IS
MADE IN EXCESS OF 182 KNOTS GROUND SPEED. (195 KNOTS GROUND
SPEED SN 1214 AND SUBS., AND SN 1000 THRU 1213 WITH ASC 190.)
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
3-78 FAA APPROVED
31 May 2000
3-14-40: Undesired Flaps Movement:
In the event of uncontrolled flap movement, proceed as follows:
1. Emergency Flap Switch ...............................................................................................EMERG
2. Emergency Flap Control .................................................. PUSH or PULL (Extend or Retract)
3. MANUAL FLAP CONT Circuit Breaker........................................................................ PULL
NOTE: With MANUAL FLAP CONT circuit breaker pulled, flaps are inoperative. Emergency
flap control may be regained by resetting MANUAL FLAP CONT circuit breaker and
operating the Emergency Flap Control.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
FAA APPROVED 3-79
31 May 2000
3-15-00: FLIGHT CONTROLS SYSTEM
3-15-60: Runaway Electric Pitch Trim:
In the event of Runaway Electric Pitch Trim, the following procedure is recommended:
1. Autopilot Disconnect Button .......................................................................PRESS and HOLD
Electric trim is disabled while switch is held.
2. Electric Pitch Trim.............................................................................................. DISENGAGE
3. Autopilot Disconnect Button ....................................................................................RELEASE
4. Retrim using manual pitch trim wheel.
NOTE: Subsequent attempts to engage the autopilot will result in automatic re-engagement of
electric trim.
Due to the relatively low torque involved, the following alternate procedure may be used for
runaway electric pitch trim:
1. Manual Pitch Trim Wheel ..........................................................................GRASP and HOLD
2. Electric Pitch Trim.............................................................................................. DISENGAGE
NOTE: Subsequent attempts to engage autopilot will result in automatic re-engagement of
electric trim.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
3-80 FAA APPROVED
31 May 2000
3-15-70: Frozen Pitch Trim:
Inoperative pitch trim may be due to mechanical failure or binding of one or more system
components from ice collected in the trim mechanism. The first sign of "Frozen Pitch Trim" is
an FGC FAIL message on EICAS caused by autopilot’s inability to trim elevator control forces.
　
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