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remain unpowered.
G. Maintain a minimum of 67% HP RPM while in this configuration.
H. For Approach and Landing:
NOTE: The crew may elect to land with "batteries only" powering the essential bus
provided there is power to the main buses from the converters. Load shedding of
the MAIN boost pumps and opening the cross flow valve prior to landing should
be sufficient to preserve batteries.
1. Gear Handle ....................................................................................................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 will 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 airplane.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
FAA APPROVED 3-65
11 October 2001
3-08-00: ENGINE CONTROL SYSTEM
3-08-10: Engine Synchronizer Failure:
Failure of the engine synchronizer will be evident by left engine failing to maintain
synchronization with the right on either low pressure or high pressure speed. Should this occur,
select the synchronizer OFF. The synchronizer has also failed if, when Selecting system OFF,
the operating light fails to extinguish after fifteen (15) seconds; should this occur, pull the ENG
SYNC circuit breaker. If the synchronizer has failed, power lever stagger and asymmetric
reverse thrust may be expected but should not present control problems. With the synchronizer
in the failed mode, the approach idle system will not limit the engine to minimum approach RPM
of 67 % HP RPM. This RPM must be monitored on approach.
On SN 1214 and subsequent and airplanes with drawing 1159SB40761/1159SB40762, the
Engine Synchronizer function is controlled by the autothrottle. The engine sync function is only
available when the Autothrottle is engaged and the Autothrottle is in the speed control mode,
e.g., cruise, V/S mode, V PATH mode, or pitch hold mode. The engine sync function is enabled
with the Autothrottle engaged by using the ON/OFF and LP/HP selector switches in the overhead
panel.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
3-66 FAA APPROVED
31 May 2000
3-08-20: Approach Idle System Failure:
1. Illumination of amber "ENG IDLE" light:
IN-FLIGHT
A. If flaps are less than 39°, minimum idle for corresponding engine may increase to 67%
HP RPM.
B. If flaps are at 39°, the flight crew must manually maintain minimum engine RPM to
67% HP RPM on approach.
ON GROUND
A. Minimum idle for the corresponding engine may increase to 67% HP RPM.
2. Approach Idle System Failure - Amber "ENG IDLE" light does not illuminate:
IN-FLIGHT
A. If flaps are at 39°, the flight crew must manually maintain minimum engine RPM to
67% HP RPM on approach.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
FAA APPROVED 3-67
29 January 2002
3-08-30: Engine Vibration:
If EVM exceeds 0.60 LP and/or 0.60 HP:
1. Power Lever ............................... RETARD UNTIL EVM RETURNS TO NORMAL LEVEL
CAUTION: EVM INDICATIONS ALONE SHOULD NOT BE USED AS CRITERIA FOR
ENGINE SHUTDOWN. IN ICING CONDITIONS, VIBRATIONS MAY
EXCEED THE ALERT LEVEL WITHOUT OTHER ABNORMAL
INDICATIONS AND ARE CONSIDERED NORMAL.
If vibration is accompanied by other failure indication:
2. Affected Engine .................................................................................................. SHUTDOWN
If in flight, see Chapter 4, Section 4-10-10: Engine Failure/Shutdown In Flight.
If on ground, see Chapter 2, Normal Procedures: Section 2-06-20: Shutdown.
3-08-40: Ice Shedding Procedures:
IN FLIGHT
To assist in shedding ice, if high vibration occurs and operational circumstances permit, one
engine at a time may be retarded to idle, held there for five (5) seconds, and then accelerated to
85% LP RPM. The power lever may then be returned to its original position.
　
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