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ABNORMAL
PROCEDURES
3-72 FAA APPROVED
31 May 2000
3-11-40: Hot Start:
If engine exceeds maximum start temperature (700°C), move HP Fuel Cock to SHUT.
Continue to motor engine, to reduce TGT, for maximum of thirty (30) seconds then START
MASTER SWITCH OFF.
Prior to next attempt to start, check fuel boost pump ON, fuel pressure normal, air source
available, and pressure adequate. Check wind direction and attempt start directly into wind;
move airplane if required. If second attempt produces hot start, shut down. DO NOT attempt
restart.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
FAA APPROVED 3-73
31 May 2000
3-13-00: FIRE DETECTION SYSTEM
3-13-20: Fire Detection System Fault:
Each of the two (Loop A and Loop B) fire detection loops of each engine is provided with a fault
discriminator circuit. Fault indicators and a single test button to test all four loops are located in
the engine control section of the overhead panel.
If a fire detection loop develops a fault, the associated amber fault light will illuminate and an
amber ENG FLT LOOP ALRT caution message with the associated tone will be generated.
Since both loops must sense a fire or overheat in order to trigger an engine fire warning, the
faulty loop will preclude that capability until it has been isolated from the system. The faulty
loop is isolated and fire detection system is restored to normal operation by pressing the amber
FAULT switch/light, at which time the OFF portion of the switch light will illuminate.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
3-74 FAA APPROVED
31 May 2000
3-14-00: FLAPS SYSTEM
3-14-10: Failure of Stabilizer/Flap Interconnect:
Failure of stabilizer/flap interconnect may be indicated by illumination of the STAB-FLAP FAIL
caution message; it will be confirmed by unsynchronized movement of the stabilizer and flap
needles on the stabilizer/flap position indicator as well as an out of trim condition as the flaps are
moved. Proceed as follows:
1. Stop further flap movement.
2. Land as soon as practicable; if further flight is necessary, match flaps to stabilizer position
and observe appropriate placard speed.
3. Select GPWS/GND SPLR FLAP ORIDE ........................................................................... ON
4. For landing:
STABILIZER FAILED AT 20° or 39° POSITION
Match flaps to stabilizer position. If appropriate, See PARTIAL FLAP LANDINGS, this Section.
If runway length is limited and the stabilizer is in 20° position, then 39° flaps may be used for
landing. In that condition, use full nose up elevator trim as required and expect heavy pull forces
on final approach and during landing.
STABILIZER FAILED AT 0° or 10° POSITION
Match flaps to stabilizer position. See PARTIAL FLAP LANDINGS this Section. If runway
length is limited, 20° flaps may be used for landing. In that condition, use full nose up elevator
trim as required and expect heavy pull forces on final approach and during landing.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
FAA APPROVED 3-75
31 May 2000
3-14-20: Wing Flaps - Alternate Operation:
If the Combined and Utility Systems fail, Auxiliary System pressure can be utilized to operate
the flaps. Use the Normal Flap Control Lever to select flap position regardless of pressure
source, either Combined, Utility or Auxiliary.
CAUTION: IF OPERATING (COMBINED OR UTILITY) HYDRAULIC PRESSURE
READS ZERO IMMEDIATELY AFTER SELECTING FLAPS, PULL BOTH
FLAP CONTROL AND MANUAL FLAP CONTROL CIRCUIT BREAKERS
BEFORE TURNING ON AUXILIARY HYDRAULIC PUMP. THIS WILL
ENSURE THAT AUXILIARY SYSTEM FLUID WILL BE AVAILABLE FOR
BRAKING AFTER LANDING.
Use the Emergency Flap Control whenever an electrical malfunction is suspected within the flap
control circuit. Asymmetry protection is provided in all modes of operation.
NOTE: When using the Emergency Flap Control, AOA indication on the PFD’s will be invalid
(Red X). Stall barrier system (Shake and Push) will continue to function normally (two
systems). When 39° Flap is selected "STALL BARR 1 FL" message on CAS display
will illuminate. Pull the No. 1 Stall Warning Computer CB on Copilots overhead
panel. Stall Barrier System will be single system operation with the operative stall
warning computer providing normal Shake and Push functions.
To use the Emergency Flap Control, proceed as follows:
1. Flap Lever ........................................................................................................AS REQUIRED
　
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