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Trim speed region.
(Greater than 0.80 Mach)
Retrim or slow airplane.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
FAA APPROVED 3A-15
31 May 2000
AMBER CAUTION MESSAGES
CAS INDICATION CAUSE CORRECTIVE ACTION
MACH TRIM OFF Pitch Trim switch OFF or
electric trim system has
failed (message inhibited at
less than 0.82 Mach).
Check pitch trim switch engaged (light
out). If switch engaged, check STAB
AUG circuit breakers. Observe mach
trim inop speed. See Section 1,
LIMITATIONS.
L-R MAIN FUEL FAIL Main boost pump has
failed.
Select alternate boost pump. Turn failed
pump OFF and pull appropriate CB in
PDB. See Section 3 for procedure.
PAX OXYGEN OFF Passenger oxygen bottle is
shut OFF at bottle.
Select bottle to OPEN position at the
bottle.
L-R PITOT HT FAIL Pitot tube heater elements
not energized.
Check PITOT HEAT switch ON/Circuit
Breaker(s) -- IN. If PITOT HEAT
illuminates, expect erroneous indications
of ASI, Air Data System Computer,
Airspeed Warning Sensor, and Mach
Trim Compensation. Depart icing
conditions.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
3A-16 FAA APPROVED
31 May 2000
AMBER CAUTION MESSAGES
CAS INDICATION CAUSE CORRECTIVE ACTION
RETRIM L-R WING
DOWN
Lateral axis out of trim. Grasp control yoke firmly. Disconnect
autopilot and retrim airplane in direction
indicated.
SNGL RUDDER LIMIT Failure of input pressure
load limiter (with flight and
combined system pressure
normal).
Avoid abnormal rudder deflection.
SPD BRAKE
EXTENDED
Speed Brakes (Flight
Spoilers) are deployed with
throttles above idle.
Retract speed brakes or reduce thrust as
desired.
SSEC DISABLED Static source error
correction to DADC has
been disabled.
Check the appropriate radio rack DADC
test switches.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
FAA APPROVED 3A-17
31 May 2000
AMBER CAUTION MESSAGES
CAS INDICATION CAUSE CORRECTIVE ACTION
STAB-FLAP FAIL Flaps UP (0°) and stabilizer
not up.
Lower flaps to correspond with stabilizer
position to prevent running out of
longitudinal trim. Maintain airspeed
within flap position limits. See Section 3
for partial flap landing and failure of
stab/flap interconnect procedures.
STALL BARRIER 1-2 Stall Barrier System giving
stall angle indication.
If either valve light is illuminated, check
airplane attitude, power, and airspeed. If
primary instruments indicate normal
conditions, disable system by pulling the
STALL WARN CMPTR circuit breaker.
Full protection is provided by operative
system.
STALL BARR 1-2 FL Stall barrier failed. It is
normal for STALL
BARRIER 1 FL to appear
any time EMERGENCY
FLAPS are used and flap
position is greater than 22°.
Check stall barrier and stall barrier valve
circuit breakers. Pull faulty barrier
breakers. Stall barrier protection is still
available with one (1) system operative.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
3A-18 FAA APPROVED
31 May 2000
AMBER CAUTION MESSAGES
CAS INDICATION CAUSE CORRECTIVE ACTION
STALL BARRIER OFF Stall Barrier Switch OFF or
system not powered.
Check Stall Barrier Switch ON ("OFF"
light out). If on, check Stall Barrier and
STALL BARR VALVE circuit breakers.
STBY PITOT HT FAIL Stby pitot heater elements
not energized.
Check Stby Pitot Heat Switch and circuit
breaker.
STEER BY WIRE FAIL Both steering channels have
failed: steering not
available. System is in
shimmy damp mode.
With ASC 176 installed, a
switch position/system
status miscompare is
detected.
Check circuit breakers. Cycle steering
ON/OFF switch. If message does not
clear, use rudder, brakes, and/or
differential power for steering. If
message occurs on ground with no
hydraulic power available, turn power
switch OFF until engines are running.
Reselect power switch ON.
If message occurs in flight see NOSE
WHEEL STEERING FAILURE,
Section 3.
TAT PROBE HT FAIL TAT probe heater has
failed.
TAT inputs to DADC’s may be
inaccurate. DADC outputs and FMS
readouts may be inaccurate. Check
circuit breaker.
GULFSTREAM AEROSPACE
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湾4飞机飞行手册AFM Gulfstream IV AIRPLANE FLIGHT MANUAL 1(83)
