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(airspeed, altitude, AOA, and vertical speed) of the PFD using the failed DADC as its air data
source, as selected on the display controllers. Other confirmation of failure is as follows:
• Transponder indications
• AOA indexer failure
• Automatic cabin pressurization control problems and faulty guidance panel indications (if
operating on the failed DADC)
• EICAS message indicating that EPR is receiving pressure information from the opposite
DADC (EPR 1 - DADC 2 or EPR 2 -DADC 1)
If a “flagged” DADC failure has occurred:
1. Opposite (Good) DADC......................................................SELECT AS DATA SOURCE ON
DISPLAY CONTROLLERS, GUIDANCE PANEL, CABIN PRESSURE CONTROL
PANEL, ETC
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
FAA APPROVED 3-95
11 October 2001
“UNFLAGGED” DADC FAILURES
An “unflagged” DADC failure will produce a blue DADC MISCOMPARE advisory CAS
message. The failure may not be readily apparent, but the following can be expected to occur:
• The autopilot and yaw damper will disconnect and will not re-engage until the faulty
DADC has been identified and isolated by pulling its circuit breaker.
• Pitch trim will remain operative.
If an “unflagged” DADC failure is suspected:
1. Faulty DADC ATTEMPT TO IDENTIFY USING PFD COMPARATOR “IAS/ALT”
WARNINGS
To determine which system is correct,
2. Independent Data Source (Standby Flight Instrumentation) ..................................ESTABLISH
With reference to independent data source established:
3. Other DADC Outputs (Pressurization System, AOA Indexers, Transponders)..........................
....................................................... CHECK FOR INDICATIONS OF FAULTY OPERATION
If observation leads to a determination of which DADC is faulty:
4. Opposite (Good) DADC.............................................................SELECT AS DATA SOURCE
ON DISPLAY CONTROLLERS, GUIDANCE PANEL, CABIN PRESSURE CONTROL
PANEL, ETC
5. Faulty DADC .............................. ISOLATE BY PULLING ITS CIRCUIT BREAKER
(DADC #1: CP, F-3; DADC #2: CP, G-3)
When at least one (1) minute has elapsed since pulling the faulty DADC circuit breaker:
6. Autopilot .............................................................................................................. RE-ENGAGE
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
3-96 FAA APPROVED
11 October 2001
3-19-00: LANDING GEAR/LANDING GEAR SYSTEMS
3-19-20: Landing Gear Alternate Operation:
FAILURE TO RETRACT
Should gear fail to retract on takeoff, Landing Gear Selection Handle should be returned to
DOWN position and the airplane should return for landing and troubleshooting on the ground.
CAUTION: USE OF THE D RING IN AN ATTEMPT TO RETRACT THE GEAR IS NOT
RECOMMENDED.
FAILURE TO EXTEND
Alternate extension will be required if normal extension does not result in a down and locked
gear condition. A loss of Combined System fluid will also require alternate extension since the
Utility System will be inoperative, and Steps 2 and 3 may be omitted.
Landing gear extension is accomplished as follows:
1. Landing Gear Handle.....................................................................................................DOWN
2. Emergency Landing Gear T-Handle ............................... PUSH (Down, to assure fully seated)
Wait minimum of thirty (30) seconds after reseating T-Handle.
3. Dump Valve D-Ring...............PULL (Pull up fully and hold for ten (10) seconds) RESTOW.
If this procedure does not result in proper gear position and indication, proceed as follows:
CAUTION: A FULLY CHARGED NITROGEN BOTTLE (3000 PSI AT 70°F (21°C)) WILL
ALLOW ONLY ONE (1) EXTENSION OF LANDING GEAR.
4. Airspeed......................................................................................................175 KCAS (or less)
5. Emergency Landing Gear T-Handle ................................................................................ PULL
NOTE: Ensure Landing Gear Handle is DOWN for proper gear position indication and nose
wheel steering operation. Operation of Emergency System is not predicated on position
of the selector handle.
GULFSTREAM AEROSPACE
GIV AIRPLANE FLIGHT MANUAL
SECTION 3
ABNORMAL
PROCEDURES
FAA APPROVED 3-97
11 October 2001
6. Landing Gear Down and Locked ........................OBSERVE LANDING GEAR EXTENDED
......................................................................... SPEED LIMITATION (250 KCAS/0.70 MT).
　
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