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instruments and CAS messages is displayed on DU 5.
END
Symbol Generator Failure AFM 3-18-20
The following table summarizes the Symbol Generator (SG) selection
possibilities:
Control Switch and Position Symbol Generator Used
PILOT EICAS COPILOT PILOT EICAS COPILOT
NORM NORM NORM 1 3 2
ALT NORM NORM 3 3 2
ALT ALT NORM 2 2 2R
ALT ALT ALT Red X Red X Red X
ALT ALT ALT 1 3 2
ALT NORM ALT 3 3 3R
NORM NORM ALT 1 3 3
NORM ALT NORM 1 2 2
NORM ALT ALT 1 1 1R
NORM = Normal
ALT = Alternate
R = Repeater of source in use by opposite side
= SPZ-8000 equipped airplanes
= SPZ-8400 equipped airplanes
END
Quick Reference Handbook
REVISION 7 ABNORMAL / EMERGENCY PROCEDURES
May 30/02 Page EA - 33
Traffic And Collision Avoidance System (TCAS)
Failure AFM 3-18-30
1. Equipment Failure:
Should TCAS fail, a TCAS FAIL blue advisory message will be
displayed on EICAS.
2. Circuit Protection:
TCAS components are protected by the TCAS circuit breaker on
the copilot’s aft circuit breaker panel (TCAS, D-11).
END
Enhanced Ground Proximity Warning System
(EGPWS) Failure AFM 3-18-40
EGPWS components are protected by EGPWS circuit breakers on
the copilot’s overhead circuit breaker panel (EGPWS AC, D-10;
EGPWS DC, E-10).
END
DADC Failures AFM 3-18-40
“Flagged” DADC Failures
A “flagged” DADC failure is one where the failure is readily apparent,
because of the blue DADC 1 (or 2) FAIL advisory CAS message, and
red “X's” through all four air data scales (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)
Continued on next page →
Quick Reference Handbook
ABNORMAL / EMERGENCY PROCEDURES REVISION 7
Page EA - 34 May 30/02
DADC Failures, ctd… AFM 3-18-40
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
“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 reengage
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
END
Quick Reference Handbook
REVISION 7 ABNORMAL / EMERGENCY PROCEDURES
May 30/02 (BRAKE BY WIRE) Page EB - 1
Brakes / Anti-Skid (Brake By Wire) Index
Hydraulic System Diagram............................................................EB-2
Emergency Brakes (Brake-By-Wire)......................................... EB-3
Wheel Brake Failure (Brake-By-Wire) ..........................................EB-3
Brake Confidence Check - Inflight (Brake-By-Wire) .....................EB-3
Uncommanded Applied Brake Pressure -
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