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05-07-10: Alternator/Converter Failure - Dual
L-R AC PWR FAIL (AMBER)
L-R DC PWR FAIL (AMBER)
If both (Left and Right) Alternator/Converter combinations fail and the APU is OFF, the
only source of electrical power is either the Standby Electrical Power system or the
batteries. This will power the Essential DC bus and Phase A of the Essential AC bus
through the Emergency Inverter (E-Inverter). In the event of power loss from both (left
and right) converters in flight, remove all non-essential electrical loads. After verifying
that neither alternator/converter can be regained by use of Section 05-07-40, Alternator/
Converter Failure - Single, proceed as follows:
1. Crossflow .....................................................................................................OPEN
2. Fuel Boost Pumps (One MAIN Only) ..........................ON (ALL OTHERS OFF)
3. L / R FUEL PRESS LOW Messages .............................................CHECK / OUT
IF COMBINED SYSTEM HYDRAULIC PRESSURE AND THE STANDBY
ELECTRICAL POWER SYSTEM ARE AVAILABLE, PROCEED WITH STEP 4. IF
NOT, PROCEED TO STEP 11.
NOTE:
Approximately twenty (20) minutes of electrical power
is available if both batteries are fully charged and
Standby Electrical Power system cannot be used.
4. All Normal Electrical Power Sources (Except Batteries) ...........................OFF
5. STANDBY ELECTRICAL POWER STBY ELEC Switch..................................ON
6. STANDBY ELECTRICAL POWER E INVERT Switch .....................................ON
7. STANDBY ELECTRICAL POWER TRU Switch ..............................................ON
CAUTION
UNLOAD ELECTRICAL SYSTEM TO STAY AT OR
UNDER 100% LOADING OF ACAND DC POWER, AS
INDICATED ON STANDBY ELECTRICAL POWER
PANEL. IF AC POWER PERCENTAGE IS OVERRANGE,
SELECT DC ITEMS OFF,AND VICE VERSA.
NOTE:
Speed brakes may be used with the Standby Electrical
Power system operating, however, speed brake
operation should be slow (approximately five (5)
seconds for full-range movement).
8. UTILITY PUMP ....................................................................OFF / AS REQUIRED
NOTE:
If the Utility Pump is left armed (OFF/ARM switch
selected to ARM), it will run continuously.
OPERATING MANUAL
EXPANDED ABNORMAL / EMERGENCY PROCEDURES 05-07-00
Page 1
October 11/01
Revision 5
IF FGC 1 AND FGC 2 INDICATE FAILED, REGAIN USE OF FGC 1 AS FOLLOWS:
9. FGC 1 / FGC 2 Circuit Breakers (CBs).......................................................PULL
• FGC #1: Copilot’s Overhead Panel, A-7
• FGC #2: Copilot’s Overhead Panel, B-7
10. FGC 1 CB Only...........................................................................................RESET
NOTE:
The Standby Electrical Power system is powered by a
hydraulically-driven motor and is therefore sensitive to
hydraulic pressure changes. Provided the limitations in
Section 01-24-10, Standby Electrical System are
observed, the Standby Electrical Power system should
operate normally. If the system drops off line as a
result of hydraulic pressure transients, it will be
necessary to cycle the STANDBY ELECTRICAL
POWER STBY ELEC switch from ON to OFF and
back to ON.
The STANDBY ELECTRICAL POWER monitor panel indicates percent power
from the source. The airplane subsystem takes standby AC power and converts it
to DC through the TRU. Standby DC is converted to AC power through the
E-Inverter. Thus, airplane DC load is displayed on the AC (PWR %) load monitor
and AC load is displayed on the DC (PWR %) load monitor. When operating on
the Standby Electrical Power system, electrical load (both AC and DC) should be
reduced to less than 100% on the STANDBY ELECTRICAL POWER monitor
panel to avoid excessive use of battery power.
All equipment powered through the Essential AC bus and Essential DC bus is
available when using the Standby Electrical Power system. Among the items
available:
Pilot’s PFD Standby Engine Instruments
DU 3 (SG 2 and 3 - ALT) Standby Warning Panel
COMM No. 1 (or No. 3 as bused) Standby Fuel Qty Indicator
NAV No. 1 and DME No. 1 Wing / Cowl Anti-Ice
ADF No. 1 Pressurization
ATC No. 1 (Transponder) Cockpit / Cabin Temp Control (1)
Display Controller No. 1 Main Fuel Boost Pumps
FMS No. 1 and IRS No. 1 Cross Flow Valve
Both DBDIs Intertank Valve
Both Clocks Tone Generator
ISDU (or 3rd NAV unit) Pilot’s and Standby Pitot Heat
DADC No. 1 Airstart Ignition
FGC No. 1 (TURN Knob Inop) Fire Detection / Protection
Flight Director Both FWCs (2)
Pitch Trim AOA No. 1
Yaw Damper Aux Hydraulic Pump
　
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本文鏈接地址：灣流4操作手冊 Gulfstream IV Operating Manual 3(82)