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galley power. Once at or below 32,000 feet PA, windshield heat and galley
power are automatically restored.
In order for ELWS to become active when selected ON, the following
selections must first occur: windshield heat must be selected ON, aircraft
electrical power sources must be selected ON and proper EPMP
configuration must be established. If these conditions are not met, an
amber ELWS FAIL annunciator is illuminated above the pilot’s and copilot’s
navigation display. The system can be reset and the annunciation
extinguished by ensuring windshield heat is selected ON and cycling the
APU LOAD meter OFF and back to ON.
The electrical load warning computer continuously performs selfmonitoring
of its hardware and software. It also monitors annunciator
outputs for excessive current conditions during normal system operation.
When operating, the ELWS provides outputs for the following
annunciations described here and shown in Figure 5 and Figure 12.
(1) An amber TEST light illuminates on the APU LOAD meter when
ELWS detects a warm or cold start with the aircraft on the ground. It
also illuminates briefly in flight as part of the self-test.
(2) An amber ADC light illuminates on the APU LOAD meter when
ELWS determines that one or both ADC inputs is invalid with the
aircraft on the ground. It also illuminates in flight when ELWS
determines that one ADC input is invalid. If both ADC inputs are
invalid, an amber ELWS FAIL annunciator is illuminated above the
pilot’s and copilot’s navigation display.
(3) An amber APU LOAD annunciator is illuminated above the pilot’s
and copilot’s navigation display when APU electrical load for
operation above 30,000 feet PA is out of limits. The APU electrical
load should then be adjusted as required.
(4) A red APU LOAD annunciator is illuminated above the pilot’s and
copilot’s navigation display when APU electrical load for operation
above 30,000 feet PA is out of limits and should be adjusted as soon
as possible. With this annunciator illuminated, the CABIN MASTER
is normally selected OFF.
(5) An amber ELWS CONFIG annunciator is illuminated above the
pilot’s and copilot’s navigation display when ELWS determines that
the EPMP is improperly configured for ELWS operation. On the
ground, illumination occurs simultaneously with illumination of the
amber ADC light on the APU LOAD meter when one air data source
is invalid.
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-24-00
Page 13
May 30/02
Revision 7
(6) An amber ELWS FAIL annunciator is illuminated above the pilot’s
and copilot’s navigation display when ELWS determines the system
is unreliable for operation above 30,000 feet PA. Normally, the
system can be reset and the annunciation extinguished by ensuring
windshield heat is selected ON and cycling the APU LOAD meter
OFF and back to ON.
(7) A white ON light illuminates on the APU LOAD meter when ELWS is
powered and operational. If ELWS detects a fault and is unable to
illuminate the ELWS FAIL annunciator, the ON light will flash twice
per second to alert the flight crew of the ELWS failure.
Airplanes with ASC 420 (Removal of APU LOAD Meter), and SN 1430
and subs: Airplanes SN 1000 through SN 1155 with both APU LOAD
Meter and ASC 420 incorporated, SN 1156 through 1429 with ASC 420
incorporated, and SN 1430 and subs have a ram air scoop installed over
the APU inlet door in order to direct more ram air into the APU. This
modification improves the high altitude performance of the APU, making
the APU LOAD meter unnecessary and thus it is removed by the ASC.
K. Distribution and Control System:
AC power control and distribution to the AC buses takes place through the
EPMP, PDB and ACBPCU. The bus system then distributes power to the
various aircraft systems. The AC bus system consists of the Left Main AC
bus, Right Main AC bus and Essential AC bus.
Normal system load during alternator operation consists of the left
converter powering the Left Main and Essential AC buses, and the right
converter powering the Right Main AC bus. If an alternator fails, the
remaining alternator automatically assumes the total electrical load.
Transfer relays allow either the Left or Right Main AC bus to receive power
from either the left or right converters. In addition, either or both main AC
buses can receive power from the APU or, if on the ground, external AC
power. The transfer relays also prevent the inadvertent connection of two
power sources to one system. The Essential AC bus provides power for
essential inflight loads. It can receive three-phase power from either of the
　
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