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must be on for the warning to be armed.
• ALTNR OFF - light capsule illuminates ALTNR OFF in white when
APU alternator is available for electric power (APU RPM at 95% or
above for more than 4 seconds) and AUX PWR switch on the
ELECTRIC MASTER panel has not been selected. When AUX PWR
is selected on the ELECTRIC MASTER panel, the ALTNR OFF light
on the APU panel will extinguish.
• EGT - digital readout of APU EGT in ¡C displayed in amber
numerals. An amber warning circular light above the readout comes
on if APU is at 100% RPM and EGT reaches 688¡C.
• RPM - digital readout of APU RPM displayed in amber numerals. An
amber warning circular light above the readout comes on if APU
OPERATING MANUAL
PRODUCTION AIRCRAFT SYSTEMS 2A-49-00
Page 9
October 11/02
Revision 8
RPM exceeds 104%.
B. BLEED AIR Panel:
Selecting APU bleed air for engine starting and air conditioning (ground
operation only) is accomplished by pressing the APU switch on the BLEED
AIR panel:
• APU - alternate action switch, signals ECU to open the APU load
control valve (after APU has reached a stabilized RPM of 95% or
more for at least 4 seconds). Indications of load control valve
operation are ON (amber) indicated in the switchlight, a rise in APU
EGT and readout of APU bleed air pressure on the BLEED AIR
panel. Selecting APU bleed air ON will also open the ISOLATION
valve in the pneumatic system to allow APU bleed air to pressurize
both sides of the system. For more information regarding APU bleed
air and the airplane pneumatic system, see section 2A-36-00 of this
manual.
NOTE:
Both engine power levers must be at the idle position
(whether engines are operating or not) for the load
control valve to open and supply bleed air to the
pneumatic system.
C. ELECTRIC MASTER Panel:
Selecting the APU alternator to power the airplane electrical systems is
accomplished by pressing the AUX PWR switch on the ELECTRIC
MASTER panel:
• AUX PWR - pressing the switchlight (with APU RPM stabilized at
95% or more for at least 4 seconds) connects APU alternator AC
power to the airplane electrical system. ON will illuminate in amber
above the switch and APU alternator frequency, voltage and load
percentage may be read on the ELECTRIC POWER MONITOR
panel.
D. Standby Warning Lights Panel (SPZ-8000 Equipped Airplanes):
• APU ALT FAILED BRG - light capsule illuminates amber when the
main bearing of the APU alternator has failed and the APU is
operating on the alternate bearing. APU operation using the
alternate bearing is limited to Þfteen (15) hours at full load or Þfty
(50) hours with no load (air bleed only).
E. Electrical Load Warning System (ELWS):
For airplanes SN 1156-1429 with the ELWS installed, a gauge on the lower
pilot side forward instrument panel indicates the electrical load of the APU
when it is used to power the electrical system in ßight. The gauge aids the
ßight crew in monitoring the APU alternator when operating near the limits
of the APU altitude envelope. The ELWS contains a processor unit, called
the Electrical Load Warning Computer (ELWC) that uses inputs from the
Digital Air Data Computers (DADCs) to aid in conÞguring the airplane
electrical load to meet APU alternator capabilities. If the APU alternator is
powering the right AC electrical bus and the airplane altitude exceeds
34,000 feet, the ELWS will load shed heat to the right windshield controller.
OPERATING MANUAL
2A-49-00 PRODUCTION AIRCRAFT SYSTEMS
Page 10
October 11/02
Revision 8
If the APU is powering the left AC electrical bus, the left windshield heat
controller will be shed above 34,000 feet. If the APU alternator is powering
the right AC electrical bus and the left converter / alternator fails (single
alternator operation), the ELWS will shed the galley master electrical load
in addition to the right windshield heat controller if airplane altitude exceeds
34,000 feet. See the description of the ELWS and illustration of the gauge
in section 2A-24-00 of this manual.
F. Forward Instrument Panel:
Two APU electrical load indicators, shown in Figure 3, are included in the
warning/caution lights panels located above the EFIS display units 2 and 5
on the pilot and copilot forward instrument panels. The indicators signal
APU electrical load and/or load monitoring abnormalities when using the
APU at high altitudes (above 30,000 feet). For more information, see the
discussion in section 2A-24-00 of this manual.
• APU LOAD (amber) / APU LOAD (red) - is a split annunciator
　
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