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computer. The dual channel computer provides buffered outputs to
the indicators for protection. The pilot AOA indicator receives data
from the left channel of the stall warning computer and the copilot
AOA indicator receives data from the right channel of the stall warning
computer. The AOA indicator is adequately marked displaying .10, .20,
.30, .40, .50, .60, .70, .80, .90, 1.0 with unnumbered marks half way between
each. The beginning of the red band at .80 represents shaker activation
and an imminent stall condition. The AOA indicators front
plate markings are consistent with the stall warning information
shown on the PFDs, a tape type presentation at the end of the airspeed
tape. The AOA indicators are powered via the L STALL WARN and R
STALL WARN circuit breakers located on the pilot’s and copilot’s circuit
breaker panels (FLIGHT group).
F40-050000-055-01
PILOT AOA
INDICATOR
COPILOT AOA
INDICATOR
INSTRUMENT PANEL LAYOUT AND AOA INDICATOR POSITION
Figure 5-5
F40-050000-055-01
Pilot’s Manual
5-30 PM-126A
AVIONICS
HONEYWELL PRIMUS 1000 AVIONICS SYSTEM
The Learjet 45 is equipped with a Honeywell Primus 1000 Avionics system.
The primary component of the Primus 1000 system is the display
flight guidance computer, or more simply, the IC-600. This computer,
together with the appropriate controllers and sensors, comprises the
Primus 1000 system. It consists of dual IC-600 (single autopilot is contained
in the copilot’s IC-600), dual air data computers, PRIMUS
weather radar system and appropriate controllers. The radio sensor
package is the Honeywell PRIMUS II integrated radio system.
ELECTRONIC FLIGHT INSTRUMENT SYSTEM (EFIS)
The PRIMUS 1000 EFIS System consists of four, 8 x 7 inch, Display
Units (DUs) driven by two Symbol Generators (SGs) resident in the two
IC-600s. The EFIS presents information to the crew in an uncluttered
format, simplifying cockpit scan, and reducing pilot workload and fatigue.
The flight instruments, engine instruments, system status, navigation,
TCAS, RADAR, and electronic checklist are all displayed on
these high resolution DUs. The EFIS is integrated with the Engine Indicating
and Crew Alerting System (EICAS) and Crew Warning Panel
(CWP) to provide the crew with not only flight monitoring indications
but also with engine data, warning, cautionary and advisory alerts (visual
and aural). Dual Primary Flight Displays (PFDs) combine attitude
and HSI formats with airspeed, vertical speed and other essential information,
such as resolution advisories for the optional TCAS system. A
Multi-Function Display (MFD) offers a full spectrum of operational capabilities,
from weather radar and mapping displays, to a custom programmable
checklist. A digital audio control system and dual Radio
Management Units (RMUs) support the communications and navigation
functions.
Pilot’s Manual
PM-126A 5-31
The display information provided on EFIS is generated by two IC-600
computers located in the nose. Each of the IC-600s contains circuitry
that performs the symbol generation function for the EFIS. Along with
interfacing with the display units, the ICs receive data from the Data
Acquisition Units (DAUs), Air Data Computers (ADCs), Attitude
Heading Reference System (AHRS), navigation system, flight management
system, autopilot and other various display controllers. The CAS
monitors the IC-600 bus interconnect, the temperature of each IC-600,
the IC cooling fans and Weight-On-Wheels (WOW). A CAS will also
illuminate if communications between the left and right ICs are invalid.
The following CAS illuminations are specific to the IC-600:
IC-600 POWER SOURCE
The #1 and #2 IC-600s are powered from the left and right essential
buses respectively. The circuits are protected by the 7.5-amp IC/SG 1
and IC/SG 2 circuit breakers on the pilot’s and copilot’s circuit breaker
panels (INSTRUMENT/INDICATIONS group).
CAS Color Description
IC 1-2 OVHT Amber #1 and/or #2 Integrated avionics Computer
(IC) are/is overheated.
IC BUS FAIL Amber -The off-side IC has failed.
or
- IC bus invalid
IC1-2 FAN FAIL White #1 and/or #2 Integrated avionics Computer
(IC) cooling fan has failed.
IC1-2 WOW INOP White The associated (#1 or #2) Integrated avionics
Computer (IC) has tripped the weight-onwheels
validity monitor.
Pilot’s Manual
5-32 PM-126A
AVIONICS MASTER SWITCHES
Left and right avionics master switches are located on the electrical
control panel below DU 2 (Figure 5-6). When the alternate action
avionics master switches are selected to On (OFF annunciator
　
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