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and distribution for avionics LRUs.
The IAPS consists of various functional units. The input/output concentrator units (IOCs) get data words and transmit them
to the correct LRU. The IAPS power supplies energize the IOCs. The IAPS environmental controller (IEC) monitors the
housing temperature and controls the fans. The control strapping units (CSUs) and the options control modules (OCMs)
set the IAPS strap settings.
The maintenance diagnostic computer (MDC), the flight management computers (FMCs), and the flight guidance computers
(FGCs) are in the IAPS card cage (ICC), but they are not part of the IAPS itself.
Their are no pilot-controlled operations required for the IAPS. Their are no pilot-controlled reversionary operations for the
IAPS.
COMPONENTS AND OPERATION
INTEGRATED AVIONICS PROCESSOR SYSTEM CARD CAGE
The IAPS card cage is the housing that contains all the components of the IAPS. The ICC is in the right equipment rack.
INPUT/OUTPUT CONCENTRATOR UNIT
The IAPS data receives from and transmits to many external systems. External system data is transmitted through the ICC
circuit card.
The two input/output concentrator units transmit data to other LRUs related to their operation. The IOCs transmit all the
display data from other LRUs to the displays.
INTEGRATED AVIONICS PROCESSOR SYSTEM POWER SUPPLY
The IAPS has an input from the 28 vdc main busses. The voltage is filtered and applied to the IAPS power supplies. The
two power supplies independently supply the applicable voltages to the necessary units in the IAPS. The No. 1 power supply
energizes the No. 1 FGC, FMC, and IOC No. 1. The No. 2 power supply energizes the No. 2 FGC, FMC, MDC, and
IOC unit No. 2.
INTEGRATED AVIONICS PROCESSOR SYSTEM ENVIRONMENTAL CONTROLLER (IEC)
The IEC controls the temperature for the ICC. The IEC monitors a pair of ICC temperature sensors and operates fans
to control the IAPS environment in each half of the IAPS.
The IEC has a power supply, two thermostats, two transducer monitor circuits, a two-speed fan, and a heat exchanger.
REV 1
AURAL/VISUAL ALERTS
Volume 2 Flight Crew Operating Manual Sep 13/2004
03-02-12 CSP 100-6 REV 1
MAINTENANCE DIAGNOSTIC COMPUTER
DESCRIPTION
The maintenance diagnostic computer (MDC) is an onboard computer that records aircraft mechanical and avionics system
data. Maintenance personnel can retrieve the information for use in engine trend analysis computation, significant event
recording, and avionics/aircraft system failure detection. The MDC is part of the IAPS and consists of an electronic circuit
board located in the ICC
COMPONENTS AND OPERATION
The MDC continuously records data for fault analysis and engine trend monitoring.
The MDC monitors engine operating time and counts the number of engine starts and thrust reverser deployments.
The MDC records engine parameters at takeoff to track engine efficiency.
If the engines exceed a maximum operating limit, the peak exceedance value is recorded along with the time and duration
of the occurrence.
The MDC data is downloadable to a maintenance facility computer. The data base unit (DBU) is located behind the pilot
on the forward bulkhead forward of the entry door. There is also a portable maintenance access terminal (PMAT) located
on the aft side of the equipment rack near the floor.
MDC data is available (when on the ground) on the top half of the right MFD by simultaneously selecting A/ICE, ECS,
and FUEL on the CCP controller. Accessing MDC data is not needed during flight and is intended to be a maintenance
function.
COCKPIT VOICE RECORDER
DESCRIPTION
The cockpit voice recorder (CVR) is a crash survivable recording device that accommodates mandatory cockpit voice recordings
up to 2 hours. The CVR is mounted in the aft equipment bay.
COMPONENTS AND OPERATION
The system records the following four audio channels:
- Copilot’s audio, boom/mask and hand held microphone
- Pilot’s audio, boom/mask and hand held microphone
- Cockpit area microphone
- Observer 3rd audio, boom/mask (Optional)
These 4 channels are recorded separately for 30 minutes at high quality recording. In addition, another 2 channels that are
generated from the first four channels are recorded at standard quality for 120 minutes. The first channel is the area microphone
and the second is a summation of the pilot and copilot’s boom/mask, hand held microphone and the observer 3rd
audio (if installed). The system starts recording when power to the left main bus is applied.
The CVR control unit is located on the center pedestal and contains an indicator, headset jack, and erase and test switches.
The test switch and indicator provide the test the area microphone channel. The headset jack provides continuos monitoring
　
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