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* TCAS system status.
The sensor status maintenance word has this data:
* WXR fault
* ILS fault
* RA fault
* DME fault
* VOR fault
* Air data fault
* Inertial reference data fault
* A/T fault
* FMC fault
* FCC fault.
The modes discrete word 1 has this data:
* L-WXR data fault
* R-WXR data fault
* L-ILS data fault
* R-ILS data fault
* LOB DU fault
* ROB DU fault
* L-MCDU fault
* R-MCDU fault
* L-SMYD fault
* R-SMYD fault
* DEU fault
* RIB DU fault
* LIB DU fault
* L-EFIS CP fault
* R-EFIS CP fault
* CU DU fault
* CL DU fault.
The DEUs compare critical input signals that are received by
both DEUs on the same ARINC 429 input bus. The onside values
are compared with the offside values. If the critical comparison
data is not the same, CDS shows CDS FAULT on the CDS
displays.
This is the critical comparison data:
* Engine fan speed (N1)
* Engine core speed (N2)
* Engine exhaust gas temperature (EGT)
* FMC bus 08 data
* FMC bus 09 data.
NOTE: This comparison test is done when the SSM of the data
is normal or test. The test is not done if the SSM is
invalid or NCD.
CDS - CROSS CHANNEL INTERFACES
EFFECTIVITY
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CDS - CROSS CHANNEL INTERFACES
CDS - CROSS CHANNEL INTERFACES
EFFECTIVITY
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CDS - CROSS CHANNEL INTERFACES
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737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
General
The display electronic units (DEU) receive ARINC 429 digital
data and analog discretes from various airplane systems. The
DEUs use this data to make the displays for the display units
(DU).
The DEUs also send data to other airplane systems. Each DEU
sends ARINC 429 data and analog discretes. These are the
ARINC 429 output buses:
* CDS general purpose bus
* Control panel feedthru buses (2)
* Data loader bus
* DEU - FMC bus
* Engine EEC buses (2)
* ACARS datalink bus
* EEC/APU bus.
CDS General Purpose (GP) Bus
The DEUs send data on the GP bus to these airplane systems:
* Flight control computer (FCC) A and B
* Stall management yaw damper (SMYD) 1 and 2
* Flight data acquisition unit (FDAU).
The GP bus also sends data to the CDS test connector in the E4
rack in the EE compartment. This is used for functional test.
The GP bus has this general data:
* Stabilizer position
* Control column position
* Control wheel position
* Rudder pedal position
* Left and right elevator position
* Left and right aileron position
* Speed brake handle position
* Rudder position
* Main engine indication data
* Main engine internal data
* Main landing gear brake temperatures
* Main hydraulic system pressures
* Main hydraulic system quantities
* Pitch attitude
* Roll attitude
* Heading data
* Groundspeed
* Radio altitude
* Radio minimums data
* Minimum decision altitude data
* Localizer and glideslope deviation
* Main fuel tank quantities
* Aux. fuel quantity
* Main engine EEC status words
* DEU status words 1 and 2
* CDS EFIS CP modes 1 and 2 discrete words
* Display discrete words 1 and 2
* Captain EFIS CP discrete word 1 and 2
* F/Os EFIS CP discrete word 1 and 2
* CDS discrete words
* CDS DEU discrete word 3.
CDS - EXTERNAL INTERFACE INTRODUCTION
EFFECTIVITY
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The main engine EEC status words have this general data:
* EEC data
* Manufacturer and option data
* Thrust rating/airplane model data
* Exceedance data
* Internal protection status
* TRA data
* Thrust reverser status data
* Engine air systems status data
* ADIRU input data status.
The DEU status word 1 has this data:
* Thrust reverser position data
　
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