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EFFECTIVITY
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737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
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General
The proximity switch electronics unit (PSEU) continuously
monitors system 1 and system 2 for internal and external faults.
Functional Description
Power from the PSEU PRI and PSEU ALTN circuit breakers go
to system 1 and system 2. Either system monitors for faults
using 28v dc power or 28v dc HOT BAT power sources. These
are the internal type fault types:
* Software/hardware faults
* Intersystem communication
* Power supply A/B faults
* Sensor drive 1/2
These are the External type faults:
* Proximity sensor wiring
* LE flaps external wiring faults
* External input configuration faults
* External input monitoring faults.
Thrust lever position is sensed from the autothrottle switch
packs. A ground is provided for the PSEU when the autothrottle
switch packs are less than 53 degrees.
Landing gear on ground (target near) inputs are sensed from
the six air/ground sensors.
No Dispatch Fault
If the PSEU senses a non-dispatchable fault, the amber PSEU
light on the P5 panel comes on 30 seconds after landing and
both thrust levers are less than 53 degrees. A signal is also sent
to the master caution card in the Flight Recorder and Mach
Airspeed Warning module for a PSEU fault.
The PSEU fault light goes off when the fault is corrected.
Dispatch Fault
If the PSEU senses a dispatchable fault, the amber PSEU light
on the P5 panel comes on 30 seconds after landing, both thrust
levers are less than 53 degrees, and either amber MASTER
CAUTION annunciator light is pushed.
When you push the MASTER CAUTION annunciator light a latch
relay in the annunciator is set. This controls 28v dc master
caution power to the K2 PSEU FAULT RELAY in the Flight
Recorder and Mach Airspeed Warning module. When the K2
relay is energized, the circuit is closed to control the amber
PSEU light.
A signal is also sent to the master caution card in the Flight
Recorder and Mach Airspeed Warning module for a PSEU fault.
The amber PSEU fault light goes off when the fault is corrected
or either amber MASTER CAUTION light is pushed again to
reset the latch relay.
AIR/GROUND SYSTEM - FUNCTIONAL DESCRIPTION - PSEU FAULT LIGHT LOGIC
EFFECTIVITY
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AIR/GROUND SYSTEM - FUNCTIONAL DESCRIPTION - PSEU FAULT LIGHT LOGIC
AIR/GROUND SYSTEM - FUNCTIONAL DESCRIPTION - PSEU FAULT LIGHT LOGIC
EFFECTIVITY
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AIR/GROUND SYSTEM - FUNCTIONAL DESCRIPTION - PSEU FAULT LIGHT LOGIC
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BOEING PROPRIETARY - Copyright#- Unpublished Work - See title page for details.
737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
Purpose
The air/ground system supplies air/ground data to airplane
systems.
Functional Description
Inputs from the system 1 sensors go to system 1 in the proximity
switch electronics unit (PSEU), and inputs from system 2
sensors go to system 2 in the PSEU. Both systems within the
PSEU share information through a common bus.
Two landing gear compressed sensors on each landing gear
send air/ground position to the PSEU. The PSEU processes the
signals from the compressed sensors, operates the air/ground
relays, and sends these outputs to airplane systems:
* Ground mode
* Air mode
* Left gear on ground mode (system 1 only)
* Right gear on ground mode (system 2 only)
* Nose gear on ground mode
* Parking brake set on ground (system 1 only).
System 1 sends ground mode signals to the system 1 air/
ground relays and airplane systems when targets move near
any two or more of the system 1 and system 2 MLG compressed
sensors.
System 1 sends air mode signals to the system 1 air/ground
relays and airplane systems when targets move far from any
three of the system 1 and system 2 MLG compressed sensors.
System 1 sends nose gear on ground mode signals to airplane
systems when targets move near any two or more MLG
compressed sensors and one or both NLG compressed
　
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