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SWS - SMYD - FUNCTIONAL DESCRIPTION
EFFECTIVITY
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737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
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SWS - SMYD - FUNCTIONAL DESCRIPTION
SWS - SMYD - FUNCTIONAL DESCRIPTION
EFFECTIVITY
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737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
27-32-00-510
Purpose
The control column shakers shake the control columns to alert
the pilots of a stall condition.
Location
The control column shakers attach to the control columns.
Physical Description
Each control column shaker has a 28v dc motor and an
unbalanced ring. There is one electrical connector on each unit.
Functional Description
The motor drives an unbalanced ring. The ring shakes the
control column.
SWS - CONTROL COLUMN SHAKER
EFFECTIVITY
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SWS - CONTROL COLUMN SHAKER
SWS - CONTROL COLUMN SHAKER
EFFECTIVITY
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737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
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Purpose
The test switches of stall warning test panel do a test of the stall
warning system.
Location
The stall warning test panel is on the P5 aft overhead panel.
Physical Description
The stall warning test panel has two push button switches.
Functional Description
Each test switch lets you do a test of the stall warning system.
When you push switch 1, you do a test of stall warning system 1
with operation of the control column shaker on the captain
control column. When you push switch 2, you do a test of stall
warning system 2 with operation of the control column shaker
on the first officer control column.
If there are no faults, the control column shaker operates. If
there are faults, the control column shaker does not operate.
When you push the test switch, the stall warning system does a
test of these:
* SWS software
* SWS hardware
* Test switches (electrical short)
* Air data bus valid (ADIRU)
* IR Bus valid (ADIRU)
* DEU data (TAI)
* AOA synchros
* Flap position transmitters
* LE Asymmetry
* LE UCM
* N1 and N2 status
* Program pins.
During the test, the control column shaker operates until you
release the test switch, or a maximum of 20 seconds. The 20
second maximum time limit prevents damage to the control
column shaker motor. The stall warning test is inhibited when
the airplane is in the air.
SWS - STALL WARNING TEST PANEL
EFFECTIVITY
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SWS - STALL WARNING TEST PANEL
SWS - STALL WARNING TEST PANEL
EFFECTIVITY
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SWS - STALL WARNING TEST PANEL
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737-600/700/800/900 AIRCRAFT MAINTENANCE MANUAL
Purpose
The elevator feel shift module (EFSM) supplies increased
system A pressure to the dual feel actuator to increase control
column feel forces during a stall.
Location
The elevator feel shift module is on the left side of the stabilizer
compartment aft bulkhead in the 48 section. Open the section 48
access and blow out door to get access.
Physical Description
The elevator feel shift module has these components:
* Housing
* Dual coil solenoid valve
* Pressure reducer
* Pressure operated mode valve
* Relief valve
* Restrictor
* Internal filter.
The dual coil solenoid valve is a line replaceable unit (LRU) and
is spring biased to the normal position.
The pressure reducer is a slide and sleeve assembly that is
spring biased to the supply pressure position.
The mode valve is a slide assembly that is spring biased to the
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