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D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
Flight Control Switches
Figure 506/27-81-00-990-809
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
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D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
TASK 27-81-00-730-801
9. Leading Edge Cruise Depressurization Test
A. References
Reference Title
24-22-00-860-811 Supply Electrical Power (P/B 201)
29-11-00-860-801 Hydraulic System A or B Pressurization (P/B 201)
29-11-00-860-805 Hydraulic System A or B Power Removal (P/B 201)
B. Location Zones
Zone Area
117 Electrical and Electronics Compartment - Left
211 Flight Compartment - Left
212 Flight Compartment - Right
C. Access Panels
Number Name/Location
117A Electronic Equipment Access Door
D. Prepare for the Test
SUBTASK 27-81-00-010-003
(1) Open this access panel:
Number Name/Location
117A Electronic Equipment Access Door
SUBTASK 27-81-00-860-048
(2) Do this task: Supply Electrical Power, TASK 24-22-00-860-811.
SUBTASK 27-81-00-860-049
WARNING: MAKE SURE ALL PERSONS AND EQUIPMENT ARE CLEAR OF THE FLIGHT CONTROL
SURFACES, THE THRUST REVERSERS, AND THE LANDING GEAR. THESE
COMPONENTS CAN MOVE SUDDENLY WHEN YOU SUPPLY HYDRAULIC POWER.
THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
(3) To pressurize the hydraulic system B, do this task: Hydraulic System A or B Pressurization,
TASK 29-11-00-860-801.
E. Leading Edge Cruise Depressurization Test
SUBTASK 27-81-00-860-083
WARNING: MAKE SURE PERSONS AND EQUIPMENT ARE CLEAR OF THE LEADING EDGE FLAPS
AND SLATS AND THE TRAILING EDGE FLAPS. THE FLAPS AND SLATS WILL MOVE
DURING THIS TEST. THIS CAN CAUSE INJURY TO PERSONS AND DAMAGE TO
EQUIPMENT.
(1) Move the flap control lever to the 1-unit position to extend the leading edge flaps and slats and
the trailing edge flaps.
SUBTASK 27-81-00-740-004
(2) Do this test of the leading edge cruise depressurization valve:
(a) Move the ALTERNATE FLAPS ARM switch on the P5-3 panel to the ARM position.
(b) Use the FSEU to operate the leading edge cruise depressurization valve:
737-600/700/800/900
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BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
1) Push the ON/OFF button on the front panel of the FSEU to turn on the display.
NOTE: The display will show EXISTING FAULTS?.
2) Push the down arrow until OTHER FUNCTNS? shows on the display.
3) Push the YES button to select OTHER FUNCTNS? on the FSEU.
4) Push the YES button to select SET OUTPUTS? from the OTHER FUNCTNS? menu.
5) Push the YES button to select LE DEPR VALVE? from the menu.
6) Push the YES button to select SET ON? on the display.
(c) Make sure the leading edge flaps and slats do not move.
(d) Wait until the FSEU display shows LE DEPR VALVE?.
NOTE: This will take approximately 75 seconds.
(e) Move the flap control lever to the UP position.
(f) Make sure the leading edge flaps and slats and the trailing edge flaps do not move to the
retracted position.
(g) Push the YES button on the FSEU to display SET ON?.
(h) Push the YES button to select SET ON? on the display.
(i) Make sure the leading edge flaps and slats retract and that the trailing edge flaps stay
extended.
NOTE: The LE FLAPS TRANSIT lights will stay on.
(j) Wait until the FSEU display shows LE DEPR VALVE?.
NOTE: This will take approximately 75 seconds.
(k) Make sure the leading edge flaps and slats move to the extend position.
(l) Move the ALTERNATE FLAPS ARM switch to the OFF position.
(m) Make sure the leading edge flaps and slats, and the trailing edge flaps move to the
retracted position.
F. Put the Airplane Back to Its Usual Condition.
SUBTASK 27-81-00-860-084
(1) Push the ON/OFF button on the front panel of the FSEU to turn the display off.
SUBTASK 27-81-00-860-085
(2) Move the flap control lever to the UP position to retract the flaps and slats.
SUBTASK 27-81-00-410-003
(3) Close this access panel:
Number Name/Location
117A Electronic Equipment Access Door
SUBTASK 27-81-00-860-051
(4) To remove pressure from hydraulic system B, do this task: Hydraulic System A or B Power
Removal, TASK 29-11-00-860-805.
------------------------- END OF TASK ---------------------------
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Feb 10/2006
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