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(Part #: F72928-58, Supplier: 81205, A/P Effectivity: 737-600, -700,
-700C, -700ER, -700QC, -800, -900, -900ER, -BBJ)
C. Location Zones
Zone Area
311 Area Aft of Pressure Bulkhead - Left
312 Area Aft of Pressure Bulkhead - Right
323 Vertical Fin - Front Spar To Rear Spar
D. Access Panels
Number Name/Location
311BL Stabilizer Trim Access Door
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
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E. Procedure
SUBTASK 27-31-00-010-019
(1) Open this access panel:
Number Name/Location
311BL Stabilizer Trim Access Door
SUBTASK 27-31-00-390-001
(2) Seal the drain hole in each pitot probe on the vertical fin.
SUBTASK 27-31-00-020-004
(3) Remove the drain plugs from the pitot lines.
SUBTASK 27-31-00-480-007
(4) Connect the pressure gage lines from the regulator, SPL-1742 to the drain holes of the pitot
lines.
SUBTASK 27-31-00-480-008
CAUTION: MAKE SURE THAT THE PITOT PROBE HAS NO ADDED WEIGHT ON IT FROM THE
TEST HOSE. THE PROBE CAN BEND OR TWIST OUT OF TOLERANCE.
(5) Connect the pressure lines from the regulator, SPL-1742 to the two pitot probes on the vertical
fin.
SUBTASK 27-31-00-790-001
(6) Do a pitot system leak test:
CAUTION: DO NOT INCREASE THE PRESSURE TO MORE THAN 6 PSIG (474 KNOTS KCAS)
DURING THE TEST. IF THE PRESSURE IS MORE THAN 6 PSIG, (41.4 KPA) IT CAN
CAUSE DAMAGE TO THE ELEVATOR FEEL COMPUTER.
(a) Operate the regulator, SPL-1742, to apply pressure between 4.9 and 5.1 psig (33.8 and 35.2
kPa).
(b) Set the shutoff valve in the regulator, SPL-1742 to the OFF position.
(c) Make sure that the pressure does not decrease more than 0.3 psig (2.1 kPa) (12 knots
KCAS) during a 2-minute time.
(d) Operate the regulator, SPL-1742, to decrease the pressure to zero.
SUBTASK 27-31-00-160-001
(7) Remove the seals from the drain holes in each pitot probe.
SUBTASK 27-31-00-080-007
(8) Remove the pressure gage lines from the regulator, SPL-1742 to the drain holes.
SUBTASK 27-31-00-080-008
(9) Remove the pressure lines from the regulator, SPL-1742 to the pitot probes.
SUBTASK 27-31-00-430-002
(10) Install the drain plugs on the pitot lines.
SUBTASK 27-31-00-410-018
(11) Close this access panel:
Number Name/Location
311BL Stabilizer Trim Access Door
------------------------- END OF TASK ---------------------------
737-600/700/800/900
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Elevator Pitot-Static System
Figure 515 (Sheet 1 of 2)/27-31-00-990-814
737-600/700/800/900
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Elevator Pitot-Static System
Figure 515 (Sheet 2 of 2)/27-31-00-990-814
737-600/700/800/900
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TASK 27-31-00-700-812
23. Feel Force System - Test
(Figure 502, Figure 515, Figure 523)
A. General
(1) Use this test to make sure the elevator feel computer operates correctly. The elevator feel
computer changes the control column forces as the airspeed changes.
B. References
Reference Title
22-11-00-820-802 Elevator Rigging Test (P/B 501)
27-31-00-700-801 Null Procedure - Mach Trim Actuator (P/B 201)
27-31-00-800-801 Elevator Hydraulic System A and B - Pressurization (P/B 201)
27-31-00-840-801 Put the Elevator Hydraulic systems A and B Back to the Condition
Before the Pressurization (P/B 201)
C. Tools/Equipment
NOTE: When more than one tool part number is listed under the same "Reference" number, the
tools shown are alternates to each other within the same airplane series. Tool part numbers
that are replaced or non-procurable are preceded by "Opt:", which stands for Optional.
Reference Description
COM-1557 Gauge - Force
(Part #: DG-200, Supplier: 92456, A/P Effectivity: 737-ALL)
(Part #: DPP-500G, Supplier: 92456, A/P Effectivity: 737-ALL)
(Part #: DPPH-150, Supplier: 92456, A/P Effectivity: 737-ALL)
(Part #: DPPH-50, Supplier: 92456, A/P Effectivity: 737-ALL)
(Part #: FDIX 100, Supplier: 0BFD9, A/P Effectivity: 737-ALL)
　
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