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BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
c) Make sure the rod end extends more than half of the distance across the inspection
hole in the stabilizer pushrod [2].
d) Tighten the checknut [24].
e) Install the lockwire, G01048.
2) Install the washer [22] and nut [23] to the bolt [21].
(d) Connect the spring [16] to the elevator feel computer assembly [1].
CAUTION: MAKE SURE YOU CONNECT THE HYDRAULIC LINES TO THE CORRECT PORTS.
IF YOU INSTALL THE HYDRAULIC LINES TO INCORRECT PORTS, YOU CAN
CAUSE DAMAGE TO THE ELEVATOR FEEL COMPUTER.
(e) Connect the hydraulic lines to the elevator feel computer assembly [1].
NOTE: See (TASK 20-10-51-400-804) for instructions on correct tubing installation.
1) Remove the caps and plugs.
2) Connect the hydraulic lines to the elevator feel computer assembly [1].
(f) Remove the caps and plugs from pitot lines, static line.
(g) Connect the pitot lines and static lines to the fittings on the elevator feel computer
assembly [1]:
(h) Connect the electrical connector [7] to the elevator feel computer assembly [1].
SUBTASK 27-31-37-080-002
(7) Remove the rig pin E-4 of the rig pin kit, SPL-1585 from the input arm [8] and elevator feel
computer assembly [1].
SUBTASK 27-31-37-860-006
(8) Do this task: Put the Elevator Systems A and B Back to the Condition Before the Pressure
Removal, TASK 27-31-00-840-802.
SUBTASK 27-31-37-870-001
(9) Bleed the elevator control system:
(a) Move the control column full forward then full aft until the movement is smooth.
NOTE: When you bleed the remaining air out of the system, the artificial feel force
increases.
SUBTASK 27-31-37-210-001
(10) Make sure that there is no hydraulic leakage from the elevator feel computer.
H. Put the Airplane Back to Its Initial Condition
SUBTASK 27-31-37-860-007
(1) Remove the safety tags and close these circuit breakers:
F/O Electrical System Panel, P6-2
Row Col Number Name
B 2 C01064 AFCS SYS B MACH TRIM DC
B 3 C01046 AFCS SYS B FCC DC
B 4 C00716 AFCS SYS B ENGAGE INTLK
B 10 C00207 FLIGHT CONTROL STAB TRIM CONT
C 1 C01037 AFCS SYS B MACH TRIM AC
C 2 C01042 AFCS SYS B SNSR EXC AC
D 10 C00840 FLIGHT CONTROL STAB TRIM ACTUATOR
737-600/700/800/900
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BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
F/O Electrical System Panel, P6-3
Row Col Number Name
D 13 C00311 INDICATOR MASTER DIM BUS 1
D 14 C00312 INDICATOR MASTER DIM BUS 2
SUBTASK 27-31-37-730-001
(2) Do this task: Feel Force System - Test, TASK 27-31-00-700-812.
SUBTASK 27-31-37-410-001
(3) 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 BALANCE PANEL - REMOVAL/INSTALLATION
1. General
A. This procedure has these tasks:
(1) A removal of an elevator balance panel
(2) An installation of an elevator balance panel.
B. The elevator balance panel is referred to as the "balance panel" in this procedure.
TASK 27-31-41-000-801
2. Elevator Balance Panel - Removal
(Figure 401, Figure 402)
A. References
Reference Title
27-31-00-800-802 Remove Pressure from the Elevator Hydraulic Systems A and B
(P/B 201)
B. 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
SPL-1585 Kit - Rigging Pins, All Systems
(Part #: F70207-109, Supplier: 81205, A/P Effectivity: 737-600, -700,
-700C, -700ER, -700QC, -800, -900, -900ER, -BBJ)
C. Location Zones
Zone Area
211 Flight Compartment - Left
212 Flight Compartment - Right
316 APU Compartment - Right
333 Left Horizontal Stabilizer - Rear Spar to Trailing Edge
343 Right Horizontal Stabilizer - Rear Spar to Trailing Edge
D. Access Panels
Number Name/Location
318BR Tailcone Access Door
333BB Horizontal Stabilizer, Access Panel, Trailing Edge
333CB Horizontal Stabilizer, Access Panel, Trailing Edge
333DB Horizontal Stabilizer, Access Panel, Trailing Edge
　
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