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Config 1
Page 519
Jun 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
1) Make sure the rod ends cover at least 50 percent of the inspection holes at two end of
the rods (10 locations).
(i) Remove the rig pin R-1, R-2, R-3, R-4, and R-5.
(j) Operate the rudder pedals through one full travel cycle.
1) Make sure the control cables RA and RB are at the correct tension as given in
(Table 501).
(k) Install the locking clips on the turnbuckles.
H. Put the Airplane Back To Its Usual Condition
SUBTASK 27-21-00-010-024-001
(1) Close these access panels:
Number Name/Location
113AW Forward Nose Wheel Well Panel
113BW Forward Nose Wheel Well Panel
114AW Forward Nose Wheel Well Panel
114BW Forward Nose Wheel Well Panel
324AL Vertical Fin, Aft Fin Access Door
SUBTASK 27-21-00-010-025-001
(2) Close these access doors:
Number Name/Location
112A Forward Access Door
311BL Stabilizer Trim Access Door
324CL Vertical Fin, Access
SUBTASK 27-21-00-860-078-001
(3) Do this task: Put the Rudder Systems A, B, and Standby Back to the Condition Before the
Pressure Removal, TASK 27-21-00-840-802.
------------------------- END OF TASK ---------------------------
TASK 27-21-00-820-809-001
5. Control Rod for Main Rudder Power Control Unit Adjustment
(Figure 502)
A. General
(1) Use this task to adjust the control rod for the main rudder power control unit (PCU).
B. References
Reference Title
24-22-00-860-811 Supply Electrical Power (P/B 201)
24-22-00-860-812 Remove Electrical Power (P/B 201)
27-21-00-800-801 Rudder Hydraulic System A, B, or Standby Pressurization (P/B 201)
27-21-00-840-801 Put the Rudder Hydraulic systems A, B, and Standby 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.
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN 001-005, 155-157, 201-999 PRE SB 737-27-1253 27-21-00
Config 1
Page 520
Jun 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
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)
D. Location Zones
Zone Area
211 Flight Compartment - Left
212 Flight Compartment - Right
324 Vertical Fin - Rear Spar To Trailing Edge
E. Access Panels
Number Name/Location
324CL Vertical Fin, Access
324DL Trailing Edge Access
F. Prepare for the Adjustment
SUBTASK 27-21-00-860-079-001
(1) Do this task: Supply Electrical Power, TASK 24-22-00-860-811.
SUBTASK 27-21-00-010-026-001
(2) To get access to the main PCU, do this step:
Open this access panel:
Number Name/Location
324DL Trailing Edge Access
SUBTASK 27-21-00-010-027-001
(3) to get access to the rudder feel and centering unit, do this step:
Open this access panel:
Number Name/Location
324CL Vertical Fin, Access
SUBTASK 27-21-00-860-080-001
WARNING: MAKE SURE THAT PERSONS AND EQUIPMENT ARE CLEAR OF ALL CONTROL
SURFACES BEFORE YOU SUPPLY HYDRAULIC POWER. AILERONS, RUDDER,
ELEVATORS, FLAPS, SPOILERS, LANDING GEAR, AND THRUST REVERSERS CAN
MOVE QUICKLY WHEN YOU SUPPLY HYDRAULIC POWER. THIS CAN CAUSE INJURY
TO PERSONS AND DAMAGE TO EQUIPMENT.
(4) Pressurize the rudder hydraulic system B, do this task: Rudder Hydraulic System A, B, or
Standby Pressurization, TASK 27-21-00-800-801.
SUBTASK 27-21-00-860-081-001
(5) Make sure the rudder trim indicator is in the neutral position.
SUBTASK 27-21-00-480-019-001
(6) Install the rig pin R-5 from the rig pin kit, SPL-1585 in the rudder feel and centering unit.
(a) Make sure you can install the rig pin R-5 freely with no movement of the rudder feel and
centering unit output crank.
737-600/700/800/900
AIRCRAFT MAINTENANCE MANUAL
EFFECTIVITY
GUN 001-005, 155-157, 201-999 PRE SB 737-27-1253 27-21-00
Config 1
Page 521
Jun 10/2007
D633A101-GUN
BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details
G. Control Rod for the Main PCU Adjustment
SUBTASK 27-21-00-710-072-001
(1) Adjust the control rod [36] of the main PCU:
(a) If the rudder trailing edge is greater than 0.50 in. (12.7 mm) from the neutral position, then
　
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