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1) After the initial breakout, the force required to continue wheel motion should increase
steadily and smoothly.
Verify that there is no binding or sudden increase in the force required to turn the
wheel.
2) Make sure the aileron spring cartridge extends and can move freely while you turn the
control wheel.
(e) Turn the captain’s control wheel fully counterclockwise and hold.
(f) Turn the first officer’s control wheel clockwise through neutral and beyond 10 units right
aileron, and return the control wheel to neutral.
1) After the initial breakout, the force required to continue wheel motion should increase
steadily and smoothly.
Verify that there is no binding or sudden increase in the force required to turn the
wheel.
2) Make sure the aileron spring cartridge compresses and can move freely while you turn
the control wheel.
(g) Return the captain’s control wheel to neutral.
(h) Insert a 0.0625 inch (1.6 mm) pin a minimum distance of .50 inch (12.7 mm) into the
inspection hole in the aileron input crank (Fig. 501) to verify that the crank has not moved on
the shaft and the shear rivets in the crank are not sheared.
E. Put the Airplane Back to Its Usual Condition
SUBTASK 27-11-00-860-067
(1) Remove power from hydraulic systems A and B, do this task: Hydraulic System A or B Power
Removal, TASK 29-11-00-860-805.
SUBTASK 27-11-00-860-094
(2) Do this task: Remove Electrical Power, TASK 24-22-00-860-812.
------------------------- END OF TASK ---------------------------
TASK 27-11-00-700-806
15. Aileron Spring Cartridge and Transfer Mechanism Functional Test
(Figure 501)
A. 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)
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. 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 ALL 27-11-00
Page 561
Oct 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BOEING PROPRIETARY - Copyright#Unpublished Work - See title page for details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)
SPL-1670 Mount - Control Wheel Protractor
(Part #: F72790, Supplier: 81205, A/P Effectivity: 737-100, -200, -200C,
-300, -400, -500, -600, -700, -700C, -700ER, -700QC, -800, -900, -900ER,
-BBJ)
SPL-1674 Assembly - Adapter, Control Wheel, Torque and Force Test
(Part #: F72867-1, Supplier: 81205, A/P Effectivity: 737-100, -200,
-200C, -300, -400, -500, -600, -700, -700C, -700ER, -700QC, -800, -900,
-900ER, -BBJ)
SPL-1680 Protractor - Assembly, Control Column
(Part #: 4MIT65B80307-1, Supplier: 81205, A/P Effectivity: 737-100,
-200, -200C, -300, -400, -500, -600, -700, -700C, -700ER, -700QC, -800,
-900, -900ER, -BBJ)
(Part #: A27021-29, Supplier: 81205, A/P Effectivity: 737-100, -200,
-200C, -300, -400, -500, -600, -700, -700C, -700ER, -700QC, -800, -900,
-900ER, -BBJ)
C. Location Zones
Zone Area
211 Flight Compartment - Left
212 Flight Compartment - Right
D. Prepare for the Test
SUBTASK 27-11-00-860-052
(1) Do this task: Supply Electrical Power, TASK 24-22-00-860-811.
SUBTASK 27-11-00-860-053
WARNING: MAKE SURE ALL PERSONS AND EQUIPMENT ARE CLEAR OF THE FLIGHT CONTROL
SURFACES, THE THRUST REVERSERS, AND THE LANDING GEAR. THE CONTROL
SURFACES, THE THRUST REVERSERS, AND THE LANDING GEAR CAN MOVE
SUDDENLY WITH THE PRESSURIZATION OF A HYDRAULIC SYSTEM. THIS CAN
CAUSE INJURY TO PERSONS AND DAMAGE TO EQUIPMENT.
(2) Pressurize hydraulic systems A and B, do this task: Hydraulic System A or B Pressurization,
TASK 29-11-00-860-801.
SUBTASK 27-11-00-210-002
(3) Make sure the FLT CONTROL A and B switches, on the forward overhead panel P5, are ON.
SUBTASK 27-11-00-860-054
(4) Make sure you can freely install and remove the rig pin A/S-15, from the rig pin kit, SPL-1585, in
the aileron trim actuator Figure 501.
SUBTASK 27-11-00-480-018
(5) Install the mount, SPL-1670, the control column assembly protractor, SPL-1680, and the adapter,
SPL-1674 on the captain’s control wheel.
NOTE: If the adapter, SPL-1674 is not available, apply a tangent force to the captain’s control
　
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