27-09-94
 ALL  ú ú 02 Page 208 ú Nov 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 S 482-030
 (2)  
Use the rigging beam set to identify the neutral position of the outboard trailing edge flap:

 (a)  
Hold the flap rigging beam below the wing near the inboard end of the outboard flap.

 NOTE: The nylon pad must be at the aft end, and the nylon rod
____ on the forward end on the black stripe marks.
 (b)  
Move the beam forward until the scale lightly touches the flap trailing edge.

 (c)  
Align the notch on the nylon pad at the aft end with the black stripe marks.

 (d)  
Align the notch on the nylon rod on the forward end with the black stripe marks.

 (e)  
Apply a 30 pound force (up direction) on the aft flap near the rigging tool.

 (f)  
Read the scale on the rigging beam to find the position of the flap trailing edge.

 (g)  
Apply a 30 pound force on the aftflap near the outboard end.

 (h)  
Measure between the fixed rib at the outboard end of the flap and the flap trailing edge to find the neutral position.

 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-09-94
 ALL  ú ú 01 Page 209 ú Nov 15/97
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 AILERON AND AILERON TRIM CONTROL SYSTEM -
_________________________________________ DESCRIPTION AND OPERATION
_________________________
 1.  General_______
 A.  The aileron and aileron trim control system provides airplane lateral control. The ailerons are assisted by the flight spoilers (Ref 27-61-00). There is one aileron and balance tab on each wing. Rotation of either aileron control wheel results in movement of the ailerons and movement of the flight spoilers. The ailerons are powered by two independent hydraulic power control units connected to separate hydraulic systems. Either power unit is capable of providing full power control response to aileron control system inputs. In the event of total hydraulic failure, lateral control is maintained manually. Manual control forces are minimized by aileron balance tabs and hinged balance panels. The balance tabs are mechanically connected by rods to the wing structure.
 B.  The aileron control system is actuated by rotation of either the captain's or first officer's aileron control wheel. The control wheels rotate the control wheel drum and aileron control bus drums (Fig. 1). Aileron control bus cables (ACBA and ACBB) between the aileron control bus drums provide an interconnect between the captain's and the first officer's aileron control wheels. Aileron control cables (AA and AB) from the captain's control wheel drum attach to an aileron control quadrant; which through a shaft, drives two cranks and two input rods. Each input rod connects to a power control unit. A cam is mounted on the control quadrant shaft to engage with a spring-loaded roller for the purpose of centering and trim. Each aileron power control unit is connected to a crank on a bus drum to which aileron bus system cables are fastened. The aileron bus system cables (ABSA and ABSB) lead to left and right aileron wing quadrants. The ailerons are actuated through a control rod by the aileron wing quadrants. During manual operation, the ailerons are manually operated by pilot effort. The forces are transmitted from the control wheel through the power unit input linkage stops. This establishes a direct mechanical link from the control wheel to effect aileron displacement.
 C.  Hydraulic power is furnished to the aileron control system by two functionally independent 3000 psi systems. Hydraulic power from both systems is controlled by the flight control shutoff valves in the flight control hydraulic modular packages (AMM 27-00-00/001, Flight Controls). The modular packages are located in the left and right main wheel wells where the absence of wheel well doors assures quick and convenient access. Two FLT CONTROLS shutoff valve switches together with two low pressure warning lights are located on the overhead panel.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

 27-11-00
　
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