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E.  The aileron bus system cables (ABSA and ABSB), are routed along the rear spar of each wing and connect each of the aileron wing quadrants to the bus drum. The bus system cables are provided with a cable slack take-up device in each wing. This device consists of a spring attached to the axis of the outboard turnaround pulley.
F.  The base of the first officer's control column is equipped with a transfer mechanism. The transfer mechanism allows normal control wheel motion to be transmitted through the cables on the captain's control column only. If a malfunction occurs which jams the aileron control system, lateral control is achieved by the spoiler system operated directly by cables from the first officer's control column. When this occurs, the first officer will have to exert a maximum force of 117 pounds, to overcome the spring in the transfer mechanism and operate the spoilers.
G.  Aileron trim is provided by turning an aileron trim control knob on the pilots' control stand. The aileron trim wheel, through cables, adjusts the position of a centering spring and trim mechanism, providing aileron trim. Aileron trim control cables (ATA and ATB) are routed under the cabin floor on the left side of the airplane. The cables connect a control drum on the aileron trim control unit to a drum at the aileron centering spring and trim mechanism. Trim system stops are located within the trim control knob mechanism.
2.  Aileron
A.  Each aileron is a frame structure consisting mainly of leading and trailing edge spars and ribs, all fabricated from aluminum alloy. A clad aluminum skin is flush-riveted to this structure. On some airplanes, the ailerons are of graphite/epoxy construction with upper and lower skins of graphite/epoxy tape and nomex honeycomb core. An aileron balance tab is attached to the rear spar of the aileron by four hinge bearings. Outboard of the balance tab, the aileron trailing edge is of honeycomb construction. The aileron is provided with four hinge bearings attached to the front spar. Access panels are provided for each hinge bearing. Individual bearings may be replaced without removing the aileron. The aluminum nose of the aileron extends forward between the hinge bearings and is connected to one balance panel in bay No. 3.
B.  The aileron control rod attaches the aileron to the aileron wing quadrant. Dual pushrods that connect the balance tab to the wing structure pass through the aileron.
500 
27-11-0 Page 4  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Jun 20/85 

G03082
500  Lateral Control System – Schematic 
May 01/99  Figure 2  27-11-0 
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

C.  The aileron and balance tab are independently balanced. The aileron is statically balanced as a component. The balance tab is statically balanced by adding or installing weights to the balance panel. The number of weights required is subject to the weight of the balance tab.
D.  In No. 1, 2, and 4 bays, the aileron nose extension does not have a balance panel, but has a polyamide nylon seal mounted upon the nose extension coming into contact with a seal baffle. These seals along with a similar seal on the balance panel, control the airflow around the front of the aileron. A clearance between the aileron nose and the wing structure provide the controlled airflow area necessary for balance panel operation.
3.  Aileron Balance Tab
A.  The aileron balance tab functions to reduce the force required to position the aileron. Motion of the tab is controlled by dual tab pushrods which provide attachment between tab and wing structure (Fig. 7). Balance tab travel is opposite to aileron travel, that is, a downward movement of the aileron produces an upward movement of the balance tab.
B.  The aileron balance tab is a thin tapered light weight control surface with an aluminum spar, fiberglass honeycomb core, fiberglass skin, and an aluminum alloy nose. On some airplanes, the aileron balance tab is of graphite/epoxy construction with a nomex honeycomb core. It is attached to the aileron rear spar by four hinge bearings. Left and right balance tabs are identical except for mounting of the mast fitting and related fairing.
C.  The aileron balance tab may be replaced without rebalancing the aileron. Each tab is furnished with adjust weights that bolt to the balance panel. The required number of adjust weights is stamped on a data plate attached to each balance tab.
4.  Aileron Balance Panels and Seals
A.  Aileron balance panels reduce the force required to position the ailerons in flight. Each aileron has one balance panel located at number 3 bay. The balance panel is connected to the aileron nose by a continuous hinge at the aft edge. The forward edge of each balance panel is attached to the wing structure by an idler hinge which provides the necessary articulation for movement of the balance panel (Fig. 3). The seals at the hinge points are made of dacron fabric impregnated with silicone rubber. Mylar seals are installed along the inboard and outboard edges of the balance panel.
　
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