(3)  
Set up flange machining operation as shown and proceed as follows:

(a)  
Rotate -310 micrometer barrel assembly counterclockwise from bottomed out position to the "40" mark (or 10 graduations = 0.10 inch travel).

(b)  
With -107 facing cutter in place, rotate cutter by hand and advance -313 collar clamp assembly until cutter makes contact with highest point on the new bushing flange. Tighten setscrew in -313 collar clamp assembly to hold arbor firmly.

(c)  
Rotate micrometer barrel clockwise back to bottomed setting (this will give an additional 0.10 inch of clearance).

(d)  
Proceed to spotface by backing off (counterclockwise) barrel assembly until amount of material determined in step E (2) is removed.

NOTE: Make readings periodically to prevent overtravel.

(e)  
Reverse set-up to spotface opposing flange to engineering specified dimension between bushing faces.

(f)  
Finish spotface surfaces per Fig. 803.

(4)  
Fillet seal around flange outside diameter and void at end of bushing with sealant. Apply primer topcoat over sealant.

F.  Install horizontal stabilizer (Ref 27-41-11).
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27-41-131 Page 814  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Jan 20/82 

TRAILING EDGE FLAP SYSTEM - DESCRIPTION AND OPERATION
1. General
A.  The trailing edge flap system provides additional lift during takeoff and landing by increasing the camber of the wing. This is accomplished with four triple-slotted trailing edge flaps operating in conjunction with four leading edge flaps and six leading edge slats. (See figure 1.) Refer to 27-81-0, Leading Edge Flaps and Slats, for details of the leading edge devices.
B.  Each trailing edge flap is a triple-slotted structure consisting of a foreflap, a midflap and an aftflap. Each midflap is connected to two flap carriages that travel on tracks attached to the lower wing surface. The flaps are faired with the wing when retracted and are mechanically separated to form slots when extended. The slots provide increased lift by reducing stagnation of air flowing over the flap surface. With the flaps extended, the area of the flaps is greatly increased.
C.  The trailing edge flaps are actuated either hydraulically or electrically by one drive system. (See figure 1.) During normal operation, the flap drive system is hydraulically powered. During alternate flap operation, the drive system is electrically powered. Each trailing edge flap is actuated by two flap transmission assemblies. A friction brake installed in the inboard transmission assembly on each flap prevents flap retraction due to airloads. Eight transmission assemblies are connected through torque tubes and gearboxes to a flap power unit. Both the hydraulic and electric drive motors are attached to the power unit. The flap system is normally controlled by a manually operated flap lever on the pilots' control stand. The lever operates a cable system connected to a quadrant on a control valve mechanism. The control valve supplies system A hydraulic fluid to the flap hydraulic motor to drive the flap system. A flow limiting valve installed upstream of the control valve regulates the speed of the hydraulic motor by limiting fluid flow. Mechanical follow-up is incorporated in the flap system to close the control valve when the flaps reach the desired position.
D.  The flap alternate drive system may be used if the flaps cannot be operated hydraulically. Flap alternate system operation is controlled by the alternate flaps arm switch and control switch on the overhead panel. Energizing the alternate flaps arm switch supplies power to actuate a motor operated bypass valve. Actuating the valve to the bypass position interconnects the inlet ports on the flap hydraulic motor. This allows fluid to circulate within the motor, thus preventing a hydraulic lock opposing alternate flap operation. The alternate flaps control switch is used to actuate the flaps down and up electrically.
500 
Nov 15/67  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-51-0 Page 1 

G11341G11288
Trailing Edge Flap System Component Location  535 
27-51-0  Figure 1 (Sheet 1)  May 15/72 
Page 2 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

535  Trailing Edge Flap System Component Location 
May 15/72  Figure 1 (Sheet 2)  27-51-0 
Page 3 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

2.  Trailing Edge Flap
A.  Each trailing edge flap consists of a midflap, a foreflap and an aftflap. The three flap segments are mechanically separated during flap extension. Each trailing edge flap is supported by two flap carriages which travel on tracks mounted under the wing. The trailing edge flap is driven by two transmission assemblies that attach to the midflap.
　
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