(6)  
Position center stanchion (4) outboard hinge within 0.06 inch of the middle and lower segment hinge centerline.

(7)  
Rotate lower stanchion (3) against bumper and hold.

(8)  
Drill eight 0.199 ±0.003/-0.000-inch holes in handrail per predrilled holes in handrails. Install BACB30LA6-2 lockbolts (detail B).

(9)  
Adjust and connect upper tie rod (8) so upper outboard stanchion contacts rub pad on hub of upper segment crank.

(10)
Adjust and connect tie rod (1) to maintain center stanchion (4) outboard hinge within 0.06 inch of lower ladder segment hinge centerline with a 2- to 5-pound preload on lower bumper by lower stanchion (3).

F.  Close aft airstair circuit breaker on P6 panel.
G.  Operate airstairs slowly and check handrails for smooth operation with no binding.
500 
Aug 1/74  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  52-14-141 Page 405 

EMERGENCY EXITS - DESCRIPTION AND OPERATION
1. General
A.  An emergency exit hatch is located on each side of the fuselage over the wing area for use in emergency exit from the passenger cabin. The two hatches are of the plug-type and are identical in size and operation. Each emergency exit hatch can be opened from inside or outside the airplane by a spring-loaded manually operated handle that is located above the window near the top of the hatch. The emergency exit hatches are covered in 52-21-0.
B.  The emergency evacuation of passengers from the passenger cabin can be facilitated through the use of door-mounted evacuation slides. For information on the evacuation slide installations, refer to Chapter 25, Emergency Equipment.
C.  The control cabin right sliding window can be operated from outside the airplane as an emergency exit. A spring-loaded release handle located outside and below the sliding window permits an operator to unlock and slide the window first inwards and then aft to its fully opened position. The sliding window emergency release mechanism is covered in Control Cabin Sliding Windows, Chapter 56.
D.  An emergency exit feature is provided in the control cabin door, which permits the release and removal of the two upper blowout panels from the door. The emergency exit is used if an obstruction on the aft side of the door prevents the control cabin door from opening and thus prevents communication with the passenger cabin. For further information, refer to Control Cabin Door - Description and Operation, 52-51-0.
500 
May 15/70  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  52-20-0 Page 1 

EMERGENCY EXIT HATCH - DESCRIPTION AND OPERATION
1.  General
A.  Two emergency exit hatches are provided to facilitate emergency exit from the passenger cabin. These individual hatches are located one on each side of the fuselage over the wing area. Each emergency exit hatch can be opened from inside or outside the airplane by a spring-loaded manually-operated handle located near the top of the hatch. A detachable light above the hatch illuminates the area for exit hatch operation. For additional information on this light, refer to LIGHTS, Chapter 33.
B.  Each hatch (Fig. 1) is supported in the hatch opening by a lower pivot fitting which is engaged with a lower pivot hook on the sill of the hatch opening. (See detail C, figure 1.) Two heel pads attached to the lower edge of the hatch on each side of the lower pivot fitting bear against the sill of the hatch opening. The hatch may be opened from inside or outside of the airplane by means of a manually-operated handle, located at the top of the hatch. The handle is an integral casting formed with a pull-type lever on the inside surface, and a push-type panel flush with the outside contour of the hatch. A continuous seal is attached around the entire edge of the handle frame. The lower end of the handle on the inside of the hatch is pinned to a torque tube. Two torsion springs, one on each side of the handle, are at one end attached to the outside of the torque tube, and at the other end bear against a wear plate on the handle frame. Each end of the torque tube is attached to separate bell crank assemblies. Each bell crank assembly rotates in a spherical bearing, which is supported in a bearing housing. One bearing housing is attached to the forward frame of the hatch, and the other to the aft frame. Two latch rollers, one on each bell crank, engage with the latch fittings attached to the forward and aft frames of the hatch opening. When the passenger cabin is pressurized, adjustable stop pins attached to the forward and aft edge of the hatch, contact stop fittings attached to the forward and aft frames of the hatch opening. The stops transmit the pressurization loads on the hatch to the fuselage structure surrounding the hatch, and prevent excessive deflection of the continuous seal attached around the entire edge of the hatch. A window is located below the hatch operating handle.
　
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