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C.  Lockwire (Mone1) - MS20995NC40
3.  Prepare to Remove Hydraulic Brake Control Cables
A.  Check that gear ground lock assembly is installed in nose gear (Ref 32-00-01).
B.  Chock wheels and release parking brake.
C.  Open forward access door 1103 just forward of nose wheel well to gain access to cables, turnbuckles, and pulleys.
D.  Unlock and remove passenger seats to clear floor covering area to gain access to brake metering valve control quadrant assemblies (Ref Chapter 25, Passenger Seats).
NOTE: Seats and floor covering are above forward half of main wheel well.
E.  Remove carpet as necessary (Ref Chapter 25, Passenger Cabin Floor Covering).
F.  Remove the right and left outboard floor panels, as necessary, to gain access to brake metering valve control quadrant assemblies.
4.  Remove Hydraulic Brake Control Cables
A.  Remove lockwires and separate each pair of turnbuckles (l, Fig. 401) on cable systems LGBA, LGBA' and LGBB, LGBB' respectively and remove locking clip (2) from each turnbuckle. Discard locking clips.
B.  Loosen turnbuckles of each system.
C.  Disconnect cables of cable systems LGBA, LGBA' and LGBB, LGBB' at right and left horizontal quadrants respectively.
D.  Disconnect cables of cable systems LGBA, LGBA' and LGBB, LGBB' at right and left brake metering valve quadrants respectively and remove cables.
May 20/82 32-41-81 Page 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

Brake Control Cables Installation  500 
32-41-81 Page 402  Figure 401 (Sheet 1) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Apr 01/97 

502  Brake Control Cables Installation 
Apr 01/97  Figure 401 (Sheet 2) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  32-41-81 Page 403 

5.  Install Hydraulic Brake Control Cables
A.  String replacement cables E. F, G, and H through fairleads and connect to their respective brake metering valve control quadrant (3). (See detail B, figure 401.)
B.  String replacement cables A, B, C, and D through their respective fairleads and pulleys and connect to their respective horizontal quadrant.
C.  Connect all cables at turnbuckles (l). (See detail A, figure 401.)
D.  Adjust cables per 32-41-0, Hydraulic Brake System - Adjustment/Test.
E.  Lockwire turnbuckles of cable systems LGBA, LGBA' and LGBB, LGBB' together with lockwire. (See detail A, figure 401.)
F.  Test brake system. Refer to 32-41-0, Hydraulic Brake System - Adjustment/Test.
6.  Restore Airplane to Normal Configuration
A.  Close forward access door 1103.
B.  Install the right and left outboard floor panels from station 664 thru station 695.
C.  Install carpet. Refer to Passenger Cabin Floor Covering, Chapter 25.
D.  Install passenger seats. Refer to Passenger Seats, Chapter 25.
E.  Set parking brake.
500 
32-41-81 Page 404  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Aug 15/67 

ANTISKID SYSTEM - DESCRIPTION AND OPERATION
1. General
A.  In the antiskid mode of operation, the antiskid system prevents wheels skidding by limiting the hydraulic pressure applied to the brakes by the hydraulic brake system, 32-41-0. Maximum braking efficiency is obtained when all wheels are in a slight skid or at a maximum rate of deceleration short of a skidding wheel. The system electronically controls an antiskid control valve to continuously vary braking pressure in response to wheel action. The system controls wheels individually. Each wheel rate of deceleration is compared with a preset rate of deceleration. Wheel decelerations within the airplane deceleration capability produce no correction signal. Wheel decelerations above this rate are treated as skids or approaching skids and correction signals are sent to the antiskid control valve to reduce applied brake pressure. The correction signal is reduced when the wheel returns to speed again. The system continuously seeks a level of correction signal which produces skidding of slight severity and thereby attains maximum braking efficiency. Maximum braking is obtained under any variety of runway conditions.
B.  Automatic braking is controlled by an autobrake circuit card located in the antiskid control unit. It operates independently of the antiskid system to apply the brakes without input from the brake pedals on the flight deck. The autobrake circuit card compares actual airplane velocity as computed from the wheel speed transducer signals with a reference deceleration velocity which is programmed into the circuit card. The difference between the actual and reference velocity produces an error voltage which is transmitted to an autobrake valve. This valve modulates hydraulic pressure to all four brakes in response to the voltage. Fluid from the autobrake valve is ported through the antiskid valves before reaching the brakes. In this way the antiskid system will override automatic braking at all times to provide skid and locked wheel protection.
　
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