2)  Stop spinning transducer drive coupling. Ensure left outboard brake releases momentarily and then applies.

(e)  
Test left inboard transducer. 1) Manually spin left inboard transducer drive coupling. Check that right inboard brake releases.

2)  Stop spinning transducer drive coupling. Check that left inboard brake releases momentarily and then applies.

(f)  
Test right inboard transducer. 1) Manually spin right inboard transducer drive coupling. Check that left inboard brake releases.

2)  Stop spinning transducer drive coupling. Check that right inboard brake releases momentarily and then applies.

(g)  
Test right outboard transducer. 1) Manually spin right outboard transducer drive coupling. Check that left outboard brake releases.

2)  Stop spinning transducer drive coupling. Check that right outboard brake releases momentarily and then applies.

(h)  
Release parking brake and connect electrical connector D928 to shutoff valve. Check that inboard and outboard ANTISKID INOP lights go off.

(i) 
 Install hubcaps.

(8)  
Test Landing Gear Lever Up Switch

(a) 
 Set parking brake.

(b)  
Check that gear ground lock assemblies are installed (Ref 32-00-01).

WARNING:  CHECK THAT GROUND LOCK ASSEMBLIES ARE INSTALLED IN ALL LANDING GEAR TO PREVENT INADVERTENT OPERATION OF GEAR. INJURY TO PERSONNEL AND/OR EQUIPMENT COULD RESULT IF GEAR RETRACTS.

(c)  
Place landing gear lever in UP position.

(d)  
Press AIR SENSING TEST and GRD SENSING TEST switches on landing gear electrical module. 1) Check that ANTISKID INOP lights on pilot's panel do not come on. 2) Check that brakes do not release.

(e)  
Release AIR SENSING TEST and GRD SENSING TEST switches.

(f)  
Place landing gear lever in DN position.

(g)  
Release parking brake.

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32-42-0  Jun 20/87
Page 508
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

D.  Restore Airplane to Normal
(1)  
Determine if there is further need for electrical power on airplane; if not, shut down source.

(2)  
Close ground interconnect valve circuit breaker on P6 panel.

(3)  
Determine if there is further need for hydraulic power on airplane; if not, remove systems A and B hydraulic power (Ref 29-11-0 and 29-12-0).

(4)  
Verify ground interconnect valve circuit breaker on P6 panel is closed.

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ANTISKID SYSTEM - INSPECTION/CHECK
1.  Antiskid System Inspection
A.  General
(1)  Visual inspection of skid control system wiring and components should be accomplished as a part of routine periodic inspection of the aircraft brake hydraulic and electrical systems.

B.  Prepare for Examination
(1)  
Examine control box assembly.

(a)  
Check for security of installation in electronic equipment rack.

(b)  
Check front panel indicator lenses, switches, and test receptacle dust cover for tightness.

(2) 
 Examine electrical wiring.

(a)  
Check tightness of electrical connectors and receptacles at control box, each valve unit, and each wheel transducer.

(b)  
Check wires and cables for damage or deterioration to insulation, shielding, or conductors, and for proper routing and clamping.

CAUTION:  CHECK WIRING HARNESS IN AREA PASSING UNDER AXLE FOR DAMAGE OR PREVIOUS REPAIR. IF WIRES HAVE BEEN DAMAGED OR SPLICED, REPLACE HARNESS.
NOTE:  If fitting at main gear axle is loose, replace fitting or add up to two split washers between fitting and axle by removing elbow fitting, loosening connecting fitting, removing expandable fitting from axle, slipping split washer(s) over antiskid wiring, and reinstalling fittings. If more than two washers are required to tighten fitting, replace harness or install new fittings.
(3)  
Examine control valve units.

(a)  
Check for security of attachment hardware and lockwiring.
　
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