(3)  
Close all landing gear circuit breakers on P6 panel.

(4)  
Ensure wheel chocks are in place.

(5)  
Release parking brake.

(6)  
Set inboard and outboard antiskid switches on pilot's panel to OFF position. Ensure ANTISKID INOP lights are on.

(7)  
Set both inboard and outboard antiskid switches to ON position. Ensure ANTISKID INOP lights go off.

(8)  
Set parking brake. Ensure ANTISKID INOP lights go off.

NOTE:  The ANTISKID INOP lights may come on momentarily when parking valve opens or closes.

(9)  
Release parking brake. Ensure ANTISKID INOP lights remain off.

(10)
Pull inboard antiskid circuit breaker. Ensure inboard ANTISKID INOP light comes on. 

(11)
Push inboard antiskid circuit breaker in. Ensure inboard ANTISKID INOP light goes off.

(12)
Pull outboard antiskid circuit breaker. Ensure outboard ANTISKID INOP light comes on.

(13)
Push outboard antiskid circuit breaker in. Ensure outboard ANTISKID INOP light goes off.

(14)
Test Wheel Speed Transducers

(a)  
Remove hubcaps from wheels to be tested and rotate transducer drive coupling to check for excessive bearing free play and drive shaft is not bent.

(b)  
Ensure parking brake is released and disconnect electrical connector D928 from parking brake shutoff valve. Ensure inboard and outboard ANTISKID INOP lights on pilot's panel come on..

(c)  
Set parking brake.

(d)  
Test the left outboard transducer. 

NOTE:  The ANTISKID INOP lights may come on momentarily when parking brake valve opens or closes.
531 
32-42-11 Page 402  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  May 01/76 

531  Antiskid Transducer Installation 
May 15/71  Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  32-42-11 Page 403 

1)  Turn the left outboard transducer drive coupling to approximately 500-1000 RPM.
NOTE:  The transducer spin-up equipment tool can be used to rapidly turn the transducer.
2) Make sure the right outboard brake releases.
3) Stop the movement of the transducer as quickly as possible.
4) Make sure the left outboard brake releases momentarily and then applies again

in 5 to 10 seconds.
(e)  Test left inboard transducer. 1) Turn the left inboard transducer drive coupling to approximately 500-1000 RPM.
NOTE:  The transducer spin-up equipment tool can be used to rapidly turn the transducer.
2)  Make sure the right inboard brake releases.
531 
32-42-11 Page 404  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Apr 01/97 

3) Stop the movement of the transducer as quickly as possible. 
4) Make sure the left inboard brake releases momentarily and then applies again in
5 to 10 seconds. 
(f)  Test the right inboard transducer. 
1)  Turn the right inboard transducer drive coupling to approximately 500-1000 RPM.
NOTE:  The transducer spin-up equipment tool can be used to rapidly turn the transducer.
2) Make sure the left inboard brake releases.
3) Stop the movement of the transducer as quickly as possible.
4) Make sure the right inboard brake releases momentarily and then applies again

in 5 to 10 seconds.
(g)  Test the right outboard transducer. 
1)  Turn the right outboard transducer drive coupling to approximately 500-1000 RPM.
NOTE:  The transducer spin-up equipment tool can be used to rapidly turn the transducer.
2) Make sure the left outboard brake releases.
3) Stop the movement of the transducer as quickly as possible.
4) Make sure the right outboard brake releases momentarily and then applies

again in 5 to 10 seconds.
(h)  Release parking brake and connect electrical connector D928 to shutoff valve. Ensure inboard and outboard ANTISKID INOP lights go off.
G.  Position hubcap on wheel verifying drive coupling engages spider.
H.  Attach hubcap to wheel with three sets of bolts and washers. Install lockwire.
I.  If wheel is on outboard side, install hubcap fairing.
J.  Set parking brake.
K.  Determine if there is further need for electrical power on airplane; if not, shut down source.
L.  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).
531 
Apr 01/97  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  32-42-11 Page 405 
　
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