Landing Gear Electrical Module  525 
32-09-100  Figure 1  Feb 15/73 
Page 2 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

LANDING GEAR ELECTRICAL MODULE - REMOVAL/INSTALLATION
1.  General
A.  To remove the landing gear electrical module, make sure that power is removed from airplane; then release latch and remove unit from rack. When installing landing gear electrical module, make sure that pins are straight in component and rack; insert component in rack and secure latch.
B.  Whenever the landing gear module is replaced, perform landing gear electrical module adjustment/test.
500 
May 15/68  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  32-09-100 Page 401 

LANDING GEAR ELECTRICAL MODULE - ADJUSTMENT/TEST

1.  Landing Gear Electrical Module Test
A.  General
NOTE:  This test may be performed with the airplane on jacks, providing the ground mode is simulated when required.
(1)  
This test is performed only to test the function of those system circuits which are electrically connected to the module when the landing gear electrical module has been replaced. This test is not conclusive unless the individual systems have been tested and found to be operating satisfactorily except where the system test and/or trouble shooting indicates that the module be replaced. If any component (such as switches, valves, or sensors) of the individual system has been altered or replaced, the individual system must be tested before this test can be performed.

(2)  
It is preferred that the complete landing gear electrical module test be performed whenever the module has been replaced. However, at least the following portions of the test must always be performed to ensure system integrity and airplane safety after module replacement.

(a)  
Landing gear position indicating and warning function

(b)  
Aural warning function

(c) 
 Anti-skid function

(d)  
Automatic speed brake function

(e) 
 Stall warning function

(f)  
APU fire horn function

(g)  
Standby electrical power system function

(3)  
For all tests which require positioning of thrust levers, the thrust lever position is given in degrees from idle stop. If it is desirable to use linear dimensions (arc length at control stand cover top) for positioning thrust levers, refer to Chapter 76, Engine Control Cables -Maintenance Practices, for conversion data.

B.  Equipment and Materials
(1)  
Ground Lock Assemblies (Ref 32-00-01)

(2)  
Airplane Control Surfaces Protractor - F52485-500

(3)  
Hydraulic ground cart

(4)  
Deleted

(5)  
Actuator: 1020 steel per Mil-S-7952 17-4PH steel per AMS 5643 15-5PH steel Permalloy – HYMU (carpenter steel) Molly Permalloy (Allegheny Ludlum) Size: 0.05 inch thick, large enough to completely cover sensor face (also  called a slug in the procedure)

510 
Oct 20/93  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  32-09-100 Page 501 

(6)  Deactuator: 5062, 6061, 7075, or 2024 aluminum copper Size: 0.05 inch thick, large enough to completely cover sensor face (also called a copper shield in the procedure)
(7)  Antiskid/Auto Brake Tester - F80129-100
C.  Prepare for Test
(1)  
Check that electrical power is connected.

(2)  
Check that external hydraulic pressure supply is connected but do not pressurize hydraulic systems A and B until instructed.

(3)  
Check that landing gear is down and locked with ground lock assemblies installed (Ref 32-00-01).

(4)  
Check that thrust levers are in IDLE position.

(5)  
Place protractor in position on thrust lever(s) and set protractor to 0 degree.

D.  Test Landing Gear Electrical Module
(1)  
Test landing gear position indicating and warning function of landing gear electrical module.

(a)  
Check that LANDING GEAR - LIGHTS, LANDING GEAR - ANTISKID TEST, ANTISKID FAILURE WARNING AND PARKING BRAKE circuit breakers, and all circuit breakers under INDICATOR LIGHTS MASTER DIMMING BUS located on P6 panel are closed.

(b)  
With landing gear lever in DN position and both throttle levers retarded to a position less than 7 degrees above idle stop, check that landing gear green indicator lights are on and red warning lights are off.
　
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