S 424-018

 (5)  
Connect the electrical connector to the autopilot stabilizer trim servo.

 S 424-019

 (6)  
Connect the electrical connector to the stabilizer trim electric actuator.

 S 714-008

 (7)  
Do a test of the actuator operation (AMM 49-51-21/501).

 S 414-009

 (8)  
Close the access door for the horizontal stabilizer compartment.

 S 864-023

 (9)  
Remove the DO-NOT-CLOSE tag and close the circuit breaker:

 (a)  E3-3 Electrical Shelf, APU Control Unit
 S 864-021
 (10) Remove the stabilizer trim lock assembly from the stabilizer trim wheel.
 (a)  
Remove the safety pin and the pin through the yoke.

 (b)  
Remove the stabilizer trim lock.

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 ALL  ú ú 01 Page 407 ú Nov 15/97
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
////////////////////////A / GTCP85-129 SERIES /737-300/400/500/ ENGINES/MAINTENANCE MANUAL ////////////////////////
S 864-022
 (11) Set the circuit breakers and the switch:
 (a)  
Remove the DO-NOT-CLOSE tags and close these circuit breakers on the P18 Circuit Breaker Panel. 1) AUTOPILOT STABILIZER TRIM SERVO 2) AUTO FLT CONT SYS A WARN LIGHT BAT 3) AUTO FLT CONT SYS A ENGAGE INTLK A 4) AUTO FLT CONT SYS A FCC DC 5) AUTO FLT CONT SYS A SNSR EXC AC 6) AIRPLANES WITH MECHANICAL AILERON FORCE LIMITER;

 AFDS AIL FORCE LIM
 7) AFDS MCP DC
 8) AUTO FLT CONT SYS A MACH TRIM DC
 9) AUTO FLT CONT SYS A MACH TRIM AC

 (b)  
Remove the DO-NOT-CLOSE tags and close these circuit breakers on the P6 Circuit Breaker Panel: 1) AUTO FLT CONT SYS B WARN LIGHT BAT 2) AUTO FLT CONT SYS B ENGAGE INTLK B 3) AUTO FLT CONT SYS B FCC DC 4) AUTO FLT CONT SYS B SNSR EXC AC 5) AFDS MCP CRS-2 6) AUTO FLT CONT SYS B MACH TRIM DC 7) AUTO FLT CONT SYS B MACH TRIM AC 8) STABILIZER TRIM CONT 9) STABILIZER TRIM ACTUATOR

 (c)  
Remove the DO-NOT-OPERATE tag from the APU master switch on the P5 forward overhead panel.

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 ALL  ú ú 01 Page 408 ú Nov 12/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
APU BLEED AIR SYSTEM - DESCRIPTION AND OPERATION
________________________________________________
 1.  General
_______
 A.  The bleed air system for the APU supplies the compressed air for the air conditioning system, engine start system, and other pneumatic components of the airplane. The bleed air system also decreases compressor surge when the airplane is in flight and there in no bleed load. The bleed air system has these components:
 (1)  
the bleed air valve

 (2)  
the bleed air duct

 (3)  
AIRPLANES WITHOUT THE ETC;
 the APU control thermostat

 (4)  
AIRPLANES WITH THE ETC;
 the proportional control valve

 (5)  
the differential pressure regulator

 (6)  
the surge bleed valve.

 2.  Bleed Air Valve
_______________
 A.  The bleed air valve controls the bleed airflow from the APU turbine plenum to the airplane pneumatic ducts. The bleed air valve is installed on the bleed air duct at the front of the APU compartment. The bleed air valve has a main valve, actuator, rate control valve, and switcher valve. A housing contains the main valve. The main valve is a butterfly valve that is usually in the closed position. The housing for the main valve has a port for a control air connection that is upstream of the butterfly valve. The actuator has a spring-loaded diaphragm and a linkage that closes the switcher valve. The switcher valve is a two-ball selector valve that is operated by a solenoid. The switcher valve controls the airflow to the two sides of the actuator diaphragm. One ball of the switcher valve is a check valve for the control air pressure. The other ball is the check valve for the switcher. The rate control valve controls a poppet-valve that is contained in the housing.
　
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