500 
Jun 20/83  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-31-201 Page 503 

E.  Restore Airplane to Normal Configuration
(1)  
Return control columns to neutral position.

(2)  
Restore airplane to normal hydraulic configuration (Ref 27-31-0).

(3)  
Ensure all valve handles are positioned OPEN.

(4)  
Pivot locking bar down and secure to module. Install lower mounting bolt with head aft. Place washer under bolt head on either side of module.

(5)  
Close access door and install access panel.

(6)  
Service hydraulic reservoirs, if required (Ref Chapter 12, Hydraulic Servicing).

500 
27-31-201 Page 504  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Jun 20/83 

MANUAL ISOLATION VALVES - REMOVAL/INSTALLATION
1. General
A.  There are six manual isolation valves in the isolation valve hydraulic module. The following procedure provides instructions for removing and installing any individual valve. Isolation valve No. 2 supplies hydraulic system A power to rudder, and isolation valve No. 5 supplies hydraulic system B power to rudder.
2.  Equipment and Materials
A.  Skydrol Assembly Lube MCS 352, or Hydraulic Fluid, Fire-Resistant, BMS 3-11
3.  Prepare for Removal
A.  Remove elevator systems A and B hydraulic power. Refer to 27-31-0, Elevator and Tab Control System - Maintenance Practices.
B.  Open aft compartment access door 3701. Refer to Chapter 12, Access Doors and Panels.
4.  Remove Manual Isolation Valve
A.  Remove lower mounting bolt securing locking bar to module. Pivot locking bar upward to gain access to valve. (See figure 401.)
B.  Break lockwire and remove four mounting bolts.
C.  Remove valve from module.
D.  Plug valve chamber in module.
504 
Feb 15/73  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-31-211 Page 401 

G34976
Manual Isolation Valve Installation  500 
27-31-211Page 402   Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Aug 15/72 

5. Install Manual Isolation Valve
NOTE:  Do not interchange Ronson and Whittaker valve handles. If these valve handles are interchanged on a valve, position of handle will not correspond with position of valve and loss of hydraulic power will occur.
A. Remove elevator systems A and B hydraulic power (Ref 27-31-0).
B. Lubricate packings and valve lightly with assembly lube or hydraulic fluid (Fig. 401).
C. Install packings and backup rings on valve.
D. Remove plugs from module and install valve. Secure with four mounting bolts.
E. Provide elevator systems A and B hydraulic power (Ref 27-31-0).
F. Exercise control column or rudder pedals to bleed hydraulic lines.
G. Visually check valve for hydraulic leakage.
H. Test valve (Ref 27-31-201, Adjustment /Test).
I. Ensure all valve handles are positioned OPEN.
J. Pivot locking bar down. Install lower mounting bolt and washers.
6. Restore Airplane to Normal
A. Restore airplane to normal hydraulic configuration (Ref 27-31-0).
B. Close aft compartment access door.
C. Service hydraulic reservoirs, if required (Ref Chapter 12, Hydraulic Servicing).
501 
Feb 1/75  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-31-211 Page 403 

ELEVATOR PITOT -STATIC SYSTEM - MAINTENANCE PRACTICES
1.  General
A.  Par. 2 covers Elevator Pitot -Static System Flushing.
B.  Par. 3 covers Pitot System Drainage Inspection/Check.
C.  Par. 4 covers Static System Drainage Inspection/Check.
D.  Par. 5 covers Pitot System Drainage Plug.
E.  Par. 6 covers Pitot Probe Inspection/Check.
2.  Elevator Pitot-Static System Flushing
A.  Equipment and Materials
(1)  Dry air pressure source - 0 to 15 psi (gage) with filter and gage for measuring pressure
B.  Flush Elevator Pitot-Static System (Fig. 201)
(1)  
Disconnect pitot lines from pitot probes and feel computer.

(2)  
Remove drain plugs from pitot lines.

(3)  
Flush left pitot line with dry filtered air (not exceeding 15 psig) for 3 minutes. Flush separately from probe end, feel computer end, and drain plug end.

(4)  
Repeat step (3) for right pitot line.

(5)  
Disconnect drain lines from feel computer and flush both lines from each end with dry filtered air (not exceeding 15 psig) for 3 minutes.
　
中國航空網(wǎng) www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機(jī)維護(hù)手冊(cè) 飛行操縱 FLIGHT CONTROLS 2(128)