CABLE SYSTEM  NO. OF SEALS  LOCATION  ACCESS PANEL NO. 
LH ELEVATOR CABLES  2  AFT PRESSURE BULKHEAD  3701 
RH ELEVATOR CABLES  2  AFT PRESSURE BULKHEAD  3701 
RUDDER CABLES  2  AFT PRESSURE BULKHEAD  3701 
RUDDER TRIM CABLES  2  AFT PRESSURE BULKHEAD  3701 
STABILIZER TRIM CABLES  2  AFT PRESSURE BULKHEAD  3701 
SPEED BRAKE CABLES  2  LH WHEEL WELL CEILING  WHEEL WELL 

G02965
500  Installation and Location of Flight Control Cable Air pressure Seals 
May 15/68  Figure 201  27-09-121 
Page 201 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

FLIGHT CONTROL CABLE GUARD - REMOVAL/INSTALLATION
1.  Remove Control Cable Guard (Fig. 401)
A.  Attach DO-NOT-OPERATE tags to the control columns.
B.  Get access to the aft cable guards.
(1) Remove the aft bulkhead lining in the rear/aft cargo area (Ref AMM 25-52-131).
C.  Remove the aft cable guards.
(1)  Loosen the clamps and remove the cable guards.
2.  Install Control Cable Guard (Fig. 401)
A.  Lubricate the cables in the cable guard area (Ref 12-26-00 SRV).
B.  Install the aft cable guards:
(1)  
Put the guard assembly (1) in its position.

(2)  
Install the washers on the sleeve of the guard assemblies (1).

(a)  Connect each set of washers with a screw and a nut.

(3)  
Put the guard assemblies (2) into the sleeve of the guard assembly (1).

(a)  
Install the three bolts on the guard assembly (2) into the slots on the sleeve of the guard assembly (1).

(b)  
Tighten the nut until the bolt does not turn easily.

(4)  
Put the clamp on the end of the guard assembly (2) between the two rivets.

(a)  
Tighten the clamp.

(b)  
Install grommets in holes if you removed it.

(5)  
Put each of the guard assemblies (1 and 2) into position with the slot on each assembly inboard.

(a)  Tighten the clamps to hold the guard assemblies.

(6)  
On some airplanes, install the guard assembly (3) with the slot on the assembly inboard.

(a)  
Tighten the clamps to hold the guard assemblies.

(b)  
Make sure that the minimum clearance between the cable guard and adjacent water and hydraulic tubing is 0.10 inch. Adjust tubing as necessary.

C.  Install the rear/aft bulkhead lining in the aft cargo area (Ref AMM 25-52-131).
D.  Remove the DO-NOT-OPERATE tags from the control columns.
E.  Do a test of the cables to make sure there is free movement (Ref 27-31-0 A/T).
505 
Feb 01/96  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-09-122 Page 401 

Control Cable Guard Installation  500 
27-09-122 Page 402  Figure 401 (Sheet 1) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 01/95 

500  Control Cable Guard Installation 
Oct 20/91  Figure 401 (Sheet 2) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-09-122 Page 403 

Control Cable Guard Installation  501 
27-09-122 Page 404  Figure 401 (Sheet 3) BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Oct 20/91 

FLIGHT CONTROLS HYDRAULIC MODULAR PACKAGE - DESCRIPTION AND OPERATION
1.  General
A.  The two flight controls hydraulic modular packages are manifold assemblies that contain the components which control hydraulic power for the aileron, rudder, elevator and spoiler control systems. Also low pressure for the aileron, rudder and elevator control systems is indicated through the modular units. The packages are identical and are located on the forward bulkhead of each main gear wheel well. (See figure 1.) System A flight control modular package is in the left wheel well and system B in the right wheel well. Each modular package is a seven port housing with drilled passageways and cavities for attached check valve, compensator cartridge , low pressure warning switch and two shutoff valves.
B.  Hydraulic fluid entering the package is routed to the two shutoff valves. When the spoiler valve is in the ON position, fluid is ported out of the modular package to the spoiler control system. When the flight controls valve is in the ON position, fluid is ported to the low pressure warning switch and then out of the package to the aileron, rudder and elevator control systems. Hydraulic return from the spoiler control system does not enter the modular package, but is returned directly to the hydraulic system return. Hydraulic return from the aileron, rudder and elevator control systems enters the modular package and is ported through the compensator cartridge and then through the check valve. From this point, fluid is ported out of the modular package to hydraulic system return. With the shutoff valves OFF, the hydraulic pressure is stopped and the shutoff valve cavity is connected to return allowing pressure in the control systems to equalize with return pressure. The aileron, rudder and elevator return pressure is maintained for gust damping after hydraulic system shutdown by the compensator cartridge. The check valve is incorporated in the modular unit return port to the hydraulic system to prevent reverse flow when hydraulic power is off.
　
中國航空網 m.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：737 AMM 飛機維護手冊 飛行操縱 FLIGHT CONTROLS 1(21)