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A.  On panel P6, open circuit breakers for IND LIGHTS.
B.  If low pressure warning switch in left wheel well is being removed, remove system A hydraulic power. If low pressure warning switch in right wheel well is being removed, remove system B hydraulic power. Check that hydraulic reservoirs are depressurized (Ref 27-51-0 MP).
C.  Disconnect electrical connector from low pressure warning switch. (Fig. 401).
D.  Break lockwire and screw low pressure warning switch from modular package.
CAUTION: BE PREPARED TO CATCH SPILLED HYDRAULIC FLUID.
E.  Take necessary precautions to prevent dirt entering warning switch cavity when switch is removed.
3.  Install Low Pressure Warning Switch
A.  Lightly lubricate O-rings and backup rings with hydraulic fluid or assembly lube. Install O-ring and backup rings on replacement low pressure warning switch.
B.  Screw low pressure warning switch into modular package and tighten within 50 to 200 pound-inches torque range (Fig. 401).
C.  Lockwire low pressure warning switch to shutoff valve motor mounting bolt.
D.  Install electrical connector at low pressure warning switch.
E.  On panel P6, close circuit breaker for IND LIGHTS.
F.  Test low pressure warning switch. Refer to Low Pressure Warning Switch - A/T.
500 
Feb 15/73  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-09-241 Page 401 

G02997
Low Pressure Warning Switch Installation  500 
27-09-241  Figure 401  May 15/67 
Page 402 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

LOW PRESSURE WARNING SWITCH - ADJUSTMENT/TEST
1. Test Low Pressure Warning Switch
A.  Connect electrical power to airplane.
B.  Ensure that flight control switches are ON.
C.  Turn on hydraulic system B pump No. 1 or 2 to pressurize hydraulic system B.
D.  If low pressure warning switch in left wheel well is being tested, open hydraulic interconnect valve to pressurize hydraulic system A.
E.  Actuate aileron control wheel, rudder pedals, and control column to bleed hydraulic system.
F.  Check for hydraulic leakage at modular package.
G.  Check that LOW PRESSURE light is not illuminated.
NOTE:  System A low pressure light is controlled by the low pressure warning switch on the modular package in the left wheel well. System B low pressure light is controlled by the low pressure warning switch on the modular package in the right wheel well.
H.  Turn off hydraulic system B pumps No. 1 and 2 and close hydraulic interconnect valve.
I.  Check that LOW PRESS light is illuminated. Also check that master warning and caution lights and flight controls warning light illuminate.
J.  Determine whether there is any further need for electrical power on the airplane; if not, disconnect electrical power.
K.  Check hydraulic reservoirs and service, if required.
Aug 15/67 27-09-241 Page 501 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

FLIGHT CONTROLS TRIM CORRECTION - TROUBLE SHOOTING
1.  General
A.  Usually component failure which may cause an inflight lateral trim requirement change is readily detectable. Four items, however, may have significant effect on lateral trim requirements but are not necessarily detectable or repeatable during ground inspection. These items may occur intermittently and require as much as a 20-degree control wheel trim change.
(1)  
Unsequenced outboard foreflap

(2)  
Asymmetric inboard aftflap extension or retraction

(3)  
Leading edge outboard slats skewed

(4)  
Fractured carriage spindle

B.  In the following paragraphs these items are analyzed. Also see Flight Controls Trim Correction -Trouble Shooting for isolation and remedy of specific trim/control problem situations.
C.  The delivered condition for aileron and rudder trim limits during cruise at normal power and descent at idle power is as follows:
Aileron Rudder Trim Trim Airspeed Condition
Flaps up 3/4 unit 1/2 unit Cruise Cruise Flaps up 3/4 unit 1/2 unit 250 descent Flaps up 1 unit 1/2 unit 190 descent Flaps 15 1 unit 1/2 unit 150 descent Flaps 40 1 unit 1/2 unit 130 descent
NOTE:  The values listed in the above table are the aileron and rudder trim limits for a new airplane. Flaps should be allowed to reach the selected position before measuring trim. Measured at the aileron trim knob, a tolerance of ±3/4 aileron trim unit with flaps up or a tolerance of ±1.0 aileron trim unit for other settings from neutral position is permitted without adjustment of aileron and aileron trim control system. The trim requirement must not exceed 1.0 unit difference between any two adjacent flap settings.
　
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