527 
Feb 20/89  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-51-321 Page 501 

C.  Test airspeed switches.
(1)  
Actuate and hold flap load limiter test switch on equipment bay light panel in electronics compartment to SWITCH TEST position. Check that green LOAD LIMITER TEST LIGHT comes on.

NOTE: Apply pitot pressure to one system at a time.

(2)  
Pressurize pitot static system until differential pressure is between 1.121 inches Hg (152 knots) and 1.274 inches Hg (162 knots). Check that green LOAD LIMITER TEST LIGHT goes off.

(3)  
Decrease differential pressure until pressure is between 1.046 inches Hg (147 knots) and

1.197 inches Hg (157 knots). Check that green LOAD LIMITER TEST LIGHT comes on. Release test switch.

(4)  
Test remaining airspeed switch per steps (1) thru (3).

D.  Return airplane to normal.
(1)  
Depressurize pitot static system.

(2)  
Remove static port covers, checking that ports are free of foreign matter.

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FLAP-40-UNIT SWITCHES - REMOVAL/INSTALLATION
1. General
A.  The flap-40-unit switches are installed within the control stand and are operated by a cam on the drum of the flap handle assembly. Access to the switches is gained by removing the right stabilizer trim wheel and door from the control stand. (See figure 401.)
2.  Prepare to Remove Switches
A.  Open FLAP LOAD LIMITER circuit breaker on circuit breaker panel P6.
B.  Remove retaining nut from center hub of right stabilizer trim wheel and remove wheel from control stand.
NOTE: Do not remove splined shaft.
C.  Remove mounting screws from right door.
D.  Rotate door upwards to gain access to wires attached to lightplate and disconnect wires. Remove door.
NOTE: Replace nuts and washers on lightplate studs.
3.  Remove Flap-40-Unit Switches
A.  Remove mounting nuts and washers from switches.
B.  Pull switches from mounting screws and remove wires.
4.  Install Flap-40-Unit Switches
A.  Connect wires to switches.
B.  Install switches on mounting screws.
NOTE: Check that actuator is installed on switches.
C.  Install washers and nuts on mounting screws.
527 
Aug 15/71  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-51-331 Page 401 

G27380
Flap 40 Unit Switches Installation  530 
27-51-331  Figure 401  May 15/70 
Page 402 
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

D.  Adjust and test switches. Refer to Flap 40-Unit Switches - Adjustment/Test.
5.  Restore Airplane to Normal
A.  Install wires on lightplate studs.
B.  Install door on control stand with mounting screws.
C.  Position stabilizer trim wheel on shaft with handle 90 (+ 15) degrees from left trim wheel handle and install retaining nut.
D.  Close FLAP LOAD LIMITER circuit breaker on circuit breaker panel P6.
530 
May 15/70  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-51-331 Page 403 

FLAP 40-UNIT SWITCHES - ADJUSTMENT/TEST
1.  Flap 40-Unit Switches Adjustment
A.  Equipment and Materials
(1)  Ohmmeter
B.  Prepare to adjust flap 40-unit switches. (See figure 501.)
(1)  
Remove retaining nut from center hub of right stabilizer trim wheel and remove wheel from control stand.

NOTE:  Do not remove splined shaft.

(2)  
Remove mounting screws from right door.

(3)  
Rotate door upwards to gain access to wires attached to lightplate and disconnect wires. Remove door.

NOTE:  Replace nuts and washers on lightplate studs.
C.  Adjust flap 40-unit switches.
(1)  
Position flap control lever to 30-unit detent, and check that switch is not actuated.

(2)  
Position flap control lever 5 (+ 2) degrees aft of the 30-unit detent and check that switch is actuated.

NOTE:  Switch actuation can be ascertained by clicking sound or by checking continuity across switch terminals C and NO with an ohmmeter.
D.  If switch is not actuated, remove lockwire on cam, loosen bolts and adjust cam for actuation on aft surface of cam. Tighten bolts and lockwire.
　
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