(2)  
Actuate alternate flap drive switch to DOWN. Hold switch in this position until FLAP DOWN limit switch actuates.

CAUTION: LEADING EDGE DEVICES WILL EXTEND.

(3)  
At number 4 and 5 jackscrews, check that dimension between the stop on the ball nut and the upstop on the jackscrew less X1 dimension previously recorded is between 29.65 and

30.18 inches (Fig. 501).

(4)  
Actuate alternate flap switch to UP. Hold switch in this position until FLAPS UP limit switch actuates.

(5)  
Check that dimension X (Detail A, Fig. 501) is 0.87 to 1.03 inch. (This is approximately equal to 1-3/4 to 2-1/4 turns between the upstop on the screw yoke and the upstop on the ball nut.) Approach this position from a flaps down position.

C.  Restore Airplane to Normal Configuration
(1)  
Position alternate flap switch to OFF.

(2)  
Position flap control lever to FLAP UP detent.

(3)  
Install Inboard Flap Track Fairings (Ref 27-51-141 R/I).

(4)  
Pressurize hydraulic system A to retract leading edge devices (Ref 27-51-0).

(5)  
Depressurize hydraulic system A (Ref 27-51-0 MP).

(6)  
Determine whether there is any further need for electrical power, if not, disconnect power.

500 
Feb 20/91  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-51-291 Page 505 

FLAP LOAD LIMITER AIRSPEED SWITCHES - REMOVAL/INSTALLATION
1. General
A.  Two flap load limiter airspeed switches are located in the lower compartment just below the flight compartment floor on the right-hand side forward of the station line common to the forward bulkhead of the nose wheel well. One switch is connected to auxiliary pitot static system No. 1 and one switch is connected to auxiliary pitot static system No. 2. The airspeed switches are preadjusted and require no further adjustment at time of installation. Either switch may be removed and installed by the following procedure.
2.  Remove Flap Load Limiter Airspeed Switch
A.  Open the FLAP LOAD LIMITER circuit breaker on the P6 panel.
B.  Disconnect the pitot and static lines from airspeed switch.
C.  Disconnect electrical connector from airspeed switch.
D.  Remove mounting bolts from switch and remove switch.
3.  Install Flap Load Limiter Airspeed Switch
A.  Position airspeed switch in mounting bracket and install mounting bolts.
B.  Connect electrical connector to switch.
C.  Connect pitot and static lines to airspeed switch.
D.  Close FLAP LOAD LIMITER circuit breaker on P6 panel.
E.  Test switch (Ref Flap Load Limiter Airspeed Switches - Adjustment/Test).
527 
May 20/82  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-51-321 Page 401 

FLAP LOAD LIMITER AIRSPEED SWITCHES - ADJUSTMENT/TEST
1.  General
A.  The flap load limiter switches are located in the lower compartment just below the flight compartment floor on the right-hand side forward of the station line common to the forward bulkhead of the nose wheel well. They do not require adjustment at installation. A test of switch actuation should be performed at installation to ensure system operation.
2.  Flap Load Limiter Airspeed Switches Test
A.  Equipment and Material
(1)  A vacuum source and barometer or equivalent capable of measuring a differential pressure of up to 1.5 inches of mercury to an accuracy of + 0.005 inches of mercury.
B.  Prepare to test airspeed switches.
CAUTION:  TO PREVENT DAMAGE TO EQUIPMENT AND INSTRUMENTS, CHECK THE FOLLOWING PRECAUTIONS BEFORE APPLYING PRESSURES TO THE PITOT STATIC SYSTEM.
(1)  
Ensure that pitot static probe heaters remain off during testing.

(2)  
Apply pitot line pressure with a suitable connection to the auxiliary pitot tubes.

CAUTION:  THE PITOT PRESSURE SHALL ALWAYS EQUAL OR EXCEED STATIC LINE PRESSURE AND THE DIFFERENCE (DIFFERENTIAL PRESSURE) SHALL NOT EXCEED 10.00 INCHES OF MERCURY.

(3)  
Apply static absolute pressure to the auxiliary static system by connecting the vacuum source to the drain fittings located in the electronics bay or to the pitot static probe ports.

CAUTION:  INSTRUMENTS WILL BE DAMAGED IF STATIC PRESSURE EXCEEDS PITOT PRESSURE EVEN MOMENTARILY. STATIC PRESSURE SHALL NOT EXCEED 8000 FEET ABOVE ACTUAL AIRPORT ALTITUDE AND APPLICATION OR RELEASE OF VACUUM SHALL BE MADE AT A RATE OF CLIMB OR DESCENT OF APPROXIMATELY 3000 FEET PER MINUTE OR LESS.

(4)  
　
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