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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 S 865-364
 WARNING:_______YOU MUST OPEN THE FLAP LOAD RELIEF CIRCUIT BREAKER. YOU CAN CAUSE INJURY TO PERSONS.
 (2)  Open the FLAP LOAD RELIEF circuit breaker on the load control panel P6.
 S 865-365
 CAUTION: YOU MUST OPEN THE DIGITAL STALL WARNING COMPUTER (DSWC) CIRCUIT
_______ BREAKERS. YOU CAN CAUSE THE DSWC TO FAIL THE SELF-TEST UNTIL IT IS SET AGAIN.
 (3)  Open the STALL WARNING NO. 1 and NO. 2 circuit breakers on load control panels P6 and P18.
 S 495-403
 WARNING: FAILURE TO REMOVE VINYL ADHESIVE TAPE FROM STATIC PORTS BEFORE
_______ FLIGHT MAY CAUSE LARGE ERRORS IN AIRSPEED SENSING AND ALTITUDE SENSING SIGNALS, WHICH MAY LEAD TO LOSS OF SAFE FLIGHT.
 WARNING:_______MAKE SURE THAT THE PROBE HEAT IS NOT ON. YOU CAN CAUSE INJURY TO PERSONS.
 CAUTION:_______DO NOT EXTEND THE SEALS INTO THE STATIC PORTS. YOU CAN CAUSE DAMAGE TO THE SURFACE IN THE AREA WHEN YOU REMOVE THE SEALS.
 (4)  
Seal the forward static ports (S1) in the upper left pitot-static probe with vinyl adhesive tape.

 S 845-185

 (5)  
Seal the forward static ports (S1) in the lower right pitot-static probe with vinyl adhesive tape.

 S 845-186

 (6)  
Use these steps to connect the pneumatic test set to the captain's static system drain fitting:

 (a)  Connect the static (vacuum) source in the pneumatic test unit through the static control valve to the static cutoff valve.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH EFIS ú

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 (b)  Connect the captain's static system drain fitting to the static cutoff valve through the static system test gage and flow restrictor.
 NOTE: The captain's static system drain fitting is found on
____ the left forward end of the nose wheel well.
 (c)  Open the static cutoff valve.
 D. The Captain's Static System (Low-Range) Leak Test
 S 865-187
 CAUTION: MAKE SURE THAT THE PITOT LINE PRESSURE IS EQUIVALENT OR MORE
_______ THAN THE STATIC LINE PRESSURE. KEEP THE STATIC PRESSURE CHANGE BELOW 5000 FEET FOR EACH MINUTE. MAKE SURE THAT THE DIFFERENTIAL PRESSURE STAYS BETWEEN 0 AND 10.00 INCHES OF MERCURY. YOU CAN CAUSE DAMAGE TO THE PITOT-STATIC SYSTEM.
 (1)  Apply a vacuum to the captain's static system equal to 5,000 feet of altitude above field elevation (ambient pressure minus
 5.25 |0.25 in. Hg).
 S 865-189
 CAUTION: HOLD THE VACUUM, AS AN ALTERNATIVE, BEHIND THE CUTOFF VALVES
_______ DURING THE CUTOFF TIME. YOU CAN CAUSE DAMAGE TO THE EQUIPMENT WHEN YOU OPEN THE CUTOFF VALVES WITHOUT THE VACUUM.
 (2)  
Close the static cutoff valve to system when the necessary altitude is reached.

 (3)  
Stop for 5 to 6 minutes to allow the system to stabilize.

 (4)  
Write the altitude.

 S 865-191
 S 865-192
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH EFIS ú

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
 S 865-193
 (5)  
Stop for one minute and read the altitude again.

 S 865-194

 (6)
Make sure that the altitude does not decrease by more than 80 feet

 (0.07 in. Hg).
 S 865-195
 CAUTION: MAKE SURE THAT THE PITOT LINE PRESSURE IS EQUIVALENT OR MORE
_______ THAN THE STATIC LINE PRESSURE. KEEP THE STATIC PRESSURE CHANGE BELOW 5000 FEET FOR EACH MINUTE. MAKE SURE THAT THE DIFFERENTIAL PRESSURE STAYS BETWEEN 0 AND 10.00 INCHES OF MERCURY. YOU CAN CAUSE DAMAGE TO THE PITOT-STATIC SYSTEM.
 (7)  Open the static cutoff valve and send the captain's static system to ambient pressure.
 E. Put the Airplane Back to Its Usual Condition
　
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