S 845-234

 (6)  
Close the FLAP LOAD RELIEF circuit breaker on the load control panel P6.

 S 865-378

 (7)  
Remove electrical power if it is not necessary (AMM 24-22-00/201).

 TASK 34-11-01-795-236
 9.  The Auxiliary No. 1 Static System Low-Range Leak Test_____________________________________________________
 A. Standard Tools and Equipment
 (1)  
Air data test set, Castleberry AT700-2, Castleberry Instr & Avionics, Austin, TX; or equivalent

 (2)  
Flow restrictors, control valves, cutoff valves, and vinyl adhesive tape as required

 B. References
 (1)  
24-22-00/201, Manual Control

 (2)  
34-11-11/601, Pitot-Static Probe

 C. Prepare for the Test
 S 865-379
 (1)  Supply electrical power (AMM 24-22-00/201).
 S 865-380
 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 495-407
 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.
 (3)  Seal the aft static ports (S2) in the lower right pitot-static probe with vinyl adhesive tape.
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737-300/400/500MAINTENANCE MANUAL
 S 495-382
 (4)  
Seal the aft static ports (S2) in the upper left pitot-static probe with vinyl adhesive tape.

 S 485-383

 (5)  
Use these steps to connect the pneumatic test set to the auxiliary No. 1 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.

 (b)  
Connect the auxiliary No. 1 static system quick-disconnect drain fitting to the static cutoff valve through the static system test gage and flow restrictor.

 NOTE: The auxiliary No. 1 static system drain fitting is found
____ on the left forward end of the nose wheel well.
 (c)  Open the static cutoff valve.
 D. The Auxiliary No. 1 Static System (Low-Range) Leak Test
 S 865-245
 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 auxiliary No. 1 static system equal to 5,000 feet of altitude above field elevation (ambient pressure minus
 5.25 |0.25 in. Hg).
 S 865-247
 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 the system when the necessary altitude is reached.
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITH EFIS ú

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737-300/400/500MAINTENANCE MANUAL
 S 865-249
 (3)  
Stop for 5 to 6 minutes to allow the system to stabilize.
 S 865-250

 (4)  
Write the altitude.
 S 865-251
　
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