(k)  
Do not change the static source selector valve while vacuum is on the static system.

 (l)  
Make sure the selector valve stays in the NORMAL position unless the procedure tells you to change it.

 (m)  
Make sure the autopilot system stays off during the test.

 CAUTION: MAKE SURE THE ELECTRICAL POWER IS NOT APPLIED TO THE
_______ PITOT- STATIC HEATERS. THIS CAN CAUSE DAMAGE TO THE PITOT- STATIC PROBES.
 (n)  
Make sure the pitot-static probe heaters stay off during the test.

 (o)  
Connect the captain's, F/O's, auxiliary, and alternate static systems together during this test.

 NOTE: The source connections must be made at the static probe
____ of the pitot-static probe. The alternate static ports must be sealed off at the skin. Removal of the seals must be complete, with no deposits or roughness in or about the static ports.
 (p)  
Apply static pressure to all systems at the same time.

 (q)  
Connect the captain's, F/O's, and auxiliary pitot tubes together during the test.

 NOTE: The pressure connections of the pitot line must be made
____
 at the pitot-static probes.

 Drain fittings from the Pitot-static system can be used for the pitot and static pressure connections.
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A
737-300/400/500MAINTENANCE MANUAL
 (r)  Apply pitot pressure to all systems at the same time.
 (4)  S 865-083Disconnect the cabin altitude differential pressure indicator from its static pressure source. (a) Seal the pressure source with a cap.
 (5)  S 865-084Supply electrical power (Ref 24-22-00).
 (6)  S 715-085Do the Air Data System - Operational Test (AMM 34-12-00/501).
 S 865-048

 WARNING:_______OPEN THE CIRCUIT BREAKER FOR THE FLAP LOAD RELIEF. IF YOU DO NOT OPEN THIS CIRCUIT BREAKER, YOU CAN CAUSE INJURY TO PERSONS.
 (7)  Open the circuit breaker for the FLAP LOAD RELIEF on the load control panel, P6.
 S 865-049
 CAUTION: OPEN THE DIGITAL STALL WARNING COMPUTER (DSWC) CIRCUIT
_______ BREAKERS. IF YOU DO NOT OPEN THESE CIRCUIT BREAKERS, YOU CAN CAUSE DAMAGE TO EQUIPMENT.
 (8)  
Open the STALL WARNING No. 1 and No. 2 circuit breakers on the load control panels, P6 and P18.

 S 865-050

 (9)  
Open the NO. 1 AIR DATA COMPUTER-1 and TEMP PROBE circuit breakers on the load control panel, P18.

 S 865-051

 (10)
 Open the NO. 2 AIR DATA COMPUTER-2 circuit breakers on the load control panel, P6.

 S 865-052

 (11)
 Disconnect the connector D277 from the TAT (total air temperature) probe (Sta 260).

 S 865-053

 (12)
 Connect the decade resistance box in the TAT probe input to the ADC No. 1.

 S 865-054

 (13)
 Close the circuit breakers for the air data system on the load control panels, P6 and P18.

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
 S 865-055
 (14) Turn the altimeter BARO knob on the captain's, F/O's and standby altimeters through the full range.
 (a)  Set the altimeter BARO knobs to 29.92 from a lower number and stop.
 S 865-056
 (15)
 Connect the test set to the airplane.

 S 865-057

 (16)
 Make sure the differential pressure indicator for the cabin altitude on the pilot's overhead panel, P5, is disconnected.

 S 865-058

 (17)
 Make sure the static source selector valves are in the NORMAL position.

 F. Air Data System test
 S 865-059
 (1)  Apply pressures and resistance shown in Table 501, Test Point No. 1.
 NOTE: At each test value, permit the pressure to become stable for
　
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