(b)
Keep power on until all pressure hook-ups are opened.
(c)
Pressure changes must be flow controlled to avoid sudden changes in pressure and possible damage to air data hardware.
(d)
Keep the static pressure in the range of 3.43 to 31.02 inches of Hg.
(e)
Do not permit the static pressure to be more than 28 inches Hg. from the ambient pressure.
(f)
Keep the total pressure in the range of 3.0 to 41.0 inches of Hg.
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A 737-300/400/500MAINTENANCE MANUAL
(g)
Make pressure changes so that the rate of change of altitude is less than 5,000 feet per minute.
(h)
Make pressure changes so that the rate of change of airspeed is less than 300 knots per minute.
(i)
Keep the static line pressure less than the pitot line pressure.
(j)
Make sure the difference between the static and pitot line pressures is not larger than 10 inches of Hg.
(k)
AIRPLANES WITH STATIC SOURCE SELECTOR VALVES; Do not change the static source selector valve while vacuum is on the static system.
(l)
AIRPLANES WITH STATIC SOURCE SELECTOR VALVES; 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 ELECTRIC POWER IS NOT APPLIED TO THE
_______ PITOT-STATIC PROBE 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 pitot line pressure connections must be made at the
____
the pitot-static probes.
Drain fittings from the pitot-static system can be used for the pitot and static pressure connections.
(r) Apply pitot pressure to all systems at the same time.
S 865-050
(3)
Disconnect the cabin altitude differential pressure indicator from its static pressure source.
(4)
Supply electrical power (AMM 24-22-00/201).
S 865-051
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737-300/400/500MAINTENANCE MANUAL
S 715-087
(5) Do the Air Data System - Operational Test (AMM 34-12-01/501).
S 865-052
WARNING:_______OPEN THE CIRCUIT BREAKER FOR THE FLAP LOAD RELIEF. IF YOU DO NOT OPEN THIS CIRCUIT BREAKER, YOU CAN CAUSE INJURY TO PERSONS.
(6) Open circuit breaker for the FLAP LOAD RELIEF on the load control panel, P6.
S 865-053
CAUTION: OPEN THE DIGITAL STALL WARNING COMPUTER (DSWC) CIRCUIT
_______ BREAKERS. IF YOU DO NOT OPEN THESE CIRCUIT BREAKERS, YOU CAN CAUSE DAMAGE TO EQUIPMENT.
(7)
Open the STALL WARNING No. 1 and No. 2 circuit breakers on the load control panels, P6 and P18.
S 865-054
(8)
Open the NO. 1 AIR DATA COMPUTER-1 and TEMP PROBE circuit breakers on the load control panel, P18.
S 865-088
(9)
Open the NO. 2 AIR DATA COMPUTER-2 circuit breakers on load control panel, P6.
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