B. References
 (1)  24-22-00/201, Manual Control
 C. Access
 (1)  Location Zones
 211/212 Flight Compartment

 D. Prepare for Test
 S 215-002
 (1)  Examine each pitot-static probe before and after this test for signs of damage or unwanted material.
 S 865-003
 CAUTION: FOLLOW THESE PRECAUTIONS BEFORE YOU APPLY PRESSURE TO THE
_______ PITOT STATIC SYSTEM. IF YOU DO NOT OBEY THESE PRECAUTIONS, YOU WILL CAUSE DAMAGE TO EQUIPMENT.
 (2)  Obey these precautions before you apply pressure to the pitot static system.
 (a)  
Turn on the electrical power for the air data system before you make the static or pressure hookups.

 (b)  
Keep the power on the air data system until all pressure hookups have been opened.

 (c)  
Pressure changes must be flow controlled to prevent sudden changes in pressure and possible damage to air data hardware.

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 (d)  
Keep the static pressure in the range of 3.43 to 31.02 inches 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 Hg.

 (g)  
Make pressure changes to make sure the rate of change of altitude is less than 5,000 feet per minute.

 (h)  
Make pressure changes to make sure 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)  
Make sure the autopilot system stays off during the test.

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

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

 (n)  
Make sure the pitot-static probe heaters stay off during the tests.

 S 865-004
 (3)  Supply electrical power (AMM 24-22-00/201).
 S 865-005
 WARNING:_______OPEN THE CIRCUIT BREAKER FOR THE FLAP LOAD RELIEF. IF YOU DO NOT OPEN THIS CIRCUIT BREAKER, YOU CAN CAUSE INJURY TO PERSONS.
 (4)  Open circuit breaker for the FLAP LOAD RELIEF on load control panel, P6.
 S 865-007
 CAUTION: OPEN THE DIGITAL STALL WARNING COMPUTER (DSWC) CIRCUIT
_______ BREAKERS. IF YOU DO NOT OPEN THESE CIRCUIT BREAKERS, YOU CAN CAUSE DAMAGE TO EQUIPMENT.
 (5)  Open the STALL WARNING NO. 1 and NO. 2 circuit breakers on the load control panels, P6 and P18.
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 S 715-009
 (6)  Mach Airspeed System No. 1 test:
 (a)  Connect the pitot pressure source to the upper left pitot-static probe.
 NOTE: System drain fittings can be used for pitot and static
____
 pressure connections.

 (b)  Connect the static pressure source to the S1 port on the upper left static probe.
 WARNING: WHEN THE STATIC PORTS ARE COVERED, MAKE SURE THAT THE
_______ CONDITION IS VISIBLE FROM THE GROUND. FAILURE TO OBSERVE AND REMOVE COVERINGS OVER THE STATIC PORTS BEFORE FLIGHT MAY CAUSE LARGE ERRORS IN AIRSPEED SENSING AND ALTITUDE SENSING SIGNALS, WHICH MAY LEAD TO LOSS OF SAFE FLIGHT.
 (c)  Seal the S1 static port on the lower right pitot-static probe.
 S 715-010
 (7)  Mach Airspeed System No. 2 test:
 (a)  
Connect the pitot pressure source to the upper right pitot-static probe.

 (b)  
Connect the static pressure source to the S1 port on the upper right pitot-static probe.
　
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