S 682-004
 (1)  
Drain the pitot-static system:

 (a)  
Remove the drain plugs.

 (b)  
Turn the drain cap 180 degrees.

 1)  Put the raised, hexagonal part of the cap into the opening in the bottom of the drain body.

 (c)  
If it is necessary, flush the pitot-static lines (Ref elevator pitot-static system flushing)

 (d)  
Clean the drain plugs with solvent.

 (e)  
Install the drain plugs.

 S 712-005
 (2)  
Examine the drain system:

 (a)  
Disconnect the drain lines.

 (b)  
Examine the drain system.

 (c)  
If it is necessary, flush the drain line (Ref Elevator Pitot-Static System Flushing).

 (d)  
Reconnect the drain lines.

 TASK 27-31-17-702-008
 4.  System Test - Elevator Pitot-Static System
__________________________________________
 A.  Special Tools and Equipment
 (1)  
Air Pressure Regulator - F72928-25, -33, -34, -36, -37, or -43, or make to the specification D6-32356

 B.  
Access

 (1)  
Location Zone
 702 Tail Compartment Access Door

 (2)  
Access Panels
 3701 Stabilizer Trim Access Door

 C.  
Procedure

 (1)  
Seal the drain hole on each pitot probe on the fin.

 S 392-006
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
 S 032-007
 (2)  Remove the drain plugs from the systems A and B pitot lines below
 the feel computer.
 S 482-011
 (3)  Attach the pressure gage lines from the air pressure regulator to
 the drain holes of the pitot system A and B below the feel computer.
 NOTE:____ The airspeed values in the steps that follow are for use
 only when the static pressure on the airspeed indicator is
 open to the ambient pressure.

 S 482-012
 CAUTION: DO NOT INCREASE THE PRESSURE TO MORE THAN 6 PSI (474 KNOTS
_______ KCAS) DURING THE TEST. IF THE PRESSURE IS MORE THAN 6 PSI, IT CAN CAUSE DAMAGE TO THE FEEL COMPUTER.
 (4)  
Attach the regulated air pressure line from the air pressure regulator to the two pitot probes on the fin.

 (a)  
Pressurize the pitot-static system to 5.0 |0.1 psi (437 |4 knots KCAS).

 S 722-017
 (5)  
Do a test of the pitot-static system:

 (a)  
Turn the shutoff valve in the air pressure regulator to the OFF position.

 (b)  
Make sure that pressure does not decrease more than 0.3 psi (12 knots KCAS) during a 2-minute time.

 (c)  
Reduce the pitot pressure to zero.

 S 162-016
 (6)  
Remove the seals from the drain hole in each pitot probe on the fin.

 S 082-013

 (7)  
Remove the pressure gage lines from the drain lines below the feel computer.

 S 432-014

 (8)  
Install the drain plugs.

 (9)  
Remove the pressure lines from the two pitot probes on the fin.

 S 082-015
 EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. ú

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 ALL  ú ú 01 Page 204 ú Jul 15/98
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 TASK 27-31-17-202-018
 5. Pitot Probe - Inspection/Check
______________________________
 A. Access
 (1)  
Location Zone
 702 Tail Compartment Access Door

 (2)  
Access Panels
 3701 Stabilizer Trim Access Door

 B.
References

 (1)  
27-31-94/401, Feel System Pitot Tube

 C.
Procedure

 S 012-019
 (1)  
　
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