(6)  
Connect all pitot lines and drain lines.

(7)  
Install drain plugs.

(8)  
Ensure that no deposit or roughness exists in any port associated with pitot-static system.

(9)  
If required, perform leakage test of pitot static system (Ref 27-31-212, Adjustment/Test).

551 
Aug 01/95  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-31-212 Page 201 

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27-31-212  Figure 201  May 01/75 
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 

3.  Pitot System Drainage Inspection/Check (Fig. 201)
A.  Check Pitot System Drainage
(1)  Periodically remove drain plugs (Ref par. 5). Drain sump on drain plug by inserting raised, hexagonal portion of cap into drain body. If required, flush and test pitot lines (Ref par. 2 and Adjustment/Test). Clean drain plugs with solvent. Install drain plugs (Ref par. 5).
4.  Static System Drainage Inspection/Check (Fig. 201)
A.  Check Static System Drainage
(1)  Periodically disconnect static system drain lines and check for proper drainage. If required, flush drain lines (Ref par. 2).
5.  Pitot System Drain Plug - Removal/Installation (Fig. 201)
A.  Remove drain plug.
(1)  Remove per detail A, Fig. 201.
B.  Install drain plug.
(1)  Install plug per detail A, Fig. 201.
6.  Pitot Probe Inspection/Check
A.  Get access to the pitot tube.
B.  Examine the pitot tube for damage.
NOTE:  The pitot tube does not need to be removed for normal erosion/corrosion of the pitot tip.
(1)  
If the pitot tube is bent or the electrical heater is damaged, install a new pitot tube (Ref 27-31-141/401).

(2)  
Make sure the maximum tip bluntness of the pitot tube is not more than 0.04 inch.

551 
Aug 01/95  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  27-31-212 Page 203 

ELEVATOR PITOT-STATIC SYSTEM - ADJUSTMENT/TEST
1.  Equipment and Materials
A.  Air Pressure Regulator - F72928-53 (Preferred), or -52 (Optional)
2.  Elevator Pitot-Static System Test (Fig. 501)
A.  Seal drain hole in each pitot probe on fin.
B.  Remove drain plugs from pitot lines.
C.  Attach pressure gage lines from air pressure regulator to drain holes.
D.  Attach regulated air pressure lines from air pressure regulator to both pitot probes on fin and pressurize pitot system to 5.0 ±0.1 psi (437 ±4 knots).
CAUTION:  DO NOT RAISE TEST PRESSURE ABOVE 6 PSI (474 KNOTS) AT ANY TIME DURING TEST, FEEL COMPUTER MAY BE DAMAGED.
E.  Cut off pressure source by turning shutoff valve in air pressure regulator to OFF.
F.  Check that pressure does not drop more than 0.3 psi (12 knots) during a 2-minute period.
G.  Reduce pitot pressure to zero.
H.  Remove seals from drain holes in each pitot probe.
NOTE: Ensure seals are removed from drain holes.
I.  Remove pressure gage lines from pitot system drain holes.
J.  Install drain plugs per Detail A, Fig. 501.
K.  Remove regulated air pressure lines from both pitot probes on fin.
May 01/00 27-31-212 Page 501 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

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STALL WARNING SYSTEM DESCRIPTION AND OPERATION
1. General
A.  A stall warning system (Fig. 1) is provided to alert the pilots of an approaching stall condition. The warning is accomplished by applying vibrations to the captain's control column. Interconnection of the control columns enable the vibrations to be transferred to the first officer's column. The system consists of an angle of airflow sensor, flap position transmitter, stall warning module and a control column shaker. The angle of airflow sensor measures the airplane angle of attack. An electrical position signal from the airflow sensor is modified by the flap position transmitter synchro and then fed into the stall warning module. At predetermined combinations of flap position and airplane angle of attack, a stall-warning signal is emitted from the module to activate the control column shaker.
2.  Angle of Airflow Sensor
A.  The angle of airflow sensor provides a signal which represents airplane angle of attack. The sensor is located on the outside of the fuselage below the captain's side window (Fig. 1). The sensor consists of an aerodynamic vane that positions a synchro. The counterbalanced vane is free to rotate from stop to stop and in flight it will assume a position parallel to the airflow passing over it.
　
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