(4)  
Connect pitot pressure source and static pressure source to captain's or first officer's pitot static probe and static source to the alternate static port.

NOTE:  System drain fittings may be used for pitot and static pressure connections but are not the preferred connections.

(5)  
Seal all unused static ports in such a way that removal of seal will be complete leaving no deposits or roughness in or about ports. Seal should be properly marked to prevent removal while test is in progress.

(6)  
Place thermometer adjacent to total air temperature probe and shield from direct wind and sunlight.

(7)  
Open FLAP LOAD RELIEF circuit breaker on P6 panel.

WARNING:  FAILURE TO OPEN TE FLAP LOAD RELIEF CIRCUIT BREAKER MAY RESULT IN FLAP MOVEMENT AND INJURY TO PERSONNEL.

(8)  
Provide electrical power.

(9)  
Set barometric scale setting knob on captain's and first officer's altimeter to 29.92 inches of mercury before starting tests. Adjustment is to be made in the increasing reading direction without overshoot.

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D.  Test Air Data Pressure Instruments
(1)  Test Pneumatic Operated Instruments
(a)  Perform following series of tests for pneumatic instruments per conditions shown in Fig. 501 and 503. Perform servoed instruments test below for instruments receiving air data computer inputs. Apply head correction per step A.(5) above, when applicable.
CAUTION:  DURING TESTS, DO NOT ALLOW MACH/AIRSPEED WARNING CLACKER TO OPERATE MORE THAN 5 MINUTES PER SYSTEM OR DAMAGE WILL RESULT FROM OVERHEATING. AFTER 5\MINUTES OF OPERATION, A MINIMUM COOLING PERIOD OF 15 MINUTES SHOULD BE ALLOWED.
1)  Establish pitot and static pressure conditions in captain's, first officer's, auxiliary and alternate system lines per (Fig. 501) for increasing and decreasing altitudes.
(2)  Test Digital Air Data Computer(s)
NOTE:  Refer to A.(5), (6), and (7) when two computers are to be tested. Test below is written for computer No. 1. For computer No. 2 use applicable switches and circuit breakers.
(a)  The following steps list all self-tests. Perform those steps for self-test readouts available. 1) Rotate self-test switch to FUNCTION and press push-to-test switch. Switch must
be held depressed approximately 35 seconds. Verify following values on
indicators, as applicable, when TEST VALID WHEN LIT light on computer front
panel comes on.
a) Altitude 10,000 +30 feet (not applicable to servo-pneumatic altimeters)
b) Mach 0.785 +0.01
c) Airspeed 440 +2 knots
d) True airspeed 477.8 +6 knots (if applicable)
e) Static air temperature -29.4 +2°C (if applicable)

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C28859
530 Pneumatic Instruments Test Chart Jun 20/93 Figure 501 (Sheet 1) 34-12-0 Page 504A/504B BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

T53563 H23898
530  Pneumatic Instruments Test Chart 
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Altimeter Head Correction Test Chart  500 
34-12-0Page 506   Figure 502 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Feb 15/69 

2)  Rotate self-test switch to SLEW and press push-to-test switch. Verify that TEST VALID WHEN LIT light comes on.
3)  Rotate self-test switch to HOLD and press push-to-test switch. Verify that TEST VALID WHEN LIT light comes on.
4)  Rotate self-test switch to FAIL WARN and press push-to-test switch. Verify that TEST VALID WHEN LIT light comes on.
(3)  Test Servoed Instruments
(a)  General 1) These tests are for the servoed instruments which receive an electrical input from the air data computer.
2)  Air data computer should be tested per step (2) or known to be functioning properly before this test. The system must have been continuously energized for at least 30 minutes prior to this test.
3)  Use Fig. 503 below as directed in each test procedure. Apply head correction per step A.(5) above, when applicable.
CAUTION:  COMMAND SPEED CURSOR SELECT KNOB ON ELECTRIC MACH/AIRSPEED INDICATOR MUST BE IN MANUAL POSITION WHENEVER PERFORMANCE DATA COMPUTER CIRCUIT BREAKER IS NOT ENERGIZED OR EXCESSIVE CLUTCH WEAR MAY OCCUR.
　
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