(c)  
Absolute pressure applied to static system should never exceed ambient absolute pressure when any instrument is connected to static system.

5C8
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(d)  
Do not change setting of static source selector valve while vacuum is on static system. Check that selector valve remains in NORMAL position unless test procedures specify otherwise.

(e)  
Ensure that pitot static probe heaters remain off during tests.

(f)  
Inspect each pitot static probe head both before and after these tests for evidence of damage to circular leading edge of its barrel.

(g)  
Do not apply pressure in excess of 31 inches of mercury absolute to static lines.

CAUTION:  IF THE ABOVE PROCEDURES ARE NOT OBSERVED, EQUIPMENT AND INSTRUMENTS WILL BE DAMAGED.
(2)  To test mach airspeed system No. 1:
(a)  
Connect pitot pressure source to upper left pitot static probe and static source to S1 port on upper left pitot static probe.

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

(b)  
Seal S1 static port on lower right pitot static probe.

NOTE:  Seal static port 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.
(3)  
To test mach airspeed system No. 2:

(a)  
Connect pitot pressure source to upper right pitot static probe and static source to S1 port on upper right pitot static probe.

(b)  
Seal S1 static port on lower left static probe.

(4)  
Provide electrical power

C.  Test Mach Airspeed Warning Systems
WARNING:  WARNING DEVICE (CLACKER) SHOULD NOT BE ENERGIZED FOR MORE THAN 5 MINUTES OR DAMAGE MAY RESULT. ALLOW A MINIMUM COOLING PERIOD OF 15 MINUTES BEFORE ENERGIZING SYSTEM AGAIN.
(1)  
Check that AIR DATA, AURAL MACH/AS WARNING and CAPTAIN'S MACH A/S IND circuit breakers are closed on P18 panel.

(2)  
Open first officer's MACH A/S IND circuit breaker on P6.

(3)  
Press MACH AIRSPEED WARNING TEST NO. 1 switch located on aft overhead panel P5. Check that clacker comes on.

(4)  
Release test switch. Check that clacker goes off.

(5)  
Open Captain's MACH A/S IND circuit breaker. Close first officer's MACH IND circuit breaker.

(6)  
Repeat step (3) and (4) with MACH AIRSPEED WARNING TEST NO. 2 switch.

(7)  
Close Captain's MACH A/S IND circuit breaker.

(8)  
Apply pressures to captain's pitot static system (No. 1 mach airspeed warning system) as shown in Table I. Check that clacker comes on within tolerances indicated and go off when differential pressure is reduced below lower tolerance value.

CAUTION:  DIFFERENTIAL PRESSURE SHOULD BE BETWEEN 0 AND 10 INCHES OF MERCURY AT ALL TIMES.

(9)  
Repeat step (3) with pitot and static pressures applied to first officer's pitot static system (No. 2 mach airspeed warning system).

5C8 
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TABLE I
ALT (FEET) (REF)  STATIC PRESSURE IN HG ABSOLUTE  PITOT PRESSURE IN HG ABSOLUTE  DIFF PRESSURE IN HG ABSOLUTE  INDICATED AIRSPEED KNOTS 
Sea level 20,000 30,000 35,000  29.921 13.750 8.885 7.041  36.207 - 36.362 20.563 - 20.725 14.104 - 14.243 11.176 - 11.298  6.286 - 6.441 6.813 - 6.975 5.219 - 5.348 4.135 - 4.257  350.0 - 354.0 363.4 - 367.4 320.7 - 324.7 287.1 - 291.1 

D.  Restore Airplane to Normal Configuration
(1)  
Restore mach airspeed warning and pitot static systems to normal.

(2)
If no longer required, remove electrical power from airplane.

5C8
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

ALTITUDE ALERTING SYSTEM - DESCRIPTION AND OPERATION
EFFECTIVITY
SA ALL EXCEPT ZS-SBL thru ZS-SBR GJ B-2509 thru B-2510
1.  General
A.  The Altitude Alerting System is a part of the Automatic Flight Control System (AFCS). The AFCS utilizes the alerting system for altitude acquisition and altitude deviation alerting. Refer to 22-11-01 for altitude alerting system coverage.
Oct 20/84 34-17-0 Page 1
BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.

ALTITUDE ALERTING SYSTEM - DESCRIPTION AND OPERATION
EFFECTIVITY
　
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