(b)  Test Altimeter Indicator 1) Open following circuit breakers on panel P18:
CAPT ALTM 26V AC
CAPT ALTM VlB

2) Check that altimeter warning flag is in view and vibrator does not vibrate. 3) Close vibrator circuit breaker that was opened in step 1) above. Check that
altimeter vibrator operates. 4) Close all air data circuit breakers on panels P18. 5) Check that the altimeter warning flag disappears from view. Check that captain's
altimeter vibrator does not vibrate.
6)  Place function test select switch on computer in ALT MONITOR position and operate computer monitor switch. Check that captain's altimeter warning flag is in view with vibrator operating.
7) Release computer monitor switch and repeat step 5) above. 8) Open CAPT ALTM 26 volts ac circuit breaker on panel P18. Check that
captain's altimeter warning flag comes into view. Close circuit breaker. 9) Repeat step 5) above. 10) Ensure static source selector valve on both static systems is in NORMAL
position and that captain's altimeter warning flag is not in view. 11) Apply pressure to airplane pitot static systems to point 1 in Fig. 503. Check that altimeter readings are within tolerance shown under part A.
578 
34-12-0 Page 508  BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  Oct 20/90 

12)  Place ON-OFF switch on captain's altimeter in OFF position. Check that warning flag is in view. Release ON-OFF switch to center position. Check that captain's altimeter reading is within tolerance under part B.
13)  Place ON-OFF switch on captain's altimeter in ON position. Check that warning flag disappears from view. Release ON-OFF switch to center position.
14) Repeat steps 11) thru 13) for test points 2 thru 5 of Fig. 503.
 INPUTS 
Test Point  Altitude (Feet)  Static Press (In. Hg)  Diff Press (In. Hg)  Pitot Press (In. Hg)  Mach Input  Airspeed Input 
1 2 3 4 5  0 10,000 20,000 35,000 40,000  29.921 20.577 13.750 7.041 5.538  3.100 6.286 5.368 4.534 3.637  33.021 26.863 19.073 11.575 9.175  0.3779 0.6290 0.7034 0.8735 0.8808  250 350 325 300 270 
 OUTPUTS  Altimeter Toler  Altimeter Diff 
Test Point 1 2 3 4 5  Altitude (Feet) 0 10,000 20,000 35,000 40,000  Part A Servo *[1] 士30 ft士40 ft士50 ft士90 ft士105 ft Part B Pneu *[2] 士30 ft士90 ft士140 ft士210 ft士240 ft Part C Servo/Pneu *[3] 士40 ft士90 ft士140 ft士220 ft士250 ft Part D Pneu/Pneu *[4] 士30 ft士120 ft士190 ft士290 ft士320 ft 
Airspeed/Mach Ind 
Test Point 1 2 3 4 5  Airspeed (Knots) 250 士 2 350 士 2 325 士 2 300 士 2 270 士 2  Vmo Ind (Knots)348 士 4 353 士 4 362 士 4 285 士 4 248 士 4   Mach Ind Black Flag 0.629 士 0.01 0.703 士 0.01 0.874 士 0.01 0.881 士 0.01 

*[1]  Part A figures are tolerances applicable to the captain’s servo-pneumatic altimeter operated in the servo mode.
*[2]  Part B figures are tolerances applicable to the captain’s servo-pneumatic altimeter operated in the standby (pneumatic) mode.
*[3]  Part C figures are differences between captain’s servo-pneumatic altimeter operated in the servo mode and first officer’s pneumatic altimeter.
*[4]  Part D figures are differences between pneumatic altimeters or servo-pneumatic altimeters operated in the standby (pneumatic) mode.
578  Scale Error Test Chart 
Jun 20/93  Figure 503 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.  34-12-0 Page 509 

(c)  Test Servoed Mach/Airspeed Indicator 1) Open MACH/AIRSPEED IND circuit breaker on P18 panel. 2) Observe that mach/airspeed failure warning flags are in view. 3) Close above circuit breaker on P18. Check that mach/airspeed flags are
removed from view. 4) Apply pressure to airplane pitot static systems to test point 1 in Fig. 503. Check that mach/airspeed reading are within tolerance shown. 5) Repeat step 4) for test points 2 thru 4 of Fig. 503.
(5)  
Test Air Data Pressure Instrument System for Leakage

(a)  
Perform leakage test on each pitot static system: captain's, first officer's, and auxiliary. Apply vacuum of 22,500 士200 feet altitude to static system and pressure of 300 knots equivalent airspeed to pitot system. Check that leakage rate does not exceed 400 feet per minute and 5 knots per minute respectively.

(b)  
Reconnect cabin altimeter and differential pressure indicator to auxiliary static pressure system.

(6)  
Restore Air Data Pressure Instrument and Pitot Static Systems to Normal
　
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