(2)
Adjust static pressure to obtain a constant rate of ascent of 2,000 feet per minute (as indicated on captain's and F/O's VSI's).
(3)
Measure time required to go from 2,000 to 4,000 feet. Time should be 60士5 seconds.
(4)
Adjust static pressure to obtain a constant rate of descent of 2,000 feet per minute (as indicated on captain's and F/O's VSI's).
(5)
Measure time required to go from 4,000 to 2,000 feet. Time should be 60士5 seconds.
(6)
Observing all previously mentioned limitations and restrictions, apply pressures given in Table 501 for remaining test points. All readings should be within limits specified. Difference in reading between captain's and F/O's indicators should not exceed values shown in Table 502.
5C8
Feb 20/89 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 34-12-01 Page 505
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 6 0 10,000 20,000 35,000 40,000 0 29.921 20.577 13.750 7.041 5.538 29.921 3.100 6.286 5.368 4.534 3.637 0.817 33.021 26.863 19.073 11.575 9.175 30.738 0.378 0.629 0.703 0.874 0.881 0.197 250 350 325 300 270 130
OUTPUTS
Test Altitude Mach Airspeed Vmo
Point (Feet) *[1] Ind's *[2] Ind's *[3] Pointer
1 2 3 4 5 6 0 10,000 20,000 35,000 40,073 0 士30 士40 士50 士90 士105 士30 Blk. Mask 0.629士0.01 0.703士0.01 0.874士0.01 0.881士0.01 Blk. Mask 250士2 350士2 325士2 300士2 270士2 130士2 348353362285248348 士4 士4 士4 士4 士4 士4
Test Point Standby Altimeter Standby Airspeed
1 2 3 4 5 6 0 10,000 20,000 35,000 40,000 0 士30 士90 士140 士210 士235 士30 250士3.5 350士8.0 325士7.0 300士6.0 270士6.0 130士3.5
*[1] Refer to Table 502, Altimeter Tolerances. *[2] Max allowable difference between mach indicators is 0.012. *[3] Max allowable difference between airspeed indicators is 3 knots.
Air Data System Test Points Table 501
5C8 34-12-01 May 01/01
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BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details.
Test Altimeter Tolerance
Point Altitude Part A Part B
1 0 35 ft 40ft
2 10,000 45ft 90ft
3 20,000 60ft 140ft
4 35,000 95ft 220ft
5 40,000 110ft 250ft
6 0 35ft 40ft
PART A defines maximum allowable difference between captain's altimeter and F/O's altimeter readings.
PART B defines maximum allowable difference between captain's and F/O's altimeters and the standby pneumatic altimeter readings.
Altimeter Tolerances Table 502
(7)
Perform leakage test on each pitot static system: captain's, F/O's and auxiliary.
(a)
Apply a pressure of 300 士5 knots equivalent airspeed and a vacuum of 22,500 士200 feet altitude to pitot static system.
(b)
Cut off pressure and vacuum sources after system has stabilized. Read and record airspeed and altitude to the nearest 1 knot and 20 foot increment.
(c)
Verify leakage rate does not exceed 5 knots or 400 feet per minute.
(8)
Reduce Ps to local ambient. Change pressures at a moderate rate, and assure that pitot pressure is always equal to or greater than static pressure.
(9)
Reconnect cabin altitude differential pressure indicator.
E. Restore Airplane to Normal
(1)
Disconnect test equipment.
(2)
Remove seals from airplane's static lines, ensuring no deposit or roughness exists in or about static ports.
(3)
Remove electrical power if no longer required.
5C8
Jun 20/93 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 34-12-01 Page 507
(b) Test Servoed Indicators 1) Open ALTM 26V AC, VERT SPEED and MACH/AIRSPEED IND circuit breakers on P18 and P6 panels. 2) Set barometric setting on altimeters to 29.92 inches of mercury or 1013 millibars. 3) Observe that altimeter, vertical speed and mach/airspeed failure warning flags are in view.
4) Close above circuit breakers on panel P18 and P6. Check that altimeter, vertical speed and mach/airspeed flags are removed from view.
INPUTS
Test Altitude Static Press Diff. Press Pitot Press Mach Airspeed
Point (Feet) (In. Hg) (In.Hg) (In. Hg) Input Input
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