All values must be in the limits shown.
The difference between the captain's and F/O's indicators must not be larger then the values shown.
Do not hit or shake the indicators before you read the values.
Read the indicators at the same time for each value.
Make sure the indicators move smoothly during pressure changes.
S 865-064
(2) AIRPLANES WITH AIR DATA VSI'S;
Do this test on the vertical speed indicators.
(a)
Adjust the static pressure to get a constant rate of ascent of 2,000 feet per minute (as shown on the captain's and F/O's VSI's).
(b)
Measure the time necessary to go from 2,000 to 4,000 feet.
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737-300/400/500MAINTENANCE MANUAL
(c)
The time must be 60 |5 seconds.
(d)
Adjust the static pressure to get a constant rate of descent of 2,000 feet per minute (as shown on the captain's and F/O's VSI's).
(e)
Measure the time necessary to go from 4,000 to 2,000 feet. 1) Time must be 60 |5 seconds.
S 865-028
(3) Apply the pressures and resistances in Table 501 for all test points.
NOTE: All values must be in the limits shown.
____ The difference between the captain's and F/O's displays must not be larger then the values shown.
NOTE: The rate on the captain's and F/O's VSI's must not be more
____
than 150 ft/min apart.
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A 737-300/400/500MAINTENANCE MANUAL
INPUTS
______
Test Altitude Static Press Diff Press Pitot Press Mach Airspeed Decade Box Point_____ (Feet) _________ (In.Hg.) ________(In.Hg.) Input ______ Resistance
______ (In.Hg.) ________ _____ Input __________
1 0 29.921 0.390 30.311 0.136 90 550.7 2 5,000 24.896 3.100 27.996 0.413 250 518.1 3 15,000 16.886 0.817 17.703 0.261 130 467.5 4 25,000 11.104 5.909 17.013 0.805 340 480.9 5 35,000 7.041 3.909 10.963 0.820 279.5 416.1 6 40,000 5.538 3.637 9.175 0.881 270 401.4
OUTPUTS
_______
Test Altimeter's Mach Airspeed VmoInd's *[2] __________ Pointer
Point_____ (Feet) *[1]___________ ___________ Ind's *[3] ________ # 1 0 |30 Blk. Mask 90 |2 340 +0/-4 2 5,000 |35 0.413 |0.01 250 |2 340 +0/-4 3 15,000 |45 Blk. Mask 130 |2 340 +0/-4 4 25,000 |60 0.805 |0.01 340 |2 340 +0/-4 5 35,000 |90 0.820 |0.01 279.5 |2 279.5 +0/-4 6 40,000 |105 0.881 |0.01 271 |2 251 +0/-4
Test Standby Standby TAT SAT TAS Point_____ Altimeter ________ °C ___ Knots
_________ Airspeed ___ °C _____
1 0 |30 90 |3.5 +26.1 |2.0 +25.0 |2.0 ----2 5,000 |50 250 |3.5 + 9.3 |2.0 0.0 |2.0 266.0 |5 3 15,000 |110 130 |3.5 -16.5 |2.0 -20.0 |2.0 161.8 |5 4 25,000 |160 340 |8 - 9.8 |2.0 -40.0 |2.0 479.0 |5 5 35,000 |210 279 |6 -42.7 |2.0 -70.0 |2.0 455.4 |5 6 40,000 |235 270 |6 -50.1 |2.0 ------477.1 |5
NOTE: The SAT value for test point 6 is not necessary.
____
*[1] Refer to Table 502, Altimeter Tolerances *[2] Max permitted difference between mach indicators is 0.012 *[3] Max permitted difference between airspeed indicators is 3 knots
TABLE 501 Air Data System Test Points
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TEST ALTIMETER TOLERANCE POINT_____ ALTITUDE _________ PART B
________ PART A _________
1 0 35 ft 40 ft
2
5,000 40 ft 80 ft
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