S 865-055

 (10)
 Disconnect the connector D277 from the TAT (total air temperature) probe (Sta 260).

 S 865-056

 (11)
 Connect the decade resistance box in the TAT probe input to the ADC No. 1.

 S 865-089

 (12)
 Close the circuit breakers for the air data system on the load control panels, P6 and P18.

 S 865-057

 (13)
 Turn the altimeter BARO knob on the captain's, F/O's and standby altimeters through the full range.

 (a)  Set the altimeter BARO knobs to 29.92 from a lower number and stop.

 (14)
 Connect the test set to the airplane.

 S 865-058
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737-300/400/500MAINTENANCE MANUAL
 S 865-059
 (15) Make sure the differential pressure indicator for the cabin altitude on the pilot's overhead panel, P5, is disconnected.
 F. Air Data System - System Test
 S 785-090
 (1)  Apply the pressures and resistance shown in Table 501 for Test Point No. 1.
 NOTE: At each test point, let the pressure become stable for one
____
 minute.

 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 865-060
 (2)  Apply the pressures and resistances given in Table 501 for the other test points.
 NOTE: 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.
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737-300/400/500MAINTENANCE MANUAL
 ~............................................................................... | TABLE 501 Air Data System Test Points | | INPUTS | ................................................................................. |Test |Altitude|Static Press|Diff Press |Pitot Press| Mach |Airspeed|Decade Box| |Point| (Feet) | (In.Hg.) | (In.Hg.) | (In.Hg.) | Input |Input |Resistance| ................................................................................. |  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 | 2.....…........…............…...........…...........….......…........…..........1 ~............................................................................... | TABLE 501 Air Data System Test Points | | OUTPUTS | ................................................................................. |Test | Altimeter's | | | Vmo | |Point| (Feet) *[1] | Mach *[2] | Airspeed *[3] | Pointer | ................................................................................. |  1  | 0 |30 | Masked | 90 |2 | 340 +0/-4 | ................................................................................. |  2  | 5,000 |35 | 0.413 |0.01 | 250 |2 | 340 +0/-4 | ................................................................................. |  3  | 15,000 |45 | Masked | 130 |2 | 340 +0/-4 | ................................................................................. |  4  | 25,080 |60 | 0.809 |0.01 | 341 |2 | 341 +0/-4 | ................................................................................. |  5  | 35,073 |90 | 0.825 |0.01 | 281 |2 | 281 +0/-4 | ................................................................................. |  6  | 40,073 |105 | 0.881 |0.01 | 271 |2 | 251 +0/-4 | 2.....…....................….............…..................…...................1 *[1] Refer to Table 502, Altimeter Tolerances. *[2] Max allowable difference between Capt's and F/O's mach indications is 0.012. *[3] Max allowable difference between Capt's and F/O's airspeed indications is
　
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