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BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 ~............................................................................... | TABLE 501 Air Data System Test Points | ................................................................................. | Test | Standby | Standby | TAT | SAT | TAS | | Point | Altimeter | Airspeed | °C | °C *[1] | Knots | ................................................................................. | 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 | 481.0 |5 | ................................................................................. | 5 | 35,000 |210 | 279 |6 | -42.7 |2.0 | -70.0 |2.0 | 458.0 |5 | ................................................................................. | 6 | 40,000 |235 | 270 |6 | -50.1 |2.0 | ---------| 477.1 |5 | 2.........….............….............….............….............….............1 *[1] The SAT value for test point 6 is not necessary. ~............................................................................... | TABLE 502 Altimeter Tolerances | ................................................................................. | TEST | | ALTIMETER TOLERANCE | ALTIMETER TOLERANCE | | POINT | ALTITUDE | PART A *[1] | PART B *[2] | ................................................................................. | 1 | 0 | 35 ft | 40 ft | ................................................................................. | 2 | 5,000 | 40 ft | 65 ft | ................................................................................. | 3 | 15,000 | 50 ft | 115 ft | ................................................................................. | 4 | 25,000 | 70 ft | 170 ft | ................................................................................. | 5 | 35,000 | 95 ft | 220 ft | ................................................................................. | 6 | 40,000 | 105 ft | 240 ft | 2.......…......................….......................…........................1 *[1] PART A defines maximum allowable difference between captain's altimeter and
 F/O's altimeter readings. *[2] PART B defines maximum allowable difference between captain's altimeter and
 the standby pneumatic altimeter readings or the F/O's altimeter and the
 standby pneumatic altimeter readings.
 S 705-062
 (3)  Do the leakage test on each pitot static system: captain's, F/O's, and auxiliary.
 (a)  
Apply a pressure of 300 |5 knots airspeed and a vacuum of 22,500 |200 feet altitude to the pitot-static system.

 (b)  
When the system is stable, stop the pressure and vacuum sources.

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 34-12-01

 ú ú 04 Page 510 ú Mar 12/01
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
 (c)  
Make a note of the airspeed and altitude to the nearest 1 knot and 20 foot increments.

 (d)  
Make sure the leakage rate is not larger then 5 knots or 400 feet per minute.

 S 825-063
 (4)  Decrease the static pressure to the ambient pressure
 NOTE:____Change the pressures at a slow rate. Make sure the pitot pressure is equal to or larger than the static pressure.
 S 435-064
 (5)  
Connect the differential pressure indicator for the cabin altitude.

 S 705-065

 (6)  
Do the cabin differential-pressure indicator test.

 (a)  Connect the cabin altitude differential indicator to the No. 1 auxiliary static system.
 CAUTION: KEEP THE RATE OF ALTITUDE CHANGE TO LESS THAN 300 FEET PER
　
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