S 865-194
(3)
Stop for 5 to 6 minutes to allow the system to stabilize.
S 865-195
(4)
Write the altitude.
S 865-196
(5)
Stop for one minute and read the altitude again.
S 865-197
(6)
Make sure that the altitude does not decrease by more than 80 feet
(0.07 in. Hg).
S 865-198
CAUTION: MAKE SURE THAT THE PITOT LINE PRESSURE IS EQUIVALENT OR MORE
_______ THAN THE STATIC LINE PRESSURE. KEEP THE STATIC PRESSURE CHANGE BELOW 5000 FEET FOR EACH MINUTE. MAKE SURE THAT THE DIFFERENTIAL PRESSURE STAYS BETWEEN 0 AND 10.00 INCHES OF MERCURY. YOU CAN CAUSE DAMAGE TO THE PITOT-STATIC SYSTEM.
(7) Open the static cutoff valve and send the first officer's static system to ambient pressure.
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITHOUT EFIS ú
34-11-00
ú ú 11 Page 529 ú Nov 12/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
E. Put the Airplane to Its Usual Condition
S 085-200
CAUTION: DO NOT DISCONNECT THE PNEUMATIC TEST SET WHEN THE PITOT-STATIC
_______ SYSTEM IS NOT AT AMBIENT PRESSURE. YOU CAN CAUSE DAMAGE TO THE EQUIPMENT.
(1) Disconnect the pneumatic test set from the drain fitting.
S 085-339
WARNING: WHEN THE STATIC PORTS ARE COVERED, MAKE SURE THAT CONDITION IS
_______ VISIBLE FROM THE GROUND. FAILURE TO OBSERVE AND REMOVE COVERINGS OVER STATIC PORTS BEFORE FLIGHT MAY CAUSE LARGE ERRORS IN AIRSPEED SENSING AND ALTITUDE SENSING SIGNALS, WHICH MAY LEAD TO LOSS OF SAFE FLIGHT.
CAUTION: MAKE SURE THAT YOU REMOVE ALL OF THE PIECES OF TAPE FROM EACH
_______ PITOT-STATIC PROBE. THE SYSTEM WILL NOT OPERATE CORRECTLY WHEN THE TAPE IS IN ITS POSITION.
(2)
Remove the vinyl adhesive tape from the forward static ports (S1) on the upper right pitot-static probe.
S 085-204
(3)
Remove the vinyl adhesive tape from the forward static ports (S1) on the lower left pitot-static probe.
S 215-205
(4)
Examine the static ports for unwanted materials and rough locations on the inner and outer surfaces (Ref 34-11-11/601).
S 865-206
(5)
Close the STALL WARNING NO. 1 and NO. 2 circuit breakers on load control panels P6 and P18.
(6)
Remove electrical power if it is not necessary (Ref 24-22-00/201).
S 865-208
TASK 34-11-00-795-209
9. The Auxiliary No. 1 Static System Low-Range Leak Test
_____________________________________________________
A. Standard Tools and Equipment
(1) Air data test set, Castleberry AT700-2, Castleberry Instr & Avionics, Austin, TX; or equivalent
EFFECTIVITYùùùùùùùùùùùùùùùùùùùùùùùùùùùùùù. AIRPLANES WITHOUT EFIS ú
34-11-00
ú ú 11 Page 530 ú Nov 12/99
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A
737-300/400/500MAINTENANCE MANUAL
(2) Flow restrictors, control valves, cutoff valves, and vinyl adhesive tape as required
B. References
(1)
24-22-00/201, Manual Control
(2)
34-11-11/601, Pitot-Static Probe
C. Prepare for the Test
S 865-210
(1) Supply electrical power (Ref 24-22-00/201).
S 865-211
WARNING:_______YOU MUST OPEN THE FLAP LOAD RELIEF CIRCUIT BREAKER. YOU CAN CAUSE INJURY TO PERSONS.
(2) Open the FLAP LOAD RELIEF circuit breaker on the load control panel P6.
S 485-340
WARNING: FAILURE TO REMOVE VINYL ADHESIVE TAPE FROM STATIC PORTS BEFORE
_______ FLIGHT MAY CAUSE LARGE ERRORS IN AIRSPEED SENSING AND ALTITUDE SENSING SIGNALS, WHICH MAY LEAD TO LOSS OF SAFE FLIGHT.
WARNING:_______MAKE SURE THAT THE PROBE HEAT IS NOT ON. YOU CAN CAUSE INJURY TO PERSONS.
CAUTION:_______DO NOT EXTEND THE SEALS INTO THE STATIC PORTS. YOU CAN CAUSE DAMAGE TO THE SURFACE IN THE AREA WHEN YOU REMOVE THE SEALS.
(3)
Seal the aft static ports (S2) in the lower right pitot-static probe with vinyl adhesive tape.
中国航空网 www.aero.cn
航空翻译 www.aviation.cn
本文链接地址：737-300 400 500 AMM 飞机维护手册 导航 NAVIGATION 1(29)
