S 414-017
(11)
Install the elbow and O-ring in the static pressure port.
S 434-018
(12)
Tighten the jamnut.
S 094-019
(13)
Remove the dust cap from the static hose.
S 164-020
(14)
Make sure that no unwanted materials are in the hose.
S 434-021
(15)
Connect and tighten the static hose to the elbow to a torque value of 100 to 125 inch-pounds.
S 794-022
(16)
Do a leak test of the pitot-static system (Ref 34-11-01/501).
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34-11-21
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A
737-300/400/500MAINTENANCE MANUAL
S 394-023
(17) Apply the sealant to the static pressure port as shown in Figure
401.
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34-11-21
ALL ú ú 07 Page 405 ú Nov 15/94
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A
737-300/400/500MAINTENANCE MANUAL
AIR DATA SYSTEMS - DESCRIPTION AND OPERATION
____________________________________________
1. General_______
A. The air data system consists of the air data instruments and two air data computers. The air data instruments are the mach/airspeed indicators, vertical speed indicators (airplanes with air data VSI's), and altimeters. A combined pneumatic altimeter and airspeed indicator is provided for standby indication. In addition, a combined total air temperature, static air temperature and true airspeed indicator is also provided (Ref Fig. 1).
B. Computed airspeed and mach number are displayed on mach/airspeed combined indicators from air data computer processed pitot static air pressure data. The indicators accept an input of altitude from the air data computers for controlling the maximum operating airspeed pointer of the mach/airspeed indicators. The indicators also provide a signal to the mach airspeed warning system to actuate an aural warning when maximum operating airspeed is exceeded. A standby airspeed indicator on the captain's instrument panel operates conventionally from direct pitot-static pressure information.
C. AIRPLANES WITH AIR DATA VSI'S; The vertical speed or rate-of-climb indicators are operated by altitude rate signals from the air data computers through a range of 0 to 6000 feet per minute.
D. Altitude information, derived from static pressure signals computed in the air data computers, is shown on the electric altimeters. A standby altimeter on the captain's instrument panel operates conventionally from direct static pressure information.
E. Air data computer No. 1 electrically integrates and computes, from pitot static pressures, altitude, mach number, and airspeed signals. This data is sent to the captain's air data instruments, autoflight system, mach trim, and other systems shown on Fig. 2. Power to operate the computer is obtained from circuit breaker panel P18. Air data computer No. 2 also provides altitude, mach number and airspeed signals. This data is sent to the first officer's air data instruments and other systems shown on Fig. 3. Power to operate this computer is obtained from circuit breaker panel P6.
2. Mach/Airspeed Indicator (Fig. 1 and 4)_______________________
A. The mach/airspeed indicator is a combination of two flight instruments, presenting an integrated display of computed airspeed and mach number. The pilots are each provided with an indicator.
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34-12-00
ú ú 03 Page 1 ú Jul 12/00
BOEING PROPRIETARY - Copyright (C) - Unpublished Work - See title page for details.
A 737-300/400/500MAINTENANCE MANUAL
MACH/AIRSPEED INDICATOR
Air Data System Component Location
Figure 1 (Sheet 1)
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