(3)
Test first officer's static system for leakage.
(a)
Place shutoff valve in open position.
(b)
Apply a vacuum to first officer's static system on upper right probe (preferred) or drain fitting No. 9.
(c)
Repeat steps E.(2)(c) and (d) above for first officer's static system and altimeter.
(4)
Test auxiliary No. 1 static system for leakage.
(a)
Place shutoff valve in open position.
(b)
Apply a vacuum to auxiliary No. 1 static system on lower right probe (preferred) or drain fitting No. 4.
(c)
Repeat steps E.(2)(c) and (d) above using pressure indicator or altimeter.
(5)
Test auxiliary No. 2 static system for leakage.
(a)
Place shutoff valve in open position.
(b)
Apply vacuum to upper right probe (preferred) or drain fitting No. 2.
(c)
Repeat steps E.(2)(c) and (d) above using test vacuum indicator and altimeter.
(6)
Test alternate static system for leakage.
(a)
Place shutoff valve in open position.
(b)
Apply vacuum to right flush to body mounted static ports (preferred) or drain fitting No. 5.
(c)
Repeat steps E.(2)(c) and (d) above using test vacuum indicator and altimeter.
(d)
Remove seals and adapters from captain's and first officer's static systems.
F. Restore Airplane to Normal Configuration
WARNING: Failure to remove the vinyl adhesive tape from the static ports before flight may cause large errors in airspeed sensing and altitude sensing signals which may lead to loss of safe flight.
(1)
Remove all seals and adapters from all pitot static probes that were tested. Check that no deposits or roughness exists in or about static ports or pitot head apertures.
(2)
Remove flush to body mounted adapter from alternate static port and seal if system was tested.
(3)
Remove all pitot pressure chamber drain seals.
(4)
Replace all drain fitting caps (if removed).
5C8
34-11-01 Page 506 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. May 01/98
PITOT STATIC PROBE - REMOVAL/INSTALLATION
1. General
A. The removal/installation of all pitot tubes is similar.
2. Equipment and Materials
A. Aerodynamic smoother
3. Remove Pitot Static Probe
A. Hold pitot static probe and remove screws (6) from probe base.
B. Pull probe away from airplane skin far enough to remove connectors.
C. Disconnect pitot, static and heater connectors (Fig. 401).
D. Remove probe, gasket and then shim(s) as required.
E. Cap pitot and static lines and cover electrical connector with protective cover.
4. Prepare to Install Pitot Static Probe
A. Check gasket and shim(s) (as required) for aging and wear.
B. Remove aerodynamic smoother from probe base and external body skin.
5. Install Pitot Static Probe
A. Install gasket and shim(s) (as necessary) to assure flushness between pitot-static probe and airplane skin within +0.000 or -0.020 inch (SRM 51-70).
B. Position probe close to airplane skin and connect pitot, static and heater connectors.
C. Place probe into position and secure to airplane with screws (6).
D. Measure the resistance between strut of the pitot static probe and the airplane skin with a multimeter.
1. Make sure the resistance is less than 0.010 ohm.
D. Reseal around gasket and airplane skin with aerodynamic smoother.
NOTE: It is not necessary to apply the sealant immediately if the cure time will cause a flight delay. However, you must apply the sealant as soon as possible to keep moisture out of the area between the probe and the airplane skin.
E. Perform a pitot and static test for the replaced probe per 34-11-0 A/T.
500
Sep 01/02 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. 34-11-11 Page 401
H23860
Pitot Static Probe Installation 500
34-11-11Page 402 Figure 401 BOEING PROPRIETARY - Copyright . - Unpublished Work - See title page for details. Oct 20/83
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