CAUTION: TO PREVENT INSTRUMENT/EQUIPMENT DAMAGE, PITOT
_______ PRESSURE MUST ALWAYS EQUAL OR EXCEED STATIC LINE PRESSURE AND DIFFERENCE (DIFFERENTIAL PRESSURE) MUST NOT EXCEED 10.00 INCHES OF MERCURY. DIFFERENTIAL PRESSURE MUST NOT FALL BELOW ZERO.
(d)
Operate pneumatic test set and control valves to apply required pressure or vacuum to three static systems and two pitot systems as indicated on the test gages.
(e)
On completion of test, release pressure or vacuum on both pitot systems and all three static systems.
CAUTION: TO PREVENT INSTRUMENT/EQUIPMENT DAMAGE, RELEASE OF
_______ PRESSURE OR VACUUM IS GRADUAL AND SIMULTANEOUS FOR ALL PITOT AND STATIC SYSTEMS.
(3) Restore Pitot-Static Systems to Normal
EFFECTIVITY
ALL 14 Page 204 Apr 25/9834-11-00
(a) Remove all the vinyl adhesive tape and adapters from all pitot-static probes. Check that no deposits or roughness exists in or about static ports or pitot head apertures.
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.
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.
(b) Remove flush static port adapter and the vinyl adhesive tape from the alternate static ports. Check that no deposits or roughness exists in or about either alternate static port.
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.
CAUTION: MAKE SURE THAT YOU REMOVE ALL OF THE PIECES OF TAPE
_______ FROM EACH STATIC PORT. THE SYSTEM WILL NOT OPERATE CORRECTLY WHEN THE TAPE IS IN ITS POSITION.
(c) If used, remove adapters from drain fittings or test connectors in main equipment center and/or left crawlway. Replace drain fitting or test connector caps.
E. First Officer's Pitot-Static System - Pressurization
(1) First officer's pitot-static system is pressurized per procedures of 2.D. (Captain's Pitot-Static System).
F. Alternate Static System - Pressurization
(1) Alternate static system is pressurized per procedures of 2.D. (Captain's Pitot-Static System).
G. Auxiliary Pitot-Static System No. 1 - Pressurization
(1) Prepare to pressurize auxiliary pitot-static system No. 1.
(a) On AZ 201-202, 209-211; IB 405, remove magazine from flight recorder (Ref 31-31-01).
CAUTION: VERIFY THAT MAGAZINE IS REMOVED OR DAMAGE MAY RESULT
_______
TO RECORDER MECHANISM.
EFFECTIVITY
ALL 31 Page 205 Apr 25/9834-11-00
(b) Wet pitot-static probe adapter and connect pitot inlet of lower left pitot-static probe to pitot system test gage through a flow restrictor.
CAUTION: ENSURE THAT PROBE ADAPTER IS FLUSHED WITH WATER
_______ BEFORE ATTACHING ADAPTER TO PROBE, OR PROBE AND/OR ADAPTER MAY BE DAMAGED. A SOLUTION CONSISTING OF HALF PURE ETHYLENE GLYCOL AND HALF WATER SHOULD BE USED IN FREEZING TEMPERATURES DOWN TO -40.F.
(c)
Place vinyl adhesive tape over pitot chamber drain holes in lower left pitot-static probe.
(d)
Connect static portion of probe adapter to the aft set of static ports (S2) on the upper left probe to static system test gage through a flow restrictor.
(e)
Place vinyl adhesive tape over forward set of static ports (S1) lower right pitot-static probe.
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: DO NOT EXTEND THE SEALS INTO THE PITOT DRAINS OR
_______ STATIC PORTS. YOU CAN CAUSE DAMAGE TO THE SYSTEM.
NOTE: Vacuum may be applied to static system through drain
____ fitting in main electronic equipment center (using suitable adapter). Should option be chosen, all static ports mentioned in (c) and (d) must be sealed.
Test connectors (Ref par. 1.A.) may be used instead of drain fittings to connect pneumatic test set.
(f) On LH 082-099; AF 151-199; AZ 231 WITH SB 27-2343, AND AZ 281-299; SN 351-399; IB 415-499; MP ALL; GN ALL; AT ALL; VM ALL; plus airplanes incorporating SB 27-2297; open TE FLAP LOAD RELIEF circuit breaker on P12 panel.
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本文鏈接地址：747飛機維護手冊AMM CHAPTER 34 - NAVIGATION 第34章導航1(26)
