NOTE: If trailing edge flaps are positioned at greater than
____ 25 degrees and simulated airspeed of auxiliary pitot-static system No. 1 is raised to 172 (| 3) knots, the flaps will be actuated unless TE FLAP LOAD RELIEF circuit breaker is open.
EFFECTIVITY
ALL 32 Page 206 Apr 25/9834-11-00
(g) Disconnect and cap pitot line, or connect separate static lines from test set to stabilizer control module (Ref 27-41-04). On AF 104; AZ 202; plus airplanes incorporating SB 27-2027, disconnect and cap pitot line or connect separate static line from test set to elevator feel computer (Ref 27-31-14). On LH 004-099; AF 105-199; AZ 203-299; SN ALL; IB 405-499; MD ALL; GN ALL; AT ALL; VM ALL, disconnect pitot line from elevator feel computer and stabilizer control module by means of quick-disconnect at station 2450, LBL 10.
CAUTION: ELEVATOR FEEL COMPUTER AND STABILIZER CONTROL MODULE
_______ MUST HAVE BOTH PITOT AND STATIC CONNECTIONS OR NEITHER PITOT NOR STATIC CONNECTIONS DURING TEST; OTHERWISE DAMAGE COULD RESULT TO FEEL COMPUTER AND CONTROL MODULE.
(2) Pressurize Auxiliary Pitot-Static System No. 1
(a)
Make sure test equipment installation is complete and ready for operation.
(b)
For pressures below ambient operate pitot vacuum source and control valve such that pressure in pitot system does not start to decrease until after static system has begun to evacuate. Pitot system vacuum should be monitored continuously during pump down.
(c)
For pressures above ambient, operate pitot pressure source and control valve such that pressure in pitot system begins to increase before static system starts to pressurize. Monitor instruments continuously.
(d)
Operate pneumatic test set and control valves to apply required pressure or vacuum to static system as indicated on test gages.
(e)
On completion of test, release pressure or vacuum on pitot system and static system.
CAUTION: TO PREVENT INSTRUMENT/EQUIPMENT DAMAGE, RELEASE OF
_______ PRESSURE OR VACUUM IS GRADUAL AND SIMULTANEOUS FOR ALL PITOT AND STATIC SYSTEMS.
(3) Restore Auxiliary Pitot-Static System No. 1 to Normal
EFFECTIVITY
ALL 42 Page 207 Apr 25/9834-11-00
(a) Remove all vinyl adhesive tape seals 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)
If used, remove adapter from drain fitting or test connector in main equipment center and replace drain fitting or test connector cap.
(c)
Reinstall recording magazine in flight recorder (Ref 31-31-01).
(d)
Reconnect pitot lines or disconnect test static lines or reconnect pitot lines by means of quick-disconnects at station 2450, LBL 10, whichever is applicable, to elevator feel computers and stabilizer control module.
(e)
Perform leakage test on auxiliary pitot system No. 1 (Ref 34-11-00, Adjustment/Test).
(f)
Close T.E. FLAP LOAD RELIEF circuit breaker on P12 panel.
H. Auxiliary Pitot-Static System No. 2 - Pressurization
(1) Prepare to pressurize auxiliary pitot-static system No. 2.
(a)
Disconnect static hose from rear of differential pressure indicator at flight engineer's panel P4 (Ref 21-33-05).
(b)
If installed (Ref 34-11-00, Description and Operation), disconnect static hose from galley and toilet exhaust differential pressure switch in right crawlway, station 400 (Ref 21-26-05).
CAUTION: ENSURE THAT HOSES ARE DISCONNECTED OR EQUIPMENT
_______
DAMAGE WILL RESULT.
(c) Wet pitot-static probe adapter and connect pitot inlet of lower right 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.
(d)
Place vinyl adhesive tape over pitot chamber drain holes in lower right pitot-static probe.
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本文链接地址：747飞机维护手册AMM CHAPTER 34 - NAVIGATION 第34章导航1(27)
