747飞机维护手册AMM CHAPTER 34 - NAVIGATION 第34章导航1(41)

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 GROUND. IN ADDITION, ATTACH A LABEL TO THE LEFT
 CONTROL WHEEL AS A REMINDER THAT THE PITOT
 PROBES/STATIC PORTS ARE COVERED. FAILURE TO
 REMOVE THESE COVERINGS BEFORE FLIGHT MAY CAUSE
 LARGE ERRORS IN AIRSPEED AND ALTITUDE SENSOR
 OUTPUTS THAT MAY LEAD TO LOSS OF SAFE FLIGHT.
 
 
   CAUTION: DO NOT EXTEND THE SEALS INTO THE STATIC_______
 PORTS. YOU CAN CAUSE DAMAGE TO THE SURFACE IN
 THE AREA WHEN YOU REMOVE THE TAPE.
 4)  Verify that pitot system is open to ambient.
 CAUTION: TO PREVENT INSTRUMENT/EQUIPMENT DAMAGE, KEEP_______
 RATE OF STATIC PRESSURE CHANGE BELOW 3000 FEET
 PER MINUTE AND DIFFERENTIAL PRESSURE BETWEEN
 0 AND 10 INCHES OF MERCURY.
 5)  Open static cutoff valve. Use pneumatic test unit and
 static control valve to apply a vacuum equivalent to the
 ambient pressure minus 5.25 (|0.25) inch Hg or 5000 feet
 above airport altitude as indicated on captain's altimeter
 or pitot system test gages.
 6)  When required vacuum has been reached and has stabilized,
 close static cutoff valve.
 CAUTION: VACUUM MUST BE HELD AS A BACKUP BEHIND CUTOFF_______
 VALVES DURING CUTOFF PERIOD. FOLLOWING THIS,
 CUTOFF VALVES ARE REOPENED. RELEASE OF VACUUM
 IS GRADUAL AND SIMULTANEOUS FOR ALL STATIC
 SYSTEMS.
 7)  Immediately after closing cutoff valve, read and record
 indication on static system gages.

 EFFECTIVITY

 
 ALL  01.1 Page 509  Oct 25/9834-11-00
 8)  After 1 minute, read and record values indicated on the aircraft altitude indicators and the system test gage. Vacuum must not have decreased more than 0.07 inch Hg or an equivalent decrease of 80 feet indicated altitude.
 9)  Release vacuum on static system, and remove all adapters and seals from pitot-static probes.
 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: TO PREVENT PITOT-STATIC PROBE DAMAGE, VISUALLY
_______
   CHECK EACH PROBE AND VERIFY NO PIECES OF COLORED
   TAPE REMAIN ON PROBE.
 (b)
Test first officer's static system for leakage.

 1)  Repeat steps 2.D.(3)(a) 1) thru 9), with test adapter connected on upper right pitot-static probe, and with static port (S2) on lower left pitot-static probe sealed.

 (c)
Test auxiliary static system No. 1 for leakage.

 1)  On AZ 201-202, 209-211; IB 405, turn on, or remove magazine from ARINC 542 type flight recorder.
 2)  On LH 082-099; AF 121, 122, 151-199; AZ 281-299; SN 351-399; MD ALL; GN ALL; AT ALL; VM ALL, plus airplanes incorp SB 27-2297; open TE FLAP LOAD RELIEF circuit breaker on P12 panel.
 WARNING: FAILURE TO OPEN TE FLAP LOAD RELIEF CIRCUIT
_______ BREAKER MAY RESULT IN INJURY TO PERSONNEL.
 3)  Repeat steps 2.D.(3)(a) 1) thru 9), with test adapter connected on lower right pitot-static probe, and with static port (S2) on upper left pitot-static probe sealed.
 (d) Test auxiliary static system No. 2 for leakage.
 1)  On LH 001-070; AF 101-150; AZ 231 WITHOUT SB 27-2343, AND AZ 201-230, 232-280; SN 301-350; IB ALL; less airplanes incorp SB 27-2297,
 open TE FLAP LOAD RELIEF circuit breaker on P12 panel.
 WARNING: FAILURE TO OPEN FLAP LOAD RELIEF CIRCUIT BREAKER
_______ MAY RESULT IN INJURY TO PERSONNEL.
 2)  Repeat steps 2.D.(3)(a) 1) thru 9), with test adapter connected on lower left pitot-static probe, and with static port (S2) on upper right pitot-static probe sealed.
 E.  Full Range Leakage Test - Pitot Static System
 (1) Prepare for Test
 (a) Ensure that autopilot remains off during this test.
 EFFECTIVITY
 
 ALL  41.1 Page 510  Oct 25/9834-11-00
 (b)  
Set both static source selector valves to NORMAL position. They will remain in this position throughout the test.

 (c)  
If installed (Ref 34-11-00, Description and Operation), disconnect and cap static hose from galley and toilet exhaust differential pressure switch in right crawlway at station 400 (Ref 21-26-05).

 (d)  
Disconnect and cap static hose from differential pressure gage at rear of flight engineer's panel P4 (Ref 21-33-05).

 (e)  
Ensure that pitot-static probe heaters remain off during this test.

 (f)  
　
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