(c)
Wet pitot-static probe test adapter and install on upper left pitot-static probe.
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. TO PREVENT PROBE MISALIGNMENT, TEST HOSES AND ADAPTERS MUST BE SUPPORTED IN SUCH A WAY AS TO ADD NO EXTRA WEIGHT ON PROBES.
(d)
Connect pitot-static probe to cutoff valves through system test gages and flow restrictors.
(e)
Disconnect static line from left elevator feel computer, if connected.
(f)
On AZ 201-202, 209-211; IB 401-402, 405, turn on, or remove magazine from flight recorder.
(7) If first officer's pitot-static probe (upper right) is to be checked for leakage:
(a) Temporarily seal static ports on No. 1 auxiliary pitot-static probe (lower left).
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 AMY LEAD TO LOSS OF SAFE FLIGHT.
(b)
Temporarily seal pitot pressure chamber drain hole in first officer's pitot-static probe (upper right).
(c)
Wet pitot-static probe test adapter and install on upper right pitot-static probe.
CAUTION: OBSERVE CAUTIONS AS STATED IN STEP D.(6)(c).
_______
(d)
Connect pitot-static probe to cutoff valves through system test gages and flow restrictors.
(e)
Disconnect static line from differential pressure indicator.
EFFECTIVITY
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(f) Disconnect static line from right elevator feel computer, if connected.
(8) If No. 1 auxiliary pitot-static probe (lower left) is to be checked for leakage:
(a) Temporarily seal static ports on first officer's pitot-static probe (upper right).
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 AMY LEAD TO LOSS OF SAFE FLIGHT.
(b)
Temporarily seal pitot pressure chamber drain hole in No. 1 auxiliary pitot-static probe (lower left).
(c)
Wet pitot-static probe test adapter and install on lower left pitot-static probe.
CAUTION: OBSERVE CAUTIONS AS STATED IN STEP D.(6)(c).
_______
(d)
Connect pitot-static probe to cutoff valves through system test gages and flow restrictors.
(e)
Disconnect static line from differential pressure indicator.
(f)
On AZ 201-202, 209-211; IB 401-402, 405, turn on, or remove magazine from flight recorder.
(g)
Disconnect static line from right elevator feel computer, if connected.
(h)
Disconnect pitot line from left elevator feel computer and stabilizer control module.
(9) If No. 2 auxiliary pitot-static probe (lower right) is to be checked for leakage:
(a) Temporarily seal static ports on captain's pitot-static probe (upper left).
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 AMY LEAD TO LOSS OF SAFE FLIGHT.
(b)
Temporarily seal pitot pressure chamber drain hole in No. 2 auxiliary pitot-static probe (lower right).
(c)
Wet pitot-static probe test adapter and install on lower right pitot-static probe.
CAUTION: OBSERVE CAUTIONS AS STATED IN STEP D.(6)(c).
_______
(d) Connect pitot-static probe to cutoff valves through system test gages and flow restrictors.
EFFECTIVITY
ALL 18 Page 503 Apr 25/9834-11-01
(e)
On AZ 201-202, 209-211; IB 401-402, 405, turn on, or remove magazine from flight recorder (Ref 31-31-01).
(f)
Disconnect static line from left elevator feel computer, if connected.
(g)
Disconnect pitot line from right elevator feel computer and stabilizer control module.
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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(50)
