(b)  
Remove adapter and vinyl adhesive tape from lower left pitot-static probe.

 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 THAT NO PIECES OF COLORED
   TAPE REMAIN ON PROBE.
 (c) Test first officer's pitot system for leakage.
 CAUTION: TO PREVENT INSTRUMENT/EQUIPMENT DAMAGE, KEEP RATE
_______ OF PITOT PRESSURE CHANGE BELOW 300 KNOTS PER MINUTE AND DIFFERENTIAL PRESSURE BETWEEN 0 AND 10 INCHES OF MERCURY.
 EFFECTIVITY
 
 ALL  29.1 Page 513  Oct 25/9834-11-00
 1)  Use adapter and drain seal (similar to paragraph (2)(a)) to attach upper right pitot-static probe to pneumatic test unit.
 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 GYLCOL 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.
 2)  Repeat steps (b) 2) thru 4).
 3)  Remove adapter and vinyl adhesive tape from upper right pitot-static probe.
 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.
 
 (d) Test auxiliary pitot system No. 2 for leakage.
 CAUTION: TO PREVENT INSTRUMENT/EQUIPMENT DAMAGE, KEEP RATE
_______ OF PITOT PRESSURE CHANGE BELOW 300 KNOTS PER MINUTE AND DIFFERENTIAL PRESSURE BETWEEN 0 AND 10 INCHES OF MERCURY.
 1)  Use adapter and drain seal (similar to paragrapn (2)(a)) to attach lower right pitot-static probe to pneumatic test unit.
 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.
 2)  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,
 EFFECTIVITY
 
 ALL  28.1 Page 514  Oct 25/9834-11-00
 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 (b) 2) thru 4). 4) Remove adapter and vinyl adhesive tape from lower right pitot-static probe.
 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. 
 (4) Test Static Systems
 (a) Connect test equipment as follows: (Fig. 501)
 CAUTION: TO PREVENT PROBE MISALIGNMENT, TEST HOSES AND
_______ ADAPTERS MUST BE SUPPORTED IN SUCH A WAY AS TO ADD NO EXTRA WEIGHT ON PROBES.
 1)  Connect static (vacuum) source in pneumatic test unit through static control valve to three static cutoff valves.
 2)  Using static system pitot-static probe adapters, connect forward set of static ports (S1) on upper right probe and aft set of static ports (S2) on lower right probe to two of static cutoff valves through static system test gages and flow restrictors.
 3)  Using flush static port adapter, connect right alternate static port to third static cutoff valve through a static system test gage and flow restrictor.
 4)  Seal these locations with vinyl adhesive tape:
 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.
　
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