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9/27/01 b. After the conclusion of the leak test, return the system to its normal flying configu ration. Remove tape from static ports and pitot drain holes and replace the drain plug. 12-58. STATIC SYSTEM TESTS must comply with the static system tests required by 14 CFR 91.411 and be performed by an appro priately-rated repair station with the appropri ate test equipment. If the manufacturer has not issued instructions for testing static systems, the following may be used: a. Connect the test equipment directly to the static ports, if practicable. Otherwise, connect to a static system drain or tee connec tion and seal off the static ports. If the test equipment is connected to the static system at any point other than the static port, it should be made at a point where the connection may be readily inspected for system integrity. Observe maintenance precautions given in paragraph 12-60 of this section. b. Do not blow air through the line to ward the instrument panel. This may seriously damage the instruments. Be sure to disconnect the instrument lines so no pressure can reach the instruments. c. Apply a vacuum equivalent to 1,000 feet altitude, (differential pressure of approxi mately 1.07 inches of mercury or 14.5 inches of water) and hold. d. After 1 minute, check to see that the leak has not exceeded the equivalent of 100 feet of altitude (decrease in differential pres sure of approximately 0.0105 inches of mer cury or 1.43 inches of water). 12-59. TEST PITOT SYSTEM in accor dance with the aircraft manufacturer’s instruc tions. If the manufacturer has not issued in AC 43.13-1B CHG 1 structions for testing pitot systems, the fol lowing may be used: a. Seal the drain holes and connect the pitot pressure openings to a tee to which a source of pressure and manometer or reliable indicator is connected. b. Restrain hoses that can whip due to applied pressure. c. Apply pressure to cause the airspeed indicator to indicate 150 knots (differential pressure 1.1 inches of mercury or 14.9 inches of water), hold at this point and clamp off the source of pressure. After 1 minute, the leakage should not exceed 10 knots (decrease in differ ential pressure of approximately 0.15 inches of mercury or 2.04 inches of water). CAUTION: To avoid rupturing the diaphragm of the airspeed indicator, apply pressure slowly and do not build up excessive pressure in the line. Release pressure slowly to avoid dam- aging the airspeed indicator. d. If the airspeed indicator reading de- clines, check the system for leaky hoses and loose connections. e. Inspect the hoses for signs of deterio ration, particularly at bends and at the connec tion points to the pitot mast and airspeed indi cator. Replace hoses that are cracked or hard ened with identical specification hoses. Any time a hose is replaced, perform a pressure check. Warning: Do not apply suction to pi- tot lines. 12-60. MAINTENANCE PRECAUTIONS. Observe the following precautions in all pitot static system leak testing: Par 12-57 Page 12-21PDF Image | AFS-640
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