(b)
If a static pressure system is necessary for the functioning of instruments, systems, ordevices,it must comply withtheprovisions ofparagraphs(b)(1) through(3) of this section.
(1)
The design and installation of a static pressure system must be such that–
(i)
Positive drainage of moisture is provided;
(ii)
Cha.ng of the tubing, and excessive distortion or restriction at bends in the tubing, is avoided; and
(iii) The materials used are durable, suitable for the purpose intended, and protected against corrosion.
(2)
A proof test must be conducted to demonstrate the integrity of the static pressure system in the following manner :
(i)
Unpressurized airplanes. Evacuate the staticpressure system to apressure di.erential of approximately 1 inch of mercury or to a reading on the altimeter, 1,000 feet above the aircraft elevation at the time of the test. Without additionalpumpingfor aperiod of1 minute, theloss ofindicated altitude must not exceed 100 feet on the altimeter.
(ii)
Pressurized airplanes. Evacuate the static pressure system until a pres-sure di.erential equivalent to the maximum cabin pressure di.erential for which the airplane is type certi.cated is achieved. Without additio-nal pumping for a period of 1 minute, the loss of indicated altitude must not exceed 2 percent of the equivalent altitude of the maximum cabin di.erential pressure or 100 feet, whichever is greater.
(3) If a static pressure system is provided for any instrument, device, or system requiredby the operating rulesof this chapter, each staticpressureport must bedesignedorlocatedin such mannerthatthe correlationbetween airpressure in the static pressure system and true ambient atmospheric static pressure is not altered when the aircraft encountersicing conditions.An anti-icing means or an alternate source of static pressure may be used in showing compliance with this requirement. If the reading of the altimeter, when on the alternate static pressure system di.ers from the reading of the altimeter when on the primarystatic systemby morethan50feet, a correction card mustbeprovided for the alternate static system.
(c)
Except asprovidedinparagraph(d) ofthis section,ifthe staticpressure system incorporatesboth aprimary and an alternatestaticpressuresource,the meansfor selecting one or the other source must be designed so that–
(1)
When either source is selected, the other is blocked o.; and
(2)
Both sources cannot be blocked o. simultaneously.
(d)
For unpressurized airplanes, paragraph (c)(1) of this section does not apply if it canbe demonstrated that the staticpressure system calibration, when either static pressuresourceisselected,isnotchangedby the other staticpressuresourcebeing open or blocked.
(e)
[Each static pressure system must be calibrated in .ight to determine the system error.The system error,inindicatedpressure altitude, at sea-level, with a standard atmosphere, excluding instrument calibration error, may not exceed ±30 feet per 100knotspeedfor the appropriate con.gurationin the speed rangebetween1.3VS0 with .aps extended, and 1.8VS1 with .aps retracted. However, the error need not be less than 30 feet.
(f)
[Reserved]]
(g)
Forairplanesprohibitedfrom .ightininstrument meteorological oricing conditions, in accordance withSec. 23.1559(b) ofthispart,paragraph(b)(3) ofthis section does not apply.
Amdt. 23-50, E.. 03/12/96
FAR23.1326 :[Pitotheatindication systems.]
[If a .ight instrument pitot heating system is installed to meet the requirements speci.ed in Sec. 23.1323(d), an indication system must be provided to indicate to the .ight crew whenthatpitotheating systemis not operating.Theindication system must comply with the following requirements :
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Elodie Roux. Septembre 2003
Subpart F : Equipment
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本文链接地址：FAA规章 美国联邦航空规章 Federal Aviation Regulations 2(85)
