(d)
Eachpressure altimeter mustbe approved and mustbe calibrated toindicatepres-sure altitude in a standard atmosphere, with a minimum practicable calibration error when the corresponding static pressures are applied.
(e)
Each system must be designed and installed so that the error in indicated pressure altitude, at sealevel, with a standard atmosphere, excludinginstrument calibration error, does not result in an error of more than ±30 feet per 100 knots speed for the appropriate con.guration in the speed range between [1.23 VSRO] with .aps extended and[1.7VSR1], with .aps retracted. However, the error need not be less than ±30 feet.
(f)
Ifanaltimetersystemif.tted with adevicethatprovidescorrectionstothealtimeter indication, the device must be designed andinstalledin such manner that it canbe bypassed when it malfunctions, unless an alternate altimeter system is provided. Each correction device must be .tted with a means for indicating the occurrence of reasonably probable malfunctions, including power failure, to the .ight crew. The indicating means must be e.ective for any cockpit lighting condition likely to occur.
(g)
Except asprovidedinparagraph(h) 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 sourceis selected,the otherisblocked o.; and
(2)
Both sources cannot be blocked o. simultaneously.
(h)
For unpressurized airplanes, paragraph (g)(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.
Amdt. 25-108, E.. 12/26/2002
FAR 25.1326 : Pitot heat indication systems.
[Ifa .ightinstrumentpitotheating systemisinstalled,anindicationsystemmustbe provided to indicate to the .ight crew when that pitot heating system is not operating. The indication system must comply with the following requirements :
(a)
The indication provided must incorporate an amber light that is in clear view of a .ight crewmember.
(b)
The indication provided must be designed to alert the .ight crew if either of the following conditions exist :
(1)
The pitot heating system is switched ”o.”.
(2)
Thepitotheating systemisswitched ”on” and anypitottubeheating element
is inoperative.] Amdt. 25-43, E.. 4/12/78
FAR 25.1327 : Magnetic direction indicator.
(a)
Each magnetic direction indicator must be installed so that its accuracy is not ex-cessively a.ected by the airplane’s vibration or magnetic .elds.
(b)
Thecompensatedinstallationmay nothaveadeviation,inlevel .ight,greaterthan 10 degrees on any heading.
FAR 25.1329 : Automatic pilot system.
(a)
Each automatic pilot system must be approved and must be designed so that the automatic pilot can be quickly and positively disengaged by the pilots to prevent it from interfering with their control of the airplane.
(b)
Unless thereis automatic synchronization, eachsystem musthave a means to readily indicatetothepilotthealignmentof theactuatingdeviceinrelationtothe control system it operates.
(c)
Each manually operated control for the system must be readily accessible to the pilots.
(d)
Quick release(emergency) controls mustbe onboth control wheels, on the side of each wheel opposite the throttles.
(e)
Attitude controls must operate in the plane and sense of motion speci.ed in Sec.
25.777(b) and Sec. 25.779(a)for cockpit controls.The direction of motion must be plainly indicated on, or adjacent to, each control.
(f)
The system must be designed and adjusted so that, within the range of adjustment available to the humanpilot, it cannotproduce hazardousloads on the airplane, or createhazardousdeviationsinthe .ightpath,underany conditionof .ightappro-priate to its use either during normal operation, or in the event of a malfunction, assuming that corrective actionbegins within a reasonableperiod oftime.
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 4(20)
