(b)
For each multiengine rotorcraft, identical powerplant instruments must be located so as to prevent confusion as to which engine each instrument relates.

(c)
Instrument panel vibration may not damage, or impair the readability or accuracy of, any instrument.

(d)
[If a visual indicator is provided to indicate malfunction of an instrument, it must be e.ective under all probable cockpit lighting conditions.]

Amdt. 27-13, E.. 9/1/77
FAR 27.1322 : Warning,caution,and advisory lights
[Ifwarning, caution, or advisory lights are installed in the cockpit, they must, unless otherwise approved by the Administrator, be–
(a)
Red, for warning lights (lights indicating a hazard which may require immediate corrective action);

(b)
Amber,forcautionlights(lightsindicatingthepossible needforfuture corrective action);

(c)
Green, for safe operation lights; and

(d)
Any other color,including white,forlights notdescribedinparagraphs(a) through (c)of this section,provided the colordi.ers su.ciently fromthe colorsprescribed inparagraphs(a) through(c) of this sectionto avoidpossible confusion.]

Amdt. 27-11, E.. 2/1/77
′
Elodie Roux. Septembre 2003
Subpart F–Equipment
FAR 27.1323 : Airspeed indicating system
(a)
[Each airspeed indicating instrument must be calibrated to indicate true airspeed (at sea levelwith a standard atmosphere) with a minimum practicable instrument calibration error whenthe correspondingpitot and staticpressures are applied.

(b)
The airspeed indicating system must be calibrated in .ight at forward speeds of 20 knots and over.

(c)
]Ateachforward speed above80percent ofthe climbout speed,the airspeedindicator must indicate true airspeed, at sea level with a standard atmosphere, to within an allowable installation error of not more than the greater of–

(1)
±3 percent of the calibrated airspeed; or

(2)
5 knots.

Amdt. 27-13, E.. 9/1/77
FAR27.1325 :[Staticpressure systems.]
(a)
[Eachinstrumentwith static air case connections mustbe vented sothatthein.uence of rotorcraft speed, the opening and closing of windows, air.ow variation, and moisture or other foreign matter does not seriously a.ect its accuracy.

(b)
Each static pressure port must be designed and located in such manner that the correlation between air pressure in the static pressure system and true ambient atmospheric static pressure is not altered when the rotorcraft encounters icing conditions.An anti-icing means or an alternate source of staticpressure maybe 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 primary static system by more than 50 feet, a correction card must be provided 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 sourceis selected,the otherisblocked o.; and

(2)
Both sources cannot be blocked o. simultaneously.

(d)
For unpressurized rotorcraft,paragraph(c)(1) ofthis sectiondoes not applyifit canbe demonstrated that the staticpressure system calibration, when either static pressuresourceisselected,isnotchangedby the other staticpressuresourcebeing open or blocked.]

Amdt. 27-13, E.. 9/1/77
FAR 27.1327 : Magnetic direction indicator
(a) [Except asprovidedinparagraph(b)of this section–
(1)
Each magneticdirectionindicatormustbeinstalled sothatits accuracyisnot excessively a.ectedby therotorcraft’svibrationormagnetic .elds; and
　
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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(122)