(1)
The instrument that most e.ectively indicates the attitude must be on the panelinthetop centerposition;

(2)
The instrument that most e.ectively indicates airspeed must be adjacent to and directly to the left of the instrument in the top center position;

(3)
The instrument that most e.ectively indicates altitude must be adjacent to anddirectly tothe right of theinstrumentinthetop centerposition; and

(4)
The instrument that most e.ectively indicates direction of .ight, other than the magneticdirectionindicator requiredbySec.23.1303(c), mustbe adjacent to anddirectly belowtheinstrumentinthetop centerposition; and

(5)
Electronic display indicators may be used for compliance with paragraphs (d)(1)through(d)(4) of this section when suchdisplays comply with require-ments in Sec. 23.1311.

(e)
If avisualindicatorisprovided toindicate malfunctionof aninstrument,it mustbe e.ective under all probable cockpit lighting conditions.

Amdt. 23-49, E.. 03/11/96
FAR 23.1322 : Warning, caution, and advisory lights.
If warning, 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.

(e)
[E.ective under all probable cockpit lightingconditions.]

Amdt. 23-43, E.. 05/10/93
′
Elodie Roux. Septembre 2003
Subpart F : Equipment
FAR 23.1323 : 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)
Eachairspeed systemmustbecalibratedin .ighttodeterminethesystemerror.The system error, including position error, but excluding the airspeed indicator instru-ment calibration error, may not exceed three percent of the calibrated airspeed or .ve knots, whichever is greater, throughout the following speed ranges :

(1)
1.3VS1 to VMO/MMO or VNE, whichever is appropriate with .aps retracted.

(2)
1.3VS1 to VFE with .aps extended.

(c)
[Thedesign andinstallation ofeach airspeedindicating system mustprovidepositive drainage of moisture from the pitot static plumbing.

(d)
If certi.cation for instrument .ight rules or .ight in icing conditions is requested, each airspeed system must have a heated pitot tube or an equivalent means of preventing malfunction due to icing.

(e)
In addition,for commuter categoryairplanes, the airspeedindicating system mustbe calibrated todeterminethe system errorduring the accelerate-takeo.ground run. The ground run calibration must be obtained between 0.8 of the minimum value of V1 and 1.2 times the maximum value of V1, considering the approved ranges of altitude and weight. The ground run calibration must be determined assuming an engine failure at the minimum value of V1.

(f)
For commuter category airplanes, where duplicate airspeed indicators are required, their respective pitot tubes must be far enough apart to avoid damage to both tubes in a collision with a bird.]

Amdt. 23-49, E.. 03/11/96
FAR 23.1325 : Static pressure system.
(a)
Each instrument provided with static pressure case connections must be vented so that the in.uence of airplane speed, the opening and closing of windows, air.ow variations, moisture, or other foreign matter will least a.ect the accuracy of the instruments except as notedinparagraph(b)(3) of this section.
　
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本文鏈接地址：FAA規章 美國聯邦航空規章 Federal Aviation Regulations 2(84)