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Federal Aviation Administration, DOT § 23.1311

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Federal Aviation Administration, DOT § 23.1311 Federal Aviation Administration, DOT § 23.1311 INSTRUMENTS: INSTALLATION (b) The electronic display indicators, including their systems and installa- § 23.1311 Electronic display instru- tions, and considering other airplane ment systems. systems, must be designed so that one (a) Electronic display indicators, in- display of information essential for cluding those with features that make continued safe flight and landing will isolation and independence between remain available to the crew, without powerplant instrument systems im- need for immediate action by any pilot practical, must: for continued safe operation, after any (1) Meet the arrangement and visi- single failure or probable combination bility requirements of § 23.1321. of failures. (2) Be easily legible under all lighting (c) As used in this section, ‘‘instru- conditions encountered in the cockpit, ment’’ includes devices that are phys- including direct sunlight, considering ically contained in one unit, and de- the expected electronic display bright- vices that are composed of two or more ness level at the end of an electronic physically separate units or compo- display indictor’s useful life. Specific nents connected together (such as a re- limitations on display system useful mote indicating gyroscopic direction life must be contained in the Instruc- indicator that includes a magnetic tions for Continued Airworthiness re- sensing element, a gyroscopic unit, an quired by § 23.1529. amplifier, and an indicator connected (3) Not inhibit the primary display of together). As used in this section, attitude, airspeed, altitude, or power- ‘‘primary’’ display refers to the display plant parameters needed by any pilot to set power within established limita- of a parameter that is located in the tions, in any normal mode of oper- instrument panel such that the pilot ation. looks at it first when wanting to view (4) Not inhibit the primary display of that parameter. engine parameters needed by any pilot [Doc. No. 27806, 61 FR 5168, Feb. 9, 1996] to properly set or monitor powerplant limitations during the engine starting EFFECTIVE DATE NOTE: By Amdt. 23–62, 76 FR 75760, Dec. 2, 2011, § 23.1311 was amended mode of operation. by revising paragraphs (a)(5), (a)(6), (a)(7), (5) Have an independent magnetic di- and paragraph (b), effective Jan. 31, 2012. For rection indicator and either an inde- the convenience of the user, the revised text pendent secondary mechanical altim- is set forth as follows: eter, airspeed indicator, and attitude instrument or individual electronic § 23.1311 Electronic display instrument sys- display indicators for the altitude, air- tems. speed, and attitude that are inde- (a) * * * pendent from the airplane’s primary (5) For certification for Instrument Flight electrical power system. These sec- Rules (IFR) operations, have an independent ondary instruments may be installed in magnetic direction indicator and either an independent secondary mechanical altim- panel positions that are displaced from eter, airspeed indicator, and attitude instru- the primary positions specified by ment or an electronic display parameters for § 23.1321(d), but must be located where the altitude, airspeed, and attitude that are they meet the pilot’s visibility require- independent from the airplane’s primary ments of § 23.1321(a). electrical power system. These secondary in- (6) Incorporate sensory cues for the struments may be installed in panel posi- pilot that are equivalent to those in tions that are displaced from the primary po- the instrument being replaced by the sitions specified by § 23.1321(d), but must be electronic display indicators. located where they meet the pilot’s visibility (7) Incorporate visual displays of in- requirements of § 23.1321(a). strument markings, required by (6) Incorporate sensory cues that provide a quick glance sense of rate and, where appro- §§ 23.1541 through 23.1553, or visual dis- priate, trend information to the parameter plays that alert the pilot to abnormal being displayed to the pilot. operational values or approaches to es- (7) Incorporate equivalent visual displays tablished limitation values, for each of the instrument markings required by parameter required to be displayed by §§ 23.1541 through 23.1553, or visual displays this part. that alert the pilot to abnormal operational 305 VerDate Mar<15>2010 11:30 Mar 22, 2012 Jkt 226044 PO 00000 Frm 00315 Fmt 8010 Sfmt 8003 Y:\SGML\226044.XXX 226044 pmangrum on DSK3VPTVN1PROD with CFR § 23.1321 14 CFR Ch. I (1–1–12 Edition) values or approaches to established limita- adjacent to and directly below the in- tion values, for each parameter required to strument in the top center position; be displayed by this part. and (b) The electronic display indicators, in- cluding their systems and installations, and (5) Electronic display indicators may considering other airplane systems, must be be used for compliance with paragraphs designed so that one display of information (d)(1) through (d)(4) of this section essential for continued safe flight and land- when such displays comply with re- ing will be available within one second to the quirements in § 23.1311. crew by a single pilot action or by automatic (e) If a visual indicator is provided to means for continued safe operation, after indicate malfunction of an instrument, any single failure or probable combination of it must be effective under all probable failures. cockpit lighting conditions. * * * * * [Doc. No. 4080, 29 FR 17955, Dec. 18, 1964, as amended by Amdt. 23–14, 38 FR 31824, Nov. 19, § 23.1321 Arrangement and visibility. 1973; Amdt. 23–20, 42 FR 36968, July 18, 1977; Amdt. 23–41, 55 FR 43310, Oct. 26, 1990; 55 FR (a) Each flight, navigation, and pow- 46888, Nov. 7, 1990; Amdt. 23–49, 61 FR 5168, erplant instrument for use by any re- Feb. 9, 1996] quired pilot during takeoff, initial climb, final approach, and landing § 23.1322 Warning, caution, and advi- must be located so that any pilot seat- sory lights. ed at the controls can monitor the air- If warning, caution, or advisory plane’s flight path and these instru- lights are installed in the cockpit, they ments with minimum head and eye must, unless otherwise approved by the movement. The powerplant instru- Administrator, be— ments for these flight conditions are (a) Red, for warning lights (lights in- those needed to set power within pow- dicating a hazard which may require erplant limitations. immediate corrective action); (b) For each multiengine airplane, (b) Amber, for caution lights (lights identical powerplant instruments must indicating the possible need for future be located so as to prevent confusion as corrective action); to which engine each instrument re- (c) Green, for safe operation lights; lates. and (c) Instrument panel vibration may (d) Any other color, including white, not damage, or impair the accuracy of, for lights not described in paragraphs any instrument. (a) through (c) of this section, provided (d) For each airplane, the flight in- the color differs sufficiently from the struments required by § 23.1303, and, as colors prescribed in paragraphs (a) applicable, by the operating rules of through (c) of this section to avoid pos- this chapter, must be grouped on the sible confusion. instrument panel and centered as near- (e) Effective under all probable cock- ly as practicable about the vertical pit lighting conditions. plane of each required pilot’s forward vision. In addition: [Amdt. 23–17, 41 FR 55465, Dec. 20, 1976, as (1) The instrument that most effec- amended by Amdt. 23–43, 58 FR 18976, Apr. 9, tively indicates the attitude must be 1993] on the panel in the top center position; (2) The instrument that most effec- § 23.1323 Airspeed indicating system. tively indicates airspeed must be adja- (a) Each airspeed indicating instru- cent to and directly to the left of the ment must be calibrated to indicate instrument in the top center position; true airspeed (at sea level with a stand- (3) The instrument that most effec- ard atmosphere) with a minimum prac- tively indicates altitude must be adja- ticable instrument calibration error cent to and directly to the right of the when the corresponding pitot and stat- instrument in the top center position; ic pressures are applied. (4) The instrument that most effec- (b) Each airspeed system must be tively indicates direction of flight, calibrated in flight to determine the other than the magnetic direction indi- system error. The system error, includ- cator required by § 23.1303(c), must be ing position error, but excluding the 306 VerDate Mar<15>2010 11:30 Mar 22, 2012 Jkt 226044 PO 00000 Frm 00316 Fmt 8010 Sfmt 8010 Y:\SGML\226044.XXX 226044 pmangrum on DSK3VPTVN1PROD with CFR Federal Aviation Administration, DOT § 23.1325 airspeed indicator instrument calibra- (1) From 0.8 of the minimum value of V1 to tion error, may not exceed three per- the maximum value of V2, considering the cent of the calibrated airspeed or five approved ranges of altitude and weight; and knots, whichever is greater, through- (2) The ground run calibration must be de- termined assuming an engine failure at the out the following speed ranges: minimum value of V1. (1) 1.3 VS1 to VMO/MMO or VNE, which- ever is appropriate with flaps re- tracted. * * * * * (2) 1.3 V 1 to V with flaps extended. S FE § 23.1325 Static pressure system. (c) The design and installation of each airspeed indicating system must (a) Each instrument provided with provide positive drainage of moisture static pressure case connections must from the pitot static plumbing. be so vented that the influence of air- (d) If certification for instrument plane speed, the opening and closing of flight rules or flight in icing conditions windows, airflow variations, moisture, is requested, each airspeed system or other foreign matter will least af- must have a heated pitot tube or an fect the accuracy of the instruments equivalent means of preventing mal- except as noted in paragraph (b)(3) of function due to icing.
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