Federal Aviation Administration, DOT § 25.1303

all of the tasks associated with the sys- § 25.1303 Flight and navigation instru- tems’ and equipment’s intended func- ments. tions. Such installed equipment and (a) The following flight and naviga- systems must meet the following re- tion instruments must be installed so quirements: that the instrument is visible from (a) Flight deck controls must be in- each pilot station: stalled to allow accomplishment of all (1) A free air temperature indicator the tasks required to safely perform or an air-temperature indicator which the equipment’s intended function, and provides indications that are convert- information must be provided to the ible to free-air temperature. flightcrew that is necessary to accom- (2) A clock displaying hours, min- plish the defined tasks. utes, and seconds with a sweep-second (b) Flight deck controls and informa- pointer or digital presentation. tion intended for the flightcrew’s use (3) A direction indicator (non- must: stabilized magnetic compass). (1) Be provided in a clear and unam- (b) The following flight and naviga- biguous manner at a resolution and tion instruments must be installed at precision appropriate to the task; each pilot station: (2) Be accessible and usable by the (1) An airspeed indicator. If airspeed flightcrew in a manner consistent with limitations vary with altitude, the in- the urgency, frequency, and duration of dicator must have a maximum allow- their tasks; and able airspeed indicator showing the (3) Enable flightcrew awareness, if variation of VMO with altitude. awareness is required for safe oper- (2) An altimeter (sensitive). ation, of the effects on the airplane or (3) A rate-of-climb indicator (vertical systems resulting from flightcrew ac- speed). tions. (4) A gyroscopic rate-of-turn indi- (c) Operationally-relevant behavior cator combined with an integral slip- of the installed equipment must be: skid indicator (turn-and-bank indi- (1) Predictable and unambiguous; and cator) except that only a slip-skid indi- (2) Designed to enable the flightcrew cator is required on large airplanes to intervene in a manner appropriate with a third attitude instrument sys- to the task. tem useable through flight attitudes of ° (d) To the extent practicable, in- 360 of pitch and roll and installed in accordance with § 121.305(k) of this stalled equipment must incorporate title. means to enable the flightcrew to man- (5) A bank and pitch indicator (gyro- age errors resulting from the kinds of scopically stabilized). flightcrew interactions with the equip- (6) A direction indicator (gyroscop- ment that can be reasonably expected ically stabilized, magnetic or non- in service. This paragraph does not magnetic). apply to any of the following: (c) The following flight and naviga- (1) Skill-related errors associated tion instruments are required as pre- with manual control of the airplane; scribed in this paragraph: (2) Errors that result from decisions, (1) A speed warning device is required actions, or omissions committed with for turbine engine powered airplanes malicious intent; and for airplanes with VMO/MMO greater (3) Errors arising from a crew- than 0.8 VDF/MDF or 0.8 V D/MD. The member’s reckless decisions, actions, speed warning device must give effec- or omissions reflecting a substantial tive aural warning (differing distinc- disregard for safety; and tively from aural warnings used for (4) Errors resulting from acts or other purposes) to the pilots, whenever threats of violence, including actions the speed exceeds VMO plus 6 knots or taken under duress. MMO +0.01. The upper limit of the pro- duction tolerance for the warning de- [Doc. No. FAA–2010–1175, 78 FR 25846, May 3, 2013] vice may not exceed the prescribed warning speed.

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(2) A machmeter is required at each (7) A device that indicates, to the pilot station for airplanes with com- flight crew (during flight), any change pressibility limitations not otherwise in the power output, for each engine indicated to the pilot by the airspeed with— indicating system required under para- (i) An automatic propeller feathering graph (b)(1) of this section. system, whose operation is initiated by a power output measuring system; or [Amdt. 25–23, 35 FR 5678, Apr. 8, 1970, as amended by Amdt. 25–24, 35 FR 7108, May 6, (ii) A total engine piston displace- 1970; Amdt. 25–38, 41 FR 55467, Dec. 20, 1976; ment of 2,000 cubic inches or more. Amdt. 25–90, 62 FR 13253, Mar. 19, 1997] (8) A means to indicate to the pilot when the propeller is in reverse pitch, § 25.1305 Powerplant instruments. for each reversing propeller. The following are required power- (c) For turbine engine-powered air- plant instruments: planes. In addition to the powerplant (a) For all airplanes. (1) A fuel pres- instruments required by paragraph (a) sure warning means for each engine, or of this section, the following power- a master warning means for all engines plant instruments are required: with provision for isolating the indi- (1) A gas temperature indicator for vidual warning means from the master each engine. warning means. (2) A fuel flowmeter indicator for (2) A fuel quantity indicator for each each engine. fuel tank. (3) A tachometer (to indicate the (3) An oil quantity indicator for each speed of the rotors with established oil tank. limiting speeds) for each engine. (4) An oil pressure indicator for each (4) A means to indicate, to the flight independent pressure oil system of crew, the operation of each engine each engine. starter that can be operated continu- (5) An oil pressure warning means for ously but that is neither designed for each engine, or a master warning continuous operation nor designed to means for all engines with provision prevent hazard if it failed. for isolating the individual warning (5) An indicator to indicate the func- means from the master warning means. tioning of the powerplant ice protec- (6) An oil temperature indicator for tion system for each engine. each engine. (6) An indicator for the fuel strainer (7) Fire-warning devices that provide or filter required by § 25.997 to indicate visual and audible warning. the occurrence of contamination of the (8) An augmentation liquid quantity strainer or filter before it reaches the indicator (appropriate for the manner capacity established in accordance in which the liquid is to be used in op- with § 25.997(d). eration) for each tank. (7) A warning means for the oil (b) For reciprocating engine-powered strainer or filter required by § 25.1019, if airplanes. In addition to the powerplant it has no bypass, to warn the pilot of instruments required by paragraph (a) the occurrence of contamination of the of this section, the following power- strainer or filter screen before it plant instruments are required: reaches the capacity established in ac- (1) A carburetor air temperature indi- cordance with § 25.1019(a)(2). cator for each engine. (8) An indicator to indicate the prop- (2) A cylinder head temperature indi- er functioning of any heater used to cator for each air-cooled engine. prevent ice clogging of fuel system (3) A manifold pressure indicator for components. each engine. (d) For turbojet engine powered air- (4) A fuel pressure indicator (to indi- planes. In addition to the powerplant cate the pressure at which the fuel is instruments required by paragraphs (a) supplied) for each engine. and (c) of this section, the following (5) A fuel flowmeter, or fuel mixture powerplant instruments are required: indicator, for each engine without an (1) An indicator to indicate thrust, or automatic altitude mixture control. a parameter that is directly related to (6) A tachometer for each engine. thrust, to the pilot. The indication

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