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338 

14 CFR Ch. I (1–1–24 Edition) 

§ 25.1301 

Subpart F—Equipment 

G

ENERAL

 

§ 25.1301

Function and installation. 

(a) Each item of installed equipment 

must— 

(1) Be of a kind and design appro-

priate to its intended function; 

(2) Be labeled as to its identification, 

function, or operating limitations, or 
any applicable combination of these 
factors; 

(3) Be installed according to limita-

tions specified for that equipment; and 

(4) Function properly when installed. 
(b) EWIS must meet the require-

ments of subpart H of this part. 

[Doc. No. 5066, 29 FR 18333, Dec. 24, 1964, as 
amended by Amdt. 25–123, 72 FR 63405, Nov. 8, 
2007] 

§ 25.1302

Installed systems and equip-

ment for use by the flightcrew. 

This section applies to installed sys-

tems and equipment intended for 
flightcrew members’ use in operating 
the airplane from their normally seat-
ed positions on the flight deck. The ap-
plicant must show that these systems 
and installed equipment, individually 
and in combination with other such 
systems and equipment, are designed 
so that qualified flightcrew members 
trained in their use can safely perform 
all of the tasks associated with the sys-
tems’ and equipment’s intended func-
tions. Such installed equipment and 
systems must meet the following re-
quirements: 

(a) Flight deck controls must be in-

stalled to allow accomplishment of all 
the tasks required to safely perform 
the equipment’s intended function, and 
information must be provided to the 
flightcrew that is necessary to accom-
plish the defined tasks. 

(b) Flight deck controls and informa-

tion intended for the flightcrew’s use 
must: 

(1) Be provided in a clear and unam-

biguous manner at a resolution and 
precision appropriate to the task; 

(2) Be accessible and usable by the 

flightcrew in a manner consistent with 
the urgency, frequency, and duration of 
their tasks; and 

(3) Enable flightcrew awareness, if 

awareness is required for safe oper-

ation, of the effects on the airplane or 
systems resulting from flightcrew ac-
tions. 

(c) Operationally-relevant behavior 

of the installed equipment must be: 

(1) Predictable and unambiguous; and 
(2) Designed to enable the flightcrew 

to intervene in a manner appropriate 
to the task. 

(d) To the extent practicable, in-

stalled equipment must incorporate 
means to enable the flightcrew to man-
age errors resulting from the kinds of 
flightcrew interactions with the equip-
ment that can be reasonably expected 
in service. This paragraph does not 
apply to any of the following: 

(1) Skill-related errors associated 

with manual control of the airplane; 

(2) Errors that result from decisions, 

actions, or omissions committed with 
malicious intent; 

(3) Errors arising from a crew-

member’s reckless decisions, actions, 
or omissions reflecting a substantial 
disregard for safety; and 

(4) Errors resulting from acts or 

threats of violence, including actions 
taken under duress. 

[Doc. No. FAA–2010–1175, 78 FR 25846, May 3, 
2013] 

§ 25.1303

Flight and navigation instru-

ments. 

(a) The following flight and naviga-

tion instruments must be installed so 
that the instrument is visible from 
each pilot station: 

(1) A free air temperature indicator 

or an air-temperature indicator which 
provides indications that are convert-
ible to free-air temperature. 

(2) A clock displaying hours, min-

utes, and seconds with a sweep-second 
pointer or digital presentation. 

(3) A direction indicator (non-

stabilized magnetic compass). 

(b) The following flight and naviga-

tion instruments must be installed at 
each pilot station: 

(1) An airspeed indicator. If airspeed 

limitations vary with altitude, the in-
dicator must have a maximum allow-
able airspeed indicator showing the 
variation of V

MO

with altitude. 

(2) An altimeter (sensitive). 
(3) A rate-of-climb indicator (vertical 

speed). 

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339 

Federal Aviation Administration, DOT 

§ 25.1305 

(4) A gyroscopic rate-of-turn indi-

cator combined with an integral slip- 
skid indicator (turn-and-bank indi-
cator) except that only a slip-skid indi-
cator is required on large airplanes 
with a third attitude instrument sys-
tem useable through flight attitudes of 
360

° 

of pitch and roll and installed in 

accordance with § 121.305(k) of this 
title. 

(5) A bank and pitch indicator (gyro-

scopically stabilized). 

(6) A direction indicator (gyroscop-

ically stabilized, magnetic or non-
magnetic). 

(c) The following flight and naviga-

tion instruments are required as pre-
scribed in this paragraph: 

(1) A speed warning device is required 

for turbine engine powered airplanes 
and for airplanes with V

MO

/M

MO

greater 

than 0.8 V

DF

/M

DF

or 0.8 V 

D

/M

D

. The 

speed warning device must give effec-
tive aural warning (differing distinc-
tively from aural warnings used for 
other purposes) to the pilots, whenever 
the speed exceeds V

MO

plus 6 knots or 

M

MO

+ 0.01. The upper limit of the pro-

duction tolerance for the warning de-
vice may not exceed the prescribed 
warning speed. 

(2) A machmeter is required at each 

pilot station for airplanes with com-
pressibility limitations not otherwise 
indicated to the pilot by the airspeed 
indicating system required under para-
graph (b)(1) of this section. 

[Amdt. 25–23, 35 FR 5678, Apr. 8, 1970, as 
amended by Amdt. 25–24, 35 FR 7108, May 6, 
1970; Amdt. 25–38, 41 FR 55467, Dec. 20, 1976; 
Amdt. 25–90, 62 FR 13253, Mar. 19, 1997] 

§ 25.1305

Powerplant instruments. 

The following are required power-

plant instruments: 

(a) 

For all airplanes. (1) A fuel pres-

sure warning means for each engine, or 
a master warning means for all engines 
with provision for isolating the indi-
vidual warning means from the master 
warning means. 

(2) A fuel quantity indicator for each 

fuel tank. 

(3) An oil quantity indicator for each 

oil tank. 

(4) An oil pressure indicator for each 

independent pressure oil system of 
each engine. 

(5) An oil pressure warning means for 

each engine, or a master warning 
means for all engines with provision 
for isolating the individual warning 
means from the master warning means. 

(6) An oil temperature indicator for 

each engine. 

(7) Fire-warning devices that provide 

visual and audible warning. 

(8) An augmentation liquid quantity 

indicator (appropriate for the manner 
in which the liquid is to be used in op-
eration) for each tank. 

(b) 

For reciprocating engine-powered 

airplanes. In addition to the powerplant 
instruments required by paragraph (a) 
of this section, the following power-
plant instruments are required: 

(1) A carburetor air temperature indi-

cator for each engine. 

(2) A cylinder head temperature indi-

cator for each air-cooled engine. 

(3) A manifold pressure indicator for 

each engine. 

(4) A fuel pressure indicator (to indi-

cate the pressure at which the fuel is 
supplied) for each engine. 

(5) A fuel flowmeter, or fuel mixture 

indicator, for each engine without an 
automatic altitude mixture control. 

(6) A tachometer for each engine. 
(7) A device that indicates, to the 

flight crew (during flight), any change 
in the power output, for each engine 
with— 

(i) An automatic propeller feathering 

system, whose operation is initiated by 
a power output measuring system; or 

(ii) A total engine piston displace-

ment of 2,000 cubic inches or more. 

(8) A means to indicate to the pilot 

when the propeller is in reverse pitch, 
for each reversing propeller. 

(c) 

For turbine engine-powered air-

planes.  In addition to the powerplant 
instruments required by paragraph (a) 
of this section, the following power-
plant instruments are required: 

(1) A gas temperature indicator for 

each engine. 

(2) A fuel flowmeter indicator for 

each engine. 

(3) A tachometer (to indicate the 

speed of the rotors with established 
limiting speeds) for each engine. 

(4) A means to indicate, to the flight 

crew, the operation of each engine 
starter that can be operated continu-
ously but that is neither designed for 

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