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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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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