title-14-part-29-sec29-1305

654

14 CFR Ch. I (1–1–24 Edition)

§ 29.1301

Subpart F—Equipment

ENERAL

§ 29.1301

Function and installation.

Each item of installed equipment

must—

(a) Be of a kind and design appro-

priate to its intended function;

(b) Be labeled as to its identification,

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

tions specified for that equipment; and

(d) Function properly when installed.

§ 29.1303

Flight and navigation instru-

ments.

The following are required flight and

navigational instruments:

(a) An airspeed indicator. For Cat-

egory A rotorcraft with V

less than a

speed at which unmistakable pilot cues
provide overspeed warning, a maximum
allowable airspeed indicator must be
provided. If maximum allowable air-
speed varies with weight, altitude,
temperature, or r.p.m., the indicator
must show that variation.

(b) A sensitive altimeter.
(c) A magnetic direction indicator.
(d) A clock displaying hours, min-

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

(e) A free-air temperature indicator.
(f) A non-tumbling gyroscopic bank

and pitch indicator.

(g) 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 rotorcraft with a
third attitude instrument system
that—

(1) Is usable through flight attitudes

80 degrees of pitch and

120 degrees

of roll;

(2) Is powered from a source inde-

pendent of the electrical generating
system;

(3) Continues reliable operation for a

minimum of 30 minutes after total fail-
ure of the electrical generating system;

(4) Operates independently of any

other attitude indicating system;

(5) Is operative without selection

after total failure of the electrical gen-
erating system;

(6) Is located on the instrument panel

in a position acceptable to the Admin-
istrator that will make it plainly visi-
ble to and useable by any pilot at his
station; and

(7) Is appropriately lighted during all

phases of operation.

(h) A gyroscopic direction indicator.
(i) A rate-of-climb (vertical speed) in-

dicator.

(j) For Category A rotorcraft, a speed

warning device when V

is less than

the speed at which unmistakable over-
speed warning is provided by other
pilot cues. The speed warning device
must give effective aural warning (dif-
fering distinctively from aural warn-
ings used for other purposes) to the pi-
lots whenever the indicated speed ex-
ceeds V

plus 3 knots and must oper-

ate satisfactorily throughout the ap-
proved range of altitudes and tempera-
tures.

(Secs. 313(a), 601, 603, 604, and 605 of the Fed-
eral Aviation Act of 1958 (49 U.S.C. 1354(a),
1421, 1423, 1424, and 1425); and sec. 6(c), Dept.
of Transportation Act (49 U.S.C. 1655(c)))

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29–12, 41 FR 55474, Dec. 20,
1976; Amdt. 29–14, 42 FR 36972, July 18, 1977;
Amdt. 29–24, 49 FR 44438, Nov. 6, 1984; 70 FR
2012, Jan. 12, 2005]

§ 29.1305

Powerplant instruments.

The following are required power-

plant instruments:

(a) For each rotorcraft—
(1) A carburetor air temperature indi-

cator for each reciprocating engine;

(2) A cylinder head temperature indi-

cator for each air-cooled reciprocating
engine, and a coolant temperature indi-
cator for each liquid-cooled recipro-
cating engine;

(3) A fuel quantity indicator for each

fuel tank;

(4) A low fuel warning device for each

fuel tank which feeds an engine. This
device must—

(i) Provide a warning to the crew

when approximately 10 minutes of usa-
ble fuel remains in the tank; and

(ii) Be independent of the normal fuel

quantity indicating system.

(5) A means to indicate manifold

pressure for each altitude engine;

(6) An oil pressure indicator for each

pressure-lubricated gearbox.

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Federal Aviation Administration, DOT

§ 29.1305

(7) An oil pressure warning device for

each pressure-lubricated gearbox to in-
dicate when the oil pressure falls below
a safe value;

(8) An oil quantity indicator for each

oil tank and each rotor drive gearbox,
if lubricant is self-contained;

(9) An oil temperature indicator for

each engine;

(10) An oil temperature warning de-

vice to indicate unsafe oil tempera-
tures in each main rotor drive gearbox,
including gearboxes necessary for rotor
phasing;

(11) A means to indicate the gas tem-

perature for each turbine engine;

(12) A means to indicate the gas pro-

ducer speed for each turbine engine;

(13) A tachometer for each engine

that, if combined with the applicable
instrument required by paragraph
(a)(14) of this section, indicates rotor
r.p.m. during autorotation.

(14) At least one tachometer to indi-

cate, as applicable—

(i) The r.p.m. of the single main

rotor;

(ii) The common r.p.m. of any main

rotors whose speeds cannot vary appre-
ciably with respect to each other; and

(iii) The r.p.m. of each main rotor

whose speed can vary appreciably with
respect to that of another main rotor;

(15) A free power turbine tachometer

for each turbine engine;

(16) A means, for each turbine engine,

to indicate power for that engine;

(17) For each turbine engine, an indi-

cator to indicate the functioning of the
powerplant ice protection system;

(18) An indicator for the filter re-

quired by § 29.997 to indicate the occur-
rence of contamination of the filter to
the degree established in compliance
with § 29.955;

(19) For each turbine engine, a warn-

ing means for the oil strainer or filter
required by § 29.1019, if it has no bypass,
to warn the pilot of the occurrence of
contamination of the strainer or filter
before it reaches the capacity estab-
lished in accordance with § 29.1019(a)(2);

(20) An indicator to indicate the func-

tioning of any selectable or control-
lable heater used to prevent ice clog-
ging of fuel system components;

(21) An individual fuel pressure indi-

cator for each engine, unless the fuel
system which supplies that engine does

not employ any pumps, filters, or other
components subject to degradation or
failure which may adversely affect fuel
pressure at the engine;

(22) A means to indicate to the

flightcrew the failure of any fuel pump
installed to show compliance with
§ 29.955;

(23) Warning or caution devices to

signal to the flightcrew when ferro-
magnetic particles are detected by the
chip detector required by § 29.1337(e);
and

(24) For auxiliary power units, an in-

dividual indicator, warning or caution
device, or other means to advise the
flightcrew that limits are being exceed-
ed, if exceeding these limits can be haz-
ardous, for—

(i) Gas temperature;
(ii) Oil pressure; and
(iii) Rotor speed.
(25) For rotorcraft for which a 30-sec-

ond/2-minute OEI power rating is re-
quested, a means must be provided to
alert the pilot when the engine is at
the 30-second and 2-minute OEI power
levels, when the event begins, and
when the time interval expires.

(26) For each turbine engine utilizing

30-second/2-minute OEI power, a device
or system must be provided for use by
ground personnel which—

(i) Automatically records each usage

and duration of power at the 30-second
and 2-minute OEI levels;

(ii) Permits retrieval of the recorded

data;

(iii) Can be reset only by ground

maintenance personnel; and

(iv) Has a means to verify proper op-

eration of the system or device.

(b) For category A rotorcraft—
(1) An individual oil pressure indi-

cator for each engine, and either an
independent warning device for each
engine or a master warning device for
the engines with means for isolating
the individual warning circuit from the
master warning device;

(2) An independent fuel pressure

warning device for each engine or a
master warning device for all engines
with provision for isolating the indi-
vidual warning device from the master
warning device; and

(3) Fire warning indicators.

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14 CFR Ch. I (1–1–24 Edition)

§ 29.1307

(4) For each Category A rotorcraft

for which OEI Training Mode is re-
quested, a means must be provided to
indicate to the pilot the simulation of
an engine failure, the annunciation of
that simulation, and a representation
of the OEI power being provided.

cator for each engine; and

(2) Fire warning indicators, when fire

detection is required.

[Doc. No. 5084, 29 FR 16150, Dec. 3, 1964, as
amended by Amdt. 29–3, 33 FR 970, Jan. 26,
1968; Amdt. 29–10, 39 FR 35463, Oct. 1, 1974;
Amdt. 29–26, 53 FR 34219, Sept. 2, 1988; Amdt.
29–34, 59 FR 47768, Sept. 16, 1994; Amdt. 29–40,
61 FR 21908, May 10, 1996; 61 FR 43952, Aug. 27,
1996; Amdt. 29–59, 88 FR 8739, Feb. 10, 2023]

§ 29.1307

Miscellaneous equipment.

The following is required miscella-

neous equipment:

(a) An approved seat for each occu-

pant.

(b) A master switch arrangement for

electrical circuits other than ignition.

device for each pilot station.

(e) A two-way radio communication

system.

[Amdt. 29–12, 41 FR 55473, Dec. 20, 1976]

§ 29.1309

Equipment, systems, and in-

stallations.

The equipment, systems, and instal-

lations whose functioning is required
by this subchapter must be designed
and installed to ensure that they per-
form their intended functions under
any foreseeable operating condition.
For any item of equipment or system
whose failure has not been specifically
addressed by another requirement in
this chapter, the following require-
ments also apply:

(a) The design of each item of equip-

ment, system, and installation must be
analyzed separately and in relation to
other rotorcraft systems and installa-
tions to determine and identify any
failure that would affect the capability
of the rotorcraft or the ability of the
crew to perform their duties in all op-
erating conditions.

(b) Each item of equipment, system,

and installation must be designed and
installed so that:

(1) The occurrence of any cata-

strophic failure condition is extremely
improbable;

(2) The occurrence of any major fail-

ure condition is no more than improb-
able; and

(3) For the occurrence of any other

failure condition in between major and
catastrophic, the probability of the
failure condition must be inversely
proportional to its consequences.

event of a failure must be provided
when an unsafe system operating con-
dition exists and to enable them to
take corrective action. Systems, con-
trols, and associated monitoring and
crew alerting means must be designed
to minimize crew errors that could cre-
ate additional hazards.

(d) Compliance with the require-

ments of this section must be shown by
analysis and, where necessary, by
ground, flight, or simulator tests. The
analysis must account for:

(1) Possible modes of failure, includ-

ing malfunctions and misleading data
and input from external sources;

(2) The effect of multiple failures and

latent failures;

(3) The resulting effects on the rotor-

craft and occupants, considering the
stage of flight and operating condi-
tions; and

(4) The crew alerting cues and the

corrective action required.

[Amdt. 29–59, 88 FR 8739, Feb. 10, 2023]

§ 29.1316

Electrical and electronic sys-

tem lightning protection.

(a) Each electrical and electronic

system that performs a function, for
which failure would prevent the contin-
ued safe flight and landing of the rotor-
craft, must be designed and installed so
that—

(1) The function is not adversely af-

fected during and after the time the
rotorcraft is exposed to lightning; and

(2) The system automatically recov-

ers normal operation of that function
in a timely manner after the rotorcraft
is exposed to lightning.

(b) Each electrical and electronic

system that performs a function, for
which failure would reduce the capa-
bility of the rotorcraft or the ability of
the flightcrew to respond to an adverse
operating condition, must be designed

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