title-14-part-25-sec25-899

309

Federal Aviation Administration, DOT

§ 25.899

fire (e.g., equipment shutdown or actu-
ation of a fire extinguisher) quick act-
ing means must be provided to alert
the crew.

(d) Each area where flammable fluids

or vapors might escape by leakage of a
fluid system must be identified and de-
fined.

[Amdt. 25–23, 35 FR 5676, Apr. 8, 1970, as
amended by Amdt. 25–46, 43 FR 50597, Oct. 30,
1978]

§ 25.865

Fire protection of flight con-

trols, engine mounts, and other
flight structure.

Essential flight controls, engine

mounts, and other flight structures lo-
cated in designated fire zones or in ad-
jacent areas which would be subjected
to the effects of fire in the fire zone
must be constructed of fireproof mate-
rial or shielded so that they are capa-
ble of withstanding the effects of fire.

[Amdt. 25–23, 35 FR 5676, Apr. 8, 1970]

§ 25.867

Fire protection: other compo-

nents.

(a) Surfaces to the rear of the na-

celles, within one nacelle diameter of
the nacelle centerline, must be at least
fire-resistant.

(b) Paragraph (a) of this section does

not apply to tail surfaces to the rear of
the nacelles that could not be readily
affected by heat, flames, or sparks
coming from a designated fire zone or
engine compartment of any nacelle.

[Amdt. 25–23, 35 FR 5676, Apr. 8, 1970]

§ 25.869

Fire protection: systems.

(a) Electrical system components:
(1) Components of the electrical sys-

tem must meet the applicable fire and
smoke protection requirements of
§§ 25.831(c) and 25.863.

(2) Equipment that is located in des-

ignated fire zones and is used during
emergency procedures must be at least
fire resistant.

(3) EWIS components must meet the

requirements of § 25.1713.

(b) Each vacuum air system line and

fitting on the discharge side of the
pump that might contain flammable
vapors or fluids must meet the require-
ments of § 25.1183 if the line or fitting is
in a designated fire zone. Other vacuum
air systems components in designated

fire zones must be at least fire resist-
ant.

must—

(1) Not be located in any designated

fire zone,

(2) Be protected from heat that may

be generated in, or escape from, any
designated fire zone, and

(3) Be installed so that escaping oxy-

gen cannot cause ignition of grease,
fluid, or vapor accumulations that are
present in normal operation or as a re-
sult of failure or malfunction of any
system.

[Amdt. 25–72, 55 FR 29784, July 20, 1990, as
amended by Amdt. 25–113, 69 FR 12530, Mar.
16, 2004; Amdt. 25–123, 72 FR 63405, Nov. 8,
2007]

ISCELLANEOUS

§ 25.871

Leveling means.

There must be means for determining

when the airplane is in a level position
on the ground.

[Amdt. 25–23, 35 FR 5676, Apr. 8, 1970]

§ 25.875

Reinforcement near propel-

lers.

(a) Each part of the airplane near the

propeller tips must be strong and stiff
enough to withstand the effects of the
induced vibration and of ice thrown
from the propeller.

(b) No window may be near the pro-

peller tips unless it can withstand the
most severe ice impact likely to occur.

§ 25.899

Electrical bonding and protec-

tion against static electricity.

(a) Electrical bonding and protection

against static electricity must be de-
signed to minimize accumulation of
electrostatic charge that would cause—

(1) Human injury from electrical

shock,

(2) Ignition of flammable vapors, or
(3) Interference with installed elec-

trical/electronic equipment.

(b) Compliance with paragraph (a) of

this section may be shown by—

(1) Bonding the components properly

to the airframe; or

(2) Incorporating other acceptable

means to dissipate the static charge so

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310

14 CFR Ch. I (1–1–24 Edition)

§ 25.901

as not to endanger the airplane, per-
sonnel, or operation of the installed
electrical/electronic systems.

[Amdt. 25–123, 72 FR 63405, Nov. 8, 2007]

Subpart E—Powerplant

ENERAL

§ 25.901

Installation.

(a) For the purpose of this part, the

airplane powerplant installation in-
cludes each component that—

(1) Is necessary for propulsion;
(2) Affects the control of the major

propulsive units; or

(3) Affects the safety of the major

propulsive units between normal in-
spections or overhauls.

(b) For each powerplant—
(1) The installation must comply

with—

(i) The installation instructions pro-

vided under §§ 33.5 and 35.3 of this chap-
ter; and

(ii) The applicable provisions of this

subpart;

(2) The components of the installa-

tion must be constructed, arranged,
and installed so as to ensure their con-
tinued safe operation between normal
inspections or overhauls;

(3) The installation must be acces-

sible for necessary inspections and
maintenance; and

(4) The major components of the in-

stallation must be electrically bonded
to the other parts of the airplane.

power unit installation, it must be es-
tablished that no single failure or mal-
function or probable combination of
failures will jeopardize the safe oper-
ation of the airplane except that the
failure of structural elements need not
be considered if the probability of such
failure is extremely remote.

(d) Each auxiliary power unit instal-

lation must meet the applicable provi-
sions of this subpart.

[Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as
amended by Amdt. 25–23, 35 FR 5676, Apr. 8,
1970; Amdt. 25–40, 42 FR 15042, Mar. 17, 1977;
Amdt. 25–46, 43 FR 50597, Oct. 30, 1978; Amdt.
25–126, 73 FR 63345, Oct. 24, 2008]

§ 25.903

Engines.

(a)

Engine type certificate. (1) Each en-

gine must have a type certificate and

must meet the applicable requirements
of part 34 of this chapter.

(2) Each turbine engine must comply

with one of the following:

(i) Sections 33.76, 33.77 and 33.78 of

this chapter in effect on December 13,
2000, or as subsequently amended; or

(ii) Sections 33.77 and 33.78 of this

chapter in effect on April 30, 1998, or as
subsequently amended before Decem-
ber 13, 2000; or

(iii) Comply with § 33.77 of this chap-

ter in effect on October 31, 1974, or as
subsequently amended prior to April
30, 1998, unless that engine’s foreign ob-
ject ingestion service history has re-
sulted in an unsafe condition; or

(iv) Be shown to have a foreign object

ingestion service history in similar in-
stallation locations which has not re-
sulted in any unsafe condition.

OTE

: § 33.77 of this chapter in effect on Oc-

tober 31, 1974, was published in 14 CFR parts
1 to 59, Revised as of January 1, 1975. See 39
FR 35467, October 1, 1974.

(3) Each turbine engine must comply

with one of the following paragraphs:

(i) Section 33.68 of this chapter in ef-

fect on January 5, 2015, or as subse-
quently amended; or

(ii) Section 33.68 of this chapter in ef-

fect on March 26, 1984, or as subse-
quently amended before January 5,
2015, unless that engine’s ice accumula-
tion service history has resulted in an
unsafe condition; or

(iii) Section 33.68 of this chapter in

effect on October 31, 1974, or as subse-
quently amended prior to February 23,
1984, unless that engine’s ice accumula-
tion service history has resulted in an
unsafe condition; or

(iv) Be shown to have an ice accumu-

lation service history in similar instal-
lation locations which has not resulted
in any unsafe conditions.

(b)

Engine isolation. The powerplants

must be arranged and isolated from
each other to allow operation, in at
least one configuration, so that the
failure or malfunction of any engine, or
of any system that can affect the en-
gine, will not—

(1) Prevent the continued safe oper-

ation of the remaining engines; or

(2) Require immediate action by any

crewmember for continued safe oper-
ation.

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