page-115

309

Federal Aviation Administration, DOT

§ 25.903

§ 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
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 February 23, 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 1, 1974, or as subse-
quently amended prior to February 23,

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