Federal Aviation Administration, DOT

Section 25.903

Section 25.899 Electrical bonding and protection against static electricity.
(a) Electrical bonding and protection
against static electricity must be designed 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 electrical/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, personnel, or operation of the installed
electrical/electronic systems.
[Amdt. 25-123, 72 FR 63405, Nov. 8, 2007]

Subpart E - Powerplant

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GENERAL
Section 25.901 Installation.
(a) For the purpose of this part, the
airplane powerplant installation includes 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 inspections or overhauls.
(b) For each powerplant - 
(1) The installation must comply
with - 
(i) The installation instructions provided under SectionSection 33.5 and 35.3 of this chapter; and
(ii) The applicable provisions of this
subpart;
(2) The components of the installation must be constructed, arranged,
and installed so as to ensure their continued safe operation between normal
inspections or overhauls;
(3) The installation must be accessible for necessary inspections and
maintenance; and
(4) The major components of the installation must be electrically bonded
to the other parts of the airplane.
(c) For each powerplant and auxiliary
power unit installation, it must be established that no single failure or mal-

function or probable combination of
failures will jeopardize the safe operation 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 installation must meet the applicable provisions 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]

Section 25.903

Engines.

(a) Engine type certificate. (1) Each engine 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 December 13, 2000; or
(iii) Comply with Section 33.77 of this chapter in effect on October 31, 1974, or as
subsequently amended prior to April
30, 1998, unless that engine-s foreign object ingestion service history has resulted in an unsafe condition; or
(iv) Be shown to have a foreign object
ingestion service history in similar installation locations which has not resulted in any unsafe condition.
NOTE: Section 33.77 of this chapter in effect on October 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 effect on January 5, 2015, or as subsequently amended; or
(ii) Section 33.68 of this chapter in effect on February 23, 1984, or as subsequently amended before January 5,
2015, unless that engine-s ice accumulation service history has resulted in an
unsafe condition; or
(iii) Section 33.68 of this chapter in
effect on October 1, 1974, or as subsequently amended prior to February 23,

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