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14 CFR Ch. I (1–1–14 Edition)
§ 25.1438
such that they meet the requirements
defined in § 25.1435(a)(1) through (a)(5);
(3) Have means to minimize the re-
lease of harmful or hazardous con-
centrations of hydraulic fluid or vapors
into the crew and passenger compart-
ments during flight;
(4) Meet the applicable requirements
of §§ 25.863, 25.1183, 25.1185, and 25.1189 if
a flammable hydraulic fluid is used;
and
(5) Be designed to use any suitable
hydraulic fluid specified by the air-
plane manufacturer, which must be
identified by appropriate markings as
required by § 25.1541.
(c)
Tests. Tests must be conducted on
the hydraulic system(s), and/or sub-
system(s) and elements, except that
analysis may be used in place of or to
supplement testing, where the analysis
is shown to be reliable and appropriate.
All internal and external influences
must be taken into account to an ex-
tent necessary to evaluate their ef-
fects, and to assure reliable system and
element functioning and integration.
Failure or unacceptable deficiency of
an element or system must be cor-
rected and be sufficiently retested,
where necessary.
(1) The system(s), subsystem(s), or
element(s) must be subjected to per-
formance, fatigue, and endurance tests
representative of airplane ground and
flight operations.
(2) The complete system must be
tested to determine proper functional
performance and relation to the other
systems, including simulation of rel-
evant failure conditions, and to sup-
port or validate element design.
(3) The complete hydraulic system(s)
must be functionally tested on the air-
plane in normal operation over the
range of motion of all associated user
systems. The test must be conducted at
the system relief pressure or 1.25 times
the DOP if a system pressure relief de-
vice is not part of the system design.
Clearances between hydraulic system
elements and other systems or struc-
tural elements must remain adequate
and there must be no detrimental ef-
fects.
[Doc. No. 28617, 66 FR 27402, May 16, 2001]
§ 25.1438
Pressurization and pneu-
matic systems.
(a) Pressurization system elements
must be burst pressure tested to 2.0
times, and proof pressure tested to 1.5
times, the maximum normal operating
pressure.
(b) Pneumatic system elements must
be burst pressure tested to 3.0 times,
and proof pressure tested to 1.5 times,
the maximum normal operating pres-
sure.
(c) An analysis, or a combination of
analysis and test, may be substituted
for any test required by paragraph (a)
or (b) of this section if the Adminis-
trator finds it equivalent to the re-
quired test.
[Amdt. 25–41, 42 FR 36971, July 18, 1977]
§ 25.1439
Protective breathing equip-
ment.
(a) Fixed (stationary, or built in) pro-
tective breathing equipment must be
installed for the use of the flightcrew,
and at least one portable protective
breathing equipment shall be located
at or near the flight deck for use by a
flight crewmember. In addition, port-
able protective breathing equipment
must be installed for the use of appro-
priate crewmembers for fighting fires
in compartments accessible in flight
other than the flight deck. This in-
cludes isolated compartments and
upper and lower lobe galleys, in which
crewmember occupancy is permitted
during flight. Equipment must be in-
stalled for the maximum number of
crewmembers expected to be in the
area during any operation.
(b) For protective breathing equip-
ment required by paragraph (a) of this
section or by the applicable Operating
Regulations:
(1) The equipment must be designed
to protect the appropriate crewmember
from smoke, carbon dioxide, and other
harmful gases while on flight deck
duty or while combating fires.
(2) The equipment must include—
(i) Masks covering the eyes, nose and
mouth, or
(ii) Masks covering the nose and
mouth, plus accessory equipment to
cover the eyes.
(3) Equipment, including portable
equipment, must allow communication
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