Section 25.1438

14 CFR Ch. I (1-1-19 Edition)

(c) Tests. Tests must be conducted on
the hydraulic system(s), and/or subsystem(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 extent necessary to evaluate their effects, and to assure reliable system and
element functioning and integration.
Failure or unacceptable deficiency of
an element or system must be corrected and be sufficiently retested,
where necessary.
(1) The system(s), subsystem(s), or
element(s) must be subjected to performance, 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 relevant failure conditions, and to support or validate element design.
(3) The complete hydraulic system(s)
must be functionally tested on the airplane 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 device is not part of the system design.
Clearances between hydraulic system
elements and other systems or structural elements must remain adequate
and there must be no detrimental effects.
[Doc. No. 28617, 66 FR 27402, May 16, 2001]

spaschal on DSK3GDR082PROD with CFR

Section 25.1438 Pressurization
matic systems.

and

pneu-

(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 pressure.
(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 required test.
[Amdt. 25-41, 42 FR 36971, July 18, 1977]

Section 25.1439 Protective breathing equipment.
(a) Fixed (stationary, or built in) protective 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, portable protective breathing equipment
must be installed for the use of appropriate crewmembers for fighting fires
in compartments accessible in flight
other than the flight deck. This includes isolated compartments and
upper and lower lobe galleys, in which
crewmember occupancy is permitted
during flight. Equipment must be installed for the maximum number of
crewmembers expected to be in the
area during any operation.
(b) For protective breathing equipment 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
with other crewmembers while in use.
Equipment available at flightcrew assigned duty stations must also enable
the flightcrew to use radio equipment.
(4) The part of the equipment protecting the eyes shall not cause any appreciable adverse effect on vision and
must allow corrective glasses to be
worn.
(5) The equipment must supply protective oxygen of 15 minutes duration
per crewmember at a pressure altitude
of 8,000 feet with a respiratory minute
volume of 30 liters per minute BTPD.
The equipment and system must be designed to prevent any inward leakage
to the inside of the device and prevent

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