905
Federal Aviation Administration, DOT
§ 35.43
§ 35.40
Functional test.
The variable-pitch propeller system
must be subjected to the applicable
functional tests of this section. The
same propeller system used in the en-
durance test (§ 35.39) must be used in
the functional tests and must be driven
by a representative engine on a test
stand or on an airplane. The propeller
must complete these tests without evi-
dence of failure or malfunction. This
test may be combined with the endur-
ance test for accumulation of cycles.
(a) Manually-controllable propellers.
Five hundred representative flight cy-
cles must be made across the range of
pitch and rotational speed.
(b) Governing propellers. Fifteen
hundred complete cycles must be made
across the range of pitch and rota-
tional speed.
(c) Feathering propellers. Fifty cy-
cles of feather and unfeather operation
must be made.
(d) Reversible-pitch propellers. Two
hundred complete cycles of control
must be made from lowest normal
pitch to maximum reverse pitch. Dur-
ing each cycle, the propeller must run
for 30 seconds at the maximum power
and rotational speed selected by the
applicant for maximum reverse pitch.
(e) An analysis based on tests of pro-
pellers of similar design may be used in
place of the tests of this section.
[Amdt. 35–8, 73 FR 63349, Oct. 24, 2008]
§ 35.41
Overspeed and overtorque.
(a) When the applicant seeks ap-
proval of a transient maximum pro-
peller overspeed, the applicant must
demonstrate that the propeller is capa-
ble of further operation without main-
tenance action at the maximum pro-
peller overspeed condition. This may
be accomplished by:
(1) Performance of 20 runs, each of 30
seconds duration, at the maximum pro-
peller overspeed condition; or
(2) Analysis based on test or service
experience.
(b) When the applicant seeks ap-
proval of a transient maximum pro-
peller overtorque, the applicant must
demonstrate that the propeller is capa-
ble of further operation without main-
tenance action at the maximum pro-
peller overtorque condition. This may
be accomplished by:
(1) Performance of 20 runs, each of 30
seconds duration, at the maximum pro-
peller overtorque condition; or
(2) Analysis based on test or service
experience.
[Amdt. 35–8, 73 FR 63349, Oct. 24, 2008]
§ 35.42
Components of the propeller
control system.
The applicant must demonstrate by
tests, analysis based on tests, or serv-
ice experience on similar components,
that each propeller blade pitch control
system component, including gov-
ernors, pitch change assemblies, pitch
locks, mechanical stops, and feathering
system components, can withstand cy-
clic operation that simulates the nor-
mal load and pitch change travel to
which the component would be sub-
jected during the initially declared
overhaul period or during a minimum
of 1,000 hours of typical operation in
service.
[Amdt. 35–8, 73 FR 63349, Oct. 24, 2008]
§ 35.43
Propeller hydraulic compo-
nents.
Applicants must show by test, vali-
dated analysis, or both, that propeller
components that contain hydraulic
pressure and whose structural failure
or leakage from a structural failure
could cause a hazardous propeller ef-
fect demonstrate structural integrity
by:
(a) A proof pressure test to 1.5 times
the maximum operating pressure for
one minute without permanent defor-
mation or leakage that would prevent
performance of the intended function.
(b) A burst pressure test to 2.0 times
the maximum operating pressure for
one minute without failure. Leakage is
permitted and seals may be excluded
from the test.
[Amdt. 35–8, 73 FR 63349, Oct. 24, 2008]
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