903
Federal Aviation Administration, DOT
§ 35.35
(e) The propeller control system
must be designed and constructed so
that the loss, interruption or abnormal
characteristic of airplane-supplied
electrical power does not result in haz-
ardous propeller effects. The power
quality requirements must be described
in the appropriate manuals.
[Amdt. 35–8, 73 FR 63347, Oct. 24, 2008]
§ 35.24
Strength.
The maximum stresses developed in
the propeller may not exceed values ac-
ceptable to the Administrator consid-
ering the particular form of construc-
tion and the most severe operating
conditions.
[Amdt. 35–8, 73 FR 63348, Oct. 24, 2008]
Subpart C—Tests and Inspections
§ 35.31
[Reserved]
§ 35.33
General.
(a) Each applicant must furnish test
article(s) and suitable testing facili-
ties, including equipment and com-
petent personnel, and conduct the re-
quired tests in accordance with part 21
of this chapter.
(b) All automatic controls and safety
systems must be in operation unless it
is accepted by the Administrator as
impossible or not required because of
the nature of the test. If needed for
substantiation, the applicant may test
a different propeller configuration if
this does not constitute a less severe
test.
(c) Any systems or components that
cannot be adequately substantiated by
the applicant to the requirements of
this part are required to undergo addi-
tional tests or analysis to demonstrate
that the systems or components are
able to perform their intended func-
tions in all declared environmental and
operating conditions.
[Amdt. 35–8, 73 FR 63348, Oct. 24, 2008]
§ 35.34
Inspections, adjustments and
repairs.
(a) Before and after conducting the
tests prescribed in this part, the test
article must be subjected to an inspec-
tion, and a record must be made of all
the relevant parameters, calibrations
and settings.
(b) During all tests, only servicing
and minor repairs are permitted. If
major repairs or part replacement is
required, the Administrator must ap-
prove the repair or part replacement
prior to implementation and may re-
quire additional testing. Any unsched-
uled repair or action on the test article
must be recorded and reported.
[Amdt. 35–8, 73 FR 63348, Oct. 24, 2008]
§ 35.35
Centrifugal load tests.
The applicant must demonstrate that
a propeller complies with paragraphs
(a), (b) and (c) of this section without
evidence of failure, malfunction, or
permanent deformation that would re-
sult in a major or hazardous propeller
effect. When the propeller could be sen-
sitive to environmental degradation in
service, this must be considered. This
section does not apply to fixed-pitch
wood or fixed-pitch metal propellers of
conventional design.
(a) The hub, blade retention system,
and counterweights must be tested for
a period of one hour to a load equiva-
lent to twice the maximum centrifugal
load to which the propeller would be
subjected during operation at the max-
imum rated rotational speed.
(b) Blade features associated with
transitions to the retention system (for
example, a composite blade bonded to a
metallic retention) must be tested ei-
ther during the test of paragraph (a) of
this section or in a separate component
test for a period of one hour to a load
equivalent to twice the maximum cen-
trifugal load to which the propeller
would be subjected during operation at
the maximum rated rotational speed.
(c) Components used with or attached
to the propeller (for example, spinners,
de-icing equipment, and blade erosion
shields) must be subjected to a load
equivalent to 159 percent of the max-
imum centrifugal load to which the
component would be subjected during
operation at the maximum rated rota-
tional speed. This must be performed
by either:
(1) Testing at the required load for a
period of 30 minutes; or
(2) Analysis based on test.
[Amdt. 35–8, 73 FR 63348, Oct. 24, 2008]
VerDate Mar<15>2010
10:12 Mar 18, 2014
Jkt 232046
PO 00000
Frm 00913
Fmt 8010
Sfmt 8010
Y:\SGML\232046.XXX
232046
pmangrum on DSK3VPTVN1PROD with CFR