title-14-part-33-sec33-93

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14 CFR Ch. I (1–1–24 Edition)

§ 33.92

testing of § 33.87, the applicant must
conduct additional tests to dem-
onstrate that the systems or compo-
nents are able to perform the intended
functions in all declared environmental
and operating conditions.

(b) Temperature limits must be es-

tablished for those components that re-
quire temperature controlling provi-
sions in the aircraft installation to as-
sure satisfactory functioning, reli-
ability, and durability.

fluid tank may not fail or leak when
subjected to a maximum operating
temperature and an internal pressure
of 5 p.s.i., and each pressurized hydrau-
lic fluid tank must meet the require-
ments of § 33.64.

(d) For an engine type certificated

for use in supersonic aircraft, the sys-
tems, safety devices, and external com-
ponents that may fail because of oper-
ation at maximum and minimum oper-
ating temperatures must be identified
and tested at maximum and minimum
operating temperatures and while tem-
perature and other operating condi-
tions are cycled between maximum and
minimum operating values.

[Doc. No. 3025, 29 FR 7453, June 10, 1964, as
amended by Amdt. 33–6, 39 FR 35469, Oct. 1,
1974; Amdt. 33–26, 73 FR 48285, Aug. 19, 2008;
Amdt. 33–27, 73 FR 55437, Sept. 25, 2008; Amdt.
33–27, 73 FR 57235, Oct. 2, 2008]

§ 33.92

Rotor locking tests.

If continued rotation is prevented by

a means to lock the rotor(s), the engine
must be subjected to a test that in-
cludes 25 operations of this means
under the following conditions:

(a) The engine must be shut down

from rated maximum continuous
thrust or power; and

(b) The means for stopping and lock-

ing the rotor(s) must be operated as
specified in the engine operating in-
structions while being subjected to the
maximum torque that could result
from continued flight in this condition;
and

rotor(s) must be held stationary under
these conditions for five minutes for
each of the 25 operations.

[Doc. No. 28107, 61 FR 28433, June 4, 1996]

§ 33.93

Teardown inspection.

(a) After completing the endurance

testing of § 33.87 (b), (c), (d), (e), or (g)
of this part, each engine must be com-
pletely disassembled, and

(1) Each component having an adjust-

ment setting and a functioning char-
acteristic that can be established inde-
pendent of installation on the engine
must retain each setting and func-
tioning characteristic within the limits
that were established and recorded at
the beginning of the test; and

(2) Each engine part must conform to

the type design and be eligible for in-
corporation into an engine for contin-
ued operation, in accordance with in-
formation submitted in compliance
with § 33.4.

(b) After completing the endurance

testing of § 33.87(f), each engine must be
completely disassembled, and

(1) Each component having an adjust-

(2) Each engine may exhibit deterio-

ration in excess of that permitted in
paragraph (a)(2) of this section, includ-
ing some engine parts or components
that may be unsuitable for further use.
The applicant must show by inspec-
tion, analysis, test, or by any combina-
tion thereof as found necessary by the
FAA, that structural integrity of the
engine is maintained; or

graph (b) of this section, each engine
for which the 30-second OEI and 2-
minute OEI ratings are desired, may be
subjected to the endurance testing of
§§ 33.87 (b), (c), (d), or (e) of this part,
and followed by the testing of § 33.87(f)
without intervening disassembly and
inspection. However, the engine must
comply with paragraph (a) of this sec-
tion after completing the endurance
testing of § 33.87(f).

[Doc. No. 26019, 61 FR 31329, June 19, 1996, as
amended by Amdt. 33–25, 73 FR 48124, Aug. 18,
2008]

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