Section 33.51

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

runs at other power must be made at
8,000 feet altitude pressure;
(iii) The entire run specified in paragraph (d)(4) of this section must be
made at 8,000 feet altitude pressure;
(iv) The portion of the runs specified
in paragraph (d)(5) of this section at 80
percent of rated maximum continuous
power must be made at 8,000 feet altitude pressure and the portions of the
runs at other power must be made at
critical altitude pressure;
(v) The entire run specified in paragraph (d)(6) of this section must be
made at critical altitude pressure; and
(vi) The turbosupercharger used during the endurance test must be run on
the bench for 50 hours at the limiting
turbine wheel inlet gas temperature
and rotational speed for rated maximum continuous power operation unless the limiting temperature and
speed are maintained during 50 hours of
the rated maximum continuous power
operation.
[Amdt. 33-3, 32 FR 3736, Mar. 4, 1967, as
amended by Amdt. 33-6, 39 FR 35465, Oct. 1,
1974; Amdt. 33-10, 49 FR 6851, Feb. 23, 1984]

Section 33.51 Operation test.
The operation test must include the
testing found necessary by the Administrator to demonstrate backfire characteristics, starting, idling, acceleration, overspeeding, functioning of propeller and ignition, and any other operational characteristic of the engine. If
the engine incorporates a multispeed
supercharger drive, the design and construction must allow the supercharger
to be shifted from operation at the
lower speed ratio to the higher and the
power appropriate to the manifold
pressure and speed settings for rated
maximum continuous power at the
higher supercharger speed ratio must
be obtainable within five seconds.

spaschal on DSK3GDR082PROD with CFR

[Doc. No. 3025, 29 FR 7453, June 10, 1964, as
amended by Amdt. 33-3, 32 FR 3737, Mar. 4,
1967]

Section 33.53 Engine system and component
tests.
(a) For those systems and components that cannot be adequately substantiated in accordance with endurance testing of Section 33.49, the applicant
must conduct additional tests to demonstrate that systems or components

are able to perform the intended functions in all declared environmental and
operating conditions.
(b) Temperature limits must be established for each component that requires temperature controlling provisions in the aircraft installation to assure satisfactory functioning, reliability, and durability.
[Doc. No. 3025, 29 FR 7453, June 10, 1964, as
amended by Amdt. 33-26, 73 FR 48285, Aug. 19,
2008]

Section 33.55

Teardown inspection.

After completing the endurance
test - 
(a) Each engine must be completely
disassembled;
(b) Each component having an adjustment setting and a functioning
characteristic that can be established
independent of installation on the engine must retain each setting and functioning characteristic within the limits
that were established and recorded at
the beginning of the test; and
(c) Each engine component must conform to the type design and be eligible
for incorporation into an engine for
continued operation, in accordance
with information submitted in compliance with Section 33.4.
[Amdt. 33-6, 39 FR 35466, Oct. 1, 1974, as
amended by Amdt. 33-9, 45 FR 60181, Sept. 11,
1980]

Section 33.57

General conduct of block tests.

(a) The applicant may, in conducting
the block tests, use separate engines of
identical design and construction in
the vibration, calibration, detonation,
endurance, and operation tests, except
that, if a separate engine is used for
the endurance test it must be subjected
to a calibration check before starting
the endurance test.
(b) The applicant may service and
make minor repairs to the engine during the block tests in accordance with
the service and maintenance instructions submitted in compliance with
Section 33.4. If the frequency of the service is
excessive, or the number of stops due
to engine malfunction is excessive, or a
major repair, or replacement of a part
is found necessary during the block
tests or as the result of findings from
the teardown inspection, the engine or

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