Section 33.90

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

(iii) An intermediate value for bleed
air and power extraction representative of that which might be used as a
maximum for aircraft during approach
to a landing.
(4) If testing facilities are not available, the determination of power extraction required in paragraph (a)(3)(ii)
and (iii) of this section may be accomplished through appropriate analytical
means.
(b) The operation test must include
all testing found necessary by the Administrator to demonstrate that the
engine has safe operating characteristics throughout its specified operating
envelope.
[Amdt. 33-4, 36 FR 5493, Mar. 24, 1971, as
amended by Amdt. 33-6, 39 FR 35469, Oct. 1,
1974; Amdt. 33-10, 49 FR 6853, Feb. 23, 1984]

Section 33.90 Initial maintenance inspection
test.
Each applicant, except an applicant
for an engine being type certificated
through amendment of an existing type
certificate or through supplemental
type certification procedures, must
complete one of the following tests on
an engine that substantially conforms
to the type design to establish when
the initial maintenance inspection is
required:
(a) An approved engine test that simulates the conditions in which the engine is expected to operate in service,
including typical start-stop cycles.
(b) An approved engine test conducted in accordance with Section 33.201 (c)
through (f).
[Doc. No. FAA-2002-6717, 72 FR 1877, Jan. 16,
2007]

spaschal on DSK3GDR082PROD with CFR

Section 33.91 Engine system and component
tests.
(a) For those systems or components
that cannot be adequately substantiated in accordance with endurance
testing of Section 33.87, the applicant must
conduct additional tests to demonstrate that the systems or components are able to perform the intended
functions in all declared environmental
and operating conditions.
(b) Temperature limits must be established for those components that require temperature controlling provisions in the aircraft installation to as-

sure satisfactory functioning, reliability, and durability.
(c) Each unpressurized hydraulic
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 hydraulic fluid tank must meet the requirements of Section 33.64.
(d) For an engine type certificated
for use in supersonic aircraft, the systems, safety devices, and external components that may fail because of operation at maximum and minimum operating temperatures must be identified
and tested at maximum and minimum
operating temperatures and while temperature and other operating conditions 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]

Section 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 includes 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 locking the rotor(s) must be operated as
specified in the engine operating instructions while being subjected to the
maximum torque that could result
from continued flight in this condition;
and
(c) Following rotor locking, the
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]

Section 33.93 Teardown inspection.
(a) After completing the endurance
testing of Section 33.87 (b), (c), (d), (e), or (g)
of this part, each engine must be completely disassembled, and
(1) 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

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