title-14-part-33-sec33-57

712

14 CFR Ch. I (1–1–24 Edition)

§ 33.51

runs at other power must be made at
8,000 feet altitude pressure;

(iii) The entire run specified in para-

graph (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 alti-
tude pressure and the portions of the
runs at other power must be made at
critical altitude pressure;

(v) The entire run specified in para-

graph (d)(6) of this section must be
made at critical altitude pressure; and

(vi) The turbosupercharger used dur-

ing 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 max-
imum continuous power operation un-
less 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]

§ 33.51

Operation test.

The operation test must include the

testing found necessary by the Admin-
istrator to demonstrate backfire char-
acteristics, starting, idling, accelera-
tion, overspeeding, functioning of pro-
peller and ignition, and any other oper-
ational characteristic of the engine. If
the engine incorporates a multispeed
supercharger drive, the design and con-
struction 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.

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

§ 33.53

Engine system and component

tests.

(a) For those systems and compo-

nents that cannot be adequately sub-
stantiated in accordance with endur-
ance testing of § 33.49, the applicant
must conduct additional tests to dem-
onstrate that systems or components

are able to perform the intended func-
tions in all declared environmental and
operating conditions.

(b) Temperature limits must be es-

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

[Doc. No. 3025, 29 FR 7453, June 10, 1964, as
amended by Amdt. 33–26, 73 FR 48285, Aug. 19,
2008]

§ 33.55

Teardown inspection.

After completing the endurance

test—

(a) Each engine must be completely

disassembled;

(b) Each component having an ad-

justment setting and a functioning
characteristic that can be established
independent of installation on the en-
gine must retain each setting and func-
tioning characteristic within the limits
that were established and recorded at
the beginning of the test; and

form to the type design and be eligible
for incorporation into an engine for
continued operation, in accordance
with information submitted in compli-
ance with § 33.4.

[Amdt. 33–6, 39 FR 35466, Oct. 1, 1974, as
amended by Amdt. 33–9, 45 FR 60181, Sept. 11,
1980]

§ 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 dur-
ing the block tests in accordance with
the service and maintenance instruc-
tions submitted in compliance with
§ 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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§ 33.67

its parts may be subjected to any addi-
tional test the Administrator finds
necessary.

testing facilities, including equipment
and competent personnel, to conduct
the block tests.

[Doc. No. 3025, 29 FR 7453, June 10, 1964, as
amended by Amdt. 33–6, 39 FR 35466, Oct. 1,
1974; Amdt. 33–9, 45 FR 60181, Sept. 11, 1980]

Subpart E—Design and Construc-

tion; Turbine Aircraft Engines

§ 33.61

Applicability.

This subpart prescribes additional de-

sign and construction requirements for
turbine aircraft engines.

§ 33.62

Stress analysis.

A stress analysis must be performed

on each turbine engine showing the de-
sign safety margin of each turbine en-
gine rotor, spacer, and rotor shaft.

[Amdt. 33–6, 39 FR 35466, Oct. 1, 1974]

§ 33.63

Vibration.

Each engine must be designed and

constructed to function throughout its
declared flight envelope and operating
range of rotational speeds and power/
thrust, without inducing excessive
stress in any engine part because of vi-
bration and without imparting exces-
sive vibration forces to the aircraft
structure.

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

§ 33.64

Pressurized engine static parts.

(a) Strength. The applicant must es-

tablish by test, validated analysis, or a
combination of both, that all static
parts subject to significant gas or liq-
uid pressure loads for a stabilized pe-
riod of one minute will not:

(1) Exhibit permanent distortion be-

yond serviceable limits or exhibit leak-
age that could create a hazardous con-
dition when subjected to the greater of
the following pressures:

(i) 1.1 times the maximum working

pressure;

(ii) 1.33 times the normal working

pressure; or

(iii) 35 kPa (5 p.s.i.) above the normal

working pressure.

(2) Exhibit fracture or burst when

subjected to the greater of the fol-
lowing pressures:

(i) 1.15 times the maximum possible

pressure;

(ii) 1.5 times the maximum working

pressure; or

(iii) 35 kPa (5 p.s.i.) above the max-

imum possible pressure.

(b) Compliance with this section

must take into account:

(1) The operating temperature of the

part;

(2) Any other significant static loads

in addition to pressure loads;

(3) Minimum properties representa-

tive of both the material and the proc-
esses used in the construction of the
part; and

(4) Any adverse geometry conditions

allowed by the type design.

[Amdt. 33–27; 73 FR 55437, Sept. 25, 2008;
Amdt. 33–27, 73 FR 57235, Oct. 2, 2008]

§ 33.65

Surge and stall characteristics.

When the engine is operated in ac-

cordance with operating instructions
required by § 33.5(b), starting, a change
of power or thrust, power or thrust
augmentation, limiting inlet air dis-
tortion, or inlet air temperature may
not cause surge or stall to the extent
that flameout, structural failure, over-
temperature, or failure of the engine to
recover power or thrust will occur at
any point in the operating envelope.

[Amdt. 33–6, 39 FR 35466, Oct. 1, 1974]

§ 33.66

Bleed air system.

The engine must supply bleed air

without adverse effect on the engine,
excluding reduced thrust or power out-
put, at all conditions up to the dis-
charge flow conditions established as a
limitation under § 33.7(c)(11). If bleed
air used for engine anti-icing can be
controlled, provision must be made for
a means to indicate the functioning of
the engine ice protection system.

[Amdt. 33–10, 49 FR 6851, Feb. 23, 1984]