Federal Aviation Administration, DOT

Section 33.67

its parts may be subjected to any additional test the Administrator finds
necessary.
(c) Each applicant must furnish all
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 Construction; Turbine Aircraft Engines
Section 33.61

Applicability.

This subpart prescribes additional design and construction requirements for
turbine aircraft engines.
Section 33.62

Stress analysis.

A stress analysis must be performed
on each turbine engine showing the design safety margin of each turbine engine rotor, spacer, and rotor shaft.
[Amdt. 33-6, 39 FR 35466, Oct. 1, 1974]

Section 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 vibration and without imparting excessive vibration forces to the aircraft
structure.
[Doc. No. 28107, 61 FR 28433, June 4, 1996]

spaschal on DSK3GDR082PROD with CFR

Section 33.64

Pressurized engine static parts.

(a) Strength. The applicant must establish by test, validated analysis, or a
combination of both, that all static
parts subject to significant gas or liquid pressure loads for a stabilized period of one minute will not:
(1) Exhibit permanent distortion beyond serviceable limits or exhibit leakage that could create a hazardous condition 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 following 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 maximum 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 representative of both the material and the processes 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]

Section 33.65 Surge and stall characteristics.
When the engine is operated in accordance with operating instructions
required by Section 33.5(b), starting, a change
of power or thrust, power or thrust
augmentation, limiting inlet air distortion, or inlet air temperature may
not cause surge or stall to the extent
that flameout, structural failure, overtemperature, 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]

Section 33.66 Bleed air system.
The engine must supply bleed air
without adverse effect on the engine,
excluding reduced thrust or power output, at all conditions up to the discharge flow conditions established as a
limitation under Section 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]

Section 33.67 Fuel system.
(a) With fuel supplied to the engine
at the flow and pressure specified by
the applicant, the engine must function properly under each operating
condition required by this part. Each
fuel control adjusting means that may

713

VerDate Sep<11>2014

12:50 Apr 30, 2019

Jkt 247046

PO 00000

Frm 00723

Fmt 8010

Sfmt 8010

Y:\SGML\247046.XXX

247046