713 

Federal Aviation Administration, DOT 

§ 33.67 

its parts may be subjected to any addi-
tional 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 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] 

§ 33.67

Fuel system. 

(a) With fuel supplied to the engine 

at the flow and pressure specified by 
the applicant, the engine must func-
tion properly under each operating 
condition required by this part. Each 
fuel control adjusting means that may 

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