761 

Federal Aviation Administration, DOT 

§ 35.34 

by the declared environmental condi-
tions, including temperature, electro-
magnetic interference (EMI), high in-
tensity radiated fields (HIRF) and 
lightning. The environmental limits to 
which the system has been satisfac-
torily validated must be documented in 
the appropriate propeller manuals. 

(3) A method is provided to indicate 

that an operating mode change has oc-
curred if flight crew action is required. 
In such an event, operating instruc-
tions must be provided in the appro-
priate manuals. 

(b) The propeller control system 

must be designed and constructed so 
that, in addition to compliance with 
§ 35.15: 

(1) No single failure or malfunction of 

electrical or electronic components in 
the control system results in a haz-
ardous propeller effect. 

(2) Failures or malfunctions directly 

affecting the propeller control system 
in a typical airplane, such as struc-
tural failures of attachments to the 
control, fire, or overheat, do not lead 
to a hazardous propeller effect. 

(3) The loss of normal propeller pitch 

control does not cause a hazardous pro-
peller effect under the intended oper-
ating conditions. 

(4) The failure or corruption of data 

or signals shared across propellers does 
not cause a hazardous propeller effect. 

(c) Electronic propeller control sys-

tem imbedded software must be de-
signed and implemented by a method 
approved by the Administrator that is 
consistent with the criticality of the 
performed functions and that mini-
mizes the existence of software errors. 

(d) The propeller control system 

must be designed and constructed so 
that the failure or corruption of air-
plane-supplied data does not result in 
hazardous propeller effects. 

(e) The propeller control system 

must be designed and constructed so 
that the loss, interruption or abnormal 
characteristic of airplane-supplied 
electrical power does not result in haz-
ardous propeller effects. The power 
quality requirements must be described 
in the appropriate manuals. 

[Amdt. 35–8, 73 FR 63347, Oct. 24, 2008] 

§ 35.24

Strength. 

The maximum stresses developed in 

the propeller may not exceed values ac-
ceptable to the Administrator consid-
ering the particular form of construc-
tion and the most severe operating 
conditions. 

[Amdt. 35–8, 73 FR 63348, Oct. 24, 2008] 

Subpart C—Tests and Inspections 

§ 35.31

[Reserved] 

§ 35.33

General. 

(a) Each applicant must furnish test 

article(s) and suitable testing facili-
ties, including equipment and com-
petent personnel, and conduct the re-
quired tests in accordance with part 21 
of this chapter. 

(b) All automatic controls and safety 

systems must be in operation unless it 
is accepted by the Administrator as 
impossible or not required because of 
the nature of the test. If needed for 
substantiation, the applicant may test 
a different propeller configuration if 
this does not constitute a less severe 
test. 

(c) Any systems or components that 

cannot be adequately substantiated by 
the applicant to the requirements of 
this part are required to undergo addi-
tional tests or analysis to demonstrate 
that the systems or components are 
able to perform their intended func-
tions in all declared environmental and 
operating conditions. 

[Amdt. 35–8, 73 FR 63348, Oct. 24, 2008] 

§ 35.34

Inspections, adjustments and 

repairs. 

(a) Before and after conducting the 

tests prescribed in this part, the test 
article must be subjected to an inspec-
tion, and a record must be made of all 
the relevant parameters, calibrations 
and settings. 

(b) During all tests, only servicing 

and minor repairs are permitted. If 
major repairs or part replacement is 
required, the Administrator must ap-
prove the repair or part replacement 

VerDate Sep<11>2014 

09:06 Jun 28, 2024

Jkt 262046

PO 00000

Frm 00771

Fmt 8010

Sfmt 8010

Y:\SGML\262046.XXX

262046

jspears on DSK121TN23PROD with CFR