1、892 14 CFR Ch. I (1111 Edition) Pt. 35 the concurrence of the Administrator of the EPA. Doc. No. FAA20090112, 74 FR 19128, Apr. 28, 2009 PART 35AIRWORTHINESS STANDARDS: PROPELLERS Subpart AGeneral Sec. 35.1 Applicability. 35.2 Propeller configuration. 35.3 Instructions for propeller installation and
2、 operation. 35.4 Instructions for Continued Airworthi-ness. 35.5 Propeller ratings and operating limita-tions. 35.7 Features and characteristics. Subpart BDesign and Construction 35.11 Reserved 35.13 Reserved 35.15 Safety analysis. 35.17 Materials and manufacturing methods. 35.19 Durability. 35.21 V
3、ariable and reversible pitch propel-lers. 35.22 Feathering propellers. 35.23 Propeller control system. 35.24 Strength. Subpart CTests and Inspections 35.31 Reserved 35.33 General. 35.34 Inspections, adjustments and repairs. 35.35 Centrifugal load tests. 35.36 Bird impact. 35.37 Fatigue limits and ev
4、aluation. 35.38 Lightning strike. 35.39 Endurance test. 35.40 Functional test. 35.41 Overspeed and overtorque. 35.42 Components of the propeller control system. 35.43 Propeller hydraulic components. 35.45 Reserved 35.47 Reserved APPENDIX A TO PART 35INSTRUCTIONS FOR CONTINUED AIRWORTHINESS AUTHORITY
5、: 49 U.S.C. 106(g), 40113, 44701 44702, 44704. SOURCE: Docket No. 2095, 29 FR 7458, June 10, 1964, unless otherwise noted. Subpart AGeneral 35.1 Applicability. (a) This part prescribes airworthiness standards for the issue of type certifi-cates and changes to those certificates, for propellers. (b)
6、Each person who applies under Part 21 for such a certificate or change must show compliance with the appli-cable requirements of this part. (c) An applicant is eligible for a pro-peller type certificate and changes to those certificates after demonstrating compliance with subparts A, B and C of this
7、 part. However, the propeller may not be installed on an airplane unless the applicant has shown compliance with either 23.907 or 25.907 of this chapter, as applicable, or compliance is not required for installation on that airplane. (d) For the purposes of this part, the propeller consists of those
8、 components listed in the propeller type design, and the propeller system consists of the propeller and all the components nec-essary for its functioning, but not nec-essarily included in the propeller type design. Amdt. 353, 41 FR 55475, Dec. 20, 1976, as amended by Amdt. No. 358, 73 FR 63346, Oct.
9、 24, 2008 35.2 Propeller configuration. The applicant must provide a list of all the components, including ref-erences to the relevant drawings and software design data, that define the type design of the propeller to be ap-proved under 21.31 of this chapter. Amdt. No. 358, 73 FR 63346, Oct. 24, 200
10、8 35.3 Instructions for propeller instal-lation and operation. The applicant must provide instruc-tions that are approved by the Admin-istrator. Those approved instructions must contain: (a) Instructions for installing the propeller, which: (1) Include a description of the oper-ational modes of the
11、propeller control system and functional interface of the control system with the airplane and engine systems; (2) Specify the physical and func-tional interfaces with the airplane, air-plane equipment and engine; (3) Define the limiting conditions on the interfaces from paragraph (a)(2) of this sect
12、ion; (4) List the limitations established under 35.5; VerDate Mar2010 14:10 Mar 01, 2011 Jkt 223043 PO 00000 Frm 00902 Fmt 8010 Sfmt 8010 Y:SGML223043.XXX 223043wwoods2 on DSK1DXX6B1PROD with CFRProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-893 Fed
13、eral Aviation Administration, DOT 35.15 (5) Define the hydraulic fluids ap-proved for use with the propeller, in-cluding grade and specification, related operating pressure, and filtration lev-els; and (6) State the assumptions made to comply with the requirements of this part. (b) Instructions for
14、operating the propeller which must specify all proce-dures necessary for operating the pro-peller within the limitations of the propeller type design. Amdt. No. 358, 73 FR 63346, Oct. 24, 2008 35.4 Instructions for Continued Air-worthiness. The applicant must prepare Instruc-tions for Continued Airw
15、orthiness in accordance with appendix A to this part that are acceptable to the Admin-istrator. The instructions may be in-complete at type certification if a pro-gram exists to ensure their completion prior to delivery of the first aircraft with the propeller installed, or upon issuance of a standa
16、rd certificate of airworthiness for an aircraft with the propeller installed, whichever occurs later. Amdt. 355, 45 FR 60181, Sept. 11, 1980 35.5 Propeller ratings and operating limitations. (a) Propeller ratings and operating limitations must: (1) Be established by the applicant and approved by the
17、 Administrator. (2) Be included directly or by ref-erence in the propeller type certificate data sheet, as specified in 21.41 of this chapter. (3) Be based on the operating condi-tions demonstrated during the tests re-quired by this part as well as any other information the Administrator re-quires a
18、s necessary for the safe oper-ation of the propeller. (b) Propeller ratings and operating limitations must be established for the following, as applicable: (1) Power and rotational speed: (i) For takeoff. (ii) For maximum continuous. (iii) If requested by the applicant, other ratings may also be est
19、ablished. (2) Overspeed and overtorque limits. Amdt. No. 358, 73 FR 63346, Oct. 24, 2008 35.7 Features and characteristics. (a) The propeller may not have fea-tures or characteristics, revealed by any test or analysis or known to the applicant, that make it unsafe for the uses for which certificatio
20、n is re-quested. (b) If a failure occurs during a certifi-cation test, the applicant must deter-mine the cause and assess the effect on the airworthiness of the propeller. The applicant must make changes to the design and conduct additional tests that the Administrator finds necessary to establish t
21、he airworthiness of the propeller. Amdt. No. 358, 73 FR 63346, Oct. 24, 2008 Subpart BDesign and Construction 35.11 Reserved 35.13 Reserved 35.15 Safety analysis. (a)(1) The applicant must analyze the propeller system to assess the likely consequences of all failures that can reasonably be expected
22、to occur. This analysis will take into account, if ap-plicable: (i) The propeller system in a typical installation. When the analysis de-pends on representative components, assumed interfaces, or assumed in-stalled conditions, the assumptions must be stated in the analysis. (ii) Consequential second
23、ary failures and dormant failures. (iii) Multiple failures referred to in paragraph (d) of this section, or that result in the hazardous propeller ef-fects defined in paragraph (g)(1) of this section. (2) The applicant must summarize those failures that could result in major propeller effects or haz
24、ardous propeller effects defined in paragraph (g) of this section, and estimate the probability of occurrence of those ef-fects. (3) The applicant must show that hazardous propeller effects are not pre-dicted to occur at a rate in excess of that defined as extremely remote (probability of 107or less
25、 per propeller VerDate Mar2010 14:10 Mar 01, 2011 Jkt 223043 PO 00000 Frm 00903 Fmt 8010 Sfmt 8010 Y:SGML223043.XXX 223043wwoods2 on DSK1DXX6B1PROD with CFRProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-894 14 CFR Ch. I (1111 Edition) 35.15 flight h
26、our). Since the estimated prob-ability for individual failures may be insufficiently precise to enable the ap-plicant to assess the total rate for haz-ardous propeller effects, compliance may be shown by demonstrating that the probability of a hazardous propeller effect arising from an individual fa
27、il-ure can be predicted to be not greater than 108per propeller flight hour. In dealing with probabilities of this low order of magnitude, absolute proof is not possible and reliance must be placed on engineering judgment and previous experience combined with sound design and test philosophies. (b)
28、If significant doubt exists as to the effects of failures or likely com-bination of failures, the Administrator may require assumptions used in the analysis to be verified by test. (c) The primary failures of certain single elements (for example, blades) cannot be sensibly estimated in numer-ical te
29、rms. If the failure of such ele-ments is likely to result in hazardous propeller effects, then compliance may be shown by reliance on the prescribed integrity requirements of this part. These instances must be stated in the safety analysis. (d) If reliance is placed on a safety system to prevent a f
30、ailure progressing to hazardous propeller effects, the pos-sibility of a safety system failure in combination with a basic propeller fail-ure must be included in the analysis. Such a safety system may include safe-ty devices, instrumentation, early warning devices, maintenance checks, and other simi
31、lar equipment or proce-dures. If items of the safety system are outside the control of the propeller manufacturer, the assumptions of the safety analysis with respect to the reli-ability of these parts must be clearly stated in the analysis and identified in the propeller installation and oper-ation
32、 instructions required under 35.3. (e) If the safety analysis depends on one or more of the following items, those items must be identified in the analysis and appropriately substan-tiated. (1) Maintenance actions being carried out at stated intervals. This includes verifying that items that could f
33、ail in a latent manner are functioning prop-erly. When necessary to prevent haz-ardous propeller effects, these mainte-nance actions and intervals must be published in the instructions for con-tinued airworthiness required under 35.4. Additionally, if errors in mainte-nance of the propeller system c
34、ould lead to hazardous propeller effects, the appropriate maintenance procedures must be included in the relevant pro-peller manuals. (2) Verification of the satisfactory functioning of safety or other devices at pre-flight or other stated periods. The details of this satisfactory func-tioning must
35、be published in the appro-priate manual. (3) The provision of specific instru-mentation not otherwise required. Such instrumentation must be pub-lished in the appropriate documenta-tion. (4) A fatigue assessment. (f) If applicable, the safety analysis must include, but not be limited to, as-sessment
36、 of indicating equipment, manual and automatic controls, gov-ernors and propeller control systems, synchrophasers, synchronizers, and propeller thrust reversal systems. (g) Unless otherwise approved by the Administrator and stated in the safety analysis, the following failure defini-tions apply to c
37、ompliance with this part. (1) The following are regarded as haz-ardous propeller effects: (i) The development of excessive drag. (ii) A significant thrust in the oppo-site direction to that commanded by the pilot. (iii) The release of the propeller or any major portion of the propeller. (iv) A failu
38、re that results in excessive unbalance. (2) The following are regarded as major propeller effects for variable pitch propellers: (i) An inability to feather the pro-peller for feathering propellers. (ii) An inability to change propeller pitch when commanded. (iii) A significant uncommanded change in
39、 pitch. (iv) A significant uncontrollable torque or speed fluctuation. Amdt. No. 358, 73 FR 63346, Oct. 24, 2008 VerDate Mar2010 14:10 Mar 01, 2011 Jkt 223043 PO 00000 Frm 00904 Fmt 8010 Sfmt 8010 Y:SGML223043.XXX 223043wwoods2 on DSK1DXX6B1PROD with CFRProvided by IHSNot for ResaleNo reproduction o
40、r networking permitted without license from IHS-,-,-895 Federal Aviation Administration, DOT 35.23 35.17 Materials and manufacturing methods. (a) The suitability and durability of materials used in the propeller must: (1) Be established on the basis of ex-perience, tests, or both. (2) Account for en
41、vironmental condi-tions expected in service. (b) All materials and manufacturing methods must conform to specifica-tions acceptable to the Administrator. (c) The design values of properties of materials must be suitably related to the most adverse properties stated in the material specification for
42、applica-ble conditions expected in service. Amdt. No. 358, 73 FR 63347, Oct. 24, 2008 35.19 Durability. Each part of the propeller must be designed and constructed to minimize the development of any unsafe condi-tion of the propeller between overhaul periods. 35.21 Variable and reversible pitch prop
43、ellers. (a) No single failure or malfunction in the propeller system will result in unintended travel of the propeller blades to a position below the in-flight low-pitch position. The extent of any intended travel below the in-flight low- pitch position must be documented by the applicant in the app
44、ropriate manu-als. Failure of structural elements need not be considered if the occurrence of such a failure is shown to be extremely remote under 35.15. (b) For propellers incorporating a method to select blade pitch below the in-flight low pitch position, provisions must be made to sense and indic
45、ate to the flight crew that the propeller blades are below that position by an amount defined in the installation manual. The method for sensing and indicating the propeller blade pitch po-sition must be such that its failure does not affect the control of the pro-peller. Amdt. No. 358, 73 FR 63347,
46、 Oct. 24, 2008 35.22 Feathering propellers. (a) Feathering propellers are in-tended to feather from all flight condi-tions, taking into account expected wear and leakage. Any feathering and unfeathering limitations must be docu-mented in the appropriate manuals. (b) Propeller pitch control systems t
47、hat use engine oil to feather must in-corporate a method to allow the pro-peller to feather if the engine oil sys-tem fails. (c) Feathering propellers must be de-signed to be capable of unfeathering after the propeller system has sta-bilized to the minimum declared out-side air temperature. Amdt. No
48、. 358, 73 FR 63347, Oct. 24, 2008 35.23 Propeller control system. The requirements of this section apply to any system or component that controls, limits or monitors propeller functions. (a) The propeller control system must be designed, constructed and vali-dated to show that: (1) The propeller con
49、trol system, op-erating in normal and alternative oper-ating modes and in transition between operating modes, performs the func-tions defined by the applicant through-out the declared operating conditions and flight envelope. (2) The propeller control system functionality is not adversely affected by the declared environmental condi-tions, including temperature, electro-magnetic interference (EMI),
