Document
Federal Aviation Administration, DOT Pt. 35 may still comply with the require- (iv) nvPM EI (particles/kg of fuel) num ments. Failure may be caused by exces- at each thrust setting of the LTO sive data scatter, too few data points, cycle; or erroneous data used to regress an (v) nvPM number emission rate accurate curve. Without deleting or re- [nvPM EI × fuel flow] in particles/s; num (vi) Total gross emissions of nvPM moving any prior measurement data, mass measured over the LTO cycle in additional data acquired from further mg; tests may improve the CI by adding to the sample population. (vii) Total gross emissions of nvPM number measured over the LTO cycle (e) The following information must in particles; be reported to the FAA substantiating (viii) LTO nvPM /thrust in mg/kN; compliance with nvPM limits of § 34.25 mass (ix) LTO nvPM /thrust in particles/ of this part: num kN; and (1) The values of nvPM emissions (x) Maximum nvPM in μ g/m ; and MC measured and computed in accordance (5) For each engine tested for certifi- with the procedures and calculated as cation purposes, the characteristic lev- required by this subpart in § 34.71 of els for the maximum nvPM , the LTO MC this part and paragraphs (a) through nvPM /thrust, and the LTO nvPM / mass num (d) of this section; thrust.
(2) For each engine tested: (i) Engine model, series, and serial PART 35—AIRWORTHINESS number; STANDARDS: PROPELLERS (ii) Rated thrust (kN); (iii) Overall pressure ratio; Subpart A—General (iv) The methods of data acquisition; and Sec.
(v) The method of data analysis cho- 35.1 Applicability.
sen by the applicant under paragraphs 35.2 Propeller configuration.
35.3 Instructions for propeller installation (a) through (d) of this section.
and operation.
(3) Demonstration that the fuel used 35.4 Instructions for Continued Airworthi- for each test is in compliance with the ness.
fuel specification listed in Appendix 4 35.5 Propeller ratings and operating limita- of ICAO Annex 16, Volume II (incor- tions.
porated by reference, see § 34.4). For the 35.7 Features and characteristics.
fuel used for nvPM emissions certifi- Subpart B—Design and Construction cation, include the following fuel char- acteristics: 35.11 [Reserved] (i) Hydrogen/carbon ratio; 35.13 [Reserved] (ii) Net heat of combustion (MJ/kg); 35.15 Safety analysis.
35.16 Propeller critical parts.
(iii) Hydrogen content (mass per 35.17 Materials and manufacturing methods.
cent); 35.19 Durability.
(iv) Total aromatics content (volume 35.21 Variable and reversible pitch propel- per cent); lers.
(v) Naphthalene content (volume per 35.22 Feathering propellers.
cent); and 35.23 Propeller control system.
35.24 Strength.
(vi) Sulfur content (ppm by mass).
(4) For each engine tested for certifi- Subpart C—Tests and Inspections cation purposes, the following values measured and computed in accordance 35.31 [Reserved] with the procedures of § 34.71 of this 35.33 General.
35.34 Inspections, adjustments and repairs.
part: 35.35 Centrifugal load tests.
(i) Fuel flow (kg/s) at each thrust set- 35.36 Bird impact.
ting of the LTO cycle; 35.37 Fatigue limits and evaluation.
(ii) nvPM EI (mg/kg of fuel) at mass 35.38 Lightning strike.
each thrust setting of the LTO cycle; 35.39 Endurance test.
(iii) nvPM mass emission rate [nvPM 35.40 Functional test.
EI × fuel flow] in mg/s; 35.41 Overspeed and overtorque.
mass 14 CFR Ch. I (1–1–25 Edition) § 35.1 35.42 Components of the propeller control § 35.3 Instructions for propeller instal- system.
lation and operation.
35.43 Propeller hydraulic components.
The applicant must provide instruc- 35.45–35.47 [Reserved] tions that are approved by the Admin- A PPENDIX A TO P ART 35—I NSTRUCTIONS FOR istrator. Those approved instructions C ONTINUED A IRWORTHINESS must contain: AUTHORITY : 49 U.S.C. 106(f), 106(g), 40113, (a) Instructions for installing the 44701–44702, 44704.
propeller, which: (1) Include a description of the oper- S OURCE : Docket No. 2095, 29 FR 7458, June ational modes of the propeller control 10, 1964, unless otherwise noted.
system and functional interface of the control system with the airplane and Subpart A—General engine systems; (2) Specify the physical and func- § 35.1 Applicability.
tional interfaces with the airplane, air- (a) This part prescribes airworthiness plane equipment and engine; standards for the issue of type certifi- (3) Define the limiting conditions on cates and changes to those certificates, the interfaces from paragraph (a)(2) of for propellers.
this section; (b) Each person who applies under (4) List the limitations established part 21 for such a certificate or change under § 35.5; must show compliance with the appli- (5) Define the hydraulic fluids ap- cable requirements of this part.
proved for use with the propeller, in- (c) An applicant is eligible for a pro- cluding grade and specification, related peller type certificate and changes to operating pressure, and filtration lev- els; and those certificates after demonstrating compliance with subparts A, B, and C (6) State the assumptions made to comply with the requirements of this of this part. However, the propeller part.
may not be installed on an airplane un- (b) Instructions for operating the less the applicant has shown compli- propeller which must specify all proce- ance with either § 23.2400(c) or § 25.907 of dures necessary for operating the pro- this chapter, as applicable, or compli- peller within the limitations of the ance is not required for installation on propeller type design.
that airplane.
(d) For the purposes of this part, the [Amdt. 35–8, 73 FR 63346, Oct. 24, 2008] propeller consists of those components § 35.4 Instructions for Continued Air- listed in the propeller type design, and worthiness.
the propeller system consists of the propeller and all the components nec- The applicant must prepare Instruc- essary for its functioning, but not nec- tions for Continued Airworthiness in essarily included in the propeller type accordance with appendix A to this part that are acceptable to the Admin- design.
istrator. The instructions may be in- [Amdt. 35–3, 41 FR 55475, Dec. 20, 1976, as complete at type certification if a pro- amended by Amdt. 35–8, 73 FR 63346, Oct. 24, gram exists to ensure their completion 2008; Doc. FAA–2015–1621, Amdt. 35–10, 81 FR prior to delivery of the first aircraft 96700, Dec. 30, 2016] with the propeller installed, or upon issuance of a standard certificate of § 35.2 Propeller configuration.
airworthiness for an aircraft with the The applicant must provide a list of propeller installed, whichever occurs all the components, including ref- later.
erences to the relevant drawings and [Amdt. 35–5, 45 FR 60181, Sept. 11, 1980] software design data, that define the type design of the propeller to be ap- § 35.5 Propeller ratings and operating proved under § 21.31 of this chapter.
limitations.
[Amdt. 35–8, 73 FR 63346, Oct. 24, 2008] (a) Propeller ratings and operating limitations must: Federal Aviation Administration, DOT § 35.15 (1) Be established by the applicant assumed interfaces, or assumed in- and approved by the Administrator. stalled conditions, the assumptions (2) Be included directly or by ref- must be stated in the analysis.
erence in the propeller type certificate (ii) Consequential secondary failures data sheet, as specified in § 21.41 of this and dormant failures.
chapter. (iii) Multiple failures referred to in (3) Be based on the operating condi- paragraph (d) of this section, or that tions demonstrated during the tests re- result in the hazardous propeller ef- quired by this part as well as any other fects defined in paragraph (g)(1) of this information the Administrator re- section.
quires as necessary for the safe oper- (2) The applicant must summarize ation of the propeller. those failures that could result in (b) Propeller ratings and operating major propeller effects or hazardous limitations must be established for the propeller effects defined in paragraph following, as applicable: (g) of this section, and estimate the (1) Power and rotational speed: probability of occurrence of those ef- (i) For takeoff. fects.
(ii) For maximum continuous. (3) The applicant must show that (iii) If requested by the applicant, hazardous propeller effects are not pre- other ratings may also be established. dicted to occur at a rate in excess of (2) Overspeed and overtorque limits. that defined as extremely remote ¥ 7 (probability of 10 or less per propeller [Amdt. 35–8, 73 FR 63346, Oct. 24, 2008] flight hour). Since the estimated prob- ability for individual failures may be § 35.7 Features and characteristics.
insufficiently precise to enable the ap- (a) The propeller may not have fea- plicant to assess the total rate for haz- tures or characteristics, revealed by ardous propeller effects, compliance any test or analysis or known to the may be shown by demonstrating that applicant, that make it unsafe for the the probability of a hazardous propeller uses for which certification is re- effect arising from an individual fail- quested.
ure can be predicted to be not greater (b) If a failure occurs during a certifi- ¥ 8 than 10 per propeller flight hour. In cation test, the applicant must deter- dealing with probabilities of this low mine the cause and assess the effect on order of magnitude, absolute proof is the airworthiness of the propeller. The not possible and reliance must be applicant must make changes to the placed on engineering judgment and design and conduct additional tests previous experience combined with that the Administrator finds necessary sound design and test philosophies.
to establish the airworthiness of the (b) If significant doubt exists as to propeller.
the effects of failures or likely com- [Amdt. 35–8, 73 FR 63346, Oct. 24, 2008] bination of failures, the Administrator may require assumptions used in the analysis to be verified by test.
Subpart B—Design and (c) The primary failures of certain Construction single propeller elements (for example, blades) cannot be sensibly estimated in § 35.11 [Reserved] numerical terms. If the failure of such § 35.13 [Reserved] elements is likely to result in haz- ardous propeller effects, those ele- § 35.15 Safety analysis.
ments must be identified as propeller (a)(1) The applicant must analyze the critical parts. For propeller critical propeller system to assess the likely parts, applicants must meet the pre- consequences of all failures that can scribed integrity specifications of reasonably be expected to occur. This § 35.16. These instances must be stated analysis will take into account, if ap- in the safety analysis.
plicable: (d) If reliance is placed on a safety (i) The propeller system in a typical system to prevent a failure progressing installation. When the analysis de- to hazardous propeller effects, the pos- pends on representative components, sibility of a safety system failure in 14 CFR Ch. I (1–1–25 Edition) § 35.16 combination with a basic propeller fail- (1) The following are regarded as haz- ure must be included in the analysis. ardous propeller effects: Such a safety system may include safe- (i) The development of excessive ty devices, instrumentation, early drag.
(ii) A significant thrust in the oppo- warning devices, maintenance checks, site direction to that commanded by and other similar equipment or proce- the pilot.
dures. If items of the safety system are (iii) The release of the propeller or outside the control of the propeller any major portion of the propeller.
manufacturer, the assumptions of the (iv) A failure that results in excessive safety analysis with respect to the reli- unbalance.
ability of these parts must be clearly (2) The following are regarded as stated in the analysis and identified in major propeller effects for variable the propeller installation and oper- pitch propellers: ation instructions required under § 35.3.
(i) An inability to feather the pro- (e) If the safety analysis depends on peller for feathering propellers.
one or more of the following items, (ii) An inability to change propeller those items must be identified in the pitch when commanded.
analysis and appropriately substan- (iii) A significant uncommanded tiated.
change in pitch.
(1) Maintenance actions being carried (iv) A significant uncontrollable out at stated intervals. This includes torque or speed fluctuation.
verifying that items that could fail in [Amdt. 35–8, 73 FR 63346, Oct. 24, 2008, as a latent manner are functioning prop- amended by Amdt. 35–9, 78 FR 4041, Jan. 18, erly. When necessary to prevent haz- 2013; Amdt. 35–9A, 78 FR 45052, July 26, 2013] ardous propeller effects, these mainte- nance actions and intervals must be § 35.16 Propeller critical parts.
published in the instructions for con- The integrity of each propeller crit- tinued airworthiness required under ical part identified by the safety anal- § 35.4. Additionally, if errors in mainte- ysis required by § 35.15 must be estab- nance of the propeller system could lished by: lead to hazardous propeller effects, the (a) A defined engineering process for appropriate maintenance procedures ensuring the integrity of the propeller must be included in the relevant pro- critical part throughout its service life, peller manuals.
(b) A defined manufacturing process (2) Verification of the satisfactory that identifies the requirements to functioning of safety or other devices consistently produce the propeller crit- at pre-flight or other stated periods.
ical part as required by the engineering The details of this satisfactory func- process, and tioning must be published in the appro- (c) A defined service management priate manual.
process that identifies the continued airworthiness requirements of the pro- (3) The provision of specific instru- peller critical part as required by the mentation not otherwise required.
engineering process.
Such instrumentation must be pub- lished in the appropriate documenta- [Amdt. 35–9, 78 FR 4042, Jan. 18, 2013] tion.
(4) A fatigue assessment.
§ 35.17 Materials and manufacturing methods.
(f) If applicable, the safety analysis must include, but not be limited to, as- (a) The suitability and durability of sessment of indicating equipment, materials used in the propeller must: manual and automatic controls, gov- (1) Be established on the basis of ex- ernors and propeller control systems, perience, tests, or both.
synchrophasers, synchronizers, and (2) Account for environmental condi- propeller thrust reversal systems.
tions expected in service.
(g) Unless otherwise approved by the (b) All materials and manufacturing Administrator and stated in the safety methods must conform to specifica- analysis, the following failure defini- tions acceptable to the Administrator.
tions apply to compliance with this (c) The design values of properties of part. materials must be suitably related to Federal Aviation Administration, DOT § 35.23 the most adverse properties stated in § 35.23 Propeller control system.
the material specification for applica- The requirements of this section ble conditions expected in service.
apply to any system or component that [Amdt. 35–8, 73 FR 63347, Oct. 24, 2008] controls, limits or monitors propeller functions.
§ 35.19 Durability.
(a) The propeller control system must be designed, constructed and vali- Each part of the propeller must be dated to show that: designed and constructed to minimize (1) The propeller control system, op- the development of any unsafe condi- erating in normal and alternative oper- tion of the propeller between overhaul ating modes and in transition between periods.
operating modes, performs the func- § 35.21 Variable and reversible pitch tions defined by the applicant through- propellers.
out the declared operating conditions and flight envelope.
(a) No single failure or malfunction (2) The propeller control system in the propeller system will result in functionality is not adversely affected unintended travel of the propeller by the declared environmental condi- blades to a position below the in-flight tions, including temperature, electro- low-pitch position. The extent of any magnetic interference (EMI), high in- intended travel below the in-flight low- tensity radiated fields (HIRF) and pitch position must be documented by lightning. The environmental limits to the applicant in the appropriate manu- which the system has been satisfac- als. Failure of structural elements need torily validated must be documented in not be considered if the occurrence of the appropriate propeller manuals.
such a failure is shown to be extremely (3) A method is provided to indicate remote under § 35.15.
that an operating mode change has oc- (b) For propellers incorporating a curred if flight crew action is required.
method to select blade pitch below the In such an event, operating instruc- in-flight low pitch position, provisions tions must be provided in the appro- must be made to sense and indicate to priate manuals.
the flight crew that the propeller blades are below that position by an (b) The propeller control system amount defined in the installation must be designed and constructed so manual. The method for sensing and that, in addition to compliance with indicating the propeller blade pitch po- § 35.15: sition must be such that its failure (1) No single failure or malfunction of does not affect the control of the pro- electrical or electronic components in peller. the control system results in a haz- ardous propeller effect.
[Amdt. 35–8, 73 FR 63347, Oct. 24, 2008] (2) Failures or malfunctions directly affecting the propeller control system § 35.22 Feathering propellers.
in a typical airplane, such as struc- (a) Feathering propellers are in- tural failures of attachments to the tended to feather from all flight condi- control, fire, or overheat, do not lead tions, taking into account expected to a hazardous propeller effect.
wear and leakage. Any feathering and (3) The loss of normal propeller pitch unfeathering limitations must be docu- control does not cause a hazardous pro- mented in the appropriate manuals.
peller effect under the intended oper- (b) Propeller pitch control systems ating conditions.
that use engine oil to feather must in- (4) The failure or corruption of data corporate a method to allow the pro- or signals shared across propellers does peller to feather if the engine oil sys- not cause a hazardous propeller effect.
tem fails.
(c) Electronic propeller control sys- (c) Feathering propellers must be de- tem imbedded software must be de- signed to be capable of unfeathering signed and implemented by a method after the propeller system has sta- approved by the Administrator that is bilized to the minimum declared out- consistent with the criticality of the side air temperature.
performed functions and that mini- [Amdt. 35–8, 73 FR 63347, Oct. 24, 2008] mizes the existence of software errors.
14 CFR Ch. I (1–1–25 Edition) § 35.24 (d) The propeller control system § 35.34 Inspections, adjustments and must be designed and constructed so repairs.
that the failure or corruption of air- (a) Before and after conducting the plane-supplied data does not result in tests prescribed in this part, the test hazardous propeller effects.
article must be subjected to an inspec- (e) The propeller control system tion, and a record must be made of all must be designed and constructed so the relevant parameters, calibrations that the loss, interruption or abnormal and settings.
characteristic of airplane-supplied (b) During all tests, only servicing electrical power does not result in haz- and minor repairs are permitted. If ardous propeller effects. The power major repairs or part replacement is quality requirements must be described required, the Administrator must ap- in the appropriate manuals.
prove the repair or part replacement prior to implementation and may re- [Amdt. 35–8, 73 FR 63347, Oct. 24, 2008] quire additional testing. Any unsched- uled repair or action on the test article § 35.24 Strength.
must be recorded and reported.
The maximum stresses developed in [Amdt. 35–8, 73 FR 63348, Oct. 24, 2008] the propeller may not exceed values ac- ceptable to the Administrator consid- § 35.35 Centrifugal load tests.
ering the particular form of construc- The applicant must demonstrate that tion and the most severe operating a propeller complies with paragraphs conditions.
(a), (b) and (c) of this section without [Amdt. 35–8, 73 FR 63348, Oct. 24, 2008] evidence of failure, malfunction, or permanent deformation that would re- Subpart C—Tests and Inspections sult in a major or hazardous propeller effect. When the propeller could be sen- § 35.31 [Reserved] sitive to environmental degradation in service, this must be considered. This § 35.33 General.
section does not apply to fixed-pitch wood or fixed-pitch metal propellers of (a) Each applicant must furnish test article(s) and suitable testing facili- conventional design.
ties, including equipment and com- (a) The hub, blade retention system, and counterweights must be tested for petent personnel, and conduct the re- quired tests in accordance with part 21 a period of one hour to a load equiva- lent to twice the maximum centrifugal of this chapter.
load to which the propeller would be (b) All automatic controls and safety subjected during operation at the max- systems must be in operation unless it imum rated rotational speed.
is accepted by the Administrator as (b) Blade features associated with impossible or not required because of transitions to the retention system (for the nature of the test. If needed for example, a composite blade bonded to a substantiation, the applicant may test metallic retention) must be tested ei- a different propeller configuration if ther during the test of paragraph (a) of this does not constitute a less severe this section or in a separate component test.
test for a period of one hour to a load (c) Any systems or components that equivalent to twice the maximum cen- cannot be adequately substantiated by trifugal load to which the propeller the applicant to the requirements of would be subjected during operation at this part are required to undergo addi- the maximum rated rotational speed.
tional tests or analysis to demonstrate (c) Components used with or attached that the systems or components are to the propeller (for example, spinners, able to perform their intended func- de-icing equipment, and blade erosion tions in all declared environmental and shields) must be subjected to a load operating conditions.
equivalent to 159 percent of the max- imum centrifugal load to which the [Amdt. 35–8, 73 FR 63348, Oct. 24, 2008] component would be subjected during Federal Aviation Administration, DOT § 35.39 operation at the maximum rated rota- (2) A typical airplane.
tional speed. This must be performed [Amdt. 35–8, 73 FR 63348, Oct. 24, 2008, as by either: amended by Doc. FAA–2015–1621, Amdt. 35–10, (1) Testing at the required load for a 81 FR 96700, Dec. 30, 2016] period of 30 minutes; or § 35.38 Lightning strike.
(2) Analysis based on test.
The applicant must demonstrate, by [Amdt. 35–8, 73 FR 63348, Oct. 24, 2008] tests, analysis based on tests, or expe- rience on similar designs, that the pro- § 35.36 Bird impact.
peller can withstand a lightning strike The applicant must demonstrate, by without causing a major or hazardous tests or analysis based on tests or expe- propeller effect. The limit to which the rience on similar designs, that the pro- propeller has been qualified must be peller can withstand the impact of a 4- documented in the appropriate manu- pound bird at the critical location(s) als. This section does not apply to and critical flight condition(s) of a typ- fixed-pitch wood propellers of conven- ical installation without causing a tional design.
major or hazardous propeller effect.
[Amdt. 35–8, 73 FR 63348, Oct. 24, 2008] This section does not apply to fixed- pitch wood propellers of conventional § 35.39 Endurance test.
design.
Endurance tests on the propeller sys- [Amdt. 35–8, 73 FR 63348, Oct. 24, 2008] tem must be made on a representative engine in accordance with paragraph § 35.37 Fatigue limits and evaluation.
(a) or (b) of this section, as applicable, without evidence of failure or malfunc- This section does not apply to fixed- tion.
pitch wood propellers of conventional (a) Fixed-pitch and ground adjust- design.
able-pitch propellers must be subjected (a) Fatigue limits must be estab- to one of the following tests: lished by tests, or analysis based on (1) A 50-hour flight test in level flight tests, for propeller: or in climb. The propeller must be op- (1) Hubs.
erated at takeoff power and rated rota- (2) Blades.
tional speed during at least five hours (3) Blade retention components.
of this flight test, and at not less than (4) Components which are affected by 90 percent of the rated rotational speed fatigue loads and which are shown for the remainder of the 50 hours.
under § 35.15 to have a fatigue failure (2) A 50-hour ground test at takeoff mode leading to hazardous propeller ef- power and rated rotational speed.
fects.
(b) Variable-pitch propellers must be (b) The fatigue limits must take into subjected to one of the following tests: account: (1) A 110-hour endurance test that (1) All known and reasonably foresee- must include the following conditions: able vibration and cyclic load patterns (i) Five hours at takeoff power and that are expected in service; and rotational speed and thirty 10-minute (2) Expected service deterioration, cycles composed of: variations in material properties, man- (A) Acceleration from idle, ufacturing variations, and environ- (B) Five minutes at takeoff power mental effects.
and rotational speed, (c) A fatigue evaluation of the pro- (C) Deceleration, and peller must be conducted to show that (D) Five minutes at idle.
hazardous propeller effects due to fa- (ii) Fifty hours at maximum contin- tigue will be avoided throughout the uous power and rotational speed, intended operational life of the pro- (iii) Fifty hours, consisting of ten 5- peller on either: hour cycles composed of: (1) The intended airplane by com- (A) Five accelerations and decelera- plying with § 23.2400(c) or § 25.907 of this tions between idle and takeoff power chapter, as applicable; or and rotational speed, 14 CFR Ch. I (1–1–25 Edition) § 35.40 (B) Four and one half hours at ap- tenance action at the maximum pro- proximately even incremental condi- peller overspeed condition. This may tions from idle up to, but not includ- be accomplished by: ing, maximum continuous power and (1) Performance of 20 runs, each of 30 rotational speed, and seconds duration, at the maximum pro- (C) Thirty minutes at idle.
peller overspeed condition; or (2) The operation of the propeller (2) Analysis based on test or service throughout the engine endurance tests experience.
prescribed in part 33 of this chapter.
(b) When the applicant seeks ap- (c) An analysis based on tests of pro- proval of a transient maximum pro- pellers of similar design may be used in peller overtorque, the applicant must place of the tests of paragraphs (a) and demonstrate that the propeller is capa- (b) of this section.
ble of further operation without main- tenance action at the maximum pro- [Amdt. 35–8, 73 FR 63348, Oct. 24, 2008] peller overtorque condition. This may § 35.40 Functional test.
be accomplished by: The variable-pitch propeller system (1) Performance of 20 runs, each of 30 must be subjected to the applicable seconds duration, at the maximum pro- functional tests of this section. The peller overtorque condition; or same propeller system used in the en- (2) Analysis based on test or service durance test (§ 35.39) must be used in experience.
the functional tests and must be driven [Amdt. 35–8, 73 FR 63349, Oct. 24, 2008] by a representative engine on a test stand or on an airplane. The propeller § 35.42 Components of the propeller must complete these tests without evi- control system.
dence of failure or malfunction. This The applicant must demonstrate by test may be combined with the endur- tests, analysis based on tests, or serv- ance test for accumulation of cycles.
ice experience on similar components, (a) Manually-controllable propellers.
that each propeller blade pitch control Five hundred representative flight cy- system component, including gov- cles must be made across the range of ernors, pitch change assemblies, pitch pitch and rotational speed.
locks, mechanical stops, and feathering (b) Governing propellers. Fifteen system components, can withstand cy- hundred complete cycles must be made clic operation that simulates the nor- across the range of pitch and rota- mal load and pitch change travel to tional speed.
which the component would be sub- (c) Feathering propellers. Fifty cy- jected during the initially declared cles of feather and unfeather operation overhaul period or during a minimum must be made.
of 1,000 hours of typical operation in (d) Reversible-pitch propellers. Two service.
hundred complete cycles of control must be made from lowest normal [Amdt. 35–8, 73 FR 63349, Oct. 24, 2008] pitch to maximum reverse pitch. Dur- ing each cycle, the propeller must run § 35.43 Propeller hydraulic compo- for 30 seconds at the maximum power nents.
and rotational speed selected by the Applicants must show by test, vali- applicant for maximum reverse pitch.
dated analysis, or both, that propeller (e) An analysis based on tests of pro- components that contain hydraulic pellers of similar design may be used in pressure and whose structural failure place of the tests of this section.
or leakage from a structural failure [Amdt. 35–8, 73 FR 63349, Oct. 24, 2008] could cause a hazardous propeller ef- fect demonstrate structural integrity § 35.41 Overspeed and overtorque.
by: (a) When the applicant seeks ap- (a) A proof pressure test to 1.5 times proval of a transient maximum pro- the maximum operating pressure for peller overspeed, the applicant must one minute without permanent defor- demonstrate that the propeller is capa- mation or leakage that would prevent ble of further operation without main- performance of the intended function.
Federal Aviation Administration, DOT Pt. 35, App. A (6) Scheduling information for each part of (b) A burst pressure test to 2.0 times the propeller that provides the recommended the maximum operating pressure for periods at which it should be cleaned, ad- one minute without failure. Leakage is justed, and tested, the applicable wear toler- permitted and seals may be excluded ances, and the degree of work recommended from the test.
at these periods. However, the applicant may refer to an accessory, instrument, or equip- [Amdt. 35–8, 73 FR 63349, Oct. 24, 2008] ment manufacturer as the source of this in- formation if it shows that the item has an §§ 35.45–35.47 [Reserved] exceptionally high degree of complexity re- quiring specialized maintenance techniques, test equipment, or expertise. The rec- ommended overhaul periods and necessary A PPENDIX A TO P ART 35—I NSTRUCTIONS cross-references to the Airworthiness Limi- FOR C ONTINUED A IRWORTHINESS tations section of the manual must also be included. In addition, the applicant must in- A 35.1 GENERAL clude an inspection program that includes (a) This appendix specifies requirements the frequency and extent of the inspections for the preparation of Instructions for Con- necessary to provide for the continued air- tinued Airworthiness as required by § 35.4. worthiness of the propeller.
(b) The Instructions for Continued Air- (7) Troubleshooting information describing worthiness for each propeller must include probable malfunctions, how to recognize the Instructions for Continued Airworthiness those malfunctions, and the remedial action for all propeller parts. If Instructions for for those malfunctions.
Continued Airworthiness are not supplied by (8) Information describing the order and the propeller part manufacturer for a pro- method of removing and replacing propeller peller part, the Instructions for Continued parts with any necessary precautions to be Airworthiness for the propeller must include taken.
the information essential to the continued (9) A list of the special tools needed for airworthiness of the propeller.
maintenance other than for overhauls.
(c) The applicant must submit to the FAA (b) Propeller Overhaul Section. (1) Dis- a program to show how changes to the In- assembly information including the order structions for Continued Airworthiness made and method of disassembly for overhaul.
by the applicant or by the manufacturers of (2) Cleaning and inspection instructions propeller parts will be distributed.
that cover the materials and apparatus to be used and methods and precautions to be A 35.2 FORMAT taken during overhaul. Methods of overhaul (a) The Instructions for Continued Air- inspection must also be included.
worthiness must be in the form of a manual (3) Details of all fits and clearances rel- or manuals as appropriate for the quantity evant to overhaul.
of data to be provided.
(4) Details of repair methods for worn or (b) The format of the manual or manuals otherwise substandard parts and components must provide for a practical arrangement.
along with information necessary to deter- mine when replacement is necessary.
A 35.3 CONTENT (5) The order and method of assembly at The contents of the manual must be pre- overhaul.
pared in the English language. The Instruc- (6) Instructions for testing after overhaul.
tions for Continued Airworthiness must con- (7) Instructions for storage preparation in- tain the following sections and information: cluding any storage limits.
(a) Propeller Maintenance Section. (1) Intro- (8) A list of tools needed for overhaul.
duction information that includes an expla- nation of the propeller’s features and data to A 35.4 AIRWORTHINESS LIMITATIONS SECTION the extent necessary for maintenance or pre- ventive maintenance. The Instructions for Continued Airworthi- (2) A detailed description of the propeller ness must contain a section titled Airworthi- and its systems and installations. ness Limitations that is segregated and (3) Basic control and operation information clearly distinguishable from the rest of the describing how the propeller components and document. This section must set forth each systems are controlled and how they oper- mandatory replacement time, inspection in- ate, including any special procedures that terval, and related procedure required for apply. type certification. This section must contain (4) Instructions for uncrating, acceptance a legible statement in a prominent location checking, lifting, and installing the pro- that reads: ‘‘The Airworthiness Limitations peller. section is FAA approved and specifies main- (5) Instructions for propeller operational tenance required under §§ 43.16 and 91.403 of checks. the Federal Aviation Regulations unless an 14 CFR Ch. I (1–1–25 Edition) Pt. 36 alternative program has been FAA ap- Subparts L–N [ Reserved ] proved.’’ Subpart O—Documentation, Operating [Amdt. 35–5, 45 FR 60182, Sept. 11, 1980, as Limitations and Information amended by Amdt. 35–6, 54 FR 34330, Aug. 18, 1989] 36.1501 Procedures, noise levels and other information.
36.1581 Manuals, markings, and placards.
PART 36—NOISE STANDARDS: AIR- 36.1583 Noncomplying agricultural and fire CRAFT TYPE AND AIRWORTHI- fighting airplanes.
NESS CERTIFICATION A PPENDIX A TO P ART 36—A IRCRAFT N OISE M EASUREMENT AND E VALUATION U NDER Subpart A—General § 36.101 APPENDIX B TO P ART 36—N OISE L EVELS FOR Sec.
T RANSPORT C ATEGORY AND J ET A IR - 36.1 Applicability and definitions.
PLANES U NDER § 36.103 36.2 Requirements as of date of application.
A PPENDIXES C–E TO P ART 36 [R ESERVED ] 36.3 Compatibility with airworthiness re- A PPENDIX F TO P ART 36—F LYOVER N OISE R E - quirements.
QUIREMENTS FOR P ROPELLER -D RIVEN 36.5 Limitation of part.
S MALL A IRPLANE AND P ROPELLER -D RIVEN , 36.6 Incorporations by reference.
COMMUTER C ATEGORY A IRPLANE C ERTIFI - 36.7 Acoustical change: Transport category CATION T ESTS P RIOR TO DECEMBER 22, 1988 large airplanes and jet airplanes.
A PPENDIX G TO P ART 36—T AKEOFF N OISE R E - 36.9 Acoustical change: Propeller-driven QUIREMENTS FOR P ROPELLER -D RIVEN small airplanes and propeller-driven S MALL A IRPLANE AND P ROPELLER -D RIVEN , commuter category airplanes.
COMMUTER C ATEGORY A IRPLANE C ERTIFI - 36.11 Acoustical change: Helicopters.
CATION T ESTS ON OR A FTER D ECEMBER 22, 36.13 Acoustical change: Tiltrotor aircraft.
A PPENDIX H TO P ART 36—N OISE R EQUIRE - Subpart B—Transport Category Large MENTS FOR H ELICOPTERS U NDER S UBPART Airplanes and Jet Airplanes H A PPENDIX I TO P ART 36 [R ESERVED ] 36.101 Noise measurement and evaluation.
A PPENDIX J TO P ART 36—A LTERNATIVE N OISE 36.103 Noise limits.
C ERTIFICATION P ROCEDURE F OR H ELI - 36.105 Flight Manual Statement of Chapter COPTERS U NDER S UBPART H H AVING A 4 equivalency.
M AXIMUM C ERTIFICATED T AKEOFF W EIGHT 36.106 Flight Manual statement of Chapter O F N OT M ORE T HAN 7,000 POUNDS 14 noise level equivalency.
A PPENDIX K TO P ART 36—N OISE R EQUIRE - MENTS FOR T ILTROTORS U NDER S UBPART K Subpart C [ Reserved ] A UTHORITY : 42 U.S.C. 4321 et seq.; 49 U.S.C.
Subpart D—Noise Limits for Supersonic 106(g), 40113, 44701–44702, 44704, 44715; sec. 305, Transport Category Airplanes Pub. L. 96–193, 94 Stat. 50, 57; E.O. 11514, 35 FR 4247, 3 CFR, 1966–1970 Comp., p. 902.
36.301 Noise limits: Concorde.
S OURCE : Docket No. 9337, 34 FR 18364, Nov.
18, 1969, unless otherwise noted.
Subpart E [ Reserved ] Subpart F—Propeller Driven Small Airplanes Subpart A—General and Propeller-Driven, Commuter Cat- egory Airplanes § 36.1 Applicability and definitions.
(a) This part prescribes noise stand- 36.501 Noise limits.
ards for the issue of the following cer- Subpart G [ Reserved ] tificates: (1) Type certificates, and changes to Subpart H—Helicopters those certificates, and standard air- worthiness certificates, for subsonic 36.801 Noise measurement.
transport category large airplanes, and 36.803 Noise evaluation and calculation.
36.805 Noise limits. for subsonic jet airplanes regardless of category.
Subparts I–J [ Reserved ] (2) Type certificates and changes to those certificates, standard airworthi- Subpart K—Tiltrotors ness certificates, and restricted cat- egory airworthiness certificates, for 36.1101 Noise measurement and evaluation.
36.1103 Noise limits. propeller-driven, small airplanes, and