b. Supplemental Information
(1) Aircraft Configuration for Noise Certification: An applicant’s proposal for an aircraft configuration to be certified under the requirements of part 36 must include any type design changes that may be a result of airworthiness standards testing and analysis, and which would result in acoustical changes (See section 36.1(c), Supplemental Information item number (2) for FAA criteria on when aircraft type design changes represent an acoustical change). If an applicant does not propose the appropriate aircraft configuration, additional noise certification testing and analysis may be required.
c. Procedures
None
16. Section 36.1(c).
Each person who applies under 14CFR part 21 of this chapter for approval of an acoustical change described in § 21.93(b) of this chapter must show that the aircraft complies with the applicable provisions of Sections 36.7, 36.9, or 36.11 of this part in addition to the applicable airworthiness requirements of this chapter.
a. Explanation:
This section specifies part 36 requirements when “ voluntary” changes are made to the type design of an aircraft under the provisions of part 21.
b. Supplemental Information:
(1) Acoustical Change: Part 21, section 21.93(b) defines an aircraft “acoustical change” and specific aircraft configurations excepted from part 36 requirements. The text of part 21, section 21.93(b) is as follows (Also see paragraph 6-3(i) of reference 7 of this AC).
(b) For the purpose of complying with part 36 of this chapter, and except as provided in paragraphs (b)(2), (b)(3), and (b)(4) of this section, any voluntary change in the type design of an aircraft that may increase the noise levels of that aircraft is an “acoustical change” (in addition to being a minor or major change as classified in paragraph in paragraph (a) of this section) for the following aircraft:
(1) Transport category large airplanes.
(2) Jet (Turbojet powered) airplanes (regardless of category). For airplanes to which this paragraph applies, “acoustical changes” do not include changes in type design that are limited to one of the following– (I) Gear down flight with one or more retractable landing gear down during the entire flight, or
(ii) Spare engine and nacelle carriage external to the skin of the airplane (and return of the pylon or other external mount), or
(iii) Time-limited engine and/or nacelle changes, where the change in type design specifies that the airplane may not be operated for a period of more than 90 days unless compliance with the applicable acoustical change provisions of part 36 of this chapter is shown for that change in type design.
(3) Propeller driven commuter category and small airplanes in the primary, normal, utility, acrobatic, transport, and restricted categories, except for airplanes that are:
(I) Designated for “agricultural aircraft operations” (as defined in 34 137.3 of this chapter, effective January 1, 1966) to which § 36.1583 of this chapter does not apply, or
(ii) Designated for dispensing fire fighting materials to which § 36.1583 of this chapter does not apply, or
(iii) US registered, and that had flight time prior to January 1, 1955 or
(iv) Land configured aircraft reconfigured with floats or skis. This reconfiguration does not permit further exception from the requirements of this section upon any acoustical change not enumerated in § 21.93(b).
(4) Helicopters, (except for those helicopters that are designated exclusively for “agricultural aircraft operations”, as defined in § 137.2 of this chapter, as effective on January 1, 1966, for dispensing fire fighting materials, or for carrying external loads, as defined in § 133.1(b) of this chapter, as effective on December 20, 1976). For helicopters to which this paragraph applies, “acoustical changes” include the following type design changes:
(i) Any changes to, or removal of, a muffler or other component designed for noise control.
(ii) Any other design or configuration change (including a change in the operating limitations of the aircraft) that, based on FAA-approved analytical or test data, the Administrator determines may result in an increase in noise level.”
(2) Voluntary Changes in Type Design: A voluntary change in the configuration of an aircraft means a change in the type design of that aircraft. Examples of voluntary changes in aircraft type design that may affect part 36 certificated noise levels are as follows:
i. Increased engine thrust (power) to improve aircraft performance;
ii. Maximum gross weight changes;
iii. Limitations on operational flap settings related to noise;
iv. Hardware revisions (e.g., vortex generators, flap configuration, wing tip stabilizers, wing tip fuel tanks, etc.);
v. Engine modifications to improve engine performance, acceleration, deceleration, or surge margin protection;
vi. Addition of wing or body hardware to improve aerodynamics;
vii. External nacelle changes to improve air flow patterns;
viii. Engine inlet changes to improve ice protection;
ix. Reduction of engine blade tip clearances to improve inlet flow characteristics, and;
x. Modifications to engine/nacelle acoustic treatments.
(3) Acoustical Change Criteria: A voluntary change in the type design of an aircraft that may result in an increase in its certificated noise levels is defined as an “ acoustical change.” The numerical criteria used by the FAA in defining an acoustical change is a change in certificated flyover, lateral or approach noise levels of
0.10 EPNdB/dB (A) (if such changes are not formally tracked by an FAA approved method) or 0.30 EPNdB/dB (A) if an applicant has obtained an FAA approved plan to track and sum cumulative changes. These criteria are also provided in section 1.4.3 of the appended ICAO TM and are established to limit the cumulative effects of multiple small changes.
(4) No Acoustical Changes: Type design changes that do not result in an “ acoustical change” as defined in part 21, section 21.93(b) are referred to as “no acoustical changes” (NAC).
(5) NAC Cumulative Effects: When type design changes result in reduced noise levels, an applicant may elect not to provide the full part 36 substantiation, but instead provide FAA with data and/or information to substantiate a NAC. However subsequent type design changes may require full part 36 certification because of cumulative acoustical effects. Example: An applicant proposes a configuration change which will reduce the noise levels by approximately 2.1 dB for the flyover noise measurement point, 1.1 dB for the lateral noise measurement point, and with no change in noise level at the approach noise measurement point.
FAA verifies that the noise levels were reduced, and the applicant accepts the pre-change configuration certificated noise levels as published in the AFM to apply to this change in type design. The applicant may not make another type design change as a NAC that increases the flyover noise level and the lateral noise level without providing substantiation of the cumulative effects of this type design change on AFM noise certificated levels. Multiple type design changes must be evaluated on a cumulative basis (as a combined single configuration) for each noise measurement point for the purposes of determining whether there is an acoustical change.
(6) Non-Standard Jet Airplane Configurations: Sections 21.93(b)(2)(i) and (ii) specify exceptions under which certain changes in jet airplane type design are not subject to compliance with 14 CFR part 36 requirements because such configurations are not intended for normal operations, but are typically required for maintenance operations (e.g., ferry flights, transporting engines to aircraft that cannot be ferried, etc.).
(7) Time-Limited Changes: Time-Limited engine or nacelle changes on jet airplanes for periods of up to 90 days (as specified in part 21, section 21.93(b)(2)(iii)) may be necessary for continued airplane operation until maintenance can be performed on the original engines or nacelles that were changed. These changes must comply with applicable airworthiness standards and the maintenance, preventative maintenance, rebuilding and alteration inspection requirements of part 43. Such changes do not require compliance with part 36 requirements even though they may result in an increase in airplane noise levels, relative to the certificated noise levels. FAA policy (See Federal Register Vol. 64, No. 225, Page 65655, dated November 23, 1999) permits the 90 day period allowed by part 21, section 21.93(b)(2)(iii) to continue to be used after December 31, 1999, but only for maintenance-related purposes. It cannot be used for meeting Stage 3 requirements due to lack of an adequate number of spare engines or nacelles, or insufficient number of engines or nacelles to operate a Stage 3 fleet at a given time. Section 21.93(b)(2)(iii) may only be used to intermix engines when maintenance is required and no conforming engine or nacelle for the configuration is available.
(8) Special Purpose Aircraft: Type design changes to propeller-driven small airplanes and helicopters do not need to comply with the provisions of part 36 when they are operated for special purposes as specified in part 21, sections 21.93(b)(3)(i-iv) and 21.93(b)(4).
c. Procedures
(1) Applicant’s Responsibility: Pursuant to section 21.93(b), an applicant must identify type design changes that affect an aircraft’s certificated noise levels by aircraft serial number and must demonstrate part 36 compliance for those aircraft. The noise levels approved by the FAA for the modified aircraft must be documented in an FAA Approved AFM or RFM by either a revision to the AFM or RFM (typically an option only available to the aircraft manufacturer), an AFM or RFM Supplement (for Supplemental Type Certificates and Field Approvals), or a Supplemental AFM or RFM (for aircraft that do not have a FAA Approved AFM or RFM).
Configurations and modifications for which noise approval is required must be found to comply with applicable airworthiness requirements specified in part 21 as well as the requirements of part 36 [reference section 36.3].
(2) NAC Approvals: FAA may approve results of component laboratory demonstrations, backto-back noise comparisons from ground tests or flight tests of each configuration, acoustical analyses, etc as acceptable for substantiating that an applicant’s proposed changes to an aircraft type design is an NAC. The results from these evaluations must be applicable to an aircraft’s certified noise levels at the part 36 reference noise measurement points.
17. Section 36.1(d)
Each person who applies for the original issue of a standard airworthiness certificate for a subsonic transport category large airplane or for a jet airplane under14CFR part 21 § 21.183 must, regardless of date of application, show compliance with the following provisions of this part (including Appendix B):
(1) The provisions of this part in effect on December 1, 1969, for subsonic airplanes that have not had any flight time before-- (I) December 1, 1973, for airplanes with maximum weights greater than 75,000 pounds, except for airplanes that are powered by Pratt & Whitney Turbo Wasp JT3D series engines;
(ii) December 31, 1974, for airplanes with maximum weights greater than 75,000 pounds and that are powered by Pratt & Whitney Turbo Wasp JT3D series engines; and
(iii) December 31, 1974, for airplanes with maximum weights of 75,000 pounds and less.
(2) The provisions of this part in effect on October 13, 1977, including the stage 2 noise limits, for Concorde airplanes that have not had flight time before January 1, 1980.
a. Explanation
None
b. Supplemental Information
(1) Requirements for Issuance of Airworthiness Certificates: An airworthiness certificate is issued for each airplane produced, and is a means of distinguishing (by date of issuance) airplanes within a production run that comply with the noise certification requirements of part 36. Prior to the original issuance of a standard airworthiness certificate (see part 21, section 21.183) and regardless of the date of application for certification, compliance with the regulatory requirements of part 36 (including Appendix B) is required for a transport category large airplane, or for a jet airplane regardless of category (see paragraph 6-3(k)(1) of reference 7 of this AC). The following Table summarizes the requirements of section 36.1(d).
Maximum Airplane Weights Airplane Types Engine Configuration Effective Date of part36 Compliance Date for Airplanes With Initial Flight Time on or After
75,000 pounds or less Subsonic All engines December 1, 1969 December 31, 1974 Greater than 75,000 Subsonic Without Pratt & Whitney JT3D engines December 1, 1969 December 1, 1973 Greater than 75,000 Subsonic With Pratt & Whitney JT3D engines December 1, 1969 December 31, 1974 Concorde – all weights Supersonic All engines October 13, 1977 January 1, 1980
(2) “Grandfathered” Airplanes: Airplane types not identified above are “grandfathered” airplanes and are permitted to continue normal operations without showing compliance with the requirements of part 36.
For example, the twin-engine propeller-driven Convair 580 or Douglas DC-3 airplanes that first logged flight time before December 31, 1974, did not have to comply with the noise provisions of part 36 and may have received a standard airworthiness certificate under the provisions of part 21, section 21.183, or may have received a standard airworthiness certificate under the provisions of the regulations in effect at the time of certification without compliance with part 36.
c. Procedures:
None.
18. Section 36.1(e)
Each person who applies for the original issue of a standard airworthiness certificate under part 21, § 21.183, or for the original issue of a restricted category airworthiness certificate under 1 part 21, § 21.185, for propeller-driven, commuter category airplanes for a propeller-driven small airplane that has not had any flight time before January 1, 1980, must show compliance with the applicable provisions of this part.
a. Explanation
None
b. Supplemental Information
(1) Requirements for Issuance of Airworthiness Certificates: An applicant must show compliance of individual airplanes with the requirements of part 36 prior to issuance of airworthiness certificates, as prescribed in part 21, section 21.183 or 21.185 (see paragraph 6-3(k)(2) of reference 7 of this AC).
(2) Commuter Category Airplanes: Since airworthiness standards for commuter category airplanes became effective February 17, 1987, (under part 21, Amendment 21-59) there are no airplanes in this category with initial flight time before January 1, 1980. All commuter category airplanes are thus required to show compliance with the noise certification requirements of part 36.
c. Procedures
None.
19. Section 36.1(f)
For the purpose of showing compliance with this part for transport category large airplanes and jet-airplanes regardless of category, the following terms have the following meanings:
(1) A "Stage 1 noise level" means a flyover, lateral or approach noise level greater than the Stage 2 noise limits prescribed in section B36.5(b) of Appendix B of this part.
(2) A "Stage 1 airplane" means an airplane that has not been shown under this part to comply with the flyover, lateral, and approach noise levels required for Stage 2 or Stage 3 airplanes.
(3) A "Stage 2 noise level" means a noise level at or below the Stage 2 noise limits prescribed in section B36.5(b) of Appendix B of this part but higher than the Stage 3 noise limits prescribed in section B36.5(c) of Appendix B of this part.
(4) A "Stage 2 airplane" means an airplane that has been shown under this part to comply with Stage 2 noise levels prescribed in section B36.5(b) of Appendix B of this part (including use of the applicable tradeoff provisions specified in section B36.6) and that does not comply with the requirements for a Stage 3 airplane.
(5) A "Stage 3 noise level" means a noise level at or below the Stage 3 noise limits prescribed in section B36.5(c) of Appendix B of this part.
(6) A "Stage 3 airplane" means an airplane that has been shown under this part to comply with Stage 3 noise levels prescribed in section B36.5(c) of Appendix B of this part (including use of the applicable tradeoff provisions specified in section B36.6).
(7) A "subsonic airplane" means an airplane for which the maximum operating limit speed, Mom does not exceed a Mach number of 1.
(8) A "supersonic airplane" means an airplane for which the maximum operating limit speed, Mmo exceeds a Mach number of 1.
20. Section 36.1(g)
For the purpose of showing compliance with this part for transport category large airplanes and jet airplanes regardless of category, each airplane may not be identified as complying with more than one stage or configuration simultaneously.
a. Explanation
This section specifies that each airplane configuration may be certificated to noise levels within the noise limits established for one stage only.
b. Supplemental Information
(1) In-flight Configuration Changes: In-flight changes in an airplane configuration (including changes in maximum gross weight) that could result in multiple certificated noise levels for a given noise measurement point or stage classification are not permitted. They are changes in the airplane type design and therefore require a change in operating limitations. A change in maximum gross weight requires an applicant to remove an airplane from service, and comply with the approval procedures of part 43.5 and 43.7. The type design approval procedures under part 21 must be followed if the change does not have prior certification approval.
c. Procedures
None
21. Section 36.1(h)
For the purpose of showing compliance with this part, for helicopters in the primary, normal, transport, and restricted categories, the following terms have the specified meanings:
(1) Stage 1 noise level means a takeoff, flyover, or approach noise level greater than the Stage 2 noise limits prescribed in section H36.305 of Appendix H of this part, or a flyover noise level greater than the Stage 2 noise limits prescribed in section J36.305 of appendix J of this part.
(2) Stage 1 helicopter means a helicopter that has not been shown under this part to comply with the takeoff, flyover, and approach noise levels required for Stage 2 helicopters as prescribed in section H36.305 of Appendix H of this part, or a helicopter that has not been shown under this part to comply with the flyover noise level required for Stage 2 helicopters as prescribed in section J36.305 of Appendix J of this part.
(3) Stage 2 noise level means a takeoff, flyover, or approach noise level at or below the Stage 2 noise limits prescribed in section H36.305 of Appendix H of this part, or a flyover noise level at or below the Stage 2 limit prescribed in section J36.305 of Appendix J of this part.
(4) Stage 2 helicopter means a helicopter that has been shown under this part to comply with Stage 2 noise limits (including applicable tradeoffs) prescribed in section H36.305 of Appendix H of this part, or a helicopter that has been shown under this part to comply with the Stage 2 noise limit prescribed in section J36.305 of Appendix J of this part.
a. Explanation
None
b. Supplemental Information
(1) The Stage 1 noise limits apply to all helicopters for which application for a type certificate or a change in type design was made prior to March 6, 1986.
(2) The Stage 2 noise levels apply to all helicopters for which application for a type certificate or a change in type design is made on or after March 6, 1986, with the following exception. For helicopters for which application for issuance of an original type certificate in the normal, transport or restricted category is made on or after March 6, 1986, and which the FAA finds to be the first civil version of a helicopter which was designed and constructed for, and accepted for operational use by an Armed Force of the U.S. or the U.S. Coast Guard on or before March 6, 1986, it must be shown that the noise levels of the helicopter certificated under the provisions of Appendix H are no greater than Stage 2 levels plus 2 EPNdB at each measuring point. There is no
corresponding provision under Appendix J. The tradeoff provision of H36.305(b) may not be used to show compliance with Stage 2 levels plus 2 EPNdB, nor may they be used to increase any noise level beyond these limits. Subsequent civil versions (acoustic changes) must meet the Stage 2 requirements without the extra 2 EPNdB at each measuring point. The tradeoff provisions of H36.305(b) may be used in showing stage 2 compliance for these subsequent versions.
(3) Helicopters Excepted: Helicopters that are designated exclusively for agricultural aircraft operations, as defined in part 137, section 137.3, for dispensing fire fighting materials, or for carrying external loads, as defined in part 133, section 133.1(b) are excluded from the noise certification requirements.
(4) Stage 1/Stage 2: A helicopter, with a maximum take-off weight of 6000lbs (2,721kg) or less, that marginally fails to comply with the Stage 2 noise limit (by ~0.5 dB margin) prescribed in appendix J (section J36.305) has the alternative to comply with the Stage 2 noise limit of Appendix H (section H36.305). Note: The Appendix J noise limit uses a sound exposure level (SEL) that was defined more stringent by approximately 2 dB than the corresponding average of the three Appendix H noise limits in EPNL. However, this is no guarantee that subsequent Appendix H noise certification testing will comply, especially for a military helicopter seeking civil certification.
c. Procedures
None
22. Section 36.2 Requirements as of date of application.
(a) Section 21.17 of this chapter notwithstanding, each person who applies for a type certificate for an aircraft covered by this part, must show that the aircraft meets the applicable requirements of this part that are effective on the date of application for that type certificate. When the time interval between the date of application for the type certificate and the issuance of the type certificate exceeds 5 years, the applicant must show that the aircraft meets the applicable requirements of this part that were effective on a date, to be selected by the applicant, not earlier than 5 years before the issue of the type certificate.
(b) Section 21.101(a) of this chapter notwithstanding, each person who applies for an acoustical change to a type design specified in § 21.93(b) of this chapter must show compliance with the applicable requirements of this part that are effective on the date of application for the change in type design. When the time interval between the date of application for the change in type design and the issuance of the amended or supplemental type certificate exceeds 5 years, the applicant must show that the aircraft meets the applicable requirements of this part that were effective on a date, to be selected by the applicant, not earlier than 5 years before the issue of the amended or supplemental type certificate.
(c) If an applicant elects to comply with a standard in this part that was effective after the filing of the application for a type certificate or change to a type design, the election:
(1) must be approved by the FAA;
(2) must include standards adopted between the date of application and the date of the election;
(3) may include other standards adopted after the standard elected by the applicant as determined by the FAA.
a. Explanation
Section 36.2 specifies the applicable part 36 requirements to be those in effect on the date of application for the a) aircraft type certificate or b) change in type design. If the time interval between application for the type certificate (or change in type design) and the issuance of the type certificate (or amended or supplemental type certificate) exceeds 5 years, the applicable part 36 requirements are those in effect, on a date to be selected by the applicant, not earlier than 5 years before the date of issuance of the type certificate, amended type certificate, or supplemental type certificate.
Section 36.2(c) permits the applicant to elect to demonstrate compliance with a later part 36 standard than is required by section 36.2(a) or (b). For the purposes of Section 36.2, “standard” refers to any of the requirements contained in part 36. As specified in sections 36.2(c)(1) and (2), an applicant’s election of a later standard is subject to FAA approval, and the election must include standards adopted between the date of application and the effective date of the standard that the applicant has elected to comply with. Thus, an applicant’s election to demonstrate compliance with a particular later standard would also require that compliance be demonstrated with all other part 36 standards (applicable to the aircraft type) adopted between the date of application and the effective date of the standard that the applicant has elected to comply with. Further, in accordance with section 36.2(c)(3), the FAA may require compliance with other standards that were adopted after the date of the elected standard. For the purposes of section 36.2(c)(3), “other standards” refers to other 14 CFR part 36 standards. For example, if the compliance standard elected under section 36.2(c)(3) had later been revised, the FAA may determine that it is appropriate for compliance to be demonstrated with the revised standard. Such a determination would also require that compliance be demonstrated with all other part 36 standards (applicable to the aircraft type) adopted between the date of application and the effective date of the standard that the FAA has determined to be the appropriate compliance basis.
b. Supplemental Information
None
c. Procedures
None
23. Section 36.3 Compatibility with airworthiness requirements
It must be shown that the aircraft meets the airworthiness regulations constituting the type certification basis of the aircraft under all conditions in which compliance with this part is shown, and that all procedures used in complying with this part, and all procedures and information for the flight crew developed under this part, are consistent with the airworthiness regulations constituting the type certification basis of the aircraft.
a. Explanation
None
b. Supplemental Information
None
c. Procedures
(1) Aircraft certification tests and analyses must be conducted using configurations, procedures and information which are consistent with the airworthiness regulations applicable to that aircraft. For example, noise tests or analyses may not be conducted with landing flap settings which could not meet the applicable airworthiness regulation requirements.
24. Section 36.5 Limitation of part
Pursuant to 49 U.S.C. 1431(b)(4), the noise levels in this part have been determined to be as low as is economically reasonable, technologically practicable, and appropriate to the type of aircraft to which they apply. No determination is made, under this part, that these noise levels are or should be acceptable or unacceptable for operation at, into, or out of, any airport.
a. Explanation
This section specifies legal limitations regarding part 36.
b. Supplemental Information
(1) Scope of part 36 Regulation: Part 36 requires compliance with U.S. Government noise standards for aircraft type and airworthiness certification but does not include noise standards related to aircraft operations, such as is provided in part 91. Part 36 certificated noise levels are achieved using procedures which can be duplicated practicably in normal operations by flight crews with safe reserves of thrust (power) and speed.
Public Law 103-272 (reference 2 of this AC), mandates that the Administrator of the FAA prescribe standards to measure and evaluate aircraft noise. Under this law, an original type certificate may be issued for an aircraft for which substantial noise abatement can be achieved only after the FAA Administrator prescribes standards and regulations that apply to that aircraft. Consideration must be given to relevant information on aircraft noise, consultations with appropriate US and State authorities, whether the standards or regulations are consistent with the highest degree of safety and are economically reasonable, technologically practical, and appropriate for the type of aircraft to which they apply.
c. Procedures
None
25. Section 36.6 Incorporations by reference
26. Section 36.6(a)
General. This part prescribes certain standards and procedures that are not set forth in full text in the rule. Those standards and procedures are contained in published material which is reasonably available to the class of persons affected and has been approved for incorporation by reference by the Director of the Federal Register under 5 U.S.C. 552 (a) and 1 CFR Part 51.
27. Section 36.6(b)
Incorporated matter. (1) Each publication, or part of a publication, which is referenced but not set forth in full-text in this part and which is identified in paragraph (c) of this section is hereby incorporated by reference and made a part of part 36 of this chapter with the approval of the Director of the Federal Register. (2) Incorporated matter which is subject to subsequent change is incorporated by reference according to the specific reference and to the identification statement.
Adoption of any subsequent change in incorporated matter is made under part 11 of this chapter and 1 CFR part 51.
a. Explanation
This section specifies requirements for publications or documents to be “incorporated by reference” into part 36 and the process necessary when incorporated matter is subject to subsequent change.
b. Supplemental Information
None
c. Procedures
None
28. Section 36.6(c)
Identification statement. The complete title or description, which identifies each published matter incorporated by reference in this part, is as follows:
(1) International Electrotechnical Commission (IEC) Publications.
(i) IEC Publication No. 179, entitled "Precision Sound Level Meters," dated 1973.
(ii) IEC Publication No. 225, entitled "Octave, Half-Octave, Third Octave Band Filters Intended for the Analysis of Sounds and Vibrations," dated 1966.
(iii) IEC Publication No. 651, entitled "Sound Level Meters," first edition, dated 1979.
(iv) IEC Publication No. 561, entitled "Electro-acoustical Measuring Equipment for Aircraft Noise Certification," first edition, dated 1976.
(v) IEC Publication No. 804, entitled "Integrating-averaging Sound Level Meters," first edition, dated 1985.
(vi) IEC Publication 61094-3, entitled “measurement microphones- Part 3: Primary Method for Free-Field Calibration of Laboratory Standard Microphones by the Reciprocity Technique”, first edition, dated 1995
(vii) IEC Publication 61094-4, entitled “Measurement Microphones- Part 4: Specifications for Working Standard Microphones”, first edition, dated 1995
(viii) IEC Publication 61260, entitled “Electroacoustics-Octave-Band and Fractional-Octave-Band filters”, first edition, dated 1995
(ix) IEC Publication 61265: entitled “Instruments for Measurement of Aircraft Noise- Performance Requirements for Systems to Measure One-Third-Octave-Band Sound Pressure Levels in Noise Certification of Transport-Category Aeroplanes”, first edition, dated 1995
(x) IEC Publication 60942, entitled “Electroacoustics- Sound Calibrators”, second edition, dated 1997
(2) Society of Automotive Engineers (SAE) Publications. (i) SAE ARP 866A, entitled "Standard Values at Atmospheric Absorption as a Function of Temperature and Humidity for Use in Evaluating Aircraft Flyover Noise," dated March 1975.
a. Explanation
This section identifies standards and procedures that are incorporated by reference into part 36 as requirements for noise measurement and evaluation of various aircraft types.
b. Supplemental Information
(1) Other Publications. Other publications (see reference list of the appended ICAO TM) may be useful to an applicant during implementation of an aircraft noise certification process. Applicant proposals for use of standards and procedures found in these publications must be included in an applicant’s noise compliance demonstration plan and approved by FAA. An applicant should also contact an ACO Specialist prior to submittal of a noise compliance demonstration plan to FAA to determine whether there are new standards and procedures that are applicable to his particular aircraft noise certification process.
c. Procedures
None
29. Section 36.6(d)
Availability for purchase. Published material incorporated by reference in this part may be purchased at the price established by the publisher or distributor at the following mailing addresses:
(1) IEC publications,
(i) International Electrotechnical Commission,3, rue de Varembe, Case postale 131, 1211 Geneva 20, Switzerland
(ii) American National Standard Institute, 11 West 42nd Street, New York City, New York 10036 (Electronic mail address: INFO@ANSI.org).
(2) SAE publications. Society of Automotive Engineers, Inc., 400 Commonwealth Drive, Warrentown, Pennsylvania 15096.(Electronic mail address: SAE@SAE.org)
a. Explanation
None
b. Supplemental Information
(1) Addresses of Other Organizations: Addresses for other organizations that produce technical standards, references and publications that relate to aircraft noise certification are as follows:
(i) Bureau International de Métrologie Légale 11, rue Turgot 75009 Paris, France
(ii) Engineering Science Data Unit International, Ltd.
251-259 Regent Street London, England W1R 7AD, United Kingdom
(iii) International Civil Aviation Organization 999 University Street Montreal, Quebec Canada H3C 5H7 (Electronic mail address: Sales_unit@ICAO.org)
(iv) National Institute of Standards and Technology Building 101, Room A903 Gaithersburg, Maryland 20899 (Electronic mail address: Inquiries@NIST.gov)
c. Procedures
None
30. Section 36.6(e)
Availability for inspection. A copy of each publication incorporated by reference in this part is available for public inspection at the following locations:
(1) FAA Office of the Chief Counsel, Rules Docket, Room 916, Federal Aviation Administration Headquarters Building, 800 Independence Avenue, SW., Washington, D.C.
(2) Department of Transportation, Branch Library, Room 930, Federal Aviation Administration Headquarters Building, 800 Independence Avenue, SW., Washington, D.C.
(3) The respective Region Headquarters of the Federal Aviation Administration as follows:
(i) New England Region Headquarters, 12 New England Executive Park, Burlington, Massachusetts 01803.
(ii) Eastern Region Headquarters, Federal Building, John F. Kennedy (JFK) International Airport, Jamaica, New York 11430.
(iii) Southern Region Headquarters, 1701 Columbia Avenue, College Park, Georgia, 30337.
(iv) Great Lakes Region Headquarters, O'Hare Lake Office Center, 2300 East Devon Avenue, Des Plaines, Illinois 60018.
(v) Central Region Headquarters, Federal Building, 601 East 12th Street, Kansas City Missouri 64106.
(vi) Southwest Region Headquarters,2601 Meacham Boulevard, Fort Worth, Texas 76137-4298.
(vii) Northwest Mountain Region Headquarters 1601 Lind Avenue, Southwest, Renton, Washington 98055.
(viii) Western-Pacific Region Headquarters 15000 Aviation Boulevard, Hawthorne, California 92007.
(ix) Alaskan Region Headquarters, 222 West 7th Avenue, # 14, Anchorage, Alaska 99513.
(x) European Office Headquarters, 15, Rue de la Loi (3rd Floor), B-1040 Brussels, Belgium.
a. Explanation
None
b. Supplemental Information
(1) Other DOT/FAA Addresses: Current addresses of U.S. Department of Transportation and FAA organizations (and Specialists) that might provide assistance to an applicant are as follows:
(2) FAA/DOT Offices, Washington, D.C.:
(i) FAA Office of Environment and Energy (AEE-1) Federal Aviation Administration Headquarters Building, Room 900W, 800 Independence Avenue, SW.
Washington D.C. 20591
(ii) FAA Office of the Chief Council (AGC-1) Federal Aviation Administration Headquarters Building, Room 900E 800 Independence Avenue, SW.
Washington D.C. 20591
(iii) U.S. Department of Transportation Branch Library Federal Aviation Administration Headquarters Building, Room 930 800 Independence Avenue, SW.
Washington D.C. 20591
(3) FAA Noise Certification Specialists:
(i) Rotorcraft Noise Certification Specialist (ASW-110) Federal Aviation Administration Rotorcraft Directorate 2601 Meacham Boulevard Fort Worth, Texas, 76137-4298
(mailing address:
DOT FAA Fort Worth, Texas 76193-0110)
(ii) Small Airplane Noise Certification Specialist (ACE-111) Federal Aviation Administration Small Airplane Directorate 901 Locust, Room 301