(March 15, 2007 Civil Aviation Administration of China announced 182th come into force on April 15, 2007) list of a chapter I General provisions article 36.1 of the applicable scope and definition article 36.2 36.3 Airworthiness requirements of the filing date requirements of article 36.5 of the compatibility of the provisions of article 36.6 36.7 acoustics of the reference file changes: transport category airplanes and Jets 36th .9 Article acoustic change: propeller small aircraft and propeller commuter class aircraft subsection 36.11 article acoustic change: helicopter b chapter transport class big aircraft and Jet subsection 36.101 article noise measurement and evaluation subsection 36.103 article noise limit subsection 36.105 article flight manual in the on fourth stage noise equivalent sex of description c chapter (alternate) d chapter (alternate) e chapter (alternate) f chapter propeller small aircraft and propeller     Section 36.501 commuter aircraft noise limits chapter g (standby) Chapter h 36.803 section 36.801 helicopter noise measurement of noise assessment and calculation of noise limit chapter I~N of section 36.805 (alternate) o chapter files, usage restrictions and information procedures article 36.1501, article 36.1581 of the noise level and other information manual, marks and signs 36.1583 don't have to meet noise restrictions in agriculture and fire-fighting aircraft in annex a in accordance with section 36.101 section A36.1 Introduction to measurement and evaluation of aircraft noise A36.2 noise certification test and measurement conditions received section A36.3 on the ground of article A36.4 of the aircraft noise measurement based on measurement data to calculate the effective perceived noise level of A36.5 and to article A36.6 of the Civil Aviation Administration of China to submit data characters Number and unit of atmospheric attenuation section A36.8 section A36.7 (backup) the amendment to section A36.9 aircraft flight test results of annex b, group transportation under section 36.103 B36.1 and Jet noise level measurement and assessment of noise noise metrics for the evaluation of section B36.2 section B36.3 section B36.4 test reference noise measurement point noise measuring points B36.5 maximum   Section B36.6 section B36.7 of the comprehensive evaluation of the noise level noise certification benchmark and test procedures for noise certification conditions section B36.8 Annex C-E (standby) certification tests annex f on November 17, 1988, small propeller aircraft and propeller-driven commuter airplane flew over the noise requirements part a general provisions scope of section F36.1 section F36.101 of part b noise measurement     General test conditions section F36.105 section F36.103 acoustic measurement system measurement, recording, and reproducing apparatus noise measurement procedure section F36.109 section F36.107 section F36.111 of the data records, submitted and approved flight procedures part c data amendment to section F36.201 of the amended section F36.203 section d effectiveness of noise limits F36.301 aircraft noise limit annex g certification test on or after November 17, 1988 's small propeller aircraft and propeller commuter planes take off noises to claim a part of the scope of article G36.1 of the general part b noise measurement section G36.101 section G36.103 General test conditions acoustic measurement systems G36.105 measuring, recording and playback equipment G36.10 7 noise measurement procedure section G36.109 data records, submitted and approved G36.111 flight program part c data correction amended section G36.203 section G36.201 test results the results section G36.301 of part d noise limits the effectiveness of aircraft noise limitations annex h of helicopter noise requirements under Chapter h part a baseline condition H36.     1 General test conditions H36.5 H36.3 base bar, symbols and units in part b in accordance with section 36.801 noise measuring noise certification test and measurement conditions section H36.101 section H36.105 section H36.103 departure test conditions over the test conditions section H36.107 enter H36.109 test conditions helicopter received ground noise measurement     Measured data submission and amendment of section H36.111 section H36.113 the atmosphere of acoustic attenuation in part c under section 36.803 noise evaluation and calculation of section H36.201 article H36.203 in EPNdB noise evaluation of noise level calculation section d section H36.205 detailed data correction procedures pursuant to article H36.301 section 36.805 noise limits noise measurement, assessment and calculation of Section H36.303 (backup) section H36.305 annex I noise level (standby) Annex j maximum authorized takeoff weight not more than 3175 kg (7,000 pound) helicopter based on h helicopter noise alternative certification program a part of baseline conditions section J36.1 section J36.5 article J36.3 of the General benchmark test conditions (standby) part b in accordance with section 36.801-noise Measurement of sound section J36.101 noise certification test and measurement conditions section J36.103 (backup) section J36.107 section J36.105 flew over the test condition (backup) section J36.109 in the helicopter received ground noise measurement submission requirements section J36.113 section J36.111 (standby) in part c under section 36.803 noise evaluation and calculation of j 36.201, noise assessment, in SELdB section J36.203 section J36.205 a detailed noise level calculation of correction procedures in accordance with part d section 36.805 noise limitations of section J36.301 of the noise measurement, assessment and calculation of section J36.303 (backup) section J36.305 noise limitations of a chapter I General provisions article 36.1 of the applicable scope and definitions (a) these provisions The following certificates are issued and change the set noise standards: (1) the subsonic transport aircraft and subsonic jet aircraft type certificate, supplemental type certificate issuance and change of ratifications and design modifications, and a standard certificate of airworthiness issued, except as otherwise provided by the General Administration of civil aviation of China.     In these provisions, "subsonic transport aircraft and subsonic jet aircraft" means maximum take off weight of 8618 kg (19000 pounds) above the propellor-driven aircraft, and subsonic jet aircraft of any category, but required takeoff at maximum takeoff weight not more than 610 metres in length except for the jets. (2) small propeller aircraft and propeller-driven commuter aircraft type certificate, supplemental type certificate, type design approval and design approvals issued and change, as well as standard airworthiness certificates and restricted special certificate of airworthiness is issued. Section 36.1583 of the provisions enshrined in and except as otherwise provided by the General Administration of civil aviation of China.     In these provisions, "the small propeller aircraft and propeller-driven commuter aircraft" means maximum take off weight of 8618 kg (19000 pounds) and propeller-driven aircraft. (3) (alternate) (4) helicopter type certificate and supplementary type certificate, type design approvals and design approvals issued and change, as well as standard airworthiness certificates and restricted special certificate of airworthiness is issued.     Only for agricultural operations, for spraying fire-extinguishing materials or designed to carry external loads of helicopters, and except as otherwise provided by the General Administration of civil aviation of China.     (B) apply the provisions specified by the airworthiness certificate, the applicant must show that in addition to meeting Chinese civil aviation regulations in the applicable provisions, shall comply with the provisions of the applicable provisions.     (C) application of acoustic changes, the applicant must show that in addition to meeting Chinese civil aviation regulations in the applicable provisions, shall comply with the provisions of article 36.7 in 36.11, 36.9, or applicable terms and conditions.     (D) (alternate) (e) (alternate) (f) for transport class big aircraft and any category of Jet, on showed that meet this provides,, following terms has following meaning: (1) "first stage noise level" refers to flew over the, and cross side or entry noise level is greater than this provides annex b subsection B36.5 article (b) in the provides of second stage noise limit.     (2) the "first phase of aircraft" means not in accordance with these provisions indicate that the second or third stage aircraft needed to reach across the plane, lateral and approach noise levels.     (3) the second stage of "noise level" means at or below the provisions of annex b, section B36.5 (b) provided for in the second phase noise limiting, but above the provisions of annex b, section B36.5 (c) provided for in the third phase noise limits of the noise level.     (4) the second stage of "aircraft" means these provisions show that in accordance with the provisions of annex b, section B36.5 (b) provided for in the second phase of the noise limits (including use of applicable assessment provisions in section B36.6), which do not meet noise restriction requirements for phase III aircraft.     (5) "third phase noise level" means at or below the provisions of annex b, section B36.5 (c) provided for in the third phase noise limits of the noise level.     (6) "third aircraft" means these provisions show that in accordance with the provisions of annex b, section B36.5 (c) stage III noise limit laid down in (including use of applicable assessment provisions in section B36.6) of the aircraft.     (7) "subsonic aircraft" means the maximum speed limit Mmo is Mach 1 aircraft.     (8) "supersonic aircraft" means the maximum use limit Mmo than Mach 1 aircraft.     (9) "stage four noise level" means at or below the provisions of annex b, section B36.5 (d) provided for in the fourth phase noise limits of the noise level.     (10) "phase IV aircraft" means according to this provided that it does not exceed the provisions of annex b, section B36.5 (d) aircraft noise restrictions provided for in the fourth stage.     (11) "the fourth chapter noise level" means at or below entered into force on March 21, 2002 volume I of Annex 16 to the Convention on international civil aviation, 4th chapter in the 7th amendment to the maximum noise level defined in section 4.4.    (G) for transport category aircraft and jets of any kind, that is consistent with this purpose, each plane can not be confirmed to qualify more than one phase or configurations. (H) for primary class, and normal class, and transport class and limited with class of helicopter, on showed that meet this provides,, following terms has following meaning: (1) "first stage noise level" refers to took off, and flew over the or entry noise level is greater than this provides annex h of subsection H36.305 article provides of second stage noise limit, or flew over the noise is greater than this provides annex j of subsection J36.305 article provides of second stage noise limit.     (2) "first-phase helicopter" means not in accordance with the provisions of annex h indicate that compliance with these provisions set forth in section H36.305 of the second phase of takeoff, helicopter overflight and approaching noise restrictions, or has not been indicated in accordance with the provisions set out in section J36.305 of annex j of the second stage flew over helicopter noise restrictions.     (3) the second stage of "noise level" means the entry of takeoff, flying over or noise levels at or below these provisions set forth in section H36.305 of annex h of phase noise limiting, or less than stipulated in section J36.305 of annex j of this provision the second stage flew over the noise limit.     (4) the second stage of "helicopter" means to demonstrate compliance according to the provisions of the provisions set forth in section H36.305 of annex h of phase noise limiting (including the terms of application of the integrated assessment), helicopter, or has indicated that in accordance with the provisions of article J36.305 of the annex j of the second phase of helicopter noise limits. (5) "maximum normal operating speed" is by the manufacturer developed and approved by the General Administration of civil aviation of China approved airworthiness limitations the maximum rotor speed. If it provides for maximum rotor speed tolerance, maximum normal operating speed is a given tolerance limit. If the speed automatically changes with flight conditions, in the noise of the validation procedure should be using the maximum normal operating speed flight conditions.     If the pilots can change speed, noise approval procedures should be used in the manual correspond to the power limits specified in part the maximum normal operating speed. (April 15, 2007, the first amendment) article 36.2 of the filing date requirements (a) as article 21.17 21, the aircraft type certificate must show that the aircraft meets the requirements of the applicant on the date of application for type certificate valid requirements.     Application for type certificate for more than 5 years with the type certificate issued, the applicant must show that the aircraft meets the rule has been awarded type certificate valid for 5 years before the date of the request, the time can be selected by the applicant. (B) as provided under Part 21 section 21.101, applying for model design (section 21.93) acoustic changes, the applicant must show that satisfy this rule has been applied for type design changes in effect on the date of the request.     If applying for model design changes and issued type certificate amended or supplemental type certificate for more than 5 years between, the applicant must show that the aircraft meets the rule has been awarded type certificate amended or supplemental type certificate valid for 5 years before the date of the request, the time can be selected by the applicant.     (C) if the applicants meet the requirement application for type certificate or type design changes effective after the date of the standard, this selection: (1) must be approved by the Civil Aviation Administration of China.     (2) must include the date of the application and the criteria for selecting between the date of entry into force.     (3) must also include the Civil Aviation Administration of China after the applicants believe that other standards apply.     (April 15, 2007 first times Amendment) subsection 36.3 article airworthiness requirements of compatible sex must proved: aircraft in showed that meet this provides Shi, in all conditions Xia are meet constitute model qualified validation based of the airworthiness regulations; for meet this provides and take of all program, and this provides for flight unit developed of all program and information, and constitute aircraft model qualified validation based of the about airworthiness regulations Zhijian is coordination consistent of. 36.5, subject to the provisions of this article shall be determined in the economically reasonable, technically feasible and are applied with the aircraft-type conditions, noise level as low as possible.     At, entering or leaving any airports in China run, determines whether the noise level is acceptable in the present provisions, stipulated separately.     Section 36.6 references (a) overview provided for in this provision is not in the full text of these provisions set forth standards and procedures.     (B) references (1) referenced but not the full text of these provisions described in this section (c), points out that each publication or part of a publication, all belong to this part of the.     (2) reference file changes decided by the Civil Aviation Administration of China according to the actual situation of use.     (C) reference documents describe the requirements identified by the full title or description is as follows: (1) the International Electrotechnical Commission (IEC) publication (I) IEC Publication 179th, was entitled "precision sound level meters" (1973).     (Ii) IEC Publication No. 225, entitled "sound and vibration analysis in octave, one-second, octave, octave one-third filter" (1966).     (Iii) IEC Publication No. 651, entitled "sound level meters" (1979).     (Iv) IEC Publication No. 561, entitled "electro-acoustic measuring instruments for aircraft certification" (1976 version).     (V) IEC Publication No. 804, entitled "score average sound level meters" (1985 version).     (Vi) IEC Publication di61094-3hao, entitled "Methods of measurement for microphones-3rd part: using interactive technologies laboratory microphone for free-field calibration method version 1.0 (1995)".     (VII) IEC Publication di61094-4hao, entitled "Methods of measurement for microphones-part 4: microphones work standards requirements version 1.0 (1995)".     (VIII) IEC Publication No. 61260, entitled "electroacoustics – octave-band and fractional-octave-band filters version 1.0 (1995)".     (IX) IEC Publication No. 61265, entitled "electroacoustics-aviation noise measuring instruments and transport aircraft noise certification measurements in one-third of broad-band frequency sound pressure level device performance requirements, version 1.0 (1995)".     (X) IEC Publication No. 60942, entitled "electroacoustics-sound calibration, version 2.0 (1997)".     (2) the Institute of vehicle engineers (SAE) publication (I) SAE ARP866A, entitled "evaluation of aircraft flying over the noise as the temperature and humidity of atmospheric absorption function standard value" (March 15, 1975).     (3) international standards and recommended practices, entitled "environmental protection, volume I of Annex 16 to the Convention on international civil aviation, aircraft noise", issued in July 1993, third edition, March 21, 2002, issued by the 7th amendment.     (April 15, 2007, the first amendment) article 36.7 acoustic changes: transport aircraft and jets (a) scope this section applies in accordance with the regulations of the Civil Aviation of China civil aviation products and parts certification regulations (CCAR-21) application of acoustic changes approved or recognised by the transport planes and jets.     (B) General requirements except as otherwise provided, this article includes aircraft, acoustic changes approved or recognised requirements are as follows: (1) at the time showed that compliance must be in accordance with the provisions in annex a of the application procedure and conditions for the measurement and assessment of noise levels.     (2) must, in accordance with the provisions of annex b, section B36.7 and section B36.8 of the applicable requirements of that annex b noise restrictions set forth in section B36.5. (C) phase prior to the aircraft type design change is the first stage of aircraft, apart from this section, (b) the provisions of paragraph, the following apply: (1) if the aircraft in the aircraft model before the design change was the first stage, after the model design changes, the machine shall not exceed noise levels generated by the models before the design change.     Annex b to the provisions of section B36.6 of the comprehensive assessment of articles may be used to improve the phase noise level, unless the plane is the second phase of the plane.     (2) in addition: (I) in the type design changes before and after the trial period, which shall not be less than the approved maximum power of power or thrust or thrust, and (ii) in the type design during the overflight and lateral noise test carried out before the change, you must use a suitable for the most quiet approval of the maximum takeoff weight of airworthiness approval form.     (D) second stage aircraft in model design change zhiqian is second stage aircraft of, except this article (b) paragraph of content outside, following content also also applies: (1) for in model design change zhiqian letter road than for 2 or more big of high letter road than Jet engine aircraft: (I) in model design change zhihou, aircraft of noise level shall not over: (a,) each third stage noise limit plus 3EPNdB, or (b) each second stage noise limit, both take small who;     (Ii) using annex b to the provisions of section B36.6 of the comprehensive assessment to determine compliance with this paragraph relating to the second phase noise limiting or third stage with 3EPNdB noise limits (as applicable) and (iii) in the type design during the overflight and lateral noise test carried out before the change, you must use a suitable for the most quiet approval of the maximum takeoff weight of airworthiness approval form.     (2) before the type design change by-pass ratio of less than 2 high by-pass ratio Jet engine aircraft: (I) after the aircraft type design changes may be a phase plane, and (ii) type design during the overflight and lateral noise test carried out before the change, you must use a suitable for the most quiet approval of the maximum takeoff weight of airworthiness approval form.     (E) third phase of the aircraft if the aircraft before the design change was the third phase of aircraft types, subject to this section, (b) application of the provisions of the following clause: (1) (alternate) (2) if the type design changes required to meet the stage III noise levels, this aircraft type design changes must be a phase III aircraft.     (3) (alternate) (4) before the design change was the third phase of aircraft types, and is the fourth phase of the plane after the design change, aircraft must be maintained for the fourth stage.     (F) a fourth phase is the fourth phase of the aircraft before the plane model design changes, aircraft must be maintained for the fourth stage after the change.    (April 15, 2007 first times Amendment) subsection 36.9 Article acoustic change: propeller small aircraft and propeller commuter class aircraft for by China Civil Aviation Regulations civil aviation products and parts qualified validation provides (CCAR-21) application acoustic change approved or recognized of primary class, and normal class, and practical class, and stunt class, and transport class and limited with class of propeller small aircraft and propeller commuter class aircraft, following provides applies: (A) the type design according to the provisions before the change documents for some models of planes, after the change shall not exceed the noise limit of the provisions of this section 36.501.     (B) model design in accordance with this requirement before the change have any aircraft of model documents shall not exceed the larger of the following two values: (1) the provisions set out in section 36.501 noise limit, or (2) in front of the type design change in accordance with the provisions of this section 36.501 measurement and correction, noise level. (April 15, 2007, the first amendment) article 36.11 acoustic changes: helicopters this section applies to all in accordance with the regulations of the Civil Aviation of China civil aviation products and parts certification regulations (CCAR-21) application acoustic changes approved or accepted by the junior class, normal, transport category helicopters and restricted class. The compliance of the requirements of this article must be according to the provisions in annex h shows.     Maximum authorized takeoff weight not more than 3175 kg (7,000 pound) helicopter, compliance according to the provisions of this section of the annex j indicated. (A) General requirements except as otherwise provided, this article includes helicopters, acoustic changes approved or recognised requirements are as follows: (1) at the time showed that compliance, must be in accordance with the provisions set out in annex h-b and c-parts in the applicable procedures and criteria to measure, assess and evaluate noise levels.     Maximum takeoff weight of less than 3175 kg (7,000 pound) helicopter, according to the provisions in annex j of the alternative method to demonstrate compliance, and flew over the noise of the provisions set out in annex j must according to the provisions of annex j b and c are part of the application of the provisions of the procedures and conditions for measuring, assessing and calculating. (2) must, in accordance with the provisions of the applicable provisions of section d of annex h to that provided for in section H36.305 of annex h, noise level.     Annex j to this show that compliance of the helicopter, and it must be by the applicable provisions of part d of the annex to that article to the provisions of annex j of J36.305 noise level requirements for compliance. (B) the first phase of helicopters in addition to section 36.805 (c) provides, before changing the model design is the first phase of the helicopter, in model design changes, article H36.305 of annex h of the machine shall not exceed (a) (1) the prescribed noise limits. Article H36.305 shall not be used (b) integrated evaluation of noise levels exceed these limits to the first stage.     If applicants choose to annex j of this provision shows that compliance, model design for the first phase of the helicopter before the change, in model design changes, annex j shall not exceed the provisions of section J36.305 (a) under the second phase noise restrictions.     (C) phase II helicopter model design changes for the second phase of a helicopter, helicopter model design changes must remain a second stage.     (The first time on April 15, 2007 amendments) b chapter section 36.101 of transport aircraft and Jet noise measurement and evaluation for transport category aircraft and jet fighters, the noise must be according to the provisions of annex a requirements or equivalent program approved by the Civil Aviation Administration of China to measurement and assessment.     (The first time on April 15, 2007 amendments) section 36.103 noise limits (a) for subsonic transport aircraft and subsonic jet aircraft, the noise level must be according to the provisions laid down in annex a, measurement and evaluation, and according to the provisions set out in annex b of the measurement points and the test procedure section B36.8 (or an approved equivalent program) to show compliance.     (B) model validation applications submitted before January 1, 2006, you must show that the noise level does not exceed the provisions of Appendix b in the B36.5 (c) provided for in stage III noise limits. (C) type approval applied for on or after January 1, 2006 submission, you must show that the noise level does not exceed the provisions of Appendix b in B36.5 (d) provided for in the fourth phase noise restrictions. Applications can be processed by January 1, 2006, in accordance with stage IV noise certification of their own accord.     If you choose to follow the phase IV review, the provisions of article 36.7 (f) requirements apply. (April 15, 2007, the first amendment) 36.105 flight manuals to the fourth stage of noise equivalent description of all aircraft meet the noise certification requirements under phase IV, the flight manual or operating manual must include the following statement: approved by CCAR-36 in the following noise level is (insert validation of aircraft CCAR-36 on the basis of the revision number) obtained from the analysis of data obtained under test, Meet the requirements of CCAR-36 b maximum noise level under phase IV.     Civil Aviation Administration of China believes that in order to get the noise level and noise measurement and assessment procedures and entered into force on March 21, 2002 volume I of Annex 16 to the Convention on international civil aviation annex 2 the 4th chapter of the 7th amendment requires the equivalent noise level. (April 15, 2007 first times Amendment) c chapter (alternate) (April 15, 2007 first times Amendment) d chapter (alternate) e chapter (alternate) f chapter propeller small aircraft and propeller commuter class aircraft subsection 36.501 article noise limit (a) following aircraft must showed that and chapter match: (1) application issued any a model documents of normal class, and practical class, and stunt class, and transport class and limited with class propeller small aircraft, and application issued any a model documents of screw     Propeller commuter aircraft.     (2) (alternate) (3) primary category aircraft (I) subject to this section, (a) (3) (ii) provides the contents of, to apply for junior type design approval of the aircraft and not previously according to the provisions of annex f validation must demonstrate compliance with the provisions of annex g.     (Ii) on normal class, and practical class, and stunt class aircraft, in following situation Xia, no longer requirements showed that on this provides of meet sex: (a,) has has by China civil aviation regulations issued of model certificate, and (b) has has by China civil aviation regulations issued of standard airworthiness card, and (c) since model design yilai yet has had acoustic change, and (d) yiqian yet by this provides annex f or annex g validation and (e) application to primary class of aircraft. (B) is completed prior to November 17, 1988 noise certification test aircraft belong to the content of the specification, must, in accordance with Appendix f of part b and in part c or equivalent program approved by the Civil Aviation Administration of China measurement and provisions on noise levels to indicate compliance.     Must show that the aircraft's noise level is less than part d in the annex f to apply noise restrictions. (C) prior to November 17, 1988 unfinished noise certification test aircraft belong to the content of the specification, must, in accordance with annex g of part b and part c or equivalent program approved by the Civil Aviation Administration of China measurement and provisions on noise levels to indicate compliance.     Must show that the aircraft's noise level is less than part d in the annex g to the applicable noise restrictions. Chapter g (standby) Chapter h section 36.801 helicopter noise measurement for primary classes, normal classes, classes and restricted class of transport helicopters, the noise must be according to the provisions set out in part b of annex h to the test conditions and noise measurement point measurement or measurement of an equivalent program approved by the Civil Aviation Administration of China.     Maximum authorized takeoff weight not more than 3175 kg (7,000 lb) primary type, normal type, class and restricted category of transport helicopters, such as according to the provisions of annex j to demonstrate compliance, the noise must be according to the provisions set out in annex j, part b test conditions and noise measurement point measurement or measurement of an equivalent program approved by the Civil Aviation Administration of China. (April 15, 2007, the first amendment) article 36.803 noise assessment and calculated in accordance with section 36.801 requirements and according to the provisions of annex h of noise measurement data must be obtained amendments to the provisions of annex h of the baseline conditions and according to the provisions of part a of the annex h of part c or equivalent program approved by the Civil Aviation Administration of China for assessment.     Section 36.801 according to requirements and noise measurement data obtained from Annex j of this provision must be amended to part a of annex j of this provision of the baseline conditions and according to the provisions of annex j c or equivalent program approved by the Civil Aviation Administration of China for assessment.     Section 36.805 noise limits (a) subject to subsection 36.11 (b) specified, application documents for any models of primary classes, normal, transport category helicopters and restricted class, must comply with the requirements of annex h, part d second phase noise limiting, or in accordance with the provisions set out in annex j, part d's noise limits.     (B) except this article (d) (2) of provides outside, this article including of helicopter, must showed that: for according to this provides annex h showed that meet sex of helicopter, its noise level is unlikely to Yu the annex in the H36.305 article provides of applies limit, or: for according to this provides annex j showed that meet sex of helicopter, its noise level is unlikely to Yu the annex in the J36.305 article provides of applies limit.     (C) (alternate) (d) of primary category helicopters: (1) subject to paragraph (d) (2) provided, apply for a junior type design approval and not according to the provisions in annex h approval, must demonstrate compliance with annex h to this provision.     (2) for normal class and transport class helicopter, in following situation Xia, without again showed that on this provides of meet sex: (I) has by China civil aviation regulations issued of normal class or transport class model certificate, (ii) has by China civil aviation regulations issued of standard airworthiness card, (iii) no model design of acoustic change, (iv) yiqian never by this provides annex h validation had, and (v) application to primary class helicopter. I~N (backup) o chapter files, use restrictions and 36.1501, noise-level of the data and other information (a) according to this regulation in order to obtain validation of noise levels using all programs, weight, shape and configuration, and other information or data, including flight, testing and analysis of the use of an equivalent program, needed to be developed and approved.     During the type certification achieved noise levels must be included in the approved aircraft (rotary-wing aircraft) in flight manual.     (B) in order to change or extend an existing flight database and the approval of additional test data (for example, acoustic changes to certification of the engine used in the static test of acoustic data), for access to the additional data the test procedures, forms and configurations, as well as other information and procedures must be developed and approved.    36.1581 manuals, tags, and labels (A) the aircraft flight manual or rotorcraft flight manual had been approved, the airplane flight manual or rotorcraft flying Handbook approved in part, except as provided in this article 36.1583 provisions, must include the following information.     If the aircraft flight manual or rotary-wing aircraft flight manual is not approved, you must get the approval of the other manual information, marks and signs in any combination to provide these programs and information.     (1) transport aircraft and jet fighters, defined and required by the provisions of annex b corresponds to the maximum takeoff weight, maximum landing weight and morphology of overflights, lateral and approach, the noise level must be a value of the data.     (2) on small propeller aircraft, by the provisions of annex g definition and requirement corresponds to the maximum takeoff weight and morphology of takeoff, the noise level must be a value of the data.     (3) the rotorcraft, defined and required by Annex h to this provision corresponds to the maximum takeoff weight and morphology of takeoff, flying over, comes into play at a time, or by the provisions of annex j definitions and requirements correspond to the maximum takeoff weight and morphology of overflights, the noise level must be a value of the data.     (B) if additional information on using noise-level included in the approved parts of the airplane flight manual, its noise level additional information must be validated list and article 36.1581 and (a) the information requested is clearly distinguished. (C) close to the noise levels that are listed must be written on the following statement: "the aircraft noise levels in, entering or leaving any airport operation is acceptable, there is need to establish a civil aviation administration of China. "(D) for transport category aircraft and jet fighters, if they meet the provisions of takeoff or landing noise requirements of the respective weights of less than maximum weight determined in accordance with the applicable airworthiness requirements, in the usage restrictions section of the airplane flight manual must be using these smaller weight limit.     That is, the maximum takeoff weight of not more than takeoff noise requires the critical takeoff weight.     (E) for propeller small aircraft and propeller commuter class aircraft, if they for meet this provides annex f of flew over the noise requirements and used of weight is less than maximum weight and its poor value reached the noise test by needed fuel of weight Shi, or for meet this provides annex g of took off noise requirements and used of weight is less than maximum took off weight Shi, is in approved of aircraft flight manual of using limit part in the, and in approved of manual information in the, and or in approved of signs Shang, must will this a smaller of weight as using limit. (F) for primary class, and normal class, and transport class and limited with class helicopter, if for meet this provides of took off, and flew over the and landing noise requirements by used of weight below China Civil Aviation Regulations normal class spin wing aircraft airworthiness standard (CCAR-27) subsection 27.25 article (a) or China Civil Aviation Regulations transport class spin wing aircraft airworthiness standard (CCAR-29) subsection 29.25 article (a) by determine of qualified validation maximum took off weight,     Approved rotorcraft flight manual limitations section, approved manual material, or in the approved signs must be less weight as the effects are limited.     (G) subject to subsection (d), (e) and (f), other than those mentioned, this provision has no other use restrictions.     36.1583 don't have to meet noise restrictions in agriculture and fire fighting aircraft (a) this section applies to aviation operations flight, including flight or for withdrawal of spraying fire extinguishing material for small propeller planes flying.     (B) this section relates to the aircraft must be provided in accordance with article 36.1581 of the following use restrictions: noise limits: the machine is not in line with the Chinese civil aviation regulations, the aircraft type and airworthiness certification noise regulations (CCAR-36) the noise limits and must be in accordance with the Civil Aviation Administration of China run running noise restrictions in the regulations. (April 15, 2007, the first amendment) annex a in accordance with section 36.101 section A36.1 Introduction to measurement and evaluation of aircraft noise A36.2 noise certification test and measurement conditions section A36.3 section A36.4 received aircraft noise measurement based on measurement data to calculate the effective perceived noise level A36.5 to China article A36.6 of the General Administration of civil aviation to submit data, symbols and units A36     .7 atmospheric attenuation section A36.8 (backup) section A36.9 aircraft flight test results of amended section A36.1 A36.1.1 this annex on the basis of introduction section 36.101 article 36.803 and aircraft noise certification test conditions and determines the noise assessment value (expressed in effective perceived noise level EPNL) program.     A36.1.2 this Annex gives instructions and procedures in order to ensure consistency of the compliance tests, and different models of planes of trials have compared a geographically.     A36.1.3 this annex includes: complete list of symbols and units, perceived noisiness of mathematical formulas, atmospheric attenuation determination procedures, as well as from non-reference conditions to base conditions noise level correction procedures in detail.     A36.1.4 for fourth phase of aircraft, annex 16 to the Convention on international civil aviation, third edition of the first volume, issued on March 21, 2002 the 7th amendment of Appendix 2, can be used as a noise measurement and evaluation method of choice.     Section A36.2 noise certification test and measurement conditions A36.2.1 Overview A36.2.1.1 the provisions of this article to make the noise certification test conditions and the measurement procedure must be used. Note: many applications for noise certification involves only small change to the aircraft type design, can reliably determine the noise usually changes without the need for a comprehensive test of the outlined in this annex. To this end, the approval of the Civil Aviation Administration of China allowing the use of an equivalent program. In order to reduce costs and provide reliable results, equivalent may also be used in the comprehensive test validation procedures.     About subsonic jet and propeller aircraft noise certification with an equivalent program in instructional materials advisory notices see the provisions in force. A36.2.2 A36.2.2.1 to measure aircraft noise in the test environment, you must select a relatively flat terrain, and there are no dense foliage or tall grass, shrubs and trees, such as a strong sound absorbing characteristics of materials. In projection on the ground of the microphone as the vertex of the cone-shaped space, there shall be no significant effect on aircraft field of obstacles.     Range of cone-shaped space is: the axis is perpendicular to the ground, half angle of 80 °.     Note: measure personnel may itself constitute such barriers.     A36.2.2.2 test must in following atmosphere conditions Xia for: (a) no precipitation; (b) in above ground 10 meters (33 feet) at and aircraft Zhijian of whole biography sound path Shang, atmosphere temperature in-10 ℃ ~35 ℃ (14 ° F~95 ° f) Zhijian, relative humidity in 20~95% Zhijian; Note: should take measures to ensure noise measurement, and aircraft track track and the meteorological measurement of instrument in its environment qualified range within operation. (C) in above ground 10 meters (33 feet) at and aircraft Zhijian whole biography sound path Shang of relative humidity and atmosphere temperature, not makes center frequency for 8kHz of one-third times frequency drive Shang of sound attenuation is greater than 12dB/100 meters, unless: (1) dew point and dry points temperature used precision in ± 0.5 ℃ (± 0.9 ° f) within of device to measurement, and for get relative humidity     And atmospheric stratification method described in A36.2.2.3 per a one-third octave-equivalent weighted sound attenuation, or (2) after the revision to the baseline condition, PNLT peak frequency of value not more than 400Hz. (D) If according to above ground 10 meters (33 feet) at of meteorological conditions get in 3150Hz of one-third times frequency drive Shang, atmosphere of sucking sound coefficient in PNLTM sound spread path Shang of changes over ± 0.5dB/100 meters (± 1.6dB/1000 feet), that late on must by A36.2.2.3 on atmosphere for layered, calculation each one-third times frequency drive Shang of equivalent weighted sound attenuation, layered number to meet China CAAC of requirements.     If you do not need to be layered, each measurement, each one-third equivalent of the octave sound attenuation by the corresponding frequency band 10 m respectively above the ground (33 feet) and the atmosphere at the altitude of the aircraft at the time of PNLTM average sound absorption coefficient to determine. (E) 10 meters above the ground (33 ft) average wind speed is not more than 22-kilometer/hour (12), and for aircraft wind does not exceed 13-kilometer/hour (7). Average wind speed of 30 second average cycle in a 10dB reduction intervals must be determined.     At 10 metres above the ground, 10dB falling intervals of maximum wind speed is not more than 28-kilometer/hour (15), and Crosswinds do not exceed 18-kilometer/hour (10 knots).     (F) provided by the General Administration of civil aviation of China records noise at the measuring point, should not have significant effects on noise level measurement of wind or other abnormal weather conditions.     (G) must be made within 30 minutes of each noise measurement of meteorological measurements and interpolates each noise measurement of real time meteorological data obtained. A36.2.2.3 in accordance with A36.2.2.2 (c) or A36.2.2.2 (d) requirements need to be layered calculations, will have to lift the plane with 10 meters above the ground (33 feet) between the layers of the atmosphere into a number of equal height, height of each layer has a minimum value of 30 meters (100 feet). In each layer, the 3150Hz one-third atmospheric sound absorption coefficient on the octave change is not more than ± 0.5dB/100 m (± 1.6dB/1000 ft). At the time of PNLTM, the whole sound propagation path must satisfy this requirement.     Can use each layer top and air at the bottom of each layer is characterized by average sound absorption coefficient of sound absorption characteristics.     A36.2.2.4 Airport control tower or other facilities used to test on-site meteorological data, must be approved by the Civil Aviation Administration of China.     A36.2.3 track A36.2.3.1 track of aircraft height and lateral position must be approved by the Civil Aviation Administration of China, methods that do not rely on the original flight instrument determine, such as radar tracking, theodolite triangulation or imaging proportional technology.     A36.2.3.2 in PNLT maximum 10dB to ensure access to sufficient data on distance, must use synchronization signals along the track of the aircraft position and records linked to noise the noise measurement points. A36.2.3.3 must be approved automatically record sample rate adjustment data required in article A36.9 of the annex location and performance data.     Measuring instruments must be approved by the Civil Aviation Administration of China. Section A36.3 receives the measurement of aircraft noise on the ground A36.3.1 is defined as A36.3, concepts are defined as follows: A36.3.1.1 Measuring system: combination of devices used for measuring the sound pressure level, including sound calibrators, windshield, microphone system, signal recording and adjusting device, one-third-octave analysis system. Note: actual installation may include multiple microphone system, its output signal regulator consists of multi-channel recording/analysis device while recording.     For purposes of this section, each measurement is a measurement of a complete system.     A36.3.1.2 microphone system: part of the measuring system, the input sound pressure signals into electrical signals, typically including microphones, preamplifiers, extension cables and other necessary equipment.     A36.3.1.3 angle: IEC61094-3 and IEC61094-4 (revision) defined in the axis of the microphone, the sound source to the angle of the microphone diaphragm Center, in degrees.     Note: when the angle of incidence is 0 °, the sound "normal (vertical)," into the microphone; when the angle is 90 °, in order "to the incident."     A36.3.1.4 benchmark: in degrees as a unit, prescribed by the microphone manufacturers relative to the direction 0 ° incident angle of sound incidence, free field sensitivity of microphone level in that direction within the specified tolerance range.     A36.3.1.5 free-field sensitivity of microphone system: frequency sinusoidal plane wave is specified, required angle of incidence, the microphone output RMS voltage with no microphones when the ratio of the root-mean-square sound pressure at that location, based on the Volt/Pascal unit.     A36.3.1.6 free-field sensitivity of microphone system level: refers to the microphone 20 times the base 10 system free-field sensitivity with 1 volt/Pascal baseline sensitivity ratio of the value in dB units.     Note: free-field sensitivity of microphone system-level can be determined, from the audio system output voltage level (dB, reference voltage of 1V) subtracted from the input to the microphone in the sound pressure level (dB, reference sound pressure is 20 µ Pa), plus 93.98dB.     A36.3.1.7 average time band sound pressure level: on a dB basis, on a specified one-third octave, over a specified time interval, square of the instantaneous sound pressure on average 20 μ Pa reference sound pressure take the base 10 logarithm of the ratio of the square of, and then multiplied by 10.     A36.3.1.8 drive: the dB unit, measurement system in the sound pressure signal is recorded and one-third octave analysis, reference for the adjustment device corresponding to the different settings of any specific grade range of ceiling must be rounded off to the nearest decibel.     A36.3.1.9 calibration of sound pressure level: baseline environmental conditions are used to determine the entire sound of sensitivity calibration of the measurement system of coupled-cavity sound pressure level, in dB units.     A36.3.1.10 benchmark-level schedule: on a dB basis, including calibration of sound pressure level, used to determine the level of measurement system for acoustic sensitivity range.     A36.3.1.11 calibration check frequency: sinusoidal sound pressure generated by the sound calibrator signal frequency, in Hz units.     A36.3.1.12 differential: in dB units refers to any one-thirteenth-octave Center frequencies, and at a certain level on the drive measured output signal level with the corresponding input signal level difference.     A36.3.1.13 benchmark differentials: in dB units, for a specified frequency, and at a certain level range measured sound pressure level relative to the calibration of the differential input signal, can be adjusted according to the level drive properly.     A36.3.1.14 nonlinear: one-third-octave Center frequencies provided at any level on the drive differential differential of minus the appropriate benchmark for the determination of all the input and output signals are associated with the same baseline, in dB units. A36.3.1.15 scope of work: prescribed level range and frequency stability of the entire measurement system input sinusoidal signal level range, not including microphones, but includes the microphone preamplifier microphone system and other signal conditioning equipment.     In this context, level linearity in within the prescribed tolerances, in dB units.     Note: when determining scope of work regardless of the microphone cable.     A36.3.1.16 windshield insertion loss: one-third octave Center frequencies of the provision, in accordance with the provisions of the angle of incidence, microphones installed windshield displays sound pressure level difference between the before and after, in dB units.     A36.3.2 A36.3.2.1 benchmark for measuring system performance baseline environmental conditions environmental conditions are as follows: (a) atmospheric temperature of 23 ℃ (73.4 ° f), and (b) static pressure 101,325 kPa; and (c) relative humidity 50%.     A36.3.3 overview note: instruments in line with the provisions of this section to measure aircraft noise as a function of time can be obtained one-third SHG Cheng Sheng pressure level, used to calculate the effective perceived noise level referred to in section A36.4. A36.3.3.1 measurement system must by by China with Aviation General approved of and following equivalent of equipment composition: (a) wind cover (see A36.3.4); (b) microphone system (see A36.3.5); (c) records and replay system, for store measuring have of aircraft noise signal to for analysis (see A36.3.6); (d) one-third times frequency drive analysis system (see A36.3.7); and (e) calibration system,     Ensure that the system of acoustic sensitivity within the prescribed tolerances (see A36.3.8). A36.3.3.2 measurement system involving the device that converts analog signals into digital signals, the frequency is less than 12.5kHz, the conversion process may result in aliasing level at least a low ceiling 50dB linear work range of the device, its sampling rate is not less than 28kHz.     Before the signal in the digital process, must be processed by the anti-aliasing filter.     A36.3.4 windshield A36.3.4.1 in the case of no wind, in the prescribed form is installed on the windshield on the microphone, for grazing incidence of sinusoidal sound in 50Hz to 10kHz (inclusive) range one-third-octave Center frequencies caused by insertion loss shall not exceed ± 1.5dB. A36.3.5 microphone system A36.3.5.1 microphone system must comply with the provisions of A36.3.5.2 to A36.3.5.4. Civil Aviation Administration of China according to the electro-acoustic performance may approve a different microphone system.     When you use two or more sets of the same type of microphone system, confirmed that at least one system meets all specifications is sufficient proof of the conformity of the entire system.     Note: applicants must be in accordance with the requirements of A36.3.9 calibration and check each microphone system. A36.3.5.2 the microphone should be installed to center the sensor than 1.2 metres (4 feet), and tangent angle must set its direction, even sensitive components are basically located in the advance base of aircraft flight path and the plane determined by the measurement point.     The placement of the microphone holder must minimize the interference of the sound measurement, and figure A36-1 shows the angle of the microphone.     A36.3.5.3 in the reference direction, microphone and preamplifier in 50Hz to 5kHz (including) within the one-third octave Center frequencies of free-field sensitivity level in the calibration check frequency sensitivity level within ± 1.0dB, and in the center frequency of 6.3kHz, 8kHz, 10kHz, not more than ± 2.0dB. (Editor Note: here icon see manuscript) figure A36-1 microphone of sound angle schematic A36.3.5.4 for sine Sonic, in 50Hz to 10kHz range within each one-third times frequency drive of center frequency Shang, microphone system of free field sensitivity level in sound angle for 30 °, and 60 °, and 90 °, and 120 ° and 150 ° Shi, and angle for 0 ° Shi (method to incident) difference not over table A36-1 to out numerical.     Table A36-1 phase angle of incidence free field sensitivity differential shall not exceed the larger angle tolerances. A36.3.6.1 A36.3.6 to record and replay system to record and replay systems, such as digital or tape recorders, computer system, or other permanent data storage device, used to store the sound pressure signal for further analysis. Aircraft sound of all recorded in acoustic signal completely. Record and replay system used in noise certification test records speed and/or the data sample rate must meet the provisions of A36.3.6.2 to A36.3.6.9.     Must prove that the system test the selected bandwidth channel compliance and records.     A36.3.6.2 records referred to in A36.3.9 and reproducing systems must be calibrated. (A) as the frequency increased aircraft noise attenuation spectrum quickly, so I can have my measurement system appropriate preemphasis network to changing network and as compensation.     If adding a preemphasis network, the Center frequencies from 800Hz to 10kHz (included) one-third-octave range, provided by a preemphasis network gain relative to the gain in 800Hz, shall not be greater than 20dB. A36.3.6.3 is used to enter the whole measuring system (including all microphone microphone system) stability of sinusoidal signals, signal level does not exceed the equivalent base-level calibration on the process level of sound pressure level of 5dB. Displayed by the readout device, 50Hz to 10kHz one-third octave on an arbitrary center frequency the average signal level cannot exceed the calibration check the frequency range of ± 1.5dB.     Measurement systems (including a-d conversion device) in frequency response of 10kHz to 11.2kHz, must be within the frequency response of 10kHz ± 0.3dB. Note: the extended frequency response measurement does not include microphone cables.     This does not rule out A36.3.9.5 record pink noise, the microphone extension cable requirements. A36.3.6.4 for analog tape recording, the use of tape recording sound pressure level not exceeding the calibration 5dB 1kHz sine signal, the amplitude fluctuations not exceeding ± 0.5dB.     Compliance with average characteristics equivalent to a spectrum analyzer equipment certified.     A36.3.6.5 for all of the appropriate grade range and enter the measuring system (including all microphone microphone system) stability of sinusoidal signals, octave Center frequencies in one-third 50Hz, 1kHz, 10kHz and frequency of calibration checks (if the frequency is not among them), the level range bound below 50dB linear work range-level nonlinear does not exceed ± 0.5dB.     Note 1: the parts level linear measurement systems according to the test method described in IEC 61265.     Note 2: the level of linear measurement does not include microphone extension cable.     A36.3.6.6 on the drive at the baseline level, relative to the calibration of sound pressure level the sound level must be at the level below the upper bound at least 5dB, but should not be more than 30dB.    A36.3.6.7 linear work range of the adjacent level range must overlap overlap 50dB, minus level attenuation caused by adjustment of the drive controller. Note: the measurement system of the drive controller may change the attenuation of the system, such as 10dB or 1dB.     In 10dB steps level, requires a minimum amount of overlap is 40dB; level in 1dB steps, minimum overlap 49dB.     A36.3.6.8 overload indicator must be included in the record and replay system, and can occur on any level range give you overload an overload indication.     A36.3.6.9 measuring system allows changes in FADER manipulate DB step size must be known.     A36.3.7 analysis systems shall comply with A36.3.7.2 through A36.3.7.7 for A36.3.7.1 analysis system for the analysis of the frequency bandwidth, gain and channel configuration setting requirements. A36.3.7.2 analysis system of output must by as time function of one-third times frequency Cheng Sheng pressure level composition, these sound pressure level is through has following characteristics of analysis system on noise signal (prior records of) for processing get of: (a) a 24 a one-third times frequency drive filter device or equivalent device, center frequency from 50Hz to 10kHz (containing); (b) system of response and average characteristics, in principle told, is on any a one-third times frequency drive filter of output for square, and Average and as time average sound pressure level displayed or storage; (c) for spectrum analysis of continuous sound pressure level sampling interval must for 500 ± 5 milliseconds, regardless of have as A36.3.7.4 in the defined of "slow" time weighted; (d) in read out data or Analyzer heavy reset during, analysis system not processing sound pressure signal and lost data of continued time not over 5ms; and (e) analysis system from 50Hz to at least 12kHz (containing) must for real-time operation.     This requirement for all channels of the multi-channel system.     From 50Hz to 10kHz A36.3.7.3 in the center frequency (including) within the one-third octave analysis system of minimum standards is the revision of IEC 61260 class 2 electrical performance requirements.     Note: one-third octave analysis is specified in IEC 61260 system testing procedures, including the relative attenuation, anti-aliasing filter, real-time operations, ramp and score in the effective bandwidth of the filter response. A36.3.7.4 with one-third octave Analyzer in "slow" time average, its various Center frequencies to suddenly start or interruption of sinusoidal signal amplitude response must be started after 0.5 seconds, 1.5 seconds, 1 second, 2 seconds and suddenly interrupted after 0.5 seconds and 1 second for instantaneous sampling. Rose response relative Yu stable state of numerical must is: 0.5 seconds-4 ± 1dB 1 seconds-1.75 ± 0.75dB 1.5 seconds-1 ± 0.5dB 2 seconds-0.5 ± 0.5dB in 0.5 seconds and 1 seconds of declined response relative Yu initial stable state of output signal level and corresponding of rose response readings of and must is equal to-6.5 ± 1dB, zhihou of rose and declined response of and should for -7.5dB or more low.     This is equivalent to a nominal 1 second time constant (that is, an average time of 2 seconds) average. A36.3.7.5 one-third Cheng Sheng pressure level by not using "slow" time weighted Analyzer output OK, must be processed after simulating the "slow" time-weighted. Simulation of "slow" time weighted sound pressure level can through following of equation with continuous index average process get: (Editor Note: here formula see manuscript) which, Ls (i,k) for simulation of "slow" time weighted sound pressure level, l (i,k) for by measuring of 0.5 seconds time average sound pressure level, by Analyzer output of subsection k period and subsection I a one-third times frequency drive determine. When k=1, formulas to the right of "slow" time weighted sound pressure Ls (I, (k-1=0)) set to 0dB.     Continuous index average process available following by four a sampling average process export of equation (k ≥ 4) approximate expression: (Editor Note: here formula see manuscript) which, Ls (i,k) for simulation of "slow" time weighted sound pressure level, l (i,k) for by measuring of 0.5 seconds time average sound pressure level, by Analyzer output of subsection k period and subsection I a one-third times frequency drive determine. Sum of the weighting factors are 1.0 in the above two equations.     Through either equation to calculate sound pressure level, starting from the 6th 0.5 seconds of sample data, or 2.5 seconds after the start of effective data analysis. Note: the coefficients of the two equations in the limited time of 0.5 seconds on average to determine the equivalent sound pressure level "slow" weighted sound pressure levels.     When the average of a data sample time is 0.5 seconds, the two equations cannot be used.     A36.3.7.6 characterization of "slow" time-weighted instantaneous sound pressure level features time must be earlier than the actual reading time 0.75 seconds. Note: the defined requirements for instantaneous time records noise connected with noise aircraft position on the issue, and to consider "slow" time-weighted average period.     For every 0.5 second data record can be considered as transient time of 2 seconds on average, 1.25 seconds after the cycle starts.     A36.3.7.7 sound pressure level resolution, whether displayed or stored, it must be 0.1dB or later. Acoustic sensitivity of A36.3.8 system A36.3.8.1 system must use sound calibrator of known frequencies produce a known sound pressure levels to be sure.     Sound calibrator is the minimum standard requirements of revised IEC 60942 class 1L. A36.3.9 system calibration and check the A36.3.9.1 of China's general administration of civil aviation requirements, measurement system and equipment calibration and inspection must be carried out in accordance with the provisions of A36.3.9.2 to A36.3.9.10 method. One-third Cheng Sheng of the Analyzer output pressure level the calibration adjustment, including environmental effects on the output level of the sound calibrator, must be submitted to the General Administration of civil aviation of China. Overload displays collected data is not valid, and shall not be used. If overload occurs during recording, the related test data that is not valid.     If an overload occurs during analysis, you should reduce the sensitivity to remove overload, re-analysis. A36.3.9.2 free-field frequency response of microphone system electronic static Exciter, combined with the data provided by the manufacturer, or by muffling devices within the free-field test to be sure. Frequency response correction must be determined within 90 days of each series.     One-third Cheng Sheng of the Analyzer output pressure levels the audio system of the non-uniform frequency response correction must be reported to the Civil Aviation Administration of China. Issued by A36.3.9.3 of aircraft noise in the microphone within a range of ± 30 ° tangent incident incident (see figure A36-1), the tangent angle of incidence free field correction can only consider the impact of its direction.     In other cases, noise sampling every 0.5 seconds must be to determine the angle and direction of amendment. A36.3.9.4 for analog tape recorders, each tape in the beginning and at the end of at least 30 seconds of pseudo random noise or pink noise.     Only when the tape opening and records at the end of the signal in the 10kHz one-third octave on the difference of not more than 0.75dB, the data from the tape recording of an analog signal is considered reliable. A36.3.9.5 the whole measuring system used in test series (not including microphones) frequency response must be determined using pseudo random noise or pink noise, the noise levels are on the class path used does not exceed the test center frequency from 50Hz to 10kHz (inclusive) the calibration for each one-third octave sound pressure level of 5dB. Noise generator output must be within 6 months before the start of each test series, calibrate the bodies authorised by the Civil Aviation Administration of China. And each of the output on the one-third octave changes relative to the previous calibration values greater than 0.2dB are not allowed.     One-third Cheng Sheng of the Analyzer output pressure level frequency response correction done, must be submitted to the Civil Aviation Administration of China.     A36.3.9.6 is used for noise certification measurements and calibration of equipment, its switched-gain performance of the regulator must be checked every 6 months test series, to ensure that the maximum error is less than 0.1dB. A36.3.9.7 sound calibrators of coupled-cavity sound pressure levels must be based on the test environment, use the manufacturer's calculations on the impact of atmospheric pressure and temperature information. Measurement of the sound pressure level will be used to establish systems for acoustic sensitivity.     Output sound calibrators must be within 6 months before the start of each test series, calibrate the bodies authorised by the Civil Aviation Administration of China, and in contrast to the calibration value of less than 0.2dB. A36.3.9.8 in each test day, sound pressure levels must be fully calibrated to ensure that major environmental conditions in each test series, acoustic sensitivity of the measuring system is known. Every day immediately before and after each test series record of acoustic sensitivity difference of not more than 0.5dB. Output level of calibration, once a atmospheric pressure correction, use 0.5dB restrictions. The arithmetic mean of the measurements before and after the test as a measurement system of the sound sensitivity level.     One-third Cheng Sheng of the Analyzer output press the calibration correction must be submitted to the General Administration of civil aviation of China.     A36.3.9.9 each recording medium, such as magnetic tape reels, cassettes, disks in its beginning and records at least 10 seconds at the end of the calibration signal sound pressure level. A36.3.9.10 center frequency from 50Hz to 10kHz (inclusive) on each octave one-third, windshield insertion loss must have the appropriate angle of incidence free field of sinusoidal sound signal. According to the amendment to section A36.3.9.3 direction, the direction and the grazing incidence angle must not exceed 30 °. Without defacing the windshield, the insertion loss according to the data provided by the manufacturer. In addition, the insertion loss of the windshield must be within 6 months before the start of each test series, calibrate the bodies authorised by the Civil Aviation Administration of China, and in each Octave in relation one-third last calibration value of less than 0.4dB.     One-third Cheng Sheng of the Analyzer output pressure level the windshield free of insertion loss of correction must be submitted to the Civil Aviation Administration of China. A36.3.10 environmental noise A36.3.10.1 noise, including the acoustic background noise to the measurement system of electric noise, you must record for at least 10 seconds at the measuring point, gain should be set in the system when measuring aircraft noise levels. Environmental noise must be representative of the background noise when flying over the test.     When the PNL expressed and analyzed in the same way (see A36.4.1.3 (a)), only ambient noise at least 20dB lower than maximum PNL values of aircraft, the records of aircraft noise is acceptable. A36.3.10.2 10dB reduction (see A36.4.5.1) the sound pressure levels of aircraft in each one-third on the octave, must be established in accordance with section A36.3.10.1 of the average ambient noise level at least 3dB, or adjust the method must be approved by the Civil Aviation Administration of China.     The provisions in force in the Advisory Circular method is presented. Section A36.4 based on measurement data to calculate the effective perceived noise level A36.4.1 Overview A36.4.1.1 the basic elements of noise certification standards is called the effective perceived noise level (EPNL), measured in EPNdB noise assessment criteria. EPNL is a numerical evaluation of the impact of aircraft noise on human subjective, by irregular spectrum of fixed duration and amendments of instantaneous noise level composed of PNL.     Irregularity correction of spectrum, also known as the "pure-tone correction factors", is the only amendments made to the largest pure tones within each time increment. A36.4.1.2 the three basic physical characteristics are required to measure the sound pressure: SPL, frequency distribution and time variation.     To determine the EPNL, requires that aircraft noise measurement every 0.5 seconds during time period, calculated 24 one-third octave on the instantaneous sound pressure level.     A36.4.1.3 noise subjective response of EPNL assessment standard is based on the measuring the physical properties of the noise received, the calculation process consists of the following 5 steps: (a) A36.4.2.1 (a) 24 one-third in octave into perceived noisiness Cheng Sheng pressure level (NA), and then adds the value of perceived noise level get an instant PNL (k).     (B) to take into account people's subjective response to spectra irregularities, for pure tones each spectrum to calculate the correction factor c (k).     (C) every 0.5 seconds on the time period, pure tone correction factor added to the perceived noise level, get the tone correction noise PNLT (k): calculates all the tone correction value of instantaneous noise level, and to determine the maximum value of PNLTM.     (D) duration of correction factor d is based on the pure tone correction noise level with the time calculated from the curve through points. (E) effective feel noise level EPNL by maximum tone amendment feel noise level and continued time amendment factor of algebra and by determine: A36.4.2 feel noise level A36.4.2.1 instantaneous feel noise level PNL (k), must by the one-third times frequency drive of instantaneous sound pressure level SPL (i,k) is out, its steps following: (a) first step: using A36.4.7 in the of NA table of mathematics formula, will 50Hz to 10kHz range within of the one-third times frequency drive of SPL (     I,k) converted into perceived noisiness n (j,k).     (B) step two: using the following formula, first obtain the perceived noisiness values n (i,k) added to: (Editor's Note: this formula see manuscript), n (k) is 24 n (i,k), the maximum values for the value n (k) for the total perceived noisiness.     (C) step three: using the following formula, will feel noise n (k) converted into perceived noise level PNL (k): (Editor's Note: this formula see manuscript) Note: the PNL (k) curves given in the Advisory Circular on the provisions currently in force.     A36.4.3 spectrum not rules sex amendment A36.4.3.1 spectrum in the has obviously not rules sex of noise (for example, maximum discrete frequency components or tone), must with by following steps calculation out of amendment factor c (k) for amendment: (a) first step: in according to A36.3.9 for amendment Hou, from 80Hz one-third times frequency drive (third frequency drive) began, by following method calculation sound pressure level of changes (or "slope"):     (B) the second step: circle the slope change in the slope of the absolute value is greater than 5 s (i,k), that is: (c) step three: (1) if the slope of a circle s (i,k) value is positive, the value is greater than the slope and algebra s (i-1,k), the sound pressure level SPL (i,k).     (2) if the slope of a circle s (i,k) number is zero or negative, and the slope s (i-1,k) is positive, the sound pressure level SPL (i-1,k).     (3) for all other cases, not sound pressure level.     (D) the fourth step: follow calculated new, adjusted the sound pressure level SPL' (i,k):  : (1) not ring out sound pressure levels, the new sound pressure level sound pressure level equal to the original, namely: SPL' (i,k) =SPL (i,k). (2) for 1 to 23 frequency Zhong Cheng (containing) was circle out of sound pressure level, makes new sound pressure level is equal to Qian, and Hou sound pressure level of arithmetic average value, that: (Editor Note: here formula see manuscript) (3) if most high frequency drive (i=24) of sound pressure level was circle out, is makes the frequency drive of new sound pressure is equal to: (e) fifth step: including a assumed of 25th frequency drive zainei, by following method again calculation new slope s' (i,k): (f) sixth step on serial number I from 3 to 23 of frequency drive,     By following formula calculation three a adjacent slope of arithmetic average: (Editor Note: here formula see manuscript) (g) seventh step from 3rd frequency drive up to 24 frequency drive check, by following formula calculation one-third times frequency Cheng Sheng pressure level of last knot SP ″ (i,k): (Editor Note: here formula see manuscript) (h) eighth step: by following formula calculation soundtrack pressure level and eventually this end of sound pressure level of poor f (i,k): and only note is equal to or is greater than 1.5 of value.     (I) the Nineth step: according to the sound pressure level difference f (i,k) and A36-2, each one-third octave (3-24) pure-tone correction factor. (J) the tenth step: specify the Nineth step determines the maximum values for tone correction factor c (k). (Pure tone correction program examples in this advisory notices are given of the provisions currently in force. ) Tone amendment feel noise level by c (k) and corresponding of PNL (k) added to determine, that: if suspected subsection k period any subsection I a one-third times frequency drive of tone amendment factor have since Yu non-actual tone (or additional Yu actual tone) of a species factors, or is have since Yu not belongs to aircraft noise of any spectrum not rules sex Shi, can through bandwidth than this one-third times frequency drive bandwidth more narrow of filter do further analysis. If these are confirmed, you can determine this based on narrow-band analysis of sound pressure level at the end of SPL' (i,k) the revised value used to calculate the corresponding one-third octave tone correction of the correction factor.    Other methods of removing false tone correction must be approved. (Editor's Note: this chart see manuscripts) table A36-2 tone correction factor A36.4.3.2 for pure tones of a remarkable, if it corresponds to the frequency was recorded in two adjacent one-third octave, this pure-tone correction program will underestimate the EPNL values.     The applicant must prove that: (a) there was no pure tones in the two adjacent one-third is recorded in the octave, or (b) if significant tone in two adjacent one-third octave is recorded, you can fix them to the full record in a single one-third values in octave. A36.4.4 tone correction, noise level A36.4.4.1 tone correcting perceived noise level PNLTM is A36.4.3 program calculates tone correction of perceived noise level PNLT (k) the maximum value.     In order to obtain satisfactory noise time history must be measured at 0.5 second intervals.     Note 1: A36.2 is an example of a time history of flying over the noise, figure had been clearly identified in the maximum value.     Note 2: If there is no tone correction factors, PNLTM equals PNLM. A36.4.4.2 won the PNLTM value must also be in two-stage sampling of 500 milliseconds before and after data finding maximum tone correction factors corresponding to the frequency bands in order to identify because of the pure tones appear in different one-third on the octave and pure-tone effect that may occur at the PNLTM.     If the tone correction factor c PNLTM (k) value is less than the above 5 adjacent time interval c (k), on average, you must use the c (k) to recalculate the average PNLTM value. (Editor Note: here icon see manuscript) figure A36-2 tone amendment feel noise level as aircraft flew over the time of function of example A36.4.5 continued time amendment A36.4.5.1 continued time amendment factor d is with points method determine of, equation following: (Editor Note: here formula see manuscript) type in the t is return a of of time constants, PNLTM is PNLT of maximum value, t (1) is PNLT is greater than PNLTM-10 of time beginning, in time t (2) zhihou,     PNLT kept is always less than the PNLTM-10. A36.4.5.2 PNLT is calculated from the measured values from the SPL, in General, its function does not have a clear formula as a time.     Therefore, you can use summation notation instead of the integral symbol, the equation into: (Editor's Note: this formula see manuscript), type t is for the purpose of calculating PNLT (k) used by time increment, and d is accurate to 0.5 seconds interval, PNLT during that time interval (k) greater than or equal to PNLTM-10.     A36.4.5.3 in order to get a feeling of satisfaction, noise level time history must be used: (a) time interval t for 0.5 seconds or (b) use a shorter time, together with the approved limits and constants.     A36.4.5.4 in the A36.4.5.2 formula is used to calculate d, t and t must use the following values: T=10 seconds and t=0.5 seconds (or approved sampling interval).     Using the above values, d formula: (Editor's Note: this formula see original) type d is defined by the points corresponds to the value of PNLTM-10 the duration. A36.4.5.5 used in A36.4.5.2 procedures, if PNLTM-10 limit value fall PNLT (k) between the calculated value (usually), you must select PNLT PNLTM-10 (k) value as the duration interval boundaries.     Appear PNLT (k) of more than one peak, you must select the appropriate threshold values, the duration to achieve the greatest possible value. A36.4.6 effective perceived noise level the General subjective effects of aircraft noise on people, based on the effective perceived noise level (EPNL).     EPNL tone correction of perceived noise level Max PNLTM correction d algebra and the duration, namely: (Editor's Note: this formula see manuscript) PNLTM and d are calculated according to the procedures contained in A36.4.2,A36.4.3,A36.4.4 and A36.4.5.     A36.4.7 mathematical formula tables A36.4.7.1 sound pressure level (SPL) and the perceived noisiness of the relationship between the values as shown in Figure A36-3 and table A36-3.     A36.4.7.2 mathematics formula of based is: (a) line of slope (m (b), m (c), m (d) and m (e)); (b) line in SPL axis Shang of cut from (SPL (b) and SPL (c)); and (c) continuous points of coordinates: SPL (a) and LOGN (a), SPL (d) and logn=-1.0,SPL (e) and LOGN=log (0.3).   A36.4.7.3 calculates the value using the following formula: (Editor's Note: this formula see manuscript) A36.4.7.4 table A36-3 lists are calculated as a function of sound pressure level of perceived noisiness required constant values. (Editor Note: here icon see manuscript) figure A36-3 as sound pressure level function of feel noise table A36-3 na value mathematics calculation formula in the of constants (Editor Note: here formula see manuscript) subsection A36.5 article to China Civil Aviation General submitted data A36.5.1 Overview A36.5.1.1 representative with physical measurement of data and on physical measurement for amendment by using of data, must by by approved of form permanent to records down, and attached in test records zhihou.     A36.5.1.2 all of the amendments must be submitted to the Civil Aviation Administration of China, and approved by the Civil Aviation Administration of China, including device response deviation amendments made to your measurements.     A36.5.1.3 the applicant must be submitted as required in the acquired data in each step of the operation on the inherent errors of estimation. A36.5.2 data submissions applicants must submit a noise certification of compliance reports, should include the following: A36.5.2.1 the applicant must provide the sound pressure levels measured and corrected, use one-third times said Cheng Sheng pressure level.     Measuring equipment must meet the standards referred to in article A36.3 of this annex.     A36.5.2.2 the applicant must submit for the measurement and analysis of acoustic performance and meteorological data of the manufacturer and model of the device.     A36.5.2.3 the applicant must be submitted for each test in the process of or immediately before and after the test, provided for in article A36.2 of this annex of the observation point measurements of atmospheric environment of the following data: (a) the air temperature and relative humidity and (b) the maximum, minimum and average wind speed; (c) atmospheric pressure.     A36.5.2.4 the applicant must be submitted to the local topography, landform, and may interfere with the recording of the event.     A36.5.2.5 applicants must submitted following information: (a) aircraft and engine of type, and model and serial number (as has); (b) aircraft of outside profile size and engine of location; (c) each test Shi aircraft of total weight and each test series of gravity range; (d) each test aircraft of configuration, as flap wing, and deceleration Board and landing gear location; (e) If installation auxiliary power plant (APU), its in each test in the whether work;     (F) each flight test in the engine introduction gas and engine power extraction of State; (g) each flight test of indicates empty speed, km/hours (section); (h) engine performance data: (1) on Jet: each flight test from aircraft instrument and manufacturers provides of data get of engine performance parameter, including static thrust, and engine pressure than, and exhaust temperature and fan or pressure gas machine speed; (2) on propeller aircraft: each flight test from aircraft instrument and manufacturers provides of data get of engine performance parameter, including brake horsepower, and remaining thrust (or equivalent axis horsepower, or engine torque) and propeller speed; (I) each flight test aircraft of track and to speed; (j) applicants must report aircraft whether for had modified or with may effect aircraft noise characteristics of non-standard equipment.     Any such alterations and non-standard equipment must be approved by the Civil Aviation Administration of China. A36.5.3 noise certification benchmark conditions A36.5.3.1 the aircraft must be submitted and performance data and noise measurement result in amendments to annex b to the regulations of the noise certification requirements baseline condition.     Applicants are required to submit these criteria, including benchmarks and configuration. A36.5.4 results of A36.5.4.1 must be drawn from the results of three average EPNL values and their 90% confidence interval and submit. Each of these values is in the appropriate measuring station (across, entry or lateral) on all valid test of acoustic measurement values to be amended, the arithmetic mean of the results obtained. If in any of the stations several sets of acoustic measurement system is used, then the data must be obtained for each test average as a single measured value.     You must make the following calculation: (a) for each flight phase, calculating the arithmetic mean of the measured values of each microphone; (b) used in this paragraph (a) calculated the value of each of the baseline conditions (over, cross or enter) all of the arithmetic mean, confidence is 90%. A36.5.4.2 noise certification, minimum number of samples of each measurement point is six. Sample size must be large enough so that each of three noise certification an average noise level, 90% established by the statistical confidence intervals of not more than ± 1.5EPNdB.     Unless otherwise provided by the General Administration of civil aviation of China, any results are not omitted in the average.     Note: the method of calculating the confidence interval allowed by the 90% given in the Advisory Circular on the provisions currently in force.     A36.5.4.3 average EPNL values in accordance with A36.5.4.1 of the program evaluated, must be able to control the noise certification standards to assess the noise performance of the aircraft.     Section A36.6, symbols and units section A36.7 atmospheric attenuation atmospheric attenuation A36.7.1 must follow the procedures set out in the A36.7.2 to determine.     A36.7.2 atmosphere of sound attenuation and frequency, and temperature and humidity Zhijian of relationship with following equation said: A36.7.2 (a) using inch units of formula: (Editor Note: here formula see manuscript) which η (δ) column Yu table A36-4 in the, F0 column Yu table A36-5 in the; a, (I) is attenuation coefficient, units for dB/1000 feet; θ is temperature, units for China's degrees; h is relative humidity, to percentage said.     A36.7.2 (b) using the metric formula: (Editor's Note: this formula see manuscript), η (δ) shown in table A36-4, F0 are listed in table A36-5; a (I) is the attenuation coefficient, unit dB/100 m; θ is the temperature, in degrees Celsius; h is the relative humidity, expressed as a percentage. A36.7.3 table A36-4 lists in accordance with the formula to be used when the value in the A36.7.2.     Use quadratic interpolation if necessary.     Section A36.8 (standby) the amendment to section A36.9 aircraft flight test results of A36.9.1 when the noise certification test conditions and when benchmark conditions to, must use the methods in this section to make appropriate adjustments to measured noise data.     A36.9.1.1 for following of differences, must with A36.9.3 and A36.9.4 by said of method one of on measured of noise value for adjustment: (a) by square is inversely proportional to law and the atmosphere attenuation of effect, along spread path Shang of noise attenuation of differences; (b) by aircraft relative Yu measurement points of distance and speed of effect, noise continued time of differences; (c) by engine work of test conditions and benchmark conditions different effect, engine issued of source noise of differences; (D) testing of different effect than the reference airspeed the airspeed, aircraft/engine source noise differences. In addition to space velocity on the duration of impact, space velocity on the impact of active noise must also be considered.     For a conventional aircraft, and when the pilot when airspeed and benchmark margin of airspeed above 28-kilometer/hour (15), must be used by the General Administration of civil aviation of China approved the test data and/or analysis to quantify the impact of speed adjustment to noise level assessments.     A36.9.1.2 in following conditions Xia, must with A36.9.4 in the by said of "full" adjustment method on took off and entry test of results for amendment: (a) using "simplified" method Shi, adjustment volume in flew over the Shi is greater than 8dB, or in entry Shi is greater than 4dB, or (b) using "simplified" method get of flew over the or entry noise of eventually EPNL value, and this provides subsection B36.5 article by said of noise limit value difference not to 1dB.     A36.9.2 flight profile described below, test and flight profile of the base under two conditions, consists of geometric position relative to the ground, along with the aircraft relative to the ground speed, and engine control parameters to determine the aircraft noise to describe.     A36.9.2.1 takeoff profile Note: figure A36-4 represents a typical takeoff profile. (A) aircraft began takeoff point a, point b, in point c at a constant angle of climb for the first time. If you use the down thrust or power, in point d and point e stop.     This second constant-angle of the plane began to climb, until the end of the noise certification take off track f. (B) K1 for takeoff noise measurement station AK1 was taxiing distance from start point to overflight noise measurement points.     K2 is a lateral noise measuring stations, it is located parallel to the runway centre line and provides distance apart on one of the lines, in the process of taking off the noise level at maximum.     (C) AF is according to the requirements of Appendix A36.2.3.2, locations and on aircraft noise measurements at a distance.     A36.9.2.2 enter the profile Note: figure A36-5 represents a typical entry section.     (A) aircraft noise certification the g-spot begins to enter the track and j-grounded, and runway distance for OJ.     (B) K3 is approaching noise measuring stations, K3O is approaching noise measuring point distance from the runway.     (C) GI according to the requirements of Appendix A36.2.3.2, locations and on aircraft noise measurements at a distance. Approach the plane datum point of the measuring instrument landing system (ILS) antenna.     If you did not install ILS antenna, irreplaceable reference point must be approved by the Civil Aviation Administration of China.     (Editor's Note: the icons here see original) figure A36-4 typical takeoff profile (Editor's Note: the icons here see manuscript) A36-5 enter the profile of the typical adjustment A36.9.3 A36.9.3.1 Overview of the simplified method described below, simplified adjustment method, included in the PNLTM moment, due to test conditions and differences between the baseline condition on calculated from measurement data of EPNL adjustments. A36.9.3.2 on PNL and PNLT adjustments (a) figure A36-6 part track test track and benchmark, including entry of appropriate for calculating overflight and EPNL noise of time.     In Figure A36-6: (1) representative of the XY part track test (including appropriate for calculating overflight and enter the time course of EPNL), track and XrYr represent the corresponding part of the benchmark. (2) Q on behalf of noise for noise measurement k measured at PNLTM, aircraft position on the test track, Qr is the corresponding location on the track in the base, Kr is benchmarks measuring points.     QK and QrKr is measured separately and the baseline noise transmission, Qr is assuming the QK and QrKr with their flight path into the same angle θ and determined.    (Editor's Note: the icons here see manuscript) A36-6 profile characteristic of impact sound pressure level (B) figure A36-7 (a) and (b) (b) (1) and (2) the track test and track the benchmark, including the corresponding noise for calculating lateral EPNL time history.     (1) figure A36-7 (a), the track XY represents part of the test (including the corresponding is used to calculate the time course of lateral EPNL); A36-7 (b), track XrYr on behalf of the corresponding part of the benchmark. (2) Q on behalf of noise for noise measurement k measured at PNLTM, aircraft position on the track in testing. Qr is the corresponding location on the track in the baseline. Kr is benchmarks measuring points. QK and QrKr is measured separately and the baseline noise transmission.     Kr on the cross under the siding, Kr and identification of Qr is assuming the QK and QrKr: (I) with the respective flight path into the same angle θ; and (ii) ψ angles with the same ground.     Note: in the case of lateral noise measurements, sound propagation is affected not only by the inverse square law and the effect of atmospheric attenuation, and rely mainly on ψ angles of surface absorption and reflection effects. A36.9.3.2.1 constitute PNL (in PNLTM Shi k points measurement to of PNL) of one-third times frequency Cheng Sheng pressure level SPL (I) must adjustment to benchmark level SPL (I) r following: A36.9.3.2.1 (a) using inch units of formula following: this expression type in the, (1) 0.001 (a, (I)-a (I) 0) QK is consider sound attenuation coefficient changes effect made of adjustment, a, (I) and a, (I)     0 respectively is according to this provides subsection A36.7 article determine of test and benchmark atmosphere conditions Xia of attenuation coefficient; (2) 0.001A (I) 0 (QK-QrKr) is consider biography sound path length changes on sound attenuation effect by do of adjustment; (3) 20log (QK/QrKr) is according to square is inversely proportional to law, on biography sound path length changes effect of adjustment; (4) QK and QrKr to feet for units, a, (I) and a, (I) 0 to dB/1000 feet for units.     A36.9.3.2.1 (b) using metric units formula following: this expression type in the, (1) 0.01 (a, (I)-a (I) 0) QK is consider sound attenuation coefficient changes effect made of adjustment, a, (I) and a, (I) 0 respectively is according to this provides subsection A36.7 article determine of test and benchmark atmosphere conditions Xia of attenuation coefficient; (2) 0.01a (I) 0 (QK-QrKr) is consider biography sound path length changes on sound attenuation effect by do of adjustment;     (3) 20log (QK/QrKr) is based on the inverse square law, the adjustment of the transmission path length changes (4) QK and QrKr m units, a (I) and (I) 0 to dB/100 metres.     A36.9.3.2.1.1 PNLT amendments (a) modified SPL (I) r values are converted to PNLTr and (b) use the following formula to calculate the correction 1:A36.9.3.2.1.2 1 Summary of algebra and added to the measured data on the EPNL. (Editor's Note: the icons here see manuscript) A36-7 lateral measurement-A36.9.3.2.2 of the base station during a test flight, PNLTM are several PNLT within 2dB of peaks, each peak must be processed according to the procedure described in A36.9.3.2.1, the amendments will be added to the corresponding peak on, to produce the corresponding adjusted PNLT peak.     If these peaks exceed the PNLTM value exceeds the maximum amount as further adjustments to be added to the measured data on the EPNL. A36.9.3.3 adjust the duration fixed A36.9.3.3.1 when measured under the conditions of the flight path and/or ground speed under the condition of different base base flight path and/or when the ground speed, EPNL values calculated from measured data must be continuous time to adjust.     Such adjustments must be calculated according to the methods described below.     A36.9.3.3.2 on the track as shown in Figure A36-6, adjust the calculated according to the following formula: 2 algebra and added to the measured data on the EPNL. A36.9.3.4.1 A36.9.3.4 source noise for noise certification flight test engine noise measurements of all parameters with those calculated under baseline conditions or differences between the parameter set, you must compute the adjustment and application of active noise. Adjust the amount approved by the Civil Aviation Administration of China, the manufacturer provides data to determine. For this adjustment of the characteristic data given in Figure A36-8, is an engine control parameters μ and EPNL curves. EPNL data have been modified to all other relevant baseline conditions (aircraft weight, speed, altitude, and temperature), and to the engine with an average engine (definition in B36.7 (b) (7) a modification of noise differences between.     Requires that µ r range there are enough data points to calculate the horizontal side, flying over and approaching noise source noise correction.     (Editor's Note: the icons here see manuscript) A36-8 noise thrust correction A36.9.3.4.2 corresponds to the parameter μ EPNL values of r minus EPNL values corresponding to the parameter μ calculated item 3, and algebra, and added to the measured data on the EPNL. A36.9.3.5 symmetric sex adjustment A36.9.3.5.1 on cross side noise value (in B36.4 (b) provides of measurement points determination) of symmetric sex adjustment, by following steps for: (a) if symmetric measurement points is main cross side noise measurement line Shang get of maximum noise level of points of symmetric points, is validation noise level must is in this two points Shang measuring have of noise level of arithmetic average value (see figure A36-9 (a)); (b) if not meet (a) of conditions, It is assumed that the noise changes with the height of an aircraft is the same on both sides, that is to say on both sides of the relationship between noise and height difference between the curve is constant (see figure A36-9 (b)).     Approved maximum noise level is the average of the two curves. (Editor's Note: the icons here see manuscript) A36-9 symmetry correction A36.9.4 full A36.9.4.1 Overview of the adjustment as described in this section, complete the adjustment method including calculation and test of the measuring point corresponds to the reference measuring point in the baseline condition of PNLT time history, and with the new time history directly EPNL.     Key principles see A36.9.4.2 to A36.9.4.4.1. A36.9.4.2 PNLT calculation (a) shown in Figure A36-10 (a) (1) and (2) the track test and track the benchmark, including entry of appropriate for calculating overflight and EPNL noise of time.     In Figure A36-10: (1) XY represents part of the observed flight path, including appropriate for calculating overflight and enter the time course of EPNL, track and XrYr represent the corresponding part of the benchmark. (2) Q0,Q1,Qn on behalf of T0,T1 and TN time measured on the flight path of an aircraft. Point Q1 is the T1 time observed in noise measurement point k one-third SHG Cheng Sheng pressure level SPL (I) 1 point of noise emission. Accordingly, Qr1 TR1 time measurement point in the benchmark benchmark Kr observed track work pressure level SPL (I) noise emission points R1. Q1K and Qr1Kr respectively, and benchmarks for measuring sound transmission paths, with their respective flight path into Theta 1. Similarly, Qr0 and Qrn is correspond to the observed flight path on Q0 and Qn datum points on the track.     Q0 and Qn option so that all Qr0 and Qrn, peak at 10dB between PNLTr value (calculated according to A36.9.4.2.2 and A36.9.4.2.3) are included.     (Editor's Note: the icons here see manuscript) A36-10 complete track adjustment method of test and reference (b) figure A36-11 (a) and (b) (b) (1) and (2) the track test and track the benchmark, including the corresponding noise for calculating lateral EPNL time history.     (1) figure A36-11 (a), XY represents part of the observed flight path, including the corresponding course of time used to calculate lateral EPNL; A36-11 (b), track XrYr on behalf of the corresponding part of the benchmark. (2) Q0,Q1,Qn on behalf of T0,T1 and TN time measured on the flight path of an aircraft. Point Q1 is the T1 time observed in noise measurement point k one-third SHG Cheng Sheng pressure level SPL (I) 1 point of noise emission. Accordingly, Qr1 TR1 time measurement point in the benchmark benchmark Kr observed track work pressure level SPL (I) noise emission points R1. Q1K and Qr1Kr respectively, and benchmarks for measuring sound transmission paths. Similarly, Qr0 and Qrn is correspond to the observed flight path on Q0 and Qn datum points on the track. Q0 and Qn option so that all Qr0 and Qrn, peak at 10dB between PNLTr value (calculated according to A36.9.4.2.2 and A36.9.4.2.3) were included on a particular horizontal siding and Kr.     Therefore, determines where the Kr and Qr1 according to the following: (I) Q1K and Qr1Kr, respectively, and their respective flight path into Theta 1. (Ii) with the approval of the Civil Aviation Administration of China, the angle ψ 1 and ψ difference between R1 min.     For geometric reasons, generally cannot be selected to Kr, ψ 1 and ψ while maintaining equal R1 to meet A36.9.4.2 (b) (2) (I) the criteria in.     Note: for lateral noise measurement, is affected not only by the inverse square law of sound propagation and atmospheric attenuation of the impact and influence of absorption and reflection by the ground effect ground absorption and reflection effects associated with ψ angles. (Editor Note: here icon see manuscript) figure A36-11 (a) measured flight track (Editor Note: here icon see manuscript) figure A36-11 (b) benchmark flight track A36.9.4.2.1 in A36.9.4.2 (a) (2) and (b) (2) in the of moments TR1 than T1 late (because Qr1Kr>Q1K), respectively difference: (1) aircraft to speed Vr flew distance Qr1Qr0 by needed of time minus to speed v flew distance Q1Q0 by needed of time     (2) the time required for sound propagation through the Qr1Kr-Q1K distance. Note: for A36.9.4.2 (a) (2) (b) (2) described in the flight path, reduced thrust or power use to form a thrust or power and thrust or power reduction in track tests and benchmarks.     When between them when the transition has an impact on the end result, you must use the approved method of interpolation to calculate, for example, the provisions in force in the Advisory Circular method. A36.9.4.2.2 in order to explain testing conditions and transmission path lengths under baseline conditions and differences in atmospheric conditions, the measured SPL (I) value of 1 must adjust to baseline values with the A36.9.3.2.1 method this appendix SPL (I) R1. The corresponding PNLr1 values must be calculated according to the A36.4.2.     PNLr values must be calculated at the time interval t0 to TN. A36.9.4.2.3 for each of the PNLr1 values, you must use the methods described in Appendix A36.4.3 analysis of SPL (I) r values to determine the tone correction factors C1 and added to PNLr1 get PNLTr1.     Using the methods referred to in this paragraph, must be evaluated on a time interval t0 to TN PNLTr value. A36.9.4.3 duration of fixed A36.9.4.3.1 Must draw up every 0.5 seconds interval PNLT corresponding PNLTr values versus time curves (PNLTr1 value corresponds to the time TR1).     Then use this method to determine the duration of the provisions amended in Appendix A36.4.5.1 to get EPNLr.     A36.9.4.4.1 A36.9.4.4 source noise source must be determined using the method in Appendix A36.9.3.4 noise adjustments 3.     (April 15, 2007, the first amendment) in annex b in accordance with section 36.103 B36.1 transport and Jet noise level measurement and assessment of noise noise metrics for the evaluation of section B36.2 section B36.3 section B36.4 test reference noise measurement point noise measuring points B36.5 maximum noise level comprehensive evaluation section B36.7 section B36.6 noise certification criteria and conditions Section B36.8 noise certification test procedures-section B36.1 noise measurement and assessment of (a) must use the procedure provided in annex a, or an approved equivalent program, to determine the aircraft's noise level.     Aircraft noise level must conform to the requirements of this annex.     (B) for the fourth phase of aircraft, annex 16 to the Convention on international civil aviation, third edition of the first volume, issued on March 21, 2002 the 7th amendment of Appendix 2, can be used as a noise measurement and evaluation method of choice.     Section B36.2 noise noise evaluation metrics are metrics for the evaluation of the procedure according to the provisions in annex a of the calculated effective perceived noise level, expressed in EPNdB. Subsection B36.3 article benchmark noise measurement points Dang by this provides of program for test Shi, except subsection B36.6 article in the provides of situation, aircraft in following the points of noise level shall not over subsection B36.5 article of provides: (a) cross side full power benchmark noise measurement points: (1) for Jet: the points is located in and runway center line and extension phase parallel, distance runway center line 450 meters (1476 feet) of sideline Shang, aircraft away from to Hou the points of noise level maximum. For engine number more than 3 units of phase I or phase II aircraft, the point is from the runway centre line 648 m (0.35 miles) on the sidelines. If approved by the Civil Aviation Administration of China, can assume that maximum lateral noise in takeoff thrust point corresponds to an extension of the Centre of the runway the plane from a height of 300 meters (985 feet). For phase I or phase II of the four aircraft, the altitude of 435 metres (1427 feet). Plane flew over the noise measurement point's height should be in the target +100-the height of 50 meters (+328-164 feet) range.     For non-Jet-engine-powered aircraft, corresponding to maximum height shall be fixed by the test of lateral noise. (2) for propeller-driven aircraft: the point is an extension of the runway centre line, corresponding at full takeoff power the climb to 650 m (2133 ft) high.     Testing conducted prior to April 15, 2007, the applicant may choose to use B36.3 (a) (1), the noise measurement points.     (B) over the reference noise measurement point: the point is an extension of the runway centre line, away from the takeoff start 6500 meters (21325 feet). (C) the approach reference noise measurement point: the point is an extension of the runway centre line, away from the runway 2000 meters (6562 feet).     Equivalent on the track from runway 300 meters (984 feet) on the slope of 3 ° glide path leads from a height of 120 meters (394 feet) at the corresponding points on the ground level.     Section B36.4 test noise measurement point (a) if the test noise measurement point is not on the reference noise measurement points, you need to modify the position, track and test flight path correction to reference the same way. (B) the applicant must be a sufficient number of lateral noise measurements down to the General Administration of civil aviation of China show that can determine the maximum noise level on the sidelines. For the jets, while the other side of the runway to set noise measuring points are measurements of a symmetric. For propeller-driven aircraft, due to its lateral asymmetry of the noise, should at the same time for each noise measurement points on the other side of the runway measuring symmetry.     Points on either side of the runway in vertical ± 10 meters (33 feet) range are considered to be symmetric.     B36.5 maximum noise level in addition to the annex to cases provided for in section B36.6, in accordance with annex a of noise assessment methods for the determination of the maximum noise level shall not exceed the following values: (a) for the first phase of a plane acoustic changes, no matter how much the number of engines, the noise level should be consistent with 36.7 (c) provisions.     (B) for the second phase of the aircraft, regardless of the number of engine: (1) flying over: the maximum weight is equal to or greater than 272000 kg (the 600000 pounds) at 108EPNdB, from 272000 kg maximum weight (the 600000 lb) reduction by half, reduce 5EPNdB, up to the maximum weight of 34000 kg (75000 lbs) or more hours of 93EPNdB.     (2) lateral and approach: the maximum weight is equal to or greater than 272000 kg (the 600000 pounds) at 108EPNdB, from 272000 kg maximum weight (the 600000 lb) reduction by half, reducing the 2EPNdB until the maximum mass of 34000 kg or less (75000 lbs) at 102EPNdB.     (C) for the third stage of aircraft: (1) flying over: (I) more than three engine aircraft: the maximum weight is equal to or greater than 385000 kg (850000 pound) at 106EPNdB, maximum weight from 385000 kg (850000 pound) reduction by half, reducing the 4EPNdB, up to the maximum weight of 20200 kg or less (44673 pounds) at 89EPNdB;     (Ii) three-engine aircraft: the maximum weight is equal to or greater than 385000 kg (850000 pound) at 104EPNdB, maximum weight from 385000 kg (850000 pound) reduction by half, reducing the 4EPNdB, up to the maximum weight of 28600 kg or less (63177 pounds) at 89EPNdB;     (Iii) less than three engine aircraft: the maximum weight is equal to or greater than 385000 kg (850000 pound) at 101EPNdB, maximum weight from 385000 kg (850000 pound) reduction by half, reducing the 4EPNdB, up to the maximum weight is equal to or less than 48100 kg (106250 pounds) at 89EPNdB.     (2) lateral: regardless of the number of engines, the maximum weight is equal to or greater than 400000 kg (882000 lb), 103EPN, maximum weight from 400000 (882000 lb) reduction by half, reducing the 2.56EPNdB, up to the maximum weight of 35000 kg or less (77200 pounds) at 94EPNdB.     (3) entry: regardless of the number of engines, the maximum weight is equal to or greater than 280000 kg (617300 lb), 105EPNdB, maximum weight from 280000 kg (617300 lb) reduction by half, reducing the 2.33EPNdB, up to the maximum weight of 35000 kg or less (77200 pounds) at 98EPNdB.     (D) for any phase fourth aircraft, which flew over the cross and enter a maximum noise level of Annex 16 to the Convention on international civil aviation, third edition of the first volume on March 21, 2002, issued by the 7th amendment of the 4th chapter, paragraph 4.4, and the 3rd chapter, maximum noise level set out in paragraph 3.4.     Subsection B36.6 article integrated evaluation except this provides subsection 36.7 (c) (1) and 36.7 (d) (1) (ii) article in the by limit of situation, if in a or two a measurement points at of maximum noise level over provides value, must meet following conditions: (a) beyond value of sum shall not is greater than 3EPNdB; (b) any one points at of beyond value shall not is greater than 2EPNdB; and (c) any beyond value must has other one points or the points of reduced volume offset.     Noise certification benchmarks and conditions of section B36.7 (a) General requirements: (1) all benchmark program must meet the requirements of article 36.3 of this provision.     (2) the aircraft performance and flight path calculations must use the benchmark programs approved by the Civil Aviation Administration of China.     (3) the applicant must use this section (b) and (c) take off and approach of benchmark. (4) (backup) (5) the benchmark procedure must be determined according to the following reference conditions.     Used to calculate the absorption coefficient, the baseline atmospheric temperature and relative humidity on the uniform.     (I) sea-level atmospheric pressure 101,325 kPa (2116 lb per square foot), and (ii) the outside air temperature is 25 ° c (77 ° f), that is, ISA + 10 c, and (iii) the relative humidity of 70% and (iv) no wind; (v) in order to define the benchmark took off for takeoff and lateral noise measurement section, provides the track gradient is zero. (B) take off benchmark program: take off the baseline track should be calculated as follows: (1) took off from the start to climb away from the runway at least during the height of the following, you must use the average takeoff thrust or power.     Takeoff thrust/power used must be given in the performance section in the aircraft flight manual, provided for in the B36.7 (a) (5) properly under the reference atmospheric conditions specified in maximum thrust/power can be obtained at run time.     (I) for the first phase and jet aircraft engine bypass ratio is less than 2 second stage, the following applies: (a) more than three aircraft-engine 214 m (700 ft).     (B) all other aircraft-305 m (1000 ft).     (Ii) for the third stage of aircraft and Jet engine bypass ratio is greater than or equal to 2 the second phase of the aircraft, the following applies: (a) more than three aircraft-engine 210 metres (689 ft).     (B) engine number three aircraft-260 meters (853 feet).     (C) fewer than three aircraft-engine 300 meters (984 feet).     (2) reach above (b) (1) under the terms of paragraph height, not to thrust or power reduced to less than the power required to maintain the following, take one of the biggest: (I) 4% the climb gradient, or (ii) multiple aircraft, one does not work when in level flight. (3) for the determination of total power lateral noise levels, should take off at full power and there is no thrust or power on the basis of the calculated flight path.     Tests conducted on April 15, 2007, in accordance with this section (b), (2) a single benchmark tracks include thrust reduction set out in paragraphs, but as an alternate method for determining the lateral noise levels. (4) the takeoff base speed should be selected by the applicant, all engines for the normal takeoff and climb speed, it is at least V2+19 km/h (V2+10), but not more than V2+37 km/h (V2+20). The speed must be reached as soon as possible after the aircraft off the ground, and maintain this throughout the takeoff noise certification test speed.    For all aircraft, speed the noise values measured on test day must be revised to the acoustic base speed. (5) apart from the landing gear can collect, and took off on a whole benchmark program, must be selected by the applicant to take off configuration. Configuration refers to the center of gravity and can affect aircraft performance and noise of the aircraft systems status.     For example, the position of the lift system, APU is working, and whether the engine bleed air extraction and power. (6) when you release the brake weight must be a maximum takeoff weight of noise certification requirements. This weight may lead to article 36.1581 (d) set out in the operational limit; and (7) the average engine is defined as in the validation process, in accordance with the flight manual procedures and limits provided for in, meet the requirements of flight test engines average. Determine the thrust/power and control parameters (for example, N1 or EPR) relationship between.     Validation tests for noise measurement value should be corrected by this relationship. (C) enter the benchmark approach track benchmark is calculated as follows: (1) the plane flew steadily along a 3 ° glide path (2) on subsonic aircraft, and at the approach measurement point is above the line, engine thrust and power stability, keep the approach speed at VREF+19 kph (VREF+10). VREF for the "base landing rate", which is defined as: aircraft with a specific landing configuration, in artificial landing, falling to determine the landing distance by landing the screen height when the plane's speed. Must in entry measurement points above established and keep entry speed; (3) in whole airworthiness validation test of entry benchmark program in the, except landing gear down outside, aircraft should keep constant of entry configuration; (4) landing Shi aircraft of weight should is this section (c) (3) paragraph in the according to noise qualified validation requirements provides of, in landing configuration Xia by allows of maximum landing weight, except this provides subsection 36.1581 article (d) of provides outside; (5) must used most critical of fly institutions type, Defined for this configuration is: the weight of the aircraft weight for the validation requirements, including aerodynamic control surfaces, lift and drag devices during normal open, able to generate the highest noise level of configuration.     This configuration includes the provisions in annex a of the A36.5.2.5 lists, with maximum landing weight during normal operation of the continuous state of noise impact of all projects.     Section B36.8 noise certification testing procedures (a) all test procedures must be approved by the Civil Aviation Administration of China.     (B) test procedures and noise measurements must be conducted in accordance with an approved manner and to get the noise assessment value EPNL, effective perceived noise decibels (EPNdB) as a unit, as described in annex a. (C) acoustic data obtained should be adjusted according to the method referred to in annex a to this chapter under baseline conditions.     Speed and thrust force adjustment must be carried out in accordance with the provisions of section A36.9. (D) if noise certification of test weights apply different weight for takeoff and approach EPNL necessary adjustments should not exceed 2EPNdB and 1EPNdB, respectively. You must use the data to determine the approved by the Civil Aviation Administration of China took off and enter the EPNL changes with weight under two experimental conditions.     As track entry track deviation from benchmark EPNL adjustments must not exceed 2EPNdB.     (E) for entry test, 3 ° ± 0.5 ° stable glide angle is acceptable. (F) If you use a different base programs the equivalent test procedures, test procedures and all adjusted the results to benchmark programs must be approved by the Civil Aviation Administration of China. For taking off the adjustment amount is less than 16EPNdB, the entry does not exceed 8EPNdB.     If the adjusted amount over 8EPNdB and 4EPNdB, respectively, and the result to be lower than the limits provided for in section B36.5 noise level 2EPNdB. (G) during takeoff, lateral, entry test, instantaneous indicated airspeed of aircraft must be maintained at ± 10dB reduction range average air speed 3%. The need to refer to the pilot to determine the airspeed.     However, when instantaneous indicates changes in airspeed range in 10dB drop more than ± 5.5 km/h (± 3) and reviewed by the General Administration of civil aviation of China on behalf of judgment is caused by atmospheric turbulence, you can believe that the noise certification flights canceled because of too much under the influence of atmospheric turbulence.     (April 15, 2007, the first amendment) Annex C-E (standby) (April 15, 2007, the first amendment) certification tests annex f on November 17, 1988, small propeller aircraft and propeller-driven commuter airplane flew over the noise requirements part a general provisions section F36.1 section F36.101 general scope of part b noise measurement test conditions section F36.103 acoustic measurement system     F36.105, measuring, recording, and reproducing apparatus noise measurement procedure section F36.109 section F36.107 section F36.111 of the data records, submitted and approved flight procedures part c data amendment to section F36.201 of the amended section F36.203 section d effectiveness of noise limits noise limitations of part a, section F36.301 aircraft, General provisions     Section F36.1 scope of article 36.1 section 36.501 and (b), the small propeller aircraft, noise level restrictions imposed in this annex and data measurement and correction procedures. Section F36.101 of part b noise test conditions (a) tests must be relatively flat terrain, without the sound absorption characteristics of dense, tall weeds or bushes and trees.     Above the location of the measuring point, the axis perpendicular to the ground, half cone angle of 75 ° taper of airspace, without seriously affecting the aircraft sound barrier.     (B) the test must be carried out under the following conditions (1) no rain.     (2) relative humidity no higher than 90% or less than 30%. (3) 10 meters above the ground (33 feet), environment temperature shall not be less than 5 ° c (41 ° f) or above 30 degrees Centigrade (86 degrees f).     If measurement points from the airport meteorological station at 1.83 km (1 nautical mile) or less, allows the use of the airport reported temperatures. (4) 10 meters above the ground (33 feet), and report wind speed shall not exceed 19-kilometer/hour (10 knots). Report wind speed greater than 7-kilometer/HR (4), direction of flight and the angle between the wind direction must be within ± 15 °, and wind and inverse direction of flight number must be the same.     If you measure the distance from the airport's wind speed table 1.83-kilometer (1-mile) range, allows the use of airport reporting winds.     (5) in the required when measuring the noise point records, did not significantly change the aircraft noise levels in a temperature inversion or abnormal conditions such as wind.     (6) flight test program, measuring equipment and noise measurement procedures must be approved by the Civil Aviation Administration of China.     (7) the sound pressure level of the noise assessment data, in line with article F36.103 of this annex must be used acoustic equipment to measure.     F36.103 AMS AMS must by approved device equivalent to the following equipment: (a) microphone systems, the frequency response shall be in accordance with article F36.105 of this annex set out in the measurement and analysis system for precision.     (B) a tripod or similar microphone stand, sounds should be measured by its smallest.     (C) recording and playing device characteristics, frequency response and dynamic range to meet the requirements of article F36.105 of this annex response and accuracy. (D) using a known sound pressure level sine wave or broadband noise acoustic calibrator.     If you use a broadband noise, for non-overloaded signal level, you must use the average and maximum root mean square (RMS) value to represent. F36.105, measure, record, and playback equipment (a) must record the noise caused by aircraft.     Tape recorder can be used. (B) the system must comply with the International Electrotechnical Commission (IEC) publication entitled, 179th "precision sound level meters" requirement.     The file referred to by 36.6 of China civil aviation regulations.     (C) in the 45~11200Hz frequency range, the entire system can detect flat sine wave of amplitude response must be in IEC Publication 179th (1973 Edition) within the tolerances set. (D) if necessary because the device dynamic range limit, record the channel must have a high frequency changing to and the reverse during playback to straightening.     Must for correction: 800~11200 Hz signal moments to record the sound pressure level of the noise changes between the maximum and minimum one-third octave less than 20dB. (E) if requested, the recorded noise signals must be according to IEC Publication 179th (1973), by those with "slow" Dynamics "a" filters to interpretation.     Filter the output signal must be sent to the square-law detection affecting about 1 second or 800 milliseconds charging time constants detector loops.     (F) equipment must be acoustic free field calibration equipment calibration and authorities require when analyzing the tape recording, analysis must be carried out according to the General Administration of civil aviation of China approved by the e-schools.     (G) when the wind speed exceeds 11-kilometer/HR (6) must be in the process of measuring aircraft noise to the microphones in the wind shield. Noise measurement procedures of section F36.107 (a) must point to a known direction of the microphone so that it receives maximum voice as much as possible and the calibration of the direction line.     Microphone sensor must be above the ground about 1.2 meters (4 feet).     (B) in order to check the sensitivity and to provide acoustic sound level data analysis baseline levels of these two purposes, must be prior to and after each test, acoustic calibrator immediately at the scene with the recorded acoustic calibration system. (C) the gain of the system must be adjusted to the level of aircraft noise measurement to be used. On the acoustic background noise includes noise and measurement system noise at the test site must be recorded and measured.     If an aircraft background sound pressure level sound pressure level is not more than at least 10dB (a), you must use an approved method to correct for background sound pressure level sound pressure level measured on impact. Section F36.109 data records, submitted and approved (a) measured by physical measurement data or for the correction of the data must be recorded and attached to a permanent record, but made to a standard device response deviation correction of measurement do not need to submit.     All other amendments have to be approved, must be estimated in order to finally data of each individual error inherent in the operation.     (B) where the application referred to in article F36.105 of this annex technical requirements of the equipment measured sound pressure level, and amended, must be submitted. (C) for all acoustic measurement and analysis, aircraft performance and meteorological data for the device type must be submitted.     (D) in article F36.101 of this annex on the measure provided for in point, before each test, the test or trial period, immediately following measured atmospheric data must be submitted as follows: (1) the air temperature and relative humidity; (2) the maximum, minimum and average wind speed.     (E) the local terrain, ground cover and may interfere with the audio commentary on the event, must be submitted. (F) must submitted following aircraft information: (1) aircraft, and engine and propeller of type don't, and model and serial number (if has words); (2) may effect aircraft noise characteristics of any modified or non-standard equipment; (3) maximum validation took off weight; (4) each flew over the measurement points Shi of empty speed, to km/hours said; (5) each flew over the Shi, with each minutes turned number and other about parameter said of engine performance; (6) with has calibration of aircraft height table, and     After approval of photography or an approved tracking devices the aircraft height measured in metres and (g) must be based on an approved guarantee and of this annex, test procedures and conditions correspond to a sufficient number of sample rate, record the plane's speed, position and engine performance parameters.     F36.111 flight procedures (a) that is consistent with this annex on noise levels required test, must contain at least six times in the measurement location above the level, these flat fly when passing above the measurement point shall be (Editor's Note: this mathematical manuscripts) height deviation above the measurement point within the range of ± 10 °.     (B) every time flying over the test must be carried out under the following conditions: (1) power must be not less than the aircraft flight manual, or the approved information manual, approved sign or any combination of approved instrument tag under normal use within the scope of the supreme power.     (2) propeller speed must be based on the same aircraft in cruise flight form the stable speed, but if the power state of the provisions of this paragraph, aircraft speed is the maximum speed permitted by more than flying, you can speed up the flight.     Amendments of part c data F36.201 data (a) when the temperature exceeds 20 ° ± 5 ℃ (68 ± 9 ° f) range, or when the humidity is lower than 40%, and noise data must be corrected according to the General Administration of civil aviation of China approved method to 25 c (77 ° f) and relative humidity 70%. (B) of this section must be used (c) set out in the amendment. Correction amount must be determined according to the methods provided for in this annex, and algebra and added to the measured value.     This correction is limited to 5dB (a) or less.     (C) performance fix must be calculated according to the following formula: (Editor's Note: this formula see manuscript) D15-takeoff at maximum authorized takeoff weight to 15 meters (50 feet) height distance (unit: m) R/C-validation of the best climb rate (units: m/s) Vy-best climb speed, its unit identical to the climb.     (D) when taking off to 15 meters (50 feet) in height when the distance is not part of an approved performance data, the single aircraft must use 610 meters (2000 ft), multiple aircraft must use the 825 meters (2700 feet). Section F36.203 the validity of the results (a) derived from test results must average DB (a) confidence and 90%.     Noise level here is valid for all measurement points across the revised acoustics made test flights the arithmetic mean of the measured values. (B) the number of sampling must be sufficient to establish statistically no more than ± 1.5dB (a) 90% confidence.     Unless it has been approved by the Civil Aviation Administration of China, and must not be omitted from any results in the average.     Part d F36.301 aircraft noise limits of the noise limits (a) must be used in accordance with this part b of the annex and the provisions of part c of the measure and correction of noise data to prove consistent with this section. (B) the weight is equal to or less than 600 kg (1320 lb), the noise level must not exceed 68dB (a).     If a weight of more than 600 kg (1320 lb), is less than or equal to 1500 kilograms (3300 lb), noise limits to 1dB/75 kilograms (1dB/165 pounds) rates increased linearly until 1500 kilograms (3300 lb) weight of 80dB (a) than the weight after noise restrictions remain for 80dB (a) constant.  Annex g certification test on or after November 17, 1988 's small propeller aircraft and propeller commuter planes take off noises to claim a part of the scope of article G36.1 of the general part b noise G36.101 General conditions section G36.103 AMS G36.105 measuring, recording and playback equipment noise measurement procedures of section G36.107 section G36.109 Data records, submitted and approved G36.111 flight program part c data correction amended section G36.203 section G36.201 test results the results section G36.301 of part d noise limits the effectiveness of aircraft noise limit the scope of article G36.1 of the General provisions of part a of the annex to article 36.1 section 36.501 and (c) involve small propeller aircraft and propeller-driven commuter class     Measurement of aircraft noise level restrictions imposed and noise as well as the data state of the revision to the standard procedures. Section G36.101 of part b noise test conditions (a) tests must be relatively flat terrain, without the sound absorption characteristics of dense, tall weeds or bushes and trees.     Above the location of the measuring point, the axis perpendicular to the ground, half cone angle of 75 ° taper of airspace, without seriously affecting the aircraft sound barrier.     (B) test must in following conditions Xia for: (1) no rainfall; (2) environment atmosphere temperature in 2.2 ℃ and 35 ℃ Zhijian (36 ° f and 95 ° f); (3) relative humidity in 20% and 95% Zhijian (containing); (4) wind speed not over 19-kilometer/hours (10 section) and side wind not over 9-kilometer/hours (5 section), with 30 seconds within average; (5) in requirements of measurement points records Shi, no makes aircraft noise level produced obviously change of temperature inverse increased or exception of wind, conditions; (6) meteorological measurements must be on the ground more than 1.2 meters (4 feet) and 10 meters (33 feet) in between.     If the measuring station at the airport meteorological measuring 1.83 km (1 nautical mile) or less, you can use the data from the weather station.     (C) flight test program, measuring equipment and noise measurement procedures must be approved by the General Administration of civil aviation of China.     (D) the sound pressure level of the noise assessment data, in line with article G36.103 of this annex must be used acoustic equipment to measure.     Section G36.103 AMS AMS approved equipment must have the following characteristics: (a) microphone systems, the frequency response shall conform to the provisions of article G36.105 of the annex to the measurement and analysis system for precision.     (B) a tripod or similar audio support, measured by its sound interference should be minimized.     (C) recording and playing device characteristics, frequency response and dynamic range should meet the requirements of article G36.105 of this annex by the response and accuracy. (D) using a known sound pressure level sine wave or broadband noise acoustic calibrator.     If you use a broadband noise, for non-overloaded signal level, you must use the average and maximum root mean square (RMS) value to represent. G36.105, measure, record, and playback equipment (a) must record the noise caused by aircraft.     Diagram approved tape recorder, sound level recorder or sound level meters are acceptable. (B) the system must comply with the International Electrotechnical Commission (IEC) publication No. 651 "sound level meters" and publication No. 561 "on aircraft noise certification electro-acoustic measurement equipment" requirement, the two files have been referred to by article 36.6 of this provision.     Provisions must comply with the IEC No. 651 sound level meter type sound level meter requirements.     (C) in the 45~11200Hz frequency range, the entire system can detect flat sine wave of amplitude response must be within the tolerance range specified in IEC Publication No. 651. (D) if necessary because the device dynamic range limit, record high frequency preemphasis and channel must be increased when replay reverse correction.     Must for correction: 800~11200Hz between the instant recording of sound pressure level of the noise signal changes between the maximum and minimum one-third octave band is less than 20dB. (E) noise in the output signal must be according to IEC Publication No. 651, labeled "slow" Dynamics "a" filters up to interpretation.     Can use the icon sound level recorder, the sound level meter or the equivalent digital recorders to record. (F) the equipment must be in free field calibration equipment for schools. Authorities analysis requires analysis of tape recording equipment must be carried out according to the General Administration of civil aviation of China approved by the e-schools.     If applicable, must be according to the provisions in annex a of the calibration requirements of A36.3.8 and A36.3.9.     (G) when the wind speed exceeds 9-kilometer/HR (5), must be measured in the process of aircraft noise in the microphone and wind shield. Noise measurement procedures of section G36.107 (a) microphone must be 12.7 mm diameter pressure, with protective grid mounted in inverted position, its films at the top of a metal disc 7 mm of the microphone, and parallel to the disc. White paint of the metallic disk must be 40 cm in diameter and at least 2.5 mm thick, horizontally and flush with the ground, buried in the ground, there shall be no gap at the bottom of the disc.     Microphone position must be on the flight line perpendicular to the radius of the disc and test aircraft, from the disc Center 3/4 RADIUS. (B) in order to check the sensitivity and to provide acoustic reference level sound level data analysis purposes, must be prior to and after each test, live acoustic calibrator immediately recorded the acoustic calibration of the system.     If you are using a tape recorder or diagram sound level recorder, must make use of pink noise, or random pseudo noise on the frequency response of the system at the level of full scale reading during this experiment determines the 10dB. (C) the gain of the system must be adjusted to the measurement of aircraft noise level for ambient noise, including acoustic background noise and electrical noise measurement systems record and determination at the test site.     If an aircraft background sound pressure level sound pressure level is not more than at least 10dB (a) must begin with a closer to takeoff points points of departure, and approved amendments to the benchmarking results.    Section G36.109 data records, submitted and approved (A) represent the physical measurement data or for the correction of the measured data must be recorded and attached to a permanent record, but responses to standard deviation measured amendments made do not need to submit. All other amendments must be approved.     Last data must be estimated in order to make individual errors that are inherent in every step of the operation.     (B) where the application referred to in article G36.105 of this annex technical requirements of the equipment measured sound pressure level, and amended, must be reported.     (C) for all acoustic measurement and analysis, aircraft performance and meteorological data for the device type must be submitted. (D) in this annex subsection G36.101 article in the provides of measurement points Shang, each test Qian, and test Hou or test during, immediately measuring have of following atmosphere data must submitted: (1) environment temperature and relative humidity; (2) each test Shi of maximum and average wind speed and wind; (e) for local terrain, and ground cover real and the may interference recording of event of reviewed, are must submitted; (f) must with by approved of, and not rely on normal flight instrument of method, as radar track, and Longitude instrument triangle positioning or optical set standard technology determine aircraft relative Yu benchmark flight track of location; (g) must submitted following aircraft information: (1) aircraft, and engine and propeller of type don't, and model and serial number (if has words); (2) may effect aircraft noise characteristics of any modified or non-standard equipment; (3) maximum validation took off weight; (4) for each flight test, with normal calibration had of instrument by determine of flew over the measurement points height Shi of empty speed and environment temperature; (5) for each flight test Engine performance parameters such as air pressure or power, propeller speed (RPM) and other parameters must be properly calibrated instruments to measure.     For example, when the plane's mechanical speed table, must be an independent device accuracy is within ± 1%, verify that the rotational speed of the propeller (6) must use approved methods to record flying directly above the station for the requirements of article G36.201 of this annex when needed for the amend airspeed, position, and performance data. G36.111 flight procedures (a) noise measurement points are located on the center line of the runway extension from the takeoff point 2500 m (8200 ft). Planes must be perpendicular to the measuring points ± 10 ° and base height ± 20% range over the measuring point. Flight test program with the approval of the maximum takeoff weight of start and after every flight an hour must be adjusted to the maximum weight weight. Each flight tests must be based on the best climb rate indicates that airspeed Vy ± 9-kilometer km/h (5 knots).     All testing, measuring and data correction program must be approved by the Civil Aviation Administration of China.     (B) take off track base must be calculated according to the following atmospheric conditions: (1) to 1013.25 mbar (101,325 kPa) sea-level atmospheric pressure, (2) ambient air temperature is 15 ° c (59 ° f), and (3) relative humidity 70%; (4) zero wind speed.     (C) take off track base must be calculated according to the following two stages: (1) phase, (I) from release brakes to runway 15 meters (50 feet) high point must take off power.     (Ii) constant takeoff configuration must be selected by the applicant at this stage remains the same.     (Iii) when you release the brake the aircraft's maximum takeoff weight has to be requested for noise certification of maximum weight.     (Iv) the first stage must be paved with the horizontal runway takeoff of airworthiness approval of commensurate value (or seaplane is compatible with the corresponding values).     (2) phase II (I) corresponds to the second stage to the end of the first phase.     (Ii) the airplane must be in the form of climbing gear up (if you can put away), flap in the second stage must be set to the corresponding the normal up position from start to finish.     (Iii) speed must be the best climb speed Vy. (Iv) aircraft equipped with fixed-pitch propeller, in the second stage engine takeoff power must be maintained from start to finish. For aircraft equipped with constant speed propeller of variable pitch propeller, or, in the second stage engine takeoff power and speed must be maintained from start to finish. If in the process of reaching the datum point airworthiness limitations are not allowed to take off in power and speed, you must remain within the scope of this restriction allows takeoff power and speed; you must maintain maximum continuous power and speed. In the second phase must be used according to the airworthiness standards in takeoff power allowed by the long time.     Baseline level should assume that climb gradients for each power setting. 　　Section G36.201 of part c data correction of test results (a) these amendments take into account the following: (1) testing weather conditions and differences between the baseline condition caused by atmospheric absorption differences. 　　(2) the actual aircraft flight path noise path length difference between the track and benchmark.     (3) test and benchmark conditions between the spiral direction of blade tip Mach number change.     (4) change of engine power between the test and reference conditions. (B) when the test conditions specified in Figure G1 beyond the noise data obtained during the atmospheric absorption correction is required. 　　Method must be approved by the Civil Aviation Administration of China outside the scope of noise data revised to 15 c (59 ° f) and relative humidity 70%.     (Editor's Note: this graphic originals) in Figure G1 does not need for measurement of sound absorption correction window (c) Helix blade tip Mach number does not need to be amended if the spiral direction of blade tip Mach number: (1) 0.70 or below, its test of Helix spiral direction of blade tip Mach number in the Datum blade tip Mach number 0.014.     (2) greater than 0.70 but equal to or less than 0.80, its test of Helix spiral direction of blade tip Mach number in the Datum blade tip Mach number less than 0.007. (3) greater than 0.80, its propeller blade tip Mach number test is at the base of the spiral direction of blade tip Mach number less than 0.005.     Mechanical tachometer, if the spiral direction of blade tip Mach number greater than 0.80, its test of Helix spiral direction of blade tip Mach number in the Datum blade tip Mach number less than 0.008. (D) Dang test conditions in provides conditions zhiwai, must with approved of program or following simplified program for amendment: (1) must with plus is equal to Xia type of value to put measuring have of sound level from test day meteorological conditions amendment to benchmark conditions: type in the HT for test aircraft in noise measurement points are above flew Shi to meters said of height, HR is in benchmark conditions Xia to meters said of height, a, is test day conditions Xia in 500Hz at of sucking sound rate, as motor vehicle Engineers Association (SAE) ARP866A, file by provides.     The document entitled "assessing aircraft flying over the noise as the temperature and humidity of atmospheric absorption function standard value", has been referred to by article 36.6 of this provision. (2) you must use algebraic addition plus (1) to decibels of sound levels measured for height adjustment. When test day conditions in Figure G1 range, HT in an aircraft noise measurement points for test flew out just above the height of HR as a benchmark level. When test day conditions in Figure G1 outside the prescribed limits, and (3) must be the algebraic addition with (2) oars Mach number correction on the spiral direction sound pressure level measured in decibels, MT and MR representing the test here and the Datum blade tip Mach number. Constant k is equal to the measured by the sound level dB (a) relationship with the blade tip Mach number derived from slope of the curve. K values can also be determined from the approved data. When MT is less than MR k nominal value of 150 is available. When MT is greater than the nominal value of k shall not be used for amendments MR.     Benchmark MR spiral direction of blade tip Mach number is the corresponding measuring points above the benchmark in the State (speed, air speed and temperature) of the Mach number.     (4) the sound level must be measured in decibels of engine power using algebraic methods plus an increment equal to the value of an amended: PT and PR is here representing the engine power tests and benchmarks. Section G36.203 the validity of the results (a) flew over the measuring point must be at least 6 times. Must be derived from the results of average noise level (LAMax) values within the limits 90% of confidence.     Average noise level is valid for all measurement points across the test flight as amended, acoustics of the arithmetic mean of the measured values. (B) the number of sampling must be sufficient to establish statistically no more than ± 1.5dB (a) 90% confidence.     Unless it has been approved by the Civil Aviation Administration of China, and must not be omitted from any results in the average.     Part d G36.301 aircraft noise limits of the noise limits (a) must be used according to the provisions of part b and c of the present annex the measured noise and amended data to prove consistent with this section. (B) for multiple aircraft and single aircraft prototype validation applications received prior to April 15, 2007, when aircraft weight is equal to or less than 600 kg (1320 lb), the noise level must not exceed 76dB (a). If a weight of more than 600 kg (1320 lb), noise varies linearly with the logarithm of the weight of the plane, each weight increases 1 time, noise 9.83dB DB (a). Up to 88dB (a), that remained unchanged until 8618 kg (19000 pounds).     G2 noise level limits and weight curves. (C) the prototype validation applications received on or after April 15, 2007 the single aircraft when the aircraft's maximum authorized takeoff weight is equal to or less than 570 kg (1257 lb), the noise level should not exceed 70dB (a). If weight greater than 570 kg (1257 lb), noise varies linearly with the logarithm of the weight of the plane, each weight increases 1 time, noise 10.75dB DB (a). Up to 85dB (a), that remained unchanged until 8618 kg (19000 pounds).     G2 single plane is given the noise level restrictions and weight curves.     (Editor's Note: graphics here see original) G2 on noise levels and weight curves (April 15, 2007, the first amendment) Annex h helicopter noise requirements under Chapter h, a part of the baseline conditions section H36.1 General H36.3 base H36.5 bar, symbols and units in part b of the test conditions under section 36.801 noise H36.101 noise certification test and measurement conditions Section H36.105 section H36.103 departure test conditions over test conditions section H36.109 section H36.107 enter test conditions in the measurement of the noise of the helicopter received ground measured data submission and amendment section H36.111 section H36.113 part c of atmospheric attenuation According to article 36.803 noise assessment and calculation of section H36.201 article H36.203 in EPNdB noise evaluation of noise levels of calculation section d section H36.205 detailed data correction procedures pursuant to article H36.301 section 36.805 noise limits noise measurement, assessment and calculation of section H36.303 (standby) part a of the section H36.305 noise level baseline condition     Subsection H36.1 article General this annex provides has subsection 36.1 article determine of helicopter of noise requirements, including: (a) according to h chapter of helicopter noise qualified validation test by must followed of conditions and in each test process in the according to subsection 36.801 article measurement helicopter noise must using of measurement program; (b) according to subsection 36.803 article will measuring have of data amendment to benchmark conditions by must using of program and calculation to effective feel noise level (EPNL) for noise evaluation volume of program;     (C) under section 36.805 noise restrictions must demonstrate compliance.     Section H36.3 reference test conditions (a) atmospheric conditions, performance data and noise the noise certification measurements must be revised to the following reference atmospheric conditions, which assumes that this condition exists in the ground to the height of the position (1) sea-level pressure of 1,013.2,500 PA (2116 lb per square foot).     (2) the ambient temperature is 25 ° c (77 ° f) (3) relative humidity of 70% (4) with no wind (b) benchmark testing benchmark tests as flat, and in a 10dB reduction no obstacles on the track within the line of sight.     (C) take off the baseline profile (1) H1 gives a typical takeoff profile, including the baseline condition. (2) the reference track is defined as a starting point (from the ground 20 meters (65 feet) high and in front of the Center microphone position 500 meters (1640 feet) points) started to angle β a line sloping upward, the angle β is the lowest engine certification the best climb rate and Vy definitions. Constant climb angle β values are determined by data of the manufacturer (approved by the Civil Aviation Administration of China) export to determine baseline conditions of flight profiles.     Beginning on Cr constant climb angle β, then crossed a station until the end of corresponding type certification take off track (Ir). (D) level over the base profile Dr points represent levels began to fly the reference section (see figure H2), helicopter flight from Dr close horizontally, when measured at point a helicopter from the ground 150 m (492 feet). The airspeed stabilizes at 0.9VH;0.9VNE;0.45VH+120 kph (0.45VH+65); 0.45VNE+120 km/h (0.45VNE+65), four small. Throughout the 10dB reduction time on max continuous RPM rotor stability.     Helicopter levels over a point, proceed to the Jr. (E) for noise certification, VH is defined as in the largest certification weight, at sea-level pressure of 1,013.2,500 PA (2116 lb per square foot), 25 c (77 ° f) environment can be obtained under the conditions corresponding to the maximum continuous power minimum engine torque to get Flight airspeed. VNE is known as no one can surpass the value of air speed.     Noise certification of VH and VNE values must be listed in the rotorcraft flight manual.     (F) enter the reference section (1) figure H3 the entry profile is given, including the baseline conditions. (I) helicopters where e represents the entry section begins. Should be sufficient distance (EK) location to ensure that the required records in respect of helicopter helicopter noise is the biggest pure-tone correction noise level (PNLTM) 10dB reduction of time periods.     Track benchmark, ErKr shows that run is in stable conditions, torque, RPM, indicating that airspeed and 6 ° approach angle of descent rate. (Ii) testing comes into play section by the entrance angle β with highly AH over a point just above the reach of k points to determine k noise certification points for buying the end point of the section.     Test entry angle β to be between 5.5 and 6.5 degrees. (2) helicopter to h-point 6 ° approach slope is stable and maintained throughout the 10dB reduction within the time the slope.     Helicopter by e and continue along the approach slope until you reach k points.     Subsection H36.5 article symbol and units in on helicopter noise qualified validation of this annex in the by using of symbol and units of meaning following: b part according to subsection 36.801 article of noise measurement subsection H36.101 article noise qualified validation test and measurement conditions (a) General this section provides has implementation noise qualified validation test must meet of conditions and in each measurement helicopter noise of test in the must using of measurement program.     (B) test site requirements (1) shows that meet the requirements of helicopter noise level of certification tests must include a series of departures, level flying over and approaching flight, must measure provided for in this section where the measurement point to measure the noise in flight.     (2) every takeoff tests, flew over the test and entry tests include flight-track below the baseline track noise measuring stations and two lines of stations to measure, each side measuring stations and from the baseline on both sides of the base flight-track flight-track 150 meters (492 feet) and with a vertical line.     (3) each line noise measuring stations and flight trajectory measurement stations on the ground level difference of not more than 6 m (20 ft).     (4) in each noise measurement of sound absorption characteristics of ground station should not be too large, such as dense grasses, shrubs or trees caused by. (5) took off, flying over or approaching noise measurements in PNLTM10dB during the drop, there shall be no obstructions can significantly affect the helicopter noise field (which may not exist in the following space): (I) for all measuring stations on the ground tracks or on the sideline, to the measuring point (on the ground directly below the microphone), cone-shaped space.     This cone-shaped space is defined as 80 ° to the axis perpendicular to the ground half cone angle of space, and (ii) on the sideline noise measuring stations for microphones with helicopters in the space above the line of sight.     (6) if taking off and flying over the test series was not at the request of noise certification under the condition of maximum takeoff weight, you should implement the following additional requirements: (I) tests and taking off over testing is at least once at or exceeding the maximum authorized weight of.     (Ii) for each weight must be in the maximum authorized weight of test +5% or-10% range.     (7) entry of each test must be aircraft steadily along 6 ° ± 0.5 ° approach angle, and meet the requirements of the provisions of section H36.107.     (8) if the enter the test series is not in the authorized maximum landing weight under the conditions requested by, you should implement the following additional requirements apply: (I) at least an entry test in is equal to or exceeds the maximum landing weight.     (Ii) the weight of each test must be between 90% and 105% of the maximum authorized weight.     (C) meteorological limits test must be conducted in the following atmospheric conditions: (1) no rain or other precipitation. (2) noise measuring 10 meters above the ground and in helicopters (33 feet) sound propagation paths between high environmental temperature ~35 ℃-10 ℃ (14 ° F~95 ° f) (inclusive).     Must use the noise measuring 10 meters above the ground (33 feet) measurement of air temperature and relative humidity to modify the propagation path of sound absorption.     (3) noise measuring stations 10 metres above the ground and in the aircraft's relative humidity and ambient temperature conditions should be made in one-third-octave Center frequencies for atmospheric attenuation of the 8kHz band is not more than 12dB/100 metres, and relative humidity of 20%~95% (inclusive). (4) measured at 10 metres above the ground wind speed does not exceed 19-kilometer/hour (10 knots) and cross-wind component does not exceed 9-kilometer/HR (5).     Measure wind speed must be used in a 10dB reduction method of continuously for a period of 30 seconds on average.     (5) there should be no rules weather conditions (including turbulence), each noise measurement station can significantly affect the helicopter noise measurements of meteorological conditions. (6) the requirements of this annex to wind speed, temperature and relative humidity measurement in noise measuring stations must be around 10 metres above the ground on a high, measurements of atmospheric conditions must be recognized by the Civil Aviation Administration of China representatives of regional meteorological conditions near the ground where the measurement of aircraft noise.     In some cases, fixed weather stations (such as at the airport and other facilities exist) can meet the requirements.     (7) the temperature and relative humidity measurements must be at every 30 minutes measured noise test measurement.     (D) aircraft test procedure (1), test procedures and measurement of noise emitted by aircraft must be based on the provisions laid down in annex a, the unit EPNdB, called the effective perceived noise level noise evaluation of measuring methods for and dealt with.     (2) must be approved by the Civil Aviation Administration of China and has nothing to do with normal flight instrument determine relative to the base of the helicopter flight path (through the noise measuring stations flight path) the height and horizontal position, for example, radar tracking, theodolite triangulation, laser tracking, photographic or differential global positioning system. (3) the helicopter along the track to the position should be approved by the Civil Aviation Administration of China in sample rate synchronization signal and noise measuring stations will measure the noise mapping. PNLTM10dB falling within the whole time helicopter position relative to the baseline trajectory must be recorded.     Measurement and sampling equipment must be approved by the Civil Aviation Administration of China.     (4) must be approved by the Civil Aviation Administration of China's equipment and sampling rate when amendments to records requested in section H36.205 of the annex to the aircraft performance data.     Section H36.103 departure test conditions (a) subject to section H36.101 and section H36.205 of this annex (b) applicable requirements, this section applies to all take off in this annex indicate that compliance with part 36 noise test. (B) a group must consist of at least six times as follows over the ground track of noise measuring stations (three stations at the same time measurement) flight: (1) the airspeed is Vy ± 9-kilometer/hour (5) or approved minimum climb speed after take off ± 9-kilometer km/h (5 knots), whichever is greater.     Must be arrive within the entire period of 10dB reduction and maintain this speed.    (2) each test flight levels must be at a distance of flight-track noise measuring 20 meters above the ground (65 ft) height. (3) reaching from the noise measurement station 500 meters (1640 feet) point, the helicopter is required to stabilize the corresponding to the lowest installed engine power under reference atmospheric conditions of maximum takeoff power or gear box torque limit, whichever is less.     (4) must be in a 10dB reduction within the entire period of helicopter maintained ambient temperature at sea level best climb speed at 25 ℃ ± 9-kilometer km/h (5 knots), or when ambient temperature 25 ° c at sea level to approve minimum climb speed after take off, whichever is greater.     (5) in a 10dB reduction period, average rotor speed may not be functioning at maximum normal rotor speed range changed more than ± 1%.     (6) in the entire 10dB reduction period, helicopters should be benchmark tracks over ± 10 ° or ± 20 m (65 ft) within the flight, whichever is greater.     (7) took off throughout the baseline program, applicants are selected to take off configuration should be maintained unchanged, and landing gear position to maintain airworthiness tests determine the optimum climb speed when Vy location.     Section H36.105 flew over the test conditions (a) subject to section H36.101 and section H36.205 (c) applicable requirements, this section applies to all carried out according to the provisions of this annex demonstrate compliance to 36 over the noise test. (B) a set of tests must be made up of at least six flights.     Downwind level flight of times should and wind level flew over the flight of times equal, and in three a noise measurement station while measurement: (1) level flight cruise configuration; (2) from ground track noise measurement station 150 ± 9 meters (492 ± 30 feet) of height, and (3) in whole 10dB drop of time paragraph within, helicopter should in benchmark track vertical above ± 10 ° or ± 20 meters (65 feet) range within flight, both take big who.     (C) over the noise test must be conducted as follows: (1) in whole over the measurement section, should be kept at 0.9VH or 0.9VNE, or 0.45VH+120 kilometers per hour (0.45VH+65) or 0.45VNE+120 kilometers per hour (0.45VNE+65), four small.     (2) in a 10dB reduction period, rotor speed shall not exceed the maximum average normal rotor operating speed ± 1%.     (3) when the helicopter's noise level measured by 10dB reduction in PNLTM when the time period, the power must be stable.     (D) the deviation from the reference airspeed the airspeed must not exceed ± 9-kilometer km/h (5 knots).     Section H36.107 entering test conditions (a) in addition to section H36.101 and section H36.205 of this annex (d) requirements, this section applies to all on the basis of this annex shows that meet the entry test in 36.     (B) a group test must by at least six times flew flight ground track noise measurement station (three a noise measurement station Shang while measurement) of following flight composition: (1) in 6 ° ± 0.5 ° of entry slope Shang; (2) from ground track noise measurement station 120 ± 10 meters (394 ± 33 feet) of height; (3) in whole 10dB drop of time paragraph within, helicopter should in benchmark track vertical above horizontal ± 10 ° or ± 20 meters (65 feet) range within flight, both take big who;     (4) to stable of is equal to validation qualified of best climb speed Vy or by approved of minimum entry speed for, take which larger of, in entry and crossed flight track benchmark points until normal grounding of time within power keep not variable; and (5) in 10dB drop of time paragraph within, average spin wing speed shall not over maximum normal spin wing run speed ± 1%; and (6) should in whole entry benchmark program in the keep airworthiness validation test in the entry configuration not variable, landing gear in down bit.     (C) the deviation from the reference airspeed the airspeed must not exceed ± 9-kilometer km/h (± 5).     Section H36.109 in the helicopter received ground noise measurement of Appendix a to these rules of use are given in the section A36.3 measurement system and measurement, calibration and analysis of the General program. Measured data submission and amendment of section H36.111 (a) general framework represents the physical measurements of data or correction of the measured data, including the device response deviation correction made to the measurement results must be recorded in a permanent way, and attached to the record. Each amendment must be submitted to, and approved by the Civil Aviation Administration of China.     Each step of the final data must be inherent in the operation of a single error is estimated.     (B) the data submitted (1) measured sound pressure level and amendments must be used with this annex conforms to the standards set forth in section H36.109 of the device represented by the one-third SHG Cheng Sheng pressure level obtained.     (2) equipment used for noise measurement and analysis of all of the models, as well as aircraft performance and weather data to be submitted.     (3) measured in the whole process, in order to verify conformity to requirements of this annex, the atmospheric environment data must be submitted.     (4) must be submitted to the local topography, floor coverings, as well as those events that can affect the sound recording.     (5) the following information must be submitted to the aircraft: (I) and rotary-wing aircraft engine model, type and serial number.     (Ii) total size of aircraft and engines.     (Iii) each test flight the aircraft gross weight.     (Iv) aircraft configuration, including the position of the landing gear.     (V) speed (km/h).     (Vi) the helicopter from the flight instruments and manufacturer data engine performance.     (VII) aircraft flight path (relative to the height of the land, with the metre), the track must be approved by the Civil Aviation Administration of China has nothing to do with normal flight instrument set, such as a radar tracking station, theodolite triangulation, laser positioning, camera positioning technology. (6) aircraft speed and position parameters must be modified and the engine performance to noise certification provided for in article H36.3 of this annex reference sample rate recording of test conditions.     The horizontal position relative to the reference ground tracks must be submitted.     (C) data correction (1) location of the aircraft, must be performance data and noise measurement value correction to this annex, section H36.3 and section H36.205 of the noise certification under baseline conditions. (2) must apply for certification with the base estimation under the condition of tracks and measured under the test conditions test track deviation between the measured track amendments. With helicopter flight path or the performance of the necessary corrections, export data can be approved by the Civil Aviation Administration of China, this amendment is for the difference between the measured and the baseline is, and varies with distance attenuation values and appropriate tolerance correction.     On following of any combination, EPNL amendment must not over 2.0EPNdB, except in took off flight conditions Xia not over 4.0EPNdB, which 1 (see H36.205 (f) (1)) and 2 (see H36.205 (g) (1) (I)) in the of -7.5Log (AL/ALr) items of arithmetic and of total shall not over 2.0EPNdB: (I) helicopter no from measurement station of are above through.     (Ii) the base track and any difference between the actual test flight path.     (Iii) the details provided for in article H36.205 of this annex amendment requirements. (Iv) taking into account the test engine thrust or power base of engine power or thrust on the difference between the measured levels of noise levels across the any of the amendments.     In article H36.205 of this annex set out the detailed requirements for the amendment.     (3) in a 10dB reduction period, helicopters on each one-third octave sound pressure levels must be more than the A36.3.10.1 average background sound pressure level determined by at least 3dB, or use a method approved by the Civil Aviation Administration of China. (D) the validity of the results (1) must be derived from test results meet the 90% confidence of three average EPNL values, each value must be taking off, level over all valid tests and entry conditions as amended, the arithmetic mean of the measured values.     90% degree of confidence applies to individually take off, flying and approach. (2) to take off, flying over, enter the certification measurements, experiments are at least six times. The number of samples must be validation enough for three average noise level of each put in 90% of the statistical confidence level, the confidence level is not more than ± 1.5EPNdB.     Unless otherwise provided by the General Administration of civil aviation of China, on the average shall not be discarded during processing any results. (3) for the purposes of this annex, at least six times the takeoff, approach and level of six times over six times.     In order to comply with this requirement, each flight must be conducted on all three noise measuring stations valid record.     (4) is used to calculate and benchmark conditions and the approved flight profile VH and Vy values must be measured and modified SPL submissions. Section H36.113 of atmospheric attenuation (a) in accordance with this annex qualified helicopter noise measured during the validation test of one-third-octave spectrum value must conform to or amendments to section H36.3 (a) provided for in the baseline condition. Each amendment must be considered along the aircraft and microphones for sound propagation paths between the test day and date conditions of atmospheric attenuation of differences.     Unless the atmospheric conditions within the testing window provided in this annex, the test data is not acceptable. (B) 50Hz~10kHz each one-third octave attenuation rate varies with distance attenuation rate according to SAE ARP866A "for assessing aircraft flying over the noise as the temperature and humidity of atmospheric absorption function standard value" formula and table in to determine.     Respectively, in the provisions of section A36.7 in metric units or imperial units given atmospheric attenuation formula.     (C) atmosphere attenuation of amendment (1) whenever following situation Shi, on measuring have of data by calculation of EPNL value must for amendment: (I) Dang temperature and relative humidity of environment atmosphere conditions not meet benchmark conditions, that respectively for 25 ℃ (77 ° f), 70% Shi; (ii) Dang measuring have of track not meet benchmark track Shi; (iii) must with ground on 10 meters height of points at measuring have of temperature and relative humidity amendment spread path sound absorption. (2) must be counted in each one-third within the 50Hz~10kHz octave from the aircraft to the microphone location on sound propagation paths as a whole the average decay rate.     The decay rate must be used in article H36.111 of this annex (d) calculation of the required amendments. Part c in accordance with article 36.803 noise assessment and calculation of H36.201 measured in EPNdB noise evaluation of (a) in accordance with article 36.803, units must be used for effective perceived noise decibels (EPNdB) the effective perceived noise level (EPNL) for noise assessment. In addition to this section (b) provided, 36 annex a must be used in the program of EPNL.    Noise values are included in annex a of the requirements, including: (1) the perceived noise level, (2) spectra are not amendments to the rules, (3) tone correction; (4) the duration, amendment (5) the effective perceived noise level, and (6) na table of an arithmetic expression.     (B) with A36.4.3.1 (a), the noise certification of the helicopter, its spectrum is not amended 50Hz one-third times to the rules must be amended from Cheng Sheng starting pressure level.     Section H36.203 the calculation of noise (a) to verify compliance with section H36.305 of the noise level limit, three noise measuring points at the same time the noise value measured must be an arithmetic average to get single EPNL values of each flight. (B) for each test series, which took off, flying over or approaching series noise level calculation, must be at least 6 flying EPNdB average values of the individual.     Valid for all the tests, and article H36.111 of this annex (d) 90% confidence the EPNdB value applies individually to each test series. Section H36.205 detailed data correction procedures (a) general framework if the test conditions are not consistent with those set out in article H36.305 of this annex the noise certification reference conditions, you must implement the following amendments: (1) if test and benchmark for measuring different conditions, must be calculated by measuring noise figure of EPNL values is modified.     Lead to different values, including: (I) measurement test conditions of atmospheric absorption and benchmark test different conditions of atmospheric absorption, or (ii) measurements track different track and benchmark. (2) amendment procedure would produce one or more of the following possible correction values, these values must be calculated algebraically EPNL, to amend it to reference conditions: (I) the flight profile must define benchmarks and test conditions. This program requires noise and flight path using a sync signal synchronous recording, to determine the flight test section, including PNLTM of noise measuring stations observed when aircraft position.     Take off condition, revision to the baseline condition of the flight profile to export data by the General Administration of civil aviation of China approved by the manufacturer. (Ii) corresponds to PNLTM, and from the aircraft to the microphone sound propagation path must be on the test and the reference section which determines. PNLTM spectrum of SPL values must be in effect on the following amendments: (a) the variation of the atmospheric absorption (b) as a result of sound propagation path length changes of atmospheric absorption changes; and (c) sound propagation path length changes lead to the inverse-square law amendments.     Amended PNLTM of SPL values are converted to base conditions value and subtract with the original PNLTM, by representatives of the poor must be added to in algebra EPNL values calculated from the measured data of the correction. (Iii) measurement of noise measuring stations, measured distance PNLTM and reference PNLTM from different, so you must calculate the correction coefficient ratios used to determine the duration of the noise.     The effective perceived noise level (EPNL) up to the maximum tone correction noise level (PNLTM) and algebra and correction factor to determine the duration.     (Iv) aircraft flying over, alternate sources of noise correction required by the Civil Aviation Administration of China approved and must be determined and amended, to solve the measurement test conditions and changes in baseline noise level due to the differences in terms of.     (B) take off sections (1) H1 gives a typical takeoff profile, including the baseline conditions.     (I) benchmarks take off track in the section H36.3 (c) provisions.     (Ii) each test parameter is a helicopter performance, weight and atmospheric conditions such as temperature, air pressure, wind speed and direction function.     (2) really took off, the helicopter is in level flight, height is from flight-track noise measuring 20 meters above the ground (65 feet), and Vy ± 9-kilometer/h (± 5) minimum climb speed after take off or approval, whichever is greater, to c. (Editor's Note: graphics here see original) took off and benchmark profiles measured figure H1 (3) figure H1 gives a geometric relationships can affect sound propagation. L is for a station to PNLTM, the helicopter took off on a measured position on the track, while Lr is the corresponding location on the path of sound propagation in the baseline.     AL and ALr angle θ with the respective track. (C) level over the profile (1) noise is given in Figure H2 type certification over the section. Air speed must be stabilized in the section H36.3 (d) gives the reference airspeed ± 9-kilometer/h (± 5) range.     Wind levels over the flight number should be over with the wind level flight times are equal. (Editor's Note: this graphic originals) and benchmark profiles across the measured figure H2 (2) when the test conditions are given in Figure H2 does not meet the required benchmark comparison of conditions across the section. Helicopters must be recorded on the DJ of a sufficiently long position, to ensure less than 10dB compared PNLTM's record of helicopter noise across the time. Flying over the profiles determined by the height of AG and AG is a function of operating parameters controlled by the pilot.     Point m is measured by a station to observe the PNLTM helicopter in position on the track, Mr is the benchmark on track corresponds to the position of the point.     (D) entry profile (1) typical approach is given in Figure H3 section, including the baseline conditions. (2) in the entire 10dB reduction period, helicopters along the 6 ° (± 0.5 °), average of two slopes, close to the h position.     Deviation from the average of 6 ° approach slope in front of the test must be approved by the Civil Aviation Administration of China. (Editor's Note: graphics here see original) H3 and benchmark approach profile measurements of (3) the measure is given in the figure H3 part of the approach track and benchmark, including the main geometric relationships can affect sound propagation. Entry reference tracks by EK and approach allows for measurement of angle theta. Er, and Kr, defined approach angle of 6 °-ideal base position. N was observed at a station at the PNLTM measured by helicopter into position on the track. Nr is the corresponding base into position on the track.     Measurements and the baseline noise propagation path is AN and ANr, all of them with individual tracks into the same angle θ APP, corresponds to the approach tracks of their respective PNLTM.     (E) the source noise levels over the amendments (1) level across, if any combination of the following three situations (I) airspeed deviation from the reference value.     (Ii) rotor speed deviation from the reference value.     (Iii) the temperature deviation from the reference value.     Lead and noise related parameters values and the reference values deviate from, the source noise adjustments must be based on data provided by the General Administration of civil aviation of China approved by the manufacturer to determine. (2) the deviation from the Datum blade tip Mach number correction, must according to the base near several different airspeed the airspeed over the test the results of PNLTM on the sensitivity curve of the wing-tip Mach number to determine. Helicopters unable to reach the benchmark to test values, as long as the data cover at least 0.03 Mach range will allow extrapolation to the sensitivity curve. Blade tip Mach number calculate forward must use true airspeed, aircraft measurements of external air temperatures and rotor speed. Must be on each of the three certification microphone locations, namely, left, in the middle line and exported, its forward line on the right side of blade tip Mach number-relationship with PNLTM. Left and right line is relative to the direction of each flight.     Must use the appropriate PNLTM for PNLTM relationship for each microphone data correction.     (F) PNLT amendment if measurement of atmosphere conditions of temperature and relative humidity and this annex by provides of benchmark conditions (25 ℃ (77 ° f), 70%) different, is must according to this section (a) from measuring have of data calculation on EPNL value of amendment following: (1) took off track on figure H1 to out of took off track, will in a, station observation to of aircraft in l Shi of PNLTM of spectrum decomposition into single of SPL (I) of value. (I) step 1: a set of correction calculated by the following formula: where: SPL (I) and SPL (I) r is measured separately and adjusted in the I-th one-third octave sound pressure level. The first amendment Amendment to the variation of the atmospheric absorption, a (I) and (I) o are the test and reference atmospheric conditions when I a one-third octave sound attenuation coefficient, AL is to measure sound propagation paths of departure. In imperial units, the conversion factor constant c is 0.001 to 0.01 in metric units. Second amendment is due to the different sound path length and the correction of atmospheric absorption, ALr basis taking off sound propagation paths.     Third amendment is taken on sound propagation path length difference of the inverse square law amendments.     (Ii) step 2: SPL, as amended (I) r PNLT value converted to reference conditions, a revision of items obtained by the following formula: this correction will be algebra and added to the measured data in the form of EPNL values calculated on a fixed value.     (2) horizontal track over (I) of this section (f) (1) amendment to take off track as described in procedure also applies to the level of flying over the track, only this time with H2 level in sound propagation paths across the SPL (I) r values are as follows: here AM, AMr is measured separately and reference level over the sound propagation paths.     (Ii) after flying over the conditions of the program and this section (f) (1) (ii) about take off track in the program.     (3) enter the track (I) of this section (f) (1) take off track, as described in the amendment procedure applies also to the approach track, only this time associated with the approaching sound propagation paths in the H3 SPL (I) r values are as follows: here AN, ANr is measured separately and benchmarks comes into play over the sound propagation paths.     (Ii) the entry conditions following the procedures in this section (f) (1) (ii) about take off track in the program.     (4) sideline microphone (I) sideline microphone in this section (f) (1) in the on took off track provides of program also applies Yu spread to sideline location of noise, and SPL (I) r of value and figure H3 in the measuring have of sideline sound spread path about, that: on took off: X=L, and Xr=Lr on flew over the: X=M, and Xr=Mr on entry: X=N, and Xr=Nr (ii) zhihou of sideline track program and this section (f) (1) (ii) in the about took off track of program as. (G) duration of revision (1) if the takeoff and approach for measuring track respectively, and in accordance with section A36.5 (d) (2) as amended and benchmark tracking is not the same as is necessary for measurement data to calculate the duration fixed EPNL values.    This amendment must be calculated according to the following: (I) take off track to take off track as shown in Figure H1, correction of calculations derived from the following formula: This modification must be in the form of algebra into EPNL on calculated from the measured data. Length ALr and AL, respectively from the noise measurement stations a measured to track and benchmark measurement distance take off track and benchmark takeoff distance.     Minus sign indicates that the specific duration of the amended, if you measure the height of track than the amended track, EPNL values calculated from measured data must be decreased.     (Ii) horizontal track over on level track over, correction of calculations derived from the following formula: AM here is from the measurement of noise measuring stations a measured over the track distance, AMr will noise measurement points a to the base flying over the baseline distance of the track.     (Iii) approach flight path for the approach shown in Figure H3 track correction need to be calculated from the equation: here AN be approaching from the noise measurement stations a measured track measure distance, ANr is from noise measuring stations a benchmark approach track baseline distance. (Iv) sideline microphone on sideline flight track, amendment items following calculation: here s is based on flight conditions of sideline measurement station, helicopter of location x and Xr corresponds to Yu: on took off: X=L, and Xr=Lr on entry: X=M, and Xr=Mr on flew over the: X=N, and Xr=Nr (2) must on took off, flew over the and entry of sideline microphone by this section in the by said of program amendment. Despite the noise vary, dependent on helicopter models of radiation directivity patterns, but to test and benchmark tracking, spread angle θ must be the same. Elevation angle ψ shall not be bound by it, but you must determine and submit it. Civil Aviation Administration of China will provide angle ψ acceptable limits.     When these limits are exceeded the data correction, you must use the methods approved by the Civil Aviation Administration of China.     D pursuant to article H36.301 section 36.805 noise limits noise measurement, assessment and calculations must be based on the annex, part b and part c for measurement of noise levels, assessing and calculating, to demonstrate compliance to the provisions of part d of the annex. Subsection H36.303 article (alternate) subsection H36.305 article noise level (a) limit for meet this annex, must through flight test showed that, calculation get of helicopter in this annex of subsection H36.305 article (a) in the provides of measurement points Shang of noise level not over following value, different weight between of numerical with within push method get: (1) first stage helicopter acoustic change of noise limit: (I) for took off, and flew over the and entry of calculation get of noise level,     Where the noise limits on noise levels over the second stage 2EPNdB the first phase of the helicopter, shall not exceed the model after model design changes before the design change, noise level.     (Ii) for takeoff and overflight and calculated from the approaching noise levels, noise limits on where the noise level does not exceed the second stage 2EPNdB the first phase of the helicopter, shall not exceed the second phase after the design change noise restrictions and 2EPNdB. (2) the second phase noise limits are as follows: (I) take off maximum takeoff weights greater than or equal to 80000 kg (176370 pounds) at 109EPNdB.     Halve the weight of each noise level reduction 3.01EPNdB, up to 89EPNdB, and then limit the constant. (Ii) over the maximum takeoff weight greater than or equal to 80000 kg (176370 pounds), is 108EPNdB.     Halve the weight of each noise level reduction 3.01EPNdB, up to 88EPNdB, and then limit the constant. (Iii) to approach the maximum takeoff weight greater than or equal to 80000 kg (176370 pound), 110EPNdB.     Halve the weight of each noise level reduction 3.01EPNdB, up to 90EPNdB, and then limit the constant.     (B) integrated evaluation except according to this provides subsection H36.11 article (b) of limit range yiwai, in following situation Xia, according to subsection H36.203 article determine of calculation get of took off, flew over the or entry noise level in the of a or two a can over this section (a) by provides of limit: (1) over volume of and is unlikely to Yu 4EPNdB; (2) any a over volume not is greater than 3EPNdB; (3) all over volume completely was other by needed of calculated of noise level of reduced volume by offset. (April 15, 2007, the first amendment) Annex I (alternate) Annex j maximum authorized takeoff weight not more than 3175 kg (7,000 pound) helicopter based on h helicopter noise alternative certification program a part of baseline conditions section J36.1 section J36.5 article J36.3 of the General benchmark test conditions (standby) part b under section 36.801 noise J36.101 noise     Certification test and measurement conditions section J36.103 (backup) section J36.107 section J36.105 flew over the test condition (backup) section J36.109 in the helicopter received ground noise measurement submission requirements section J36.113 section J36.111 (standby) 36.803 noise assessment and calculation of the part c in accordance with article J36.20l in SELdB of noise evaluation Section J36.203 noise level calculation section J36.205 detailed data correction procedures in accordance with part d 36.805 noise limits J36.301 of noise measurement, assessment and calculation of section J36.303 (backup) section J36.305 section J36.1 of noise levels on a part of the baseline condition identified in section 36.1 of the General provisions of this annex and the provisions of chapter h of the maximum authorized takeoff Weight not is greater than 3175 kg (7,000 pounds) of primary class, and normal class, and transport class and limited with class helicopter alternative of noise validation requirements, including: (a) implementation according to h chapter of helicopter alternative of noise validation test by must followed of conditions and in test process in the according to subsection 36.801 article measurement helicopter noise must using of alternative of noise measurement program; (b) according to subsection 36.803 article will measuring have of data amendment to benchmark conditions by must using of alternative program and calculation to sound exposed level (     SEL) alternative procedures for noise assessment; (c) must be indicated under section 36.805 meet noise restrictions. Subsection J36.3 article benchmark test conditions (a) atmosphere conditions must amendment to following of noise qualified validation benchmark atmosphere conditions, that assumes that this conditions exists Yu ground to aircraft of height location; (1) sea level pressure 76 cm mercury column (2116 pounds each sq ft) (2) environment temperature for 25 ℃ (77 ° f) (3) relative humidity for 70% (4) no wind (b) benchmark test field benchmark test field for flat of, and in a, weighted time course of 10dB drop the points zainei of track of sight above didn't     For obstructions. (C) levels over baseline profile flew over the base profile for noise measuring 150 meters above the ground level (492-foot) level flight. Base flew over the track sections with straight, fly directly over the noise monitoring stations. The airspeed stabilizes at 0.9VH;0.9VNE;0.45VH+120 kph (0.45VH+65); or 0.45VNE+120 kilometers per hour (0.45VNE+65), four small, and flew over the measurement period to maintain this speed.     Throughout the 10dB reduction period on rotor stability at the maximum normal operating RPM. (1) for noise certification, VH is defined as in the largest certification on the weight, pressure at sea level is 1,013.2,500 PA (2,116 pounds per square foot), 25 ℃ environment available engine power corresponds to the maximum continuous power minimum norms obtained Flight airspeed.     Noise certification of VH and VNE values must be listed in the flight manual.     (2) the VNE is not beyond speed.     (D) the weight of the helicopter noise certification shall be the maximum takeoff weight.     Section J36.5 (standby) part b under section 36.801 noise J36.101 noise certification test and measurement conditions (a) general framework this section provides for implementation must meet the noise certification test conditions and test must be used for each measurement of helicopter noise measurement procedures.     (B) test site requirements (1) in each of noise measuring stations around the ground should not have excessive sound absorption characteristics, such as dense grasses, shrubs or trees caused by. (2) over noise measurements at maximum sound level a 10dB reduction within the period, the helicopter's noise measuring stations (on the ground directly below the microphone), cone-shaped space shall not have the effect of aircraft noise barriers exist.     This cone-shaped space is defined as 80 ° to the axis perpendicular to the ground half cone angle of space. (C) meteorological limits test must be conducted in the following atmospheric conditions: (1) no rain or other precipitation (2) 2 ℃-35 ℃ environment temperature (36 ° F-95 ° f) (inclusive), and the relative humidity is 20%-95% (inclusive).     Test site within the relative humidity and ambient temperature conditions should be 8kHz one-third octave on the atmospheric sound absorption is less than 10dB/100 meters (30.5dB/1000 feet). (3) wind speed is not more than 19-kilometer/hour (10 knots) and cross-wind component does not exceed 9-kilometer/HR (5).     Measure wind speed must be less than 30 seconds with continuous average method. (4) the temperature, relative humidity, wind speed and direction measurements must be 1.2 m above the ground (4 ft) to 10 m (33 ft) high region between measurements.     Unless approved by the General Administration of civil aviation of China, or temperature and relative humidity measurements must be carried out on the same height above the ground.     (5) in noise measuring stations recorded noise, no significant effects of helicopter acoustic pressure level and irregular wind (including turbulence) or other abnormal weather conditions.     (6) if the measuring point at a fixed station 2000 m (6560 ft) range (for example can be found at the airport or other facilities), and approved by the Civil Aviation Administration of China, you can use the weather measurement reports on temperature, relative humidity and wind speed.     (D) test procedures for helicopters (1) test procedures and measurement of noise emitted by helicopter, must be able to annex to the present regulations section J36.109 (b) as set out in the sound exposure level (SEL) noise evaluation method of measurement and processing.    (2) must be approved by the Civil Aviation Administration of China and has nothing to do with normal flight instrument approach, such as radar tracking, theodolite triangulation laser technology for tracing or camera location, determine the height of the aircraft relative to the noise measurement points, and enough J36.205 of these rules require amendments. (3) if the applicant demonstrates a helicopter design features in this benchmark test carried out under the conditions provided for in annex J36.3, approved by the Civil Aviation Administration of China, this annex reference test conditions can be changed to standard test conditions, but unable to meet benchmarks required by design features only the range of test conditions.     Section J36.103 (backup) section J36.105 flew over the test conditions (a) the provisions of this section flight test conditions and allowed for the test carried out according to this annex over the noise of random deviations. (B) a set of tests must be made up of at least six flights.     Downwind component levels over the flight number with the headwind component level equal to the number of flights across the.     (1) in level flight and cruise flight; (2) from the noise measurement station above 150 ± 15 m (492 ± 50 feet) altitude, and (3) at the measuring station is within the range of ± 10 ° above.     (C) over the noise test must be conducted as follows: (1) in article J36.3 of this annex (c) provides the reference airspeed flight, which may make the necessary adjustments to related benchmarks and test conditions the same for ahead of the blade tip Mach number. (I) forward of paddle pointed Mach number (MAT) defined for wing leaves leaves pointed rotating speed (VR) and helicopter vacuum speed (VT) of arithmetic and divided by 25 ℃ (77 ° f) Shi of Sonic (c) (1135.6 feet/seconds or 346.13 m/s), that MAT= (VR+VT)/c; and (ii) empty speed not should deviated from adjustment had of benchmark empty speed of ± 5-kilometer/hours (± 3 section), or by China Civil Aviation General approved of equivalent of deviated from benchmark of forward of paddle pointed Mach number.     Throughout over the measurement period adjustments should maintain the reference airspeed.     (2) rotor speed RPM speed stability at the maximum normal operating power (± 1%); and (3) when the helicopter's noise level measured by the maximum sound level a 10dB (LAMAX) within the period of time, the power must be stable.     (D) the certification required by this provision, each weight must be in a helicopter to fly the test the maximum takeoff weight of + 5% to-10%.     (E) despite has this article (b) (2) of provides, but if in test field of environment noise by this annex subsection J36.109 article provides of requirements and in this annex subsection J36.109 article provides of noise measurement station measuring have of helicopter of maximum a, sound level noise in 15dB within, so can using China Civil Aviation General approved of lower height flew over the, and with China Civil Aviation General approved of method will results adjustment to benchmark measurement points.     Section J36.107 (backup) section J36.109 in the noise of the helicopter received ground measurements (a) General (1) for noise certification purposes in accordance with this annex and helicopter noise measurement must be conducted by the General Administration of civil aviation of China approved the acoustic equipment and measurement methods. (2) in this section (b) clear and defined the specification for measuring noise evaluation of the requirements of this annex. In this section, (c) and (d) requirements are laid down in the acoustic equipment.     (E) and (f) provide calibration and measurement procedures required by this annex.     (B) noise unit definitions (1) sound exposure level (SEL, or recorded as LAE) is defined to be at a given time, or event "a" weighted sound pressure (PA) of the square of the time integral, in dB units, its 20 μPa standard reference sound pressure (P0) square of the benchmark time of one second as a benchmark.     (2) the units defined by the following: (Editor's Note: this formula see manuscript) T0 benchmark score for a second time (t2-t1) for the integration time interval.     (3) paragraph (b) (2) the integral equation can be written as follows: (Editor's Note: this formula see manuscript)-LA (t) is the a-weighted sound pressure level of the variable.     (4) the use, integration time (t2-t1) shall be not less than the time interval for, LA (t) first reaches its maximum value (LAMAX) 10dB and continually to less than the maximum value of 10dB.     (5) the SEL can be approximated by type: type a time tolerance, given by the following formula: t = (t2-t1)/2,LAMAX definition to the standard reference sound pressure (P0) the square as the base of the a-weighted sound pressure (slow performance) maximum value in dB units.     (C) measuring system AMS must be approved by the Civil Aviation Administration of China and equivalent to the following equipment: (1) system and frequency response of the microphone, and with this section (d), the measurement and analysis of the accuracy of the system is compatible.     (2) a tripod or similar microphone installation device for the measurement of sound energy interference should be kept to the minimum.     (3) recording and playback equipment, its frequency response and dynamic range properties should be linked to this section (d) required in the response is consistent with precision.     (4) calibration and checking of the measuring system must be used in A36.3.9 procedures. (D) measurement, recording and playback devices (1) measure the helicopters flew over the noise integrating sound level meter can directly use, or time history written in the a-weighted sound level is set to "slow" response graphic sound level recorder, SEL values can be determined from it.     Approved by the Civil Aviation Administration of China, can use a tape recorder, recorded noise signals for later analysis.     (I) each test across the SEL values can be directly obtained by integrating sound level meter, sound level meter meeting the International Electrotechnical Commission standard publications, No. 804, entitled "score average sound level meters" (referred to by article 36.6 of this provision), the model 1 is set to "slow" response. (Ii) helicopter acoustic signals, and this section (e) calibration signal, this section provided (f) provides the background noise signal recorded on the tape recorder, later in this section (d) (1) (I) provides analysis of integrating sound level meter. Tape recorder record/replay system (including tape) must meet the requirements of this provision A36.3.6.     Tape recorder must satisfy IEC Publication No. 561, "electro-acoustic measuring instruments for aircraft certification" section 36.6 of the provided references.     (Iii) the entire system must be with the IEC Publication No. 651 "sound level meters" recommended consistent characteristics (referred to by article 36.6 of this provision), the file is given on the microphone, amplifier, and indicating instruments characteristic of norms.     (Iv) for 45Hz to 11500HzA weighting curves, the whole system's response relative to sensitive sites such as plane waves in IEC Publication No. 651 "sound level meters" table and type 1 instrument within the error limits specified in table v, which has been referred to by article 36.6 of this provision. (V) each time the helicopter flew over the wind noise measurement microphones must cover.     Windshield must be causing the attenuation as a function of frequency in accordance with this section (e) requires the acoustic calibration correction of the measured data, every amendment must provide reports.     (E) calibration (1) If a helicopter acoustic signal is with a tape recorder for later analysis, measurement systems and system components must be according to the provisions in annex a of regulation of A36.3.6 calibrations.     (2) If a helicopter acoustic signal is a direct integral of sound level meter, then: (I) flew over during the test and measurement all the sensitivity of the system should be in series across the test before and after and the middle (no more than one hour) in known bands known sound pressure level sine wave noise acoustic calibration checks. (Ii) at the trial every day, if the calibration value of less than 0.5dB, then the device will be considered to be satisfied with the performance of the system.     Flying over the SEL collected test data included in the calibration values will be adjusted for any changes. (Iii) each calibration equipment including acoustic calibrator, the base microphone and performance analysis of calibration voltage insert device must be in a helicopter flying over the start of the six-months to complete.     Each calibration shall date back to the Agency authorised by the Civil Aviation Administration of China. (F) noise measurement procedure (1) microphone must be pressure-sensitive capacitive type, designed to be almost the same angle of incidence response.     Microphone should be installed in the Center above the surface of the sensing element 1.2 meters (4 feet) and facing into the ray makes sensors, diaphragm, largely on behalf of the helicopter flight path noise measuring stations in the plane defined by the.     (2) If you are using a tape recorder, and during the trial, using pseudo random noise or pink check, all reading must be determined for the power system frequency response range in 10dB. (3) ambient noise, including the acoustic background noise and measurement system noise should be determined at the test site, and the system gain should be set in a helicopter used for noise measurement of sound levels.     If a helicopter sound level no more than background noise of 15dB (a) flying over in the General Administration of civil aviation of China approved to lower heights, test results with the General Administration of civil aviation of China approved methods to adjust to baseline measurement points. (4) if the helicopter noise measurement by integrating sound level meter, the operator should monitor the entire process across the a-weighted (slow response) noise levels to ensure SEL integral process includes the maximum a-weighted sound level (LAMAX) and 10dB points over the course of time between all the noise.     The operator shall record the SEL integral start and end at the time of the actual sound pressure level dB (a), and the sound level (LAMAX) noise data points and get the value of time (in seconds) according to article J36.111 of this annex (b) requirement as part of the report submitted. Submission requirements under article J36.111 (a) general framework represents the physical measurements of data or correction of the measured data, including the device response deviation correction made to the measurement results must be recorded in a permanent way, and attached to the record.     Each amendment must be submitted to the approval of the Civil Aviation Administration of China.     (B) the data submitted upon completion of the test the test report must include the following data submitted to the Civil Aviation Administration of China: (1) and in article J36.109 of this Annex provided that conforms to the standard equipment of the measured sound pressure level and amendments.     (2) equipment for all acoustic measurement and analysis models, as well as aircraft performance, flight path, and meteorological data.     (3) measured in the whole process, in order to verify conformity to requirements of this annex, the atmospheric environment data.     (4) the local topography, floor coverings, as well as those events that can affect the sound recording.     (5) the helicopter the following information: (I) and rotary-wing helicopters, engine model, type and serial number (if any).     (Ii) total size of helicopter and engine and the position of the rotor, rotor blades, anti torque system models, engines and rotary-wing reference operating conditions.     (Iii) the possible effects of helicopter noise characteristics of non-standard equipment of any changes.    (Iv) maximum takeoff weight accredited according to the requirements of this annex. (V) the form of aircraft, including the position of the landing gear.     (Vi) VH and VNE airspeed (small) and the revised benchmarks airspeed.     (VII) each test flight of the aircraft gross weight.     (VIII) each test flight for the indicated airspeed and true airspeed.     (IX) each test flight speed, if measured.     (X) by aircraft instrumentation and data determined by the helicopter manufacturer and engine performance.     (XI) the helicopter's flight path (relative to the height of the land), stands as a benchmark to assess the noise measurement (in metre), the track must be approved by the Civil Aviation Administration of China has nothing to do with normal flight instrument set, such as radar tracking, theodolite triangulation, laser positioning, camera positioning technology.     (6) the helicopter position and performance data in accordance with the provisions of section J36.205 amended, the sampling rate must be approved by the Civil Aviation Administration of China record demonstrates compliance of article J36.105 of the rules of property and location restrictions. Section J36.113 (spare) parts under 36.803 noise assessment and calculation of J36.201 in SELdB noise evaluation of article J36.109 of this annex must be used (b) provisions are given in dB (a) sound exposure level (SEL) noise assessment measurement. Flying over the SEL values can be determined directly by integrating sound level meter.     Integrating sound level meter specification and management requirements for these instruments, see article J36.109 of this annex. Section J36.203 the calculation of noise (a) to verify compliance with article J36.305 of this annex the noise level limits, effective over SEL noise levels, according to article J36.205 of this annex after revision to the baseline condition, flew over the arithmetic mean of the series Gets a SELdB must be (a) average.     Unless there is a requirement or approval of the Civil Aviation Administration of China, and may not be canceled during a flying over on the average flight. (B) helicopters overflew the audited minimum number of samples measure acceptable is 6 times.     Minimum number of samples must be large enough so that no more than 1.5dB (a) established in the context of statistical confidence 90%.     (C) all data used and calculations made according to the requirements of this article, including the 90% calculation of confidence must be written and submitted to the reporting requirements of article J36.111 of this annex. Section J36.205 detailed data correction procedures (a) if the certification test conditions for the measurement of annex b does not meet the baseline conditions stipulated in article J36.3 of this annex, must be in accordance with this section (b) (c) provides methods to measure noise data for proper adjustment.     At least, high deviations from baseline conditions and benchmarks for speed and adjust the difference between the reference airspeed must make appropriate adjustments.     (B) on deviated from benchmark height adjustment can approximate said for: type in the J1 is to dB for units of volume value, must to generation numerical added to measuring have of SEL noise value Shang to Amendment deviated from benchmark flight track, HT is helicopter directly flew noise measurement points of test height, to meters for units, constants 12.5 for meter and the spherical spread of effect and deviated from benchmark height of continued time of effect.     (C) benchmark empty speed and benchmark adjustment empty speed Zhijian of difference of adjustment by Xia type calculation get: type in the J3 is to dB for units of volume value, must to generation numerical added to measurement of SEL noise level to amendment in noise measurement station accept to of flew over the measurement during benchmark empty speed adjustment of effect, VR is this annex subsection J36.3 article (c) provides of benchmark empty speed, VRA is this annex subsection J36.105 article (c) provides of adjustment benchmark empty speed.     (D) subject to article J36.105 of this annex (c) prescribed airspeed adjustments into account as reference noise changes, over having to source noise during revision.     (E) do not have to base ground speed and the actual speed made the difference.     (F) No atmospheric attenuation correction of deviations from baseline conditions.     (G) according to article J36.105 of this annex provides adjustments to the SEL test and benchmark flight procedures must be less than the difference between the 2.0dB (a), unless a greater degree of adjustment is worth to the approval of the Civil Aviation Administration of China.     (H) all data used and calculations made pursuant to this section must be documented and submitted reporting requirements under article J36.111 of this annex.     D pursuant to article J36.301 section 36.805 noise limits noise measurement, assessment and calculations must be based on the annex, part b and part c for measurement of noise levels, assessing and calculating, to demonstrate compliance to the provisions of part d of the annex. Subsection J36.303 article (alternate) subsection J36.305 article noise limit for meet this annex, calculation get of helicopter in this annex subsection J36.101 article provides of measurement points Shang noise level must not over following value (different weight between of numerical with within push method): (a) on primary class, and normal class, and transport class and limited with class has maximum validation took off weight not over 3175 kg (7000 pounds) and by this annex for noise test of helicopter, in maximum validation took off weight Xia, Phase noise limiting relative to 788 kg (1737 lbs) 82dB (SEL), 1 time for each additional weight added to 3.0dB.     This restriction can be expressed by the following equation: according to the validation requirements of this annex, MTOW maximum take off weight, in kilograms.     (B) the procedures required by this annex shall be governed by the International Electrotechnical Commission IEC Publication No. 804, titled "score average sound level meters" (1985 version).    (April 15, 2007, the first amendment)