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Doc 9501, Volume I Second Edition Corrigendum No. 1 English only 22/4/15 ENVIRONMENTAL TECHNICAL MANUAL CORRIGENDUM No. 1 1. Please replace existing pages 2-1, 2-2, 4-15, 4-80, 4-97, 4-101, 4-104, 4-105, 4-109 and Index-i by the attached new pages bearing the notation Corr. 1, dated 22/4/15. 2. Record the entry of this corrigendum on page iii of the manual.
2-1 Chapter 2 GENERAL GUIDELINES 2.1 APPLICABILITY OF CURRENT AND PREVIOUS AMENDMENTS TO ANNEX 16, VOLUME I Since the publication of the first edition of Annex 16 many amendments and new editions have been published. Each amendment and new edition retains the older chapters e.g. Chapter 2, even though they may no longer be applicable to new types of aircraft. Since each new amendment or edition succeeds the previous version, the applicability provisions of each chapter are in principle retained, thus preserving their continuity. The first section of Chapters 2, 3, 4, 5, 6, 8, 10, 11 and 12 of the Annex, together with the paragraphs concerning applicability in Chapter 1 of the Annex, define the applicability of each chapter. Their applicability to new types is determined by the date the application for the Type Certificate was submitted to the State of Design. In many instances the chapter and maximum noise levels so determined for a new type are also applicable to its derived versions e.g. the applicability provisions of Chapter 3 refer to all aeroplanes, including their derived versions. In some cases the applicability provisions apply only to derived versions e.g. Chapter 8, 8.1.3. In these cases the applicability provisions are determined by the date the application for certification of the change in type design was submitted to the certificating authority of the Contracting State that first certificated the change in type design. Note. The applicability provisions for derived versions are not dependent on how the associated change, or changes, in type design came about e.g. amended Type Certificate or Supplemental Type Certificate. The authority of the State of Design or, in the case of derived versions, the original certificating authority, should ensure that the demonstration of compliance is in accordance with the procedures and recommended practices that are described in the amendment to Annex 16 that is applicable at the date of submittal for either the Type Certificate or approval of the change in type design as required by Chapter 1, 1.10 through 1.13. Note. Changes to test procedures and evaluation methods are usually approved by the Committee on Aviation Environmental Protection CAEP on the basis that they are stringency neutral. The question arises as to the status of these approvals as each new amendment to the Annex is published. a For the authority of the State of Design in the case of new types, or the original certificating authority in the case of derived versions, the approved certification noise levels corresponding to the amendment to the Annex and revision of this manual that were applicable at the time the application for approval was submitted remain valid and should not be reassessed against any changes made in later amendments or revisions. b Many applications for a Type Certificate or for approval of a change in type design are submitted to authorities other than that of the State of Design or original certificating authority. Often these applications are submitted several years after their submittal to the first certificating authority. During this period many new amendments to the Annex and corresponding revisions of this manual may have been published. In the case of an application for a Type Certificate or an application for the 22/4/15 Corr. 1
2-2 Environmental Technical Manual approval of a change in type design, the applicable Standards are determined according to the provisions of Chapter 1 of the Annex. For an authority to whom these later submittals are made, the acceptable means of compliance, technical procedures and equivalent procedures would be those described in the amendment to the Annex and the version of this manual that are applicable at the time the applications are submitted to this authority. The applicability provisions of each chapter do not change over time. However the reference and test procedures and the evaluation methods defined in the appendices do, on occasion, change with each new amendment or edition. An applicant may propose, with supporting justification, to the certificating authority to accept the means of compliance and demonstration procedures described in earlier amendments to Annex 16 and equivalent procedures described in earlier versions of this manual on the basis that they are equivalent to the currently applicable ones. Note. Bilateral arrangements between Contracting States will facilitate the mutual recognition by other certificating authorities of approvals granted by certificating authorities of the State of Design. 2.2 CHANGES TO AIRCRAFT TYPE DESIGNS INVOLVING DERIVED VERSIONS Many of the equivalent procedures given in this manual relate to derived versions where the procedure used yields the information needed to obtain the certification noise levels of the derived versions by adjusting the noise levels of the flight datum aircraft i.e. the most appropriate aircraft for which the noise levels were measured during an approved flight test demonstration. The physical differences between the flight datum aircraft and the derived version can take many forms, such as an increased take-off mass, an increased engine thrust, changes to the powerplant or propeller or rotor types, etc. Some of these differences will alter the distance between the aircraft and the noise certification reference points, others the noise source characteristics. Procedures used in the determination of the certification noise levels of the derived versions will therefore depend upon the change to the aircraft being considered. However, where several similar changes are being made, such as the introduction of engines from different manufacturers, the procedures used to obtain the certification noise levels of each derivative aircraft should be followed in identical fashion. 2.3 CHANGES TO AIRCRAFT TYPE DESIGNS INVOLVING NO-ACOUSTICAL CHANGES Aircraft/engine model design changes and airframe/engine performance changes may result in very small changes in aircraft certification noise levels that are not acoustically significant. These changes are referred to as no-acoustical changes NACs. For this manual NACs, which do not result in modification of an aircrafts certification noise levels, are defined as a changes in aeroplane certification noise levels approved by the certificating authority which do not exceed 0.10 dB at any noise measurement point and which an applicant does not track b cumulative changes in aeroplane certification noise levels approved by the certificating authority whose sum is greater than 0.10 dB but not more than 0.30 dB at any noise measurement point and for which an applicant has an approved tracking procedure c for helicopters certificated according to the Standards of Chapter 8 of the Annex, changes in any one of the certification noise levels approved by the certificating authority which do not exceed 0.30 EPNdB and 22/4/15 Corr. 1
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Doc 9501. Environmental Technical Manual. Volume I- Procedures for the Noise Certification of AircraftAnnex 16. Vol 3. Edition 1. Environmental Protection. Volume III. Aeroplane CO2 EmissionsDoc 9501. Vol 2. Edition 4. Environmental Technical Manual. Volume II. Procedures for the Emissions Certification of Aircraft EnginesВСЕ ДОКУМЕНТЫALL DOCUMENTSDoc 9501
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