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Agenda Item 3: Review of technical proposals relating to aircraft noise.

 REPORT OF WG1

– NOISE TECHNICAL

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VOLUME I

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Recommendation 3/1

– Amendments to Annex 16

— Environmental Protection 9ROXPH,2 Aircraft Noise

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Recommendation 3/2

– Publication of the Environmental Technical Manual,

Volume I

— Aircraft Noise

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Table 1 - Mid-Term (2020) Cumulative Noise Margin Goals Relative to Chapter 4

Aircraft Category BPR

Goal NR

TRL6 NR TRL8 Cum

Ref Cum

Goal TRL6 Cum

Goal TRL8

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10 9

9 4

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9.5 13±4

8.5±4

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9.5 9

9 3

0.5 12.5

10 12±4

9.5±4
Short Medium Range Twin (SMR2)

Turbofans : 78 tonnes (nominal) 98 tonnes (max)

CROR : 78 tonnes (nominal) 91 tonnes (max) 9±1

9±1

-

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17.5

-

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16

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1.5

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19

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17.5±4

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10±1 16

16 14.5

14.5 6

2.5 22

18.5 20.5±4

17±4
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9±1 17.5

17.5 16

16 5

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16 21±4

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Table 2 - Long-Term (2030) Cumulative Noise Margin Goals Relative to Chapter 4

Discussion and Conclusions

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CROR: 78 tonnes (nominal) 91 tonnes (max) 13±1

13±1

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25

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1.5

5

2 30±4

26.5±4

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 6 -

-

-

- Long Range Twin (LR2) 230 tonnes (nominal) 290 tonnes (max) 13±1

13±1 22

22 -

- 6

2.5 28±4

24.5±4 -

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11±1 22

22 -

- 5

-1.5 27±4

20.5±4 -

-

* CROR cumulative margin with uncertainties range from 7.5 to 15.5 EPNdB for 78 tonne nominal weight aircraft. ** CROR cumulative margin with uncertainties range from 4.5 to 12.5 EPNdB for 91 tonne maximum weight aircraft .&$(3:3

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Margins
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- Aircraft Noise

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APPENDIX A

PROPOSED AMENDMENT TO ANNEX 16, VOLUME I

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TEXT OF PROPOSED AMENDMENT TO THE

INTERNATIONAL STANDARDS AND RECOMMENDED PRACTICES

ENVIRONMENTAL PROTECTION

ANNEX 16

TO THE CONVENTION ON INTERNATIONAL CIVIL AVIATION

VOLUME I

AIRCRAFT NOISE

. . .

FOREWORD

. . .

Applicability

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— Chapters 2 and, 3, 4 and 14 exclude jet aeroplanes having short take-off and landing (STOL) capabilities which, pending the development by ICAO of a suitable definition, are described for the purpose of this Annex as those requiring a runway (w ith no stopway or clearway) of 610 m or less at the maximum certificated mass for airworthiness.

. . .

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PART II. AIRCRAFT NOISE CERTIFICATION

. . .

CHAPTER 1. ADMINISTRATION

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CHAPTER 2.

. . . 2.4 Maximum noise levels

. . .

Note.

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6HH:RUN,WHP1

CHAPTER 3.

1.

— SUBSONIC JET AEROPLANES

— Application for Type Certificate submitted on or after 6 October 1977 and before 1 January 2006

2.

— PROPELLER-DRIVEN AEROPLANES OVER 8 618 kg

— Application for Type Certificate submitted on or after 1 January 1985 and before 1 January 2006 PROPELLER-DRIVEN AEROPLANES OVER 8 618 kg

— Application for Type Certificate submitted on or after 1 January 1985 and before 1 January 2006

. . .

6HH:RUN,WHP1

3.4 Maximum noise levels

. . .

Note.

— See Attachment A for equations for the calculation of maximum permitted noise levels as a function of take-off mass.

. . . CHAPTER 4.



### 1.

— SUBSONIC JET AEROPLANES AND PROPELLER-DRIVEN AEROPLANES

WITH MAXIMUM CERTIFICATED TAKE

- OFF MASS 55 000 kg AND OVER

— Application for Type Ce rtificate submitted on or after 1 January 2006 and

before 31 December 2017

2.

— SUBSONIC JET AEROPLANES WITH MAXIMUM CERTIFICATED TAKEOFF MASS LESS THAN 55 000 kg

— Application for Type Certif icate submitted on or after 1 January 2006 and before

31 December 2020

2.3.

— PROPELLER-DRIVEN AEROPLANES WITH MAXIMUM CERTIFICATED

TAKE -OFF MASS LESS THAN 55 000 kg AND OVER 8 618 kg

— Application for Type Certificate submitted on or after 1 January 2006 and before 31

December 2020

4.1 Applicability

Note.

— See also Chapter 1, 1.10, 1.11, 1.12 and 1.13.

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. . .

CHAPTER 5.

. . .

5.4 Maximum noise levels

. . .

Note.

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CHAPTER 6.

. . .

6.3 Maximum noise levels

. . .

Note 1.

— Where an aeroplane comes within the provisions of Chapter 10, 10.1.2, the limit of 80 dB(A) applies up to 8 618 kg.

Note 2.

— See Attachment A for equations for the calculation of maximum permitted noise levels as a function of take-off mass.

. . .

CHAPTER 8.

. . .

8.4 Maximum noise levels

. . .

Note.

— See Attachment A for equations for the calculation of maximum permitted noise levels as a function of take-off mass.

. . .

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CHAPTER 10.

. . .

10.4 Maximum noise levels

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. . .

CHAPTER 11.

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11.4 Maximum noise level

. . .

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CHAPTER 14

1.

— SUBSONIC JET AEROPLANES AND PROPELLER-DRIVEN AEROPLANES WITH MAXIMUM CERTIFICATED TAKE-OFF MASS 55 000 kg AND OVER

— Application for Type Certificate submit ted on or after 31 December 2017

2.

— SUBSONIC JET AEROPLANES WITH MAXIMUM CERTIFICATED TAKE-OFF MASS LESS THAN 55 000 kg

— Application for Type Certificate submit ted on or after 31 December 2020

3.

— PROPELLER-DRIVEN AEROPLANES WITH MAXIMUM CERTIFICATED TAKE-OFF MASS LESS THAN 55 000 kg AND OVER 8 618 kg

— Application for Type Certificate submitted on or after 31 December 2020

14.1 Applicability

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— See Attachment A for equations for the calculation of maximum permitted noise levels as a function of take-off mass.

14.5 Noise certification reference procedures

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14.6 Test procedures

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14.7 Recertification

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APPENDIX 1.

. . .

2.2 General test conditions

. . .

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APPENDIX 2. EVALUATION METHOD FOR

NOISE CERTIFICATION OF:



### 1.

— SUBSONIC JET AEROPLANES

— Application for Type Certificate submitted on or after 6 October 1977

2.

— PROPELLER-DRIVEN AEROPLANES OVER 8 618 kg

— Application for Type Cert ificate submitted on or after 1 January 1985

3.

— HELICOPTERS

Note.

— See Part II, Chapters 3, 4 and, 8 and 14.

. . .

  Definitions and specifications

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— The definition of this instant in time is required to correlate the recorded noise with the aircraft position when the noise was emitted and ta kes into account the averaging period of the SLOW weighting. For each one-half second data record this instant in time may also be identified as 1.25 seconds after the start of the associated 2 seconds 2-second averaging period.

. . .

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3.8 Calibration systems

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APPENDIX 3.

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2.2 General test conditions

. . .

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APPENDIX 4.

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— The certificating authority may approve the use of calibrators compliant with class 2 of the current IEC standard, or the use of calibrators compliant with class 1 of an earlier standard, if the applicant can show that the calibrator had previously been approved for noise certification use by a certificating authority.

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APPENDIX 6.

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— The certificating authority may approve the use of calibrators compliant with class 2 of the current IEC standard, or the use of calibrators comp liant with class 1 of an earlier standard, if the applicant can show that the calibrator had previously been approved for noise certification use by a certificating authority.

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.

. . .

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ATTACHMENTS TO ANNEX 16, VOLUME I

ATTACHMENT A. EQUATIONS FOR THE CALCULATION OF

MAXIMUM PERMITTED NOISE LEVELS AS A FUNCTION OF TAKE-OFF MASS

Note.

— See Part II, 2.4.1, 2.4.2, 3.4.1, 4.4, 5.4, 6.3, 8.4.1, 8.4.2, 10.4, 11.4.1 and, 11.4.2 and 14.4.1.

. . .

11. CONDITIONS DESCRIBED IN CHAPTER 11, 11.4.2

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ATTACHMENT G. GUIDEL INES FOR THE ADMINISTRATION

OF NOISE CERTIFICATION DOCUMENTATION

. . .

2. NOISE CERTIFICATION DOCUMENTATION

2.1 Information to be provided

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 Item 10. Maximum landing mass and unit for certificates issued under Chapters 2, 3, 4, 5 and, 12

and 14

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NOISE DATA FOR LAND-USE PLANNING PURPOSES

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PROPOSED AMENDMENT OF THE ENVIRONMENTAL TECHNICAL MANUAL (VOL. I)

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TEXT OF PROPOSED AMENDMENT OF THE ENVIRONMENTAL TECHNICAL MANUAL (VOL. I)

FOREWORD

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PROPOSED AMENDMENT TO ANNEX 16, VOLUME I

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TO THE CONVENTION ON INTERNATIONAL CIVIL AVIATION

VOLUME I

AIRCRAFT NOISE

. . .

PART I. DEFINITIONS

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PART II. AIRCRAFT NOISE CERTIFICATION

CHAPTER 1. ADMINISTRATION

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ATTACHMENT F. GUIDEL INES FOR NOISE CERTIFICATION

OF CHAPTER 13. TILT-ROTOR AIRCRAFT

Note.

— See Part II, Chapter 13.

Note 1.

— These guidelines are applicable to heavier-than-air aircraft that can be supported in flight chiefly by the reactions of the air on two or more power-driven rotors on axes which can be changed from substantially vertical to horizontal.

Note 2 1.

— These guidelines Standards are not intended to be used for tilt-rotor aircraft that have one or more configurations that are certificated for airworthiness for STOL only. In such cases, different or additional guidelines procedures /conditions would likely be needed.

1. 13.1 APPLICABILITY

Note.

— See also Chapter 1, 1.10, 1.11, 1.12 and 1.13.

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2. 13.2 NOISE EVALUATION MEASURE

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Note.

— Additional data in SEL and L Amax as defined in Appendix 4, and one-third octave SPLs as defined in Appendix 2 corresponding to L Amax should be made available to the certificating authority for land-use planning purposes

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3. 13.3 NOISE MEASUREMENT REFERENCE POINTS

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4. 13.4 MAXIMUM NOISE LEVELS

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Note 1.

— For the tilt-rotor aircraft in aeroplane mode, there is no maximum noise level.

Note 2.

— VTOL/conversion mode is all approved configurations and flight modes where the design operating rotor speed is that used for hover operations.

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Note.

— The equations for the calculation of noise levels as a function of take-off mass presented in Section 8 7 of Attachment A, for Conditions De scribed in Chapter 8, 8.4.1 are consistent with the maximum noise levels defined in these guidelines 13.4.

5. 13.5 TRADE-OFFS

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6. 13.6 NOISE CERTIFICATION REFERENCE PROCEDURES

13.6.1 General conditions

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13.6.2 Take-off reference procedure

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13.6.3 Overflight reference procedure

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Note.

— For noise certification purposes, V CON is defined as the maximum authorized speed for VTOL/conversion mode at a specific nacelle angle.

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Note 1.

— For noise certification purposes, V MCP is defined as the maximum operating limit airspeed for aeroplane mode corresponding to minimum engine installed, maximum continuous power (MCP) available for sea level pressure (1 013.25 hPa), 25°C (77°F) ambient conditions at the relevant maximum certificated mass; and V MO is the maximum operating (MO) limit airspeed that may not be deliberately

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Note 2.

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13.6.4 Approach reference procedure

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7. 13.7 TEST PROCEDURES

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. . .

APPENDIX 2. EVALUATION METHOD FOR

NOISE CERTIFICATION OF:

1.

— SUBSONIC JET AEROPLANES

— Application for Type Certificate submitted on or after 6 October 1977

2.

— PROPELLER-DRIVEN AEROPLANES OVER 8 618 kg

— Application for Type Certificate submitted on or after 1 January

1985

3.

— HELICOPTERS

4.

— TILT-ROTORS

Note.

— See Part II, Chapters 3, 4 and, 8, 13 and 14.

. . .

ATTACHMENT A. EQUATIONS FOR THE CALCULATION OF

MAXIMUM PERMITTED NOISE LEVELS AS A FUNCTION OF TAKE-OFF MASS

Note.

— See Part II, 2.4.1, 2.4.2, 3.4.1, 4.4, 5.4, 6.3, 8.4.1, 8.4.2, 10.4, 11.4.1 and 11.4.2 ,13.4 and 14.4.1.

. . .

7. CONDITIONS DESCRIBED IN CHAPTER 8, 8.4.1 AND CHAPTER 13, 13.4

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ATTACHMENT F. GUIDELINES FOR NOISE CERTIFICATION

OF TILT-ROTOR AIRCRAFT

Note.

— See Part II, Chapter 13.

[Reserved]

Editorial note.

— Delete  WKH UHPDLQGHU RI

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. . .

ATTACHMENT G. GUIDEL INES FOR THE ADMINISTRATION

OF NOISE CERTIFICATION DOCUMENTATION

Note.

— See Part II, Chapter 1.

. . .

2. NOISE CERTIFICATION DOCUMENTATION

2.1 Information to be provided

. . .

 Item 14. The approach noise level in the corresponding

 unit for documents issued under Chapters 2, 3, 4, 5, 8 and, 12, 13 and 14

7KHDSSURDFKQRLVHOHYHODVGHILQHGLQWKHUHOHYDQWFKDSWHU,W VKRXOGVSHFLI\WKHXQLWHJ(31G%RIWKH QRLVHOHYHODQGWKHQRLVHOHYHOVKRXOGEHVWDWHGWRWKHQHDUHV WWHQWKRIDG%7KLVLWHPLVLQFOXGHGRQO\LQ

WKHQRLVHFHUWLILFDWLRQGRFXPHQWDWLRQIRUDLUFUDIWFHUWLILFDWHG WR&KDSWHUVDQGDQG

. . .

 Item 16. The overflight noise level in th e corresponding unit for documents issued under Chapters 6, 8 and, 11 and 13

7KHRYHUIOLJKWQRLVHOHYHODVGHILQHGLQWKH UHOHYDQWFKDSWHU ,WVKRXOGVSHFLI\WKHXQLW HJ(31G%RU G%$RIWKHQRLVHOHYHODQGWKHQRLVHOHYHOVKRXOGEHVWDWHG WRWKHQHDUHVWWHQWKRIDG%7KLVLWHPLV LQFOXGHGRQO\LQWKH QRLVHFHUWLILFDWLRQGRFXPHQWDWLRQ IRUDLUF UDIWFHUWLILFDWHGWR&KDSWHUVDQG

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Note.

— For tilt-rotor aircraft certificat ed according to Chapter 13 onl y the overflight noise level

established in VTOL/conversion mode need be stated.&$(3:3

$SSHQGL[&WRWKH5HSRUWRQ$JHQGD,WHP &

 Item 17. The take-off noise level in the corres ponding unit for documents issued under Chapters 8 and, 10 and 13

7KH WDNHRII QRLVH OHYHO DV GHILQHG LQ WKH UHOHYDQW FKDSWHU ,W  VKRXOG VSHFLI\ WKH XQLW HJ (31G% RU G%$RIWKHQRLVHOHYHODQGWKHQRLVHOHYHOVKRXOGEHVWDWHG WRWKHQHDUHVWWHQWKRIDG%7KLVLWHPLV LQFOXGHGRQO\LQWKHQRLVHFHUWLILFDWLRQGRFXPHQWDWLRQIRUDLUF UDIWFHUWLILFDWHGWR&KDSWHUVDQGDQG



. . .

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