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

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figures & N.02.04: Nomenclature, symbols and units

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and adjustment to reference conditions 

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Recommendation 3/1 – Amendments to Annex 16 —

Environmental Protection9ROXPH,2Aircraft Noise 

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Recommendation 3/2 – Publication of the Environmental Technical Manual, 

Volume I — Aircraft Noise

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 STATE OF THE ART AND EMERGING ISSUES 

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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 CumRef

Cum

Goal TRL6

Cum

Goal TRL8

Regional Jet (RJ)

40 tonnes (nominal)

50 tonnes (max)

7±1

7±1

10

10

9

9

4

-0.5

14

9.5

13±4

8.5±4

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45 tonnes (nominal)

53 tonnes (max) -

-

9.5

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

-

-

17.5

17.5

-

-

16

16

-

-

5

1.5

-

-

22.5

19

-

-

21±4

17.5±4

-

-

Long Range Twin (LR2)

230 tonnes (nominal)

290 tonnes (max)

10±1

10±1

16

16

14.5

14.5

6

2.5

22

18.5

20.5±4

17±4

Long Range Quad (LR4)

440 tonnes (nominal)

550 tonnes (max)

9±1

9±1

17.5

17.5

16

16

5

-1.5

22.5

16

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14.5±4
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Table 2 - Long-Term (2030) Cumulative Noise Margin Goals Relative to Chapter 4 

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Goal TRL6

Cum

Goal TRL8

Regional Jet (RJ)

40 tonnes (nominal)

50 tonnes (max)

9±1

9±1

17.5

17.5

-

-

4

-0.5

21.5±4

17±4

-

-

Large Turboprops 

45 tonnes (nominal)

53 tonnes (max) -

-

-

-

-

-

-

-

-

-

-

-

Short Medium Range Twin (SMR2)

Turbofans: 78 tonnes (nominal)

 98 tonnes (max)

CROR: 78 tonnes (nominal)

91 tonnes (max)

13±1

13±1

-

-

25

25

8.5

8.5

-

-

-

-

5

1.5

5

2

30±4

26.5±4

* 13.52/6

** 10.52/6

-

-

-

-

Long Range Twin (LR2)

230 tonnes (nominal)

290 tonnes (max)

13±1

13±1

22

22

-

-

6

2.5

28±4

24.5±4

-

-

Long Range Quad (LR4)

440 tonnes (nominal)

550 tonnes (max)

11±1

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 . 
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Estimate (Cumulative 

margin to Chapter 4)

Design and Test 

Margins

190 12.6 EPNdB +2/-6 EPNdB

220 11.0 EPNdB +2/-6 EPNdB

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5633 Recommendation 3/5 — Amendments to Annex 16 —

Environmental Protection, Volume I — Aircraft Noise

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5633 Recommendation 3/8 — Amendment to Annex 16, Volume I 

- 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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Note.— 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 (with no stopway or clearway) of 610 m or less at the 

maximum certificated mass for airworthiness.

. . .

6HH:RUN,WHP1

PART II. AIRCRAFT NOISE CERTIFICATION 

. . .

CHAPTER 1. ADMINISTRATION 

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CHAPTER 2. 

. . .

2.4 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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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 Certificate 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 Certificate 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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function of take-off mass.

. . .

CHAPTER 5. 

. . .

5.4 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 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 

. . .

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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 submitted 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 submitted 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

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

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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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VSHFLILHGLQDEDQGF

. . .

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6HH:RUN,WHP1

APPENDIX 1. 

. . .

2.2 General test conditions 

. . .

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. . .

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&$(3:3

$SSHQGL[$WRWKH5HSRUWRQ$JHQGD,WHP $

. . .

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. . .

6HH:RUN,WHP1

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

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

. . .

  Definitions and specifications

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. . .

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$

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. . .

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H

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. . .

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. . .

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Note.— The definition of this instant in time is required to correlate the recorded noise with the 

aircraft position when the noise was emitted and takes 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. 

. . . 

6HH:RUN,WHP1

3.8 Calibration systems 

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Editorial note.— DeleteSDUDJUDSKLQWRWR

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. . .

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4.2 Perceived noise level 

. . .

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. . .
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4.7 Mathematical formulation of noy tables 

. . .

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. . .

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. . .

6HH:RUN,WHP1

APPENDIX 3. 

. . .

2.2 General test conditions 

. . .

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. . .

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. . .

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. . .

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6HH:RUN,WHP1

APPENDIX 4. 

. . .

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. . .

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NWDQG

. . .

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. . .

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. . .

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Note.— 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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certificating authority.

. . .

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APPENDIX 6.

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4.3 Sensing, recording and reproducing equipment 

. . .

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Note.— The certificating authority may approve the use of calibrators compliant with the class 2 

specifications 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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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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4.4 Noise measurement procedures 

. . .

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Note.— Digital audio recorders typically do not exhibit substantial variation in frequency response 

or level sensitivity, therefore the pink noise testing described in 4.4.3 is not necessary for digital audio 

recorders. Design characteristics for digital audio recorders should be compliant with class 1 

performance specifications of IEC 61672-14 IEC 61672-13. 

. . .

6HH:RUN,WHP1

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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12. CONDITIONS DESCRIBED IN CHAPTER 14, 14.4.1

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Note.— The slope of the limit lines in the lower and higher weight regions are essentially the same. 

The observed minor differences between the coefficients of the equations defining the slopes of the lateral 

and approach lines are a consequence of the limits in Chapter 14, Sections 14.4.1.1 and 14.4.1.3 being 

defined with fixed end points. For all practical purposes the minor differences between the coefficients 

are considered to be insignificant.

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ATTACHMENT C.

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ATTACHMENT E. APPLICABILITY OF ANNEX 16 NOISE CERTIFICATION STANDARDS 

FOR PROPELLER-DRIVEN AEROPLANES1
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ATTACHMENT G. GUIDELINES FOR THE ADMINISTRATION 

OF NOISE CERTIFICATION DOCUMENTATION 

. . .

2. NOISE CERTIFICATION DOCUMENTATION 

2.1 Information to be provided 

. . .

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

and 14

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. . .

Item 13. The lateral/full-power noise level in the corresponding 

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

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Item 14. The approach noise level in the corresponding 

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

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Item 15. The flyover noise level in the corresponding 

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

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ATTACHMENT H. GUIDELINES FOR OBTAINING HELICOPTER 

NOISE DATA FOR LAND-USE PLANNING PURPOSES

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APPENDIX B

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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APPENDIX C 

PROPOSED AMENDMENT TO ANNEX 16, VOLUME I 

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PROPOSED AMENDMENT TO 

ANNEX 16 

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. GUIDELINES 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 LAmax as defined in Appendix 4, and one-third octave SPLs as 

defined in Appendix 2 corresponding to LAmax 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 Described 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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Note.— For noise certification purposes, VCON 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, VMCP 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 VMO is the maximum operating (MO) limit airspeed that may not be deliberately

exceeded. 

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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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. . .
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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. GUIDELINES 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

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. . .

Item 16. The overflight noise level in the corresponding unit for documents issued under 

Chapters 6, 8 and, 11 and 13 

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Note.— For tilt-rotor aircraft certificated according to Chapter 13 only the overflight noise level 

established in VTOL/conversion mode need be stated.
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Item 17. The take-off noise level in the corresponding unit for documents issued under Chapters 

8 and, 10 and 13 

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. . .

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