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APP 6-6
ATTACHMENTS TO ANNEX 16, VOI,UME I
ATTACHMENT A. EQUATIONS FOR THE CALCULATION OF
NOISE LEVELS AS A FUNCTION OF TAKE-OFF MASS
Note.- See Part 11, 2.4.1, 2.4.2, 3,4,l, 4.4, 5.4. 6.3, 8.4.1, 8.4.2, 104. 11.4.1 and 11.4.2.
1. CONDITIONS DESCRIBED IN CHAPTER 2,2.4.1
M = Maximum take-off
mass ~n 1 000 ka C 34
Late1111 noise level (EPNdB) 1 102 1 91.83 + 6.64 log M LO8
2. CONDITIONS DESCRIBED IN CHAPTER 5 2.4.2
Approach noise level (EPNdB)
Flyover noise level (EPNdB)
M = Maximum take-off
mass in 1 000 kg 0 34 35 4R.3 66.72 133.45 280 325 400
Lateral noise Level (EPNdB)
All aeroplanes I 97
1 02
93
83.87 + 8.5 1 Log M
91 83 + 6-64 log M 108
-
67.56 4. 16.61 log M I 108
Approach noise level (WNdD)
All aeroplanes 1 101 89.03 + 7.75 log M I 108
3. CONDITIONS DESCRIBED IN CHAPTER 3.3.4.1
Flp ver 2 engines
noise levek
(EPNdB)
4 mgines
M = Maximum take-off
mass in 1 000 kg 0 20.2 28.6 35 48.1
Lateral full-power noise level
(EPNdB)
All aeroplanes
93
Approach noise leve.1 (EPNdB)
All aeroplanes
I
Flyover 2 engines
noise Icvek or lcss 1 89 66.65 + 13.29 log M
70.62 + 13.29 bg M
1.
-.-. - -69.6 1-; + 13.29 log M -- . -- - .
104
4 engnm
or more 1 u9 1
107
108
93
93
71.65 + 13.29 log M
ANNEX 16 - VOLUME 1 ATT A-1 2411 1/05
67.56 + 16.61 log M 73.62 + 13.29 log M
67.56 + 16.61 log M 1 74.62 + 13.29 lag M
Annex 16 - Environnlentnl Protection
4. CONDITIONS DESCRIBED IN CHAPTER 4,4.4
Volume I
Each of the following conditions shall apply:
EPNLL 5 LIMIT,: EPNL, 5 LIMIT*: and EPNLt 5 Llh41TF,
[(LIMITL - EPNL,) + (LIMIT* - EPNLA) + ( L ~ I T-F E PNLFII 1 10
[(LIMIT, - EPNL,) + (LIMIT,, - EPNL,)] 2 2; [(LIMIT, - EPNL,) + (LIMITF - EPNL,)] 1- 2; and
[(LIMIT* - EPNL,) -6 (LIMIT, - EPNk)] 2 2
where
=FILL, EPNLA and EPNLF. are respectively h e noise levels at the lateral, approach and flyover reference noise measurement
points when determined. to one decimal place. in accordance with the noise evaluation method of Appendix 2; and
LIMITL. LIMIT,. and LIMITF are respectively the maximum permined noise levels at the lateral, approach and flyover reference
noise measurement points determined, to one decimal place, in accordance with he equations for the conditions described in
Chapter 3, 3.4.1 (Condition 3).
5. CONDITIONS DESCRIBED IN CHAPTER 5,5.4
M = Mex~mumt rkc-dT
mass in 1 000 kg 5.7 34.0
Lsteial noise level (EPNdB) *- 85.83 + 6.64 log M 1 103
Appmach noise level (EPNdFt) 87.83 + 6.64 loe M 1 05
Flpver noise level (EPNdJ3) 1 89 63..56+ 16.61 log M 1 106
6. CONDITIONS DESCRIBED IN CHAPTER 6-63
7. CONDlTlONS DESCRIBED IN CHAPTER 8.8.4.1
M = Maximum take-off
mass ~n I 000 kg 0 0.6 - I .5 8.618
M = Maximum take-off
mass in I 000 kg 0 0.788
Na~sele vel ~nd B(& 1 68 / 60 + 13.33 M 80
8. CONDlTIONS DESCRIBED IN CHAPTER 8, 8.4.2
-.
-Ta ke-off nose lcvcl (EPNdB)
Approach noise level (EPNdBI
Ovutlight noise level (EPNdB)
M = Maximum takc-aff
mars in l 000 kg 0 0.788
Takrufl' norse level (EPNdB) 1 R6 I 87.03 + 9.97 log M I 106
-.-
109
110
P. - 88 89.02 + 9.97 log M
89
90
2411 1 /M ATT A-2
I OR
W03 +997 Idg M
91.03 + 9.97 lop M
Approach noise level (EPNdB)
- --
Ovcrtllght noise level (EPNQB)
A-.
89 90.03 + 9.97 lug M LO9
84 1 85.03 + 9.97 log M 104
Anner 16 - Environawntnl Protection
9. CONDITIONS DESCRIBED IN CHAPTER 10,10.4 a) and 10.4 b)
10.4 a);
M = Maximum t a k e 4
m-ass in 1 000 kg 0 0.6 --- . - - .- -- - 1.4 8.618
I
- --
-Nois e-. l-evel in- -.d, B-(-A--) - ----- 83.23 + 32.07 log M ! 88 - - - - - - ,
10. CONDITIONS DESCRIBED IN CHAPTER 11,11.4.1
M = Mmimum takeoff
mass in 1 000 kg 0 0.57 -.-.. -- - 1.5 8.61%
M - Maximum rake-nff
mass in L 000 kg 0 0.788
kois lwel im dB(A)
11. CONDITIONS DESCRIBED IN CHAPTER 11.11.4.2
70
Noise level in dB SEL
ATT A-3
78.71 + 35.70 log M
82
M = Maximum tak~off
rnass in 1 000 kg 0 1.417 3.175
05
83.03 + 9.97 log M
Noisc level in dS SEL R2 80.49 + 9.97 log M
ATTACHMENT B. GUIDELINES FOR NOISE CERTIFICATION OF
PROPELLER-DRIVEN STOL AEROPLANES
Note.- See Part It, Chaprer 7.
Note I.- For the puvase of these guidelines. SrOL aeroplanes
are those which. when operating in the s h o ~tak e-ofJ
and landing mode, consisrent with the relevonr airworthiness
wquiwmenrs, require a runway length (with no sropway or
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