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of 10.4 a) does nat am lor applications
for C of A of derived version accepted b,4
on or after 4 November 2M4.
Application for C of A, etc.
of prototype accepted
on or alter
1 January 1985
Application lor C of A, etc.
of prototype or derived
version acceDted on or a k r
1 7 November 1988
C of A for individual
aeroplane issued
an or after
26 November 1981
ATTACHMENT F, GUIDELINES FOR NOISE CERTIFICATION
OF TILT-ROTOR AIRCRAFT
Nore.- See Pmr 11, Chqprer. 13.
Note I.- These guidelines aM applicable to heovier~thonoir
airtmp thot can be supported in flight chiefly by the
reactions of the air on two or mow power-driven mtors on
axes which can be chonged jivm substantially vertical to
hot-i~ontul.
Note 2.- nrese guidelines ore not intended to be uedfor
ralf-rotor aired .#7ur have one or more conf;gurations that am
cerrif;cuted for. oirworrhiness for STOL only. In such cmes.
drflemr or addirional guiiielines would likely be needed.
I. APPLICABILITY
The following guidelines should be applied to all tilt-rotor
aimaft, including tbeir derived versions, for which a type
certificate of ainvorthincs was issued on or after 13 May 1998.
Note.- Certijicotion of tilf-mror oiru-aji which are copoble
of cmrying exrernal load or exrernal equipmen1 should be
mode witl~out~ wchIw ds or. eqwipmenrjitred.
2. NOISE EVALUATION MEASURE
The noise evaluation measure should be the effective
perceived noise level in EPNdB as described in Appendix 2 of
this Annex.
Note.- Additional doro in SEL mrd LAmr 0s deJned tn
Appendiv 4, and one-third ortaw SPLs CIS defined in Appendix
2 corresponding ro LAmr should be made ovoilabk 10 :he
certijicoting outhoriiy for- landme plonnir7g pwrpmes.
3. NOISE MEASUREMENT
REFERENCE POINTS
A tilt-rotor aircraft, when tested In accordance with the
reference procedures of Section 6 and (he test procedures of
Section 7. should not exceed the noise levels specificd in
Section 4 at the following reference points:
I) a flight peth rcfercncc point locared on rhc ground
vertically below the flight path dcfined in thc takc-off
refcrcncc procedure (see 6.2) nnd 5W m horizontally
in the direction of flight from hc point at which transition
to climbing flighr is initiated In the reference
procedure;
2) two other points on the lyound symntnetrically
disposed at 150 m on both sides of the flight path
defined in the takesff reference procedure and lying
on a line through the flight path reference point.
b) Overj7ight rejewnce noise meostrwmenr points:
1) a flight path reference point located on the ground
150 m (492 ft) vertically below the flight path
defined in the overflight reference procedure (see
6.3);
2) two other pints on the ground symnetrically disposed
at 150 m on both sides of the flight path
defined in the overflight reference procedure and
lying on a Line through thc flight path rekrence point.
c) Approwh refiwnce noise rnememenr points:
I ) a flighl path reference point located on the ground
120 tn (394 R) vertically below the flight path
defined in the approach reference procedure (see
6.4). On level ground, this corresponds to a position
1 140 m from the intersection of the 6.0 degree
approach path with the ground plane;
2) two other points on the ground symmctrically
disposed at 150 m on both s~deso f the flight path
defined in the approach re fcrence procedure and lying
on a line through the flight path reference point.
4. MAXIMUM NOISE LEVELS
For tilt-rotor a~rcraft specificd in Section 1. the maximum
noise levels. when determined in accordance w~thth e noise
evaluation method of Appcndix 2 for helicopters, should not
exceed the rollowing:
a) AI rlre rok~-uflJigtrrp ar/) n;fi~trcpo.i~rl r: 109 EPNdB
for tilt-rotor aircraft in VTOLlconversio~n~l odc with
maximum ccrlificated trkc-off mass. at which rhc noisc
certificar~on is requestcd. of XO 000 kg and ovcr and
dccrcclsing linearly with lhc logxilhm of 11ic 1111-rotor
ANNEX 16 - VOLIJME I AI"T F-1 2411 1/05
Annex 16 - Environmental Protection Volume 1
aircrafi mass at n rate of 3 EPNd0 per halving of mass
down to 119 EPNdB afier which the llinit is constant.
b) AI the overjlighr path W ~ P I V ~ CpPo int: 108 EPNdB
for tilt-rotor nircraft in VTOL/conversion mode with
rnaxirnum certificated takeoff mass, at which the noisc
certification is requested. of RO 000 kg and over and
docrcasing linearly with the logarithm of the tilt-rotor
aircraft rnass nt n rate of 3 EPNdB per halving of mass
down to 88 EPNdB after which the limit is constant.
　
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