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Federal Aviation Regulation Appendix G to Part 36 - Takeoff Noise Requirements for Propeller-Driven Small Airplane and Propeller-Driven, Commuter Category Airplane Certification Tests on or After December 22, 1988
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Appendix G to Part 36 — Takeoff Noise Requirements for Propeller-Driven Small Airplane and Propeller-Driven, Commuter Category Airplane Certification Tests on or After December 22, 1988
G36.1 Scope.
G36.101 General Test Conditions.
G36.103 Acoustical measurement system.
G36.105 Sensing, recording, and reproducing equipment.
G36.107 Noise measurement procedures.
G36.109 Data recording, reporting, and approval.
G36.111 Flight procedures.
G36.201 Corrections to Test Results.
G36.203 Validity of results.
G36.301 Aircraft Noise Limits.
Section G36.1 Scope. This appendix prescribes limiting noise levels and procedures for measuring noise and adjusting these data to standard conditions, for propeller driven small airplanes and propeller-driven, commuter category airplanes specified in §§36.1 and 36.501(c).
Sec. G36.101 General Test Conditions.
Sec. G36.103 Acoustical Measurement System.
Sec. G36.105 Sensing, Recording, and Reproducing Equipment.
(b) The characteristics of the complete system must comply with the requirements in International Electrotechnical Commission (IEC) Publications No. 651, entitled “Sound Level Meters” and No. 561, entitled “Electro-acoustical Measuring Equipment for Aircraft Noise Certification” as incorporated by reference under §36.6 of this part. Sound level meters must comply with the requirements for Type 1 sound level meters as specified in IEC Publication No. 651.
Sec. G36.107 Noise Measurement Procedures.
Sec. G36.109 Data Recording, Reporting, and Approval.
Sec. G36.111 Flight Procedures.
Sec. G36.201 Corrections to Test Results.
Delta (M)=(HTα—0.7 HR)/1000
where HTis the height in feet under test conditions, HRis the height in feet under reference conditions when the aircraft is directly over the noise measurement point and α is the rate of absorption for the test day conditions at 500 Hz as specified in SAE ARP 866A, entitled “Standard Values of Atmospheric Absorption as a function of Temperature and Humidity for use in Evaluating Aircraft Flyover Noise” as incorporated by reference under §36.6.
where HTis the height of the test aircraft when directly over the noise measurement point and HRis the reference height.
where MTand MRare the test and reference helical tip Mach numbers, respectively. The constant “k” is equal to the slope of the line obtained for measured values of the sound level in dB(A) versus helical tip Mach number. The value of k may be determined from approved data. A nominal value of k=150 may be used when MTis smaller than MR. No correction may be made using the nominal value of k when MTis larger than MR. The reference helical tip Mach number MRis the Mach number corresponding to the reference conditions (RPM, airspeed, temperature) above the measurement point.
Delta (3)=K3log (PR/PT)
where PRand PTare the test and reference engine powers respectively obtained from the manifold pressure/torque gauges and engine rpm. The value of K3shall be determined from approved data from the test airplane. In the absence of flight test data and at the discretion of the Administrator, a value of K3=17 may be used.
Sec. G36.203 Validity of Results.
Sec. G36.301 Aircraft noise limits.
(Secs. 313(a), 603, and 611(b), Federal Aviation Act of 1958 as amended (49 U.S.C. 1354(a), 1423, and 1431(b)); sec. 6(c), Department of Transportation Act (49 U.S.C. 1655 (c)); Title I, National Environmental Policy Act of 1969 (42 U.S.C. 4321 et seq .); E. O. 11514, March 5, 1970 and 14 CFR 11.45).
[Amdt. 36–16, 53 FR 47400, Nov. 22, 1988; 53 FR 50157, Dec. 13, 1988, as amended by Amdt. 36–22, 64 FR 55602, Oct. 13, 1999; Amdt. 36–54, 67 FR 45236, July 8, 2002; Amdt. 36–27, 70 FR 45504, Aug. 5, 2005; Amdt. 36–28, 71 FR 532, Jan. 4, 2006]
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