Van Horn Aviation | Composite Rotor Blades
Van Horn Aviation | Composite Rotor Blades

Acoustics Testing

Acoustics TESTING

206 Tail Rotor Blade Acoustics Testing

If noise is a concern in your neighborhood, fly neighborly with VHA tail rotor blades!

Our 206B/L and OH-58 composite tail rotor blades can decrease the overall noise signature of the helicopter by up to 41 percent. As part of the FAA certification for the 206B tail rotor blade, VHA was required to test the helicopter’s overall noise level with the VHA blades installed.

Acoustics TESTING

Hear The Difference!

206 Tail Rotor Blade Baseline Acoustics:

VHA 206 Tail Rotor Blade Acoustics:

The acoustic flight tests were performed on March 3, 2009, at the Buttonwillow-Elk Hills Airport in Kern County, Calif. A 206B fitted with the OEM tail rotor made several passes over calibrated noise measurement equipment to establish baseline noise levels. Flyovers were conducted at a target height of 490 feet AGL, with equal flights northwest-bound and southeast-bound. The tests were then repeated with the VHA tail rotor configuration.

Tail Rotor Configuration Aircraft Weight Flyover Level Stage 2 Limit Test Level Minus Limit
Baseline Bell OEM 3,200 82.9 84.6 -1.7
Modified Van Horn Aviation 3,200 80.6 84.6 -4.0

According to data presented in the report published by Acoustical Analysis Associates, Inc., the firm that conducted the acoustics testing in accordance with the FAA approved flight plan, the sound exposure of the 206B fitted with the VHA tail rotor blades was 80.6 decibels compared to the measured OEM decibel level of 82.9 decibels. 

Due to the non-linear nature of the decibel system, the 2.3 decibel difference results in a 41% decrease in noise level. The noise level limit specified in 14 CFR Part 36 Appendix J for a maximum takeoff weight of 3200 pounds is 84.6 decibels. For more information, please review our white paper on the acoustic testing.

Tail Rotor Configuration Aircraft Weight Flyover Level Stage 2 Limit Test Level Minus Limit
Baseline Bell OEM 3,200 82.9 84.6 -1.7
Modified Van Horn Aviation 3,200 80.6 84.6 -4.0

According to data presented in the report published by Acoustical Analysis Associates, Inc., the firm that conducted the acoustics testing in accordance with the FAA approved flight plan, the sound exposure of the 206B fitted with the VHA tail rotor blades was 80.6 decibels compared to the measured OEM decibel level of 82.9 decibels. 

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    Due to the non-linear nature of the decibel system, the 2.3 decibel difference results in a 41% decrease in noise level. The noise level limit specified in 14 CFR Part 36 Appendix J for a maximum takeoff weight of 3200 pounds is 84.6 decibels. For more information, please review our white paper on the acoustic testing.

Acoustics TESTING

206B Main Rotor Blade Acoustics Testing

As part of the Supplemental Type Certification (STC) process, VHA hired a contracting firm to conduct acoustics testing of the 206B main rotor blade. The test was conducted on April 29, 2015 in Kern County, California, using a similar equipment setup as for the 206 tail rotor blade acoustics test conducted in 2009. A 206B JetRanger fitted with VHA tail rotor blades flew multiple passes at the prescribed altitude, first using the OEM metal main rotor blades, and then using the composite VHA main blades.

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    Unlike the tail rotor blade test, which showed a dramatic drop in noise between the metal blade and the VHA composite blade, the main rotor blade was less conclusive. While the VHA main rotor blade met FAA acoustic requirements, there was not enough difference between the metal and composite blades to show a definitive drop in decibels. VHA personnel believe that atmospheric conditions and the difference in noise signature between the two blades may have accounted for test results. The test was not run with metal tail rotor blades.


    VHA personnel and others who operate VHA main and tail rotor blades notice a marked difference in the cabin compared to flying the OEM metal blades. VHA intends to run the acoustics test again during the 206L main rotor blade program, and will update this page with the results.

Unlike the tail rotor blade test, which showed a dramatic drop in noise between the metal blade and the VHA composite blade, the main rotor blade was less conclusive. While the VHA main rotor blade met FAA acoustic requirements, there was not enough difference between the metal and composite blades to show a definitive drop in decibels. VHA personnel believe that atmospheric conditions and the difference in noise signature between the two blades may have accounted for test results. The test was not run with metal tail rotor blades.


VHA personnel and others who operate VHA main and tail rotor blades notice a marked difference in the cabin compared to flying the OEM metal blades. VHA intends to run the acoustics test again during the 206L main rotor blade program, and will update this page with the results.

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