What it approves
Installation of Power Flow Systems, Inc. (PFS) tuned exhaust system.
What the certificate says
From the PDF’s text layer, without the form’s printed wording. Layout and order may differ; the PDF is the record.
certifies that the change in the type design for th e following product with the limitations and condi tions therefor as specified hereon meets the airworthiness requiremen ts of Part 27 of the Federal Aviation Regulations.
Description of Type Design Change: Installation of Power Flow Systems, Inc. (PFS) tuned exhaust system drawing PFS-17101, rev A, dated 11/2/2009 or later FAA approved revisions. Installed per Power Flow Systems, Inc. drawing 117101, rev A, dated 11/2/2009 or later FAA approved revisions and Tuned Exhaust System Installation Instructions and Instructions for Continued Airworthiness, PFS-17160, rev A, dated 1/26/2010 or later FAA approved revisions.
Limitations and Conditions : Applicable to Robinson R22 Series aircraft equipped with O-320-B2C engines only.
Instructions for Continued Airworthiness contained in Tuned Exhaust System Installation Instructions and Instructions for Continued Airworthiness, PFS-17160, rev A, dated 1/26/2010 or later FAA approved revisions must be made available to the operator at the time of installation.
Power Flow Systems, Inc.
1585 Aviation Center Parkway Hangar 804 Daytona Beach, FL 32114 H10WE Make : Robinson Model : R22; R22 Alpha; R22 Beta; R22 Mariner
Date of application : August 31, 2009
Date of issuance : July 16, 2010
( Signature )
Melvin Taylor, Manager Atlanta Aircraft Certification Office
( Title )
FAA F ORM 8110-2-1(10-69) PAGE 2 of 3 PAGES
Number
FAA F ORM 8110-2-1(10-69) PAGE 3 of 3 PAGES
Number SR03863AT Date of Issuance: July 16, 2010
The engine performance effects of this STC were evaluated and were found to be within the limitations of the aircraft and engine Type Certificates. Any additional modifications that contribute to HP increases could adversely affect the aircraft or engine airworthiness. This approval should not be extended to other aircraft of this model on which other previously approved modifications are incorporated, unless it is determined by the installer that the interrelationship between this change and any other previously approved modifications will produce no adverse effect upon the airworthiness of that airplane. If the holder agrees to permit another person to use this certificate to alter the product, the holder shall give the other pe rson written evidence of that permission.
Certification Basis:
Based on 14CFR §§ 21.115 and 21.101, this STC modif ication to the type design is considered not to be a major or significant change.
Original Certification Basis : 14 CFR Part 27 dated February 1, 1965, including Amendments 27-1 through 27-10. § 27.1559 of Amendment 27-21 is an option for all S/Ns.
National Environmental Act of 1969 Noise Control Act of 1972 Equivalent Safety Finding :
Number TD10352LA-R/S-1 14 CFR Part 27.1401(d), Anticollision Light System END___
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