What it approves
Installation of LORD Tension-Torsion Strap Assembly
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.
27 Federal Aviation (See Type Certificate Data Sheet No. H2SW and Page 3 for complete certification basis)
Installation of LORD Tension-Torsion Strap Assembly in accordance with LORD Master Drawing List “Lord-MDL-206-310- 004101, Rev.-, dated March 15, 2017 and installation instructions in accordance to LORD supplemental ICA SM-6553, ECCN 9E991, Rev.-, dated January 17, 2017, or later FAA approved revisions.
1. FAA Accepted Instructions for Continued Airworthiness, ICA Manual ECCN 9E991, Rev.-, dated January 17, 2017, or later FAA approved revisions is required for this modification.
2. The installer must determine whether this design change is compatible with previously approved modifications.
3. If the holder agrees to permit another person to use this certificate to alter a product, the holder must give the other person written evidence of that permission.
LORD Corporation 4644 Wadsworth Road Dayton, OH 45411-4220 H2SW Bell Helicopter Textron Canada Limited 206A, 206B, 206L, 206L-1, 206L-3, 206L-4 October 27, 2016
April 10, 2017
Original Signed By:
Marcus Runyan for
(Signature) Karol Mordasiewicz Manager Airframe & Administrative Branch Chicago Aircraft Certification Office
(Title)
FAA FORM 8110-2-1(10-69) PAGE 2 of 3 PAGES
FAA FORM 8110-2-1(10-69) PAGE 3 of 3 PAGES
SR04913CH Date of Issuance: April 10, 2017
Based on 14 CFR § 21.115 and 21.101, and the FAA policy for significant changes in FAA Order 8110.48, the certification basis for the modified Bell Helicopter Textron Canada Limited TCDS [H2SW] 206 series is as follows:
a. The type certification basis for the Bell Helicopter 206 series rotorcraft is shown on TCDS H2SW for parts not changed or not affected by this change. See Lord Master Drawing List [LORD-MDL-206-310-004101/004103, Rev -].
b. The certification basis for the parts changed or affected by this change since the reference date of application, October 27, 2016, is based upon part 27 as amended by Amendment 27-0 through 27-38.
Based on 14 CFR § 21.115 and 21.101, and the FAA policy for significant changes in FAA Order 8110.48, the certification basis for this modification was determined to be:
14 CFR 27 Regulations at the latest amendment(s) 27-0 through 27-38.
14 CFR 27.301Loads.Amdt. 27-0, 27.303 F.O.S., Amdt.27-0, 27.305 Strength & Deformation, Amdt.27-0, 27.601(a) Design, Amdt.27-0, 27.602(a)(b) Critical Parts, Amdt. 27-38, 27.603 Materials, Amdt. 27-16, 27.605(a) Fabrication, Amdt. 27-16,
27.609Protection, Amdt. 27-0, 27.611 Inspections, Amdt. 27-0, 27.613 Material strength properties and design values, Amdt.
27-26, 27.623(a) Bearing Factor, Amdt. 27-0., 27.1301 Function and Installation, Amdt. 27-0., 27.1309(a)Equipment, Systems, and Installation, Amdt. 27-46., 27.1529 Instructions For Continued Airworthiness, Amdt. 27-18.
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ADs that name this STC · 0
An AD can apply because an STC is installed, or mention one in its text.