Federal Aviation Administration (FAA), DOT.
Notice of issuance of design criteria.
This notice announces the issuance of the design criteria for (a) fire protection of the connection between the metal structure of an engine mount and composite airframe and (b) structural substantiation of the winglets for the Aquila GmbH AT01. These additional provisions addressing JAR-VLA (Joint Aviation Requirements-Very Light Aircraft) parts 865, 1191, and 445 are the same as those issued by the airworthiness authority for Germany, the Luftfahrt-Bundesamt (LBA), in the original certification of the aircraft. The airplane will be certificated under the provisions of 14 CFR part 21, §21.29, as a 14 CFR part 21, §21.17(b), special class aircraft, JAR-VLA, using the requirements of JAR-VLA Amendment VLA/92/01 as developed by the Joint Aviation Authority, and under Title 14 of the Code of Federal Regulations.
October 20, 2003.Start Further Info
FOR FURTHER INFORMATION CONTACT:
Mr. Karl Schletzbaum, Project Support Office, ACE-112, 901 Locust, Kansas City, Missouri 64106 or at telephone number 816-329-4146.End Further Info End Preamble Start Supplemental Information
Discussion of Comments
A notice of availability was published on September 2, 2003 (68 FR 56809). No comments were received, and the design criteria are adopted as proposed.
This airplane will be certified under the requirements of JAR-VLA (Joint Aviation Requirements-Very Light Aircraft) Amendment VLA/92/01 as developed by the Joint Aviation Authority and 14 CFR part 21, § 21.17. Start Printed Page 63842
Additional Requirements: Engine Mount Connection Design Criteria
The Aquila AT01 is a full composite single-engine aircraft with the engine mount fitted to the glass fiber composite fuselage. The airplane will be certified to the requirements of JAR/VLA 865 (Fire protection of flight controls and other flight structure) and JAR/VLA 1191 (Firewalls). However, tests must be performed that demonstrate that the interface between the metallic engine mount and the glass fiber reinforced plastic fuselage withstand a fire for 15 minutes while carrying loads under the following conditions:
(a) With one lost engine mount fitting the loads are distributed over the remaining 3 engine mount fittings. The most critical of these fittings must be chosen for the test.
(1) The loads are:
(i) In Z-direction the mass of the propulsion unit multiplied by a maneuvering load factor resulting from a 30° turn for 15 minutes, superimposed by a maneuvering load of 3 seconds representing the maximum positive limit maneuvering load factor of n=3.8 arising from JAR/VLA 337(a).
(ii) In X-direction the engine propulsion force at maximum continuous power for 5 minutes.
(b) The flame to which the component test arrangement is subjected must provide a temperature of 500° C within the target area.
(c) The flame must be large enough to maintain the required temperature over the entire test zone, i.e., the fitting on the engine compartment side.
(d) It must be shown that the test equipment, e.g., burner and instrumentation are of sufficient power, size, and precision to yield the test requirements arising from paragraphs (a) to (c) above. Guidance will be drawn from advisory material AC 20-135 to AC 23-2.
Additional Requirements: Winglets
Since winglets, as a specific structural element, are not addressed in the JAR/VLA requirements, the following is required:
Compliance must be demonstrated to the requirements of JAR 23.445—Outboard fins or winglets.Start Signature
Issued in Kansas City, Missouri, on October 20, 2003.
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 03-28138 Filed 11-7-03; 8:45 am]
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