[Federal Register Volume 68, Number 217 (Monday, November 10, 2003)]
[Notices]
[Pages 63841-63842]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 03-28138]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration


Additional Requirements: Aquila GmbH Engine Mount Connection 
Design Criteria and Winglets for the Aquila GmbH AT01 JAR-VLA Airplane

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of issuance of design criteria.

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SUMMARY: 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, Sec. 21.29, as a 
14 CFR part 21, Sec. 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.

EFFECTIVE DATE: October 20, 2003.

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.

SUPPLEMENTARY 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.

Design Criteria

    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, Sec.  
21.17.

[[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[deg] 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[deg] 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.

    Issued in Kansas City, Missouri, on October 20, 2003.
Michael Gallagher,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 03-28138 Filed 11-7-03; 8:45 am]
BILLING CODE 4910-13-P