Federal Register: November 10, 2003 (Volume 68, Number 217)
DOCID: FR Doc 03-28138
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
ACTION: Reports and guidance documents; availability, etc.:
DOCUMENT ACTION: Notice of issuance of design criteria.
Additional Requirements: Aquila GmbH Engine Mount Connection Design Criteria and Winglets for the Aquila GmbH AT01 JAR-VLA Airplane
EFFECTIVE DATES: October 20, 2003.
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 JARVLA (Joint Aviation RequirementsVery Light Aircraft) parts 865, 1191, and 445 are the same as those issued by the airworthiness authority for Germany, the LuftfahrtBundesamt (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, JARVLA, using the requirements of JARVLA Amendment VLA/92/01 as developed by the Joint Aviation Authority, and under Title 14 of the Code of Federal Regulations.
Engine mount connection and winglets design for Aquila GmbH AT01 JAR-VLA Airplane,
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 JARVLA
(Joint Aviation RequirementsVery Light Aircraft) Amendment VLA/92/01
as developed by the Joint Aviation Authority and 14 CFR part 21, Sec. 21.17.
Additional Requirements: Engine Mount Connection Design Criteria
The Aquila AT01 is a full composite singleengine 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 Zdirection 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 Xdirection 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 20135 to AC 232. 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. 0328138 Filed 11703; 8:45 am]
BILLING CODE 491013P
FOR FURTHER INFORMATION CONTACT
Mr. Karl Schletzbaum, Project Support Office, ACE112, 901 Locust, Kansas City, Missouri 64106 or at telephone number 8163294146.