Airworthiness directives: Dornier,
[Federal Register: June 6, 2003 (Volume 68, Number 109)]
[Rules and Regulations]
[Page 33842-33844]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr06jn03-5]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
[Docket No. 2003-NM-102-AD; Amendment 39-13184; AD 2003-11-24]
RIN 2120-AA64
Airworthiness Directives; Dornier Model 328-100 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
SUMMARY: This amendment adopts a new airworthiness directive (AD) that is applicable to all Dornier Model 328-100 series airplanes. This action requires installation of retainers instead of washers in the upper and lower torsion bars of the rudder tab. This action is necessary to prevent a spring tab torsion bar from slipping through its retaining adapters, which could result in a loose spring tab; the loss of both tension springs could allow the spring tab to flutter and result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
DATES: Effective June 23, 2003.
The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of June 23, 2003.
Comments for inclusion in the Rules Docket must be received on or before July 7, 2003.
ADDRESSES: Submit comments in triplicate to the Federal Aviation Administration (FAA), Transport Airplane Directorate, ANM-114, Attention: Rules Docket No. 2003-NM-102-AD, 1601 Lind Avenue, SW., Renton, Washington 98055-4056. Comments may be inspected at this location between 9 a.m. and 3 p.m., Monday through Friday, except Federal holidays. Comments may be submitted via fax to (425) 227-1232. Comments may also be sent via the Internet using the following address: 9-anm-iarcomment@faa.gov. Comments sent via the Internet must contain ``Docket No. 2003-NM-102-AD'' in the subject line and need not be submitted in triplicate. Comments sent via fax or the Internet as attached electronic files must be formatted in Microsoft Word 97 or 2000 or ASCII text.
The service information referenced in this AD may be obtained from FAIRCHILD DORNIER, DORNIER Luftfahrt GmbH, P.O. Box 1103, D-82230 Wessling, Germany. This information may be examined at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., Suite 700, Washington, DC.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington
[[Page 33843]]
98055-4056; telephone (425) 227-2125; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION: The Luftfahrt-Bundesamt (LBA), which is the airworthiness authority for Germany, recently notified the FAA that an unsafe condition may exist on all Dornier Model 328-100 series airplanes. The LBA advises that, on an affected airplane, a lower torsion spring was found to be loose and an upper torsion spring had migrated. The torsion spring system is part of the rudder tab control and comprises two torsion springs and adapters. The design of the torsion spring and structure adapters could result in a poor fit, allowing the spring to slip through the adapters. Loss of both tension springs, if not corrected, could allow the spring tab to flutter and result in reduced controllability of the airplane.
Explanation of Relevant Service Information
Dornier has issued Service Bulletin SB-328-27-298, Revision 1, dated November 21, 2002, which describes procedures for installation of a retainer instead of a washer in the upper and lower torsion bars of the rudder tab. Accomplishment of the action specified in the service bulletin is intended to adequately address the identified unsafe condition. The LBA classified this service bulletin as mandatory and issued German airworthiness directive 2003-104, dated April 3, 2003, to ensure the continued airworthiness of these airplanes in Germany.
FAA's Conclusions
This airplane model is manufactured in Germany and is type certificated for operation in the United States under the provisions of Sec. 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and the applicable bilateral airworthiness agreement. Pursuant to this bilateral airworthiness agreement, the LBA has kept the FAA informed of the situation described above. The FAA has examined the findings of the LBA, reviewed all available information, and determined that AD action is necessary for products of this type design that are certificated for operation in the United States.
Explanation of Requirements of Rule
Since an unsafe condition has been identified that is likely to exist or develop on other airplanes of the same type design registered in the United States, this AD is being issued to prevent a spring tab torsion bar from slipping through its retaining adaptors, which could result in a loose spring tab; the loss of both tension springs could allow the spring tab to flutter and result in reduced controllability of the airplane. This AD requires installation of a retainer instead of a washer in the upper and lower torsion bars of the rudder tab. The actions are required to be accomplished in accordance with the service bulletin described previously.
Changes to 14 CFR Part 39/Effect on the AD
On July 10, 2002, the FAA issued a new version of 14 CFR part 39 (67 FR 47997, July 22, 2002), which governs the FAA's airworthiness directives system. The regulation now includes material that relates to altered products, special flight permits, and alternative methods of compliance. This material will no longer be included in each individual AD; however, the office authorized to approve AMOCs will be defined in each individual AD.
Determination of Rule's Effective Date
Since a situation exists that requires the immediate adoption of this regulation, it is found that notice and opportunity for prior public comment hereon are impracticable, and that good cause exists for making this amendment effective in less than 30 days.
Comments Invited
Although this action is in the form of a final rule that involves requirements affecting flight safety and, thus, was not preceded by notice and an opportunity for public comment, comments are invited on this rule. Interested persons are invited to comment on this rule by submitting such written data, views, or arguments as they may desire. Communications shall identify the Rules Docket number and be submitted in triplicate to the address specified under the caption ADDRESSES. All communications received on or before the closing date for comments will be considered, and this rule may be amended in light of the comments received. Factual information that supports the commenter's ideas and suggestions is extremely helpful in evaluating the effectiveness of the AD action and determining whether additional rulemaking action would be needed.
Submit comments using the following format:
[sbull] Organize comments issue-by-issue. For example, discuss a request to change the compliance time and a request to change the service bulletin reference as two separate issues.
[sbull] For each issue, state what specific change to the AD is being requested.
[sbull] Include justification (e.g., reasons or data) for each request.
Comments are specifically invited on the overall regulatory, economic, environmental, and energy aspects of the rule that might suggest a need to modify the rule. All comments submitted will be available, both before and after the closing date for comments, in the Rules Docket for examination by interested persons. A report that summarizes each FAA-public contact concerned with the substance of this AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments submitted in response to this rule must submit a self-addressed, stamped postcard on which the following statement is made: ``Comments to Docket Number 2003-NM-102-AD.'' The postcard will be date stamped and returned to the commenter.
Regulatory Impact
The regulations adopted herein will not have a substantial direct effect on the States, on the relationship between the national Government and the States, or on the distribution of power and responsibilities among the various levels of government. Therefore, it is determined that this final rule does not have federalism implications under Executive Order 13132.
The FAA has determined that this regulation is an emergency regulation that must be issued immediately to correct an unsafe condition in aircraft, and that it is not a ``significant regulatory action'' under Executive Order 12866. It has been determined further that this action involves an emergency regulation under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979). If it is determined that this emergency regulation otherwise would be significant under DOT Regulatory Policies and Procedures, a final regulatory evaluation will be prepared and placed in the Rules Docket. A copy of it, if filed, may be obtained from the Rules Docket at the location provided under the caption ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.
Adoption of the Amendment
0 Accordingly, pursuant to the authority delegated to me by the Administrator, the Federal Aviation Administration amends part 39 of the Federal Aviation Regulations (14 CFR part 39) as follows:
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PART 39--AIRWORTHINESS DIRECTIVES
0 1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0 2. Section 39.13 is amended by adding the following new airworthiness directive:
2003-11-24 Dornier Luftfahrt GMBH: Amendment 39-13184. Docket 2003- NM-102-AD.
Applicability: Model 328-100 series airplanes, certificated in any category, as listed in Dornier Service Bulletin SB-328-27-298, Revision 1, dated November 21, 2002.
Compliance: Required as indicated, unless accomplished previously.
To prevent a spring tab torsion bar from slipping through its retaining adaptors, which could result in a loose spring tab; and to further prevent the loss of both tension springs, which could allow the spring tab to flutter and result in reduced controllability of the airplane, accomplish the following:
Retainer Installation
(a) Within 2 months after the effective date of this AD: Install a retainer instead of a washer in the upper and the lower torsion bars of the rudder, in accordance with Dornier Service Bulletin SB- 328-27-298, Revision 1, dated November 21, 2002. Installation of a retainer before the effective date of this AD in accordance with Dornier Service Bulletin SB-328-27-298, dated March 26, 1999, is acceptable for compliance with the requirements of this paragraph.
Alternative Methods of Compliance
(b) In accordance with 14 CFR 39.19, the Manager, International Branch, ANM-116, FAA, is authorized to approve alternative methods of compliance for this AD.
Incorporation by Reference
(c) Unless otherwise specified in this AD, the actions shall be done in accordance with Dornier Service Bulletin SB-328-27-298, Revision 1, dated November 21, 2002. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR part 51. Copies may be obtained from Fairchild Dornier, Dornier Luftfahrt GmbH, P.O. Box 1103, D-82230 Wessling, Germany. Copies may be inspected at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., Suite 700, Washington, DC.
Note: The subject of this AD is addressed in German airworthiness directive 2003-104, dated April 3, 2003.
Effective Date
(d) This amendment becomes effective on June 23, 2003.
Issued in Renton, Washington, on May 29, 2003. Ali Bahrami, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 03-13974 Filed 6-5-03; 8:45 am]
BILLING CODE 4910-13-P
