Federal Aviation Administration, DOT.
This amendment adopts a new airworthiness directive (AD), applicable to certain Dornier Model 328-100 and 328-300 series airplanes, that requires replacement of the bolts with new bolts with wirelocking on the Support One of the rudder spring tab. This action is necessary to ensure replacement of improper bolts installed on the rudder spring tab that could back out over time, which could result in reduced structural integrity of the airplane. This action is intended to address the identified unsafe condition.
Effective September 20, 2002.
The incorporation by reference of certain publications listed in the Start Printed Page 53470regulations is approved by the Director of the Federal Register as of September 20, 2002.
The service information referenced in this AD may be obtained from Fairchild Dornier, Dornier Luftfahrt GmbH, PO Box 1103, D-82230 Wessling, Germany. This information may be examined at the Federal Aviation Administration (FAA), Transport Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, Washington; or at the Office of the Federal Register, 800 North Capitol Street, NW., suite 700, Washington, DC.Start Further Info
FOR FURTHER INFORMATION CONTACT:
Tom Groves, Aerospace Engineer, International Branch, ANM-116, FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 227-1503; fax (425) 227-1149.End Further Info End Preamble Start Supplemental Information
A proposal to amend part 39 of the Federal Aviation Regulations (14 CFR part 39) to include an airworthiness directive (AD) that is applicable to certain Dornier Model 328-100 and 328-300 series airplanes was published in the Federal Register on April 5, 2002 (67 FR 16331). That action proposed to require replacement of the bolts with new bolts with wirelocking on the Support One of the rudder spring tab.
Interested persons have been afforded an opportunity to participate in the making of this amendment. No comments were submitted in response to the proposal or the FAA's determination of the cost to the public.
The FAA has determined that air safety and the public interest require the adoption of the rule as proposed.
The FAA estimates that 53 Model 328-100 series airplanes and 20 Model 328-300 series airplanes of U.S. registry will be affected by this AD, that it will take approximately 1 work hour per airplane to accomplish the required actions, and that the average labor rate is $60 per work hour. Required parts will be supplied by the manufacturer at no cost to the operators. Based on these figures, the cost impact of the AD on U.S. operators is estimated to be $4,380, or $60 per airplane.
The cost impact figure discussed above is based on assumptions that no operator has yet accomplished any of the requirements of this AD action, and that no operator would accomplish those actions in the future if this AD were not adopted. The cost impact figures discussed in AD rulemaking actions represent only the time necessary to perform the specific actions actually required by the AD. These figures typically do not include incidental costs, such as the time required to gain access and close up, planning time, or time necessitated by other administrative actions.
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.
For the reasons discussed above, I certify that this action (1) is not a “significant regulatory action” under Executive Order 12866; (2) is not a “significant rule” under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and (3) will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. A final evaluation has been prepared for this action and it is contained in the Rules Docket. A copy of it may be obtained from the Rules Docket at the location provided under the caption ADDRESSES.Start List of Subjects
List of Subjects in 14 CFR Part 39End List of Subjects
Adoption of the Amendment
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:Start Part
PART 39—AIRWORTHINESS DIRECTIVESEnd Part Start Amendment Part
1. The authority citation for part 39 continues to read as follows:End Amendment Part
2. Section 39.13 is amended by adding the following new airworthiness directive:End Amendment Part
2002-16-13 Dornier Luftfahrt GMBH: Amendment 39-12852. Docket 2001-NM-313-AD.
Applicability: Model 328-100 series airplanes having serial numbers 3005 through 3119 inclusive, and Model 328-300 series airplanes having serial numbers 3105 through 3167 inclusive, excluding serial number 3164; certificated in any category.
This AD applies to each airplane identified in the preceding applicability provision, regardless of whether it has been modified, altered, or repaired in the area subject to the requirements of this AD. For airplanes that have been modified, altered, or repaired so that the performance of the requirements of this AD is affected, the owner/operator must request approval for an alternative method of compliance in accordance with paragraph (b) of this AD. The request should include an assessment of the effect of the modification, alteration, or repair on the unsafe condition addressed by this AD; and, if the unsafe condition has not been eliminated, the request should include specific proposed actions to address it.
Compliance: Required as indicated, unless accomplished previously.
To ensure replacement of improper bolts installed on the rudder spring tab that could back out over time, which could result in reduced structural integrity of the airplane, accomplish the following:
(a) Within 90 days after the effective date of this AD, replace the bolts with new bolts with wirelocking on the Support One of the rudder spring tab (including torquing the bolts to the proper setting), per the Accomplishment Instructions of Dornier Service Bulletin SB-328-55-351 (for Model 328-100 series airplanes); or SB-328J-55-058, Revision 1 (for Model 328-300 series airplanes); both dated April 10, 2001; as applicable.
Alternative Methods of Compliance
(b) An alternative method of compliance or adjustment of the compliance time that provides an acceptable level of safety may be used if approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA. Operators shall submit their requests through an appropriate FAA Principal Maintenance Inspector, who may add comments and then send it to the Manager, International Branch, ANM-116.
Information concerning the existence of approved alternative methods of compliance with this AD, if any, may be obtained from the International Branch, ANM-116.
Special Flight Permits
(c) Special flight permits may be issued in accordance with §§ 21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197 and 21.199) to operate the airplane to a location where the requirements of this AD can be accomplished.
Incorporation by Reference
(d) The replacement shall be done in accordance with Dornier Service Bulletin SB-328-55-351, dated April 10, 2001; or Dornier Service Bulletin SB-328J-55-058, Revision 1, dated April 10, 2001; as applicable. This incorporation by reference was approved by the Director of the Federal Register in accordance with 5 U.S.C. 552(a) Start Printed Page 53471and 1 CFR part 51. Copies may be obtained from Fairchild Dornier, Dornier Luftfahrt GmbH, PO 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.
The subject of this AD is addressed in German airworthiness directives 2001-260 and 2001-261, both dated September 6, 2001.
(e) This amendment becomes effective on September 20, 2002.Start Signature
Issued in Renton, Washington, on August 7, 2002.
Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 02-20511 Filed 8-15-02; 8:45 am]
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