[Federal Register: May 5, 2004 (Volume 69, Number 87)]
[Rules and Regulations]
[Page 24952-24953]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr05my04-12]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 2003-NM-120-AD; Amendment 39-13606; AD 2004-09-17]
RIN 2120-AA64
Airworthiness Directives; Dornier Model 328-100 and -300 Series
Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to all Dornier Model 328-100 and -300 series airplanes, that
requires a one-time inspection for fracture and/or breakage of the
hinge bolt of the output rod of the rudder spring tab lever assembly,
and corrective action if necessary. This AD also requires modification
of the hinge bolt. This action is necessary to prevent fracture and/or
breakage of the hinge bolt, which could result in migration of the bolt
tail, a loose spring tab, and consequent reduced controllability of the
airplane. This action is intended to address the identified unsafe
condition.
DATES: Effective June 9, 2004.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of June 9, 2004.
ADDRESSES: The service information referenced in this AD may be
obtained from AvCraft Aerospace GmbH, P.O. 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 National Archives
and Records Administration (NARA). For information on the availability
of this material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-2125; fax (425) 227-1149.
SUPPLEMENTARY 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 all Dornier Model 328-100 and -300
series airplanes was published in the Federal Register on March 5, 2004
(69 FR 10379). That action proposed to require a one-time inspection
for fracture and/or breakage of the hinge bolt of the output rod of the
rudder spring tab lever assembly, and corrective action if necessary.
That action also proposed to require modification of the hinge bolt.
Comments
We provided the public the opportunity to participate in the
development of this AD. No comments have been submitted on the proposed
AD or on the determination of the cost to the public.
Conclusion
We have carefully reviewed the available data and determined that
air safety and the public interest require adopting the AD as proposed.
Cost Impact
We estimate that 112 airplanes of U.S. registry will be affected by
this AD, that it will take about 1 work hour per airplane to accomplish
the inspection and modification, and that the average labor rate is $65
per work hour. Required parts will cost about $205 per airplane. Based
on these figures, the cost impact of the AD on U.S. operators is
estimated to be $30,240, or $270 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.
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.
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.
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:
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:
2004-09-17 Fairchild Dornier GmbH (Formerly Dornier Luftfahrt GmbH):
Amendment 39-13606. Docket 2003-NM-120-AD.
Applicability: All Model 328-100 and 328-300 series airplanes,
certificated in any category.
Compliance: Required as indicated, unless accomplished
previously.
To prevent fracture and/or breakage of the hinge bolt of the
output rod of the rudder spring tab lever assembly, which could
result in migration of the bolt tail, a loose spring tab, and
consequent reduced controllability of the airplane, accomplish the
following:
[[Page 24953]]
One-Time Inspection/Corrective Action/Modification
(a) Within 4 months after the effective date of this AD: Do a
one-time detailed inspection of the hinge bolt of the output rod of
the rudder spring tab lever assembly for fracture and/or breakage of
the hinge bolt by doing all the applicable actions per the
Accomplishment Instructions of Dornier Service Bulletin SB-328-27-
423 (for Model 328-100 series airplanes) or SB-328J-27-159 (for
Model 328-300 series airplanes), both dated February 4, 2002, as
applicable.
Note 1: For the purposes of this AD, a detailed inspection is
defined as: ``An intensive visual examination of a specific
structural area, system, installation, or assembly to detect damage,
failure, or irregularity. Available lighting is normally
supplemented with a direct source of good lighting at intensity
deemed appropriate by the inspector. Inspection aids such as mirror,
magnifying lenses, etc., may be used. Surface cleaning and elaborate
access procedures may be required.''
(1) If no fracture or breakage is found: Before further flight,
modify the hinge bolt by doing all the applicable actions per the
Accomplishment Instructions of the applicable service bulletin.
(2) If any fracture or breakage is found: Before further flight,
replace the bolt per a method approved by either the Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate;
or the Luftfahrt-Bundesamt (or its delegated agent); then modify the
hinge bolt as required by paragraph (a)(1) of this AD.
Alternative Methods of Compliance
(b) In accordance with 14 CFR 39.19, the Manager, International
Branch, ANM-116, is authorized to approve alternative methods of
compliance for this AD.
Incorporation by Reference
(c) Unless otherwise provided in this AD, the actions shall be
done in accordance with Dornier Service Bulletin SB-328-27-423,
dated February 4, 2002; or Dornier Service Bulletin SB-328J-27-159,
dated February 4, 2002; as applicable. 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 AvCraft Aerospace 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 National Archives and Records Administration (NARA). For
information on the availability of this material at NARA, call 202-
741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html
.
Note 2: The subject of this AD is addressed in German
airworthiness directives 2003-137 and 2003-143, both dated May 15,
2003.
Effective Date
(d) This amendment becomes effective on June 9, 2004.
Issued in Renton, Washington, on April 26, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-10021 Filed 5-4-04; 8:45 am]
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