[Federal Register Volume 61, Number 62 (Friday, March 29, 1996)]
[Rules and Regulations]
[Pages 14016-14017]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-7398]
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DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-136-AD; Amendment 39-9554; AD 96-07-05]
Airworthiness Directives; Dornier Model 328-100 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 certain Dornier Model 328-100 series airplanes, that
requires installation of a reinforcement doubler on the rudder skin.
This amendment is prompted by the results of a design review of this
airplane model that revealed inadequate structural strength of the
attachment fitting of the rudder damper and of the adjacent structure.
The actions specified by this AD are intended to prevent failure of the
attachment structure of the rudder damper in the event of aerodynamic
gust loads, as the result of inadequate structural strength of the
subject structure.
DATES: Effective April 29, 1996.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of April 29, 1996.
ADDRESSES: The service information referenced in this AD may be
obtained from Dornier Luftfahrt 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 Office of the
Federal Register, 800 North Capitol Street NW., suite 700, Washington,
DC.
FOR FURTHER INFORMATION CONTACT: Gary Lium, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-1112; fax (206) 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 certain Dornier Model 328-100
series airplanes was published in the Federal Register on January 3,
1996 (61 FR 133). That action proposed to require installation of a
reinforcement doubler on the rudder skin.
Interested persons have been afforded an opportunity to participate
in the making of this amendment. Due consideration has been given to
the single comment received.
The commenter supports the proposed rule.
After careful review of the available data, including the comment
noted above, the FAA has determined that air safety and the public
interest require the adoption of the rule as proposed.
The FAA estimates that 12 airplanes of U.S. registry will be
affected by this AD, that it will take approximately 2 work hours 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 operators. Based on these figures, the cost
impact of the AD on U.S. operators is estimated to be $1,440, or $120
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 regulations adopted herein will not have substantial direct
effects 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, in accordance with Executive Order 12612, it is
determined that this final rule does not have sufficient federalism
implications to warrant the preparation of a Federalism Assessment.
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
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
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]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
96-07-05 Dornier: Amendment 39-9554. Docket 95-NM-136-AD.
Applicability: Model 328-100 series airplanes, serial numbers
3005 through 3024 inclusive; certificated in any category.
Note 1: 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
[[Page 14017]]
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 prevent failure of the attachment structure of the rudder
damper in the event of aerodynamic gust loads, accomplish the
following:
(a) Within 6 months after the effective date of this AD, install
a reinforcement doubler on the rudder skin in accordance with
Dornier Service Bulletin SB-328-27-063, Revision 1, dated January
26, 1995.
(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, Standardization Branch, ANM-113,
FAA, Transport Airplane Directorate. Operators shall submit their
requests through an appropriate FAA Principal Maintenance Inspector,
who may add comments and then send it to the Manager,
Standardization Branch, ANM-113.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(c) Special flight permits may be issued in accordance with
sections 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.
(d) The installation shall be done in accordance with Dornier
Service Bulletin SB-328-27-063, Revision 1, dated January 26, 1995.
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 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.
(e) This amendment becomes effective on April 29, 1996.
Issued in Renton, Washington, on March 21, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-7398 Filed 3-28-96; 8:45 am]
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