[Federal Register: November 2, 2004 (Volume 69, Number 211)]
[Rules and Regulations]
[Page 63439-63440]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr02no04-1]
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Rules and Regulations
Federal Register
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[[Page 63439]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2004-18787; Directorate Identifier 2003-NM-264-AD;
Amendment 39-13837; AD 2004-22-09]
RIN 2120-AA64
Airworthiness Directives; Fokker Model F27 Mark 100, 200, 300,
400, 500, 600, and 700 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
Fokker Model F27 Mark 100, 200, 300, 400, 500, 600, and 700 series
airplanes. This AD requires a one-time high-frequency eddy current
inspection for cracking of the attachment lugs of the aileron spring
tab balance unit, and corrective actions if necessary. This AD is
prompted by a report indicating that, during heavy turbulence, a pilot
needed to apply aileron trim to maintain level flight because cracking
of the upper inboard attachment lug of the aileron spring tab balance
unit, probably due to corrosion, had caused permanent deflection of the
spring tab and consequent aileron damage. We are issuing this AD to
prevent diminished control of the airplane in turbulence or total loss
of roll control for the affected wing.
DATES: This AD becomes effective December 7, 2004.
The incorporation by reference of certain publications listed in
the AD is approved by the Director of the Federal Register as of
December 7, 2004.
ADDRESSES: For service information identified in this AD, contact
Fokker Services B.V., P.O. Box 231, 2150 AE Nieuw-Vennep, The
Netherlands. You can examine this information 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
.
You can examine the contents of this AD docket on the Internet at
http://dms.dot.gov, or in person at the Docket Management Facility,
U.S. Department of Transportation, 400 Seventh Street, SW., Room PL-
401, on the plaza level of the Nassif Building, Washington, DC.
FOR FURTHER INFORMATION CONTACT:
Technical information: Tom Rodriguez, Aerospace Engineer;
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425)
227-1137; fax (425) 227-1149.
Plain language information: Marcia Walters, marcia.walters@faa.gov.
Examining the Docket
The AD docket contains the proposed AD, comments, and any final
disposition. You can examine the AD docket on the Internet at http://dms.dot.gov
, or in person at the Docket Management Facility office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the DOT
street address stated in the ADDRESSES section.
SUPPLEMENTARY INFORMATION: The FAA proposed to amend 14 CFR part 39
with an AD for all Fokker Model F27 Mark 100, 200, 300, 400, 500, 600,
and 700 series airplanes. The proposed AD was published in the Federal
Register on August 6, 2004 (69 FR 47806), to require a one-time high-
frequency eddy current inspection for cracking of the attachment lugs
of the aileron spring tab balance unit, and corrective actions if
necessary.
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.
Costs of Compliance
This AD will affect about 38 airplanes of U.S. registry. The
actions will take about 5 work hours per airplane, at an average labor
rate of $65 per work hour. Based on these figures, the estimated cost
of the AD for U.S. operators is $12,350, or $325 per airplane.
Regulatory Findings
We have determined that this AD will not have federalism
implications under Executive Order 13132. This AD 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.
For the reasons discussed above, I certify that this AD:
(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.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD. See the ADDRESSES section for a location to
examine the regulatory evaluation.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 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.
[[Page 63440]]
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive:
2004-22-09 Fokker Services B.V.: Amendment 39-13837. Docket No. FAA-
2004-18787; Directorate Identifier 2003-NM-264-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective December
7, 2004.
Affected ADs
(b) None.
Applicability
(c) This AD applies to all Fokker Model F27 Mark 100, 200, 300,
400, 500, 600, and 700 series airplanes; certificated in any
category.
Unsafe Condition
(d) This AD was prompted by a report indicating that, during
heavy turbulence, a pilot needed to apply aileron trim to maintain
level flight because cracking of the upper inboard attachment lug of
the aileron spring tab balance unit, probably due to corrosion, had
caused permanent deflection of the spring tab and consequent aileron
damage. We are issuing this AD to prevent diminished control of the
airplane in turbulence or total loss of roll control for the
affected wing.
Compliance
(e) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Inspection
(f) Within 24 months after the effective date of this AD,
perform a one-time high-frequency eddy current inspection for
cracking of the attachment lugs of the aileron spring tab balance
units by doing all the actions in the Accomplishment Instructions of
Fokker Service Bulletin F27/27-137, dated March 19, 2003. If no
loose paint, corrosion damage, or crack is found during this
inspection, no further action is required by this AD.
Repair and Rework of Attachment Lugs
(g) If no crack is found during the inspection required by
paragraph (f) of this AD, but it was necessary to remove loose paint
or corrosion to perform the inspection: Prior to further flight,
rework the attachment lugs in accordance with the Accomplishment
Instructions of Fokker Service Bulletin F27/27-137, dated March 19,
2003. If corrosion damage has caused any attachment lug to exceed
the dimensional limits specified in the service bulletin: Prior to
further flight, replace the aileron spring tab balance unit with a
serviceable unit, in accordance with the Accomplishment Instructions
of Fokker Service Bulletin F27/27-137, dated March 19, 2003, or
repair the lug in accordance with a method approved by the Manager,
International Branch, ANM-116, FAA, Transport Airplane Directorate;
or the Civil Aviation Authority--The Netherlands (CAA-NL) (or its
delegated agent).
Replacement
(h) If any crack is found during the inspection required by
paragraph (f) of this AD: Prior to further flight, replace the
aileron spring tab balance unit with a serviceable unit, in
accordance with the Accomplishment Instructions of Fokker Service
Bulletin F27/27-137, dated March 19, 2003.
No Reporting Requirement
(i) Although Fokker Service Bulletin F27/27-137, dated March 19,
2003, specifies to submit certain information to Fokker Services
B.V., this AD does not include such a requirement.
Alternative Methods of Compliance (AMOCs)
(j) The Manager, International Branch, ANM-116, has the
authority to approve AMOCs for this AD, if requested in accordance
with the procedures found in 14 CFR 39.19.
Related Information
(k) Dutch airworthiness directive 2003-037, dated March 31,
2003, also addresses the subject of this AD.
Material Incorporated by Reference
(l) You must use Fokker Service Bulletin F27/27-137, dated March
19, 2003, to perform the actions that are required by this AD,
unless the AD specifies otherwise. The Director of the Federal
Register approves the incorporation by reference of this document in
accordance with 5 U.S.C. 552(a) and 1 CFR part 51. For copies of the
service information, contact Fokker Services B.V., P.O. Box 231,
2150 AE Nieuw-Vennep, The Netherlands. For information on the
availability of this material at the National Archives and Records
Administration (NARA), call (202) 741-6030, or go to http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
You may view the AD docket at the Docket
Management Facility, U.S. Department of Transportation, 400 Seventh
Street SW., Room PL-401, Nassif Building, Washington, DC.
Issued in Renton, Washington, on October 19, 2004.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 04-24221 Filed 11-1-04; 8:45 am]
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