[Federal Register: April 22, 2008 (Volume 73, Number 78)]
[Rules and Regulations]
[Page 21519-21520]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr22ap08-1]
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Rules and Regulations
Federal Register
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[[Page 21519]]
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-26490; Directorate Identifier 2006-CE-075-AD;
Amendment 39-15481; AD 2008-09-01]
RIN 2120-AA64
Airworthiness Directives; Alpha Aviation Design Limited (Type
Certificate No. A48EU Previously Held by APEX Aircraft and AVIONS
PIERRE ROBIN) Model R2160 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above. This AD results from mandatory continuing
airworthiness information (MCAI) issued by an aviation authority of
another country to identify and correct an unsafe condition on an
aviation product. The MCAI describes the unsafe condition as:
To prevent failure of the wing structure and assembly components
due to undetected fatigue and corrosion * * *
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective May 27, 2008.
On May 27, 2008, the Director of the Federal Register approved the
incorporation by reference of certain publications listed in this AD.
ADDRESSES: You may examine the AD docket on the Internet at http://
www.regulations.gov or in person at Document Management Facility, U.S.
Department of Transportation, Docket Operations, M-30, West Building
Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC
20590.
FOR FURTHER INFORMATION CONTACT: Karl Schletzbaum, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4146; fax: (816) 329-4090.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a supplemental notice of proposed rulemaking (NPRM) to
amend 14 CFR part 39 to include an AD that would apply to the specified
products. That NPRM was published in the Federal Register on February
5, 2008 (73 FR 6634). That NPRM proposed to correct an unsafe condition
for the specified products. The MCAI states:
To prevent failure of the wing structure and assembly components
due to undetected fatigue and corrosion * * *
The MCAI requires that you inspect the wing structure and fuselage
attachment and repair any defects that you find.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting the AD as proposed.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a NOTE within the AD.
Costs of Compliance
Based on the service information, we estimate that this AD will
affect 9 products of U.S. registry. We also estimate that it will take
about 15 work-hours per product to comply with basic requirements of
this AD. The average labor rate is $80 per work-hour. Required parts
will cost about $1,326 per product.
Based on these figures, we estimate the cost of this AD to the U.S.
operators to be $22,734 or $2,526 per product.
We have no way to determine what aircraft will need replacement
parts that may be required based on the results of any inspection.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We 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 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.
[[Page 21520]]
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD Docket.
Examining the AD Docket
You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains the NPRM, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Office (telephone (800) 647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
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.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new AD:
2008-09-01 Alpha Aviation Design Limited (Type Certificate No. A48EU
previously held by APEX Aircraft and AVIONS PIERRE ROBIN): Amendment
39-15481; Docket No. FAA-2006-26490; Directorate Identifier 2006-CE-
075-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective May 27,
2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Model R2160 airplanes, serial numbers 001
through 378, certificated in any category.
Subject
(d) Air Transport Association of America (ATA) Code: 57: Wings.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
To prevent failure of the wing structure and assembly components
due to undetected fatigue and corrosion * * *
The MCAI requires that you inspect the wing structure and fuselage
attachment and repair any defects that you find.
Actions and Compliance
(f) Unless already done, do the following actions:
(1) Disassemble the wings from the fuselage and inspect the wing
structure and assembly components using instruction No. 1 in Robin
Aviation Service Bulletin No. 123, revision 3, dated December 23,
1999. If any defects are found, repair following Robin Aviation
Service Bulletin No. 123, revision 3, dated December 23, 1999. Use
the following compliance times for the inspection:
(i) For airplanes with less than 4,000 hours time-in-service
(TIS): When the airplane reaches a total of 3,500 hours TIS or
within the next 100 hours TIS after May 27, 2008 (the effective date
of this AD), whichever occurs later, and thereafter at intervals not
to exceed 750 hours TIS.
(ii) For airplanes with 4,000 hours TIS or more that have not
complied with the special instruction in paragraph E of Avions
Pierre Robin Service Bulletin No. 123, revision 2, dated November
14, 1995: Within the next 100 hours TIS after May 27, 2008 (the
effective date of this AD) and thereafter at intervals not to exceed
750 hours TIS.
(iii) For airplanes with 4,000 hours TIS or more that have
complied with the special instruction in paragraph E of Avions
Pierre Robin Service Bulletin No. 123, revision 2, dated November
14, 1995: Within the next 750 hours TIS after May 27, 2008 (the
effective date of this AD) and thereafter at intervals not to exceed
750 hours TIS.
(2) When the airplane reaches a total of 3,500 hours TIS with
original wing-to-fuselage bolts installed or 3,500 hours TIS of an
airplane since new bolts have been installed or within the next 100
hours TIS after May 27, 2008 (the effective date of this AD),
whichever occurs later, do a non-destructive inspection of the wing-
to-fuselage retaining bolts and replace any bolts that do not pass
this inspection following instruction No. 2 in Robin Aviation
Service Bulletin No. 123, revision 3, dated December 23, 1999.
Thereafter, repetitively inspect wing-to-fuselage retaining bolts
and replace any bolts that do not pass this inspection every 750
hours TIS following instruction No. 2 in Robin Aviation Service
Bulletin No. 123, revision 3, dated December 23, 1999.
Note 1: The requirement for a 3,500-hour inspection is a time
since new or time since installation (that is, the TIS of new
bolts).
(3) Within the next 50 hours TIS after re-assembling the wing
and thereafter at intervals not to exceed 100 hours TIS, inspect the
wing-to-fuselage retaining bolts for correct torque settings
following instruction No. 3 in Robin Aviation Service Bulletin No.
123, revision 3, dated December 23, 1999. The required torque value
is 22 ft-lb with nut part number 95.24.39.010. Tighten to 16 ft-lb
(pre-loading) and then torque from 16 to 22 ft-lb.
FAA AD Differences
Note 2: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
Standards Office, FAA, has the authority to approve AMOCs for this
AD, if requested using the procedures found in 14 CFR 39.19. Send
information to ATTN: Karl Schletzbaum, Aerospace Engineer, FAA,
Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4146; fax: (816) 329-4090.
Before using any approved AMOC on any airplane to which the AMOC
applies, notify your appropriate principal inspector (PI) in the FAA
Flight Standards District Office (FSDO), or lacking a PI, your local
FSDO.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(h) Refer to MCAI Civil Aviation Authority AD DCA/R2000/28,
dated September 28, 2006, and Robin Aviation Mandatory Service
Bulletin No. 123, revision 3, dated December 23, 1999, for related
information.
Material Incorporated by Reference
(i) You must use Robin Aviation Mandatory Service Bulletin No.
123, revision 3, dated December 23, 1999, to do the actions required
by this AD, unless the AD specifies otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of this service information under 5
U.S.C. 552(a) and 1 CFR part 51.
(2) For service information identified in this AD, contact Alpha
Aviation, Ingram Road, Hamilton Airport, RD 2, Hamilton 2021, New
Zealand; telephone: 011 64 7 843 7070; fax: 011 64 7 843 8040;
Internet: http://www.alphaaviation.co.nz.
(3) You may review copies at the FAA, Central Region, Office of
the Regional Counsel, 901 Locust, Room 506, Kansas City, Missouri
64106; 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/cfr/ibr-locations.html.
Issued in Kansas City, Missouri, on April 11, 2008.
James E. Jackson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-8509 Filed 4-21-08; 8:45 am]
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