[Federal Register: October 11, 2007 (Volume 72, Number 196)]
[Proposed Rules]
[Page 57896-57898]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr11oc07-22]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2006-26490; Directorate Identifier 2006-CE-75-AD]
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: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD results from mandatory
continuing airworthiness information (MCAI) issued by an aviation
authority of
[[Page 57897]]
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 * * *
The proposed AD would require actions that are intended to address the
unsafe condition described in the MCAI.
DATES: We must receive comments on this proposed AD by November 13,
2007.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov.
Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
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 this proposed AD, 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.
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:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2006-
26490; Directorate Identifier 2006-CE-75-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD because of those comments.
We will post all comments we receive, without change, to http://www.regulations.gov
, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The Civil Aviation Authority (CAA), which is the airworthiness
authority for New Zealand, has issued AD DCA/R2000/28, dated September
28, 2006 (referred to after this as ``the MCAI''), 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.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Avions Pierre Robin (recent type certificate responsibility was
with APEX Aircraft and current responsibility with Alpha Aviation
Design Limited) has issued Service Bulletin No. 123, revision 2, dated
November 14, 1995; and Mandatory Service Bulletin No. 123, revision 3,
issued December 23, 1999.
The actions described in this service information are intended to
correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of the Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with this State of Design Authority, they
have notified us of the unsafe condition described in the MCAI and
service information referenced above. We are proposing this AD because
we evaluated all information and determined the unsafe condition exists
and is likely to exist or develop on other products of the same type
design.
Differences Between This Proposed 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 proposed different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
described in a separate paragraph of the proposed AD. These
requirements, if ultimately adopted, will take precedence over the
actions copied from the MCAI.
Costs of Compliance
We estimate that this proposed AD will affect 10 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 proposed 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 proposed AD to
the U.S. operators to be $25,260 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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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
[[Page 57898]]
responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the 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 proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 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. The FAA amends Sec. 39.13 by adding the following new AD:
Alpha Aviation Design Limited (Type Certificate No. A48EU previously
held by Apex Aircraft and Avions Pierre Robin): Docket No. FAA-2006-
26490; Directorate Identifier 2006-CE-75-AD.
Comments Due Date
(a) We must receive comments by November 13, 2007.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Model R2160 airplanes, serial numbers 001
through 378, certificated in any category.
Reason
(d) 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
(e) Unless already done, do the following actions:
(1) 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 the effective date of this AD,
whichever occurs later, and thereafter at intervals not to exceed
750 hours TIS, disassemble the wings from the fuselage and inspect
the wing structure and assembly components following instruction No.
1 in Robin Aviation Service Bulletin No. 123, revision 3, dated
December 23, 1999. If any defects are found, before further flight,
repair following Robin Aviation Service Bulletin No. 123, revision
3, dated December 23, 1999; and Avions Pierre Robin Service Bulletin
No. 123, revision 2, issued November 14, 1995.
(2) For airplanes with 4,000 hours TIS or more that do not have
the special instruction in paragraph E of Avions Pierre Robin
Service Bulletin No. 123, revision 2, dated November 14, 1995,
incorporated: Within the next 100 hours TIS after the effective date
of this AD and thereafter at intervals not to exceed 750 hours TIS,
disassemble the wings from the fuselage and inspect the wing
structure and assembly components following instruction No. 1 in
Robin Aviation Service Bulletin No. 123, revision 3, dated December
23, 1999. If any defects are found, before further flight, repair
following Robin Aviation Service Bulletin No. 123, revision 3, dated
December 23, 1999; and Avions Pierre Robin Service Bulletin No. 123,
revision 2, issued November 14, 1995.
(3) For airplanes with 4,000 hours TIS or more that have the
special instruction in paragraph E of Avions Pierre Robin Service
Bulletin No. 123, revision 2, dated November 14, 1995, incorporated:
Within the next 750 hours TIS after the effective date of this AD
and thereafter at intervals not to exceed 750 hours TIS, disassemble
the wings from the fuselage and inspect the wing structure and
assembly components following instruction No. 1 in Robin Aviation
Service Bulletin No. 123, revision 3, dated December 23, 1999. If
any defects are found, before further flight, repair following Robin
Aviation Service Bulletin No. 123, revision 3, dated December 23,
1999; and Avions Pierre Robin Service Bulletin No. 123, revision 2,
issued November 14, 1995.
(4) For all airplanes: When the airplane reaches a total of
3,500 hours TIS after installation of the wing-to-fuselage bolts or
within the next 100 hours TIS after 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.
(5) For all airplanes: 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: This AD differs from the MCAI and/or service information
as follows: No Differences.
Other FAA AD Provisions
(f) 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
(g) Refer to MCAI Civil Aviation Authority AD DCA/R2000/28,
dated September 28, 2006; Avions Pierre Robin Service Bulletin No.
123, revision 2, issued November 14, 1995; and Robin Aviation
Mandatory Service Bulletin No. 123, revision 3, issued December 23,
1999, for related information.
Issued in Kansas City, Missouri, on October 4, 2007.
David R. Showers,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E7-20047 Filed 10-10-07; 8:45 am]
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