[Federal Register Volume 78, Number 44 (Wednesday, March 6, 2013)]
[Proposed Rules]
[Pages 14467-14469]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-05229]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0220; Directorate Identifier 2013-CE-002-AD]
RIN 2120-AA64
Airworthiness Directives; Slingsby Sailplanes Ltd. Sailplanes
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 all
Slingsby Sailplanes Ltd. Models Dart T.51, Dart T.51/17, and Dart T.51/
17R sailplanes equipped with aluminum alloy spar booms that would
supersede an existing AD. This proposed AD results from mandatory
continuing airworthiness information (MCAI) originated 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 an incident of glue joint failure on a starboard wing
caused by water entering the area of the airbrake box that resulted in
delamination and corrosion in the area of the aluminum alloy spar booms
and the wing attach fittings. We are issuing this proposed AD to
require actions to address the unsafe condition on these products.
DATES: We must receive comments on this proposed AD by April 22, 2013.
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.
For service information identified in this proposed AD, contact
Slingsby Advanced Composites Ltd., Ings Lane, Kirkbymoorside, North
Yorkshire, England YO62 6EZ; telephone: +44(0)1751 432474; Internet:
none. You may review copies of the referenced service information at
the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri
64106. For information on the availability of this material at the FAA,
call (816) 329-4148.
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: Jim Rutherford, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City,
Missouri 64106; telephone: (816) 329-4165; fax: (816) 329-4090; email:
[email protected].
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-2013-0220;
Directorate Identifier 2013-CE-002-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://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
On October 22, 1998, we issued AD 98-22-15, Amendment 39-10863 (63
FR 58624, November 2, 1998). That AD required actions intended to
address an unsafe condition on the products listed above.
Since we issued AD 98-22-15, Amendment 39-10863 (63 FR 58624,
November 2, 1998), Slingsby Aviation Ltd. has revised the related
service information to remove the 5-year repetitive ``cutout''
inspection and to add a repetitive annual inspection using an
endoscope. The endoscope inspection method would be done using existing
drain holes in the lower wing skin.
Using revised service information is mandatory within the United
Kingdom airworthiness system. It is not necessary for the Civil
Aviation Authority (CAA), which is the aviation authority for the
United Kingdom, to issue an AD to mandate the use of new service
information.
Proposing AD action is the only way the FAA can mandate the use of
new service information; however, owners/
[[Page 14468]]
operators may request approval from the FAA to use an alternative
method of compliance (AMOC).
Several U.S. operators have complained that the repetitive 5-year
``cutout'' inspection in the wooden wing skin, currently required by AD
98-22-15, Amendment 39-10863 (63 FR 58624, November 2, 1998), was by
default growing larger and larger with each inspection.
We have determined that the current 5-year repetitive ``cutout''
inspections will eventually weaken the wing structure and could result
in an unsafe condition. We concur with the change to the annual
endoscope inspection.
Relevant Service Information
Slingsby Aviation Ltd. has issued Technical Instruction T.I. No.
109/T51, Issue 3, dated August 21, 2000. 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.
Costs of Compliance
We estimate that this proposed AD will affect 10 products of U.S.
registry. We also estimate that it would take about 40 work-hours per
product to comply with the initial inspection requirement retained from
AD 98-22-15, Amendment 39-10863 (63 FR 58624, November 2, 1998) in this
proposed AD. The average labor rate is $85 per work-hour.
Based on these figures, we estimate the cost of the initial
inspection proposed in this AD on U.S. operators to be $34,000, or
$3,400 per product.
We also estimate that it would take about 2 work-hours per product
to comply with the new repetitive inspection requirement in this
proposed AD. The average labor rate is $85 per work-hour.
Based on these figures, we estimate the cost of the new repetitive
inspection proposed in this AD on U.S. operators to be $1,700, or $170
per product.
We have no way of determining the number of repetitive inspections
an owner/operator will incur over the life of the sailplane or the
number of sailplanes that will need repairs.
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 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),
(3) Will not affect intrastate aviation in Alaska, and
(4) 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, 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
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 removing Amendment 39-10863 (63 FR
58624, November 2, 1998), and adding the following new AD:
Slingsby Sailplanes Ltd.: Docket No. FAA-2013-0220; Directorate
Identifier 2013-CE-002-AD.
(a) Comments Due Date
We must receive comments by April 22, 2013.
(b) Affected ADs
This AD supersedes AD 98-22-15, Amendment 39-10863 (63 FR 58624,
November 2, 1998).
(c) Applicability
This AD applies to Slingsby Sailplanes Ltd. Models Dart T.51,
Dart T.51/17, and Dart T.51/17R sailplanes, that are:
(1) Equipped with aluminum alloy spar booms; and
(2) Certificated in any category.
(d) Subject
Air Transport Association of America (ATA) Code 57: Wing.
(e) Reason
This AD was prompted by an incident of glue joint failure on a
starboard wing caused by water entering the area of the airbrake box
that resulted in delamination and corrosion in the area of the
aluminum alloy spar booms and the wing attach fittings. The
manufacturer has also issued revised service information that
changes the repetitive inspection interval and method. We are
issuing this AD to prevent failure of the spar assembly and
adjoining structure, which could result in reduced controllability
or complete loss of control.
(f) Actions and Compliance Retained From AD 98-22-15, Amendment 39-
10863 (63 FR 58624, November 2, 1998)
Unless already done, do the following actions:
(1) Within the next 6 calendar months after December 14, 1998
(the effective date retained from AD 98-22-15, Amendment 39-10863
(63 FR 58624, November 2, 1998)), inspect the aluminum alloy spar
booms and the wing attach fittings for delamination or corrosion
damage following the ACTION section of Slingsby Aviation Ltd.
Technical Instruction T.I. No. 109/T51, Issue No. 2, dated October
7, 1997, or the ACTION section of Slingsby Aviation Ltd. Technical
Instruction T.I. No. 109/T51, Issue 3, dated August 21, 2000.
Note to paragraph (f)(1) of this AD: Slingsby Aviation Ltd.
Technical Instruction T.I. No. 109/T51, Issue No. 2, dated October
7, 1997, and T.I. No. 109/T51, Issue 3, dated August 21, 2000,
include guidance to
[[Page 14469]]
determine whether an affected sailplane is equipped with aluminum
alloy spar booms.
(2) If any corrosion or delamination damage is found during the
inspection required by paragraph (f)(1) of this AD, before further
flight, contact the manufacturer at the address specified in
paragraph (i) of this AD to obtain an FAA-approved repair scheme and
incorporate the repair.
(g) New Actions and Compliance
(1) Within 5 years after the last inspection required by AD 98-
22-15, Amendment 39-10863 (63 FR 58624, November 2, 1998) and
repetitively thereafter at intervals not to exceed 12 months, using
an endoscope, inspect the aluminum alloy spar booms and the wing
attach fittings for delamination or corrosion damage following
paragraph 11. of the ACTION section of Slingsby Aviation Ltd.
Technical Instruction T.I. No. 109/T51, Issue 3, dated August 21,
2000.
(2) If any corrosion or delamination damage is found during any
inspection required by paragraph (g)(1) of this AD, before further
flight, contact the manufacturer at the address specified in
paragraph (i) of this AD to obtain an FAA-approved repair scheme and
incorporate the repair.
(h) Other FAA AD Provisions
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: Jim Rutherford, Aerospace Engineer, FAA, Small
Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329-4165; fax: (816) 329-4090; email:
[email protected]. Before using any approved AMOC on any
sailplane 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, a federal agency may not conduct or sponsor, and a person
is not required to respond to, nor shall a person be subject to a
penalty for failure to comply with a collection of information
subject to the requirements of the Paperwork Reduction Act unless
that collection of information displays a current valid OMB Control
Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is
estimated to be approximately 5 minutes per response, including the
time for reviewing instructions, completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Comments concerning the accuracy of this
burden and suggestions for reducing the burden should be directed to
the FAA at: 800 Independence Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer, AES-200.
(i) Related Information
Refer to Civil Aviation Authority (CAA) AD British AD 005-09-97,
dated October 3, 1997; Slingsby Aviation Ltd. Technical Instruction
T.I. No. 109/T51, Issue No. 2, dated October 7, 1997; and Slingsby
Aviation Ltd. Technical Instruction T.I. No. 109/T51, Issue 3, dated
August 21, 2000, for related information. For service information
related to this AD, contact Slingsby Advanced Composites Ltd., Ings
Lane, Kirkbymoorside, North Yorkshire, England YO62 6EZ ; telephone:
+44(0)1751 432474; Internet: none. You may review copies of the
referenced service information at the FAA, Small Airplane
Directorate, 901 Locust, Kansas City, Missouri 64106. For
information on the availability of this material at the FAA, call
(816) 329-4148.
Issued in Kansas City, Missouri, on February 27, 2013.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2013-05229 Filed 3-5-13; 8:45 am]
BILLING CODE 4910-13-P