Airworthiness Directives; Slingsby Aviation Ltd. Airplanes, 69785-69787 [2013-27919]

Download as PDF Federal Register / Vol. 78, No. 225 / Thursday, November 21, 2013 / Proposed Rules Therefore, this proposed rule is categorically excluded from further NEPA review. ICE seeks any comments or information that may lead to the discovery of any significant environmental effects from this proposed rule. List of Subjects in 8 CFR Part 214 Administrative practice and procedure, Aliens, Cultural exchange programs, Employment, Foreign officials, Health professions, Reporting and recordkeeping requirements, Students. For the reasons discussed in the preamble, DHS proposes to amend Chapter I of Title 8 of the Code of Federal Regulations as follows: PART 214 — NONIMMIGRANT CLASSES 1. The authority citation for part 214 continues to read as follows: ■ Authority: 8 U.S.C. 1101, 1102, 1103, 1182, 1184, 1186a, 1187, 1221, 1281, 1282, 1301–1305 and 1372; sec.643, Pub. L. 104– 208, 110 Stat. 3009–708; Pub. L. 106–386, 114 Stat. 1477–1480; section 141 of the Compacts of Free Association with the Federated States of Micronesia and the Republic of the Marshall Islands, and with the Government of Palau, 48 U.S.C. 1901 note, and 1931 note, respectively; 48 U.S.C. 1806; 8 CFR part 2. 2. In § 214.2 revise paragraph (f)(15)(ii) and paragraph (m)(17)(ii) to read as follows: ■ § 214.2 Special requirements for admission, extension, and maintenance of status. wreier-aviles on DSK5TPTVN1PROD with PROPOSALS * * * * * (f) * * * (15) * * * (i) * * * (ii) Study. (A) F–2 post-secondary/vocational study. (1) Authorized Study at SEVPCertified Schools. An F–2 spouse or F– 2 child may enroll in less than a full course of study, as defined in 8 CFR 214.2(f)(6)(i)(A)–(D) and 8 CFR 214.2(m)(9)(i)–(iv), in any course of study described in 8 CFR 214.2(f)(6)(i)(A)–(D) or 214.2(m)(9)(i)– (iv) at an SEVP-certified school. Notwithstanding 8 CFR 214.2(f)(6)(i)(B) and 8 CFR 214.2(m)(9)(i), study at an undergraduate college or university or at a community college or junior college is not a full course of study solely because the F–2 nonimmigrant is engaging in a lesser course load to complete a course of study during the current term. An F– 2 spouse or F–2 child enrolled in less than a full course of study is not eligible VerDate Mar<15>2010 14:11 Nov 20, 2013 Jkt 232001 to engage in employment pursuant to paragraphs (9) and (10) of this subsection. (2) Full Course of Study. Subject to paragraph (f)(15)(ii)(B) and (18), an F–2 spouse and child may engage in a full course of study only by applying for and obtaining a change of status to F–1, M– 1 or J–1 nonimmigrant status, as appropriate, before beginning a full course of study. However, an F–2 spouse and child may engage in study that is avocational or recreational in nature, up to and including on a fulltime basis. (B) F–2 elementary or secondary study. An F–2 child may engage in fulltime study, including any full course of study, in any elementary or secondary school (kindergarten through twelfth grade). (C) An F–2 spouse and child violates his or her nonimmigrant status by enrolling in any study except as provided in paragraph (f)(15)(ii)(A)(2) or (B) of this section. * * * * * (m) * * * (17) * * * (i) * * * (ii) Study. (A) M–2 post-secondary/vocational study. (1) Authorized Study at SEVPCertified Schools. An M–2 spouse or M– 2 child may enroll in less than a full course of study, as defined in 8 CFR 214.2(f)(6)(i)(A)–(D) or 214.2(m)(9)(i)– (v), in any course of study described in 8 CFR 214.2(m)(9)(i)–(v) at an SEVPcertified school. Notwithstanding 8 CFR 214.2(f)(6)(i)(B) and 8 CFR 214.2(m)(9)(i), study at an undergraduate college or university or at a community college or junior college is not a full course of study solely because the M–2 nonimmigrant is engaging in a lesser course load to complete a course of study during the current term. An M– 2 spouse or M–2 child enrolled in less than a full course of study is not eligible to engage in employment pursuant to paragraph (14) of this subsection. (2) Full Course of Study. Subject to paragraph (m)(17)(ii)(B), an M–2 spouse and child may engage in a full course of study only by applying for and obtaining a change of status to F–1, M– 1, or J–1 status, as appropriate, before beginning a full course of study. However, an M–2 spouse and M–2 child may engage in study that is avocational or recreational in nature, up to and including on a full-time basis. (B) M–2 elementary or secondary study. An M–2 child may engage in fulltime study, including any full course of study, in any elementary or secondary PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 69785 school (kindergarten through twelfth grade). (C) An M–2 spouse or child violates his or her nonimmigrant status by enrolling in any study except as provided in paragraph (m)(17)(ii)(A) or (B) of this section. * * * * * ■ 3. Revise section 214.3 paragraph (l)(1)(iii) to read as follows: § 214.3 Approval of schools for enrollment of F and M nonimmigrants. (l) * * * (1) * * * (i) * * * (ii) * * * (iii) School officials may nominate as many DSOs in addition to PDSOs as they determine necessary to adequately provide recommendations to F and/or M students enrolled at the school regarding maintenance of nonimmigrant status and to support timely and complete recordkeeping and reporting to DHS, as required by this section. School officials must not permit a DSO or PDSO nominee access to SEVIS until DHS approves the nomination. * * * * * Rand Beers, Acting Secretary of Homeland Security. [FR Doc. 2013–27898 Filed 11–20–13; 8:45 am] BILLING CODE 9111–28–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0997; Directorate Identifier 2013–CE–044–AD] RIN 2120–AA64 Airworthiness Directives; Slingsby Aviation Ltd. Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for Slingsby Aviation Ltd. Model T67M260 airplanes. 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 cracked horizontal stabilizer attachment brackets, which could lead to separation of the SUMMARY: E:\FR\FM\21NOP1.SGM 21NOP1 69786 Federal Register / Vol. 78, No. 225 / Thursday, November 21, 2013 / Proposed Rules horizontal stabilizer and result in loss of control. 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 January 6, 2014. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://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, Ings Lane, Kirbymoorside, York, YO62 6EZ, United Kingdom, telephone: +44 (0) 1751 432474; fax +44 (0) 1751 433016, Internet: www.marshall-slingsby.com. You may review this 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. wreier-aviles on DSK5TPTVN1PROD with PROPOSALS Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating it in Docket No. FAA– 2013–0997; 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: Mike Kiesov, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4144; fax: (816) 329–4090; email: mike.kiesov@faa.gov. 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 VerDate Mar<15>2010 14:11 Nov 20, 2013 Jkt 232001 ADDRESSES section. Include ‘‘Docket No. FAA–2013–0997; Directorate Identifier 2013–CE–044–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 https:// 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 European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued AD No. 2012– 0169, dated August 31, 2012 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: Several cases have been reported of cracked horizontal stabiliser attachment brackets on Slingsby T67 aeroplanes. This condition, if not detected and corrected, could lead to separation of the horizontal stabiliser and consequent loss of control of the aeroplane. Prompted by these reports, Slingsby issued Service Bulletin (SB) 179 to provide instructions for repetitive inspections. The CAA UK, the State of Design authority at the time, issued AD 001–12–2002,which was later superseded by AD G–2005–0004 (EASA approval 2005–564) to require repetitive inspections and, depending on findings, replacement of the affected brackets. Since that AD was issued, Slingsby published SB 179 issue 4, which removed the Model T67M260–T3A from the Applicability (all aeroplanes of this Model are confirmed to have been scrapped) and clarified that replacement of the affected aluminum brackets with titanium brackets (Slingsby Modification M988A or B) constitutes terminating action for the repetitive inspections. For the reasons described above, this AD retains the requirements of CAA UK AD G– 2005–0004, which is superseded, removes the Model T67M260–T3A from the Applicability and confirms that installing titanium brackets constitutes terminating action for the repetitive inspection requirements of this AD. You may examine the MCAI on the Internet at https://www.regulations.gov by searching for and locating it in Docket No. FAA–2013–0997. Relevant Service Information Slingsby Advanced Composites Ltd. has issued Service Bulletin No. 179, Issue 4, dated March 15, 2007. The PO 00000 Frm 00009 Fmt 4702 Sfmt 4702 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 11 products of U.S. registry. We also estimate that it would take about 2 work-hours per product to comply with the basic inspection of the aluminum horizontal stabilizer attachment brackets requirement of this proposed AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of the proposed AD on U.S. operators to be $1,870, or $170 per product. In addition, we estimate that any necessary follow-on actions would take about 8 work-hours and require parts costing $7,250 (for all four titanium horizontal stabilizer attachment brackets), for a cost of $7,930 per product, or parts costing $9,557 (for all four aluminum horizontal stabilizer attachment brackets), for a cost of $10,237. We have no way of determining the number of products that may need these actions. 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 E:\FR\FM\21NOP1.SGM 21NOP1 Federal Register / Vol. 78, No. 225 / Thursday, November 21, 2013 / Proposed Rules 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 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ Slingsby Aviation Ltd.: Docket No. FAA– 2013–0997; Directorate Identifier 2013– CE–044–AD. wreier-aviles on DSK5TPTVN1PROD with PROPOSALS (a) Comments Due Date We must receive comments by January 6, 2014. (b) Affected ADs None. (c) Applicability This AD applies to Slingsby Aviation Ltd. Model T67M260 airplanes, all serial numbers, certificated in any category. (d) Subject Air Transport Association of America (ATA) Code 55: Stabilizers. VerDate Mar<15>2010 14:11 Nov 20, 2013 Jkt 232001 (e) Reason This AD was prompted by 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 cracked horizontal stabilizer attachment brackets. We are issuing this AD to prevent separation of the horizontal stabilizer, which could result in loss of control. (f) Actions and Compliance Unless already done, do the actions specified in paragraphs (f)(1) through (f)(4) of this AD: (1) Within the next 150 hours time-inservice (TIS) after the effective date of this AD or at the next annual inspection after the effective date of this AD, whichever occurs later, and repetitively thereafter at intervals not to exceed 150 hours TIS, inspect the aluminum horizontal stabilizer attachment brackets for cracks. Do the inspections following the ACTION instructions in Slingsby Advanced Composites Ltd. Service Bulletin S.B. No: 179, Issue 4, dated March 15, 2007. (2) If, during any inspection required in paragraph (f)(1) of this AD, any cracks are found, before further flight, replace the cracked bracket with a serviceable part. Do the replacement following the ACTION instructions in Slingsby Advanced Composites Ltd. Service Bulletin S.B. No: 179, Issue 4, dated March 15, 2007. If a serviceable aluminum horizontal stabilizer attachment bracket is used as a replacement part, repetitively inspect as specified in paragraph (f)(1) of this AD. (3) To terminate the repetitive inspections required in paragraph (f)(1) of this AD, all four aluminum horizontal stabilizer attachment brackets must be replaced with titanium horizontal stabilizer attachment brackets. (4) After installing titanium horizontal stabilizer attachment brackets, installing aluminum horizontal stabilizer attachment brackets are prohibited. (g) 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: Mike Kiesov, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4144; fax: (816) 329– 4090; email: mike.kiesov@faa.gov. 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 PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 69787 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. (h) Related Information Refer to European Aviation Safety Agency (EASA) AD No. 2012–0169, dated August 31, 2012, for related information. You may examine the MCAI on the Internet at https://www.regulations.gov by searching for and locating it in Docket No. FAA–2013– 0997. For service information related to this AD, contact Slingsby Advanced Composites, Ings Lane, Kirbymoorside, York, YO62 6EZ, United Kingdom, telephone: +44 (0) 1751 432474; fax +44 (0) 1751 433016, Internet: www.marshall-slingsby.com. You may review this 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 November 15, 2013. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service. [FR Doc. 2013–27919 Filed 11–20–13; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2013–0921; Airspace Docket No. 13–AAL–4] Proposed Modification of Class E Airspace; Sitka, AK Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Notice of proposed rulemaking (NPRM). AGENCY: This action proposes to modify Class E airspace at Sitka, AK, to SUMMARY: E:\FR\FM\21NOP1.SGM 21NOP1

Agencies

[Federal Register Volume 78, Number 225 (Thursday, November 21, 2013)]
[Proposed Rules]
[Pages 69785-69787]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-27919]


=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0997; Directorate Identifier 2013-CE-044-AD]
RIN 2120-AA64


Airworthiness Directives; Slingsby Aviation Ltd. Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
Slingsby Aviation Ltd. Model T67M260 airplanes. 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 cracked horizontal stabilizer attachment 
brackets, which could lead to separation of the

[[Page 69786]]

horizontal stabilizer and result in loss of control. 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 January 6, 2014.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://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, Ings Lane, Kirbymoorside, York, YO62 6EZ, 
United Kingdom, telephone: +44 (0) 1751 432474; fax +44 (0) 1751 
433016, Internet: www.marshall-slingsby.com. You may review this 
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 https://www.regulations.gov by searching for and locating it in Docket No. FAA-
2013-0997; 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: Mike Kiesov, Aerospace Engineer, FAA, 
Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 
64106; telephone: (816) 329-4144; fax: (816) 329-4090; email: 
mike.kiesov@faa.gov.

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-2013-0997; 
Directorate Identifier 2013-CE-044-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 https://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 European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued AD 
No. 2012-0169, dated August 31, 2012 (referred to after this as ``the 
MCAI''), to correct an unsafe condition for the specified products. The 
MCAI states:

    Several cases have been reported of cracked horizontal 
stabiliser attachment brackets on Slingsby T67 aeroplanes.
    This condition, if not detected and corrected, could lead to 
separation of the horizontal stabiliser and consequent loss of 
control of the aeroplane.
    Prompted by these reports, Slingsby issued Service Bulletin (SB) 
179 to provide instructions for repetitive inspections. The CAA UK, 
the State of Design authority at the time, issued AD 001-12-
2002,which was later superseded by AD G-2005-0004 (EASA approval 
2005-564) to require repetitive inspections and, depending on 
findings, replacement of the affected brackets.
    Since that AD was issued, Slingsby published SB 179 issue 4, 
which removed the Model T67M260-T3A from the Applicability (all 
aeroplanes of this Model are confirmed to have been scrapped) and 
clarified that replacement of the affected aluminum brackets with 
titanium brackets (Slingsby Modification M988A or B) constitutes 
terminating action for the repetitive inspections.
    For the reasons described above, this AD retains the 
requirements of CAA UK AD G-2005-0004, which is superseded, removes 
the Model T67M260-T3A from the Applicability and confirms that 
installing titanium brackets constitutes terminating action for the 
repetitive inspection requirements of this AD.

    You may examine the MCAI on the Internet at https://www.regulations.gov by searching for and locating it in Docket No. FAA-
2013-0997.

Relevant Service Information

    Slingsby Advanced Composites Ltd. has issued Service Bulletin No. 
179, Issue 4, dated March 15, 2007. 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 11 products of U.S. 
registry. We also estimate that it would take about 2 work-hours per 
product to comply with the basic inspection of the aluminum horizontal 
stabilizer attachment brackets requirement of this proposed AD. The 
average labor rate is $85 per work-hour.
    Based on these figures, we estimate the cost of the proposed AD on 
U.S. operators to be $1,870, or $170 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 8 work-hours and require parts costing $7,250 (for all four 
titanium horizontal stabilizer attachment brackets), for a cost of 
$7,930 per product, or parts costing $9,557 (for all four aluminum 
horizontal stabilizer attachment brackets), for a cost of $10,237. We 
have no way of determining the number of products that may need these 
actions.

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

[[Page 69787]]

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 adding the following new AD:

Slingsby Aviation Ltd.: Docket No. FAA-2013-0997; Directorate 
Identifier 2013-CE-044-AD.

(a) Comments Due Date

    We must receive comments by January 6, 2014.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Slingsby Aviation Ltd. Model T67M260 
airplanes, all serial numbers, certificated in any category.

(d) Subject

    Air Transport Association of America (ATA) Code 55: Stabilizers.

(e) Reason

    This AD was prompted by 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 cracked 
horizontal stabilizer attachment brackets. We are issuing this AD to 
prevent separation of the horizontal stabilizer, which could result 
in loss of control.

(f) Actions and Compliance

    Unless already done, do the actions specified in paragraphs 
(f)(1) through (f)(4) of this AD:
    (1) Within the next 150 hours time-in-service (TIS) after the 
effective date of this AD or at the next annual inspection after the 
effective date of this AD, whichever occurs later, and repetitively 
thereafter at intervals not to exceed 150 hours TIS, inspect the 
aluminum horizontal stabilizer attachment brackets for cracks. Do 
the inspections following the ACTION instructions in Slingsby 
Advanced Composites Ltd. Service Bulletin S.B. No: 179, Issue 4, 
dated March 15, 2007.
    (2) If, during any inspection required in paragraph (f)(1) of 
this AD, any cracks are found, before further flight, replace the 
cracked bracket with a serviceable part. Do the replacement 
following the ACTION instructions in Slingsby Advanced Composites 
Ltd. Service Bulletin S.B. No: 179, Issue 4, dated March 15, 2007. 
If a serviceable aluminum horizontal stabilizer attachment bracket 
is used as a replacement part, repetitively inspect as specified in 
paragraph (f)(1) of this AD.
    (3) To terminate the repetitive inspections required in 
paragraph (f)(1) of this AD, all four aluminum horizontal stabilizer 
attachment brackets must be replaced with titanium horizontal 
stabilizer attachment brackets.
    (4) After installing titanium horizontal stabilizer attachment 
brackets, installing aluminum horizontal stabilizer attachment 
brackets are prohibited.

(g) 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: Mike Kiesov, Aerospace Engineer, FAA, Small 
Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 
64106; telephone: (816) 329-4144; fax: (816) 329-4090; email: 
mike.kiesov@faa.gov. 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, 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.

(h) Related Information

    Refer to European Aviation Safety Agency (EASA) AD No. 2012-
0169, dated August 31, 2012, for related information. You may 
examine the MCAI on the Internet at https://www.regulations.gov by 
searching for and locating it in Docket No. FAA-2013-0997. For 
service information related to this AD, contact Slingsby Advanced 
Composites, Ings Lane, Kirbymoorside, York, YO62 6EZ, United 
Kingdom, telephone: +44 (0) 1751 432474; fax +44 (0) 1751 433016, 
Internet: www.marshall-slingsby.com. You may review this 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 November 15, 2013.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2013-27919 Filed 11-20-13; 8:45 am]
BILLING CODE 4910-13-P

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