This section of the FEDERAL REGISTER contains notices to the public of the proposed issuance of rules and regulations. The purpose of these notices is to give interested persons an opportunity to participate in the rule making prior to the adoption of the final rules. 

# Proposed Rules Federal Register 

### 14467

Vol. 78, No. 44

Wednesday, March 6, 2013

**DEPARTMENT OF ENERGY**

**10 CFR Part 430**

**[Docket No. EERE–2011–BT–STD–0006]**

**RIN 1904–AC43**

**Energy Conservation Program: Availability of the Preliminary**  **Technical Support Document for General Service Fluorescent Lamps**  **and Incandescent Reflector Lamps**

Correction

In proposed rule document 2013– 04711, appearing on pages 13563–13566 in the issue of Thursday, February 28, 2013, make the following correction:

On page 13563, in the second column, in the sixth paragraph, on the first and second lines, ‘‘ GSFL-IRL

_2011-STD0006@ee.doe.gov’’ should read ‘‘ GSFLIRL

_2011-STD-0006@ee.doe.gov’’. [FR Doc. C1–2013–04711 Filed 3–5–13; 8:45 am]

**BILLING CODE 1505–01–D**

**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).

**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: jim.rutherford@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–2013–0220; 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/


### 14468 Federal Register / Vol. 78, No. 44 / Wednesday, March 6, 2013 / Proposed Rules

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** 

■ 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 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


### 14469 Federal Register / Vol. 78, No. 44 / Wednesday, March 6, 2013 / Proposed Rules

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 inparagraph (i) of this AD to obtain an FAAapproved 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: jim.rutherford@faa.gov. 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**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0097; Directorate Identifier 2011–NM–243–AD]** 

**RIN 2120–AA64**

**Airworthiness Directives; The Boeing Company Airplanes** 

**AGENCY :**  Federal Aviation Administration (FAA), DOT.

**ACTION :**  Notice of proposed rulemaking (NPRM).

**SUMMARY :**  We propose to supersede an existing airworthiness directive (AD) that applies to certain The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747–400, 747– 400D, 747–400F, and 747SR series airplanes. The existing AD currently requires repetitive inspections to find cracking of the web, strap, inner chords, inner chord angle of the forward edge frame of the number 5 main entry door cutouts, the frame segment between stringers 16 and 31, and repair if necessary; and repetitive inspections for cracking of repairs. Since we issued that AD, we have received multiple reports of cracking outside of the previous fuselage inspection areas and a report of a crack that initiated at the aft edge of the inner chord rather than initiating at a fastener location, which was the previous cracking location. This proposed AD would expand the previous fuselage areas that are inspected for cracking. We are proposing this AD to detect and correct such cracks, which could cause damage to the adjacent body structure and could result in depressurization of the airplane in flight.

**DATES :**  We must receive comments on this proposed AD by April 22, 2013.

**ADDRESSES :**  You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, 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: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.

For service information identified in this proposed AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, WA 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https:// www.myboeingfleet.com. You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221. 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 (phone: 800–647–5527) is in the

**ADDRESSES** section. Comments will be available in the AD docket shortly after receipt.

**FOR FURTHER INFORMATION CONTACT :**  Nathan Weigand, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6428; fax: 425–917–6590; email: Nathan.P.Weigand@faa.gov.