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/ 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
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 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS
Federal Register / Vol. 78, No. 44 / Wednesday, March 6, 2013 / Proposed Rules 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 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. 


TKELLEY on DSK3SPTVN1PROD with PROPOSALS